Base station for unmanned aerial vehicles (UAV)

Abstract

A base station for an unmanned aerial vehicle (UAV) is disclosed. The base station includes: a housing; a sliding mechanism connected to the housing and repositionable between a retracted position and an extended position; a cradle connected to the sliding mechanism and configured to dock with the UAV such that the UAV is movable in and out of the housing during repositioning of the sliding mechanism between the retracted position and the extended position; and a charging hub connected to the sliding mechanism and configured to be electrically connected to a power source of the UAV for charging the power source.

Description

[Technical field]

[0001] The present disclosure relates to a base station (dock) for unmanned aerial vehicles (UAVs) (e.g., drones). More specifically, the present disclosure relates to a base station that includes a set of integrated systems that enable automated servicing (e.g., docking, storage, charging, operation, etc.) and housing of UAVs. [Background technology]

[0002] Known base stations for UAVs are often large, mechanically complex, and expensive. The present disclosure addresses these deficiencies, among other things, and provides a base station that achieves a significant reduction in size that allows for improved maintenance of UAVs and more efficient operation and significant cost savings. Summary of the Invention [Means for solving the problem]

[0003] In one aspect of the disclosure, a base station configured for use with an unmanned aerial vehicle (UAV) is disclosed. The base station includes: a housing; a cradle configured to receive the UAV during docking to facilitate charging of the UAV's power source; and a temperature control system connected to the cradle and configured to vary a temperature of the UAV's power source. The cradle is movable between a retracted position in which the cradle is positioned within the housing and an extended position in which the cradle is positioned outside the housing to facilitate docking with the UAV. The temperature control system includes: a thermoelectric conditioner (TEC) having a first end and a second end; a first air circuit thermally connected to the TEC and configured to regulate a temperature of the TEC; and a second air circuit thermally connected to the TEC such that the TEC is located between the first air circuit and the second air circuit. When docked with the base station, the second air circuit is configured to direct air across the cradle, thereby heating or cooling the UAV's power source. In an embodiment, the temperature control system may be configured to cool the UAV's power supply (e.g., when the base station and UAV are used in a hot environment) or to heat the UAV's power supply (e.g., when the base station and UAV are used in a cold environment). In an embodiment, the first air circuit may be configured as an open system and the second air circuit may be configured as a closed system. In an embodiment, the TEC may be configured as a Peltier system. In an embodiment, the first air circuit may include: a first plenum; a first heat sink connected to the first plenum and a first end of the TEC; and a first air circulator configured to direct air through the first plenum and across the first heat sink to change the air temperature in the first air circuit, thereby regulating the temperature of the TEC.In an embodiment, the second air circuit may include: a second plenum; a second heat sink connected to the second plenum and the second end of the TEC; and a second air circulator configured to direct air through the second plenum and across the second heat sink when docked with the base station to vary the air temperature in the second air circuit and thereby heat or cool the power source of the UAV. In an embodiment, the temperature control system may be configured to cool the power source of the UAV when docked with the base station. In an embodiment, the second plenum may define an air inlet and an air outlet. In an embodiment, the air inlet may be configured to direct air across the power source of the UAV into the cradle, and the air outlet may be configured to receive air directed across the power source of the UAV and redirect the air across the second heat sink. In an embodiment, the second plenum may include a first section and a second section that is movable relative to the first section. In an embodiment, the first section may be connected to the TEC and the second section may be connected to the cradle. In an embodiment, the first section and the second section may be configured for mating engagement when the cradle is moved to a retracted position. It is contemplated that the base station described above may include any combination of the features and elements described in this section.

[0004] In another aspect of the disclosure, a base station configured for use with a UAV is disclosed. The base station includes a temperature control system configured to vary a temperature of the UAV. The temperature control system includes: a thermoelectric conditioner (TEC); an open air circuit thermally connected to the TEC and configured to regulate a temperature of the TEC; and a closed air circuit thermally connected to the TEC such that the TEC is located between the open air circuit and the closed air circuit. When docked with the base station, the closed air circuit is configured to direct air across the UAV. In an embodiment, the temperature control system may be configured to heat or cool the UAV depending on environmental conditions. In an embodiment, the closed air circuit may include a first section and a second section that is movable relative to the first section. In an embodiment, the base station may further include a cradle configured to receive the UAV during docking to facilitate charging of the UAV. In an embodiment, the cradle may be extendable from the base station and retractable into the base station. In an embodiment, a first section of the closed air circuit may be connected to the TEC and a second section of the closed air circuit may be connected to the cradle. In an embodiment, the first section and the second section may be configured to matingly engage when the cradle is retracted into the base station. It is contemplated that the base station described above may include any combination of the features and elements described in this section.

[0005] In another aspect of the disclosure, a method for regulating a temperature of a power source in a UAV is disclosed. The method includes: docking the UAV in a cradle of a base station; retracting the cradle into the base station; and directing thermally conditioned air across a power source of the UAV via an air circuit connected to the cradle. In an embodiment, the method may further include directing the air across a heat sink thermally connected to a thermoelectric conditioner (TEC) for treatment prior to directing the air across the power source of the UAV. In an embodiment, directing the air across the heat sink may include circulating the air through a plenum connected to the heat sink. In an embodiment, retracting the cradle into the base station may include closing the air circuit. In an embodiment, closing the air circuit may include mating a first section of the plenum with a second section of the plenum. In an embodiment, the first section of the plenum may be connected to the TEC and the second section of the plenum may be connected to the cradle. It is contemplated that the method for regulating the temperature of a power supply of a UAV described above may include any combination of the features and elements described in this section.

[0006] In another aspect of the disclosure, a base station configured for use with a UAV is disclosed. The base station includes: a housing having an outer housing defining a roof section and an inner housing connected to the outer housing; one or more heating elements supported by the housing and configured to heat the roof section; one or more fiducials supported by the housing; an illumination system supported by the housing and configured to illuminate the one or more fiducials; and a visualization system supported by the housing. In an embodiment, the housing (e.g., the outer housing) may define one or more channels configured to direct water in a manner that inhibits ingress of water into the base station. In an embodiment, the base station may further include one or more temperature sensors in communication with the one or more heating elements such that the one or more heating elements activate upon receiving a signal relayed by the one or more temperature sensors indicating that the temperature has crossed a threshold value. In an embodiment, the one or more fiducials may include a first fiducial and a second fiducial, each supported by the roof section. In an embodiment, the second fiducial may be removably connected to the roof section. In an embodiment, the first fiducial may define a first surface area and the second fiducial may define a second surface area that is less than the first surface area. In an embodiment, the first surface area may be substantially within a range of (about) 40% to (about) 80% of a surface area defined by the roof section. In an embodiment, the second surface area may be substantially within a range of (about) 10% to (about) 50% of the first surface area. In an embodiment, the lighting system may include one or more light sources coupled to the roof section and configured to illuminate the first and second fiducials. In an embodiment, the lighting system may be configured to strobe the one or more light sources according to a pattern recognizable by the UAV during approach, thereby identifying the base station. In an embodiment, the visualization system may include a digital image capture device configured to identify precipitation and activate one or more heating elements.In an embodiment, the base station may further include one or more status indicators supported by the enclosure (e.g., the outer housing). In an embodiment, the base station may further include one or more internal fans to regulate temperature and / or humidity within the base station. In an embodiment, the internal fan may be supported by at least one of the outer housing and the inner housing. It is contemplated that the base stations described above may include any combination of the features and elements described in this section.

[0007] In another aspect of the disclosure, a base station configured for use with a UAV is disclosed. The base station includes: a housing; a (front) door movably connected to the housing such that the door is repositionable between a closed position and an open position; and one or more actuators extending between the door and the housing. The housing includes an outer housing and an inner housing connected to the outer housing and defining an interior cavity configured to receive a UAV. Each actuator includes a motor assembly and a linkage assembly extending between the motor assembly and the door. The motor assembly is connected (fixed) to the inner housing such that the motor assembly is located between the outer housing and the inner housing, and the linkage assembly extends through the inner housing. In an embodiment, the linkage assembly may include: a drive screw operably connected to the motor assembly such that actuation of the motor assembly rotates the drive screw; a carrier threadably engaged to the drive screw such that rotation of the drive screw axially translates the carrier; a first arm; and a second arm. In an embodiment, the first arm may have a first end pivotally connected to the carrier and a second end, and the second arm may have a first end pivotally connected to the second end of the first arm and a second end pivotally connected to the door. In an embodiment, the base station may further include a bracket fixedly connected to the door. In an embodiment, the bracket may be pivotally connected to the second end of the second arm. In an embodiment, the drive screw may be configured such that rotation of the drive screw in a first direction advances the carrier toward the door and rotation of the drive screw in a second direction advances the carrier away from the door. In an embodiment, the drive screw may include threads defining a pitch configured to inhibit transmission of force from the door to the carrier, thereby maintaining the door in a closed position. It is envisioned that the base station described above may include any combination of the features and elements described in this section.

[0008] In another aspect of the present disclosure, a base station configured for use with an unmanned aerial vehicle (UAV) is disclosed. The base station includes: a housing defining an interior cavity configured to receive the UAV; a first fiducial supported by a roof section of the housing and defining a first surface area; a second fiducial supported by the roof section of the housing and defining a second surface area that is less than the first surface area; and an illumination system supported by the roof section and configured to illuminate the first fiducial and the second fiducial. In an embodiment, the second fiducial may be configured for removable connection to the roof section. In an embodiment, the first surface area may be substantially within a range of (about) 40% to (about) 80% of the surface area defined by the roof section. In an embodiment, the second surface area may be substantially within a range of (about) 10% to (about) 50% of the first surface area. In some embodiments, the lighting system may be configured to strobe according to a pattern recognizable by the UAV during approach, thereby identifying the base station. It is contemplated that the base stations described above may include any combination of the features and elements described in this section.

[0009] In another aspect of the disclosure, a UAV is disclosed that includes a power source. The power source includes: one or more batteries; one or more heat transfer members thermally connected to the one or more batteries; and a heat exchanger thermally connected to the one or more heat transfer members, such that the one or more heat transfer members and the heat exchanger facilitate the transfer of thermal energy between the power source and the surrounding air to reduce or increase the temperature of the power source. In an embodiment, the one or more heat transfer members may extend between the one or more batteries and the heat exchanger. In an embodiment, the one or more heat transfer members may include graphite. In an embodiment, the one or more heat transfer members may be unitary in structure. In an embodiment, the one or more batteries and the one or more heat transfer members may be equal in number. In an embodiment, the one or more batteries may include a plurality of individual batteries and the one or more heat transfer members may include a plurality of individual heat transfer members. In an embodiment, the heat exchanger may include one or more diffusers to increase the surface area of ​​the heat exchanger and the distribution of thermal energy toward or away from the power source. In some embodiments, the one or more diffusers may extend axially and / or laterally along an outer surface of the heat exchanger. In some embodiments, the one or more diffusers may include multiple diffusers. In some embodiments, the multiple diffusers may be configured as fins, the fins defining one or more channels therebetween. In some embodiments, the one or more channels may be configured to direct air flow along the heat exchanger to increase the distribution of thermal energy toward or away from the power source. It is contemplated that the UAV described above may include any combination of the features and elements described in this section.

[0010] In another aspect of the present disclosure, a UAV is disclosed that includes a power source. The power source includes a heat exchanger configured to transfer thermal energy between the power source and ambient air to reduce or increase a temperature of the power source. The heat exchanger includes one or more diffusers to increase a surface area of ​​the heat exchanger and a distribution of thermal energy toward or away from the power source. In an embodiment, the one or more diffusers may extend axially and / or laterally along an outer surface of the heat exchanger. In an embodiment, the one or more diffusers may include multiple diffusers. In an embodiment, the multiple diffusers may be configured as fins, the fins defining one or more channels therebetween. In an embodiment, the one or more channels may be configured to direct a flow of air along the heat exchanger to increase a distribution of thermal energy toward or away from the power source. It is envisioned that the UAV described above may include any combination of the features and elements described in this section.

[0011] In another aspect of the disclosure, a UAV is disclosed that includes: a body; one or more antennas extending from the body; and a power source connected to the body. The one or more antennas are reconfigurable between an active configuration in which the one or more antennas extend outwardly from the body and a passive configuration in which the one or more antennas are positioned adjacent to the body. The power source includes one or more diffusers extending axially and / or laterally along an outer surface of the power source to transfer thermal energy between the power source and the surrounding air to reduce or increase a temperature of the power source. In an embodiment, the one or more antennas may be biased toward the active configuration. In an embodiment, the one or more diffusers may include multiple diffusers. In an embodiment, the multiple diffusers may be configured as fins, the fins defining one or more channels therebetween. In an embodiment, the one or more channels may be configured to direct air flow along the power source to increase the distribution of thermal energy toward or away from the power source. In some embodiments, the power source may further include one or more batteries and one or more heat transfer members thermally connected to the one or more batteries and the one or more diffusers. In some embodiments, the one or more heat transfer members may include graphite. In some embodiments, the one or more heat transfer members may be unitary in structure. It is contemplated that the UAV described above may include any combination of the features and elements described in this section.

[0012] In another aspect of the disclosure, a base station for an unmanned aerial vehicle (UAV) is disclosed that includes a housing; a sliding mechanism including an opening; and a cradle. The sliding mechanism is repositionable between a retracted position and an extended position and is secured (connected) to the housing via a first mounting portion and a second mounting portion. The first mounting portion and the second mounting portion are located between the sliding mechanism and the housing to isolate the sliding mechanism from the housing, thereby reducing vibration of the sliding mechanism during repositioning (extending and retracting) between the retracted position and the extended position. The cradle is connected to the sliding mechanism and configured to dock with the UAV such that the UAV is movable in and out of the housing during repositioning of the sliding mechanism between the retracted position and the extended position. In an embodiment, the housing may include a plurality of studs extending toward the sliding mechanism. In an embodiment, each of the first mounting portion and the second mounting portion may be configured to receive one of the plurality of studs. In an embodiment, the first mounting may include: a first bushing; a shank extending from the first bushing configured to be inserted into one of the openings of the sliding mechanism; and a fastener configured to be releasably connected to the shank such that the sliding mechanism is secured between the first bushing and the fastener. In an embodiment, the first bushing may define an opening to facilitate connection of the first bushing to the housing. In an embodiment, the shank and the fastener may be configured for threaded engagement. In an embodiment, the first bushing may include a flexible material that facilitates absorption of forces by the first mounting, thereby reducing vibration of the sliding mechanism during repositioning between the retracted position and the extended position. In an embodiment, the second mounting may include a second bushing having a non-uniform cross-sectional configuration. In an embodiment, the second bushing may include a base and a shaft extending from the base. In some embodiments, the base defines a first cross-sectional dimension and the shank defines a second cross-sectional dimension that is less than the first cross-sectional dimension, hi some embodiments, the shank can be configured to be inserted into one of the openings in the sliding mechanism.In an embodiment, the opening in the sliding mechanism may define a third cross-sectional dimension less than the first cross-sectional dimension and greater than the second cross-sectional dimension, such that the shaft can be received by the sliding mechanism such that the sliding mechanism is movable relative to the second mounting portion with two degrees of freedom oriented in a generally orthogonal relationship. In an embodiment, the second mounting portion may further include a fastener configured to secure the second bushing to the housing. It is envisioned that the base station described above may include any combination of the features and elements described in this section.

[0013] In another aspect of the disclosure, a base station for an unmanned aerial vehicle (UAV) is disclosed that includes a housing having a plurality of studs extending upwardly from the housing; a sliding mechanism including an opening; and a cradle. The sliding mechanism is repositionable between a retracted position and an extended position and is indirectly connected to the housing via a first mounting portion and a second mounting portion. The first mounting portion includes a first threaded interface configured to be connected to one of the plurality of studs and a second threaded interface separated from the first threaded interface by a flexible material. The second mounting portion includes: a base defining a first cross-sectional dimension; a shaft extending from the base and defining a second cross-sectional dimension that is less than the first cross-sectional dimension; and a channel extending through the base and the shaft and configured to receive one of the plurality of studs. The cradle is connected to the sliding mechanism and configured to dock with the UAV such that the UAV is movable in and out of the housing via the sliding mechanism. In an embodiment, the first and second mounting portions may be located between the housing and the sliding mechanism such that the housing and the sliding mechanism are physically separated by the first and second mounting portions. In an embodiment, the second threaded interface may include a shank configured to be inserted into one of the openings of the sliding mechanism and configured to connect to a fastener to secure the first mounting portion and the sliding mechanism to the housing. In an embodiment, the shank may be configured to be inserted into one of the openings of the sliding mechanism, thereby defining a third cross-sectional dimension less than the first cross-sectional dimension and greater than the second cross-sectional dimension to define a lateral gap between the shank and the opening of the sliding mechanism, allowing a predetermined lateral movement of the sliding mechanism within the housing and inhibiting lateral overtravel of the sliding mechanism. In an embodiment, the second mounting portion may further include a fastener configured to be releasably connected to the stud received by the channel such that an axial gap is defined between the fastener and the base to allow a predetermined axial movement of the sliding mechanism within the housing to inhibit axial overtravel of the sliding mechanism. It is contemplated that the base station described above may include any combination of the features and elements described in this section.

[0014] In another aspect of the disclosure, a base station for an unmanned aerial vehicle (UAV) is disclosed that includes a housing; a sliding mechanism including an opening and retractable and extendable relative to the housing to facilitate movement of the UAV in and out of the housing; a first mounting configured to be inserted into the sliding mechanism such that the first mounting is located between the sliding mechanism and the housing; and a second mounting configured to be inserted into the sliding mechanism such that the second mounting is located between the sliding mechanism and the housing, the first mounting and the second mounting including non-identical configurations. In an embodiment, the first mounting may be fixed relative to the sliding mechanism. In an embodiment, the second mounting may be configured to facilitate relative movement between the second mounting and the sliding mechanism. In an embodiment, the second mounting may include a stepped configuration. In an embodiment, the second mounting may include a base defining a first cross-sectional dimension and a stem extending from the base and defining a second cross-sectional dimension that is less than the first cross-sectional dimension. In an embodiment, the stem may be configured to be inserted into one of the openings in the sliding mechanism to define a lateral and axial gap, allowing for a predetermined lateral and axial movement of the sliding mechanism within the housing in two degrees of freedom and inhibiting overtravel of the sliding mechanism and unintended contact between the sliding mechanism and internal components of the base station. It is contemplated that the base stations described above may include any combination of the features and elements described in this section.

[0015] In another aspect of the disclosure, a method of assembling a base station for an unmanned aerial vehicle (UAV) is disclosed. The method includes: connecting a first mounting portion to a housing of the base station; connecting a second mounting portion to the housing, the first mounting portion including a first configuration and the second mounting portion including a second different configuration; connecting a sliding mechanism to the first mounting portion and the second mounting portion such that the first mounting portion and the second mounting portion are located between the sliding mechanism and the housing, thereby isolating the sliding mechanism from the housing and reducing vibration of the sliding mechanism during extension and retraction; and connecting a cradle configured to dock to the sliding mechanism to the sliding mechanism such that the UAV is movable in and out of the housing during extension and retraction of the sliding mechanism. In an embodiment, connecting the first mounting portion to the housing may include inserting a first stud extending from the housing into an opening defined by the first mounting portion. In some embodiments, inserting the first stud into the opening defined by the first mounting portion may include threadably connecting the first stud to a first bushing of the first mounting portion such that the first stud extends partially into the first bushing. In some embodiments, connecting the second mounting portion to the housing may include inserting a second stud extending from the housing into a channel defined by a second bushing of the second mounting portion such that the second stud extends through the second mounting portion. In some embodiments, connecting the sliding mechanism to the first mounting portion may include inserting a shank extending from the first bushing into an opening of the sliding mechanism. In some embodiments, connecting the sliding mechanism to the second mounting portion may include inserting a second bushing into an opening of the sliding mechanism. In some embodiments, inserting the second bushing into the opening of the sliding mechanism may include positioning a base of the second bushing between the housing and the sliding mechanism and inserting a shaft extending from the base into the opening of the sliding mechanism such that the sliding mechanism is movable relative to the second mounting portion in two degrees of freedom oriented in a generally orthogonal relationship. In some embodiments, connecting the sliding mechanism to the first mounting portion may include threadably connecting a first fastener to a shank extending from the first bushing.In some embodiments, connecting the sliding mechanism to the second mounting portion may include threadably connecting a second fastener to a second stud extending through the second bushing. In some embodiments, connecting the sliding mechanism to the second mounting portion may include forming a radial gap between the shaft portion and the opening in the sliding mechanism and forming an axial gap between the base portion and the second fastener. It is contemplated that the method of assembling the base station described above may include any combination of the features and elements described in this section.

[0016] In another aspect of the disclosure, a base station for an unmanned aerial vehicle (UAV) is disclosed, comprising: a housing defining an internal cavity configured to receive a UAV; a (front) door movably connected to the housing; an actuator extending between the door and the housing to facilitate opening and closing of the door; a cradle configured to receive the UAV; and an engagement member connected (secured) to the actuator and configured to contact a propeller assembly on the UAV to facilitate folding of the propeller assembly during movement of the UAV into the housing. The cradle is movable relative to the housing such that the cradle is repositionable between a retracted position and an extended position to facilitate movement of the UAV into and out of the housing. In an embodiment, the engagement member may comprise a flexible material that inhibits disengagement of the UAV from the cradle upon contact between the engagement member and the propeller assembly. In an embodiment, the engagement member may comprise a mounting bracket configured to be connected to the actuator. In an embodiment, the actuator may comprise a first actuator and a second actuator laterally spaced from the first actuator along a width of the housing. In an embodiment, the engagement members may include a first engagement member connected to the first actuator and a second engagement member connected to the second actuator such that the second engagement member is spaced laterally from the first engagement member along a width of the housing. It is contemplated that the base station described above may include any combination of the features and elements described in this section.

[0017] In another aspect of the disclosure, a method of docking an unmanned aerial vehicle (UAV) into a base station is disclosed, comprising: opening a (front) door of the base station; performing a first stage retraction of the UAV into the base station; rotating a rear propeller assembly into contact with an engagement member on the base station to partially fold the rear propeller assembly on the UAV; performing a second stage retraction of the UAV into the base station; rotating the rear propeller assembly into contact with the engagement member to fully fold the rear propeller assembly on the UAV; performing a third stage retraction of the UAV into the base station; rotating a front propeller assembly into contact with the engagement member to partially fold the front propeller assembly on the UAV; and fully folding the front propeller assembly. In an embodiment, performing the second stage retraction of the UAV may include folding an antenna on the UAV into contact with the door. In some embodiments, partially folding the rear propeller assembly may include rotating the first rear propeller assembly in a first direction and rotating the second rear propeller assembly in a second direction opposite the first direction. In some embodiments, fully folding the rear propeller assembly may include rotating the first rear propeller assembly in a second direction and rotating the second rear propeller assembly in the first direction. In some embodiments, fully folding the rear propeller assembly may include positioning the rear propeller assembly such that the rear propeller assembly is oriented toward the forward propeller assembly. In some embodiments, the method may further include partially closing the door to facilitate contact between the engagement member and the forward propeller assembly. In some embodiments, partially folding the forward propeller assembly may include actively rotating the first forward propeller assembly in the second direction and actively rotating the second forward propeller assembly in the first direction. In some embodiments, partially folding the front propeller assemblies may further include passively rotating the first front propeller assembly in a first direction and passively rotating the second front propeller assembly in a second direction.In some embodiments, passively rotating the first forward propeller assembly and passively rotating the second forward propeller assembly may include performing a fourth stage retraction of the UAV into the base station. In some embodiments, partially folding the forward propeller assembly may include positioning the forward propeller assembly such that the forward propeller assembly is oriented away from the rear propeller assembly. In some embodiments, fully folding the forward propeller assembly may include rotating the first forward propeller assembly in a first direction and rotating the second forward propeller assembly in a second direction. In some embodiments, fully folding the forward propeller assembly may include actively rotating the forward propeller assembly such that the forward propeller assembly is oriented toward the rear propeller assembly. It is envisioned that the method of docking a UAV into a base station described above may include any combination of the features and elements described in this section.

[0018] In another aspect of the disclosure, a method of docking an unmanned aerial vehicle (UAV) into a base station is disclosed, comprising: rotating a rear propeller assembly into contact with an engagement member on the base station to fold a rear propeller assembly on the UAV; retracting the UAV into the base station; and rotating a front propeller assembly into contact with the engagement member to fold a front propeller assembly on the UAV. In an embodiment, the method may further comprise adjusting a position of a (front) door of the base station to facilitate contact between the engagement member and the rear propeller assembly and between the engagement member and the front propeller assembly. In an embodiment, folding the rear propeller assembly and folding the front propeller assembly comprises rotating the rear propeller assembly and rotating the front propeller assembly into a bumper supported by an actuator connected to the base station door, the actuator configured to facilitate opening and closing the door. In some embodiments, folding the rear propeller assembly and folding the front propeller assembly may include rotating the rear propeller assembly and rotating the front propeller assembly into a bumper supported by the door. It is contemplated that the method of docking a UAV into a base station described above may include any combination of the features and elements described in this section.

