Parachute deployment system for unmanned aerial vehicles

Abstract

A parachute deployment system that includes a housing defining a cavity therein, a parachute located within the cavity of the housing, and a launch assembly configured to deploy the parachute and located within the cavity of the housing. The launch assembly includes a puck defining a puck cavity therein, an inflator located within the puck cavity and disposed within a retaining area of the puck, and a sabot enclosing the puck cavity and located between the puck and the parachute. The inflator is secured within the retaining area by a retaining mechanism. Responsive to a triggering event, the inflator is configured to activate to inflate the parachute and thereby deploy the parachute.

Description

SKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO PARACHUTE DEPLOYMENT SYSTEM FOR UNMANNED AERIAL VEHICLESCROSS-REFERENCE TO RELATED APPLICATIONS

[0001] This application claims priority to and the benefit of U.S. Provisional Patent No.63 / 778,541, filed March 27, 2025, U.S. Provisional Patent No. 63 / 925,294, filed November 25, 2025, U.S. Provisional Patent No. 63 / 925,297, filed November 25, 2025, and U.S.Provisional Patent No. 63 / 925,299, filed November 25, 2025, the entire contents of which are incorporated by reference herein for all purposes.TECHNICAL FIELD

[0002] The present disclosure relates to an unmanned aerial vehicle (UAV) and, more specifically, to a parachute deployment system of a UAV.BACKGROUND

[0003] Unmanned aerial vehicles (UAVs) have become increasingly prevalent in various sectors, including military, commercial, and recreational applications. These versatile devices are implemented for various tasks, including surveillance, delivery of items, photography, and agricultural monitoring. As the use of UAVs expands, ensuring their safe operation becomes paramount, particularly in scenarios where they might encounter flight anomalies and / or malfunctions. To help mitigate the risk of injury to pedestrians and / or operators, traditional parachute deployment systems may be implemented. These traditional parachute deployment systems may often rely predominantly on mechanical systems, such as spring-loaded mechanisms, which can be bulky and add significant weight to the UAV. This additional weight can adversely affect the UAVs flight time and efficiency. Additionally, these traditional parachute deployment systems may often be unreliable and unable to ensure a safe landing of the UAV during flight anomalies and / or malfunctions.

[0004] The need for rapid and reliable parachute deployment systems is underscored by the potential risks associated with UAV failures, which can lead to damage to the UAV itself, harm to people (e.g., pedestrians and / or operators), or damage to property on the ground. In response to these challenges, there is a growing demand for innovative solutions that can quickly and effectively deploy parachutes to ensure the safe descent of UAVs in the event of an emergency, such as during a flight anomaly and / or malfunction. Such deployment systemsSKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO must be capable of detecting flight anomalies promptly and effectively deploying a parachute with minimal delay to prevent accidents and reduce the minimum deployable altitude (MDA).SUMMARY

[0005] In one implementation, a parachute deployment system for an unmanned aerial vehicle is disclosed. The parachute deployment system includes a housing defining a cavity therein, a parachute located within the cavity of the housing, and a launch assembly configured to deploy the parachute and located within the cavity of the housing. The launch assembly includes a puck defining a puck cavity therein, an inflator located within the puck cavity and disposed within a retaining area of the puck, and a sabot enclosing the puck cavity and located between the puck and the parachute. The inflator is secured within the retaining area by a retaining mechanism. Responsive to a triggering event, the inflator is configured to activate to inflate the parachute and thereby deploy the parachute.

[0006] In some configurations, the inflator may be a compressed gas cartridge that is configured to release a compressed gas. The compressed gas may be directed through the puck cavity and into the parachute to deploy the parachute. The sabot may be configured to be directed towards the parachute as the compressed gas flows towards the parachute. The sabot may include fingers spaced apart by notches, and the fingers may be configured to guide the sabot within the cavity of the housing towards the parachute.

[0007] In some configurations, the housing may define an opening that permits access to the cavity of the housing. The parachute deployment system may further include a cap that is coupled to the housing to cover the opening. The cap may be configured to release from the housing when the parachute is deployed.

[0008] In some configurations, the triggering event may be one or more of a flight anomaly of the unmanned aerial vehicle or a malfunction of the unmanned aerial vehicle.

[0009] In some configurations, the parachute deployment system may further include a control unit located within the cavity of the housing. The control unit may be configured to detect the triggering event and activate the inflator. The control unit may include or be coupled to an activation mechanism, and the activation mechanism may be configured to activate the inflator in response to a command provided by the control unit. The inflator may include a pyrotechnic and the activation mechanism may be configured to ignite the pyrotechnic, or the inflator may include a compressed gas and the activation mechanism maySKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO be configured to release the compressed gas from the inflator. The puck may be located between the control unit and the parachute, and the puck may be configured to protect the control unit from damage during deployment of the parachute.

[0010] In some configurations, the sabot may be made from at least one of a thermoplastic material, a high-temperature composite material, a phenolic or paper-based material, or a metal.

[0011] In another implementation, a parachute deployment system for an unmanned aerial vehicle is disclosed. The parachute deployment system includes a housing defining a cavity therein, a cap that encloses the cavity of the housing and that is coupled to the housing, a parachute located within the cavity of the housing, a launch assembly located within the housing adjacent to the parachute such that the parachute is located between the launch assembly and the cap, and a control unit located within the cavity of the housing. The launch assembly includes a puck defining a puck cavity therein, an inflator located within the puck cavity and secured to the puck, and a sabot enclosing the puck cavity and located between the puck and the parachute. The inflator includes at least one of a compressed gas cartridge or a pyrotechnic that is configured to activate to deploy the parachute. A flow of gas generated by the inflator is configured to direct the sabot towards the parachute. The control unit is configured to detect a triggering event and activate the inflator in response to detection of the triggering event.

[0012] In some configurations, the triggering event may be one or more of a flight anomaly of the unmanned aerial vehicle or a malfunction of the unmanned aerial vehicle.

[0013] In some configurations, the parachute deployment system may be configured to attach to a side of the unmanned aerial vehicle. The parachute may be configured to deploy to decrease a speed of descent of the unmanned aerial vehicle during the triggering event.

[0014] In some configurations, the puck may define one or more vents, and the one or more vents may be configured to vent a portion of the gas towards the control unit to maintain a pressure of the gas within the housing.

[0015] In another implementation, a method of deploying a parachute of a parachute deployment system for an unmanned aerial vehicle is disclosed. The method includes determining that the parachute deployment system is mounted to the unmanned aerial vehicle, detecting, using a control unit of the parachute deployment system, a triggering event, and responsive to detecting the triggering event, deploying the parachute using a launch assembly of the parachute deployment system. The triggering event is one or more ofSKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO a flight anomaly of the unmanned aerial vehicle or a malfunction of the unmanned aerial vehicle.

[0016] In some configurations, prior to detecting the triggering event, the method may further include determining that the parachute deployment system is electrically coupled to the unmanned aerial vehicle.

[0017] In some configurations, deploying the parachute using the launch assembly of the parachute deployment system may include activating an inflator of the launch assembly to inflate the parachute. The inflator may include a pyrotechnic and activating the inflator may include igniting the pyrotechnic, or the inflator may include a compressed gas and activating the inflator may include releasing the compressed gas from the inflator.

[0018] In another implementation, a parachute deployment system for an unmanned aerial vehicle is disclosed. The parachute deployment system includes a housing defining a cavity therein, a cap coupled to the housing and that encloses the cavity of the housing, a parachute located within the cavity of the housing, a launch assembly configured to deploy the parachute upon activation, and a control unit configured to operate the launch assembly. The launch assembly is located within the cavity of the housing adjacent to the parachute. The launch assembly includes a puck defining a puck cavity therein, an inflator located within the puck cavity and coupled to the puck, and a sabot enclosing the puck cavity and located between the puck and the parachute. The control unit is located within the cavity of the housing and the launch assembly is located between the control unit and the parachute.

[0019] In some configurations, the parachute may be coupled to the puck by a tether, and the tether may be configured to maintain connection between the parachute and the puck during and after deployment of the parachute. The tether may extend through a slot defined by the sabot.

[0020] In some configurations, the housing may define an opening that permits access to the cavity of the housing, and the cap may cover the opening. During deployment, the parachute may be configured to exit the housing through the opening in a direction away from the launch assembly and the control unit. The cap may be configured to release from the housing during deployment of the parachute.

[0021] In some configurations, the cap may define a groove therein and a seal may be disposed within the groove to seal a gap between the cap and the housing.

[0022] In some configurations, the housing may be coupled to or integrally formed with a mounting bracket, and the mounting bracket may be configured to couple the parachuteSKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO deployment system to a side of the unmanned aerial vehicle.

[0023] In some configurations, the puck may be supported by a projection extending from a base of the housing and located within the cavity of the housing. The projection may define a puck mounting hole, and a fastener may extend through the puck and into the puck mounting hole to secure the puck to the housing. The control unit may be secured to the base of the housing via one or more fasteners extending through the control unit and into control unit mounting holes defined by the housing.

[0024] In some configurations, the housing may further define a port, wiring may extend through the port and may be connected to the control unit, and the wiring may be further connected to a connector that is configured to electrically connect the parachute deployment system to the unmanned aerial vehicle.

[0025] In another implementation, a parachute deployment system for an unmanned aerial vehicle is disclosed. The parachute deployment system includes a housing defining a cavity therein, a cap coupled to the housing and that encloses the cavity of the housing, a parachute located within the cavity of the housing, a launch assembly configured to deploy the parachute upon activation, and a control unit configured to operate the launch assembly. The housing is integrally formed with a mounting bracket that is configured to couple the parachute deployment system to an attachment interface located on a side of the unmanned aerial vehicle. The launch assembly is located within the cavity of the housing adjacent to the parachute. The control unit is located within the cavity of the housing and the launch assembly is located between the control unit and the parachute.

[0026] In some configurations, the parachute may be tethered to the launch assembly to maintain connection between the parachute and the launch assembly during and after activation of the launch assembly.

[0027] In some configurations, the launch assembly may further include a puck defining a puck cavity therein and an inflator located within the puck cavity and coupled to the puck. The puck may be coupled to a base of the housing and the control unit may be located between the puck and the base of the housing. Upon activation of the launch assembly, the inflator may be configured to inflate the parachute to thereby deploy the parachute.

[0028] In some configurations, the parachute deployment system may further include an indicator light disposed along an outer surface of the housing. The indicator light may be configured to indicate whether the parachute deployment system is armed.

[0029] In another implementation, an unmanned aerial vehicle system is disclosed. TheSKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO unmanned aerial vehicle system includes an unmanned aerial vehicle that includes an attachment interface located on a side of the unmanned aerial vehicle, and a parachute deployment system configured to removably couple to the attachment interface such that the parachute deployment system is positioned adjacent to the side of the unmanned aerial vehicle. The parachute deployment system is configured to deploy a parachute in response to a triggering event detected by the parachute deployment system.

[0030] In some configurations, the parachute deployment system may include a housing defining a cavity therein. The parachute may be disposed within the housing prior to deployment. The housing may be integrally formed with a mounting bracket that is configured to removably couple the parachute deployment system to the attachment interface. The attachment interface may include an attachment surface, wherein at least a portion of the mounting bracket may be configured to directly abut the attachment surface, and a connector port configured to receive a connector of the parachute deployment system to electrically couple the parachute deployment system to the unmanned aerial vehicle. The attachment surface may define one or more mounting holes that may be configured to align with one or more mounting holes defined by the mounting bracket of the parachute deployment system such that fasteners may extend through the one or more mounting holes of the mounting bracket and the one or more mounting holes of the attachment surface to couple the parachute deployment system to the unmanned aerial vehicle.

[0031] In another implementation, a parachute deployment system for an unmanned aerial vehicle is disclosed. The parachute deployment system includes a housing defining a cavity therein, a parachute located within the cavity of the housing, and a battery retention mechanism movably coupled to the mounting bracket and configured to maintain a position of a battery of the unmanned aerial vehicle when the parachute deployment system is coupled to the unmanned aerial vehicle. The housing is coupled to or integrally formed with a mounting bracket that is configured to couple the parachute deployment system to the unmanned aerial vehicle. The battery retention mechanism includes a release tab, an arm extending from the release tab, and a latch coupled to the arm. The latch is configured to engage the battery to maintain the position of the battery.

[0032] In some configurations, the latch may be configured for receiving by a cutout defined by the battery.

[0033] In some configurations, the latch may be configured to move between an engaged position, in which the latch is configured to engage the battery to maintain the position of theSKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO battery, and a disengaged position, in which the latch is configured to disengage the battery to thereby permit disconnection of the battery from the unmanned aerial vehicle. The latch may be configured to move from the engaged position to the disengaged position based upon pressing the release tab in a direction towards the unmanned aerial vehicle. The latch may be configured to move from the disengaged position to the engaged position when the release tab is released.

[0034] In some configurations, the battery retention mechanism may further include a biasing member that is configured to bias the latch towards the battery.

[0035] In some configurations, the mounting bracket may include one or more ribs that define a channel therebetween, and the arm and the latch may be at least partially disposed within the channel. The release tab may be located adjacent to the channel and may extend away from a side of the mounting bracket. The one or more ribs may be located on a back side of the mounting bracket such that the latch may be configured to be located between the mounting bracket and the battery of the unmanned aerial vehicle.

[0036] In some configurations, the latch may include a projection that is configured to contact the battery to maintain the position of the battery.

[0037] In some configurations, the battery retention mechanism may be pivotally engaged to the mounting bracket.

[0038] In another implementation, a parachute deployment system for an unmanned aerial vehicle is disclosed. The parachute deployment system includes a housing that contains a parachute and a battery retention mechanism configured to maintain a position of a battery of the unmanned aerial vehicle when the parachute deployment system is coupled to the unmanned aerial vehicle. The housing is integrally formed with a mounting bracket that is configured to couple the parachute deployment system to the unmanned aerial vehicle. The housing includes one or more ribs that are located on a back side of the mounting bracket and that define a channel therebetween. The battery retention mechanism is at least partially disposed within the channel of the mounting bracket and pivotally coupled to the mounting bracket.

[0039] In some configurations, the battery retention mechanism may be configured to pivot between an engaged position, in which the battery retention mechanism is configured to engage the battery to maintain the position of the battery, and a disengaged position, in which the battery retention mechanism is configured to disengage the battery to thereby permit disconnection of the battery from the unmanned aerial vehicle.SKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO

[0040] In some configurations, the battery retention mechanism may be coupled to the mounting bracket by a fixed pin that extends through one or more ribs of the mounting bracket. The fixed pin may define an axis of rotation of the battery retention mechanism to facilitate pivoting of the battery retention mechanism with respect to the mounting bracket. The battery retention mechanism may be further coupled to the mounting bracket by a sliding pin that extends through the one or more ribs of the mounting bracket. The one or more ribs may define a slot, and the sliding pin may be configured for guiding along the slot when the battery retention mechanism pivots about the axis of rotation. The battery retention mechanism may include a release tab, an arm extending from the release tab, and a latch coupled to the arm and configured to engage the battery to maintain the position of the battery. The fixed pin may be coupled to the arm and the sliding pin may be coupled to the latch.

