A base station that includes an integrated system for servicing UAVs

Abstract

A base station for use with an unmanned aerial vehicle (UAV) is disclosed. The base station includes: a housing; a cradle configured to charge a power source of the UAV while docked with the base station; and a temperature control system connected to the cradle and configured to vary a temperature of the power source of the UAV. The temperature control system includes: a thermoelectric conditioner (TEC); 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 power source of the UAV.

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] In an attempt to manage various environmental settings and / or scenarios (e.g., temperature, precipitation, humidity, etc.), known base stations typically include a series of regulation systems that mandate the use of enclosures that are often significantly larger than the size of the UAV being serviced and / or housed. Furthermore, conventional docking procedures often require connection of the UAV to an external power supply while the UAV's power source itself is being recharged or replaced. As a result, known base stations are often large, mechanically complex, and expensive. Summary of the Invention [Problem to be solved by the invention]

[0003] The present disclosure addresses, among other things, these deficiencies and provides improved maintenance of UAVs and base stations that achieve significant size reductions that allow for more efficient operation and significant cost savings. [Means for solving the problem]

[0004] 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 electrically connect to a power source of the UAV during docking to facilitate charging of the power source; and a temperature control system connected to the cradle and configured to vary a temperature of the power source of the UAV. 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 power source of the UAV.

[0005] 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 warmer environment) or to heat the UAV's power supply (e.g., when the base station and UAV are used in a cooler 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 to enter into mating engagement when the cradle is moved to the retracted position.It is contemplated that the base station 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 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.

[0007] 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 electrically connect to 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, the first section of the closed air circuit may be connected to the TEC and the 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 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 method of regulating a temperature of a power source in a UAV is disclosed, the method including: 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.

[0009] In an embodiment, the method may further include directing the air across a heat sink thermally connected to a thermoelectric conditioner (TEC) for processing prior to directing the air across a 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 described above may include any combination of the features and elements described in this section.

[0010] In another aspect of the present disclosure, a base station configured for use with a UAV is disclosed, the base station including: 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.

[0011] In an embodiment, the enclosure (e.g., an 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 are activated 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 affixed 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 envisioned that the base station 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 configured for use with a UAV is disclosed. The base station includes: a housing; a 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 secured 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.

[0013] In an embodiment, the coupling assembly may include: a drive screw operatively 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 translates the carrier axially; 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 towards the door and rotation of the drive screw in a second direction advances the carrier away from the door. In certain embodiments, the drive screw may include threads defining a pitch configured to inhibit the transmission of force from the door to the carrier, thereby maintaining the door in a closed position. It is contemplated that the base stations described above may include any combination of the features and elements described in this section.

[0014] 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.

[0015] In some embodiments, the second fiducial may be configured for removable connection to the roof section. In some embodiments, 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 some embodiments, 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 station described above may include any combination of the features and elements described in this section.

[0016] In another aspect of the present 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 ambient air to reduce or increase a temperature of the power source.

[0017] In some embodiments, the one or more heat transfer members may extend between the one or more batteries and the heat exchanger. 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. In some embodiments, the one or more batteries and the one or more heat transfer members may be equal in number. In some embodiments, 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 some embodiments, 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 around the heat exchanger to increase the distribution of thermal energy toward or away from the power source. It is contemplated that the UAVs described above may include any combination of the features and elements described in this section.

[0018] 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.

[0019] 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.

[0020] 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 exterior 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.

[0021] In an embodiment, the one or more antennas may be biased toward an 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 distribution of thermal energy toward or away from the power source. In an embodiment, 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 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. It is envisioned that the UAV described above may include any combination of the features and elements described in this section.

[0022] 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]

[0023] [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. 2 is a partial side view of a base station shown with one embodiment of a UAV docked in a cradle of the base station. [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] 1 is a partial side perspective view of a base station illustrating a number of actuators configured to open and close a door of the base station. FIG. [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 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 15] 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 16] FIG. 2 is a partial front perspective view of a base station illustrating a status indicator. [Figure 17] 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 18A] 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 18B] 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. [Figure 19]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 20] FIG. 1 is a schematic diagram of the other side of the base station temperature control system, including a first air circuit, a second air circuit, and a thermoelectric conditioner (TEC). [Figure 21] FIG. 13 is a schematic side view of a portion of the cradle and second air circuit. [Figure 22] FIG. 2 is a partial side schematic diagram of a temperature control system. [Diagram 23] 1 is a schematic partial side view of a temperature control system illustrating a first heat sink and a second heat sink. [Figure 24] 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. [Diagram 25] 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 26] FIG. 2 is a schematic diagram of a partial top view of a base station illustrating an internal fan. [Figure 27] 1 is a partial rear perspective view of a base station illustrating one or more channels for collecting and directing water. FIG. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0024] Summary The present disclosure relates to a base station for use with a UAV that is configured to regulate the temperature of the UAV's power source as well as charge 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 warmer environment) or to heat the UAV's power source (e.g., when the base station and UAV are used in a cooler environment).