[0019] In another aspect of the disclosure, a base station for an unmanned aerial vehicle (UAV) is disclosed. The base station includes: a housing; a sliding mechanism connected to the housing and repositionable between a retracted position and an extended position; a cradle connected to the sliding mechanism and configured to dock with the UAV such that the UAV is movable in and out of the housing during repositioning of the sliding mechanism between the retracted position and the extended position; and a charging hub connected to the sliding mechanism and configured to be electrically connected to a power source of the UAV for charging the power source. In an embodiment, the sliding mechanism may include a fixed sliding member fixedly connected to the housing and a movable sliding member slidable relative to the fixed sliding member. In an embodiment, the charging hub may be connected to the fixed sliding member. In an embodiment, the charging hub may extend into the cradle when the sliding mechanism is in the retracted position. In an embodiment, the charging hub may include a charging member configured to be electrically connected to a power source of the UAV. In some embodiments, the cradle may define an opening configured to receive the charging member such that the charging member moves in and out of the cradle during repositioning of the sliding mechanism between the retracted position and the extended position. In some embodiments, the charging hub may include a base connected to the sliding mechanism; an alignment bracket (movably) supported by the base; and a charging member connected to the alignment bracket and configured to be electrically connected to a power source. In some embodiments, the charging member may be connected to the alignment bracket such that the charging member and the alignment bracket are movable in unison along an axis of movement. In some embodiments, the alignment bracket may include an anchor that extends into a corresponding opening in the charging member to constrain relative movement between the alignment bracket and the charging member. In some embodiments, the base may be fixedly connected to the sliding mechanism. In some embodiments, the base may define a cavity configured to receive the alignment bracket such that the alignment bracket is movable through the cavity during repositioning between the normal position and the deflected position. In some embodiments, the base may include a bottom wall defining the cavity. In some embodiments, the bottom wall may define an opening configured to receive the alignment bracket to facilitate assembly of the charging hub.In some embodiments, the bottom wall may be configured to support the alignment bracket during repositioning between the normal position and the deflected position. In some embodiments, the bottom wall may define a chamfered surface configured to engage the alignment bracket to facilitate repositioning of the alignment bracket between the normal position and the deflected position. In some embodiments, the charging hub may further include a biasing member located within the cavity. In some embodiments, the biasing member may be configured to bias the alignment bracket toward the normal position. In some embodiments, the biasing member may include a first end engaged with the base and a second end engaged with the alignment bracket. In some embodiments, the alignment bracket may include an alignment member configured to be inserted into a receptacle defined by a power source of the UAV. In some embodiments, the alignment member may extend axially forward of the charging member along the axis of movement. In some embodiments, the alignment member may be vertically offset from the biasing member. In some embodiments, the charging hub may further include a cap removably connected to the base. In some embodiments, a cap may overlap the charging member to inhibit rotation of the charging member and alignment bracket relative to the base. It is contemplated that the base station described above may include any combination of the features and elements described in this section.

[0020] In another aspect of the disclosure, a charging hub of a base station configured for use with an unmanned aerial vehicle (UAV) is disclosed. The charging hub includes: a base; an alignment bracket movably supported by the base such that the alignment bracket is repositionable between a normal position and a deflected position; a biasing member positioned between the base and the alignment bracket and configured to bias the alignment bracket toward the normal position; a charging member connected to the alignment bracket such that the charging member moves simultaneously with the alignment bracket during repositioning of the alignment bracket between the normal position and the deflected position; and a cap removably connected to the base such that the cap overlaps the charging member to inhibit rotation of the charging member and the alignment bracket relative to the base. In an embodiment, the biasing member may include a first end engaged with the base and a second end engaged with the alignment bracket. In an embodiment, the alignment bracket may include an anchor extending into a corresponding opening in the charging member to inhibit relative movement between the alignment bracket and the charging member. In some embodiments, the base may define a cavity configured to receive the alignment bracket such that the alignment bracket is movable through the cavity during repositioning between the normal position and the deflected position. In some embodiments, the base may define an opening configured to receive the alignment bracket to facilitate assembly of the charging hub. In some embodiments, the base may include a bottom wall defining the cavity. In some embodiments, the bottom wall may be configured to support the alignment bracket during repositioning between the normal position and the deflected position. In some embodiments, the bottom wall may define a chamfered surface configured to engage the alignment bracket to facilitate repositioning of the alignment bracket between the normal position and the deflected position. In some embodiments, the alignment bracket may include an alignment member configured to be inserted into a receptacle defined by a power source of the UAV. In some embodiments, the alignment member may extend axially forward of the charging member and may be vertically offset from the biasing member. It is envisioned that the charging hub described above may include any combination of the features and elements described in this section.

[0021] In another aspect of the disclosure, a method of charging an unmanned aerial vehicle (UAV) using a base station is disclosed. The method includes: docking the UAV with a cradle of the base station; retracting the cradle into a housing of the base station via a sliding mechanism; and electrically connecting a power source of the UAV to a charging hub connected to the sliding mechanism, thereby charging the power source. In an embodiment, docking the UAV with the cradle may include inducing a power source into a chamber defined by the cradle via contact between the UAV and a tapered sidewall of the cradle. In an embodiment, retracting the cradle may include repositioning the sliding mechanism from an extended position to a retracted position. In an embodiment, repositioning the sliding mechanism from an extended position to a retracted position may include telescopically repositioning a movable sliding member relative to a fixed sliding member. In an embodiment, the charging hub may be connected to the fixed sliding member. In an embodiment, electrically connecting a power source of the UAV to the charging hub may include inserting a charging member into the power source. In some embodiments, retracting the cradle may include aligning a first electrical connector on the charging hub with an opening in the power source, thereby facilitating engagement of the first electrical connector with a second electrical connector on the power source. In some embodiments, aligning the first electrical connector with an opening in the power source may include inserting an alignment bracket on the charging hub into a receptacle defined by the power source. In some embodiments, retracting the cradle may include inserting the alignment bracket into the receptacle. In some embodiments, inserting the alignment bracket into the receptacle may include repositioning the alignment bracket from a normal position to a deflected position via movement of the alignment bracket relative to a base of the charging hub along an axis of movement. In some embodiments, the method may further include repositioning the alignment bracket from a normal position to a deflected position, wherein the charging member is connected to the alignment bracket such that the charging member and the alignment bracket move in unison.In some embodiments, repositioning the alignment bracket from the normal position to the biased position may include compressing a biasing member located between the alignment bracket and a base of the charging hub, the biasing member configured to bias the alignment bracket toward the normal position. In some embodiments, repositioning the alignment bracket from the normal position to the biased position may include increasing a preloaded force (e.g., biasing force) applied to the alignment bracket. In some embodiments, inserting the alignment bracket into the receptacle may include inserting an alignment member on the alignment bracket into the receptacle. In some embodiments, the alignment member may extend axially forward of the first electrical connector along the axis of movement. In some embodiments, repositioning the alignment bracket from the normal position to the biased position may include constraining rotation of the alignment bracket and the first electrical connector relative to the base via a cap removably connected to the base. It is contemplated that the method of charging a UAV using a base station described above may include any combination of the features and elements described in this section.

[0022] In another aspect of the disclosure, a method of charging an unmanned aerial vehicle (UAV) using a base station is disclosed. The method includes: docking the UAV with the base station; retracting the UAV toward a charging hub of the base station; inserting an alignment member carried by an alignment bracket of the charging hub into a receptacle of a power source of the UAV; inserting the charging member of the charging hub into an opening of the power source; increasing a preload force applied to the alignment bracket by a biasing member positioned within a base of the charging hub, the biasing member being vertically offset from the alignment member; and restraining rotation of the alignment bracket relative to the base via a cap overlying the charging member. In some embodiments, increasing the preload force may include displacing the alignment bracket and the charging member. In some embodiments, displacing the alignment bracket and the charging member may include compressing the biasing member between the alignment bracket and the base. In some embodiments, displacing the alignment bracket and the charging member may include moving the alignment bracket and the charging member in unison. In some embodiments, displacing the alignment bracket and the charging member may include axially moving the charging member within a channel defined by the cap. It is contemplated that the method of charging a UAV using a base station described above may include any combination of the features and elements described in this section.

[0023] In another aspect of the disclosure, a method of charging an unmanned aerial vehicle (UAV) using a base station is disclosed. The method includes: docking the UAV with the base station; retracting the UAV toward the charging hub of the base station to insert an alignment bracket of the charging hub into a receptacle defined by a power source of the UAV, thereby aligning a first electrical connector of the charging hub with a second electrical connector of the power source; and engaging the first electrical connector and the second electrical connector, thereby establishing an electrical connection between the base station and the UAV and charging the power source. In an embodiment, retracting the UAV toward the charging hub may include compressing a biasing member positioned between the alignment bracket and a base of the charging hub that supports the alignment bracket. In an embodiment, compressing the biasing member may include compressing the biasing member within a cavity defined by the base. In an embodiment, retracting the UAV toward the charging hub may include displacing the alignment bracket, thereby compressing the biasing member. In some embodiments, displacing the alignment bracket may include supporting the first electrical connector and causing a corresponding displacement of a charging member connected to the alignment bracket such that the alignment bracket and the charging member move in unison. It is contemplated that the method of charging a UAV using a base station described above may include any combination of the features and elements described in this section.

[0024] In another aspect of the disclosure, a base station for an unmanned aerial vehicle (UAV) is disclosed. The base station includes: a housing configured to receive the UAV and including a front end with a front door and a rear end with a rear door; a sliding mechanism connected to the housing; a cradle configured to dock with the UAV and connected to the sliding mechanism such that the UAV is movable in and out of the housing during repositioning of the cradle between a retracted position and an extended position; a first electronic module removably connected to the housing adjacent the rear door; a second electronic module removably connected to a roof section of the housing; and a third electronic module removably connected to the sliding mechanism, whereby the first electronic module, the second electronic module, and the third electronic module are individually removable from the base station. In an embodiment, the first electronic module may include: a main heat sink and an auxiliary heat sink. In an embodiment, the auxiliary heat sink may be connected to the main heat sink such that the main heat sink defines a plurality of side walls collectively defining a perimeter of the first electronic module and the auxiliary heat sink defines an end wall of the first electronic module. In an embodiment, the auxiliary heat sink may include one or more diffusers configured to increase thermal energy distribution (e.g., of the auxiliary heat sink). In an embodiment, the first electronic module may further include: a logic board supported by the main heat sink such that the logic board is located between the main heat sink and the auxiliary heat sink; a first printed circuit board assembly (PCBA) supported by the main heat sink; and an interface member located between the main heat sink and the first PCBA. In an embodiment, the first electronic module may be configured to facilitate data processing and control of the base station. For example, in an embodiment, the first PCBA may include a processor configured to facilitate data processing and control of the base station. In an embodiment, the main heat sink may define a cavity configured to receive the logic board.In an embodiment, the interface member may include at least one thermally conductive section configured to facilitate thermal energy transfer between the first PCBA and the main heat sink and at least one electrically conductive section configured to electrically ground the first PCBA. In an embodiment, the at least one electrically conductive section may include an adhesive connecting the first PCBA to the main heat sink. In an embodiment, the base station may further include an air circulation module connected to the housing adjacent the rear door. In an embodiment, the air circulation module may be positioned around the first electronic module to facilitate cooling of the first electronic module. In an embodiment, the housing may include a frame defining an exterior surface and an interior surface. In an embodiment, the first electronic module may be connected to an exterior surface of the frame and the air circulation module may be connected to an interior surface of the frame such that the frame is located between the first electronic module and the air circulation module, whereby the first electronic module is removable from the base station separately from the air circulation module. In an embodiment, the air circulation module may include ducting configured to direct air across the first electronic module and a fan supported by the ducting. In an embodiment, the rear door may include a non-metallic frame and a metal panel connected to the non-metallic frame. In an embodiment, the metal panel may be positioned corresponding to the first electronic module to create a Faraday cage for the first electronic module, thereby reducing electromagnetic radiation from the base station. In an embodiment, the rear door may further include a sealing member extending around the metal panel and configured to engage with the housing. In an embodiment, the second electronic module may be configured to control the opening and closing of the front door. In an embodiment, the second electronic module may include: an access panel removably connected to the roof section of the housing; a second PCBA connected to the access panel; and a fan connected to the access panel.In an embodiment, the access panel may be removably connected to the interior surface of the roof section via a plurality of mechanical fasteners such that the second electronic module is accessible from inside the housing. In an embodiment, the plurality of mechanical fasteners may be configured as thumb screws to allow for tool-less connection and disconnection of the access panel. In an embodiment, the third electronic module may be configured to facilitate and control repositioning of the cradle between the retracted and extended positions. For example, in an embodiment, the third electronic module may be configured to control the sliding mechanism. In an embodiment, the third electronic module may include a third PCBA removably connected to the sliding mechanism via a plurality of mechanical fasteners such that the third electronic module is accessible from inside the housing upon removal of the UAV. In an embodiment, the sliding mechanism may include a fixed sliding member connected to the housing and a movable sliding member that is slidable relative to the fixed sliding member. In an embodiment, the third PCBA may be removably connected to the fixed sliding member. It is envisioned that the base station described above may include any combination of the features and elements described in this section.

[0025] In another aspect of the disclosure, a base station for an unmanned aerial vehicle (UAV) is disclosed. The base station includes: a housing defining a window configured to receive a UAV to allow the UAV to enter and exit the base station; a door movably connected to the housing such that the door is repositionable between a closed position and an open position; a sealing member extending around the window and configured to engage the door to form a seal with the door when the door is in the closed position; and a heating system supported by the housing and configured to heat the door and / or the sealing member to support operation (e.g., opening and closing) of the door in a cold environment. In an embodiment, the heating system may include at least one light source and at least one heating element. In an embodiment, the at least one light source may be configured to identify a status of the base station. In an embodiment, the at least one light source may be supported on an exterior surface of the housing and the at least one heating element may be supported on an interior surface of the housing. In an embodiment, the base station may further include a thermal interface material located between the housing and the at least one heating element. In an embodiment, the heating system may further include at least one temperature sensor supported by the housing. In some embodiments, the door may include a thermally conductive member to further facilitate heating of the door. In some embodiments, the thermally conductive member may be embedded within the door. In some embodiments, the sealing member may include a thermally conductive member to further facilitate heating of the sealing member. In some embodiments, the thermally conductive member may be embedded within the sealing member. In some embodiments, the base station may further include at least one additional heating element supported by the roof section of the enclosure. It is envisioned that the base station described above may include any combination of the features and elements described in this section.

[0026] In another aspect of the disclosure, a docking system for an unmanned aerial vehicle (UAV) is disclosed. The docking system includes a base station configured to receive the UAV and a pedestal configured to support the base station in an elevated position. The pedestal defines an interior space configured to correspond to an exterior contour of the base station such that the base station is positionable within the pedestal to protect the base station when not in use. In an embodiment, the pedestal may be of unitary construction. In an embodiment, the pedestal may include: a top wall having a non-linear configuration; first and second side walls extending from the top wall, each having a generally linear configuration; and first and second bottom walls extending laterally inward from the first and second side walls, each having a generally linear configuration. In an embodiment, the top wall may include a first segment extending laterally inward from the first side wall; a second segment extending laterally inward from the second side wall; a third segment extending generally parallel to the first and second segments; a fourth segment extending between the first and third segments; and a fifth segment extending between the second and third segments. In an embodiment, the first and second segments may be aligned vertically. In an embodiment, the third segment may be vertically offset from the first and second segments to define a well. In an embodiment, the first side wall may be configured to define a first acute angle with a first reference axis oriented in a generally orthogonal relationship to the first bottom wall, and the second side wall may be configured to define a second acute angle with a second reference axis oriented in a generally orthogonal relationship to the second bottom wall. In an embodiment, the well may be configured to accommodate at least one antenna of the base station to create vertical clearance for the at least one antenna when the base station is positioned within the pedestal. In an embodiment, the base station may include a pair of antennas.In an embodiment, the fourth segment and the fifth segment may define approximately the same obtuse angle with the first segment and the second segment, respectively, such that when the base station is positioned within the pedestal, the well extends into a space defined between the pair of antennas. It is contemplated that the docking system described above may include any combination of the features and elements described in this section.

[0027] In another aspect of the disclosure, a base station for an unmanned aerial vehicle (UAV) is disclosed. The base station includes: a housing; a sliding mechanism connected to the housing and repositionable between a retracted position and an extended position; and a cradle connected to the sliding mechanism and defining a chamber configured to receive the UAV such that the UAV is movable in and out of the housing during repositioning of the sliding mechanism between the retracted position and the extended position. The cradle includes: an upper shell; a lower shell connected to the upper shell; and at least one thermal insulator positioned between the upper shell and the lower shell. In an embodiment, the cradle may define an airflow channel extending around the chamber and configured to facilitate air circulation within the cradle. In an embodiment, the cradle may further define an air inlet (vent) and an air outlet (vent) in communication with the airflow channel and configured to direct airflow across the chamber to heat or cool a power source of the UAV when the UAV is docked within the cradle. In an embodiment, the cradle may include a rear end defining a lead-in configured to engage with the housing during retraction of the cradle to facilitate entry of the cradle into the housing. In an embodiment, the top shell may define an angled guide surface configured to engage the UAV, thereby directing the UAV into the chamber and facilitating proper docking of the UAV within the cradle. In an embodiment, the top shell and the bottom shell may each comprise a non-metallic material. In an embodiment, the at least one insulation may comprise an insulative foam. In an embodiment, the airflow channel may be defined by the at least one insulation. In an embodiment, the airflow channel may comprise a discontinuous configuration. In an embodiment, the airflow channel may include a first channel portion and a second channel portion. In an embodiment, the first channel portion and the second channel portion may be separated by a nose section of the cradle. In an embodiment, the first channel portion may be in communication with an air inlet and the second channel portion may be in communication with an air outlet.It is contemplated that the base station described above may include any combination of the features and elements described in this section.

[0028] In another aspect of the disclosure, a base station for an unmanned aerial vehicle (UAV) is disclosed. The base station includes: a housing configured to receive the UAV; a door movably connected to the housing such that the door is repositionable between a closed position and an open position; a primary heating system associated with a roof section of the housing; and a secondary heating system associated with the door. In an embodiment, the secondary heating system may include an external light source and an internal heating element. In an embodiment, the primary heating system and / or the secondary heating system may be configured to automatically activate upon receiving an activation signal. In an embodiment, the base station may further include a temperature sensor configured to relay an activation signal to the primary heating system and / or the secondary heating system upon detecting a threshold temperature. In an embodiment, the base station may further include a visualization system supported by the housing and configured to visually inspect the environmental conditions. In an embodiment, the visualization system may be configured to relay an activation signal to the primary heating system and / or the secondary heating system. It is envisioned that the base station described above may include any combination of the features and elements described in this section.

[0029] In another aspect of the disclosure, a method for heating a base station for an unmanned aerial vehicle (UAV) is disclosed. The method includes activating a primary heating system associated with a roof section of the base station to expose at least one fiducial supported by the roof section, thereby facilitating visual identification of the base station by the UAV and / or guidance of the UAV during landing and docking with the base station. In an embodiment, the method may further include activating a secondary heating system associated with a door of the base station to facilitate opening and closing thereof. In an embodiment, activating the secondary heating system may include activating at least one thermally conductive member, where the at least one thermally conductive member is connected to the door and / or to a sealing member configured to engage the door. In an embodiment, activating the secondary heating system may include activating an external light source and activating an internal heating element. In an embodiment, activating the primary heating system and activating the secondary heating system may include automatically activating the primary heating system and automatically activating the secondary heating system upon receiving an activation signal from at least one of: a temperature sensor in the base station configured to detect a threshold temperature; a visualization system in the base station configured to visually inspect environmental conditions; and a weather station wirelessly connected to the base station. It is contemplated that the method of heating a base station for a UAV described above may include any combination of the features and elements described in this section.

[0030] In another aspect of the present disclosure, a docking system for an unmanned aerial vehicle (UAV) is disclosed. The docking system includes a base station configured to receive the UAV and a pedestal configured to receive and support the base station such that the docking system is reconfigurable between a nested configuration in which the base station is positioned within an interior space defined by the pedestal and a stacked configuration in which the base station is supported in an elevated position by the pedestal. In an embodiment, the pedestal may be configured to create a gap with the base station around its entire circumference to inhibit contact between the pedestal and the base station in the nested configuration. In an embodiment, the interior space may be configured to correspond to an exterior contour of the base station. In an embodiment, the base station may include a pair of antennas. In an embodiment, the pedestal may define a well configured to be positioned between the pair of antennas when the docking system is in the nested configuration. In an embodiment, the pedestal may include a plurality of adjustable footings configured to removably connect thereto. It is envisioned that the docking system described above may include any combination of the features and elements described in this section.

[0031] In another aspect of the disclosure, a method of using a docking system for an unmanned aerial vehicle (UAV) is disclosed. The method includes: storing a base station for the UAV within an interior space defined by a pedestal during non-use of the base station; removing the base station from the interior space defined by the pedestal; and supporting the base station on the pedestal in an elevated position. In an embodiment, the method may further include adjusting at least one footing on the pedestal, thereby stabilizing the pedestal and the base station when the base station is in the elevated position. In an embodiment, supporting the base station on the pedestal may include releasably connecting the base station to the pedestal to inhibit unintended separation thereof. In an embodiment, the method may further include: facilitating take-off of the UAV from the base station; docking the UAV with the base station after flight; and nesting the base station within the pedestal following docking of the UAV by returning the base station to the interior space. In an embodiment, nesting the base station within the pedestal may include positioning a well defined by the pedestal between antennas on the base station. It is contemplated that a method of using the docking system for a UAV described above may include any combination of the features and elements described in this section.

[0032] In another aspect of the disclosure, a base station for an unmanned aerial vehicle (UAV) is disclosed. The base station includes: a housing; a sliding mechanism connected to the housing and repositionable between a retracted position and an extended position; and a cradle connected to the sliding mechanism and defining a chamber configured to receive the UAV such that the UAV is movable in and out of the housing during repositioning of the sliding mechanism between the retracted position and the extended position. The cradle includes: an upper shell defining an air inlet and an air outlet; a lower shell connected to the upper shell; and at least one insulation positioned between the upper shell and the lower shell. The lower shell defines a first air flow opening in communication with the air inlet and a second air flow opening in communication with the air outlet. The at least one insulation defines an air flow channel in communication with the first air flow opening and the second air flow opening and extending around the chamber to facilitate air circulation within the cradle. In an embodiment, the at least one insulation may include an upper insulation and a lower insulation. In some embodiments, the airflow channel may extend between the top insulation and the bottom insulation. In some embodiments, the airflow channel may include a discontinuous configuration. In some embodiments, the airflow channel may include a first channel portion and a second channel portion. In some embodiments, the first channel portion may communicate with the air inlet and the first airflow opening, and the second channel portion may communicate with the air outlet and the second airflow opening. In some embodiments, the first channel portion and the second channel portion may be separated by a nose section of the cradle such that the nose section inhibits airflow between the first channel portion and the second channel portion, thereby directing airflow from the air inlet across the chamber and into the air outlet. It is envisioned that the base station described above may include any combination of the features and elements described in this section.

[0033] In another aspect of the disclosure, a base station for an unmanned aerial vehicle (UAV) is disclosed. The base station includes: a housing; a sliding mechanism connected to the housing and repositionable between a retracted position and an extended position; a charging hub connected to the sliding mechanism and configured to be electrically connected to a power source of the UAV; and a cradle connected to the sliding mechanism and defining a chamber configured to receive the UAV such that the UAV is movable in and out of the housing during repositioning of the sliding mechanism between the retracted position and the extended position. The cradle includes: a housing and at least one thermal insulator. The at least one thermal insulator is located within the housing and defines an airflow channel that extends discontinuously around the chamber. In an embodiment, the housing may define a charging window configured to receive the charging hub such that the charging hub is extendable into the cradle during repositioning of the sliding mechanism between the retracted position and the extended position. In an embodiment, the housing may define an air inlet and an air outlet positioned on opposite sides of the chamber. In an embodiment, the airflow channel may include a first channel portion in communication with the air inlet and a second channel portion in communication with the air outlet. In an embodiment, the first channel portion and the second channel portion may be separated by a nose section of the cradle such that the nose section inhibits air flow therebetween, thereby directing air flow from the air inlet, across the chamber, and into the air outlet. It is contemplated that the base station described above may include any combination of the features and elements described in this section.

[0034] In another aspect of the disclosure, a base station for an unmanned aerial vehicle (UAV) is disclosed. The base station includes: a housing configured to receive the UAV; and a charging hub operably connected to the housing and configured to charge the UAV. The charging hub includes: a base; an alignment bracket movably supported by the base such that the alignment bracket is repositionable between a normal position and a deflected position; and a charging member configured to be electrically connected to the UAV. The charging member is connected to the alignment bracket such that the charging member and the alignment bracket are moveable in unison along an axis of movement during repositioning of the alignment bracket between the normal position and the deflected position. In an embodiment, the charging hub may further include a biasing member positioned between the base and the alignment bracket and configured to bias the alignment bracket toward the normal position. In an embodiment, the alignment bracket may include an alignment member configured to be inserted into a receptacle defined by the UAV to facilitate proper positioning of the charging member and electrical connection of the charging hub to the UAV. In an embodiment, the alignment member may extend axially forward of the charging member along the axis of movement. In some embodiments, the alignment member may be vertically offset from the biasing member.It is contemplated that the base stations described above may include any combination of the features and elements described in this section.