[0041] In another implementation, an unmanned aerial vehicle system is disclosed. The unmanned aerial vehicle system includes an unmanned aerial vehicle that includes an attachment interface located on a side of the unmanned aerial vehicle and a battery, and a parachute deployment system configured to removably couple to the attachment interface such that the parachute deployment system is positioned adjacent to the side of the unmanned aerial vehicle. The parachute deployment system includes a battery retention mechanism that is configured to engage the battery to prevent disconnection of the battery from the unmanned aerial vehicle.

[0042] In some configurations, the battery retention mechanism may include a latch that is releasably secured within a cutout defined by the battery. The battery retention mechanism may be movable between an engaged position, in which the latch is located within the cutout, to a disengaged position, in which the latch is removed from the cutout to thereby permit disconnection of the battery from the unmanned aerial vehicle.

[0043] In some configurations, the parachute deployment system may include a mounting bracket that removably couples the parachute deployment system to the attachment interface, and the battery retention mechanism may be movably coupled to the mounting bracket.BRIEF DESCRIPTION OF THE DRAWINGS

[0044] The present disclosure is best understood from the following detailed description when read in conjunction with the accompanying drawings. It is emphasized that, according to common practice, the various features of the drawings are not to-scale. On the contrary, theSKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO dimensions of the various features are arbitrarily expanded or reduced for clarity.

[0045] FIG. l is a top perspective view of a UAV.

[0046] FIG. 2 is a bottom perspective view of the UAV of FIG. 1.

[0047] FIG. 3 is a side view of the UAV of FIG. 1.

[0048] FIG. 4 is another side view of the UAV of FIG. 1.

[0049] FIG. 5 is a side view of the UAV of FIG. 1 illustrating a parachute deployment system coupled to the UAV.

[0050] FIG. 6 is a front perspective view of the parachute deployment system shown in FIG. 5.

[0051] FIG. 7 is a back perspective view of the parachute deployment system of FIG. 6.

[0052] FIG. 8 is a close-up view of a battery retention mechanism of the parachute deployment system.

[0053] FIG. 9 is a close-up view of the battery retention mechanism of FIG. 8 engaged with a battery of the UAV of FIG. 1.

[0054] FIG. 10 is a cross-sectional view of the parachute deployment system of FIG. 6.

[0055] FIG. 11 is an exploded view of the parachute deployment system of FIG. 6.

[0056] FIG. 12 is a close-up view of the parachute deployment system of FIG. 6 with a housing of the parachute deployment system removed.

[0057] FIG. 13 is a bottom perspective view of a launch assembly of the parachute deployment system of FIG. 6.

[0058] FIG. 14 is a top perspective view of the launch assembly of FIG. 13.

[0059] FIG. 15 is a perspective view of a control unit of the parachute deployment system of FIG. 6.

[0060] FIG. 16 is a top-down view of the housing of the parachute deployment system of FIG. 6.

[0061] FIG. 17 is a block diagram of a network configuration for a UAV.

[0062] FIG. 18 is a block diagram of a UAV and a parachute deployment system of the UAV.

[0063] FIG. 19 is a flowchart illustrating an example of a technique for deploying a parachute of a parachute deployment system of a UAV.DETAILED DESCRIPTION

[0064] The present disclosure relates to a parachute deployment system of a UAV. TheSKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO parachute deployment system may be coupled to, or integrally formed with, the UAV. The parachute deployment system may be configured to deploy a parachute to ensure safe landing of the UAV when a triggering condition, such as a flight anomaly or UAV malfunction, is detected. By way of example, the parachute deployment system may be configured to detect the triggering condition, whereby the parachute deployment system may activate a launch assembly to deploy the parachute. As a result, the parachute may safely land the UAV to avoid injury to pedestrians and / or users of the UAV. Similarly, the parachute may safely land the UAV to avoid significant damage to the UAV. It is envisioned that the parachute deployment system described herein is not particularly limited to any one structure or configuration. That is, various configurations of the parachute deployment system - and thus various configurations of the UAV - may be possible based on the teachings herein.

[0065] Conventional parachute deployment systems for UAVs may often be bulky and / or heavy, thereby negatively impacting UAV flight (e.g., flight efficiency) and / or payload capacity of the UAV. Additionally, conventional parachute deployment systems for UAVs may often implement a mechanical deployment system to deploy a parachute. Such mechanical deployment systems may often fail to properly deploy the parachute under dynamic or high-stress conditions, thereby resulting in inconsistent reliability. Similarly, using a mechanical deployment system may result in slower reaction times to deploy the parachute, thereby rendering conventional parachute deployment systems ineffective in low-altitude and / or rapid-descent scenarios. Moreover, conventional parachute deployment systems may lack the necessary componentry to accurately detect and act on (e.g., deploy) flight anomalies and / or UAV malfunctions, thereby increasing the risk of one or more of ground-impact injuries to people (e.g., pedestrians and / or users of the UAV), UAV damage, or damage to objects (e.g., buildings, cars, etc.) located on the ground. Such deficiencies highlight a critical need for an improved parachute deployment system offering a more advanced and dependable solution.

[0066] The parachute deployment system described herein addresses the aforementioned shortcomings. In particular, the parachute deployment system described herein provides a more advanced system to more accurately and effectively detect triggering conditions that necessitate deployment of a parachute, such as various types of flight anomalies and / or UAV malfunctions. Additionally, the parachute deployment system described herein provides a more compact and responsive approach to parachute deployment, thereby reducing the overall weight of the parachute deployment system while also improving reliability ofSKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO parachute deployment. That is, the parachute deployment system described herein ensures reliable deployment of the parachute with a significantly faster activation (e.g., deployment) time compared to the conventional parachute deployment systems described above. For example, by enabling more effective triggering condition detection and near-instantaneous parachute deployment, the parachute deployment system described herein may dramatically improve the likelihood of a controlled and safe descent of the UAV, even from lower altitudes. Thus, the parachute deployment system described herein meets the growing demand for UAV safety by minimizing injury risk and operational losses while optimizing overall system performance.

[0067] Turning now to the figures, FIG. 1 illustrates a top perspective view of an unmanned aerial vehicle (UAV) 100. FIG. 2 illustrates a bottom perspective view of the UAV 100. The UAV 100 may include one or more propulsion mechanisms, such as the propulsion mechanisms 102, and a power source, such as a battery 104 coupled to the UAV 100. The UAV 100 may be configured for autonomous landing and / or docking with a docking station. To support the autonomous landing and / or docking, the UAV 100 may follow any suitable processes or procedures, or may include one or more components, such as those described in U.S. Application No. 16 / 991,122, filed August 12, 2020, and U.S. Provisional Application No. 63 / 527,261, filed on July 17, 2023, the entire disclosures of which are hereby incorporated by reference for all purposes.

[0068] The propulsion mechanisms 102 may include any components and / or structures suitable for supporting flight of the UAV 100. For example, as shown in FIGS. 1 and 2, the propulsion mechanisms 102 may be or may include propeller assemblies having one or more blades connected to hubs of the UAV 100. The one or more blades may be propelled by a motor to rotate the one or more blades and facilitate flight of the UAV 100, whereby the motor may be powered by a power source of the UAV 100, such as the battery 104. It should be appreciated that the configuration and / or structure of the UAV 100 may vary depending on the desired functionality of the UAV 100, and as such, the UAV 100 shown in FIGS. 1 and 2 is not intended to limit the structure of the UAV 100.

[0069] The UAV 100 may further include a camera system 106. The camera system 106 may be configured to detect, monitor, capture, record, or a combination thereof, one or more images. The camera system 106 may be configured to facilitate autonomous or user-controlled flight of the UAV 100. For example, the camera system 106 may include one or more cameras, such as the cameras 108. The cameras 108 may capture a live feed of anSKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO environment during flight, whereby a user, via a user interface (e.g., a controller), may control the UAV 100 based upon the live feed of the environment. Alternatively, or additionally, the cameras 108 may capture images of the environment and / or monitor the environment in real-time to autonomously fly through the environment. Further, the images of the environment captured by the camera system 106 may be used to detect flight anomalies and / or malfunctioning of the UAV 100. For example, the captured images may be analyzed (e.g., using a control unit of the UAV 100 and / or a control unit of a parachute deployment system of the UAV 100) to determine flight characteristics of the UAV 100. If such flight characteristics are outside of an acceptable range (e.g., the flight characteristics exceed a threshold value), the UAV 100 and / or the parachute deployment system may determine that a flight anomaly has occurred or is occurring. Responsively, the parachute deployment system may deploy a parachute to ensure that the UAV 100 lands safely.

[0070] It should be noted that the cameras 108 and the camera system 106 are not limited to any particular configuration, and any types of camera configurations (e.g., wide-angle, high-resolution, etc.) may be implemented in the UAV 100. For example, the camera system 106 may be operable via a gimbal system 110 coupled to the camera system 106, whereby the gimbal system 110 may be coupled to the UAV 100 via a mounting bracket 112 of the gimbal system 110.

[0071] As discussed herein, a parachute deployment system may be coupled to the UAV 100 and operable with the UAV 100 to ensure safe landing of the UAV 100 during flight anomalies and / or malfunctioning. The parachute deployment system - or other attachments, such as lights, speakers, sensors, etc. - may be coupled (e.g., removably coupled) to any portion of the UAV 100. For example, the parachute deployment system may be coupled to a front 114 (e.g., a front side) of the UAV 100 or a top 122 (i.e., a top side) of the UAV 100 such that the parachute deployment system may be positioned substantially in front of the UAV 100 in a manner that does not obstruct the camera system 106 shown in FIGS. 1 and 2. As such, both the camera system 106 and the parachute deployment system may be located at the front 114 of the UAV 100 with respect to a forward direction of travel of the UAV 100 (e.g., a direction of travel of the UAV 100 that is substantially parallel to the ground or along the ground). In some configurations, the parachute deployment system may also be coupled to another portion of the UAV 100, such as a rear 116 (i.e., a rear side) of the UAV 100, a first side 118 of the UAV 100, a second side 120 of the UAV 100, a bottom 124 (i.e., a bottom side) of the UAV 100, or a combination or variation thereof.SKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO

[0072] To facilitate coupling of the parachute deployment system to the UAV 100, the UAV 100 may include one or more attachment interfaces. As shown in FIGS. 1 and 2, the UAV 100 may include a plurality of attachment interfaces located on the UAV 100. For example, the UAV 100 may include a top attachment interface 126 located on the top 122 (i.e., the top side) of the UAV 100, a side attachment interface 130 located on the first side 118 of the UAV 100, a side attachment interface 130 located on the second side 120 of the UAV 100 that opposes the first side 118, and a bottom attachment interface 134 located on the bottom 124 (i.e., the bottom side) of the UAV 100.

[0073] To further illustrate positioning of such attachment interfaces, as shown in FIGS. 1 and 2, the UAV 100 (e.g., a body of the UAV 100 from which the propulsion mechanisms 102 extend) may extend along a longitudinal axis 190 of the UAV 100 from the front 114 of the UAV 100 to the rear 116 of the UAV 100. That is, the UAV 100 may extend from a first end (e.g., the front 114, which may be considered a forward end of the UAV 100) to an opposing second end (e.g., the rear 116, which may be considered an aft end of the UAV 100) along the longitudinal axis 190, whereby a length of the UAV 100 or a body thereof may be measured from the first end to the second end.

[0074] Moreover, the first side 118 of the UAV 100 may oppose the second side 120 of the UAV 100 with respect to the longitudinal axis 190. The first side 118 and second side 120 may be located on opposing sides of the longitudinal axis 190. The first side 118 may be considered a port side of the UAV 100 and the second side 120 may be considered a starboard side of the UAV 100.

[0075] Based on the above relative orientations, it can be seen in FIGS. 1 and 2 that the attachment interfaces described above may be positioned in various locations with respect to the longitudinal axis 190 of the UAV 100. As such, the parachute propulsion system described herein - or any additional attachments of the UAV 100 - may be coupled to the UAV 100 in various locations based on the various attachment interfaces.

[0076] It should be noted that the above relative orientations associated with the UAV 100 are provided for illustrative purposes and should not be construed as limiting the teachings herein. For example, although the front 114 of the UAV 100 may be considered the front end of the UAV 100 and the rear 116 of the UAV 100 may be considered the aft end of the UAV 100, such considerations do not mean that the UAV 100 only travels in a forward direction with the front 114 of the UAV 100 leading the travel. That is, the UAV 100 may travel in any direction (e.g., fore, aft, side-to-side between the port and starboard sides, in anSKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO elevational direction, etc.) with respect to the longitudinal axis 190.

[0077] Turning now back to the attachment interfaces, it should be noted that such attachment interfaces may be integrated into the UAV 100, such as a housing of the UAV 100, or may be connected to the UAV 100 to allow for attachment of various attachments. That is, the attachment interfaces may provide a connection means to easily and removably couple various attachments to the UAV 100, such as the parachute deployment system. By way of example, the top attachment interface 126 may include a top attachment surface 128. The top attachment surface 128 may be located on, or formed with, the top (i.e., the top side) of the UAV 100. The top attachment surface 128 may be configured to receive, support, or otherwise couple to - either directly or indirectly - various attachments. Similarly, the side attachment interface 130 of the first side 118 and / or the second side 120 may include a side attachment surface 132 located on, or formed with, the first side 118 and / or the second side 120 of the UAV 100. Moreover, the bottom attachment interface 134 may include a bottom attachment surface 136 located on, or formed with, the bottom 124 (i.e., the bottom side) of the UAV 100. Any number of these attachment surfaces may exist for any of the attachment interfaces. That is, an attachment interface may include more than one attachment surface (e.g., a first attachment surface and a second attachment surface) to facilitate attachment of the parachute deployment system to the UAV 100 in various locations.

[0078] FIG. 3 illustrates a side view of the UAV 100 to further illustrate the side attachment interface 130 located on the first side 118 of the UAV 100. As described above, the side attachment interface 130 of the first side 118 may include the side attachment surface 132. The side attachment surface 132 may be coupled to, or formed with, a portion of a housing 302 of the UAV that is located on the first side 118 of the UAV 100.