[0025] 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.

[0026] To increase the functionality and improve operation of the base station, the base station includes multiple 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.

[0027] 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.

[0028] 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.

[0029] 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, as seen in FIG. 2, it is contemplated that the propulsion mechanism 12 may include propellers 18. 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.

[0030] Although the particular embodiment of the UAV 10 described herein is shown as including four propulsion mechanisms 12, it should be understood that the particular number of propulsion mechanisms 12 may vary without departing from the scope of the present disclosure. Accordingly, embodiments of the UAV 10 including fewer and greater numbers of propulsion mechanisms 12 are also contemplated herein and do not exceed the scope of the present disclosure.

[0031] It is contemplated that the propulsion mechanism 12 may include fixed or variable configurations. For example, it is contemplated that the propulsion mechanism 12 may be reconfigurable between an extended (first) configuration and a folded (folded, second) configuration to enable a reduction in the overall size of the UAV 10 (e.g., during ingress into the base station 100) and thus the overall size of the base station 100, as described in further detail below.

[0032] 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.

[0033] 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 converter 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 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 warmer environment) or to transfer heat to the power source 14 (e.g., in a cooler environment), thereby improving the efficiency, operation, and / or service life of the UAV 10 and / or the power source 14.

[0034] 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.

[0035] 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.

[0036] 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.

[0037] 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 ambient (air) away from power source 14 (e.g., when used in a warmer environment) or toward power source 14 (e.g., when utilized in a cooler 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.

[0038] 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.

[0039] 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.

[0040] Base station construction Now, referring also to Figures 4-13, the base station 100 includes: a housing (body) 102; a door 104 movably connected to the housing 102; and a cradle 106 configured to receive (house) the UAV 10.

[0041] 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.

[0042] The inner housing 108 defines an interior cavity 112 configured to receive and house the UAV 10. 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 secured (mounted) to the inner housing 108 and support operation of the base station 100.

[0043] The outer housing 110 provides structural support for the base station and protects (e.g., from ingress of dust, debris, moisture, and / or water, etc.) the inner housing 108 and various components attached thereto. Additionally, the outer housing 110 supports various external components of the base station 100, as described in further detail below.

[0044] To facilitate access to the various components housed within outer housing 110 (and / or inner housing 108), in certain embodiments, it is contemplated that outer housing 110 may include an access panel 114 ( FIG. 7 ), which may be incorporated in any suitable location (e.g., the rear of outer housing 110), to support maintenance, repair, and the like. It is contemplated that access panel 114 may include a locking mechanism or other such suitable security device to discourage theft and / or unauthorized access.

[0045] 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.

[0046] The door 104 is movably connected to the outer housing 110 such that the door 104 is repositionable between a closed position ( FIG. 1 ), in which the door 104 conceals the interior cavity 112, and an open position ( FIG. 6 ), in which the interior cavity 112 is 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 closed and open positions in alternative embodiments of the present disclosure.

[0047] 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. While the particular embodiment illustrated is shown as including multiple (e.g., two) actuators 118 affixed to opposing lateral ends of the door 104, 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).

[0048] 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 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.

[0049] 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.

[0050] The cradle 106 is configured to electrically connect to the power source 14 of the UAV 10 during docking to facilitate (support) charging of the power source 14. More specifically, the cradle 106 defines a chamber 142 ( FIG. 10 ) configured to receive the power source 14 and electrical contacts 144 configured to engage one or more corresponding electrical contacts on the power source 14. To orient the UAV 10 during docking and facilitate a proper electrical interface between the power source 14 and the cradle 106, the cradle 106 defines a sidewall 146 that tapers inwardly toward the chamber 142 to define a guide surface 148, as seen in FIG.

