Device for storing and remotely launching unmanned aerial vehicles

Abstract

In various embodiments, professional vehicle launch systems and methods are provided to enable personnel to safely launch and operate one or more UAVs from a vehicle or other mobile location. In various embodiments, a launch system includes a launch device and an operations terminal. The launch device is adapted to be mounted on an exterior surface of a vehicle and is communicably coupled to the operations terminal, which is operable from an interior of the vehicle. The vehicle launch system allows an operator to control one or more UAVs from within the vehicle without requiring the operator to walk outside of the vehicle to interact with the UAV or launch device.

Description

[0001] Cross-reference to related applications

[0002] This patent application claims priority and benefit to Norwegian patent application No. 20180791, filed on June 7, 2018, entitled “Device for Storing and Remotely Launching Unmanned Aerial Vehicles,” the entire contents of which are incorporated herein by reference. Technical Field

[0003] One or more embodiments of this disclosure generally relate to unmanned aerial vehicles (UAVs), and more specifically, for example, to means, systems, and methods for storing, remotely launching, and controlling one or more UAVs. Background Technology

[0004] In many military and civilian operations, it is often desirable to keep personnel positioned and protected within a vehicle. However, without additional auxiliary equipment, the enclosed nature of the vehicle limits the possibility of surveying areas of interest and provides limited situational awareness and overview. In many scenarios, enhancing situational awareness, such as through the use of UAVs, can be critical when confined within a vehicle. However, launching UAVs without endangering personnel can be challenging. Given these considerations, there is a continued need for improved systems and methods for launching, storing, and controlling UAVs from mobile locations such as vehicles. Summary of the Invention

[0005] In various embodiments, specialized vehicle launch systems and methods are provided to enable personnel to safely launch and operate one or more UAVs from a vehicle or other mobile location. In various embodiments, a launch system includes a launching device and an operating terminal. The launching device is adapted to be mounted on an external surface of the vehicle and communicatively coupled to the operating terminal, which can be operated from inside the vehicle or other protected location. The vehicle launch system allows an operator to control one or more UAVs from inside the vehicle without requiring the operator to go outside the vehicle to interact with the UAVs or the launching device.

[0006] The scope of this invention is defined by the claims, which are incorporated herein by reference. A more comprehensive understanding of embodiments of the invention, as well as other advantages thereof, will be given to those skilled in the art by considering the following detailed description of one or more embodiments. Reference will be made to the accompanying drawings, which will first be briefly described. Attached Figure Description

[0007] Figures 1A to 1C An example of a vehicle launching system according to an embodiment of the present disclosure is shown.

[0008] Figures 2A to 2B An example of a vehicle launcher according to an embodiment of the present disclosure is shown.

[0009] Figure 3 The illustration shows a box and a launcher housing according to an embodiment of the present disclosure.

[0010] Figure 4 A side view of a launch box according to an embodiment of the present disclosure is shown.

[0011] Figure 5A The illustration shows a box for securing a UAV in a storage location according to an embodiment of the present disclosure.

[0012] Figure 5B The illustration shows a box for securing a UAV in a release / launch position according to an embodiment of the present disclosure.

[0013] Figure 6 The illustration shows a box for securing a UAV in a release / launch position according to an embodiment of the present disclosure.

[0014] Figure 7 Electrical and processing components for a vehicle launching system according to an embodiment of the present disclosure are illustrated.

[0015] Figures 8A to 8I Various views of a launch box and / or housing in a storage position and a launch position according to embodiments of the present disclosure are shown.

[0016] Figure 9 An embodiment of the external connector and the corresponding mating connector according to an embodiment of the present disclosure is illustrated.

[0017] Figure 10 This illustrates a method of using a vehicle launching device according to one or more embodiments.

[0018] Figure 11 This illustration shows an embodiment of a UAV being secured in a release / launch position and a mechanical release assembly, according to one or more embodiments.

[0019] The embodiments and advantages of this disclosure will be best understood by referring to the following detailed description. It should be understood that the same reference numerals are used to identify the same elements illustrated in one or more of the figures. Detailed Implementation

[0020] Several aspects of this disclosure generally relate to systems and methods for launching, storing, and controlling unmanned aerial vehicles (UAVs). In various embodiments, specialized vehicle launch systems and methods are provided to enable personnel to safely launch and operate one or more UAVs from a vehicle or other mobile location.