[0079] The side attachment interface 130 of the first side 118 may also define mounting holes 306 located along the side attachment surface 132. The mounting holes 306 may be located anywhere along the side attachment surface 132 to removably couple attachments, such as the parachute deployment system, to the first side 118. The side attachment interface 130 of the first side 118 may also include a connector port 308 to electrically couple attachments (e.g., the parachute deployment system) to the UAV 100. The connector port 308 may be located in a recess 310 defined by the top attachment surface 128 and / or the side attachment surface 132 of the first side 118 (see FIGS. 1 and 2). The connector port 308 may also be covered by a cover 312 to prevent moisture and / or debris from entering the connector port 308. Based on the above configuration, the parachute deployment system may beSKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO coupled to the first side 118 of the UAV 100 and be free of obstruction of operation of the UAV 100 (e.g., the propulsion mechanisms 102 and / or the camera system 106 of the UAV 100), as described further below with respect to FIG. 5.

[0080] FIG. 4 illustrates another side view of the UAV 100 to further illustrate the side attachment interface 130 located on the second side 120 of the UAV 100. As described above, the side attachment interface 130 of the second side 120 may include the side attachment surface 132. The side attachment surface 132 may be coupled to, or formed with, a portion of the housing 302 that is located on the second side 120 of the UAV 100. The side attachment interface 130 located on the second side 120 may directly oppose the side attachment interface 130 located on the first side 118. That is, the side attachment interface 130 located on the second side 120 may be symmetrically opposite to the side attachment interface 130 located on the first side 118 or may differ in configuration.

[0081] The side attachment interface 130 of the second side 120 may define mounting holes 406 located along the side attachment surface 132. The mounting holes 406 may be located anywhere along the side attachment surface 132 to removably couple attachments, such as the parachute deployment system, to the second side 120. The side attachment interface 130 of the second side 120 may also include a connector port 408 to electrically couple attachments (e.g., the parachute deployment system) to the UAV 100. The connector port 408 may be located in a recess 410 defined by the top attachment surface 128 and / or the side attachment surface 132 of the second side 120. The connector port 408 may also be covered by a cover 412 to prevent moisture and / or debris from entering the connector port 408. Based on the above configuration, an attachment, the parachute deployment system may in some configurations be coupled to the second side 120 of the UAV 100 in addition to, or in lieu of, the first side 118 of the UAV 100 and may be free of obstruction of operation of the UAV 100 (e.g., the propulsion mechanisms 102 and / or the camera system 106 of the UAV 100).

[0082] To further illustrate, FIG. 5 illustrates the side view of the UAV 100 shown in FIG. 3 (e.g., the side view of the first side 118 of the UAV 100) having a parachute deployment system 500 coupled thereto. The parachute deployment system 500 may include a housing 502 that is configured to house (e.g., contain) a parachute therein. The housing 502 may be coupled to or integrally formed with a mounting bracket 504 of the parachute deployment system 500, whereby the mounting bracket 504 may be configured to couple the parachute deployment system 500 to a side of the UAV 100.SKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO

[0083] By way of example, the mounting bracket 504 may be configured to couple the parachute deployment system 500 to the first side 118 of the UAV 100. In particular, the mounting bracket 504 may couple the parachute deployment system 500 to an attachment interface of the UAV 100, such as the side attachment interface 130 located on the first side 118 of the UAV 100. For example, as described above, the side attachment interface 130 of the first side 118 may include the side attachment surface 132. As such, at least a portion of the mounting bracket 504 may be configured to directly abut the side attachment surface 132. By way of example, the mounting bracket 504 may be mounted to the side attachment surface 132 using one or more fasteners that extend through the mounting bracket 504 and into one or more of the mounting holes 306. In one example, the side attachment surface 132 may define the mounting holes 306, which may be configured to align with one or more mounting holes defined by the mounting bracket 504 of the parachute deployment system 500 such that fasteners may extend through the one or more mounting holes of the mounting bracket 504 and into the mounting holes 306 of the side attachment surface 132 to couple the parachute deployment system 500 to the UAV 100. Thus, the parachute deployment system 500 may be removably coupled to the side attachment interface 130 of the first side 118 such that the parachute deployment system 500 may be positioned adjacent to the first side 118 of the UAV 100.

[0084] The parachute deployment system 500 may also be electrically connected to the UAV 100 when coupled to the first side 118 of the UAV 100. For example, as described above, the UAV 100 may include the connector port 308 as part of (e.g., included within or adjacent to) the side attachment interface 130 of the first side 118. The connector port 308, when the cover 312 is removed or otherwise opened, may receive a connector 506 of the parachute deployment system 500 to electrically couple the parachute deployment system 500 to the UAV 100. The connector 506 may be electrically connected to the parachute deployment system 500 (e.g., to a control unit of the parachute deployment system 500) via wiring 508 extending therebetween. For example, the housing 502 may further define a port 510 and the wiring 508 may extend through the port 510 and may be connected to the control unit of the parachute deployment system 500. The wiring 508 may be further connected to the connector 506 to electrically connect the parachute deployment system 500 to the UAV 100. As such, the parachute deployment system 500 may be both mechanically and electrically connected to the UAV 100 to facilitate communication therebetween.

[0085] While the above description illustrates removably coupling the parachuteSKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO deployment system 500 to the first side 118 of the UAV 100, a similar technique may be used to couple the parachute deployment system 500 to the second side 120 of the UAV 100 or any other portion of the UAV 100 described herein. For example, in some configurations, the mounting bracket 504 of the parachute deployment system 500 may be mounted to the side attachment interface 130 of the second side 120 via the mounting holes 406 of the side attachment interface 130 of the second side 120. As such, various mounting configurations of the parachute deployment system 500 may be possible based on the teachings herein.

[0086] FIG. 6 illustrates a front perspective view of the parachute deployment system 500. FIG. 7 illustrates a back perspective view of the parachute deployment system 500. As discussed above, the parachute deployment system 500 may include a housing 502. The housing 502 may be coupled to or integrally formed with the mounting bracket 504, which may be used to couple (e.g., mount) the parachute deployment system 500 to the UAV 100.

[0087] The housing 502 may define a cavity therein, which may contain the parachute of the parachute deployment system 500 and one or more additional components of the parachute deployment system 500, such as electronics (e.g., circuitry), a launch assembly, other components, or a combination thereof. That is, the parachute or other components may be located within the cavity of the housing 502. For example, as discussed herein, the parachute deployment system 500 may include a control unit that is located within the cavity of the housing 502. The control unit may be electrically connected to the UAV 100 via wiring 508 that extends through the port 510 defined by the housing 502, whereby the wiring 508 is electrically connected to the UAV 100 via the connector 506.

[0088] The housing 502 may further define an opening 612 that permits access to the cavity of the housing 502. To prevent moisture and / or debris from entering the housing 502 (e.g., to protect the integrity of the parachute therein and the parachute deployment system 500 as a whole), the parachute deployment system 500 may further include a cap 614 that is coupled to the housing 502 to cover the opening 612 and thus also enclose the cavity of the housing 502. To ensure proper deployment of the parachute, the cap 614 may be configured to release (e.g., decouple) from the housing 502 when the parachute is deployed. For example, the cap 614 may disconnect from the housing 502 due to a force exerted on an interior side of the cap 614 from the parachute during deployment. As such, the cap 614 may be free of obstruction of the parachute during deployment.

[0089] As discussed above, the parachute deployment system 500 may be removably coupled to the UAV 100 via the mounting bracket 504. For example, the mounting bracketSKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO 504 may couple the parachute deployment system 500 to a side of the UAV 100, such as the first side 118 and / or the second side 120 of the UAV 100. As such, the parachute deployment system 500 may be secured to the UAV 100 during operation (e.g., flight) of the UAV 100. In particular, the mounting bracket 504 may define one or more mounting holes therein, such as the mounting holes 616. Fasteners 618 may extend through one or more of the mounting holes 616 into a respective mounting hole located on the UAV 100, such as one or more of the mounting holes 306 located on the first side 118 of the UAV 100 and / or one or more of the mounting holes 406 located on the second side 120 of the UAV 100. Thus, the parachute deployment system 500 may be prevented from unwanted rotation and / or movement during operation of the UAV 100 and / or during deployment of the parachute of the parachute deployment system 500.

[0090] The parachute deployment system 500 may further include an indicator light 620 disposed along an outer surface of the housing 502. The indicator light 620 may indicate whether the parachute deployment system 500 is armed. For example, the indicator light 620 may be a light-emitting diode (LED) or other type of light (e.g., fluorescent light), which may be electrically connected to the control unit of the parachute deployment system 500. As such, when the parachute deployment system 500 is properly connected to the UAV 100 or otherwise powered, the indicator light 620 may illuminate a particular color, such as, for example, green, to indicate that the parachute deployment system 500 is armed and ready to deploy the parachute if needed. Similarly, when the parachute deployment system 500 is disconnected or not yet armed (e.g., due to manual operations or malfunction), the indicator light 620 may illuminate another designated color, such as, for example, red, to indicate that the parachute deployment system 500 is not armed. It should be noted that the indicator light 620 may utilize any desired colors and may be located anywhere along the housing 502, the mounting bracket 504, or the cap 614 of the parachute deployment system 500. Similarly, in some configurations, the parachute deployment system 500 may be free of the indicator light 620 or may implement another indicator, such as an audible indicator, which may audibly alert when the parachute deployment system 500 is armed or disarmed.

[0091] It should be noted that the housing 502 and the mounting bracket 504 may be any size and / or shape to properly adapt the parachute deployment system 500 to mount to the UAV 100 and / or to properly perform during operation of the parachute deployment system 500. That is, the housing 502 may be shaped to properly tune deployment of the parachute therein and ensure proper landing of the UAV 100. For example, as discussed herein, theSKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO parachute deployment system 500 may include a launching assembly, which may contain an inflator that is configured to deploy (e.g., inflate) the parachute using a compressed gas and / or pyrotechnic. As such, the compressed gas - either contained within the inflator or generated by ignition of the pyrotechnic - may be directed towards the parachute for proper deployment of the parachute. However, due to extreme pressure conditions within the cavity of the housing 502 caused by the compressed gas, the housing 502 may define one or more vents (e.g., vent holes or vent slots), such as the vent 622, to maintain a desired gas pressure within the housing 502. Thus, the vents of the housing 502 may be tuned (e.g., sized) to thereby tune the gas pressure within the housing 502 to effectively deploy the parachute.

[0092] While the mounting bracket 504 may mechanically secure the parachute deployment system 500 to the UAV 100, the mounting bracket 504 may also facilitate additional functionality of the parachute deployment system 500 and the UAV 100. In particular, the parachute deployment system 500 may include a battery retention mechanism 624 movably coupled to the mounting bracket 504. The battery retention mechanism 624 may be configured to maintain a position of the battery 104 of the UAV 100 when the parachute deployment system 500 is coupled to the unmanned aerial vehicle. That is, the battery retention mechanism 624 may engage the battery 104 of the UAV 100 to prevent disconnection of the battery 104 from the UAV 100, such as during operation (e.g., flight) of the UAV 100.

[0093] To further illustrate, FIG. 8 is a close-up view of the battery retention mechanism 624. As discussed above, the battery retention mechanism 624 may be movably coupled to the mounting bracket 504. For example, the battery retention mechanism 624 may be pivotally engaged to the mounting bracket 504 such that the battery retention mechanism 624, or a portion thereof, may pivot with respect to the mounting bracket 504 to engage and / or disengage the battery 104 of the UAV 100, such as in a pivot direction 828.

[0094] The battery retention mechanism 624 may include a release tab 830, an arm 832 extending from the release tab 830, and a latch 834 coupled to the arm 832. The release tab 830, the arm 832, and the latch 834 may be coupled to one another such that movement of one of the release tab 830, the arm 832, or the latch 834 may in turn cause movement of all of the release tab 830, the arm 832, and the latch 834. For example, the release tab 830, the arm 832, and the latch 834 may be integrally formed together to form a single, unitary, movable component of the battery retention mechanism 624 that is configured to pivot in the pivot direction 828.SKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO

[0095] The latch 834 may be or may include a projection, such as a tooth, knob, finger, bump, undulation, or other type of projection that is configured to extend away from the arm 832 and toward the battery 104 of the UAV 100 to engage the battery 104 (e.g., contact the battery 104) and maintain the position of the battery 104. For example, the latch 834 may be configured for receiving by a cutout defined by the battery 104, such as the first cutout 314 located along the first side 118 of the battery 104, as shown in FIG. 3, or the second cutout 414 located along the second side 120 of the battery 104, as shown in FIG. 4. The one or more cutouts defined by the battery 104 may be any opening, slot, groove, channel, or region configured to engage the latch 834 and / or receive the latch 834. For example, the one or more cutouts defined by the battery 104 may be vents configured to dissipate heat generated internally by the battery 104.

[0096] The latch 834 may be configured to move between an engaged position, in which the latch 834 may engage the battery 104 (e.g., the latch 834 may be located within the cutout of the battery 104) to maintain the position of the battery 104, and a disengaged position, in which the latch 834 disengages the battery 104 to thereby permit disconnection of the battery 104 from the UAV 100. For example, the latch 834 may be configured to move from the engaged position to the disengaged position based upon pressing (e.g., movement) of the release tab 830 in a direction towards the UAV 100, such as in the pivot direction 828. The latch 834 may further be configured to move from the disengaged position to the engaged position (i.e., back to the engaged position) when the release tab 830 is released (e.g., pressure on the release tab 830 is released). For example, the battery retention mechanism 624 may include a biasing member 836 that biases the latch 834 towards the battery 104. By way of example, the biasing member 836 may be a spring or elastic member coupled to or formed with one or more of the release tab 830, the arm 832, or the latch 834, whereby the biasing member 836 may bias the latch 834 towards the engaged position. As such, the engaged position may be considered a starting or initial position of the latch 834 that may be maintained unless the release tab 830 is pressed (e.g., moved) in the pivot direction 828 toward the UAV 100 (e.g., toward the back of the mounting bracket 504).

[0097] The battery retention mechanism 624 may be any configuration that facilitates engagement with the battery 104 of the UAV 100 to maintain a position of the battery 104 (e.g., to prevent disconnection of the battery 104) during operation of the UAV 100 when the parachute deployment system 500 is coupled to the UAV 100. That is, the battery retention mechanism 624 may have a different movable member other than the latch 834, the arm 832,SKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO the release tab 830, or a combination thereof. Similarly, the battery retention mechanism 624 may be positioned anywhere along the mounting bracket 504 or another component of the parachute deployment system 500, such as the housing 502.

[0098] In the example of the battery retention mechanism 624 shown in FIGS. 6-8, the battery retention mechanism 624 may be at least partially disposed along and / or within a back portion of the mounting bracket 504 that is configured to face the UAV 100 and the battery 104 of the UAV 100. As shown in FIG. 8, the mounting bracket 504 may include one or more ribs, such as the ribs 838 that define a channel 840 therebetween. The ribs 838 may be interconnected and may extend in any desired direction with respect to one another and with respect to the mounting bracket 504. For example, as shown in FIGS. 7 and 8, the ribs 838 may be interconnected such that all or a portion of the ribs 838 interconnect substantially orthogonal to one another. However, any orientation of the ribs 838 may be possible.