[0035] In another aspect of the disclosure, a base station for an unmanned aerial vehicle (UAV) is disclosed. The base station includes: a housing having a front end configured to receive a UAV and a rear end; a cradle configured to dock with the UAV and movable relative to the housing via a sliding mechanism; a first electronic module removably connected to the rear end of the housing and configured to facilitate data processing and control of the base station; and an air circulation module connected to the rear end of the housing and positioned around the first electronic module to facilitate cooling of the first electronic module. In an embodiment, the base station may further include a second electronic module and a third electronic module. In an embodiment, the second electronic module may be removably connected to a roof section of the housing and configured to facilitate opening and closing of the housing, and the third electronic module may be removably connected to the sliding mechanism and configured to facilitate repositioning of the cradle, whereby the first electronic module, the second electronic module, and the third electronic module may be individually removable from the base station. In an embodiment, the first electronic module may include a heat sink. In some embodiments, the ducting may define a chamber having an inner contour that corresponds to the outer contour of the heat sink. It is contemplated that the base station described above may include any combination of the features and elements described in this section.

[0036] In another aspect of the disclosure, a base station for an unmanned aerial vehicle (UAV) is disclosed. The base station includes: a metal housing; a first electronic module; a second electronic module; and a third electronic module, where the first electronic module, the second electronic module, and the third electronic module are each configured to be individually removed from the metal housing. The metal housing is configured to receive the UAV and includes a front end having a front door and a rear end having a rear door. The rear door includes a metal panel located adjacent to the first electronic module and correspondingly positioned to create a Faraday cage for the first electronic module, thereby reducing electromagnetic radiation from the base station. In an embodiment, the rear door may further include a non-metallic frame. In an embodiment, the metal panel may be connected to the non-metallic frame. In an embodiment, the second electronic module may include an access panel removably connected to a roof section of the metal housing. In an embodiment, the access panel may be removably connected to an inner surface of the roof section via a plurality of mechanical fasteners such that the second electronic module is accessible from within the metal housing. In an embodiment, the mechanical fasteners may be configured to allow tool-less connection of the access panel to the roof section and tool-less decoupling of the access panel from the roof section. In an embodiment, the base station may further include a sliding mechanism and a cradle connected to the sliding mechanism. In an embodiment, the sliding mechanism may be connected to the metal housing. In an embodiment, the sliding mechanism may be repositionable between a retracted position and an extended position. In an embodiment, the cradle may be configured to dock with the UAV such that the UAV is movable in and out of the metal housing during repositioning of the sliding mechanism between the retracted position and the extended position. In an embodiment, the third electronic module may be removably connected to the sliding mechanism such that the third electronic module is accessible from within the metal housing upon removal of the UAV. It is envisioned that the base station described above may include any combination of the features and elements described in this section.

[0037] The present disclosure is best understood from the following detailed description when read in conjunction with the accompanying drawings, in which: It is emphasized that, according to common practice, the various features of the drawings are not to scale. Conversely, dimensions of the various features have been arbitrarily expanded or reduced for clarity. [Brief description of the drawings]

[0038] [Figure 1] FIG. 1 is a front perspective view of a base station (dock) according to the principles of the present disclosure. [Diagram 2] FIG. 1 is a partial side view of a base station shown in one embodiment of a UAV docked in a cradle of the base station, the UAV including multiple propulsion mechanisms (e.g., propeller assemblies), each including a hub and multiple propeller blades connected thereto. [Diagram 3] FIG. 3 is a partial side view of a base station shown together with an alternative embodiment of the UAV seen in FIG. 2. [Figure 4] FIG. 2 is a perspective view of the bottom of the power supply of the UAV. [Diagram 5] FIG. 2 is a partial side perspective view of a power supply for a UAV. [Figure 6] FIG. 2 is a schematic diagram of a side view of a base station. [Figure 7] FIG. 2 is a partial rear perspective view of the base station. [Figure 8] FIG. 2 is a partial side perspective view of a base station illustrating a number of actuators configured to open and close a (front) door of the base station. [Figure 9] FIG. 2 is a partial top perspective view of a base station illustrating multiple actuators. [Figure 10] FIG. 2 is a partial top perspective view of a base station illustrating multiple actuators. [Figure 11] 13 is a partial front perspective view of the base station illustrating the cap supported on a sliding mechanism that facilitates movement of the cradle between retracted and extended positions. FIG. [Figure 12] FIG. 13 is a partial rear perspective view of the cap shown closed with the base station door superimposed thereon. [Figure 13]FIG. 2 is a partial side perspective view of the base station showing the cradle in an extended position. [Figure 14] 1 is a perspective view of the top surface of a sliding mechanism according to an embodiment of the present disclosure, in which the sliding mechanism is connected (fixed) to a housing of a base station via a plurality of first mounting portions and a plurality of second mounting portions. FIG. [Figure 15] 2 is a perspective view of the top surface of the sliding mechanism, the first mounting portion, and the second mounting portion. FIG. [Figure 16] 4 is a plan view of the bottom surfaces of the sliding mechanism, the first mounting portion, and the second mounting portion. FIG. [Figure 17] FIG. 13 is a partial side perspective view of the sliding mechanism, one of the first mounting portions, and one of the second mounting portions during assembly. [Figure 18] FIG. 18 is a partial side perspective view of the sliding mechanism, first mounting portion, and second mounting portion seen in FIG. 17 when assembled. [Figure 19] FIG. 2 is a perspective view of the bottom of one of the first mounting portions. [Figure 20] FIG. 2 is a transverse (horizontal) cross-sectional view of one of the first mounting parts. [Figure 21] FIG. 2 is an axial (vertical) cross-sectional view of one of the first mounting parts. [Figure 22] 11 is an axial (vertical) cross-sectional view illustrating the connection of the sliding mechanism to the housing via one of the first mounting portions. FIG. [Diagram 23] FIG. 13 is a perspective view of a side of one of the second mounting portions. [Figure 24] 13 is an axial (vertical) cross-sectional view illustrating an assembly of a housing, a sliding mechanism, and one of the second mounting portions. FIG. [Diagram 25] FIG. 2 is a partial top perspective view of the sliding mechanism, one of the first mounting portions, and one of the second mounting portions during assembly, illustrating the lateral (radial, horizontal) gap between the sliding mechanism and the second mounting portion. [Figure 26] FIG. 26 is a plan view of the sides of the sliding mechanism, first mounting portion, and second mounting portion seen in FIG. 25 when assembled, illustrating the axial (vertical) gap between the sliding mechanism and the second mounting portion. [Figure 27] 1 is a partial top perspective view of a base station illustrating one or more connecting antennas and one or more fiducials supported on the roof section. FIG. [Figure 28] FIG. 2 is a partial top perspective view of a base station according to an embodiment of the present disclosure including multiple fiducials on a roof section. [Figure 29] FIG. 2 is a partial front perspective view of a base station illustrating a status indicator. [Diagram 30] FIG. 2 is a partial top perspective view of a base station according to an embodiment of the present disclosure including a lighting system on a roof section. [Figure 31A] FIG. 13 is a partial front perspective view of the base station during movement of the cradle into a retracted position after docking of the UAV. [Figure 31B] A partial front perspective view of the base station during movement of the cradle to a retracted position after docking of the UAV, illustrating one embodiment of a contact member configured to facilitate reconfiguration (e.g., folding) of one or more antennas on the UAV. [Diagram 32] FIG. 2 is a partial top plan view of a base station and a UAV shown in a flight configuration. [Diagram 33] FIG. 2 is a plan view of the top surface of a UAV shown separated from a base station. [Figure 34A] FIG. 2 is a plan view of the top surface of the UAV shown in a stored configuration with the propeller assemblies shown in one orientation. [Figure 34B] FIG. 2 is a plan view of the top surface of the UAV shown in a stored configuration with the propeller assemblies shown in another orientation. [Figure 34C] FIG. 2 is a plan view of the top surface of the UAV shown in a stored configuration with the propeller assemblies shown in another orientation. [Fig. 34D] FIG. 2 is a partial front perspective view of a base station and a UAV during retraction of the UAV into the base station according to one embodiment of the present disclosure. [Diagram 35] 1 is a partial top plan view of a UAV illustrating a desired range of positions for a propeller assembly of the UAV in a stored configuration. [Diagram 36]FIG. 13 is a partial end view of a base station with a door shown in an open position according to one embodiment of the disclosure, including an engagement member (e.g., a bumper) supported by an actuator and configured to contact a propeller assembly to facilitate reconfiguration of the UAV to a storage configuration. [Figure 37] FIG. 2 is a partial side plan view of the base station and one of the engagement members. [Figure 38] FIG. 13 is an end view of one of the engagement members shown separated from the base station. [Figure 39] FIG. 2 is a partial side plan view of a base station illustrating the (angular) range of motion of the door. [Diagram 40] FIG. 13 is a partial side plan view of a base station illustrating the (angular) range of motion of the actuators and engagement members. [Diagram 41] 1 illustrates a method for reconfiguring (e.g., folding) a propeller assembly of a UAV. [Diagram 42] FIG. 13 is a plan view of the top surface of one of the propeller assemblies illustrating contact with one of the engagement members. [Diagram 43] FIG. 43 is a plan view of the top of the propeller assembly and engagement member seen in FIG. 42 during folding of the propeller assembly. [Diagram 44] FIG. 44 is an enlarged view of the area of ​​detail identified in FIG. 43. [Diagram 45] FIG. 13 is a side plan view of an alternative embodiment of a base station in which an engagement member is carried by a door. [Figure 46] FIG. 46 is a plan view of the end of the base station seen in FIG. [Figure 47] 1 is a schematic diagram of one side of a base station temperature control system including a first air circuit, a second air circuit, and a thermoelectric conditioner (TEC). [Figure 48] FIG. 1 is a schematic diagram of the other side of a base station temperature control system including a first air circuit; a second air circuit; and a thermoelectric conditioner (TEC). [Figure 49] FIG. 13 is a schematic side view of a portion of the cradle and second air circuit. [Figure 50]FIG. 2 is a partial side schematic diagram of a temperature control system. [Figure 51] 1 is a schematic partial side view of a temperature control system illustrating a first heat sink and a second heat sink. [Figure 52] FIG. 2 is a partial side schematic view of a first heat sink and a second heat sink shown positioned within a plenum of a second air circuit. [Figure 53A] 1 is a schematic diagram of a partial top view of a base station according to an embodiment of the present disclosure including one or more heating elements on a roof section. [Figure 53B] FIG. 53B is a schematic diagram of a partial bottom view of a base station illustrating heating elements on the roof section seen in FIG. 53A. [Figure 54] FIG. 2 is a front plan view of the base station shown nested within the pedestal. [Figure 55] FIG. 55 is a side perspective view of the base station and pedestal seen in FIG. 54, with the base station shown in the raised position. [Figure 56] FIG. 2 is a rear perspective view of an isolation cradle according to one embodiment of the present disclosure. [Figure 57] FIG. 57 is a rear perspective view of the isolation cradle seen in FIG. 56, with parts separated. [Figure 58] FIG. 13 is a side perspective view illustrating the mating of the isolation cradle with the plenum of the second air circuit. [Figure 59] FIG. 2 is a partial rear perspective view of a base station according to one embodiment of the present disclosure including multiple heating elements affixed to an inner surface of a housing. [Figure 60] FIG. 2A (Front) is a partial front perspective view of the base station with the door shown in the open position. [Figure 61] 1 is a partial rear perspective view of a base station according to one embodiment of the disclosure including a thermal interface material located between a housing and a heating element. [Figure 62] FIG. 13 is a front perspective view of a base station according to one embodiment of the disclosure, where the status indicator is configured to heat the door and / or a sealing member carried by the housing and is configured to engage the door. [Figure 63] 13 is a partial front perspective view of an alternative embodiment of a base station including a thermally conductive member embedded within the door and / or sealing member. FIG. [Figure 64] FIG. 2 is a schematic diagram of a partial top view of a base station illustrating an internal fan. [Figure 65] 1 is a partial rear perspective view of a base station illustrating one or more channels for collecting and directing water. FIG. [Figure 66] FIG. 1 is a top perspective view of a UAV shown connected to a base station charging hub, which includes a base body; an alignment bracket; one or more biasing members; a charging member; and a cap. [Figure 67] FIG. 1 is a partial top plan view of the UAV and charging hub, shown with the cap removed. [Figure 68] FIG. 1 is a top perspective view of the charging hub shown separated from the UAV. [Figure 69] FIG. 2 is a front plan view of the charging hub. [Figure 70] FIG. 2 is a plan view of the rear of the charging hub. [Figure 71A] A longitudinal cross-sectional view of the UAV and charging hub taken along line 71A-71A of Figure 66, with the alignment bracket shown in the normal position. [Figure 71B] FIG. 1 is a longitudinal cross-sectional view of the UAV and charging hub with the alignment bracket shown in a deflected position. [Figure 72] FIG. 2 is a partial longitudinal cross-sectional view of a charging hub. [Figure 73] FIG. 2 is a partial longitudinal cross-sectional view of the charging hub shown with the charging members removed. [Figure 74] FIG. 2 is a plan view of the top surface of the charging hub shown with the cap removed. [Figure 75] FIG. 1 is a plan view of the top surface of a charging hub according to one embodiment of the present disclosure, including a pair of biasing members. [Figure 76] FIG. 2 is a plan view of the rear of the base station. [Figure 77] FIG. 2 is a front perspective view of a (first) electronic module included in a base station. [Figure 78] FIG. 78 is a front perspective view of the electronic module seen in FIG. 77 with parts separated. [Figure 79] FIG. 78 is a front perspective view of the electronic module seen in FIG. 77 shown with an air circulation module. [Figure 80] FIG. 78 is a rear perspective view illustrating the connection of the electronic module seen in FIG. 77. [Figure 81] FIG. 78 is a plan view of the rear of the base station when the electronic module seen in FIG. 77 is connected. [Figure 82] FIG. 2 is a front perspective view of the base station shown with the air circulation module connected. [Figure 83] FIG. 2 is a perspective view of the rear of the base station with the rear door shown in the open position. [Figure 84] FIG. 2 is a front perspective view of the rear door of the base station. [Figure 85] FIG. 2 is a partial top perspective view of a base station illustrating a (second) electronic module. [Figure 86] FIG. 86 is a partial side perspective view of a base station illustrating the electronic module seen in FIG. [Figure 87] FIG. 86 is a front perspective view of the base station illustrating the electronic module seen in FIG. [Figure 88] FIG. 13 is a partial front perspective view of a base station illustrating the (third) electronic module. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0039] Summary The present disclosure relates to a base station for use with a UAV that is configured to charge the UAV's power source as well as regulate the temperature of the UAV's power source. In various embodiments of the present disclosure, depending on environmental conditions, the base station may be configured to cool the UAV's power source (e.g., when the base station and UAV are used in a hot environment) or heat the UAV's power source (e.g., when the base station and UAV are used in a cold environment).

[0040] To facilitate cooling and / or heating of the UAV's power source, the base station includes a temperature control system. The temperature control system includes: a thermoelectric conditioner (TEC); a first air circuit thermally connected to the TEC and configured to regulate (e.g., increase or decrease) a temperature of the TEC; and a second air circuit thermally connected to the TEC such that the TEC is located between the first air circuit and the second air circuit. The second air circuit is configured to direct treated air (e.g., cooled or heated air) across the UAV's power source, thereby heating or cooling (depending on environmental conditions) the power source.

[0041] To increase the functionality and improve operation of the base station, the base station includes a number of additional (auxiliary) systems configured to address environmental concerns (e.g., humidity, precipitation, etc.), security concerns (e.g., anti-theft systems and mechanisms), etc. For example, the base station may include: a heating element supported by the roof section to reduce the presence of snow and / or ice; one or more fiducials to facilitate visual identification of the base station by the UAV; a lighting system to improve visibility of the one or more fiducials (e.g., during nighttime operation); and a visualization system (e.g., a digital image capture device) to support observation and visual analysis of the environment in which the base station and UAV are located.

[0042] The base station includes a cradle configured to receive the UAV during docking and extendable from and retractable into the base station via a sliding mechanism. In an embodiment of the present disclosure, the sliding mechanism is (indirectly) connected (fixed) to the base station (e.g., a sheet metal substrate) via first and second mountings, which isolate the sliding mechanism from the base station to reduce vibrations (and other such movements) of the sliding mechanism during extension and retraction.

[0043] In an embodiment of the present disclosure, upon docking of the UAV with the base station, the propeller assemblies on the UAV may be reconfigured (e.g., folded) from an extended configuration to a folded configuration, thereby enabling a reduction in the overall size of the base station as well as reducing (if not completely preventing) undesired contact with the propeller assemblies. To facilitate such reconfiguration, the base station includes an engagement member that may be supported by (connected to) the base station's (front) door, a door actuator, or any other suitable structure, configured to contact the propeller assemblies to facilitate their folding. More specifically, during retraction of the cradle and UAV into the base station, the propeller assemblies are bidirectionally rotated to fold into contact with the engagement member.

[0044] 1 and 2 illustrate an unmanned aerial vehicle (UAV) 10 and a base (docking) station 100 configured for automated servicing (e.g., docking, storing, charging, operating, etc.) and housing of the UAV 10. While a single UAV 10 and a single base station 100 are shown and described herein, it is contemplated that in certain embodiments of the present disclosure, multiple UAVs 10 and multiple base stations 100 may be utilized depending, for example, on the particular intended use of the UAV 10.

[0045] UAV UAV 10 includes one or more propulsion systems 12 and a power source 14 (e.g., battery 16). To support autonomous landing and docking of UAV 10 with base station 100, it is contemplated that UAV 10 may follow any suitable process or procedure and include any suitable electrical and / or logical components, such as those described in U.S. patent application Ser. No. 16 / 991,122 (the "'122 Application"), the entire contents of which are incorporated herein by reference.

[0046] The propulsion mechanism 12 may include any components and / or structures suitable for the intended purpose of supporting flight of the UAV 10. For example, in the particular embodiment of the UAV 10 seen in FIG. 2 and FIG. 32, the propulsion mechanism 12 is configured as a propeller assembly 18 including: a propeller arm 38; a (rotatable) hub 40 supported by the propeller arm 38; and a plurality of propeller blades 42 connected (fixed) to the hub 40, either directly or indirectly (operably). More specifically, the hub 40 includes a motor 44 (or other such drive mechanism), a rotatable drive shaft 46 connected to the motor 44, and a plurality of supports 48 connected to (and extending between) the drive shaft 46 and the propeller blades 42, such that rotation of the drive shaft 46 causes corresponding rotation of the propeller blades 42. However, it should be understood that the particular configuration and / or components of the propulsion mechanism 12 may vary without departing from the scope of the present disclosure. FIG. 3, for example, illustrates an alternative configuration of the UAV 10.

[0047] In the particular embodiment of the illustrated UAV 10, the UAV 10 includes four propeller assemblies 18. More specifically, the UAV 10 includes: a (first) rear propeller assembly 18ri; a (second) rear propeller assembly 18rii; a (first) front propeller assembly 18fi; and a (second) front propeller assembly 18fii. 2, the rear propeller assemblies 18ri, 18rii and the front propeller assemblies 18fi, 18fii are oriented in opposite (vertical) directions (e.g., the rear propeller assemblies 18ri, 18rii are oriented (vertically) upward and the front propeller assemblies 18fi, 18fii are oriented (vertically) downward), such that the rear propeller assemblies 18ri, 18rii are positioned at a first vertical location (e.g., height) and the front propeller assemblies 18fi, 18fii are positioned at a second, lower vertical location (e.g., height). However, it should be understood that the particular number of propeller assemblies 18, the configuration of the propeller assemblies 18, the location of the propeller assemblies 18, and / or the orientation of the propeller assemblies 18 may vary in alternative embodiments without departing from the scope of the present disclosure. Accordingly, embodiments of UAV 10 including both fewer and greater numbers of propeller assemblies 18 are also contemplated herein and do not fall beyond the scope of this disclosure.

[0048] It is contemplated that the propeller assembly 18 may include fixed or variable configurations. For example, it is contemplated that the propeller assembly 18 may be reconfigurable between an extended (first) configuration and a folded (folded, second) configuration to facilitate a reduction in the overall size of the UAV 10 (e.g., during approach to the base station 100) and thus the overall size of the base station 100, as described in further detail below. To facilitate the reconfiguration of the propeller assembly 18 between the extended and folded configurations, in certain embodiments, it is contemplated that the propeller blades 42 may be pivotally connected to the support 48 via pivot members 50 (FIGS. 32, 42-44) (e.g., pins, struts, etc.) to facilitate folding of the propeller assembly 18, as described in further detail below.

[0049] The power source 14 is located (e.g., mounted or otherwise supported) on an underside (bottom) surface of the UAV 10 and includes one or more conductive (electrical) contacts (not shown) configured to engage (contact) one or more corresponding conductive (electrical) contacts on the base station 100 to enable charging of the power source 14, as described in more detail below.

[0050] Heat exchange As seen in Figures 4 and 5, the power source 14 includes one or more batteries 20; one or more heat transfer members 22; and a heat exchanger 24 that defines a lower (bottom) surface of the power source 14 and acts as a cover for the batteries 20 and the heat transfer member 22. The heat transfer member 22 and the heat exchanger 24 are configured to facilitate the transfer of thermal energy between the power source 14 and the surroundings (air) to reduce or increase the temperature of the power source 14. For example, depending on the particular environment in which the UAV 10 and the base station 100 are employed, the heat transfer member 22 and the heat exchanger 24 may be utilized to dissipate heat generated by the power source 14 during use and / or charging of the UAV 10 (e.g., in a hot environment) or to transfer heat to the power source 14 (e.g., in a cold environment), thereby improving the efficiency, operation, and / or service life of the UAV 10 and / or the power source 14.

[0051] In the particular embodiment illustrated, the power source 14 includes a plurality of individual (e.g., discrete) batteries 20. However, it should be understood that the particular number and / or configuration of batteries 20 may vary in alternative embodiments without departing from the scope of the present disclosure. For example, embodiments of the power source 14 including a single battery 20 are also contemplated herein.

[0052] The heat transfer member 22 is thermally connected to and extends between the batteries 20 and the heat exchanger 24. In the particular embodiment of the present disclosure illustrated, the power source 14 includes a plurality of individual (e.g., discrete) heat transfer members 22, each of which is associated with (e.g., thermally connected to) a corresponding battery 20 (e.g., such that the power source 14 includes a corresponding (equal) number of batteries 20 and heat transfer members 22). However, it should be understood that the particular number of heat transfer members 22 may vary in alternative embodiments without departing from the scope of the present disclosure, and that embodiments of the power source 14 including unequal numbers of batteries 20 and heat transfer members 22 are also contemplated herein. For example, the present disclosure contemplates embodiments in which the number of batteries 20 may exceed the number of heat transfer members 22 (e.g., embodiments in which the power source 14 includes a single heat transfer member 22 extending between the collection of batteries 20 and the heat exchanger 24), as well as embodiments in which the number of heat transfer members 22 may exceed the number of batteries 20.

[0053] The heat transfer members 22 may include (e.g., may be formed partially or entirely of) any material or combination of materials that is suitable for the intended purpose of transferring heat between and thermally connecting the batteries 20 and the heat exchanger 24. For example, in one particular embodiment, it is contemplated that the heat transfer members 22 may include (e.g., may be formed partially or entirely of) graphite. However, it should be understood that the use of other materials does not go beyond the scope of the present disclosure. In addition, while each heat transfer member 22 is shown as being of unitary construction (i.e., formed from a single piece of material), in alternative embodiments of the present disclosure, it is contemplated that each heat transfer member 22 may include a series of individual segments that are connected to each other during manufacture, assembly of the power source 14, or at any other suitable time.

[0054] Heat exchanger 24 is thermally connected to heat transfer member 22 and is configured to communicate and distribute thermal energy between power source 14 and the surroundings (air) away from power source 14 (e.g., when used in a hot environment) or toward power source 14 (e.g., when utilized in a cold environment), and may include (e.g., be formed partially or entirely from) any material or combination of materials suitable for its intended purpose. For example, it is contemplated that heat exchanger 24 may include (e.g., be formed partially or entirely from) aluminum, magnesium, copper, etc.

[0055] To increase the available surface area and thus the distribution of thermal energy (towards or away from the power source 14), in certain embodiments as illustrated throughout the figures, the heat exchanger 24 may include one or more diffusers 26, which may be configured in any manner appropriate for its intended purpose. For example, it is contemplated that the diffusers 26 may be configured as pins, protrusions, ribs, or other such surface irregularities and may extend axially (e.g., along a longitudinal axis Y) and / or laterally (e.g., along a transverse axis X) along the outer (bottom) surface 28 of the heat exchanger 24. In the particular embodiment of the heat exchanger 24 illustrated throughout the figures, for example, the diffusers 26 are configured as fins 30 that define a plurality of channels 32 therebetween that collectively direct the flow of air along the heat exchanger 24 to further increase the distribution of thermal energy.

[0056] While the particular embodiment of the present disclosure illustrated is shown as including multiple diffusers 26 and channels 32, it should be understood that the particular number of diffusers 26 and / or channels 32 may vary in alternative embodiments without departing from the scope of the present disclosure. For example, embodiments of the heat exchanger 24 including a single diffuser 26 are also contemplated herein.

[0057] base station structure Now, referring also to Figures 4-26, the base station 100 includes: a housing (body) 102 having a front end 102a and a rear end 102b; a (front) door 104 movably connected to the housing 102 (at the front end 102a); and a cradle 106 configured to receive (house) the UAV 10.