[0051] The cradle 106 is movable between a retracted position (FIGS. 2, 10) in which the cradle 106 is positioned within the housing 102 (e.g., within the internal cavity 112) and an extended position (FIG. 13) in which the cradle 106 is positioned outside the housing 102 to facilitate docking with the UAV 10. To support movement between the extended and retracted positions, the cradle 106 is connected to a telescoping slide mechanism 150 that extends through a window 152 (FIG. 1) defined by a ramp 154 ​​in the front frame 116. The slide mechanism 150 supports a cap (hatch, cover) 156 (FIG. 11) configured to correspond to the window 152 such that the cap 156 engages the ramp 154 ​​and is received within the window 152 when the cradle 106 moves into the retracted position.

[0052] 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 inner 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 ramp 154. Additionally, the engagement between the ramp 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.

[0053] 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.

[0054] 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.

[0055] 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).

[0056] pedestal 1, in one embodiment, the base station 100 may be configured for use with a pedestal 164 (or other such free-standing platform or support) to elevate the base station 100 and the UAV 10. Elevating the base station 100 and the UAV 10 creates free space that not only reduces turbulence (e.g., propeller wash) during takeoff and landing of the UAV 10, but also mitigates the ingress of debris (e.g., dust, particulates, etc.) into the base station 100.

[0057] It is contemplated that the pedestal 164 and 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 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 pedestal 164 are subjected to 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 insert into the openings to enable a fixed, releasable connection of the pedestal 164 and base station 100.

[0058] 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.

[0059] Takeoff, Landing, and Docking 14-18, the base station 100 includes a number of systems, components, and features that support the takeoff, landing, and docking of the UAV 10. 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.

[0060] 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.

[0061] 14, for example, the base station 100 includes a pair of primary connection antennas 166 affixed to (or otherwise engaged with) 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.

[0062] 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).

[0063] 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.

[0064] 13-15, 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.

[0065] 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 would not go beyond the scope of the present disclosure (e.g., to accommodate advances in visualization technology utilized in the UAV 10).

[0066] 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 removably connect to the base station 100 (e.g., roof section 176). The removably connected fiducial 168ii allows for uniform manufacturing of a set of base stations 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.

[0067] 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).

[0068] 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.

[0069] 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. 15 ) (e.g., LEDs 184) affixed, mounted, or otherwise supported by a 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 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.).

[0070] 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.

[0071] Status Indicators The status indicator 172 (FIG. 16) identifies the status of the base station 100 (e.g., the base station 100 is ready, in need of maintenance, undergoing a docking procedure with the UAV 10, etc.). In an embodiment, it is contemplated that the status indicator 172 may include a series of LEDs 186 that not only support status indication but also support illumination of the fiducial 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 fiducial 168iii and / or the cradle 106.

[0072] In the particular embodiment of the disclosure illustrated in FIG. 16, the status indicator 172 is secured, mounted, or otherwise supported on 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.).

[0073] UAV storage In certain embodiments of the present disclosure, it is contemplated that the propulsion mechanism 12 ( FIG. 2 ) (e.g., the propellers 18) of the UAV 10 may be reconfigurable between a deployed (flight) configuration and a folded (storage) configuration, allowing for a reduction in the overall size of the base station 100. To support the movement from the deployed configuration to the folded configuration, it is contemplated that the base station 100 may be configured to engage the propulsion mechanism 1212 (e.g., during retraction of the cradle 106). For example, it is contemplated that the base station 100 may include one or more engagement members configured to physically interface with the propulsion mechanism 12 to move the propulsion mechanism 12 to the folded configuration. It is contemplated that the engagement members may be integrated into (or defined within) one or more surfaces of the enclosure 102 (e.g., the front frame 116 of the outer housing 110). For example, the engagement members may be configured as rollers, brushes, or the like.

[0074] In certain embodiments of the present disclosure, it is contemplated that the engagement member may be configured to passively interact with the propulsion mechanism 12, whereby the propulsion mechanism 12 is contacted by the engagement member upon retraction of the cradle 106. Alternatively, it is contemplated that the engagement member may be configured to actively engage (interact) with the propulsion mechanism 12. For example, it is contemplated that the engagement member may be repositionable (reconfigurable) between a first position (configuration) in which the engagement member is positioned (configured) to avoid contact with the propulsion mechanism 12 (e.g., such that the engagement member is located outside the path that the propulsion mechanism 12 follows during retraction of the cradle 106) and a second position (configuration) in which the engagement member is positioned (configured) to contact the propulsion mechanism 12 (e.g., such that the engagement member is located within the path that the propulsion mechanism 12 follows during retraction of the cradle 106).

[0075] 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 internal components of the base station 100 to inhibit (if not completely prevent) unintentional 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 (FIGS. 2, 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)).