[0099] The ribs 838 may be located anywhere along the mounting bracket 504. For example, the ribs 838 may be located on a back side 842 of the mounting bracket 504 such that the latch 834 - and all or a portion of the battery retention mechanism 624 - are configured for locating between the mounting bracket 504 and the battery 104 of the UAV 100. As shown in FIG. 8, the arm 832 and the latch 834 may be at least partially disposed within the channel 840 such that substantially all of the arm 832 and / or the latch 834 are recessed from, or planar with, a back surface of the mounting bracket 504 formed by terminal ends of the ribs 838. In such a case, the latch 834 or a projection thereof may extend beyond the back surface of the mounting bracket 504 to engage the battery 104 (e.g., the cutout of the battery 104). Additionally, the release tab 830 may be located adjacent to the channel 840 to facilitate movement of the release tab 830 in the pivot direction 828. For example, the release tab 830 may extend away from a side 844 (e.g., a side edge) of the mounting bracket 504 to allow a user to press the release tab 830 in the pivot direction 828.

[0100] Based on the above configuration, the battery retention mechanism 624 may be at least partially disposed within the channel 840 of the mounting bracket 504 and pivotally coupled to the mounting bracket 504 to facilitate movement of the battery retention mechanism 624 (e.g., the latch 834) between the engaged position and the disengaged position. To facilitate pivotal engagement of the battery retention mechanism 624 with respect to the mounting bracket 504, the battery retention mechanism 624 may be coupled to the mounting bracket 504 by a fixed pin 846 that extends through one or more ribs (e.g., the ribs 838) of the mounting bracket 504. For example, the ribs 838 may further define one orSKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO more cavities, such as the cavities 848, which may be located adjacent to the channel 840 and spaced apart from the channel 840 via at least a portion of the ribs 838. As such, the fixed pin 846 may extend through one or more of the ribs 838 such that the fixed pin 846 is at least partially located in one or more of the cavities 848.

[0101] By way of example, as shown in FIG. 8, the fixed pin 846 may extend between a pair of the cavities 848 such that the fixed pin 846 may extend through a pair of the ribs 838 that at least partially form the channel 840. The fixed pin 846 may, for example, extend through apertures defined by the ribs 838. As a result, the fixed pin 846 may also extend through the arm 832 (e.g., an aperture defined by the arm 832) located within the channel 840 and may be secured via a first nut 850. The fixed pin 846 may be fixed in place with respect to the mounting bracket 504 such that the fixed pin 846 may define an axis of rotation of the battery retention mechanism 624 to facilitate pivoting of the battery retention mechanism 624 with respect to the mounting bracket 504 between the engaged position and the disengaged position.

[0102] The battery retention mechanism 624 may be further coupled to the mounting bracket 504 by a sliding pin 852 that extends through one or more of the ribs 838 of the mounting bracket 504. The ribs 838 may be the same ribs in which the fixed pin 846 extends through or may be different ribs. By way of example, as shown in FIG. 8, the sliding pin 852 may extend between another pair of the cavities 848 such that the sliding pin 852 may extend through a pair of the ribs 838 (e.g., the same pair of the ribs 838 as the fixed pin 846 or a different pair of the ribs 838) that at least partially form the channel 840. The sliding pin 852 may, for example, extend through slots 854 defined by the ribs 838. As a result, the sliding pin 852 may also extend through the latch 834 (e.g., an aperture defined by the latch 834) located within the channel 840 and may be secured via a second nut 856. That is, the fixed pin 846 may be coupled to the arm 832 and the sliding pin 852 may be coupled to the latch 834. As such, the sliding pin 852 may be configured for guiding along the slots 854 of the ribs 838 when the battery retention mechanism 624 pivots about the axis of rotation defined by the fixed pin 846 (e.g., in the pivot direction 828). As such, the sliding pin 852 may prevent unwanted lateral movement of the latch 834 to ensure that the latch 834 moves substantially or entirely in the pivot direction 828.

[0103] Based on the above, the battery retention mechanism 624 may facilitate the latch 834 being releasably secured within the cutout (e.g., the first cutout 314 located along the first side 118 of the battery 104 and / or the second cutout 414 located along the second sideSKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO 120 of the battery 104). That is, the battery retention mechanism 624 may be movable based on the above configuration between the engaged position, in which the latch 834 is located within one of the cutouts of the battery 104, and the disengaged position, in which the latch 834 is removed from the cutout of the battery 104 to thereby permit disconnection of the battery 104 from the UAV 100. Engagement of the first cutout 314 of the battery 104 by the latch 834 is further illustrated in the side view of the parachute deployment system 500 and the battery 104 shown in FIG. 9. The UAV 100 has been removed for illustrative purposes only to better show engagement between the battery retention mechanism 624 and the battery 104.

[0104] FIG. 10 illustrates a cross-sectional view of the parachute deployment system 500. FIG. 11 illustrates an exploded view of the parachute deployment system 500. As discussed herein, the parachute deployment system 500 may be coupled to the UAV 100 via the mounting bracket 504. The parachute deployment system 500 may include the housing 502, which may define a cavity 1002 therein. The housing 502 may further define the opening 612, which may permit access to the cavity 1002 and may provide an exit point (e.g., an exit opening) for a parachute 1004 during deployment of the parachute 1004. That is, the parachute 1004 may be located within the cavity 1002 of the housing 502 and, upon deployment, the parachute 1004 may at least partially extend external to the housing 502.

[0105] The housing 502 (e.g., the opening 612 of the housing 502) may be enclosed by the cap 614. As discussed herein, the cap 614 may be configured to release from the housing 502 during deployment of the parachute 1004. The cap 614 may include one or more fingers, such as the fingers 1006, which may be projections or teeth of the cap 614, that are configured to engage the housing 502, such as an internal ridge 1008 of the housing 502 located within the cavity 1002. As such, the fingers 1006 may maintain engagement between the cap 614 and the housing 502 prior to deployment of the parachute 1004.

[0106] A gap between the cap 614 and the housing 502 may also be sealed via a seal 1010. The seal 1010 may be a compressible member, such as an O-ring or gasket, which may be located between the cap 614 and the housing 502. For example, the cap 614 may define a groove 1012 therein. The seal 1010 may be disposed within the groove 1012 to seal a gap between the cap 614 and the housing 502, thereby preventing moisture and / or debris from entering the cavity 1002 of the housing 502.

[0107] The parachute deployment system 500 may further include a launch assembly 1014. The launch assembly 1014 may be configured to deploy the parachute 1004 uponSKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO activation. For example, during deployment, the parachute 1004 may exit the housing 502 through the opening 612 in a direction away from the launch assembly 1014 and a control unit 1016 of the parachute deployment system 500. The launch assembly 1014 may be located within the cavity 1002 of the housing 502 adjacent to the parachute 1004 such that the parachute 1004 may be located between the launch assembly 1014 and the cap 614.

[0108] The launch assembly 1014 may include a puck 1018 defining a puck cavity 1020 therein. The puck 1018 may be coupled to and / or supported by the housing 502. For example, the puck 1018 may be supported by a projection 1022 extending from a base 1024 (e.g., a bottom) of the housing 502 and that is located within the cavity 1002 of the housing 502. The projection 1022 may define a puck mounting hole 1026 and a puck fastener 1028, which may be a screw, bolt, pin, or other mechanical fastener, may extend through the puck 1018 and into the puck mounting hole 1026 to secure the puck 1018 to the housing 502. As such, the puck 1018 may be coupled to the base 1024 of the housing 502. In some configurations, the puck 1018 may be secured to the housing 502 in another manner. For example, the puck 1018 may be adhered to the base 1024 of the housing 502 and / or may be secured to side walls of the housing 502.

[0109] As discussed herein, the launch assembly 1014 may deploy the parachute 1004 upon activation. For example, the launch assembly 1014 may include an inflator 1030 that is located within the puck cavity 1020 and coupled to (e.g., secured to) the puck 1018. Upon activation of the launch assembly 1014, the inflator 1030 may inflate the parachute 1004 to thereby deploy the parachute 1004. As such, the parachute 1004 may deploy to decrease a speed of descent of the UAV 100 during a triggering event, such as a flight anomaly or a malfunction of the UAV 100.

[0110] The inflator 1030 may be any type of inflation device that may be used to deploy the parachute 1004 (e.g., inflate or otherwise move the parachute out of the cavity 1002 to facilitate opening of the parachute 1004). For example, the inflator 1030 may be a compressed gas cartridge that may be configured to release a compressed gas, whereby the compressed gas may be directed through the puck cavity 1020 and into the parachute 1004 to deploy the parachute 1004. In some configurations, the inflator 1030 may be or may include a pyrotechnic, which may be ignited to generate the compressed gas. As such, the inflator 1030 may include at least one of a compressed gas cartridge or a pyrotechnic that is configured to activate to deploy the parachute 1004.[OHl] The inflator 1030 may generate and / or dispense the compressed gas at aSKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO significant pressure, which could cause damage to one or more components of the parachute deployment system 500, such as the parachute 1004. To regulate and / or diffuse the compressed gas traveling towards the parachute 1004, the launch assembly 1014 may further include a sabot 1032. The sabot 1032 may enclose the puck cavity 1020 and may be located between the puck 1018 and the parachute 1004. As such, the compressed gas, when dispensed and / or generated by the inflator 1030, may direct the sabot 1032 towards the parachute 1004 to increase deployment velocity of the parachute 1004. For example, as discussed further below, the sabot 1032 may include fingers spaced apart by notches, and the compressed gas may flow towards the sabot 1032 to direct the sabot 1032 towards the parachute 1004, whereby the fingers may help guide the sabot 1032 and / or prevent rotation of the sabot 1032.

[0112] The sabot 1032 may move (e.g., translate, rotate, etc.) towards the parachute 1004 to deploy the parachute 1004 outside of the housing 502. That is, the compressed gas may direct the sabot 1032 towards the parachute 1004 to thereby move (e.g., push) the parachute 1004 out of the housing 502. Therefore, the sabot 1032 may protect the parachute 1004 substantially from direct contact with the compressed gas and / or may further ensure consistent deployment of the parachute 1004. As such, in some configurations, the sabot 1032 may physically move the parachute 1004 out of the housing 502 based upon release of the compressed gas. Additionally, in some configurations, the sabot 1032 may direct (e.g., diffuse) the flow of gas such that the gas may directly contact the parachute 1004 to thereby deploy the parachute 1004 and / or inflate the parachute 1004.

[0113] In the above examples, the puck 1018 may direct the compressed gas towards the parachute 1004 and away from the control unit 1016 of the parachute deployment system 500. As shown in FIG. 10, the control unit 1016 may be located within the cavity 1002 of the housing 502. The puck 1018 may be located between the control unit 1016 and the parachute 1004. As such, the puck 1018 may protect the control unit 1016 from damage during deployment of the parachute 1004 that may be caused by dispensing and / or generation of the compressed gas by directing the compressed gas away from the control unit 1016 and towards the parachute 1004.

[0114] The control unit 1016 may be secured to the housing 502, such as secured to the base 1024 of the housing 502 via one or more fasteners extending through the control unit 1016 and into control unit mounting holes defined by the housing 502 (see, for example, FIGS. 15-16). As such, the control unit 1016 may be secured beneath the launch assembly 1014 (e.g., beneath the puck 1018) within the cavity 1002 such that the launch assembly 1014SKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO is located between the control unit 1016 and the parachute 1004. Similarly, the control unit 1016 may be located between the puck 1018 and the base 1024 of the housing 502.

[0115] The control unit 1016 may be configured to operate the launch assembly 1014. As discussed herein, the parachute deployment system 500 may be configured to deploy the parachute 1004 in response to a triggering event detected by the parachute deployment system 500. For example, responsive to the triggering event, the inflator 1030 may activate (e.g., dispense the compressed gas and / or ignite a pyrotechnic of the inflator 1030) to inflate the parachute 1004 and thereby deploy the parachute 1004. In such a case, the control unit 1016 may be configured to detect the triggering event and activate the inflator 1030.

[0116] To detect the triggering event, the control unit 1016 may include a compact, integrated electronic assembly that may monitor flight dynamics and autonomously initiate deployment of the parachute 1004 based upon the triggering event. In some configurations, the control unit 1016 may be in communication with a control system (e.g., a control unit) of the UAV 100, which may relay information, such as flight characteristics, to the control unit 1016 to detect whether a triggering event has occurred. In some configurations, the control system of the UAV 100 may communicate a command to the control unit 1016, whereby the command may initiate activation of the inflator 1030 using the control unit 1016.

[0117] The control unit 1016 may include a microcontroller or system-on-chip (SoC) capable of executing real-time data processing algorithms. The control unit 1016 may interface with one or more onboard sensors of the UAV 100, such as at least one of an accelerometer, a gyroscope, an inertial measurement unit (IMU), a barometric pressure sensor, a GPS module, the camera system 106 (e.g., an image sensor thereof), or other sensor to continuously assess flight parameters of the UAV 100, such as at least one of velocity, orientation, altitude, or acceleration of the UAV 100. By sampling and analyzing this data, the control unit 1016 may detect deviations indicative of critical anomalies, such as uncontrolled descent, loss of orientation, or propulsion failure, using predefined threshold logic and / or machine learning algorithms tailored to the expected performance envelope of the UAV 100.

[0118] Upon detecting the triggering event, the control unit 1016 may initiate a deployment sequence by energizing an inflator circuit. This circuit typically includes a transistor-based switching mechanism (e.g., MOSFET or IGBT) controlled by a microcontroller to deliver power from an onboard energy source (such as a lithium-polymer battery or capacitor bank) to the inflator 1030. The inflator 1030 may be activated via an electrical impulse that ruptures a sealing membrane or opens a valve to rapidly releaseSKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO pressurized gas and / or ignites a pyrotechnic of the inflator 1030.

[0119] The triggering event may be any flight anomaly of the UAV 100 and / or malfunction of the UAV 100. Triggering events that may initiate deployment of the parachute 1004 may include, for example, a range of flight anomalies or hardware malfunctions indicative of an impending or active failure of the UAV 100. Examples may include an uncontrolled descent of the UAV 100 due to sudden loss of lift or propulsion, excessive angular rotation or tumbling of the UAV 100 detected via a gyroscope, or rapid acceleration of the UAV 100 inconsistent with normal flight patterns, such as during a crash or mid-air collision. Other potential triggering events may include communication loss with a ground control station (e.g., a user device), GPS signal failure resulting in uncontrolled navigation of the UAV 100, severe deviation from a programmed flight path, or detection of critical power system faults such as battery thermal runaway or voltage collapse of the battery 104 of the UAV 100. Such triggering events may warrant immediate deployment of the parachute 1004 to prevent injury, equipment loss, or damage to surrounding property. As such, the control unit 1016 may detect the triggering event and activate the inflator 1030 in response to detection of the triggering event.