[0058] The enclosure 102 includes an inner housing (shell) 108 and an outer housing (cover) 110. The respective inner and outer housings 108, 110 are configured as separate discrete structures that may be connected to one another in any suitable manner, whether fixed or removable (e.g., to allow for repeated assembly and disassembly of the base station 100 during maintenance, repair, etc.). For example, it is contemplated that the respective inner and outer housings 108, 110 may be connected via a number of mechanical fasteners (e.g., screws, pins, bolts, clips, etc.), which may be concealed (or otherwise obscured from view) to discourage theft and / or unauthorized disassembly of the base station 100.

[0059] The inner housing 108 defines an interior cavity 112 and a window 113, each of which is configured to receive and accommodate the UAV 10 and allow for the UAV 10 to enter and exit the base station 100. Additionally, the inner housing 108 provides mounting surfaces for various components of the base station 100, including, for example, electrical components, actuators, etc., that are connected (bonded, mounted) to the inner housing 108 and support operation of the base station 100.

[0060] As described in more detail below, the outer housing 110 protects the inner housing 108 and various components connected thereto (e.g., from ingress of dust, debris, moisture and / or water, etc.), supports various external components of the base station 100, and provides structural support to the base station 100. For example, in the particular embodiment illustrated, the outer housing 110 comprises a sheet metal structure. However, it should be understood that embodiments of the base station 110 in which the outer housing 110 may comprise one or more alternative materials are also contemplated herein.

[0061] To facilitate access to the various components housed within the outer housing 110 (and / or inner housing 108), in certain embodiments, the outer housing 110 may include an access panel 114 ( FIG. 7 ) to support maintenance, repair, and the like, which is contemplated as being incorporated in any suitable location. For example, in the particular embodiment illustrated, the access panel 114 is located at the rear end 102b of the enclosure 102 (e.g., outer housing 110). However, it should be understood that the particular location of the access panel 114 may vary in alternative embodiments without departing from the scope of the present disclosure (e.g., the access panel 114 may be located on the side of the base station 100 rather than at the rear end 102b).

[0062] In certain embodiments of the present disclosure, it is contemplated that the outer housing 110 may include exterior coloring that not only reduces solar loading (heating), as described in further detail below, but also promotes contrast to facilitate visualization and / or identification of the base station 100 by the UAV 10 during docking.

[0063] The door 104 is movably connected to the outer housing 110 such that the door 104 is repositionable between a (fully) closed position ( FIG. 1 ), which conceals the interior cavity 112 and the window 113, and an open position ( FIG. 6 ), in which the interior cavity 112 and the window 113 are exposed. More specifically, the door 104 is movably connected to a front frame 116 of the outer housing 110. While illustrated as pivotally connected to the front frame 116 in the particular embodiment illustrated throughout the figures, it is also envisioned that the door 104 may be slidably repositionable between a closed position and an open position in alternative embodiments of the present disclosure.

[0064] As described below, the metal (e.g., sheet metal) construction of the outer housing 110, and thus the front frame 116, allows the front frame 116 to conduct and facilitate the transfer of thermal energy in both hot and cold environments. More specifically, in hot environments the front frame 116 can operate as a heat sink, drawing thermal energy (heat) away from thermally sensitive components of the base station 100, and in cold environments the front frame 116 can operate as a thermal conduit, directing thermal energy (heat) towards certain components of the base station 100 to facilitate their heating.

[0065] To facilitate movement of the door 104 between the closed and open positions, the base station 100 includes one or more actuators 118 (FIGS. 8-10) extending between the door 104 and the housing 102. Although the particular embodiment illustrated is shown as including first and second actuators 118i, 118ii, respectively, connected (bonded) to opposing lateral ends of the door 104 such that the actuators 118i, 118ii are laterally spaced apart from one another along the width W of the housing 102, it should be understood that the present disclosure also contemplates embodiments in which a single actuator 118 may be utilized to control the position of the door 104 (e.g., to reduce the overall cost and complexity of the base station 100).

[0066] Each actuator 118 includes a motor assembly 120 (e.g., a stepper motor) and a linkage assembly 122 that extends between the motor assembly 120 and the door 104. More specifically, each motor assembly 120 is connected (secured) to the inner housing 108 such that the motor assembly 120 is located between the inner housing 108 and the outer housing 110, which protects the motor assembly 120 and inhibits the collection of any dust, debris, etc. The linkage assembly 122 extends from the motor assembly 120 through the inner housing 108 and pivotally engages the door 104 such that when the motor assembly 120 is actuated, the linkage assembly 122 applies a force to the door 104, thereby facilitating movement of the door 104 between a closed position and an open position.

[0067] Each linkage assembly 122 includes: a (threaded) drive screw 124; a carrier 126; a first arm 128; and a second arm 130. The drive screw 124 is operatively connected to the motor assembly 120 such that actuation of the motor assembly 120 rotates the drive screw 124. The carrier 126 is threadably engaged to the drive screw 124 such that rotation of the drive screw 124 translates the carrier 126 axially. More specifically, rotation of the drive screw in a first direction (e.g., clockwise) advances the carrier 126 forward (e.g., moves the carrier 126 toward the door 104) and rotation of the drive screw in a second direction (e.g., counterclockwise) advances the carrier 126 rearward (e.g., moves the carrier 126 away from the door 104). The first arm 128 includes a first end 132 that is pivotally connected (fixedly or pivotally) to the carrier 126 and a second end 134 that is pivotally connected to a second arm 130. The second arm 130 includes a first end 136 that is pivotally connected to the second end 134 of the first arm 128 and a second end 138 that is pivotally connected to a bracket 140. The bracket 140 is fixedly connected to the door 104 and allows for the transfer of force from the carrier 126 to the door 104 via the arms 128, 130.

[0068] The cradle 106 defines respective (first and second) front ends 106a, rear ends 106b (FIGS. 2, 10, 13), and a chamber 142 (FIG. 10) configured to receive the UAV 10 during docking to facilitate (support) charging of the power source 14. More specifically, the base station 100 includes a charging hub (assembly) 143 (FIGS. 10, 66-75) configured to engage and electrically connect with the power source 14 upon receiving the UAV 10 within the chamber 142, thereby charging the power source 14, as described in further detail below. To facilitate proper docking of the UAV 10 with a proper electrical interface between the power source 14 and the charging hub 143, the cradle 106 defines a sidewall 146 that tapers inwardly toward the chamber 142 to define an angled guiding surface 148 (FIG. 10). The angled guiding surface 148 is configured to engage (contact) the UAV 10 to orient the UAV 10 into the chamber 142 to facilitate placement of the UAV 10 in the cradle 106 .

[0069] The cradle 106 is movable between a (fully) retracted position (FIGS. 2, 10) in which the cradle 106 (and UAV 10) is positioned within the housing 102 (e.g., within the internal cavity 112), a number of partially retracted positions, described in more detail below, and an extended position (FIG. 13) in which the cradle 106 (and UAV 10) is positioned outside the housing 102 to facilitate docking with the UAV 10, thereby allowing the UAV 10 to be moved in and out of the housing 102. To support movement between the extended and retracted positions (extended and retracted), the cradle 106 is connected to a telescoping slide mechanism 150, which is also movable between extended and retracted positions corresponding to those of the cradle 106. The sliding mechanism 150 extends through a window 152 (FIG. 1) defined by a bezel portion 154 of the front frame 116 and supports a cap (hatch, cover) 156 (FIGS. 1, 8, 11, 12) configured to correspond to the window 152. The cap 156 is movably (e.g., pivotally) connected to (supported by) the enclosure 102 (e.g., the front frame 116 of the outer housing 110) such that the cap 156 is movable between a closed position (FIGS. 6, 11, 12) and an open position (FIGS. 1, 8) when the cradle 106 (and the sliding mechanism 150) moves between a retracted position and an extended position, respectively. More specifically, when the cradle 106 (and sliding mechanism 150) moves from the retracted position to the extended position, the cap 156 moves from the closed position to the open position, and when the cradle 106 (and sliding mechanism 150) moves from the extended position to the retracted position, the cap 156 moves from the open position to the closed position, thereby engaging the bezel portion 154 and being received within the window 152.

[0070] In certain embodiments of the present disclosure as illustrated throughout the figures, the cap 156 may include an upstanding tab 158 (FIG. 11) configured to be received within a corresponding recess 160 (FIGS. 8, 12) defined in an interior surface 162 of the door 104. Receiving the tab 158 within the recess 160 not only allows for proper closure of the door 104, but also allows the door 104 to overlap the cap 156 when closed to facilitate sealing of the housing 102 and to inhibit (if not completely prevent) the ingress of dust, debris, and the like through the door 104 and / or bezel portion 154. Additionally, the engagement between the bezel portion 154, the sliding mechanism 150, and the door 104 (e.g., receiving the tab 158 via the recess 160) improves security of the base station 100 by inhibiting access to the cradle 106 and thus the UAV 10.

[0071] The sliding mechanism 150 includes a fixed sliding member 151a (FIG. 13) supported by the housing 102, and a movable sliding member 151b slidably supported by the fixed sliding member 151a so that the sliding mechanism 150 can be telescopically moved between an extended position and a retracted position (corresponding to the extended position and the retracted position of the cradle 106). As seen in FIG. 13, it is envisioned that the fixed sliding member 151a may be positioned around the movable sliding member 151b such that the movable sliding member 151b is received by the fixed sliding member 151a, or the movable sliding member 151b may be positioned around the fixed sliding member 151a such that the fixed sliding member 151a is received by the movable sliding member 151b.

[0072] In alternative embodiments of the present disclosure, it is contemplated that the sliding mechanism 150 may be directly or indirectly (operably) connected (fixed) to the housing 102. For example, in one embodiment, it is contemplated that the sliding mechanism 150 (e.g., the fixed sliding member 151a) may be directly and fixedly (e.g., immovably) connected (fixed) to a plurality of studs 262 (FIGS. 14, 17, 21) that extend (vertically) upward (e.g., toward the sliding mechanism 150) from a sheet metal base 264 of the housing 102 and are configured to be inserted into openings (apertures) 266 (FIGS. 17, 24, 25) of the sliding mechanism 150. Alternatively, it is envisioned that the sliding mechanism 150 (e.g., fixed sliding member 151a) may be indirectly (operably) connected (fixed) to the housing 102 via a number of mountings 268 (FIGS. 14-26) located between the housing 102 (e.g., sheet metal base 264) and the sliding mechanism 150. As described in more detail below, the positioning of the mountings 268 between the housing 102 and the sliding mechanism 150 physically separates the sliding mechanism 150 from the housing 102, thereby reducing the stiffness of the interface therebetween. Physically separating the sliding mechanism 150 from the housing 102 also increases the tolerance for relative movement (deflection) between the housing 102 and the sliding mechanism 150 during extension and retraction, reducing (resonant) vibration of the sliding mechanism 150, which in turn reduces undesirable movement (e.g., shaking, jittering, etc.). In a particular embodiment of the base station 100 illustrated in FIGS. 14-26, the sliding mechanism 150 is connected (fixed) to the housing 102 via a plurality of first mounting portions 268i and a plurality of second mounting portions 268ii. The mounting portions 268i, 268ii are each configured to receive one of the studs 262 extending from the base 264 of the housing 102 and include different (e.g., non-identical) configurations (e.g., the mounting portion 268i includes a first configuration and the mounting portion 268ii includes a second, different configuration), as described in more detail below. More specifically, the mounting portions 268i are each configured to receive a first stud 262i (FIG. 22) that defines a first length LSi, and the mounting portions 268ii are each configured to receive a second stud 262ii (FIGS. 17, 18, 24) that defines a second length LSii (FIG. 24).

[0073] The mounting portion 268i defines opposing (first and second) ends 270, 272 (FIGS. 19, 21) having (first and second) female and male interfaces 274, 276, respectively, and each includes: a (first) bushing (body, body portion) 278; a shank 280; and a (first) fastener 282 (FIGS. 18, 22, 25). In the particular embodiment illustrated in FIGS. 14-26, the base station 100 includes six mounting portions 268ia-268if. More specifically, the mountings 268ia-268id are located at corner sections (regions) 284i-284iv of the sliding mechanism 150, respectively, with one mounting 268ie located between the corner sections 284i and 284ii (e.g., such that the corner sections 284i, 284ii are spaced equidistant (or approximately equidistant) from the mounting 268ie) and one mounting 268if located between the corner sections 284iii and 284iv (e.g., such that the corner sections 284iii, 284iv are spaced equidistant (or approximately equidistant) from the mounting 268if). However, it should be understood that the specific number of mountings 268i may vary in alternative embodiments without departing from the scope of the present disclosure (e.g., depending on the specific configuration of the base station 100, the sliding mechanism 150, etc.). Thus, embodiments including both greater and lesser numbers of mountings 268i are contemplated herein and do not exceed the scope of the present disclosure.

[0074] The bushing 278 includes (e.g., is partially or entirely formed from) a flexible material to separate (axially) the interfaces 274, 276 along the longitudinal axis Y1 of the mounting portion 268i to reduce vibration, wobble, jittering, and the like, and to absorb forces that arise during extension and retraction of the sliding mechanism 150. At the end 270, the bushing 278 defines an opening 286, which defines a female interface 274 and is configured to receive one of the studs 262i to facilitate connection of the bushing 278 to the housing 102 (e.g., via the stud 262i). More specifically, as seen in FIG. 22, the opening 286 extends into the bushing 278, rather than through it, such that the stud 262ii extends partially into the bushing 278.

[0075] In the particular embodiment illustrated, the opening 286 includes threads 288 that are configured to engage corresponding threads 290 ( FIG. 22 ) on the stud 262i such that the bushing 278 threadably engages (contacts) the sheet metal substrate 264 of the housing 102 (via the stud 262i). However, it is contemplated that the mounting portion 268i and the housing 102 may be configured to engage in any suitable manner. For example, in alternative embodiments of the present disclosure, it is contemplated that the threads 288, 290 may be omitted and the mounting portion 268i and the stud 262i may be configured to engage in a press-fit (interference fit) arrangement.

[0076] The shank 280 defines a male interface 276 and extends (vertically) upwardly (e.g., away from the sheet metal substrate 264) from the bushing 278 such that the shank 280 is insertable into one of the openings 266 (FIGS. 17, 24, 25) of the sliding mechanism 150. The shank 280 is configured to (releasably) connect (engage) to a fastener 282 (FIGS. 18, 22, 25) such that the sliding mechanism 150 is secured between the bushing 278 and the fastener 282. More specifically, in the particular embodiment illustrated, the shank 280 and the fastener 282 include corresponding threads 292, 294. However, it is envisioned that the shank 280 and the fastener 282 may be configured to engage (e.g., inhibit (if not entirely prevent) relative movement therebetween) in any suitable manner for the intended purpose of securing the mounting portion 268i and the sliding mechanism 150 to one another. For example, it is contemplated that in alternative embodiments, the threads 292, 294 may be omitted and the shank 280 and fastener 282 may be configured to engage in a press-fit (interference fit) arrangement.

[0077] 16-22, the mounting portion 268i is configured such that the bushing 278 is in direct contact with the housing 102 (e.g., the sheet metal base 264) and the sliding mechanism 150. Alternatively, however, it is contemplated that the mounting portion 268i may be configured such that the bushing 278 is separated from the housing 102 (e.g., the sheet metal base 264) and / or the sliding mechanism 150. For example, FIG. 26 illustrates an embodiment in which the mounting portion 268i includes an intermediate member 296 (e.g., a washer 298, an O-ring, etc.) located between the bushing 278 and the sliding mechanism 150.

[0078] Due to the flexible structure of the bushing 278, during repositioning of the sliding mechanism 150 between the retracted and extended positions, the mounting portion 268i undergoes deformation (e.g., expansion and contraction) in the lateral (radial) direction identified by arrow 1 (FIGS. 18, 21) and / or the axial (vertical) direction identified by arrow 2. The lateral and / or axial deformation permitted by the mounting portion 268i allows for relative movement between the sliding mechanism 150 and the housing 102 (e.g., the sheet metal substrate 264), thereby not only eliminating a direct rigid connection therebetween, but also damping (absorbing) vibrations during repositioning of the sliding mechanism 150 so as to increase predictability, consistency, and / or uniformity in the movement of the sliding mechanism 150.

[0079] The mounting portion 268ii defines opposing (first and second) ends 300, 302 and includes a (second) bushing (body, body portion) 304 having a base 306 and an axial portion 308 extending therefrom; a channel 310; and a (second) fastener 312. In the particular embodiment illustrated in Figures 14-26, the base station 100 includes four mounting portions 268ii. More specifically, the base station 100 includes four mounting portions 268iia-268iid located adjacent (or generally adjacent) to mounting portions 268ia-268id of the corner sections 284i-284iv of the sliding mechanism 150, respectively. However, it should be understood that the particular number of mounting portions 268ii may vary in alternative embodiments without departing from the scope of the present disclosure (e.g., depending on the particular configuration of the base station 100, sliding mechanism 150, etc.). Accordingly, embodiments including both larger and smaller numbers of mounting portions 268ii are contemplated herein and do not go beyond the scope of this disclosure.

[0080] In the particular embodiment illustrated, the bushing 304 includes (e.g., is partially or entirely formed of) a flexible material to further facilitate absorption of forces by the mounting portion 268ii and further reduce vibration of the sliding mechanism 150 during extension and retraction. However, embodiments of the base station 100 in which the bushing 304 may include a non-compliant material are also contemplated herein and do not go beyond the scope of this disclosure.

[0081] The base 306 defines a first cross-sectional dimension (e.g., diameter) D1 (FIG. 24), and the shank 308 defines a second cross-sectional dimension (e.g., diameter) D2 that is less than the first cross-sectional dimension D1, such that the bushing 304 includes (defines) a non-uniform, stepped cross-sectional configuration that varies along the longitudinal axis Y2 of the mounting portion 268ii. More specifically, the shank 308 is configured to be inserted into one of the openings 266 (FIGS. 17, 24, 25) of the sliding mechanism 150, which defines a third cross-sectional dimension (e.g., diameter) D3 (FIG. 25) that is less than the first cross-sectional dimension D1 and greater than the second cross-sectional dimension D2, such that the base 306 is positioned (located) between the housing 102 (e.g., sheet metal substrate 264) and the sliding mechanism 150. The difference between the cross-sectional dimensions D2 and D3 defined by the shaft 308 and the opening 266, respectively, results in a lateral (radial, horizontal) gap G1 (FIG. 25) therebetween. For example, in the particular embodiment illustrated, the gap G1 is substantially within a range of about 0.5 mm to about 1.5 mm (e.g., about 1 mm). However, gaps G1 outside this range are also contemplated herein and do not go beyond the scope of the present disclosure.

[0082] The channel 310 extends through the bushing 304 and is configured to receive one of the studs 262ii such that the stud 262ii extends through the mounting portion 268ii, thereby facilitating a (releasable) connection (engagement between) the stud 262ii and the fastener 312 such that the sliding mechanism 150 is secured between the bushing 304 and the fastener 312 to restrict (if not entirely prevent) relative movement between the mounting portion 268ii and the housing 102 (e.g., the stud 262ii) while allowing relative movement between the mounting portion 268ii and the sliding mechanism 150, as described in further detail below. For example, it is envisioned that the bushing 304 may be compressibly retained between the fastener 312 and the sheet metal substrate 264 to secure the mounting portion 268i to the housing 102.

[0083] In the particular embodiment illustrated, the fastener 312 includes threads 314 ( FIG. 24 ) configured to engage with threads 290 of the stud 262ii extending through the mounting portion 268ii (via the channel 310). However, it is contemplated that the stud 262ii and fastener 312 may be configured to engage in any suitable manner for the intended purpose described above. For example, in alternative embodiments, it is contemplated that the threads 290, 314 may be omitted and the stud 262ii and fastener 312 may be configured to engage in a press-fit (interference fit) configuration.

[0084] 26, when the fastener 312 is connected to the stud 262ii, an axial (vertical) gap G2 is defined between the fastener 312 and the base 306, which is equivalent to the (vertical) height HS defined by the shaft 308 of the bushing 304. For example, in the particular embodiment illustrated, the gap G2 is (substantially) within the range of (about) 1 mm to (about) 2 mm (e.g., (about) 1.5 mm). However, gaps G2 outside this range are also contemplated herein and do not go beyond the scope of the present disclosure.

[0085] The gaps G1, G2 allow the shaft 308 to be received by the opening 266 of the sliding mechanism 150 in a manner that inhibits (if not completely prevents) contact between (engagement of) the mounting portion 268ii and the sliding mechanism 150 when the sliding mechanism 150 is in a normal state (condition) (e.g., when the sliding mechanism 150 does not move during periods of extension and retraction). The gaps G1, G2 also allow movement of the sliding mechanism 150 relative to the housing 102 and the second mounting portion 268ii, which is further facilitated by the flexible material that comprises the bushing 278 of the first mounting portion 268i, with two degrees of freedom DOF1 (FIGS. 18, 25), DOF2 (FIGS. 18, 26) oriented in an orthogonal (or nearly orthogonal) relationship. More specifically, gaps G1 (FIG. 25), G2 (FIG. 26) allow for a predetermined lateral (radial) and axial (vertical) movement of the sliding mechanism 150 during extension and retraction, respectively, to limit (confine) deformation of the mounting portion 268i (relative to the housing 102 and the second mounting portion 268ii) and movement of the sliding mechanism 150, thereby reducing (if not completely preventing) lateral overtravel (e.g., in degree of freedom DOF1) and axial overtravel (e.g., in degree of freedom DOF2). Limiting the deformation of the mounting portion 268i (relative to the housing 102 and the second mounting portion 268ii) and the movement of the sliding mechanism 150 inhibits (if not completely prevents) damage (e.g., shearing) of the mounting portion 268i and overtravel of the sliding mechanism 150 within the housing 102, thereby reducing (if not completely eliminating) any possibility of undesired contact between the sliding mechanism 150 and various internal components of the base station 100. For example, during docking of the UAV 10, the sliding mechanism 150 may experience (vertical) deflection under the weight of the UAV 10 and / or as a result of forces applied to the cradle 106 during landing. However, such (vertical) deflection (e.g., movement of the sliding mechanism 150 in degree of freedom DOF2) is resisted by the mounting portion 268ii via contact between the sliding mechanism 150 and the fasteners 312, thereby also limiting axial (vertical) deformation of the mounting portion 268i, thus reducing (if not completely preventing) damage to the mounting portion 268i (e.g., excessive stretching, tearing) that might otherwise occur.

[0086] In the particular embodiment of the base station 100 illustrated in Figures 14-26, the mountings 268i and mountings 268ii include non-identical (non-similar) configurations, as described above. However, it should be understood that embodiments of the base station 100 including a single type of mounting 268 are also contemplated herein and do not go beyond the scope of the present disclosure. For example, the present disclosure contemplates an embodiment of the base station 100 that lacks mountings 268ii and exclusively includes mountings 268i.

[0087] In certain embodiments of the present disclosure, it is contemplated that the door 104 and cradle 106 may be automatically actuated upon receiving an incoming / docking signal from the UAV 10. For example, it is contemplated that the incoming / docking signal may automatically engage the actuator 118, thereby opening the door 104. Thereafter, when it is determined that the door 104 is fully opened, which may be accomplished by employment of a Hall sensor (or any other such suitable detection mechanism), the cradle 106 may be extended via (retracting) movement of the sliding mechanism 150.

[0088] Anti-theft and security measures To further improve security of the base station 100, certain embodiments of the present disclosure contemplate that the door 104 may include a locking mechanism. For example, it is contemplated that the door 104 may include a magnetic lock to keep the door 104 closed in the unpowered state to prevent inadvertent and / or unauthorized opening of the door 104 and thus access to the UAV 10.

[0089] Additionally or alternatively, it is contemplated that the actuator 118 (FIGS. 8-10) may be configured to inhibit (if not completely prevent) the transmission of force from the door 104 to the motor assembly 120, thereby maintaining the door 104 closed by resisting the application of (manual) force to the door 104. For example, it is contemplated that the threads defined by the drive screw 124 may have a fine pitch to inhibit (if not completely prevent) the transmission of force applied to the door 104 to the carrier 126, thereby maintaining the door 104 closed. Additionally or alternatively, it is contemplated that the actuator 118 may include a solenoid (or other such mechanism) configured to engage a locking pin (or other such member).

[0090] pedestal 1, in one embodiment, the base station 100 may be configured for use with a pedestal 164 (or other such self-supporting platform) configured to support the base station 100 and the UAV 10 in an elevated position (e.g., on the ground). The base station 100 and the pedestal 164 together define a docking system 165 for the UAV 10 that reduces turbulence (e.g., propeller wash) during takeoff and landing of the UAV 10 as well as creates free space to mitigate the ingress of debris (e.g., dust, particulates, etc.) into the base station 100.

[0091] It is contemplated that in certain embodiments of the docking system 165, the pedestal 164 and the base station 100 may include corresponding engagement structures (e.g., pins and holes, detents and recesses, ribs and slots, footings and channels, etc.) configured to releasably engage (connect) to facilitate proper alignment of the pedestal 164 and the base station 100 and inhibit (if not entirely prevent) unintended separation of the base station 100 from the pedestal 164, such as when the base station 100 and / or the pedestal 164 experience an applied force (e.g., wind gusts, impact with an external object, etc.). In one particular embodiment, it is contemplated that the corresponding engagement structures may include one or more openings and corresponding mechanical fasteners (e.g., bolts, screws, pins, etc.) configured to be inserted into the openings to enable a fixed, releasable connection of the pedestal 164 and the base station 100.