[0076] In the embodiment illustrated in FIG. 18A, 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. 18B illustrates another embodiment of a contact member 188 that includes a leading edge 190 and a trailing edge 192 and defines a (vertical) height H that varies between edges 190 and 192 to define an angled (chamfered, sloped) surface 194 configured to engage (contact) the antenna 34 on the UAV 10. In the particular embodiment of the disclosure seen in FIG. 18B, 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 antennas on the UAV 10, the spatial constraints of the housing 102, etc.).

[0077] 18A and 18B, the base station 100 includes a single contact member 188 affixed to (or otherwise engaged with) an 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.

[0078] It is contemplated that the contact member 188 may be secured 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 together via one or more mechanical fasteners, adhesives, or the like.

[0079] Temperature Control System 19-24, the base station 100 includes a temperature control (e.g., heating and cooling) system 200 that is connected to the cradle 106 and configured to change (adjust) the temperature of the power source 14 (FIGS. 2, 4, 5) when the UAV 10 is docked to the base station 100 (e.g., to cool or heat the UAV 10 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 warmer 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 cooler environment) are also contemplated herein and do not go beyond the scope of the present disclosure, as described in more detail below.

[0080] 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.

[0081] 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.

[0082] 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, an interference fit, etc.).

[0083] 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 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.

[0084] The upper heat sink 212 (FIGS. 23, 24) 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).

[0085] 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.

[0086] The lower plenum 220 includes a (lower) ducting system 226 that directs air flow 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., 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. The aft section 228 of the lower plenum 220 is fixedly connected (fixed) to the TEC 206 and thus fixed relative to the upper air circuit 202. The forward section 230 of the lower plenum 220 is connected (fixed) 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). 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. The air inlet 232 and the air outlet 234 each include one or more slits (or other such openings) that extend through the cradle 106 (e.g., the sidewall 146) into the chamber 142 so that air cooled by the lower air circuit 204 can be directed into the chamber 142 across the power source 14 of the UAV 10 when the UAV 10 is docked to the base station 100. More specifically, 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 air directed across the power source 14 and redirect the air through the lower plenum 220 and across the lower heat sink 224, as described in more detail below.

[0087] 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.

[0088] 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.).

[0089] 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 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.

[0090] 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).

[0091] 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. 23) 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 also 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.

[0092] 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.

[0093] 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).

[0094] 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.

[0095] 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 cooler ambient air that is being drawn into the upper air circuit 202 by the upper air circulation 210.

[0096] 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.

[0097] 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.

[0098] 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.

[0099] Snow and Ice 25, in an embodiment of the present disclosure, the base station 100 includes one or more heating elements 244 that are thermally and / or physically (e.g., via adhesive) connected to (supported by) the housing 102. While shown in the particular embodiment illustrated as being associated with (supported by) the roof section 176 of the outer housing 110, it is envisioned that the heating elements 244 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 244 increase (heat) the temperature of the outer housing 110 (e.g., to reduce the presence of snow and / or ice on the roof section 176).

[0100] It is contemplated that the heating element 244 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 element 244 may be activated manually or automatically. For example, it is contemplated that the heating element 244 may be activated via a signal relayed by one or more temperature sensors 246 in communication with the heating element 244 and configured to detect when a temperature crosses (e.g., falls below or exceeds) a predetermined threshold (e.g., 32°F). Additionally or alternatively, it is contemplated that the heating element 244 may be activated upon receiving an activation signal from a weather station (e.g., via a cloud-based connection) and / or from a visualization system 174, which may be configured to visually detect the presence of snow and / or ice.

[0101] Internal temperature and humidity control To regulate (control) the temperature and / or humidity within the base station 100, it is contemplated that the base station 100 may include one or more internal fans 248 ( FIG. 26 ), 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.

[0102] 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.

[0103] 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.

[0104] 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).

[0105] drainage In certain embodiments of the present disclosure, the housing 102 (e.g., outer housing 110) may include one or more channels 252 (FIG. 27) 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.

[0106] In the particular embodiment of the base station 100 illustrated in Figure 27, 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.

[0107] 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.

[0108] 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 244 may be eliminated.

[0109] 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.).

[0110] In a particular embodiment of the illustrated disclosure, the visualization system 174 includes a single digital image capture device 260 secured, mounted, or otherwise supported by the front 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.

[0111] 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 244 (FIG. 25), the internal fan 248 (FIG. 26), 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.

[0112] 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.

[0113] 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 further 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.