[0120] Additionally, as described above, the parachute deployment system 500 may include the wiring 508, which is omitted from FIG. 10 for illustrative purposes. The wiring 508 may be electrically connected to the control unit 1016, such as at a connection point 1034 of the control unit 1016. The connection point 1034 may be any electrical connection between the wiring 508 and the control unit 1016. For example, the connection point 1034 may be a connector (e.g., a wire-to-board connector, a magnetic connector, a snap-fit connector, etc.), a soldered connection, a terminal block, or any other type of connection that may facilitate electrical connection between the control unit 1016 and the wiring 508 to thereby electrically connect the control unit 1016 - and thus the parachute deployment system 500 - to the UAV 100 (e.g., the control system thereof) via the connector 506.

[0121] As discussed herein, deployment of the parachute 1004 may result in the parachute 1004 extending at least partially outside of the housing 502. Such deployment may be facilitated by a significant force exerted on the parachute 1004 by activation of the inflator 1030. To ensure proper deployment of the parachute 1004, the parachute 1004 may be coupled to the puck 1018 by a tether, such as the tether 1136 shown in FIG. 11. The tether 1136 may be configured to maintain connection between the parachute 1004 and the puck 1018 during and after deployment of the parachute 1004 to ensure that the parachute 1004SKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO remains connected to the parachute deployment system 500 and thus also to the UAV 100. As such, the parachute 1004 may be tethered to the launch assembly 1014 to maintain connection between the parachute 1004 and the launch assembly 1014 during and after activation of the launch assembly 1014 (e.g., activation of the inflator 1030).

[0122] To maintain such connection, the tether 1136 may be any material, such as a cable or a rope connected to the parachute 1004 or a portion of the parachute 1004 that extends towards the puck 1018. That is, the tether 1136 may be coupled to or integrally formed with the parachute 1004. As discussed further below, the tether 1136 may be coupled to the puck 1018 in any desired manner, such as using one or more mechanical engagement means, one or more mechanical fasteners, one or more adhesives, or a combination thereof.

[0123] FIG. 12 illustrates a close-up view of the parachute deployment system 500. The housing 502 of the parachute deployment system has been removed for illustrative purposes. As shown in FIG. 12, the parachute 1004 may be coupled to the puck 1018 by the tether 1136 extending therebetween. In particular, the tether 1136 may extend through a slot 1238 defined by the sabot 1032 such that the tether 1136 may be secured to the puck 1018, thereby preventing disconnection of the parachute 1004 from the parachute deployment system 500 during deployment.

[0124] As discussed herein, the sabot 1032 may enclose the puck cavity 1020 of the puck 1018 such that the sabot 1032 may be positioned between the puck 1018 and the parachute 1004, thereby diffusing the compressed gas dispersed by the inflator 1030 of the launch assembly 1014. For example, the sabot 1032 may include one or more fingers, such as the fingers 1240, which may be spaced apart by one or more notches, such as the notches 1242, located therebetween. When the sabot 1032 is coupled to the puck 1018, such as via mechanical connection means (e.g., mechanical interlocking between the puck 1018 and the fingers 1240, one or more fasteners, etc.) and / or adhesion, the compressed gas dispersed by the inflator 1030 may flow through one or more of the notches 1242 (i.e., between the fingers 1240) to inflate the parachute 1004.

[0125] As shown in FIG. 12, the fingers 1240 may extend in any orientation with respect to the sabot 1032 and / or with respect to the puck 1018 in a direction partially or substantially towards the puck 1018 to define openings for the compressed gas located between the sabot 1032 and the puck 1018 and through the notches 1242. To facilitate diffusion and / or directing of the compressed gas, the sabot 1032 may be any desired size, shape, material, or a combination thereof. For example, the sabot 1032 may be substantially rigid or may beSKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO flexible. By way of example, the sabot 1032 may be made from at least one of a thermoplastic material, a high-temperature composite material, a phenolic or paper-based material, a metal (e.g., a metal or a metal alloy), another material, or a combination thereof.

[0126] The sabot 1032 may also be further shaped and / or tuned to guide the compressed air in a desired manner towards the parachute 1004. For example, the sabot 1032 may include one or more undulations, grooves, openings (e.g., the slot 1238), or other features that may alter the flow of the compressed gas between the sabot 1032 and the parachute 1004 and / or may help direct the sabot 1032 towards the parachute 1004. By way of example, the sabot 1032 may include one or more dimples, such as the dimple 1244, which may be located on a surface of the sabot 1032 that faces the parachute 1004. The dimple 1244 may alter the flow of the compressed air during deployment of the parachute 1004, which may thereby reduce suction or drag forces that might otherwise cause the sabot 1032 to interfere with deployment of the parachute 1004. The dimple 1244 may also help ensure proper alignment between the sabot 1032 and the puck 1018 during assembly of the parachute deployment system 500.

[0127] FIG. 13 is a bottom perspective view of the puck 1018 illustrating a bottom side 1346 of the puck 1018. FIG. 14 is a top perspective view of the puck 1018 illustrating a top side 1348 of the puck 1018. The sabot 1032 has been removed in FIG. 14 for illustrative purposes.

[0128] As described herein, the launch assembly 1014 may include the inflator 1030, which may be located within the puck cavity 1020 defined by the puck 1018. For example, the inflator 1030 may be disposed within a retaining area 1350 of the puck 1018. The retaining area 1350 may be a groove, channel, receiving portion, or other means for properly locating the inflator 1030 with respect to the puck 1018. As such, the retaining area 1350 may at least partially maintain engagement between the puck 1018 and the inflator 1030.Moreover, the inflator 1030 may be secured within the retaining area 1350 by a retaining mechanism 1352, which may be one or more mechanical retaining means, such as a fastener (e.g., screw, bolt, pin, etc.), clip, tie (e.g., zip tie), or a combination thereof. As such, the inflator 1030 may remain substantially stationary with respect to the puck 1018 during deployment of the parachute 1004.

[0129] The control unit 1016 may activate the inflator 1030 (e.g., initiate deployment and / or generation of the compressed gas to inflate the parachute 1004), using an activation mechanism 1354. That is, the control unit 1016 may include or may be coupled to the activation mechanism 1354, which may be coupled to the bottom side 1346 of the puck 1018,SKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO such as via activation mechanism fasteners 1356. In some configurations, the activation mechanism 1354 may be coupled to the top side 1348 of the puck 1018.

[0130] The activation mechanism 1354 may activate the inflator 1030 in response to a command provided by the control unit 1016. For example, the activation mechanism 1354 may activate the inflator 1030 in response to receiving a command provided by the control unit 1016 when the control unit 1016 determines that a triggering event, such as those described herein, has occurred. By way of example, the inflator 1030 may include a pyrotechnic and the activation mechanism 1354 may ignite the pyrotechnic, such as by sending an electrical current to or through the activation mechanism 1354. That is, the activation mechanism 1354 may be or may include an ignition element, such as a squib, bridgewire, electro-pyrotechnic initiator, or a combination thereof. In another example, the inflator 1030 may include a compressed gas and the activation mechanism 1354 may release the compressed gas from the inflator 1030, such as by sending a current or voltage signal to an electrically actuated device (e.g., a solenoid valve, pyrotechnic actuator, rupture disk initiator, etc.) that controls the inflator 1030 to open its gas reservoir and thereby release the compressed gas.

[0131] To maintain a pressure of the compressed gas once dispersed to inflate the parachute 1004, the puck 1018 may define one or more vents, such as the vents 1358. The vents 1358 may vent a portion of the compressed gas once dispersed towards the control unit 1016 to maintain a pressure of the gas within the housing 502. For example, a portion of the gas may be vented through the vents 1358, which may ultimately be vented out of the housing 502 via the vent 622 defined by the housing 502. As such, any number, size, or location of the vents 1358 may be possible to tune performance of the parachute deployment system 500 during deployment of the parachute 1004.

[0132] As discussed herein, the tether 1136 may couple the parachute 1004 to the puck 1018. By way of example, and as shown in FIG. 13, the tether 1136 may extend through a portion of the puck 1018, such as through a tether opening 1360 defined by the puck 1018, such that the tether 1136 is secured to a knub 1362 extending from the bottom side 1346 of the puck 1018. As such, when the parachute 1004 is deployed and moves outside of the housing 502, the tether 1136 may be even further tightened around the knub 1362 to maintain engagement between the parachute 1004 and the puck 1018.

[0133] FIG. 15 illustrates a perspective view of the control unit 1016 of the parachute deployment system 500. As discussed herein, the control unit 1016 may be configured toSKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO detect a triggering event that may warrant deployment of the parachute 1004 to safely land the UAV 100. Similarly, the control unit 1016 may be configured to activate the inflator 1030 to deploy the parachute 1004, such as by using the activation mechanism 1354. Moreover, the control unit 1016 may be in communication with the UAV 100, such as via the wiring 508 connected to the control unit 1016 and the connection point 1034.

[0134] As shown in FIG. 10, the control unit 1016 may be coupled to the housing 502 to maintain a position of the control unit 1016 with respect to the housing 502. For example, the control unit 1016 may include a printed circuit board 1564, which may define one or more control unit holes, such as the control unit holes 1566. The control unit holes 1566 may align with control unit mounting holes defined by the housing 502 and located within the cavity 1002 of the housing 502. As such, fasteners may extend through the control unit holes 1566 and into the control unit mounting holes defined by the housing 502 to thereby secure the control unit 1016 to the housing 502. Additionally, the control unit 1016 may define a through-hole 1568, which may be centrally located along the printed circuit board 1564. The through-hole 1568 may receive the projection 1022 extending from the base 1024 of the housing 502 and facilitate connection of the projection 1022 to the puck 1018.

[0135] FIG. 16 illustrates a top-down view of the housing 502 of the parachute deployment system 500 to further illustrate mounting schemes utilized to couple the control unit 1016 and the puck 1018 to the housing 502. As discussed herein, the control unit 1016 may be coupled to the base 1024 via fasteners extending through the control unit holes 1566 and into control unit mounting holes defined by the base 1024 of the housing 502, such as the control unit mounting holes 1670. Similarly, the puck 1018 may be coupled to the base 1024 via the puck fastener 1028 extending through the puck 1018 and into the puck mounting hole 1026 defined by the projection 1022 that is located on the base 1024 of the housing 502.

[0136] The base 1024 of the housing 502 may also provide venting for the compressed gas dispersed by the inflator 1030. For example, as shown in FIG. 16, the base 1024 may include one or more gore vents, such as the gore vents 1672. The gore vents 1672 may be or may include a respective one of the gores 1674. The gore vents 1672 and the gores 1674 may facilitate controlled airflow (e.g., flow of the compressed gas) and regulate deployment dynamics of the parachute 1004. The gores 1674 may be defined as elongated, tapered regions of material or structural features that align with the curvature of the housing 502, thereby channeling internal air pressure along predetermined flow paths during and immediately following activation of the inflator 1030. The gore vents 1672 may be aperturesSKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO or perforations that enable the release or redistribution of the gas within the housing 502 during deployment of the parachute 1004. The arrangement of the gore vents 1672 and the gores 1674 may reduce localized overpressure, minimize parasitic drag on the parachute 1004 during deployment, promote symmetric expansion of the parachute 1004 (e.g., a canopy of the parachute), or a combination thereof.

[0137] FIG. 17 is a block diagram 1700 of a network configuration of the UAV 100 and the parachute deployment system 500. As discussed herein, the parachute deployment system 500 may be removably coupled to the UAV 100 and may be in electrical communication with the UAV 100 (e.g., the control unit 1016 of the parachute deployment system 500 may be electrically coupled to the UAV 100).

[0138] Electrical connection between the parachute deployment system 500 and the UAV 100 may be established based upon the connector 506 of the parachute deployment system 500 being inserted into a connector port of the UAV 100, such as the connector port 308 located on the first side 118 of the UAV 100. Such an electrical connection may establish communication between the parachute deployment system 500 and the UAV 100, thereby facilitating transfer of data and / or powering the parachute deployment system 500 via a power source of the UAV 100 (e.g., the battery 104). In some configurations, the parachute deployment system 500 and the UAV 100 may additionally, or alternatively, be in wireless communication with one another and / or may each include their own dedicated power source (e.g., the parachute deployment system 500 may include its own battery).

[0139] The UAV 100 may be controlled autonomously by one or more onboard processing aspects or remotely controlled by an operator. For example, an operator (e.g., a user) may control operation or otherwise communicate with the UAV 100 via a user interface 1702. The user interface 1702 may be an electronic device with which the user may interface with the UAV 100 before, during, or after flight of the UAV 100. The electronic device may be an electronic device that is remotely located from the UAV 100, such as, for example, a mobile phone, tablet, laptop, desktop, wireless controller, or a combination thereof. In some configurations, the user may also interface directly with the parachute deployment system 500 via the user interface 1702.

[0140] The UAV 100 and the user interface 1702 may be in wireless communication (e.g., wireless connection) via a network 1704 connection. The user interface 1702 may communicate with the UAV 100 via the network 1704 using a wireless communications link (e.g., a Wi-Fi network, a Bluetooth link, a ZigBee link, or another network or link). The userSKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO interface 1702 may also, in some configurations, communicate with the UAV 100 via a cloud-based network in which the user interface 1702 is located remotely from the UAV 100.

[0001] To support such a connection between the UAV 100 and the user interface 1702, the user interface 1702 and / or the UAV 100 may also be in communication with a server 1706. The server 1706 may be remotely located and configured to store data for the user interface 1702 and / or the UAV 100. The server 1706 may also be configured to store data for the parachute deployment system 500 or data for the UAV 100 associated with the parachute deployment system 500. As such, the server 1706 may communicate with the user interface 1702, the UAV 100, the parachute deployment system 500 (e.g., via the UAV 100), or a combination thereof via the network 1704. As a result, the user interface 1702, the UAV 100, the parachute deployment system 500, or a combination thereof may access data stored on the server 1706.

[0002] By way of example, the UAV 100 may access the server 1706 in response to the parachute deployment system 500 being electrically connected to the UAV 100. The UAV 100 may access the server 1706 to obtain data associated with the parachute deployment system 500, such as flight characteristic information to adjust flight of the UAV 100 to accommodate the additional payload of the parachute deployment system 500.