[0092] To discourage (if not completely prevent) unauthorized removal of the base station 100 from the pedestal 164 (e.g., to protect against theft of the base station 100 and / or the pedestal 164), it is contemplated that the pedestal 164 and base station 100 may include corresponding eyelets (or other such openings) configured to receive a lockable tether, chain, cable, rod, or the like.

[0093] Referring also to Figures 54 and 55, the pedestal 164 defines an interior space 334 having an inner contour 336 configured to correspond to the outer contour 338 of the base station 100 (e.g., such that the vertical cross-sectional configuration of the pedestal 164 approximates the vertical cross-sectional configuration of the base station 100). The interior space 334 and corresponding contours 336, 338 defined by the base station 100, respectively, allow the docking system 165 to position the base station 100 within the pedestal 164 when not in use such that the docking system 165 is reconfigurable between a nested (inactive) configuration in which the base station 100 is received by the pedestal 164, as seen in FIG. 54, and a stacked (active) configuration in which the base station 100 (and UAV 10) is supported in an elevated position by the pedestal 164, as seen in FIG. 55, (e.g., so that the base station 100 can be sorted within the interior space 334 to protect the base station 100 during transportation in inclement weather, etc.). As seen in FIG. 54, the pedestal 164 is configured and dimensioned to create a clearance with the base station 100 around the entire perimeter 340 (e.g., outer envelope) of the base station 100, thereby reducing (if not completely preventing) contact between the pedestal 164 and the base station 100.

[0094] In the particular embodiment illustrated, the pedestal 164 is of unitary (e.g., monolithic) construction and is formed from a single piece of material (rigid or semi-rigid) that may be either metallic (e.g., aluminum, sheet metal, steel, etc.) or non-metallic (e.g., plastic, polymeric carbon fiber, etc.). However, in alternative embodiments of the present disclosure, it is contemplated that the pedestal 164 may include a series of individual components connected to each other in any suitable manner (e.g., via one or more mechanical fasteners, by an interference fit, etc.).

[0095] The pedestal 164 includes a trapezoidal (or generally trapezoidal) vertical cross-sectional configuration defining: a top wall 342 having a non-linear configuration; first and second side walls 344, 346 each extending vertically from the top wall 342 and each including a linear (or generally linear) configuration; and first and second bottom walls 348, 350 extending laterally inward from the first and second side walls 344, 346, respectively, and each including a linear (or generally linear) configuration.

[0096] The upper wall 342 includes: a first segment 352i extending laterally inward from the first side wall 344; a second segment 352ii extending laterally inward from the second side wall 346; a third segment 352iii extending parallel (or generally parallel) to segments 352i, 352ii; a fourth segment 352iv extending between segments 352i and 352iii; and a fifth segment 352v extending between segments 352ii and 352iii. While segments 352i, 352ii are vertically aligned (e.g., such that segments 352i, 352ii are positioned at the same (or substantially the same) vertical location), segment 352iii is vertically offset from segments 352i, 352ii to define well 354 (e.g., such that segment 352iii is positioned at a different vertical location than segments 352i, 352ii). The inclusion of well 354 increases the strength and / or rigidity of top wall 342 and creates (vertical) clearance with base station 100 (e.g., antenna 166). Additionally, well 354 is configured to receive power cable 356 ( FIG. 7 ) of base station 100 to inhibit (if not completely prevent) bending, kinking, and / or damage to power cable 356.

[0097] In the particular embodiment illustrated, segments 352iv, 352v define the same (or approximately the same) obtuse angles αi, αii as segments 352i, 352ii, respectively, such that well 354 extends into space (gap) 358 defined between antennas 166. However, it should be understood that the particular configuration of top wall 342 and arrangement of segments 352 may vary in alternative embodiments without departing from the scope of the present disclosure. For example, embodiments are contemplated in which top wall 342 may be configured such that angles αi, αii are equal (or approximately equal) to 90°, as well as embodiments in which angles αi, αii may not be equal, as well as embodiments in which segment 352iii may be vertically aligned with segments 352i, 352ii to eliminate well 354 such that top wall 342 comprises a linear (or approximately linear) configuration.

[0098] To increase stability of the pedestal 164 (e.g., in windy conditions), the side walls 344, 346 are angled relative to the top wall 342 and the bottom walls 348, 350, respectively, such that the bottom walls 348, 350 extend laterally outward (beyond) the top wall 342. More specifically, the side walls 344, 346 are configured to define first and second (acute) angles βi, βii with first and second reference axes Ri, Rii, respectively, which are oriented orthogonal (or generally orthogonal) to the bottom walls 348, 350.

[0099] To further increase stability (e.g., on uneven terrain), it is envisioned that the pedestal 164 may include a number of adjustable footings 360. The footings 360 are configured to removably connect (engage) with the bottom walls 348, 350 and are reconfigurable to level the pedestal 164, and thus the base station 100 (e.g., by shortening and lengthening the footings 360).

[0100] Takeoff, Landing, and Docking 27-31B, the base station 100 includes a number of systems, components, and features that support takeoff of the UAV 10, landing of the UAV 10, and docking of the UAV 10 with the base station 100 after flight. For example, as described below, the base station 100 may include: one or more connection antennas 166; one or more fiducials 168 carried by the housing 102; an illumination system 170 carried by the housing 102; one or more status indicators 172 carried by the housing 102; and a visualization system 174 carried by the housing 102.

[0101] Connecting antenna The base station 100 includes a primary connection antenna 166 that facilitates wireless communication between the base station 100, directly or indirectly, and the UAV 10. For example, it is envisioned that the primary connection antenna 166 may be utilized to facilitate communication between the base station 100 and an intervening communication point, such as a hangar, warehouse, etc. In such an embodiment, the primary connection antenna 166 on the base station 100 supports direct communication with the hangar (etc.), which in turn communicates directly with the UAV 10.

[0102] 27, for example, the base station 100 includes a pair of primary connection antennas 166 connected (bonded) (or otherwise engaged) to a roof section 176 of the outer housing 110. However, it should be understood that the particular number of primary connection antennas 166 and / or the locations of the primary connection antennas 166 may vary in alternative embodiments without departing from the scope of the present disclosure. For example, embodiments including a single primary connection antenna 166 are also contemplated herein, as are embodiments in which the base station 100 may include one or more primary connection antennas 166 located on a sidewall of the outer housing 110.

[0103] In certain embodiments of the present disclosure, it is contemplated that the base station 100 may include one or more secondary communication antennas to facilitate communication over cellular and / or WiFi networks and / or support GPS functionality. In such embodiments, it is contemplated that the primary connection antenna 166 and the secondary communication antenna may operate in conjunction. For example, embodiments are contemplated in which the primary communication antenna 166 may facilitate docking of the UAV 10 with (and communication between) the base station 100, while the secondary communication antenna may facilitate communication between the base station 100 and a hangar (or vice versa).

[0104] Fiducial The fiducials 168 facilitate visual identification of the base station 100 by the UAV 10, as well as guidance of the UAV 10 during landing and docking with the base station 100. It is contemplated that the outer housing 110 may include contrasting coloring to facilitate or otherwise increase visibility and / or recognition of the fiducials 168.

[0105] In certain embodiments of the present disclosure seen in Figures 13, 27, and 28, for example, the base station 100 includes (first and second) fiducials 168i, 168ii located on (supported by) the roof section 176 of the outer housing 110 (e.g., between the primary connection antennas 166) and (third) fiducial 168iii associated with (e.g., located on or adjacent to) the cradle 106. However, it should be understood that the particular number of fiducials 168 and / or the locations of the fiducials may vary in alternative embodiments without departing from the scope of the present disclosure.

[0106] The fiducial 168i is first recognized by the UAV 10 to guide the UAV 10 during approach. The fiducial 168i defines a (first) surface area large enough to allow visual recognition by the UAV 10 from a desired distance. For example, in an embodiment, it is contemplated that the (first) surface area defined by the fiducial 168i may be substantially within a range of (about) 40% to (about) 80% of the surface area defined by the roof section 176. However, a surface area of ​​the fiducial 168i outside the disclosed range does not go beyond the scope of the present disclosure (e.g., to accommodate advances in visualization technology utilized in the UAV 10).

[0107] The fiducial 168ii is configured as an identification member 178 that is recognized by the UAV 10 during approach to the base station 100 (e.g., after recognition of the fiducial 168i), thereby allowing the UAV 10 to distinguish between multiple base stations 100 and facilitate proper pairing (e.g., docking of the UAV 10 to a designated base station 100). In an embodiment of the present disclosure, it is contemplated that the fiducial 168ii may be fixedly connected to the base station 100 (e.g., roof section 176) and the fiducial 168ii may be configured to be removably connected to the base station 100 (e.g., roof section 176). The removably connected fiducial 168ii allows for uniform manufacturing of a single base station 100 and subsequent attachment of the fiducial 168ii thereto. However, embodiments in which the fiducial 168ii may be integrally (e.g., monolithically) formed with the base station 100 do not go beyond the present disclosure.

[0108] In the particular embodiment shown, the fiducial 168ii defines a (second) surface area that is less than the (first) surface area defined by the fiducial 168i. For example, it is contemplated that the (second) surface area defined by the fiducial 168ii may be substantially within a range of (about) 10% to (about) 50% of the (first) surface area defined by the fiducial 168i. However, a surface area of ​​the fiducial 168ii outside the disclosed range does not go beyond the scope of the present disclosure (e.g., to accommodate advances in visualization technology utilized in the UAV 10).

[0109] The fiducial 168iii is configured as an April tag 180 and is recognized by the UAV 10 after recognition of the fiducial 168ii. In the particular embodiment of the present disclosure illustrated, the fiducial 168iii is located on the sliding mechanism 150 to reduce (if not completely prevent) any interference with air flow across the cradle 106 during cooling and / or heating of the power source 14 of the UAV 10, as discussed in detail below. However, embodiments in which the fiducial 168iii may be located on the cradle 106 itself are also contemplated herein and do not go beyond the scope of the present disclosure.

[0110] Lighting System The lighting system 170 is configured to improve visibility of the fiducials 168 during nighttime operation. In the particular embodiment of the disclosure illustrated, the lighting system 170 includes one or more light sources 182 ( FIG. 28 ) (e.g., LEDs 184) affixed (connected, mounted) or otherwise supported by the roof section 176 of the outer housing 110 to support illuminating (illuminating) the fiducials 168i, 168ii. It is contemplated that the lighting system 170 may be connected to any suitable power source, whether internal (e.g., a power supply controlled by a main board / processor) or external (e.g., a separate power supply, battery, etc.) to the base station 100.

[0111] In certain embodiments of the present disclosure, it is contemplated that the lighting system 170 may be configured to flash or strobe the light sources 182 according to a specific pattern controlled by the main board / processor that can be recognized by the UAV 10 during approach, thereby identifying the base station. In such embodiments, it is contemplated that the lighting system 170 may supplement or replace the fiducial 168ii as a means of identifying the base station 100.

[0112] Status Indicators The status indicators 172 (FIG. 29) identify the status of the base station 100 (e.g., the base station 100 is ready, needs servicing, is undergoing a docking procedure with the UAV 10, etc.). Each status indicator 172 includes an (external) light source 173 (e.g., one or more LEDs 186) supported by an outer (external, exterior) surface 116a of the forward frame 116, thereby supporting not only status indication but also illumination of the fiducials 168iii (FIG. 13) and / or the cradle 106 (e.g., to facilitate docking of the UAV 10). For example, in a particular embodiment, it is contemplated that one or more of the LEDs 186 may be configured to emit a colored light (e.g., red, blue, yellow, etc.) and one or more of the LEDs 186 may be configured to emit a white light to illuminate the fiducials 168iii and / or the cradle 106.

[0113] In the particular embodiment of the disclosure illustrated in FIG. 29, the status indicator 172 is fixed (connected, attached) or otherwise supported by the front frame 116 of the outer housing 110. However, it should be understood that the particular location of the status indicator 172 may vary in alternative embodiments without departing from the scope of the present disclosure. It is contemplated that the status indicator 172 may be connected to any suitable power source, whether internal to the base station 100 (e.g., a power supply controlled by a main board / processor) or external (e.g., a separate power supply, battery, etc.).

[0114] UAV storage In certain embodiments of the present disclosure, it is contemplated that the UAV 10 may be reconfigurable between a flight (deployed) configuration ( FIG. 32 ) in which the propeller assemblies 18 are in an extended configuration, and a storage (folded) configuration ( FIGS. 33 and 34A-34C ) in which each of the propeller assemblies 18 are in a folded configuration and oriented within the range of positions identified by reference letter R in FIG. 35 . Reconfiguring the UAV 10 into the storage configuration not only allows for a reduction in the overall size of the base station 100, but also reduces (if not completely prevents) undesired contact between the propeller assemblies 18 and the housing 102 ( FIG. 32 ) that could otherwise result in the UAV 10 being dislodged from the cradle 106, interference with the operation of the door 104, damage to various internal components of the base station 100, etc.

[0115] To support movement from the flight configuration to the storage configuration, it is contemplated that the base station 100 may be configured to engage the propeller assembly 18 (e.g., during retraction of the cradle 106). For example, as described in further detail below, it is contemplated that the base station 100 may include one or more engagement members configured to physically interface with the propeller assembly 18 to fold the propeller assembly 18 and move the propeller assembly 18 to a folded configuration during retraction of the cradle 106 and movement of the UAV 10 into the housing 102. It is contemplated that the engagement members may be integrated into (or defined within) one or more surfaces of the housing 102 (e.g., the forward frame 116 of the outer housing 110). For example, the engagement members may be configured as rollers, brushes, (spring-biased) stops, etc.

[0116] In certain embodiments of the present disclosure, it is contemplated that the engagement members may be configured for passive interaction with the propeller assembly 18, whereby the propeller assembly 18 contacts the engagement members upon retraction of the cradle 106. Alternatively, it is contemplated that the engagement members may be configured to actively engage (interact) with the propeller assembly 18. For example, it is contemplated that the engagement members may be repositionable (reconfigurable) between a first position (configuration) in which the engagement members are positioned (configured) to avoid contact with the propeller assembly 18 (e.g., such that the engagement members are positioned outside of the path taken by the propeller assembly 18 during retraction of the cradle 106) and a second position (configuration) in which the engagement members are positioned (configured) to contact the propeller assembly 18 (e.g., such that the engagement members are positioned within the path taken by the propeller assembly 18 during retraction of the cradle 106).

[0117] To allow for further reduction in the overall size of the base station 100, it is envisioned that the base station 100 may include one or more contact members 188 configured to engage (contact) one or more antennas 34 on the UAV 10 to facilitate reconfiguration (repositioning, folding) between an active (stored, deployed, deployed) configuration ( FIG. 2 ) in which the antenna 34 extends outward (away) from the body 36 of the UAV 10 that supports (is connected to) the power source 14, and a passive (stored, folded, undeployed) configuration in which the antenna 34 is positioned adjacent (e.g., in contact (engagement)) with the body 36 of the UAV 10. Reconfiguration of the antenna 34 from the active configuration to the passive configuration creates clearance with various internal components of the base station 100 to inhibit (if not completely prevent) unintended contact between the UAV 10 and the base station 100 during movement of the cradle 106 (and the UAV 10) between the extended position ( FIG. 13 ) and the retracted position ( FIG. 2 , FIG. 10 ). In the particular embodiment of UAV 10 illustrated throughout the figures, the antenna 34 is biased toward the active configuration via one or more biasing members (e.g., springs, etc.) such that the antenna 34 is automatically reconfigured from the passive configuration to the active configuration when the UAV 10 exits the base station 100 (e.g., via movement of the cradle 106 from a retracted position (FIGS. 2, 10) to an extended position (FIG. 13)).

[0118] In the embodiment illustrated in FIG. 31A, the contact members 188 define a channel 189 configured to receive the antenna 34 during retraction of the cradle 106 as the UAV 10 is retracted into the housing 102. FIG. 31B illustrates another embodiment of a contact member 188 including a leading edge 190 and a trailing edge 192, defining a (vertical) height H that varies between edges 190 and 192 to define an angled (chamfered, sloped, slanted) surface 194 configured to engage (contact) the antenna 34 on the UAV 10. In a particular embodiment of the disclosure seen in FIG. 31B, each contact member 188 tapers such that the height H decreases from the leading edge 190 toward the trailing edge 192. Embodiments in which each contact member 188 may taper to an increasing height H from the leading edge 190 to the trailing edge 192 are also contemplated herein and do not go beyond the scope of the present disclosure (e.g., depending on the particular configuration and / or location of the antenna 34 on the UAV 10, the spatial constraints of the housing 102, etc.).

[0119] In the embodiment illustrated in Figures 31A and 31B, the base station 100 includes a single contact member 188 that is affixed (connected) to (or otherwise engaged with) the interior (e.g., top) surface 196 of the inner housing 108. However, it should be understood that the specific number of contact members 188 and / or the locations of the contact members 188 may vary in alternative embodiments without departing from the scope of the present disclosure (e.g., depending on the number and / or locations of antennas 34 on the UAV 10). For example, embodiments including multiple contact members 188 are also contemplated herein, as are embodiments in which the base station 100 may include one or more contact members 188 located on a sidewall 198 of the inner housing 108.

[0120] It is contemplated that the contact member 188 may be secured (connected) to the inner housing 108 in any suitable manner. For example, it is contemplated that the contact member 188 may be integrally (e.g., monolithically) formed with the inner housing 108, or that the contact member 188 and the inner housing 108 may be formed as separate discrete structures that may be secured (connected) together via one or more mechanical fasteners, adhesives, or the like.

[0121] Folding the Propeller Assembly In an embodiment of the present disclosure, as shown above, it is contemplated that the base station 100 may include one or more engagement members, identified by reference numeral 316 (FIGS. 34D, 36-40), configured to facilitate movement of the propeller assembly 18 to a folded configuration during retraction of the cradle 106 and UAV 10 into the housing 102. The engagement members 316 each include a mounting bracket 318 and a bumper 320 that is supported (fastened, connected) by the mounting bracket 318 such that the bumper 320 contacts (engages) the propeller assembly 18 during retraction of the UAV into the housing 102, resulting in repeatable and consistent positioning of the propeller assembly 18 within a position range R (FIG. 35), as described in detail below.

[0122] In the particular embodiment of the disclosure illustrated, the base station 100 includes first and second engagement members 316i, 316ii supported (fixedly) by actuators 118i, 118ii, respectively, such that the engagement members 316i, 316ii are laterally spaced apart from one another along the width W of the housing 102. More specifically, the engagement members 316i, 316ii are fixedly connected to an outer (lateral) surface 322 of the linkage assembly 122 and positioned (e.g., in line with the propeller arms 38) outside (laterally outward) of the hub 40 of the propeller assembly 18, such that the UAV 10 can pass between the engagement members 316i and 316ii during retraction of the cradle 106 into the housing 102. It should be understood, however, that the particular location of the engagement member 316 may vary in various embodiments (e.g., depending on the particular configuration of the UAV 10, the desired location of the propeller assembly 18 in the folded configuration, etc.) without departing from the scope of the present disclosure. For example, the present disclosure contemplates embodiments in which the engagement member 316 may be supported (e.g., secured, connected) by (immovably supported by) the door 104, as described in further detail below.

[0123] The mounting bracket 318 may be connected to the actuator 118 (e.g., the linkage assembly 122) in any suitable manner. For example, in the particular embodiment seen in FIGS. 36-38 , the mounting bracket 318 is configured to (releasably) connect to the actuator 118 via one or more mechanical fasteners 324 (e.g., screws, pins, bolts, clips, etc.), which simplifies assembly and disassembly to facilitate repair, replacement, etc. Alternatively, however, it is contemplated that the mounting bracket 318 and the actuator 118 may be configured to connect in a press-fit (interference fit) configuration, or that the mounting bracket 318 and the actuator 118 may be fixedly (non-removably) connected. For example, in some embodiments, it is contemplated that the mounting bracket 318 and the actuator 118 may be integrally (e.g., monolithically) formed.

[0124] By mounting the engagement member 316 to the actuator 118, its vertical position can be adjusted with the opening and closing of the door 104 to facilitate proper contact with the propeller assembly 18, as described in further detail below, while also reducing (if not completely preventing) interference with the operation of the door 104 and unintended contact between the engagement member 316 and various internal components of the base station 100. In addition, with reference to Figures 39 and 40, mounting the engagement member 316 to the actuator 118 can reduce the angular range (path) A1 of motion traversed by the actuator 118, and thus the engagement member 316, during the opening and closing of the door 104, as compared to the angular range (path) A2 of motion traversed by the door 104 itself. The reduced angular path A1 allows the vertical position of the engagement member 316 to be adjusted with less angular change, allowing for a reduction in the height (length) HE (FIG. 38) of the engagement member 316, thereby further reducing any possibility of unintended contact between the engagement member 316 and various internal components of the base station 100 and the housing 102 (e.g., the front frame 116 (FIG. 36)), etc.

[0125] In certain embodiments of the present disclosure seen in FIGS. 36-38, the bumper 320 includes (e.g., is partially or entirely formed of) one or more pliable (flexible) materials, and its stiffness may be altered by varying one or more parameters of the bumper 320. For example, the stiffness of the bumper 320 may be altered by varying the height HE (FIG. 38), the (lateral) thickness T of the bumper 320, the configuration (e.g., shape, profile) of the bumper 320, the hardness of the selected material, etc. The use of pliable materials, in addition to facilitating folding of the propeller assembly 18, also allows for resilient deflection (e.g., bending) of the bumper 320, which reduces (if not completely prevents) piercing of the bumper 320 by the propeller blades 42 and dislodging of the UAV 10 from the cradle 106 that might otherwise occur. The use of a flexible material also allows the bumper 320 to return to its normal (undeflected) position upon sufficient retraction of the UAV 10, facilitating subsequent contact with the propeller assembly 18.

[0126] Although bumper 320 is illustrated in the particular embodiment of the present disclosure seen in Figures 36-38 as comprising a rubberized, weather-resistant, and wear-resistant material, it is envisioned that bumper 320 may comprise any material that supports the operations and functions described herein.

[0127] The bumper 320 includes a first (upper) end 326 that extends from (connects to) a corresponding mounting bracket 318, and a second (lower) end 328. In the particular embodiment seen in FIGS. 36-38, the second end 328 defines an angled (chamfered, beveled, inclined) surface 330. It is contemplated that the angled surface 330 may guide the bumper 320 over the propeller assembly 18 during retraction of the UAV 10 (e.g., to reduce the force applied to the UAV 10 by the engagement member 316). However, embodiments lacking the angled surface 330 are also contemplated herein and do not go beyond the scope of this disclosure.

[0128] 2, 32, and 35-41, when the UAV 10 docks with the base station 100, the door 104 is moved from a closed position (FIG. 1) to an open position (FIG. 1, FIG. 36), and the cradle 106 begins to retract (e.g., during a first stage of retraction) into the UAV 10, thereby aligning (or generally aligning) the rear propeller assemblies 18ri, 18rii with the engagement members 316. With the cradle 106 in the first partially retracted position, the door 104 is lowered (e.g., moved to a first partially closed position), and the rear propeller assemblies 18ri, 18rii are actively rotated (e.g., via actuation of corresponding motors 44 (FIG. 2)). The lowering of the door 104 facilitates contact (engagement) with the antenna 34 (FIG. 2) and its reconfiguration between active and passive configurations, as well as adjustment of the vertical position of the engagement member 316 (FIGS. 39, 40), and active rotation of the rear propeller assemblies 18ri, 18rii brings the propeller blades 42 into contact (engagement) with the engagement member 316 (throughout the following description, rotation of the propeller assemblies 18 is described from a perspective located vertically above the UAV 10). More specifically, the rear propeller assembly 18ri is rotated in a first direction (e.g., clockwise) and the rear propeller assembly 18rii is rotated in a second opposite direction (e.g., counterclockwise). Upon contact with the engagement member 316, continued rotation of the rear propeller assemblies 18ri, 18rii causes the propeller blades 42 to pivot about the pivot members 50 (FIG. 32), resulting in partial folding of the rear propeller assemblies 18ri, 18rii and moving the rear propeller assemblies 18ri, 18rii from the extended configuration toward the folded configuration.

[0129] After the rear propeller assemblies 18ri, 18rii are partially folded, retraction of the cradle 106 continues (e.g., during second stage retraction), moving the cradle 106 to a second partially retracted position and reconfiguring (folding) the antenna 34 from the active configuration to the passive configuration (e.g., via contact (engagement) with the door 104). The rear propeller assemblies 18ri, 18rii are then actively rotated (e.g., via actuation of the corresponding motors 44) such that the propeller blades 42 again contact (engage) the engagement members 316. More specifically, the rear propeller assembly 18ri is rotated in a second direction (e.g., counterclockwise) and the rear propeller assembly 18rii is rotated in a first direction (e.g., clockwise) to complete the folding of the rear propeller assemblies 18ri, 18rii such that the rear propeller assemblies 18ri, 18rii are oriented within a desired position range R (FIG. 35). The folding of the rear propeller assemblies 18ri, 18rii is thus performed in two stages (e.g., a first stage in which the rear propeller assemblies 18ri, 18rii are partially folded, and a second stage in which the rear propeller assemblies 18ri, 18rii are fully folded).