[0114] Use of the term "optionally" with respect to any element of a claim means that the element may be included or omitted, and that both alternatives are within the scope of the claim. Furthermore, the use of broad terms such as "comprises," "includes," and "having" should be understood to support narrower terms such as "consisting of," "consisting essentially of," and "consisting substantially 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.

[0115] 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 drawings.

[0116] Additionally, terms such as "approximately," "generally," "substantially," and the like should be understood to allow for variation in any numerical range or concept with which they are associated. For example, use of terms such as "approximately" and "generally" is intended to be understood to encompass variations on the order of 25%, or to allow for manufacturing tolerances and / or deviations in a design.

[0117] Although terms such as "first," "second," "third," and the like 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.

[0118] 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 cradle configured to electrically connect to a power source of the UAV during docking to facilitate charging of the power source, the cradle being 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 of the housing to facilitate docking with the UAV; a temperature control system connected to the cradle and configured to vary a temperature of a power source of 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; a second air circuit, the second air circuit thermally connected to the TEC such that the TEC is located between the first air circuit and the second air circuit; and when docked with the base station, the second air circuit is configured to direct air across the cradle to thereby heat or cool a power source of the UAV.

2. The first air circuit comprises: a first plenum; a first heat sink coupled to the first plenum and to a first end of the TEC; a first air circulator configured to direct air through the first plenum and across the first heat sink to vary the air temperature in the first air circuit, thereby regulating the temperature of the TEC; The base station of claim 1 , comprising:

3. The second air circuit comprises: a second plenum; and a second heat sink coupled to the second plenum and to the second end of the TEC; 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, thereby heating or cooling a power source of the UAV; The base station of claim 2 , comprising:

4. 4. The base station of claim 3, wherein the second plenum defines an air inlet and an air outlet, the air inlet configured to direct air into the cradle and across the power source of the UAV, and the air outlet configured to receive air directed across the power source of the UAV and redirect the air across the second heat sink.

5. 5. The base station of claim 3, wherein the second plenum includes a first section and a second section that is movable relative to the first section.

6. 6. The base station of claim 5, wherein the first section is connected to the TEC and the second section is connected to the cradle.

7. The base station of claim 5 , wherein the first section and the second section are configured to matingly engage when the cradle is moved to the retracted position.

8. The base station of claim 1 , wherein the first air circuit is configured as an open system and the second air circuit is configured as a closed system.

9. The base station of claim 1 , wherein the TEC is configured as a Peltier system.

10. The base station of claim 1 , wherein the temperature control system is configured to cool a power source of the UAV when docked with the base station.

11. 1. A base station for an unmanned aerial vehicle (UAV), the base station comprising: a temperature control system configured to vary a temperature of the UAV, the temperature control system comprising: A thermoelectric conditioner (TEC); an open air circuit thermally connected to the TEC and configured to regulate a temperature of the TEC; A base station including a closed air circuit, the closed air circuit thermally connected to the TEC such that the TEC is located between the open air circuit and the closed air circuit, the closed air circuit configured to direct air across the UAV when docked with the base station.

12. The base station of claim 11 , wherein the temperature control system is configured to heat or cool the UAV depending on environmental conditions.

13. 13. The base station according to claim 11 or 12, wherein the closed air circuit comprises a first section and a second section that is movable relative to the first section.

14. The base station of claim 13, further comprising a cradle configured to electrically connect to the UAV during docking to facilitate charging of the UAV, the cradle being extendable from the base station and retractable into the base station.

15. 15. The base station of claim 14, wherein a first section of the closed air circuit is connected to the TEC and a second section of the closed air circuit is connected to the cradle, the first section and the second section configured to matingly engage when the cradle is retracted into the base station.

16. 1. A method for regulating a temperature of a power source in an unmanned aerial vehicle (UAV), comprising: docking the UAV in a cradle of the base station; retracting the cradle into the base station; directing thermally conditioned air across a power source of the UAV via an air circuit connected to the cradle; A method comprising:

17. 20. The method of claim 16, further comprising directing the air across a heat sink thermally connected to a thermoelectric conditioner (TEC) for processing prior to directing the air across a power source of the UAV.

18. The method of claim 17 , wherein directing air across the heat sink comprises circulating the air through a plenum connected to the heat sink.

19. 20. The method of claim 18, wherein retracting the cradle into the base station includes closing the air circuit.

20. 20. The method of claim 19, wherein closing the air circuit includes mating a first section of the plenum with a second section of the plenum, the first section of the plenum being connected to the TEC and the second section of the plenum being connected to the cradle.

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