[0021] Reference Figures 1A to 1C Various embodiments of a vehicle launch system are described. The vehicle launch system includes a launch container 100 (also referred to herein as a launch device) and an operating terminal 160. The launch container 100 is adapted to be mounted on the outer surface of a vehicle 150, such as a land vehicle, a water vehicle, or other mobile structure. In various embodiments, the launch container 100 may be mounted to another device or structure and / or operate as a stand-alone unit. The operating terminal 160 is a mobile computing device communicatively coupled to the launch container 100 and operable from inside the vehicle 150 or from another protected location. The vehicle launch system allows an operator to control one or more UAVs (such as UAV 120) and launch UAV 120 from inside the vehicle 150 without requiring the operator to go outside the vehicle 150 to interact with the UAV 120 or the launch container 100.

[0022] In the illustrated embodiment, the launch container 100 includes a plurality of magazines 110 (also referred to herein as cassettes) adapted to be securely inserted into corresponding cavities (or recesses) formed in the launch container 100. One magazine 110 holds a single UAV 120 within its housing, which is positioned within a bracket 130 of the magazine 110. The magazine 110 is also adapted to have the UAV 120 moved from a storage location inside the magazine 110 by an actuator (e.g., ...). Figure 1A Example) Move to the launch position (e.g.) Figure 1B (For example), the actuator is attached to arm 142 to move the UAV such that it is positioned outside the storage cartridge 110 for launch. Each storage cartridge 110 is adapted to be easily removed and replaced by another storage cartridge 110, which may include another UAV 120.

[0023] The tray 130 is positioned on or constitutes a portion of the cover 140 of the storage cartridge 110. The tray 130 includes a charging point for charging the UAV 120 when it is in the tray 130. The tray 130 also includes a release mechanism that holds the UAV 130 in the tray 130 when in the storage position and during launch (e.g., when the UAV 120 is positioned as...). Figure 1B(In the illustrated launch position) the UAV 120 is released. The bracket 130 can also connect the UAV 120 to the operating terminal 160 for communication via a communication link. In various embodiments, the storage cartridge 110 includes one or more connectors configured to mate with corresponding connectors on the launch container 100, connecting the storage cartridge to a power source, such as the power supply of the vehicle 150, the operating terminal 160, an internal battery, or another power source. The UAV 120 can be charged when the storage cartridge 110 is positioned in the launch container 100. In various embodiments, additional connections enabling communication between the UAV 120 and the operating terminal 160 may be present, including wireless and wired communication links. In some embodiments, the launch container 100 includes electronics for communicating with and controlling the UAV 120. For example, the release mechanism may be adapted to close in response to a “close” instruction or command received from the operating terminal 160 via the transmitter 100 (e.g., holding the UAV 120 in the tray), and to open in response to an “open” instruction or command received from the operating terminal 160 via the transmitter 100 (e.g., releasing the UAV 120).

[0024] In various embodiments, the launch box 100 is also adapted to protect the UAV 120 from weather conditions. For example, the launch box 100 may include one or more components for cooling the interior of the launch box, such as a cooling fan. The launch box 100 may also include components such as heating wires for heating the inner and / or outer walls of the launch box 100 to facilitate snow and ice removal.

[0025] In some embodiments, the actuator, arm 142, and cover 140, along with associated components, are configured to break ice and obstructions positioned on the outside of cover 140 when arm 142 moves from a storage position (e.g., when cover 140 is in the closed position) to a firing position (e.g., when cover 140 is in the open position). In one embodiment, the point of rotation of the cover securing the storage cartridge is provided with play and an upward-pushing spring in the vertical direction. When the actuator is activated (which moves arm 142) but fails to open cover 140 (e.g., because ice has formed around the cover), the upward force is converted by the spring into movement of cover 140 relative to the hinge. Play around the hinge allows the actuator to push the front of cover 140 outward. This reduces the amount of movement the actuator must make, resulting in a higher force that could potentially move obstructions, such as breaking ice on top.

[0026] During operation, UAV 120 remains in its storage position, protected from environmental influences, charged, and ready for operation. When the operator provides instructions from the operating terminal 160, actuators are activated, moving UAV 120 from its storage position to its launch position. UAV 120 is then activated based on instructions from the operating terminal 160, providing sufficient thrust to climb, a release mechanism on the carrier 130 opens, and UAV 120 is launched to survey the region of interest. In various embodiments, the flight path and control of UAV 120 may be pre-programmed by the operating terminal 160, programmed (e.g., when UAV 120 is held), or controlled by a flight controller on the operating terminal 160 during flight. In some embodiments, UAV 120 terminates its flight by landing on the carrier 130 and returning to its storage position in the storage cassette 110. Flight data, such as images and videos captured during flight, can be downloaded from UAV 120 to the operating terminal 160 via a communication link.