[0003] Such data may also be obtained by the user interface 1702 to adjust an experience for the user. That is, the user interface 1702 may be adjusted to provide additional functionality, such as control of the parachute deployment system 500 via the user interface 1702. For example, a user device (e.g., tablet, phone, wireless controller, etc.) may be in communication with the UAV 100 and the server 1706 via the network 1704, whereby the user device outputs the user interface 1702 as a graphical display. In such a case, the user interface 1702 displayed on the user device may be modified to provide additional control and / or functionality of the parachute deployment system 500, such as the ability to manually arm and / or disarm the parachute deployment system 500.

[0141] Based on the above, the network 1704 may in some configurations facilitate entirely remote communication between a user and the UAV 100 (e.g., via the user interface 1702), including remote communication between the user and the parachute deployment system 500. Thus, the parachute deployment system 500 may only require an initial installation in-person and may thereafter be accessible and / or operational offsite by the user.

[0142] FIG. 18 illustrates a block diagram 1800 of the UAV 100 in communication (e.g., electrically connected) with the parachute deployment system 500. As discussed above, theSKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO UAV 100 may include one or more attachment interfaces (e.g., the side attachment interface 130 of the first side 118 and the side attachment interface 130 of the second side 120) that may mechanically receive the parachute deployment system 500 and removably couple the parachute deployment system 500 to the UAV 100. The UAV 100 may also include a communication interface 1802, a user interface 1804, a processing apparatus 1806, and a data storage device 1808.

[0004] The communication interface 1802 may be configured to communicate with a communication interface 1810 of the parachute deployment system 500, which may be part of the control unit 1016 of the parachute deployment system 500. Such communication may establish the transfer of data between the UAV 100 and the parachute deployment system 500. For example, in response to electrically coupling the parachute deployment system 500 to the UAV 100, intrinsic characteristics of the parachute deployment system 500 may be transmitted to the UAV 100 to modify one or more characteristics of the UAV 100, such as flight characteristics (e.g., propulsion characteristics), power consumption characteristics, user interface characteristics (e.g., the user interface 1804), or a combination thereof.

[0005] The processing apparatus 1806 may be in communication with the communication interface 1802. The processing apparatus 1806 may process data received by the communication interface 1802 from the parachute deployment system 500. The processing apparatus 1806 may process such data to determine whether adjustments to one or more characteristics of the UAV 100 are necessary to accommodate the parachute deployment system 500, such as the characteristics described above. For example, the processing apparatus 1806 may process the intrinsic characteristics of the parachute deployment system 500 to determine a weight of the parachute deployment system 500. Based on such weight, flight characteristics of the UAV 100 may be adjusted to ensure successful flight of the UAV 100 with the parachute deployment system 500 coupled thereto.

[0006] Additionally, the processing apparatus 1806 and / or the communication interface 1802 may access the data storage device 1808. The data storage device 1808 may be accessed to retrieve stored data (e.g., information) pertaining to the UAV 100 and / or the parachute deployment system 500.

[0143] The control unit 1016 of the parachute deployment system 500 may also include a processing apparatus 1812 and a data storage device 1814. The processing apparatus 1812 may operate in a similar manner to the processing apparatus 1806. Additionally, the data storage device 1814 may operate or function in a similar manner to the data storage deviceSKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO 1808. By way of example, the parachute deployment system 500 may receive information from the UAV 100 (e.g., via transmission between the communication interface 1802 and the communication interface 1810), whereby the information from the UAV 100 may be processed by the processing apparatus 1812. Such information from the UAV 100 may also require the processing apparatus 1812 to retrieve data from the data storage device 1814.

[0007] For example, the UAV 100 may transmit operating commands to the parachute deployment system 500 for operation of the parachute deployment system 500 via the user interface 1804, such as manual arming and / or disarming of the parachute deployment system 500. The user interface 1804 may be similar to the user interface 1702 described above. In response to transmitting the operating commands to the parachute deployment system 500, the processing apparatus 1812 may evaluate the operating commands to determine an operation of the parachute deployment system 500 in response to the operating commands. Such operating commands may be cross-referenced with data stored in the data storage device 1814 to confirm the appropriate operation of the parachute deployment system 500. However, the above is intended for illustrative purposes only. As such, the UAV 100 and the parachute deployment system 500 may operate in any number of ways.

[0008] The block diagram 1700 of the network configuration and the block diagram 1800 may include additional software and / or hardware components, which may be included in the network 1704, the UAV 100, the parachute deployment system 500, or a combination thereof.

[0009] For example, one or more of the above may include various engines, each of which may be constructed, programmed, configured, or otherwise adapted, to carry out a function or set of functions. The term engine as used herein means a tangible device, component, or arrangement of components implemented using hardware, such as by an application-specific integrated circuit (ASIC) or field-programmable gate array (FPGA), for example, or as a combination of hardware and software, such as by a processor-based computing platform and a set of program instructions that transform the computing platform into a special-purpose device to implement the particular functionality. An engine may also be implemented as a combination of the two, with certain functions facilitated by hardware alone, and other functions facilitated by a combination of hardware and software. For example, such engines may be part of, or may include, the processing apparatus 1806 of the UAV 100 and / or the processing apparatus 1812 of the parachute deployment system 500.

[0010] In an example, the software may reside in executable or non-executable form on a tangible machine-readable storage medium, such as on the server 1706, the data storageSKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO device 1808 of the UAV 100, the data storage device 1814 of the parachute deployment system 500, or a combination thereof. Software residing in non-executable form may be compiled, translated, or otherwise converted to an executable form prior to, or during, runtime. In an example, the software, when executed by the underlying hardware of the engine (e.g., the processing apparatus 1806 and / or the processing apparatus 1812), causes the hardware to perform the specified operations. Accordingly, an engine is physically constructed, or specifically configured (e.g., hardwired), or temporarily configured (e.g., programmed) to operate in a specified manner or to perform part or all of any operations described herein in connection with that engine.

[0011] Considering examples in which engines are temporarily configured, each of the engines may be instantiated at different moments in time. For example, where the engines comprise a general-purpose hardware processor core configured using software; the general-purpose hardware processor core may be configured as respective different engines at different times. Software may accordingly configure a hardware processor core, for example, to constitute a particular engine at one instance of time and to constitute a different engine at a different instance of time.

[0012] In certain implementations, at least a portion, and in some cases, all, of an engine may be executed on the processor(s) of one or more computers (e.g., the electronic device for the user interface 1702, the electronic componentry of the UAV 100, the control unit 1016 of the parachute deployment system 500, etc.) that execute an operating system, system programs, and application programs, while also implementing the engine using multitasking, multithreading, distributed (e.g., cluster, peer-peer, cloud, etc.) processing where appropriate, or other such techniques. Accordingly, each engine may be realized in a variety of suitable configurations and should generally not be limited to any particular implementation exemplified herein, unless such limitations are expressly called out.

[0013] In addition, an engine may itself be composed of more than one sub-engine, each of which may be regarded as an engine in its own right. Moreover, in the embodiments described herein, each of the various engines corresponds to a defined functionality.However, it should be understood that in other contemplated embodiments, each functionality may be distributed to more than one engine. Likewise, in other contemplated embodiments, multiple defined functionalities may be implemented by a single engine that performs those multiple functions, possibly alongside other functions, or distributed differently among a set of engines than specifically illustrated in the examples herein.SKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO

[0144] Furthermore, the above functionality may be applicable to hardware and / or software of the user interface 1702 (e.g., the remote electronic device providing the user interface 1702), the server 1706, the UAV 100, and the parachute deployment system 500.

[0145] FIG. 19 is a flowchart showing an example of a technique 1900 for deploying the parachute 1004 of the parachute deployment system 500 when coupled to the UAV 100. The technique 1900 can be executed using computing devices, such as the systems, hardware, and software described with respect to FIGS. 1-18. The technique 1900 can be performed, for example, by executing a machine-readable program or other computer-executable instructions, such as routines, instructions, programs, or other code. The steps, or operations, of the technique 1900 or another technique, method, process, or algorithm described in connection with the implementations disclosed herein can be implemented directly in hardware, firmware, software executed by hardware, circuitry, or a combination thereof.

[0146] At 1902, the technique 1900 may determine that the parachute deployment system 500 is mounted (e.g., removably coupled) to the UAV 100. The parachute deployment system 500 may be mounted to an attachment surface of the UAV, such as those shown in FIGS. 1-5. For example, the UAV 100 may automatically detect the attachment of the parachute deployment system 500 using the processing apparatus 1806 and / or the data storage device 1808 of the UAV 100 shown in FIG. 18.

[0147] At 1904, the technique 1900 may also include determining that the parachute deployment system 500 is electrically coupled to the UAV 100. For example, the parachute deployment system 500 may be electrically coupled to the UAV 100 via the connector 506 being inserted into the connector port 308 located along the first side 118 of the UAV 100. Determining that the parachute deployment system 500 is electrically coupled to the UAV 100 may include executing one or more protocols to automatically verify communication with the parachute deployment system 500 and / or ensure that the parachute deployment system 500 is recognized and / or otherwise approved for use by the UAV 100. In some implementations, the parachute deployment system 500 may automatically provide or convey information about the parachute deployment system 500, including, but not limited to, type of parachute deployment system 500, features, characteristics, functionality associated with the parachute deployment system 500, control mechanisms, other information, or a combination thereof.

[0148] Such protocols may also be used to encrypt communication between the parachute deployment system 500 and the UAV 100 and may include, for example, MAVLink or LCMSKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO protocols. The protocols may be split into separate protocol levels (e.g., higher-tier security protocols and lower-tier security protocols) based upon certain operations of the UAV 100 and / or the parachute deployment system 500. For example, lower-tier protocols may utilize a USB protocol layer (e.g., VID / PID) without cryptographic authentication, while higher-tier protocols (e.g., for control of the UAV 100) may utilize USB Authentication protocol, USB-ethernet, and transport layer security (TLS), secure socket layer (SSL) security, or similar and / or additional cryptographic authentication schemes (e.g., x.509-based certificate scheme to accommodate US federal encryption requirements). The protocols may also be utilized to establish approved users and / or approved UAVs (e.g., the UAV 100), such as through the network 1704. Moreover, the protocols may also be utilized to communicate with and / or identify serialized attachments, whereby the parachute deployment system 500 may have a unique product identification (ID) and / or a proprietary serial number.

[0149] In addition to the above protocols, a hardware ID pin may be utilized for the parachute deployment system 500, whereby the hardware ID pin may include a resistor with analog value or a similar hardware scheme to represent the parachute deployment system 500, thereby potentially eliminating software protocols in certain configurations. For example, integrated circuit communication protocols (e.g., IC and / or IC2) may be utilized to identify the parachute deployment system 500.

[0150] The technique 1900 may also include detecting, using the control unit 1016 of the parachute deployment system 500, a triggering event at 1906. The triggering event may be any one or more of the triggering events described herein, such as a flight anomaly of the UAV 100 and / or a malfunction of the UAV 100.

[0151] Responsive to detecting the triggering event, the technique 1900 may include deploying the parachute 1004 using the launch assembly 1014 of the parachute deployment system 500 at 1908. Deployment of the parachute 1004 may be completed based upon the teachings herein. For example, deploying the parachute 1004 may include activating the inflator 1030 of the launch assembly 1014 to inflate the parachute 1004. The inflator 1030 may include a pyrotechnic and activating the inflator 1030 may include igniting the pyrotechnic. The inflator 1030 may also, or alternatively, include a compressed gas and activating the inflator 1030 may include releasing the compressed gas from the inflator 1030 (e.g., from a cartridge of the inflator 1030).

[0152] Illustrative Embodiments

[0153] The implementations of this disclosure include a parachute deployment system forSKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO an unmanned aerial vehicle. The parachute deployment system includes a housing defining a cavity therein. The parachute deployment system also includes a parachute located within the cavity of the housing. The parachute deployment system further includes a launch assembly configured to deploy the parachute and located within the cavity of the housing. The launch assembly includes a puck defining a puck cavity therein. The launch assembly also includes an inflator located within the puck cavity and disposed within a retaining area of the puck, wherein the inflator is secured within the retaining area by a retaining mechanism. The launch assembly further includes a sabot enclosing the puck cavity and located between the puck and the parachute. Responsive to a triggering event, the inflator is configured to activate to inflate the parachute and thereby deploy the parachute.

[0154] In some implementations, the inflator is a compressed gas cartridge that is configured to release a compressed gas, and the compressed gas is directed through the puck cavity and into the parachute to deploy the parachute.

[0155] In some implementations, the sabot is configured to be directed towards the parachute as the compressed gas flows towards the parachute.

[0156] In some implementations, the sabot includes fingers spaced apart by notches, and the fingers are configured to guide the sabot within the cavity of the housing towards the parachute.

[0157] In some implementations, the housing defines an opening that permits access to the cavity of the housing, and the parachute deployment system further includes a cap that is coupled to the housing to cover the opening.

[0158] In some implementations, the cap is configured to release from the housing when the parachute is deployed.

[0159] In some implementations, the triggering event is one or more of a flight anomaly of the unmanned aerial vehicle or a malfunction of the unmanned aerial vehicle.

[0160] In some implementations, the parachute deployment system includes a control unit located within the cavity of the housing. The control unit is configured to detect the triggering event and activate the inflator.

[0161] In some implementations, the control unit includes or is coupled to an activation mechanism. The activation mechanism is configured to activate the inflator in response to a command provided by the control unit.

[0162] In some implementations, the inflator includes a pyrotechnic and the activation mechanism is configured to ignite the pyrotechnic, or the inflator includes a compressed gasSKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO and the activation mechanism is configured to release the compressed gas from the inflator.

[0163] In some implementations, the puck is located between the control unit and the parachute, and the puck is configured to protect the control unit from damage during deployment of the parachute.

[0164] In some implementations, the sabot is made from at least one of a thermoplastic material, a high-temperature composite material, a phenolic or paper-based material, or a metal.

[0165] The implementations of this disclosure also include a parachute deployment system for an unmanned aerial vehicle. The parachute deployment system includes a housing defining a cavity therein. The parachute deployment system also includes a cap that encloses the cavity of the housing and that is coupled to the housing. The parachute deployment system further includes a parachute located within the cavity of the housing. The parachute deployment system also includes a launch assembly located within the housing adjacent to the parachute such that the parachute is located between the launch assembly and the cap. The launch assembly includes a puck defining a puck cavity therein. The launch assembly also includes an inflator located within the puck cavity and secured to the puck, wherein the inflator includes at least one of a compressed gas cartridge or a pyrotechnic that is configured to activate to deploy the parachute. The launch assembly further includes a sabot enclosing the puck cavity and located between the puck and the parachute, wherein a flow of gas generated by the inflator is configured to direct the sabot towards the parachute. The parachute deployment system also includes a control unit located within the cavity of the housing. The control unit is configured to detect a triggering event and activate the inflator in response to detection of the triggering event.