[0130] In certain embodiments of the present disclosure, it is contemplated that the rear propeller assemblies 18ri, 18rii may be oriented forward (e.g., toward the front propeller assemblies 18fi, 18fii and the door 104) when fully folded, as seen in FIG. 34C (for example).

[0131] After the rear propeller assemblies 18ri, 18rii are fully folded, retraction of the cradle 106 continues (e.g., during a third stage retraction), the cradle 106 moves to a third partially retracted position, and the door 104 is lowered (e.g., to a second partially closed position). The retraction of the cradle 106 aligns (or generally aligns) the front propeller assemblies 18fi, 18fii with the engagement members 316, and the lowering of the door 104 adjusts the vertical position of the engagement members 316 (FIGS. 39, 40) to facilitate contact (engagement) with the front propeller assemblies 18fi, 18fii to accommodate (compensate for) the difference in vertical location (height) between the rear propeller assemblies 18ri, 18rii and the front propeller assemblies 18fi, 18fii.

[0132] The front propeller assemblies 18fi, 18fii are then actively rotated (e.g., via actuation of the corresponding motors 44) such that the propeller blades 42 contact (engage) the engagement members 316. More specifically, the front propeller assemblies 18fi are rotated in a second direction and the front propeller assemblies 18fii are rotated in a first direction. Upon contact with the engagement members 316, continued rotation of the front propeller assemblies 18fi, 18fii causes the propeller blades 42 to pivot about the pivot members 50 ( FIG. 32 ), resulting in partial folding of the front propeller assemblies 18fi, 18fii and moving the front propeller assemblies 18fi, 18fii from the extended configuration to the folded configuration.

[0133] Retraction of the cradle 106 then continues until the cradle 106 moves to the fully retracted position (e.g., during the fourth stage retraction). When the cradle 106 is moved to the fully retracted position, the cap 156 (FIGS. 1, 8, 11, 12) moves to a closed position into engagement with the bezel portion 154, and the front propeller assemblies 18fi, 18fii undergo additional passive rotation while the corresponding motors 44 become inactive. More specifically, retraction of the cradle 106 causes the front propeller assembly 18fi to rotate in a first direction via contact with the engagement member 316i and the front propeller assembly 18fii to rotate in a second direction via contact with the engagement member 316ii, resulting in a forward orientation of the front propeller assemblies 18fi, 18fii (e.g., such that the front propeller assemblies 18fi, 18fii are oriented away from the rear propeller assemblies 18ri, 18rii and toward the door 104) as seen in FIG. 34D.

[0134] The door 104 is then further lowered (e.g., to a third partially closed position) and the orientation of the front propeller assemblies 18fi, 18fii is altered to reduce (if not completely prevent) contact between the front propeller assemblies 18fi, 18fii and the door 104 during (final) closure. More specifically, the orientation of the front propeller assemblies 18fi, 18fii is reversed such that the front propeller assemblies 18fi, 18fii are oriented rearward (e.g., toward the rear propeller assemblies 18ri, 18rii, away from the door 104) as seen (for example) in FIG. 34C, thereby completing the folding of the front propeller assemblies 18fi, 18fii such that the front propeller assemblies 18fi, 18fii are oriented within the desired position range R (FIG. 35). To reverse the orientation of the front propeller assemblies 18fi, 18fii, in the particular embodiment illustrated, the front propeller assemblies 18fi, 18fii are actively rotated (e.g., via actuation of the corresponding motors 44) in a first direction and a second direction, respectively. Thus, folding of the front propeller assemblies 18fi, 18fii occurs in three stages (e.g., a first stage in which the front propeller assemblies 18fi, 18fii are partially folded via active rotation, a second stage in which the front propeller assemblies 18fi, 18fii are partially folded via passive rotation, and a third stage in which the orientation of the front propeller assemblies 18fi, 18fii is reversed).

[0135] After the cradle 106 and UAV 10 are fully retracted into the housing 102, the door 104 is lowered to a (fully) closed position.

[0136] In certain embodiments of the present disclosure, it is contemplated that the propeller assemblies 18 may undergo a final stage rotation (e.g., a third stage rotation of the rear propeller assemblies 18ri, 18rii, and a fourth stage rotation of the front propeller assemblies 18fi, 18fii). In the final stage rotation, the orientation of the propeller assemblies 18 is changed to avoid contact with various internal components of the docking station 100 (e.g., during subsequent extension of the cradle 106 and UAV 10). It is contemplated that the particular orientation of the propeller assemblies 18 achieved during the final stage rotation may vary depending on the particular location and / or configuration of the various internal components of the docking station 100. For example, embodiments are contemplated in which the front propeller assemblies 18fi, 18fii and the rear propeller assemblies 18ri, 18rii may be oriented in the same direction, and also in which the front propeller assemblies 18fi, 18fii and the rear propeller assemblies 18ri, 18rii may be oriented in different directions, as well as in which each propeller assembly 18fi, 18fii, 18ri, 18rii may be oriented differently. The present disclosure also contemplates embodiments in which final stage rotation may occur only on certain propeller assemblies 18. For example, it is contemplated that final stage rotation may occur only on the front propeller assemblies 18fi, 18fii, the rear propeller assemblies 18ri, 18rii, the front propeller assembly 18fi and the rear propeller assembly 18rii, etc.

[0137] During the aforementioned sequence, the informed positioning of the door 104 (e.g., the ability to control and vary the position (height) of the door 104 of the docking station 100, and thus the engagement member 316) reduces any possibility of unintended contact between the engagement member 316 and the UAV 10. More specifically, the ability of the engagement member 316 to remain in a raised vertical position during retraction of the cradle 106 reduces any possibility of the engagement member 316 being impaled by the propeller assembly 18 and the UAV 10 being dislodged from the cradle 106 that might otherwise occur. The informed positioning of the door 104 also allows for adjustment of the flexibility of the engagement member 316. More specifically, lowering the vertical position of the engagement member 316 and reducing its spacing from the propeller assembly 18 effectively increases the stiffness of the engagement member 316, thereby facilitating and supporting the reconfiguration of the propeller assembly 18 in the manner described above.

[0138] Additionally, the bidirectional rotation of the propeller assembly 18 described in connection with the above sequence (e.g., rotation of the propeller assembly 18 in the first and second directions) is dictated by the particular configuration of the propeller assembly 18 included in the particular embodiment of the illustrated UAV 10. For example, with reference to FIGS. 42-44, the propeller assembly 18 included in the UAV 10 defines hard stops 52 that are configured to contact adjacent propeller blades 42 to limit their continued rotation. The bidirectional rotation of the propeller assembly 18 described above addresses the hard stops 52 but allows for reconfiguration of the propeller assembly 18 in the manner described above. More specifically, rotation of the propeller assembly 18 in a first direction (e.g., clockwise) identified by arrow 3 (FIG. 42) creates engagement between the propeller blades 42 and the corresponding hard stops 52, as seen in FIGS. 43 and 44, resulting in the propeller assembly 18 being partially folded. The propeller assembly 18 is then rotated in an opposite second direction (e.g., counterclockwise) as identified by arrow 4 to complete the folding of the propeller assembly 18. However, embodiments of UAV 10 in which the propeller assembly 18 (e.g., propeller blades 42 and / or hard stops 52) may be reconfigured (altered) to allow for unidirectional rotation during reconfiguration from the extended configuration to the folded configuration are also contemplated and do not extend beyond the scope of this disclosure.

[0139] During reconfiguration of the propeller assembly 18, the active rotation of the propeller assembly 18 may be precisely controlled (e.g., via programming embedded in the UAV 10 and / or docking station 100) by varying the speed, duration, and direction of rotation. Additionally, feedback from the motors 44 (FIGS. 2, 42-44) may be utilized to detect contact between the propeller blades 42 and the hard stops 52. For example, a current spike in the motors 44 may be detected upon contact between a propeller blade 42 and a corresponding hard stop 52. In such an embodiment, when a threshold current is exceeded, the motors 44 may be caused to rotate the propeller assembly 18 in the opposite direction or to stop rotation altogether.

[0140] In another embodiment of the present disclosure, it is contemplated that during a different sequence, the motor 44 may remain inactive and folding of the propeller assembly 18 may be accomplished only via contact (engagement) with the engagement member 316. In such an embodiment, the engagement member 316 (e.g., bumper 320) acts as a guide that inhibits (if not completely prevents) unintended contact between the propeller assembly 18 and the housing 102 (e.g., piercing of the housing 102 by the propeller assembly 18) during retraction of the cradle 106. More specifically, the engagement member 316 biases the propeller blades 42 inwardly to inhibit (if not completely prevents) contact with the forward frame 116 (e.g., adjacent the door 104) (FIG. 36), which allows folding of the propeller assembly 18 via contact with the sidewall 198 (FIGS. 31A, 36) of the inner housing 108 during retraction of the cradle 106. To facilitate folding of the propeller assembly 18, it is envisioned that a visualization system 174 (FIG. 31B) may be utilized to verify that the propeller assembly 18 is properly positioned (e.g., that the propeller blades 42 have been successfully deflected to avoid contact with the forward frame 116) prior to continued retraction of the cradle 106.

[0141] 45 and 46, it is contemplated that in alternative embodiments of the base station 100, the engagement members 316 may be supported (e.g., secured, connected) by the door 104, as described above. In the particular embodiment illustrated, the engagement members 316 are configured as bumpers 332 each including a cylindrical (or generally cylindrical) configuration. However, it should be understood that the configuration of the bumpers 332 may vary without departing from the scope of the present disclosure. For example, it is contemplated that the bumpers 332 may be replaced by the bumpers 320 described above.

[0142] The bumper 332 is positioned inboard (laterally inward) of the hub 40 (FIGS. 32, 33, 35) of the propeller assembly 18 (e.g., in line with the propeller arms 38) so that the propeller assembly 18 can be aligned (or generally aligned) and oriented with the propeller arms 38 in the folded configuration, as seen in FIG. 34B.

[0143] Temperature Control System 47-52, the base station 100 includes a temperature control (e.g., heating and cooling) system 200 connected to the cradle 106 and configured to thermally regulate (e.g., cool and heat) the power source 14 (FIGS. 2, 4, 5) of the UAV 10 when the UAV 10 is docked to the base station 100 (depending on environmental conditions). In the particular embodiment of the present disclosure illustrated throughout the figures, the temperature control system 200 is configured to cool the power source 14 of the UAV 10 (e.g., when the UAV 10 and the base station 100 operate in a hot environment). However, it should be understood that embodiments in which the temperature control system 200 may be configured to heat the power source 14 of the UAV 10 (e.g., when the UAV 10 and the base station 100 operate in a cold environment) are also contemplated herein and do not go beyond the scope of the present disclosure, as described in more detail below.

[0144] The temperature control system 200 includes: an upper air circuit 202; a lower air circuit 204; and a thermoelectric conditioner (TEC) 206 thermally connected to and positioned between each of the upper and lower air circuits 202, 204.

[0145] The upper air circuit 202 is an open system that receives and circulates ambient air, which may be supplied from inside the base station 100 or from outside the base station 100 (e.g., via an air intake), to vary (regulate) the temperature of the TEC 206. The upper air circuit 202 includes: an upper (first) plenum 208; an upper (first) air circulator 210; and an upper (first) heat sink 212.

[0146] The upper plenum 208 includes an (upper) ducting system 214 that receives and circulates ambient air. The ducting system 214 may include any suitable material (or combination of materials) and may include a unitary construction in which the upper plenum 208 is formed from a single piece of material, or a segmented construction in which the upper plenum 208 is formed from multiple segments connected to each other (e.g., via one or more mechanical fasteners, adhesives, interference fits, etc.). In an embodiment, it is contemplated that the upper plenum 208 may also include one or more sensors configured to detect and monitor temperature, humidity, etc. within the upper plenum 208.

[0147] The upper air circulator 210 supports and directs the flow of air through the upper plenum 208 and across the upper heat sink 212 to vary the air temperature in the upper air 202, thereby regulating the temperature of the TEC 206, as described in further detail below. The upper air circulator 210 may include any structure or mechanism suitable for its intended purpose and may be located in any suitable location. For example, in the illustrated embodiment, the upper air circulator 210 is configured as a fan 216 (e.g., an axial fan) located within the upper plenum 208 (e.g., within the ducting system 214). However, it is also contemplated that the upper air circulator 210 may be located outside of the upper plenum 208. For example, the upper air circulator 210 may be connected to (or otherwise supported by) an exterior surface 218 of the ducting system 214.

[0148] The upper heat sink 212 (FIGS. 51, 52) is connected to (e.g., located within) the upper plenum 208 and configured to modify the temperature of the air circulated through the upper air circuit 202. For example, when the temperature control system 200 is utilized to cool the power source 14 (FIGS. 2, 4, 5) of the UAV 10, the upper heat sink 212 absorbs and distributes thermal energy (heat) generated by the TEC 206 to reduce the temperature of the air flowing through the upper plenum 208, as described in further detail below. To increase the absorption and distribution of thermal energy by the upper heat sink 212, the air flow through the upper plenum 208, and thus across the upper heat sink 212, may be increased by increasing the speed of the upper air circulator 210 (e.g., by increasing the power to the fan 216).

[0149] The lower air circuit 204 is configured as a closed system, including a lower (second) plenum 220; a lower (second) air circulator 222; and a lower (second) heat sink 224. Thus, in contrast to the upper air circuit 202, rather than drawing in additional ambient air, the lower air circuit 204 continuously circulates the air naturally present in the lower plenum 220.

[0150] The lower plenum 220 includes a (lower) ducting system 226 that directs airflow across the cradle 106 and the power source 14 of the UAV 10 when the UAV 10 is docked within the base station 100, and may include any suitable material (or combination of materials). The lower plenum 220 (e.g., the ducting system 226) includes a segmented (non-unitary) configuration that defines an aft (first, fixed) section 228 and a forward (second, movable) section 230 that is movable relative to the aft section 228. In various embodiments of the present disclosure, it is contemplated that the sections 228, 230 may include either a unitary configuration in which the sections 228, 230 are each formed from a single piece of material, or a segmented configuration in which the sections 228, 230 are formed from multiple segments connected to one another (e.g., via one or more mechanical fasteners, adhesives, interference fits, etc.). It is contemplated that in one embodiment, the lower plenum 220 may also include one or more sensors configured to detect and monitor temperature, humidity, etc. within the upper plenum 208 .

[0151] The aft section 228 of the lower plenum 220 is fixedly attached (connected) to the TEC 206 and thus fixed relative to the upper air circuit 202. The forward section 230 of the lower plenum 220 is fixedly attached (connected) to the cradle 106 and is movable with the cradle upon repositioning of the cradle 106 between the retracted position (FIGS. 2, 10) and the extended position (FIG. 13). Thus, throughout the following disclosure, any reference to the cradle 106 should be understood as referring to the assembly of the cradle 106 and the forward section 230 of the lower plenum 220.

[0152] The forward section 230 of the lower plenum 220 receives air from the aft section 228 and defines an air inlet 232 and an air outlet 234 located on opposite sides 142a, 142b of a chamber 142 defined by the cradle 106. The air inlet 232 and the air outlet 234 each include one or more vents 235 (e.g., slits, openings, or other such openings) that extend through the cradle 106 (e.g., sidewall 146) and into the chamber 142. The vents 235 facilitate air flow across the chamber 142 by directing air conditioned by the lower air circuit 204 across the power supply 14 of the UAV 10 into the cradle 106 when the UAV 10 is docked to the base station 100. More specifically, as described in further detail below, the air inlet 232 is configured to direct air into the cradle 106 and across the power source 14 of the UAV 10, and the air outlet 234 is configured to receive the air directed across the power source 14 and redirect the air through the lower plenum 220 and across the lower heat sink 224.

[0153] While shown as extending generally around the cradle 106 in the particular embodiment illustrated throughout the figures, embodiments are contemplated in which the forward section 230 of the lower plenum 220 may only partially circumscribe the cradle 106. For example, embodiments are contemplated in which the forward section 230 of the lower plenum 220 may include opposed terminal ends that define an air inlet 232 and an air outlet 234, respectively.

[0154] Additionally, while the forward section 230 of the lower plenum 220 and the cradle 106 are illustrated as being integrally (e.g., monolithically) formed in the illustrated embodiment, it is also envisioned that the lower plenum 220 and the cradle 106 may be configured to be releasably (removably) engaged to enable repeated connection and disconnection of the lower plenum 220 and the cradle 106 (e.g., via corresponding engagement structures such as detents, clips, catches, etc.).

[0155] The lower air circulator 222 supports and directs the flow of air through the lower plenum 220 and across the lower heat sink 224 to thermally condition (e.g., vary the temperature of) the air in the lower air circuit 204, thereby heating or cooling the power source 14 of the UAV 10, as described in further detail below. The lower air circulator 222 may include any structure or mechanism suitable for its intended purpose and may be located in any suitable location. For example, in the illustrated embodiment, the lower air circulator 222 is configured as a fan 236 (e.g., a blower fan) located within the lower plenum 220 (e.g., within the ducting system 226). However, it is also contemplated that the lower air circulator 222 may be located outside the lower plenum 220. For example, the lower air circulator 222 may be connected to (or otherwise supported by) an exterior surface 238 of the ducting system 226.

[0156] The lower heat sink 224 is connected to (e.g., located within) the lower plenum 220 and configured to process (e.g., modify the temperature of the air in the lower plenum 220 via cooling or heating) the air circulated therethrough before directing it across the power source 14 of the UAV 10. For example, when the temperature control system 200 is utilized to cool the power source 14 of the UAV 10, the lower heat sink 224 absorbs and distributes thermal energy (heat) from the air flowing through the lower plenum 220 to reduce its temperature, and thus the temperature of the power source 14 of the UAV 10. To increase the absorption and distribution of thermal energy by the lower heat sink 224, and thus enhance the cooling of the power source 14 of the UAV 10, the air flow through the lower plenum 220, and thus the air flow across the lower heat sink 224, may be increased by increasing the speed of the lower air circulator 222 (e.g., by increasing the power to the fan 236).

[0157] The TEC 206 is configured as a Peltier system and includes a dedicated / integrated power supply / control, as well as a first (upper, "hot") end 240 (FIG. 51) and a second (lower, "cold") end 242, each of which includes a thermal member (e.g., a ceramic plate). The first end 240 is thermally and / or physically connected to the upper heat sink 212, and the second end 242 is thermally and / or physically connected to the lower heat sink 224. Upon activation, as current flows through the TEC 206, the temperature of the first end 240 increases (up to an upper temperature threshold) while the temperature of the second end 242 decreases (up to a lower temperature threshold) until a predetermined fixed temperature difference is achieved. For example, it is envisioned that the difference between the respective upper and lower ends 240 and 242 of the TEC 206 may be substantially within a range of (approximately) 30° C. to (approximately) 70° C. (e.g., (approximately) 50° C.). However, embodiments in which the temperature difference may be outside the disclosed ranges are contemplated herein and do not go beyond the scope of the present disclosure. Thus, reducing the upper temperature threshold may result in a corresponding reduction in the lower temperature threshold.

[0158] During operation of the temperature control system 200, in the particular embodiment of the present disclosure illustrated, thermal energy (heat) generated by the TEC 206 is absorbed and dissipated by the ambient air flowing through the upper heat sink 212 and the upper plenum 208. The upper air circuit 202 thus cools a first ("hot") end 240 of the TEC 206, which in turn correspondingly cools a second ("cold") end 242 of the TEC 206, thus increasing the cooling of the air flowing through the lower plenum 220 and the power source 14 of the UAV 10 when the UAV 10 is docked to the base station 100.

[0159] Although illustrated as including a single TEC 206 in the particular embodiment shown throughout the figures, embodiments are also contemplated in which the temperature control system 200 may include multiple TECs 206. In such embodiments, it is contemplated that the TECs 206 may be identical or non-identical in configuration (e.g., it is contemplated that the temperature control system 200 may include TECs 206 that are different sizes) and / or that the TECs 206 may be arranged in series or parallel (e.g., in a stacked configuration).

[0160] As mentioned above, embodiments of the present disclosure are contemplated herein in which the temperature control system 200 may be configured to heat, rather than cool, the power source 14 of the UAV 10 when the UAV 10 is docked to the base station 100. In such an embodiment, the flow of current through the TEC 206 may be reversed (e.g., via electronic control) such that the first end 240 of the TEC 206 functions as the “cold” end and the second end 242 of the TEC 206 functions as the “hot” end.

[0161] During use of the temperature control system 200, the upper air circuit 202 draws in air from the surroundings, either within the base station 100 or from outside the base station 100, and the air is directed across the upper heat sink 212 via the upper air circulation 210. As the air flows across the upper heat sink 212, heat is extracted, thereby cooling the upper heat sink 212 and thus the first ("hot") end 240 of the TEC 206, and heating the air. The heated air is then exhausted from the upper air circuit 202 and discharged (e.g., through a vent) into or outside the base station 100 to replace the cooler ambient air being drawn into the upper air circuit 202 by the upper air circulation 210.

[0162] When the UAV 10 is docked, the forward section 230 of the lower plenum 220 mates (engages) with the aft section 228 as the cradle 106 moves from the extended position (FIG. 13) to the retracted position (FIGS. 2, 10), thereby closing the lower air circuit 204 and allowing continuous circulation of air therethrough. To facilitate mating engagement between the forward section 230 and the aft section 228, it is contemplated that the forward section 230 and the aft section 228 may include one or more seals (e.g., O-rings) or corresponding engagement structures (e.g., collars, flanges, etc.) at the interface therebetween.

[0163] Air flowing through the lower air circuit 204 is directed across the lower heat sink 224 via the lower air circulator 222, which draws heat from the air and cools it before entering the chamber 142 of the cradle 106 via the air inlet 232. As the cooled air flows across the cradle 106 and through the chamber 142, heat is drawn from the power source 14 of the docked UAV 10 (FIGS. 2, 4, 5), which is facilitated by the heat exchanger 24. More specifically, in the illustrated embodiment, the cooled air flows through channels 32 (FIG. 4) defined by the diffuser 26 (e.g., fins 30), which increases the distribution of thermal energy from the power source 14 of the UAV 10 to enhance cooling and increase the temperature of the air. After flowing across the power supply 14, the (heated) air exits the chamber 142 via the air outlet 234 and is redirected (e.g., via the lower air circulator 222) across the lower heat sink 224, cooling the air again before recirculating through the cradle 106 and across the power supply 14.

[0164] Cradle insulation 56-58, in certain embodiments of the present disclosure, it is envisioned that the cradle 106 may include an insulated structure that can enhance control over and regulation of the temperature of the power source 14 of the UAV 10 when the UAV 10 is docked within the base station 100. More specifically, the insulation of the cradle 106 promotes and facilitates cooling and heating of the power source 14 to maintain the temperature of the power source 14 for an increased period of time.

[0165] The (insulating) cradle 106 includes: an upper (first) shell 362; a lower (second) shell 364; and one or more insulators 366, where the shells 362, 364 collectively define a housing 365 of the cradle 106. It is contemplated that the shells 362, 364 and the insulator 366 may be formed from any suitable material. For example, in the particular embodiment illustrated, the shells 362, 364 each include (e.g., are formed partially or entirely from) one or more non-metallic (e.g., plastic) materials, and the insulator 366 includes (e.g., are formed partially or entirely from) a foam insulation material. However, embodiments in which the shells 362, 364 and / or the insulator 366 may include one or more alternative materials are not beyond the scope of this disclosure. For example, embodiments are contemplated herein in which shell 362 and / or shell 364 may include composite materials (eg, carbon fiber) (eg, to increase the overall strength and / or stiffness of cradle 106).

[0166] The upper shell 362 is configured to receive the UAV 10 during docking and defines the aforementioned chamber 142, side walls 146, air inlet 232 (Figures 47-49), air outlet 234, and angled guide surface 148, which collectively facilitate proper placement of the UAV 10 within the cradle 106.

[0167] The bottom shell 364 is connected to the top shell 362 and provides structural rigidity to the cradle 106. The bottom shell 364 defines a charging window 368 located at the rear end 106b of the cradle 106 and a pair of air flow openings 370, 372 in communication with the air inlet 232 and the air outlet 234, respectively, to facilitate circulation of cooled and heated air through the cradle 106 following regulation by the TEC 206. As described in further detail below, the charging window 368 is configured to receive the charging hub 143 ( FIG. 10 ) such that the charging hub 143 is extendable into and through the cradle 106 during retraction of the UAV 10 into the base station 100, thereby facilitating connection of the charging hub 143 to the power source 14 of the UAV 10. Air flow openings 370 , 372 communicate with air inlet 232 and air outlet 234 , respectively, and allow cooled and heated air to enter cradle 106 following conditioning by TEC 206 .

[0168] 58, the cradle 106 (e.g., the assembly of the cradle 106 and the forward section 230 of the lower plenum 220) includes lead-ins 374 positioned adjacent (e.g., around) the airflow openings 370, 372, each defining a chamfered (beveled, angled) end wall 376 that facilitates entry of the cradle 106 into the base station 100 during retraction. In the event of misalignment with, for example, the window 113 (FIG. 2) and contact with the housing 102 (e.g., the forward frame 116), the lead-ins 374 redirect the cradle 106 (and the forward section 230 of the lower plenum 220) laterally inward, thereby reducing (if not completely preventing) jamming, damage to the cradle 106 and / or the forward section 230 of the lower plenum 220, damage to the housing 102, and the like. The chamfered end wall 376 also facilitates proper registration of the cradle 106 (and the forward section 230 of the lower plenum 220) and is configured to engage (contact) a corresponding chamfered (beveled, angled) end wall 378 ( FIG. 58 ) on the aft section 228 of the lower plenum 220 such that upon retraction of the cradle 106, the cradle 106 (and the forward section 230 of the lower plenum 220) mates with the aft section 228 of the lower plenum 220, thereby facilitating proper airflow through the temperature control system 200 and the cradle 106 to support thermal regulation (e.g., heating and cooling) of the power source 14 of the UAV 10. The end walls 376, 378 thus define corresponding mating surfaces for the cradle 106 and the aft section 228 of the lower plenum 220, respectively.

[0169] It is contemplated that the shells 362, 364 may be connected to one another in any suitable manner. For example, in the particular embodiment of the illustrated cradle 106, the shells 362, 364 are connected via one or more mechanical fasteners (e.g., screws, pins, bolts, clips, etc.) that extend through openings 380 in the shells 362, 364. However, it is contemplated that the shells 362, 364 may be configured to connect in any suitable manner. For example, embodiments are also contemplated in which the shells 362, 364 may be configured to engage in a press-fit (interference fit) arrangement. Mechanically connecting the shells 362, 364 simplifies assembly and disassembly of the cradle 106 to facilitate repair of the cradle 106, replacement of any of its components, etc.

[0170] The insulation 366 is located and secured between the shells 362 and 364 (e.g., such that the insulation 366 is located within the housing 365) and collectively defines an airflow channel 382 that extends around the chamber 142 and thus the power source 14 when the UAV 10 is docked within the cradle 106. In the particular embodiment of the present disclosure illustrated, the cradle 106 is shown as including a pair of insulations 366 (e.g., an upper insulation 366i and a lower insulation 366ii), which makes the manufacture and assembly of the cradle 106 easy and simple. However, embodiments are also envisioned in which the cradle 106 may include a single insulation 366 that is of integral construction (e.g., a monolithic insulation 366 formed from a single piece of (insulating) material).

[0171] The insulation 366 defines an interior compartment 367 configured to receive (contain) the upper shell 362 (e.g., the chamber 142) such that the upper shell 362 extends into the insulation 366. More specifically, in the particular embodiment illustrated, the insulations 366i, 366ii each include an opening 367a and a recess 367b that collectively define the interior compartment 367 such that the chamber 142 extends through the opening 367a and is received by (positioned inwardly of) the recess 367b when the cradle 106 is assembled.

[0172] Airflow channel 382 is configured to receive, direct, and circulate thermally conditioned air within (e.g., through, across) cradle 106. In the particular embodiment illustrated, airflow channel 382 extends between insulation 366i and 366ii and includes a (first) channel portion 384 having respective rear and front ends 386 and 388 in communication with airflow opening 370 and air inlet 232, and a (second) channel portion 390 having respective rear and front ends 392 and 394 in communication with airflow opening 370 and air outlet 234. As seen in FIG. 57 , the respective front ends 388, 392 of channel portions 384, 390 are separated by a nose section 396 of cradle 106. Thus, airflow channel 382 includes a discontinuous configuration that partially circumscribes cradle 106 and chamber 142 and inhibits (if not completely prevents) air flow from forward end 388 of channel portion 384 to forward end 394 of channel portion 390, thereby directing air from air inlet 232 across chamber 142 to air outlet 234. Embodiments in which airflow channel 382 may include a continuous (uninterrupted) configuration that completely circumscribes cradle 106 and chamber 142, however, do not go beyond the scope of this disclosure.

[0173] Weather and Climate Control To enable operation in a variety of weather conditions, base station 100 includes a number of components and systems configured to regulate temperature, humidity, humidity, etc. to maximize operability in various environments.

[0174] Snow and Ice As seen in FIG. 53A and FIG. 53B, in an embodiment of the present disclosure, the base station 100 includes a (primary) heating system 244 including one or more heating elements 244a (e.g., resistive heaters 244b) thermally and / or physically (e.g., via adhesive) connected to the housing 102. While shown in the particular embodiment illustrated as being associated with the roof section 176 of the outer housing 110, it is envisioned that the heating elements 244a may be thermally and / or physically connected to any section of the outer housing 110 that may benefit from heating. When activated, the heating elements 244a increase (heat) the temperature of the outer housing 110 (e.g., reduce the presence of snow and / or ice on the roof section 176, thereby exposing (revealing) the fiducials 168 to facilitate visual identification of the base station 100 and / or guidance of the UAV 10 during landing and docking with the base station 100). To further assist in managing precipitation (e.g., snow, ice, sleet, rain, etc.), it is contemplated that roof section 176 may be pitched (e.g., at 3°-5°) to promote runoff and reduce (if not completely prevent) pooling on roof section 176.

[0175] It is envisioned that the heating element 244a may be connected to any suitable power source, whether internal (e.g., a power supply controlled by a main board / processor) or external (e.g., a separate power supply, battery, etc.) to the base station 100, and that the heating system 244 (e.g., heating element 244a) may be activated manually or automatically. For example, it is envisioned that the heating system 244 may be activated via a signal relayed by one or more temperature sensors 246 in communication with the heating element 244a and configured to detect a threshold (environmental) temperature such that the heating system 244 is automatically activated when the temperature falls below or exceeds a predetermined value (e.g., 32°F). Additionally or alternatively, it is envisioned that the heating system 244 may be activated upon receiving an activation signal from a weather station (e.g., via a cloud-based or other such wireless connection) and / or from a visualization system 174 that may be configured to visually inspect environmental conditions (e.g., detect the presence of snow and / or ice) and relay an activation signal to the heating system 244.

[0176] 59-62, to further support operation of the base station 100 in cold environments and / or conditions, it is envisioned that the base station 100 may include a (secondary) heating system 245 supported by the housing 102. More specifically, the heating system 245 includes one or more additional (internal) heating elements 244a supported by (connected to) the interior (interior) surface 116b of the front frame 116 to facilitate opening and closing of the door 104. The heating system 245 is located adjacent (or generally adjacent) to a sealing member 398, which is configured to engage (contact) the door 104 to form a seal with the door to inhibit (if not completely prevent) the ingress of dust, debris, moisture, water, and the like into the base station 100. More specifically, the sealing member 398 is supported by the housing 102 (e.g., the front frame 116) and extends around the window 113. To enhance the distribution of thermal energy from the heating element 244a, in one embodiment, it is contemplated that a thermal interface material 400 may be provided (located) between the front frame 116 and the heating element 244a, as seen in FIG. 61.

[0177] As discussed above in connection with FIGS. 53a, 53b and the heating of the roof section 176, it is envisioned that the heating system 245 may be connected to any suitable power source, whether internal or external to the base station 100, and may be activated manually or automatically (e.g., via signals relayed by one or more temperature sensors 246 upon receiving an activation signal from a weather station and / or visualization system 174, etc.). Upon activation of the heating element 244a, thermal energy is communicated to the sealing member 398 and / or door 104 to heat the sealing member 398 and / or door 104. Heating the sealing member 398 and / or door 104 melts snow, ice, etc., thereby facilitating proper opening and closing of the door 104.

[0178] In certain embodiments of the present disclosure, it is contemplated that the heating system 245 may also include a status indicator 172. In such embodiments, the light source 173 (e.g., LED 186) can help to enhance the thermal effect of the heating element 244a by utilizing the thermal conductivity of the sheet metal used that comprises the outer housing 110 (e.g., front frame 116) to communicate heat generated via operation of the status indicator 172 to the sealing member 398 and / or door 104. In such embodiments of the present disclosure, the status indicator 172 thus provides a dual function (e.g., illumination and heating of the sealing member 398 and / or door 104).

[0179] 63, in certain embodiments of the present disclosure, it is contemplated that the sealing member 398 and / or the door 104 may additionally or alternatively include one or more thermally conductive members 402 (e.g., strip heaters, wires, coils, plates, etc.) that may be connected to any suitable power source, whether internal or external to the base station 100. For example, in the particular embodiment illustrated, the base station 100 includes a (first) thermally conductive member 402i embedded within the sealing member 398 and a (second) thermally conductive member 402ii embedded within the door 104. In such embodiments, activation of the thermally conductive member 402 communicates (transmits) electrical energy to the sealing member 398 and / or the door 104, thereby heating the sealing member 398 and / or the door 104 to effect a required or desired temperature change.

[0180] Internal temperature and humidity control To regulate (control) the temperature and / or humidity within the base station 100, it is envisioned that the base station 100 may include one or more internal fans 248 ( FIG. 64 ), which may be supported in any suitable location on the inner housing 108 and / or outer housing 110. The internal fans 248 may be configured to regulate (e.g., vary, control) the temperature and / or humidity within the base station 100 and either cool the base station 100 (e.g., via thermal connections to one or more heating elements or components) or heat the base station 100.

[0181] The internal fan 248 is controllable (e.g., via the main board / processor) to draw in and exhaust air through one or more ports / vents in the outer housing 110 and / or inner housing 108, the location of which may be varied to direct the flow of air in a particular direction (e.g., across the UAV 10). For example, it is contemplated that the ports / vents may be located and / or configured to create a flow of air through the base station 100 in any effective (or other desired) pattern.

[0182] In certain embodiments of the present disclosure, it is contemplated that the internal fan 248 may be automatically activated via a signal relayed by one or more sensors 250 configured to detect temperature, humidity, etc. Additionally, or alternatively, it is contemplated that the internal fan 248 may be connected to a timer such that the internal fan 248 automatically activates at a particular time.

[0183] In connection with humidity regulation, upon detecting moisture, the sensor 250 may generate an activation signal that may be utilized to initiate one or more mitigation steps. For example, it is contemplated that the sensor may be in communication with the internal fan 248 such that upon receiving an activation signal from the sensor 250, the internal fan 248 is engaged to remove (or otherwise mitigate) excess humidity within the base station 100, thereby suppressing (if not entirely preventing) condensation that may otherwise impair the functionality of one or more components of the UAV 10 or the base station 100. For example, the presence of condensation may cause malfunction and / or damage to the electronic modules (e.g., main board / processor) and / or "fogging" of the visualization system 174. To further suppress (if not entirely prevent) the presence of humidity, condensation, moisture, and the like, it is contemplated that in certain embodiments of the present disclosure, the electronic modules may be sealed within the base station 100. For example, an electronic module, or its various components (eg, motor drivers, interface boards, light boards, etc.), may be collectively (via hermetic sealing) or individually (eg, via dip coating).

[0184] drainage In certain embodiments of the present disclosure, the housing 102 (e.g., outer housing 110) may include one or more channels 252 (FIG. 65) configured to collect and direct water away from any point of ingress into the housing 102 and / or away from any components, electronic, mechanical, or otherwise, that may be compromised by the presence of moisture so as to inhibit (if not entirely prevent) its ingress into the base station 100. For example, it is contemplated that the channels 252 may be configured to collect and direct water away from any power cables, any locking members / mechanisms, interfaces with the door 104 (FIG. 1), etc. Although the housing 102 is shown in the particular embodiment illustrated as including a single channel 252 extending around the rear outer edge 254 of the outer housing 110, it should be understood that the number of channels 252 and / or the location of the channels 252 may vary without departing from the present disclosure. For example, embodiments including one or more additional channels 252 are also contemplated herein, as are embodiments in which the enclosure 102 may include one or more channels 252 extending around the front outer edge 256 of the outer housing 110 (FIG. 1), the roof section 176, etc.

[0185] In the particular embodiment of the base station 100 illustrated in Figure 65, the channel 252 is defined by an insert 258 (molded) into the outer housing 110. However, it is contemplated that the channel 252 may be configured in any manner suitable for the intended purpose of collecting and / or directing water in the manner described herein. For example, embodiments are also contemplated in which the channel 252 may be integrally (e.g., monolithically) formed with the outer housing 110.

[0186] In certain embodiments of the present disclosure, it is contemplated that the housing 102 may include one or more seals, gaskets, etc. associated with the channel 252 to further reduce (if not completely prevent) water penetration. For example, it is contemplated that such seals, gaskets, etc. may be positioned about the insert 258 and supported by the inner housing 108 and / or the outer housing 110.

[0187] It should be understood that any of the aforementioned components and / or systems may be omitted to reduce the overall cost and complexity of the base station 100. For example, it is contemplated that in hot (e.g., desert) climates, the heating element 244a may be eliminated.

[0188] Visualization System 1, the visualization system 174 includes a digital image capture device 260 (e.g., a digital camera), etc. It is envisioned that the visualization system 174 may be connected to any suitable power source, whether internal to the base station 100 (e.g., a power supply controlled by a main board / processor) or external (e.g., a separate power supply, battery, etc.).

[0189] In a particular embodiment of the illustrated disclosure, the visualization system 174 includes a single digital image capture device 260 affixed (connected, mounted) or otherwise supported by the forward frame 116 of the outer housing 110 to support observation and visual analysis of the environment in which the base station 100 is located, as well as observation and visual analysis of the UAV 10 ( FIG. 2 ) before takeoff, during takeoff, and during landing. However, it should be understood that the number of digital image capture devices 260 and / or the location of the digital image capture devices 260 may vary in alternative embodiments without departing from this disclosure. For example, embodiments including one or more additional digital image capture devices 260 are also contemplated herein.

[0190] During operation of the base station 100, the visualization system 174 supports visual inspection of the environment and improves the safety of the base station 100 and the UAV 10 by verifying the absence of people, animals, etc., before takeoff, during takeoff, and during landing of the UAV 10, as well as improving the functionality of the base station 100. For example, it is contemplated that the visualization system 174 may be configured to identify precipitation (e.g., snow, ice, rain, etc.) and activate (trigger) the operation of the heating element 244a (FIGS. 53A, 53B), the internal fan 248 (FIG. 64), or other such systems. It is also contemplated that the visualization system 174 may be utilized to inspect the UAV 10 (e.g., before takeoff and / or during docking) and identify any damage that may lead to subsequent suboptimal performance.

[0191] Charging the UAV 66-75, charging of the UAV 10 will now be described. As described above, when docked with the base station 100, the UAV 10 and power source 14 are received by the cradle 106, which facilitates alignment and engagement with the charging hub 143. The charging hub 143 is configured to electrically connect to any suitable power source, whether internal or external to the base station 100; includes a base 404; an alignment bracket 406 movably (slidably) supported by the base 404; one or more biasing members 408; a charging member 410 including a PCB 412 and a (male) electrical connector 414; and a cap (cover, lid) 416 that overlies the charging member 410.

[0192] The base 404 is fixedly (immovably) connected to the housing 102 and supports the remaining components of the charging hub 143. More specifically, in the particular embodiment illustrated, the base 404 is fixedly (immovably) connected to the sliding mechanism 150 (e.g., fixed sliding member 151a) as seen in FIGS. 10 and 64, for example, by a number of mechanical fasteners 417 (FIG. 67) (e.g., screws, pins, bolts, clips, etc.), thereby fixing the charging hub 143 not only to the housing 102, but also to the cradle 106 and UAV 10. However, it should be understood that the particular location of the base 404 may vary in alternative embodiments without departing from the scope of the present disclosure. For example, embodiments are also envisioned in which the base 404 may be connected to the sheet metal base 264 (FIG. 14) of the housing 102.

[0193] The base 404 defines a cavity (receptacle) 418 ( FIG. 71A ) configured to receive the alignment bracket 406 (and biasing member 408) such that the alignment bracket 406 is movable within the cavity 418 relative to the base 404 during repositioning between a normal (initial, extended) position ( FIG. 71A ) and a deflected (subsequent, retracted) position ( FIG. 71B ), as described in more detail below. More specifically, the base 404 includes: a rear end wall 420 including a boss (support) 422; a front end wall 424; side walls 426, 428; and a bottom wall 430, which collectively define the cavity 418.

[0194] The bottom wall 430 is configured to support the alignment bracket 406 during repositioning between the normal position and the deflected position. The bottom wall 430 extends between the side walls 426 and 428 and includes opposing (rear) and (front) ends 434 and 436 spaced apart from the end walls 420, 424, respectively. More specifically, the ends 434, 436 of the bottom wall 430 are spaced apart (axially) from the end walls 420, 424 such that the base 404 defines a (first, rear) opening 438 and a (second, front) opening 440, respectively. The opening 438 is configured to provide access to the cavity 418 during manufacturing and assembly of the charging hub 143 (e.g., to facilitate fabrication of the base 404 and the alignment bracket 406), and the opening 440 is configured to receive the alignment bracket 406 such that the alignment bracket 406 is insertable into the base 404 during assembly of the charging hub 143.

[0195] The bottom wall 430 defines a guide surface 442 ( FIG. 73 ) configured to contact (engage) the alignment bracket 406 during extension and retraction within the cavity 418. To facilitate and support proper movement and repositioning of the alignment bracket 406, a (front) end 436 of the bottom wall 430 includes a chamfered (beveled) surface 444 configured to engage (contact) the alignment bracket 406 to orient the alignment bracket 406 into contact (engage) the guide surface 442, thereby suppressing electromagnetic interference.

[0196] The alignment bracket 406 supports (is connected to) the charging member 410 and facilitates proper alignment between the UAV 10 and the charging hub 143 during retraction of the cradle 106 and thus electrical connection of the charging member 410 to the power source 14 of the UAV 10. In the particular embodiment illustrated, the alignment bracket 406 is of unitary (e.g., monolithic) construction and formed from a single piece of material. However, in alternative embodiments of the present disclosure, it is contemplated that the alignment bracket 406 may include a series of individual components connected to each other in any suitable manner (e.g., via one or more mechanical fasteners, with an interference fit, etc.). As described in more detail below, the alignment bracket 406 includes: a head section 448; a body 450 extending from the head section 448; and legs 452 extending from the body 450.

[0197] The head section 448 defines (first and second) platforms 454, 456 configured to support the PCB 412 and the electrical connector 414, respectively, and includes one or more alignment members 458. The platform 454 defines an opening 460 configured to receive a mechanical fastener 462 ( FIG. 72 ) (e.g., a screw, pin, bolt, clip, etc.) to releasably fixedly connect the charging member 410 and the alignment bracket 406 such that the charging member 410 and the alignment bracket 406 are movable in unison (simultaneously) along the axis of movement M during repositioning of the alignment bracket 406 between the normal position and the deflected position.

[0198] The alignment member 458 extends axially forward of the charging member 410 (e.g., electrical connector 414) along the axis of movement M and is configured to be inserted into a receptacle 464 defined by the power source 14 of the UAV 10 to facilitate proper positioning of the charging member 410 and electrical connection to the UAV 10, as described in detail below. In the particular embodiment illustrated, the alignment bracket 406 includes a pair of alignment members 458i, 458ii each configured as a pin 466. However, it should be understood that the particular number and / or configuration of the alignment members 458 may be varied in various embodiments without departing from the scope of the present disclosure. For example, an embodiment of the alignment bracket 406 including a single alignment member 458 is also contemplated herein.

[0199] To improve tolerances, alignment member 458 includes a tapered (conical) end 468 and receptacle 464 includes a chamfered (beveled) mouth portion 470. The tapered end 468 of alignment member 458 and the chamfered mouth portion 470 of receptacle 464 allow for and accommodate any offset (misalignment) therebetween, thereby facilitating proper insertion of alignment member 458 into receptacle 464.

[0200] The body 450 of the alignment bracket 406 extends rearwardly from the head section 448 to define a recess 472 ( FIG. 71A ) extending between the head section 448 and the leg 452. The recess 472 is configured to receive the end wall 424 (which defines the cavity 418 in the base 404) such that the end wall 424 is axially spaced a distance D from the head section 448 of the alignment member 458, which extends parallel (or generally parallel) to the axis of movement M. During retraction of the alignment bracket 406 (e.g., when the UAV 10 is connected to the charging hub 143), the end wall 424 moves forward (e.g., toward the head section 448 of the alignment member 458) through the recess 472, and during extension of the alignment bracket 406 (e.g., when the UAV 10 is detached from the charging hub 143), the end wall 424 moves rearward (e.g., toward the legs 452) through the recess 472. Thus, the range of (maximum) relative motion between the alignment bracket 406 and the base 404 is equivalent to (defined by) the distance D between the end wall 424 of the base 404 and the head section 448 of the alignment member 458.

[0201] The leg 452 extends vertically upward from the body 450 of the alignment bracket 406 parallel (or generally parallel) to the head section 448 and includes a boss (support) 474 and an anchor (foot) 476. The boss 474 extends rearward (e.g., away from the head section 448) from the leg 452 and is (vertically) aligned (or generally aligned) with the boss 422 to facilitate engagement (contact between) of the bosses 422, 474 when the alignment member 458 is moved to the deflected position ( FIG. 71B ), whereby the bosses 422, 474 collectively define a hard stop 477 that prevents over-travel of the alignment bracket 406, and thus the charging member 410 and electrical connector 414. In certain embodiments of the present disclosure, it is contemplated that the bosses 422, 474 may be formed and accessed (e.g., during injection molding) through the openings 438 in the base 404 and that the bosses 422, 474 may provide location features (reference points) that facilitate proper assembly of the charging hub 143.

[0202] 72, the anchors 476 are configured to be inserted into corresponding openings 478 in the charging member 410 (e.g., PCB 412). Positioning the anchors 476 within the openings 478 further facilitates connection of the charging member 410 to the alignment bracket 406 and inhibits (if not completely prevents) relative movement therebetween, such that the charging member 410 moves with the alignment bracket 406 during retraction and extension.

[0203] In the particular embodiment illustrated in Figures 66-74, the charging hub 143 includes a single biasing member 408 configured as a coil spring 480. However, it should be understood that the particular number and / or configuration of the biasing members 408 may vary in alternative embodiments without departing from the scope of the present disclosure. For example, Figure 75 illustrates an embodiment of a charging hub 143 that includes a pair of biasing members 408.

[0204] The biasing member 408 is located within the cavity 418 and captured between the alignment bracket 406 and the base 404. More specifically, the biasing member 408 includes a first (rear) end 482 that engages (contacts) the base 404 and a second (front) end 484 that engages (contacts) the alignment bracket 406. More specifically, the first end 482 of the biasing member 408 is supported by (connected to) the boss 422 and the second end 484 of the biasing member 408 is supported by (connected to) the boss 474, thereby offsetting (vertically) the biasing member 408 from the alignment member 458 along a (vertical) axis V that extends orthogonal (or generally orthogonal) to the axis of movement M.

[0205] The charging hub 143 (e.g., base 404 and alignment bracket 406) are configured such that the biasing member 408 carries a preload force such that the biasing member 408 sits in compression between the alignment bracket 406 and base 404 (e.g., between bosses 422 and 474). The preload force carried by the biasing member 408 biases the alignment bracket 406 toward a normal position, enhancing alignment between the charging member 410 and the power source 14 of the UAV 10 and facilitating a proper electrical connection therebetween.

[0206] The charging member 410 includes the PCB 412 and electrical connector 414 described above, and is configured to be electrically connected to the power source 14 of the UAV 10. The electrical connector 414 is fixedly connected (e.g., soldered) to the PCB 412 to inhibit (if not completely prevent) relative movement therebetween, such that the electrical connector 414 moves with (simultaneously with) the PCB 412 and the alignment bracket 406 during repositioning of the alignment bracket 406 between the normal position and the deflected position. To allow axial displacement (movement) of the PCB 412 and the electrical connector 414 during repositioning of the alignment bracket 406, the charging hub 143 includes an opening 486 (FIGS. 67, 70, 71A) defined in its rear end 488. The opening 486 is configured to receive the PCB 412 and electrical connector 414, thereby allowing the PCB 412 and electrical connector 414 to exit and re-enter the charging hub 143 (e.g., base 404) during retraction and extension of the alignment bracket 406. As seen in FIG. 71A , for example, the PCB 412 and electrical connector 414 are configured and positioned to be hidden by the charging hub 143 when the alignment bracket 406 is in a normal position.

[0207] Together, the PCB 412 and the electrical connector 414 establish and control (regulate) the electrical connection and communication between the charging hub 143 and the power source 14 of the UAV 10. More specifically, the PCB 412 and the electrical connector 414 enable the transfer of data between the UAV 10 (via the charging hub 143) and the base station 100, including, for example, information regarding the temperature of the power source 14, the voltage of each of the batteries 20 (FIG. 5), the occurrence of under-voltage events, the number of charging cycles, the general health and status of the power source 14, etc.

[0208] The electrical connector 414 is configured to be inserted into an opening 490 of the power source 14 of the UAV 10 through a charging window 368 (FIGS. 66, 67, 71A) defined in the rear end 106b of the cradle 106. The charging window 368 is configured to receive the charging member 410 such that the charging member 410 moves in and out of the cradle 106 during repositioning of the sliding mechanism 150 and the cradle 106 between the extended and retracted positions. When the charging member 410 is inserted into the charging window 368, the electrical connector 414 engages a corresponding (female) electrical connector 492 of the power source 14 to establish an electrical connection between the base station 100 (e.g., charging hub 143) and the UAV 10 that facilitates charging of the power source 14.

[0209] In certain embodiments of the present disclosure, it is contemplated that the charging window 368 may be reconfigurable between an open position, in which the charging member 410 can be received by the charging window 368, and a closed position, in which the charging window 368 is concealed, so as to inhibit (if not completely prevent) unintended contact between the UAV 10 and the cradle 106 (e.g., the charging member 410 abutting against a wall defining the charging window 368). For example, it is contemplated that the cradle 106 may include a movable door configured to expose the charging window 368 in the open position and to conceal the charging window 368 in the closed position.