[0166] In some implementations, the triggering event is one or more of a flight anomaly of the unmanned aerial vehicle or a malfunction of the unmanned aerial vehicle.

[0167] In some implementations, the parachute deployment system is configured to attach to a side of the unmanned aerial vehicle, and the parachute is configured to deploy to decrease a speed of descent of the unmanned aerial vehicle during the triggering event.

[0168] In some implementations, the puck defines one or more vents, and the one or more vents are configured to vent a portion of the gas towards the control unit to maintain a pressure of the gas within the housing.

[0169] The implementations of this disclosure also include a method of deploying a parachute of a parachute deployment system for an unmanned aerial vehicle. The methodSKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO includes determining that the parachute deployment system is mounted to the unmanned aerial vehicle. The method also includes detecting, using a control unit of the parachute deployment system, a triggering event, wherein the triggering event is one or more of a flight anomaly of the unmanned aerial vehicle or a malfunction of the unmanned aerial vehicle. The method further includes, responsive to detecting the triggering event, deploying the parachute using a launch assembly of the parachute deployment system.

[0170] In some implementations, prior to detecting the triggering event, the method further includes determining that the parachute deployment system is electrically coupled to the unmanned aerial vehicle.

[0171] In some implementations, deploying the parachute using the launch assembly of the parachute deployment system includes activating an inflator of the launch assembly to inflate the parachute.

[0172] In some implementations, the inflator includes a pyrotechnic and activating the inflator includes igniting the pyrotechnic, or the inflator includes a compressed gas and activating the inflator includes releasing the compressed gas from the inflator.

[0173] The implementations of this disclosure also include a parachute deployment system for an unmanned aerial vehicle. The parachute deployment system includes a housing defining a cavity therein. The parachute deployment system also includes a cap coupled to the housing and that encloses the cavity of the housing. The parachute deployment system further includes a parachute located within the cavity of the housing. The parachute deployment system also includes a launch assembly configured to deploy the parachute upon activation, wherein the launch assembly is located within the cavity of the housing adjacent to the parachute. The launch assembly includes a puck defining a puck cavity therein. The launch assembly also includes an inflator located within the puck cavity and coupled to the puck. The launch assembly further includes a sabot enclosing the puck cavity and located between the puck and the parachute. The parachute deployment system further includes a control unit configured to operate the launch assembly, wherein the control unit is located within the cavity of the housing and the launch assembly is located between the control unit and the parachute.

[0174] In some implementations, the parachute is coupled to the puck by a tether, and the tether is configured to maintain connection between the parachute and the puck during and after deployment of the parachute.

[0175] In some implementations, the tether extends through a slot defined by the sabot.SKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO

[0176] In some implementations, the housing defines an opening that permits access to the cavity of the housing, and the cap covers the opening.

[0177] In some implementations, during deployment, the parachute is configured to exit the housing through the opening in a direction away from the launch assembly and the control unit.

[0178] In some implementations, the cap is configured to release from the housing during deployment of the parachute.

[0179] In some implementations, the cap defines a groove therein and a seal is disposed within the groove to seal a gap between the cap and the housing.

[0180] In some implementations, the housing is coupled to or integrally formed with a mounting bracket, and the mounting bracket is configured to couple the parachute deployment system to a side of the unmanned aerial vehicle.

[0181] In some implementations, the puck is supported by a projection extending from a base of the housing and that is located within the cavity of the housing.

[0182] In some implementations, the projection defines a puck mounting hole, and a fastener extends through the puck and into the puck mounting hole to secure the puck to the housing.

[0183] In some implementations, the control unit is secured to the base of the housing via one or more fasteners extending through the control unit and into control unit mounting holes defined by the housing.

[0184] In some implementations, the housing further defines a port, wiring extends through the port and is connected to the control unit, and the wiring is further connected to a connector that is configured to electrically connect the parachute deployment system to the unmanned aerial vehicle.

[0185] The implementations of this disclosure also include a parachute deployment system for an unmanned aerial vehicle. The parachute deployment system includes a housing defining a cavity therein, wherein the housing is integrally formed with a mounting bracket that is configured to couple the parachute deployment system to an attachment interface located on a side of the unmanned aerial vehicle. The parachute deployment system also includes a cap coupled to the housing and that encloses the cavity of the housing. The parachute deployment system further includes a parachute located within the cavity of the housing. The parachute deployment system also includes a launch assembly configured to deploy the parachute upon activation, wherein the launch assembly is located within theSKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO cavity of the housing adjacent to the parachute. The parachute deployment system further includes a control unit configured to operate the launch assembly, wherein the control unit is located within the cavity of the housing and the launch assembly is located between the control unit and the parachute.

[0186] In some implementations, the parachute is tethered to the launch assembly to maintain connection between the parachute and the launch assembly during and after activation of the launch assembly.

[0187] In some implementations, the launch assembly further includes a puck defining a puck cavity therein, wherein the puck is coupled to a base of the housing and the control unit is located between the puck and the base of the housing. The launch assembly also includes an inflator located within the puck cavity and coupled to the puck, wherein upon activation of the launch assembly, the inflator is configured to inflate the parachute to thereby deploy the parachute.

[0188] In some implementations, the parachute deployment system includes an indicator light disposed along an outer surface of the housing. The indicator light is configured to indicate whether the parachute deployment system is armed.

[0189] The implementations of this disclosure also include an unmanned aerial vehicle system. The unmanned aerial vehicle system includes an unmanned aerial vehicle that includes an attachment interface located on a side of the unmanned aerial vehicle. The unmanned aerial vehicle system also includes a parachute deployment system configured to removably couple to the attachment interface such that the parachute deployment system is positioned adjacent to the side of the unmanned aerial vehicle. The parachute deployment system is configured to deploy a parachute in response to a triggering event detected by the parachute deployment system.

[0190] In some implementations, the parachute deployment system includes a housing defining a cavity therein, the parachute is disposed within the housing prior to deployment, and the housing is integrally formed with a mounting bracket that is configured to removably couple the parachute deployment system to the attachment interface.

[0191] In some implementations, the attachment interface includes an attachment surface, wherein at least a portion of the mounting bracket is configured to directly abut the attachment surface. The attachment interface also includes a connector port configured to receive a connector of the parachute deployment system to electrically couple the parachute deployment system to the unmanned aerial vehicle.SKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO

[0192] In some implementations, the attachment surface defines one or more mounting holes that are configured to align with one or more mounting holes defined by the mounting bracket of the parachute deployment system such that fasteners may extend through the one or more mounting holes of the mounting bracket and the one or more mounting holes of the attachment surface to couple the parachute deployment system to the unmanned aerial vehicle.

[0193] The implementations of this disclosure also include a parachute deployment system for an unmanned aerial vehicle. The parachute deployment system includes a housing defining a cavity therein, wherein the housing is coupled to or integrally formed with a mounting bracket that is configured to couple the parachute deployment system to the unmanned aerial vehicle. The parachute deployment system also includes a parachute located within the cavity of the housing. The parachute deployment system further includes a battery retention mechanism movably coupled to the mounting bracket and configured to maintain a position of a battery of the unmanned aerial vehicle when the parachute deployment system is coupled to the unmanned aerial vehicle. The battery retention mechanism includes a release tab. The battery retention mechanism also includes an arm extending from the release tab. The battery retention mechanism further includes a latch coupled to the arm, wherein the latch is configured to engage the battery to maintain the position of the battery.

[0194] In some implementations, the latch is configured for receiving by a cutout defined by the battery.

[0195] In some implementations, the latch is configured to move between an engaged position, in which the latch is configured to engage the battery to maintain the position of the battery, and a disengaged position, in which the latch is configured to disengage the battery to thereby permit disconnection of the battery from the unmanned aerial vehicle.

[0196] In some implementations, the latch is configured to move from the engaged position to the disengaged position based upon pressing the release tab in a direction towards the unmanned aerial vehicle.

[0197] In some implementations, the latch is configured to move from the disengaged position to the engaged position when the release tab is released.

[0198] In some implementations, the battery retention mechanism further includes a biasing member that is configured to bias the latch towards the battery.

[0199] In some implementations, the mounting bracket includes one or more ribs that define a channel therebetween, and the arm and the latch are at least partially disposed withinSKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO the channel.

[0200] In some implementations, the release tab is located adjacent to the channel and extends away from a side of the mounting bracket.

[0201] In some implementations, the one or more ribs are located on a back side of the mounting bracket such that the latch is configured to be located between the mounting bracket and the battery of the unmanned aerial vehicle.

[0202] In some implementations, the latch includes a projection that is configured to contact the battery to maintain the position of the battery.

[0203] In some implementations, the battery retention mechanism is pivotally engaged to the mounting bracket.

[0204] The implementations of this disclosure also include a parachute deployment system for an unmanned aerial vehicle. The parachute deployment system includes a housing that contains a parachute, wherein the housing is integrally formed with a mounting bracket that is configured to couple the parachute deployment system to the unmanned aerial vehicle, and wherein the housing includes one or more ribs that are located on a back side of the mounting bracket and that define a channel therebetween. The parachute deployment system also includes a battery retention mechanism configured to maintain a position of a battery of the unmanned aerial vehicle when the parachute deployment system is coupled to the unmanned aerial vehicle. The battery retention mechanism is at least partially disposed within the channel of the mounting bracket and pivotally coupled to the mounting bracket.

[0205] In some implementations, the battery retention mechanism is configured to pivot between an engaged position, in which the battery retention mechanism is configured to engage the battery to maintain the position of the battery, and a disengaged position, in which the battery retention mechanism is configured to disengage the battery to thereby permit disconnection of the battery from the unmanned aerial vehicle.

[0206] In some implementations, the battery retention mechanism is coupled to the mounting bracket by a fixed pin that extends through one or more ribs of the mounting bracket, and the fixed pin defines an axis of rotation of the battery retention mechanism to facilitate pivoting of the battery retention mechanism with respect to the mounting bracket.

[0207] In some implementations, the battery retention mechanism is further coupled to the mounting bracket by a sliding pin that extends through the one or more ribs of the mounting bracket. The one or more ribs define a slot, and the sliding pin is configured for guiding along the slot when the battery retention mechanism pivots about the axis of rotation.SKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO

[0208] In some implementations, the battery retention mechanism includes a release tab. The battery retention mechanism also includes an arm extending from the release tab. The battery retention mechanism further includes a latch coupled to the arm and configured to engage the battery to maintain the position of the battery. The fixed pin is coupled to the arm and the sliding pin is coupled to the latch.

[0209] The implementations of this disclosure also include an unmanned aerial vehicle system. The unmanned aerial vehicle system includes an unmanned aerial vehicle that includes an attachment interface located on a side of the unmanned aerial vehicle and a battery. The unmanned aerial vehicle system also includes a parachute deployment system configured to removably couple to the attachment interface such that the parachute deployment system is positioned adjacent to the side of the unmanned aerial vehicle. The parachute deployment system includes a battery retention mechanism that is configured to engage the battery to prevent disconnection of the battery from the unmanned aerial vehicle.

[0210] In some implementations, the battery retention mechanism includes a latch that is releasably secured within a cutout defined by the battery.

[0211] In some implementations, the battery retention mechanism is movable between an engaged position, in which the latch is located within the cutout, to a disengaged position, in which the latch is removed from the cutout to thereby permit disconnection of the battery from the unmanned aerial vehicle.

[0212] In some implementations, the parachute deployment system includes a mounting bracket that removably couples the parachute deployment system to the attachment interface, and the battery retention mechanism is movably coupled to the mounting bracket.

[0213] Persons skilled in the art will understand that the various embodiments of the disclosure described herein and shown in the accompanying figures constitute non-limiting examples, and that additional components and features may be added to any of the embodiments discussed herein above without departing from the scope of the present disclosure. Additionally, persons skilled in the art will understand that the elements and features shown or described in connection with one embodiment may be combined with those of another embodiment without departing from the scope of the present disclosure and will appreciate further features and advantages of the presently disclosed subject matter based on the description provided. Variations, combinations, and / or modifications to any of the embodiments and / or features of the embodiments described herein that are within the abilities of a person having ordinary skill in the art are also within the scope of the disclosure, as areSKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO alternative embodiments that may result from combining, integrating, and / or omitting features from any of the disclosed embodiments.

[0214] Use of broader terms such as “comprises,” “includes,” and “having” should be understood to provide support for narrower terms such as “consisting of,” “consisting essentially of,” and “comprised substantially of.” Accordingly, the scope of protection is not limited by the description set out above, but is defined by the claims that follow, and includes all equivalents of the subject matter of the claims.

[0215] In the preceding description, reference may be made to the spatial relationship between the various structures illustrated in the accompanying drawings, and to the spatial orientation of the structures. However, as will be recognized by those skilled in the art after a complete reading of this disclosure, the structures described herein may be positioned and oriented in any manner suitable for their intended purpose. Thus, the use of terms such as “above,” “below,” “upper,” “lower,” “inner,” “outer,” “left,” “right,” “upward,” “downward,” “inward,” “outward,” etc., should be understood to describe a relative relationship between the structures and / or a spatial orientation of the 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 figure(s).

[0216] Additionally, terms such as “approximately,” “generally,” “substantially,” and the like should be understood to allow for variations in any numerical range or concept with which they are associated and encompass variations on the order of 25% (e.g., to allow for manufacturing tolerances and / or deviations in design). For example, the term “generally parallel” should be understood as referring to configurations in with the pertinent components are oriented so as to define an angle therebetween that is equal to 180° ± 25% (i.e., an angle that lies within the range of (approximately) 135° to (approximately) 225°) and the term “generally orthogonal” should be understood as referring to configurations in with the pertinent components are oriented so as to define an angle therebetween that is equal to 90° ± 25% (i.e., an angle that lies within the range of (approximately) 67.5° to (approximately) 112.5°). The term “generally parallel” should thus be understood as referring to encompass configurations in which the pertinent components are arranged in parallel relation, and the term “generally orthogonal” should thus be understood as referring to encompass configurations in which the pertinent components are arranged in orthogonal relation.

[0217] Although terms such as “first,” “second,” “third,” etc., may be used herein to describe various operations, elements, components, regions, and / or sections, these operations,SKY. 106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO 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 could be termed a second operation, element, component, region, or section without departing from the scope of the present disclosure.

[0218] Each and every claim is incorporated as further disclosure into the specification and represents 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 each be interpreted to include only A, only B, only C, or any combination of A, B, and C.

Claims

SKY.