[0210] The cap 416 defines a channel 494 (FIGS. 67, 74) configured to receive the charging member 410, which allows movement of the charging member 410 relative to the cap 416 (and base 404), as described in further detail below. The cap is releasably connected to the base 404 by a plurality of mechanical fasteners 496 (e.g., screws, pins, bolts, clips, etc.) (FIGS. 68, 74, 75). Thus, the cap 416 inhibits (if not completely prevents) rotation (twisting) of the alignment bracket 406 and charging member 410 relative to the base 404 that might otherwise occur as a result of a vertical offset between the alignment member 458 and the biasing member 408 during insertion of the alignment member 458 into the receptacle 464 (e.g., during repositioning of the alignment bracket from its normal position to its biased position).

[0211] It is contemplated that misalignment may occur between the charging member 410 and the power source 14 of the UAV 10 during connection of the UAV 10 to the charging hub 143. Misalignment may occur, for example, as a result of variations in installing the UAV 10 in the cradle 106, swapping out the power source 14 that results in the UAV 10 being installed in a different position in the cradle 106, etc. However, any such misalignment is accommodated by axial, vertical, and horizontal tolerances (clearances) that allow movement in three degrees of freedom of the alignment bracket 406 and the charging member 410 relative to the base 404 and cap 416. More specifically, axial movement (float, displacement) of the charging member 410 along the axis of movement M (FIG. 71A) is permitted through repositioning of the alignment bracket 406 (and charging member 410) between a normal position (FIG. 71A) and a deflected position (FIG. 71B), which is facilitated by the cavity 418 of the base 404 and the axial separation between the end wall 424 and the head section 448 of the alignment bracket 406. In addition, the charging hub 143 is configured to define vertical gaps G1, G2 (FIG. 71A) between the base 404, the charging member 410, and the cap 416, as well as horizontal (lateral) gaps G3, G4 (FIG. 67) between the charging member 410 and the cap 416 that permit movement (float, displacement) of the charging member 410 along the vertical axis V, which is facilitated by the relative dimensioning of the charging member 410 and the channel 494. Gaps G3, G4 allow movement (float, displacement) of charging member 410 within channel 494 along a horizontal axis H that extends perpendicular (or generally perpendicular) to axis of movement M and vertical axis V (FIG. 71A).

[0212] The above-mentioned axial, vertical, and horizontal tolerances not only facilitate a more robust and consistent connection of the UAV 10 and charging hub 143, but also protect the UAV 10, charging hub 143, and base station 100 during retraction of the cradle 106 and UAV 10. For example, in the case of a large misalignment (e.g., when it is physically impossible to connect the charging member 410 to the power source 14), retraction of the alignment bracket 406 and charging member 410 limits (if not completely prevents) damage to the UAV 10, charging member 410, etc. (e.g., puncture of the UAV 10, dislodging of the UAV 10 from the cradle 106, etc.).

[0213] With continued reference to Figs. 66-74, a method of charging a UAV 10 (e.g., power source 14) using the base station 100 will be described. Initially, the UAV 10 is docked in the cradle 106, during which the power source 14 is guided into the chamber 142 (Fig. 67) by the side wall 146 and the angled guiding surface 148. After docking with the cradle 106, the cradle 106 is retracted into the housing 102 via repositioning the sliding mechanism 150 from the extended position to the retracted position, during which the charging hub 143 is inserted into the cradle 106. More specifically, when the sliding mechanism 150 (and the cradle 106) moves to the retracted position, the alignment bracket 406 is inserted into the receptacle 464 defined by the power source 14 of the UAV 10, as seen in Fig. 71A, which facilitates proper positioning of the charging member 410 and alignment of the electrical connector 414 with the opening 490 of the power source 14. Continued retraction of the cradle 106 causes insertion of the charging member 410 into the power source 14 (through the opening 490) and thus engagement (contact) between the electrical connectors 414 and 492 to establish an electrical connection between the power source 14 and the charging hub 143.

[0214] During retraction of the cradle 106, biasing of the alignment bracket 406 toward the normal position (FIG. 71A) supports a proper electrical interface between the electrical connectors 414 and 492. Additionally, due to the axial tolerances introduced by the configuration of the base 404 and the alignment bracket 406, and the inclusion of the biasing member 408, the alignment bracket 406 can be repositioned between the normal position (FIG. 71A) and the biased position (FIG. 71B) as needed to accommodate misalignment between the UAV 10 and the charging hub 143, during which the biasing member 408 is compressed, thereby increasing the preloaded force carried by the biasing member 408.

[0215] Electronic module maintainability 76-88, the base station 100 includes a number of electronic modules configured to control certain functional aspects of the base station 100. More specifically, in the particular embodiment of the present disclosure illustrated, the base station 100 includes a (first) electronic module 500; a (second) electronic module 502; and a third electronic module 504. As described in further detail below, each of the electronic modules 500, 502, 504 is specifically configured and positioned to be individually connected to and disconnected from the base station 100, thereby allowing each of the electronic modules 500, 502, 504 to be individually removed (e.g., for repair, maintenance, replacement, etc.), thereby reducing downtime of the base station 100.

[0216] The electronic module 500 is supported by the housing 102 and housed behind (inside) the rear door 115 of the base station 100, which represents an alternative embodiment to the access panel 114 (FIG. 7) described above, and is hinged to the rear end 102b of the housing 102 such that the rear door 115 is repositionable between a closed position (FIG. 76) and an open position (FIG. 83). More specifically, the electronic module 500 is removably connected to a rear frame 506 of the outer housing 110 and positioned adjacent the (rear) door 115 within an access window 508 defined by the rear frame 506. In the particular embodiment illustrated, the electronic module 500 is secured (connected) to the rear frame 506 by a number of mechanical fasteners 510 (FIG. 78) (e.g., screws, pins, bolts, clips, etc.) and is located at an upper (rear) corner section 512 of the base station 100 (e.g., to enhance accessibility to the electronic module 500 during connection and disconnection). However, it should be understood that the particular location of the electronic module 500 may be varied in various embodiments without departing from the scope of the present disclosure, so long as access to the electronic module 500 is maintained in the manner described herein. For example, embodiments are contemplated in which the electronic module 500 may be connected to the rear frame 506 at a lower corner section 514 of the base station 100. With particular reference to FIG. 78, as described in detail below, the electronic module 500 includes: a main (first) heat sink 516; an auxiliary (second, supplemental, associated) heat sink 518; a logic board 520; a (first) PCBA 522; an interface member 524; and an SD card 526.

[0217] The main heat sink 516 includes (e.g., is partially or entirely formed from) a thermally conductive material (e.g., aluminum) and facilitates distribution of thermal energy away from (e.g., in hot environments and / or conditions) or towards (e.g., in cold environments and / or conditions) the electronic module 500. The main heat sink 516 includes a body 528 having a block-type configuration that provides structural integrity to the electronic module 500 increasing its stability (e.g., rigidity). Thus, the main heat sink 516 acts as (and provides) a (first) housing component 530 for the electronic module 500.

[0218] The body 528 of the main heat sink 516 defines a cavity (pocket) 532 that includes one or more recesses 534 and one or more standoffs (bosses) 536. The cavity 532 is configured to receive (contain, house) the logic board 520 such that the logic board 520 is positioned in engagement (contact) with the standoffs 536.

[0219] The auxiliary heat sink 518 is connected to the main heat sink 516 and acts as (and provides) a (second) housing component 538 of the electronic module 500 that supplements the distribution of thermal energy provided by the main heat sink 516. More specifically, in the particular embodiment illustrated, the heat sinks 516, 518 are connected by a number of mechanical fasteners 540 (e.g., screws, pins, bolts, clips, etc.), which allow for assembly and disassembly of the electronic module 500 during repair, maintenance, replacement, etc. As seen in FIG. 77 , when the heat sinks 516, 518 are connected, the main heat sink 516 defines a number of side walls 542 that collectively characterize a perimeter 544 of the electronic module 500, and the auxiliary heat sink 518 defines a (first, front) end wall 546 of the electronic module 500.

[0220] Similar to the main heat sink 516, the auxiliary heat sink 518 includes (e.g., is formed partially or entirely from) a thermally conductive material (e.g., aluminum) to facilitate distribution of thermal energy away from (e.g., in hot environments and / or conditions) or toward (e.g., in cold environments and / or conditions) the electronics module 500. Although the heat sinks 516, 518 are illustrated as including the same material of construction in the particular embodiment shown, the present disclosure also contemplates embodiments in which the heat sinks 516, 518 may include different materials of construction. For example, it is contemplated that the main heat sink 516 may include (e.g., may be formed partially or entirely from) a first material having a first thermal conductivity, and the auxiliary heat sink 518 may include (e.g., may be formed partially or entirely from) a second, different material having a second, different thermal conductivity that may be greater than or less than the first thermal conductivity.

[0221] To increase the available surface area and therefore the ability of the auxiliary heat sink 518 to distribute thermal energy, in the particular embodiment as illustrated, the auxiliary heat sink 518 includes one or more diffusers 548, which may be configured in any manner suitable for its intended purpose. For example, in the particular embodiment illustrated, the diffusers 548 are configured as fins 550 that define a plurality of channels 552 therebetween, which collectively direct the flow of air along the auxiliary heat sink 518 to further enhance the distribution of thermal energy. However, it should be understood and is envisioned that the diffusers 548 may include any suitable configuration (e.g., pins, protrusions, ribs, or other such surface irregularities) without departing from the scope of the present disclosure.

[0222] The logic board 520 supports the operation and certain functional aspects of the base station 100, including, for example, temperature control of the power supply 14, powering the heating element 244a, powering the light sources 173, 182, opening and closing the (front) door 104, extending and retracting the sliding mechanism 150 and cradle 106, communication between the base station 100, the UAV 10, and / or an external network, etc. As described above, the logic board 520 is supported by the main heat sink 516 (e.g., in the cavity 532), such that the logic board 520 is located between and protected by the heat sinks 516 and 518. In certain embodiments of the present disclosure, it is contemplated that the cavity 532 (e.g., the recess 534) may include a thermal interface material (e.g., to enhance the distribution of thermal energy from the logic board 520 to the main heat sink 516).

[0223] The (first) PCBA 522 is supported by (connected to) the main heat sink 516 so as to define a (second, rear) end wall 553 of the electronic module 500. The PCBA 522 is configured to further support operation and certain functional aspects of the base station 100 including, for example, temperature control of the power supply 14, powering the heating elements 244a, powering the light sources 173, 182, opening and closing the (front) door 104, extending and retracting the sliding mechanism 150 and cradle 106, etc. To support such operation and functionality, the PCBA 522 includes a processor 554 configured to facilitate data processing and control of the base station 100.

[0224] It is contemplated that in an embodiment, the PCBA 522 may also be connected to one or more of the antennas (e.g., antenna 166) of the base station 100 via one or more antenna ports 556 (FIG. 78). It is contemplated that connecting the PCBA 522 to the antenna 166 may enable communication over WiFi, LTE, various frequencies, etc. While shown as including two antenna ports 556 in the particular embodiment illustrated, it should be understood that the particular number of antenna ports 556 may vary without departing from the scope of the present disclosure.

[0225] The interface member 524 physically, thermally, and electrically connects and is located between the PCBA 522 and the heat sink 516. As seen in FIG. 78, the interface member includes at least one thermally conductive section 558 and at least one electrically conductive section 560. The thermally conductive section 558 includes a thermal interface material 562 and physically and thermally connects the PCBA 522 to the main heat sink 516 to facilitate the transfer of thermal energy therebetween. The electrically conductive section 560 includes an electrically conductive pressure sensitive adhesive 564 (e.g., to facilitate connection of the PCBA 522 to the main heat sink 516) and is configured to electrically ground various components of the PCBA 522 to facilitate and enhance shielding from electromagnetic interference (EMI) and / or radio frequency interference (RFI).

[0226] The SD card 526 is configured to further support the operation and certain functional aspects of the base station 100 by providing mass memory and facilitating the reading and writing of data to support processing (e.g., by the PCBA 522). While illustrated in the particular embodiment illustrated as being supported by (connected to) the logic board 520, it should be understood that the particular location of the SD card 526 may vary in alternative embodiments without departing from the scope of the present disclosure. For example, embodiments in which the SD card 526 may be supported by (or connected to) the PCBA 522 are also contemplated herein.

[0227] 79 and 82, in an embodiment, the base station 100 may further include an air circulation module 566 to further facilitate the transfer of thermal energy from the electronics module 500, thereby cooling the electronics module 500. As seen in FIG. 79, the air circulation module 566 includes ducting 568 positioned around the electronics module 500 and configured to direct a flow of air across the electronics module 500, and a (first) fan 570 supported by (connected to) the ducting 568 and configured to draw air therethrough.

[0228] The air circulation module 566 is removably supported by the housing 102 adjacent the (rear) door 115. More specifically, the air circulation module 566 is connected to the rear frame 506 by a number of mechanical fasteners 572 ( FIG. 82 ) (e.g., screws, pins, bolts, clips, etc.), which allow the electronic module 500 and the air circulation module 566 to be removed from the base station 100 independently (separately) of one another to facilitate repair, maintenance, replacement, etc., thereby further reducing downtime of the base station 100. The electronic module 500 is supported by (connected to) an outer (rear) surface 574 of the rear frame 506, whereas the air circulation module 566 is supported by (connected to) an inner (front) surface 576 of the rear frame 506, such that the rear frame 506 is located between the electronic module 500 and the air circulation module 566.

[0229] 79 , the ducting 568 is configured to cover (overlap) the electronics module 500 and is configured to correspond to the auxiliary heat sink 518. More specifically, the ducting 568 defines a chamber 578 having an inner contour 580 that mirrors (e.g., substantially matches) an outer contour 582 defined by the diffuser 548. The corresponding configuration of the ducting 568 and the diffuser 548 not only facilitates receipt of the diffuser 548 by the chamber 578, but also facilitates proper fitment of the ducting 568 and the auxiliary heat sink 518, as well as proper relative orientation of the air circulation module 566 and the electronics module 500.

[0230] As mentioned above, the electronic module 500 is positioned behind the (rear) door 115 within an access window 508 defined by the rear frame 506 (e.g., such that the door 115 is positioned adjacent (or generally adjacent) to the electronic module 500). The door 115 not only protects the electronic module 500, but also acts to reduce (if not completely eliminate) emissions from the base station 100. More specifically, together with the housing 102, the door 115 defines a Faraday cage for the electronic module 500 that reduces (if not completely eliminates) EMI and / or RFI. The door 115 also conceals and protects an air filter housing 584 (FIG. 80) for one or more of the internal fans (e.g., fan 248 (FIG. 64)) located within the base station 100.

[0231] 83 and 84, the door 115 includes: a (non-metallic) frame 586; a (metallic) panel 588 supported by (connected to) the frame 586; a sealing member 590 extending around the panel 588 and configured to engage (contact) the housing 102 (e.g., rear frame 506) to inhibit (if not completely prevent) the ingress of dust, debris, moisture, water, etc. into the base station 100; a plurality of hinges 592 pivotally connecting the door 115 to the rear frame 506; and a locking mechanism 594 to inhibit theft of and / or unauthorized access to the internal components of the base station 100 through the door 115. The multi-material construction of the door 115 (e.g., the use of both metallic and non-metallic materials) reduces the overall weight of the door 115 and thus the base station 100 as well as the overall cost of the base station 100.

[0232] The panel 588 is fixedly connected to the frame 586 by a number of mechanical fasteners 596 (e.g., screws, pins, bolts, clips, etc.) such that the panel 588 is positioned relative to the electronic assembly 500 and covers (overlaps) the electronic assembly 500 when the door 115 is closed. The metal structure of the panel 588 consequently creates an enclosed metal environment for the electronic assembly 500 when the door 115 is closed, establishing the Faraday cage described above when the housing 102 (e.g., rear frame 506) is grounded.

[0233] Although the frame 586 and the panels 588 are illustrated in the particular embodiment shown as including (e.g., being partially or entirely formed from) plastic and sheet metal, respectively, it should be understood that the particular materials used in the construction of the frame 586 and the panels 588 may vary without departing from the scope of the present disclosure.

[0234] 85-87, a (second) electronic module 502 will now be described. The electronic module 502 is configured to facilitate and control the operation of the actuator 118 and thus the opening and closing of the (front) door 104. The electronic module 502 is removably connected to the roof section 598 of the inner housing 108 and includes: an access panel 600 removably supported by (connected to) the roof section 598; a (second) PCBA 602; and (second) fans 604 each affixed to (connected to) the access panel 600.

[0235] As seen in FIG. 87 , the access panel 600 is removably connected to an inner surface 606 of the roof section 598 via a number of mechanical fasteners 608, which allow the electronic module 502 to be accessed and / or removed from within the enclosure 102. Alternatively, the electronic module 502 (e.g., PCBA 602 or fan 604) can be accessed (e.g., serviced) from the outside upon removal of the outer housing 110 ( FIG. 1 ). In the particular embodiment illustrated, the mechanical fasteners 608 are configured as thumb screws 610, which allow for tool-less (e.g., manual) connection and disconnection of the access panel 600.

[0236] 88, the (third) electronic module 504 will now be described. The electronic module 504 is supported by (connected to) the sliding mechanism 150 and configured to facilitate and control its movement and thus the repositioning of the cradle 106 between the retracted and extended positions. More specifically, the electronic module 504 includes a (third) PCBA 612 that is removably connected to the fixed sliding member 151b via a number of mechanical fasteners 614, such that the electronic module 504 can be accessed and removed from within the interior cavity 112 of the housing 102 (via the front end 102a) when the door 104 is opened and the UAV 10 is removed.

[0237] Although the present disclosure has been described in connection with certain embodiments, it is to be understood that the present disclosure should not be limited to the disclosed embodiments, but on the contrary, is intended to cover various modifications and equivalent arrangements within the scope of the appended claims, which are to be accorded the broadest interpretation so as to encompass all modifications and equivalent structures permitted by law.

[0238] Those skilled in the art will understand that the various embodiments of the present disclosure shown in the accompanying figures constitute non-limiting examples, and that additional components and features may be added to any of the embodiments discussed above without departing from the scope of the present disclosure. Moreover, those skilled in the art will understand that elements and features shown or described in connection with one embodiment may be combined with elements and features of another embodiment to achieve any desired result without departing from the scope of the present disclosure, and will be able to appreciate additional features and advantages of the subject matter of the present disclosure based on the description provided. Variations, combinations, and / or modifications within the ability of a person skilled in the art to any of the embodiments and / or features of the embodiments described herein are within the scope of the present disclosure, as are alternative embodiments that may result from combining, integrating, and / or omitting features from any of the embodiments of the present disclosure.

[0239] Use of the term "optionally" with respect to any element of a claim means that the element may be included or omitted, with both alternatives being within the scope of the claim. Furthermore, use of broad terms such as "comprising," "including," and "having" should be understood to support narrower terms such as "consisting of," "consisting essentially of," and "consisting essentially of." The scope of protection is therefore not limited by the above description, but is defined by the following claims, including all equivalents of the subject matter of the claims.

[0240] In the foregoing description, reference may be made to the spatial relationships between and spatial orientation of various structures illustrated in the accompanying drawings. However, as will be recognized by those skilled in the art after a full reading of this disclosure, the structures described herein may be positioned and oriented in any manner that is appropriate for their intended purpose. Thus, the use of terms such as "upper", "lower", "top", "bottom", "inner", "outer", "left", "right", "upward", "downward", "inward", "outward", "horizontal", "vertical", and the like, should be understood to describe the relative relationships between and / or spatial orientation of structures. Those skilled in the art will also recognize that the use of such terms may be provided in the context of the illustrations provided by the corresponding figures.

[0241] Additionally, terms such as "approximately," "generally," and "substantially" should be understood to allow for variation in any numerical range or concept with which they are associated, and to encompass variations on the order of 25% (e.g., to allow for manufacturing tolerances and / or deviations in design). For example, the term "generally parallel" should be understood as referring to a configuration of related components that are oriented to define an angle therebetween that is equal to 180° ± 25% (e.g., an angle that is within the range of (approximately) 135° to (approximately) 225°). Thus, the term "generally parallel" should be understood to refer to encompassing a configuration in which related components are disposed in a parallel relationship.

[0242] Although terms such as "first," "second," and "third" may be used herein to describe various operations, elements, components, regions, and / or sections, these operations, elements, components, regions, and / or sections should not be limited by the use of these terms in that these terms are used to distinguish one operation, element, component, region, or section from another. Thus, unless expressly stated otherwise, a first operation, element, component, region, or section can also be referred to as a second operation, element, component, region, or section without departing from the scope of the present disclosure.

[0243] Any claims are incorporated into the specification as further disclosure and represent embodiments of the present disclosure. Also, the phrases "at least one of A, B, and C" and "A and / or B and / or C" should be interpreted as including A only, B only, C only, or any combination of A, B, and C, respectively.

Claims

1. 1. A base station for an unmanned aerial vehicle (UAV), comprising: A housing and a sliding mechanism connected to the housing and repositionable between a retracted position and an extended position; a cradle connected to the sliding mechanism and configured to dock with the UAV such that the UAV is movable in and out of the housing during repositioning of the sliding mechanism between the retracted position and the extended position; a charging hub connected to the sliding mechanism and configured to be electrically connected to a power source of the UAV for charging the power source; A base station comprising:

2. The base station of claim 1 , wherein the charging hub extends into the cradle when the sliding mechanism is in the retracted position.

3. The charging hub A base body connected to the sliding mechanism; an alignment bracket supported by the base; a charging member connected to the alignment bracket and configured to be electrically connected to a power source; The base station according to claim 1 or 2, comprising:

4. The base station of claim 3 , wherein the cradle defines an opening configured to receive the charging member such that the charging member moves in and out of the cradle during repositioning of the sliding mechanism between the retracted and extended positions.

5. The base station of claim 3 , wherein the alignment bracket includes an anchor that extends into a corresponding opening in the charging member to inhibit relative movement between the alignment bracket and the charging member.

6. 4. The base station of claim 3, wherein the charging hub further comprises a cap removably connected to the base and overlapping the charging member to inhibit rotation of the charging member and the alignment bracket relative to the base.

7. The base station of claim 3 , wherein the base defines a cavity configured to receive the alignment bracket such that the alignment bracket is movable through the cavity during repositioning between the normal position and the deflected position.

8. The base station of claim 7 , wherein the base includes a bottom wall defining a cavity and configured to support the alignment bracket during repositioning between the normal position and the deflected position.

9. The base station of claim 8 , wherein the bottom wall defines an opening configured to receive an alignment bracket to facilitate assembly of the charging hub.

10. The base station of claim 8 , wherein the bottom wall defines a chamfered surface configured to engage the alignment bracket to facilitate repositioning of the alignment bracket between the normal position and the deflected position.

11. 1. A base station for an unmanned aerial vehicle (UAV), comprising: a housing configured to receive the UAV; a charging hub operably connected to the housing and configured to charge the UAV; Equipped with a charging hub, A substrate; an alignment bracket movably supported by the base such that the alignment bracket is repositionable between a normal position and a deflected position; A base station including: a charging member connected to the alignment bracket such that the charging member and the alignment bracket are movable in unison along an axis of movement during repositioning of the alignment bracket between a normal position and a deflected position; and the charging member is configured to be electrically connected to the UAV.

12. The base station of claim 11 , wherein the alignment bracket includes an alignment member configured to be inserted into a receptacle defined by the UAV to facilitate proper positioning of the charging member and electrical connection of the charging member to the UAV.

13. The base station of claim 12, wherein the alignment bracket extends axially forward of the charging member along the axis of movement.

14. The base station of claim 12 or 13, wherein the charging hub further includes a biasing member positioned between the base and the alignment bracket and configured to bias the alignment bracket toward the normal position.

15. The base station of claim 14 , wherein the alignment member is vertically offset from the biasing member.

16. 1. A charging hub for a base station configured for use with an unmanned aerial vehicle (UAV), comprising: A substrate; an alignment bracket movably supported by the base such that the alignment bracket is repositionable between a normal position and a deflected position; a biasing member positioned between the base and the alignment bracket and configured to bias the alignment bracket toward a normal position; a charging member connected to the alignment bracket such that the charging member moves simultaneously with the alignment bracket during repositioning of the alignment bracket between the normal position and the deflected position; a cap removably connected to the base such that the cap overlaps the charging member to inhibit rotation of the charging member and the alignment bracket relative to the base; Equipped with a charging hub.

17. 17. The charging hub of claim 16, wherein the alignment bracket includes an anchor that extends into a corresponding opening in the charging member to restrain relative movement between the alignment bracket and the charging member.

18. 17. The charging hub of claim 16, wherein the base defines a cavity configured to receive the alignment bracket such that the alignment bracket is movable through the cavity during repositioning between the normal position and the deflected position.

19. 19. The charging hub of claim 18, wherein the base includes a bottom wall defining a cavity and configured to support the alignment bracket during repositioning between the normal position and the deflected position, the bottom wall defining a chamfered surface configured to engage the alignment bracket to facilitate repositioning of the alignment bracket between the normal position and the deflected position.

20. 20. The charging hub of any one of claims 16-19, wherein the base defines an opening configured to receive the alignment bracket to facilitate assembly of the charging hub.

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