106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO What is claimed is:

1. A parachute deployment system for an unmanned aerial vehicle, comprising:a housing defining a cavity therein;a parachute located within the cavity of the housing; anda launch assembly configured to deploy the parachute and located within the cavity of the housing, wherein the launch assembly includes:a puck defining a puck cavity therein;an inflator located within the puck cavity and disposed within a retaining area of the puck, wherein the inflator is secured within the retaining area by a retaining mechanism; anda sabot enclosing the puck cavity and located between the puck and the parachute,wherein responsive to a triggering event, the inflator is configured to activate to inflate the parachute and thereby deploy the parachute.

2. The parachute deployment system of claim 1, wherein the inflator is a compressed gas cartridge that is configured to release a compressed gas, and wherein the compressed gas is directed through the puck cavity and into the parachute to deploy the parachute.

3. The parachute deployment system of claim 2, wherein the sabot is configured to be directed towards the parachute as the compressed gas flows towards the parachute.

4. The parachute deployment system of claim 3, wherein the sabot includes fingers spaced apart by notches, and wherein the fingers are configured to guide the sabot within the cavity of the housing towards the parachute.

5. The parachute deployment system of claim 1, wherein the housing defines an opening that permits access to the cavity of the housing, and wherein the parachute deployment system further includes a cap that is coupled to the housing to cover the opening.

6. The parachute deployment system of claim 5, wherein the cap is configured to release from the housing when the parachute is deployed.SKY.

106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO7. The parachute deployment system of claim 1, wherein the triggering event is one or more of a flight anomaly of the unmanned aerial vehicle or a malfunction of the unmanned aerial vehicle.

8. The parachute deployment system of claim 1, further comprising a control unit located within the cavity of the housing, wherein the control unit is configured to detect the triggering event and activate the inflator.

9. The parachute deployment system of claim 8, wherein the control unit includes or is coupled to an activation mechanism, and wherein the activation mechanism is configured to activate the inflator in response to a command provided by the control unit.

10. The parachute deployment system of claim 9, wherein the inflator includes a pyrotechnic and the activation mechanism is configured to ignite the pyrotechnic or the inflator includes a compressed gas and the activation mechanism is configured to release the compressed gas from the inflator.

11. The parachute deployment system of claim 8, wherein the puck is located between the control unit and the parachute, and the puck is configured to protect the control unit from damage during deployment of the parachute.

12. The parachute deployment system of claim 1, wherein the sabot is made from at least one of a thermoplastic material, a high-temperature composite material, a phenolic or paperbased material, or a metal.

13. A parachute deployment system for an unmanned aerial vehicle, comprising:a housing defining a cavity therein;a cap that encloses the cavity of the housing and that is coupled to the housing; a parachute located within the cavity of the housing;a launch assembly located within the housing adjacent to the parachute such that the parachute is located between the launch assembly and the cap, wherein the launch assembly includes:SKY.

106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO a puck defining a puck cavity therein;an inflator located within the puck cavity and secured to the puck, wherein the inflator includes at least one of a compressed gas cartridge or a pyrotechnic that is configured to activate to deploy the parachute; anda sabot enclosing the puck cavity and located between the puck and the parachute, wherein a flow of gas generated by the inflator is configured to direct the sabot towards the parachute; anda control unit located within the cavity of the housing, wherein the control unit is configured to detect a triggering event and activate the inflator in response to detection of the triggering event.

14. The parachute deployment system of claim 13, wherein the triggering event is one or more of a flight anomaly of the unmanned aerial vehicle or a malfunction of the unmanned aerial vehicle.

15. The parachute deployment system of claim 13, wherein the parachute deployment system is configured to attach to a side of the unmanned aerial vehicle, and wherein the parachute is configured to deploy to decrease a speed of descent of the unmanned aerial vehicle during the triggering event.

16. The parachute deployment system of claim 13, wherein the puck defines one or more vents, and wherein the one or more vents are configured to vent a portion of the gas towards the control unit to maintain a pressure of the gas within the housing.

17. A method of deploying a parachute of a parachute deployment system for an unmanned aerial vehicle, comprising:determining that the parachute deployment system is mounted to the unmanned aerial vehicle;detecting, using a control unit of the parachute deployment system, a triggering event, wherein the triggering event is one or more of a flight anomaly of the unmanned aerial vehicle or a malfunction of the unmanned aerial vehicle; andresponsive to detecting the triggering event, deploying the parachute using a launch assembly of the parachute deployment system.SKY.

106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO18. The method of claim 17, wherein prior to detecting the triggering event, the method further comprises determining that the parachute deployment system is electrically coupled to the unmanned aerial vehicle.

19. The method of claim 17, wherein deploying the parachute using the launch assembly of the parachute deployment system includes activating an inflator of the launch assembly to inflate the parachute.

20. The method of claim 19, wherein the inflator includes a pyrotechnic and activating the inflator includes igniting the pyrotechnic or the inflator includes a compressed gas and activating the inflator includes releasing the compressed gas from the inflator.

21. A parachute deployment system for an unmanned aerial vehicle, comprising:a housing defining a cavity therein;a cap coupled to the housing and that encloses the cavity of the housing;a parachute located within the cavity of the housing;a launch assembly configured to deploy the parachute upon activation, wherein the launch assembly is located within the cavity of the housing adjacent to the parachute, and wherein the launch assembly includes:a puck defining a puck cavity therein;an inflator located within the puck cavity and coupled to the puck; and a sabot enclosing the puck cavity and located between the puck and the parachute; anda control unit configured to operate the launch assembly, wherein the control unit is located within the cavity of the housing and the launch assembly is located between the control unit and the parachute.

22. The parachute deployment system of claim 21, wherein the parachute is coupled to the puck by a tether, and wherein the tether is configured to maintain connection between the parachute and the puck during and after deployment of the parachute.

23. The parachute deployment system of claim 22, wherein the tether extends through aSKY.

106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO slot defined by the sabot.

24. The parachute deployment system of claim 21, wherein the housing defines an opening that permits access to the cavity of the housing, and wherein the cap covers the opening.

25. The parachute deployment system of claim 24, wherein during deployment, the parachute is configured to exit the housing through the opening in a direction away from the launch assembly and the control unit.

26. The parachute deployment system of claim 24, wherein the cap is configured to release from the housing during deployment of the parachute.

27. The parachute deployment system of claim 21, wherein the cap defines a groove therein and a seal is disposed within the groove to seal a gap between the cap and the housing.

28. The parachute deployment system of claim 21, wherein the housing is coupled to or integrally formed with a mounting bracket, and wherein the mounting bracket is configured to couple the parachute deployment system to a side of the unmanned aerial vehicle.

29. The parachute deployment system of claim 21, wherein the puck is supported by a projection extending from a base of the housing and that is located within the cavity of the housing.

30. The parachute deployment system of claim 29, wherein the projection defines a puck mounting hole, and wherein a fastener extends through the puck and into the puck mounting hole to secure the puck to the housing.

31. The parachute deployment system of claim 29, wherein the control unit is secured to the base of the housing via one or more fasteners extending through the control unit and into control unit mounting holes defined by the housing.SKY.

106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO 32. The parachute deployment system of claim 21, wherein the housing further defines a port, wiring extends through the port and is connected to the control unit, and the wiring is further connected to a connector that is configured to electrically connect the parachute deployment system to the unmanned aerial vehicle.

33. A parachute deployment system for an unmanned aerial vehicle, comprising:a housing defining a cavity therein, wherein the housing is integrally formed with a mounting bracket that is configured to couple the parachute deployment system to an attachment interface located on a side of the unmanned aerial vehicle;a cap coupled to the housing and that encloses the cavity of the housing;a parachute located within the cavity of the housing;a launch assembly configured to deploy the parachute upon activation, wherein the launch assembly is located within the cavity of the housing adjacent to the parachute; and a control unit configured to operate the launch assembly, wherein the control unit is located within the cavity of the housing and the launch assembly is located between the control unit and the parachute.

34. The parachute deployment system of claim 33, wherein the parachute is tethered to the launch assembly to maintain connection between the parachute and the launch assembly during and after activation of the launch assembly.

35. The parachute deployment system of claim 33, wherein the launch assembly further comprises:a puck defining a puck cavity therein, wherein the puck is coupled to a base of the housing and the control unit is located between the puck and the base of the housing; and an inflator located within the puck cavity and coupled to the puck, wherein upon activation of the launch assembly, the inflator is configured to inflate the parachute to thereby deploy the parachute.

36. The parachute deployment system of claim 33, further comprising an indicator light disposed along an outer surface of the housing, wherein the indicator light is configured to indicate whether the parachute deployment system is armed.

37. An unmanned aerial vehicle system, comprising:SKY.

106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO an unmanned aerial vehicle that includes an attachment interface located on a side of the unmanned aerial vehicle; anda parachute deployment system configured to removably couple to the attachment interface such that the parachute deployment system is positioned adjacent to the side of the unmanned aerial vehicle, wherein the parachute deployment system is configured to deploy a parachute in response to a triggering event detected by the parachute deployment system.

38. The unmanned aerial vehicle system of claim 37, wherein the parachute deployment system includes a housing defining a cavity therein, the parachute is disposed within the housing prior to deployment, and the housing is integrally formed with a mounting bracket that is configured to removably couple the parachute deployment system to the attachment interface.

39. The unmanned aerial vehicle system of claim 38, wherein the attachment interface includes:an attachment surface, wherein at least a portion of the mounting bracket is configured to directly abut the attachment surface; anda connector port configured to receive a connector of the parachute deployment system to electrically couple the parachute deployment system to the unmanned aerial vehicle.

40. The unmanned aerial vehicle system of claim 39, wherein the attachment surface defines one or more mounting holes that are configured to align with one or more mounting holes defined by the mounting bracket of the parachute deployment system such that fasteners may extend through the one or more mounting holes of the mounting bracket and the one or more mounting holes of the attachment surface to couple the parachute deployment system to the unmanned aerial vehicle.

41. A parachute deployment system for an unmanned aerial vehicle, comprising:a housing defining a cavity therein, wherein the housing is coupled to or integrally formed with a mounting bracket that is configured to couple the parachute deployment system to the unmanned aerial vehicle;a parachute located within the cavity of the housing; andSKY.

106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO a battery retention mechanism movably coupled to the mounting bracket and configured to maintain a position of a battery of the unmanned aerial vehicle when the parachute deployment system is coupled to the unmanned aerial vehicle, wherein the battery retention mechanism includes:a release tab;an arm extending from the release tab; anda latch coupled to the arm, wherein the latch is configured to engage the battery to maintain the position of the battery.

42. The parachute deployment system of claim 41, wherein the latch is configured for receiving by a cutout defined by the battery.

43. The parachute deployment system of claim 41, wherein the latch is configured to move between an engaged position, in which the latch is configured to engage the battery to maintain the position of the battery, and a disengaged position, in which the latch is configured to disengage the battery to thereby permit disconnection of the battery from the unmanned aerial vehicle.

44. The parachute deployment system of claim 43, wherein the latch is configured to move from the engaged position to the disengaged position based upon pressing the release tab in a direction towards the unmanned aerial vehicle.

45. The parachute deployment system of claim 44, wherein the latch is configured to move from the disengaged position to the engaged position when the release tab is released.

46. The parachute deployment system of claim 41, wherein the battery retention mechanism further includes a biasing member that is configured to bias the latch towards the battery.

47. The parachute deployment system of claim 41, wherein the mounting bracket includes one or more ribs that define a channel therebetween, and wherein the arm and the latch are at least partially disposed within the channel.SKY.

106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO 48. The parachute deployment system of claim 47, wherein the release tab is located adjacent to the channel and extends away from a side of the mounting bracket.

49. The parachute deployment system of claim 47, wherein the one or more ribs are located on a back side of the mounting bracket such that the latch is configured to be located between the mounting bracket and the battery of the unmanned aerial vehicle.

50. The parachute deployment system of claim 41, wherein the latch includes a projection that is configured to contact the battery to maintain the position of the battery.

51. The parachute deployment system of claim 41, wherein the battery retention mechanism is pivotally engaged to the mounting bracket.

52. A parachute deployment system for an unmanned aerial vehicle, comprising:a housing that contains a parachute, wherein the housing is integrally formed with a mounting bracket that is configured to couple the parachute deployment system to the unmanned aerial vehicle, and wherein the housing includes one or more ribs that are located on a back side of the mounting bracket and that define a channel therebetween; anda battery retention mechanism configured to maintain a position of a battery of the unmanned aerial vehicle when the parachute deployment system is coupled to the unmanned aerial vehicle, wherein the battery retention mechanism is at least partially disposed within the channel of the mounting bracket and pivotally coupled to the mounting bracket.

53. The parachute deployment system of claim 52, wherein the battery retention mechanism is configured to pivot between an engaged position, in which the battery retention mechanism is configured to engage the battery to maintain the position of the battery, and a disengaged position, in which the battery retention mechanism is configured to disengage the battery to thereby permit disconnection of the battery from the unmanned aerial vehicle.

54. The parachute deployment system of claim 52, wherein the battery retention mechanism is coupled to the mounting bracket by a fixed pin that extends through one or more ribs of the mounting bracket, and wherein the fixed pin defines an axis of rotation of the battery retention mechanism to facilitate pivoting of the battery retention mechanism withSKY.

106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO respect to the mounting bracket.

55. The parachute deployment system of claim 54, wherein the battery retention mechanism is further coupled to the mounting bracket by a sliding pin that extends through the one or more ribs of the mounting bracket, the one or more ribs define a slot, and the sliding pin is configured for guiding along the slot when the battery retention mechanism pivots about the axis of rotation.

56. The parachute deployment system of claim 55, wherein the battery retention mechanism includes:a release tab;an arm extending from the release tab; anda latch coupled to the arm and configured to engage the battery to maintain the position of the battery,wherein the fixed pin is coupled to the arm and the sliding pin is coupled to the latch.

57. An unmanned aerial vehicle system, comprising:an unmanned aerial vehicle that includes an attachment interface located on a side of the unmanned aerial vehicle and a battery; anda parachute deployment system configured to removably couple to the attachment interface such that the parachute deployment system is positioned adjacent to the side of the unmanned aerial vehicle, wherein the parachute deployment system includes a battery retention mechanism that is configured to engage the battery to prevent disconnection of the battery from the unmanned aerial vehicle.

58. The unmanned aerial vehicle system of claim 57, wherein the battery retention mechanism includes a latch that is releasably secured within a cutout defined by the battery.

59. The unmanned aerial vehicle system of claim 58, wherein the battery retention mechanism is movable between an engaged position, in which the latch is located within the cutout, to a disengaged position, in which the latch is removed from the cutout to thereby permit disconnection of the battery from the unmanned aerial vehicle.SKY.

106. WOOl UTILITY Attorney Docket No.: NSTR-195-A-WO 60. The unmanned aerial vehicle system of claim 57, wherein the parachute deployment system includes a mounting bracket that removably couples the parachute deployment system to the attachment interface, and wherein the battery retention mechanism is movably coupled to the mounting bracket.

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