[0027] refer to Figures 2A to 2B This document describes embodiments of the vehicle launch container. In various embodiments, the launch container 200 can be used in civilian, military, and other environments, and can be adapted to mount vehicles, including ground vehicles such as consumer cars and military vehicles such as combat tanks, as well as water vehicles. In one embodiment, the launch container 200 can be mounted to the outside of the vehicle in a location that allows actuation of the storage compartment and launch of the UAV to proceed unimpeded (e.g., bolted at a connection point specified in the bottom of the launch container). In one embodiment, the launch container is adapted to mount one or more UAVs, which may include single-rotor, quadcopter, and other types of UAVs / drones. In the illustrated embodiment, the launch container base is approximately 40 × 30 cm and 25 cm high at its highest point, but other sizes can be used according to this disclosure. Although the illustrated embodiment includes four removable and replaceable boxes 210, other numbers of boxes can be used according to this disclosure. In various embodiments, the boxes 210 can be easily inserted into and / or removed from one or more launch containers. The UAV can be easily loaded into or removed from one or more boxes before or after insertion into the launch box. The power to the launch box 200 can be supplied by the vehicle's power supply, an internal battery unit, or another available power source.

[0028] The transmitter housing 200 can be remotely controlled by an operator located within the vehicle, facilitating wired communication between the operating terminal and the transmitter housing 200. An antenna located on the rear of the housing can be configured for wireless transmission to / from the operating UAV and / or the operating terminal. Connectors 220 located on the rear of the transmitter housing connect the transmitter housing 200 to the operating control unit, power supply, environmental sensors, and other communication links.

[0029] Now refer to Figure 3 Various embodiments of the cartridge and launcher housing are described in more detail. As illustrated, the launcher housing 310 includes a top 312 in which a cavity 314 (or recess) is formed, and this cavity is adapted to receive and secure the cartridge 320. The launcher housing 310 may be formed or constructed as one or more pieces, including durable plastics, metals, composite materials, or other materials suitable for rigidly securing the launcher housing to the vehicle and the UAV within the cartridge during vehicle travel, and for withstanding environmental conditions associated with the intended use. The cartridge 320 is adapted to be fitably inserted into the cavity 314 to secure the cartridge therein, and may be adapted to snap into a suitable position within the launcher housing 310. In one embodiment, the cartridge 320 includes a top 350 having a lip that contacts the surface of the top 312 of the launcher housing 310 when the cartridge 320 is inserted into the cavity 314. As illustrated, the cartridge 320 can be easily inserted and removed, and the cartridge remains securely positioned within the launcher housing 310 during travel. It should be understood that the transmitter housing 310 may include multiple cavities, each of which is adapted to receive a corresponding box 320.

[0030] In various embodiments, the housing 320 includes one or more cables or wires that provide power and / or communication to the housing and the UAV. As illustrated, cable 340 connects connector 342 to the UAV carriage. The transmitter housing 310 includes a corresponding connector 330 at the bottom of cavity 314, and this connector is arranged to mate with connector 342 when the housing 320 is inserted into cavity 314. Charging and / or control of the UAV is provided by the wired connection when connector 330 in the bottom of the housing mates with the corresponding connector 342 in the housing 320. As illustrated, when connectors 330 and 342 are engaged, the housing 320 and the UAV are connected to electrical components 360 of the transmitter housing, which facilitate control and communication with the housing and the UAV, and provide power for charging the UAV and operating the mechanisms and components within the housing 320.

[0031] In some embodiments, the housing 320 and the launch box housing 310 include weather-resistant components such as seals, insulating materials, heating wires embedded in the housing 320 and / or the launch box housing 310 to melt ice and snow, cooling mechanisms (such as cooling fans in an open space inside the launch box housing 310), and other weather-resistant components adapted to the environment.

[0032] refer to Figure 4The image illustrates a side view of an embodiment of the launch container 400. The launch container 400 includes a housing 410 having an internal cavity 412 accessible through an opening 414 on the top of the housing 410. A cassette 430 is assembleably engaged with the housing 410 to secure the cassette 430 for the movement and storage of the UAV. In this location, a connector 420 is engaged to provide power and communication to the UAV. The launch container 400 may also include electronics 440, such as printed circuit boards and / or other control components (e.g., actuator controllers for raising or lowering actuator arms and brackets between storage and launch positions) that provide communication with the UAV and cassette 430 via the connector 420. An external connector 450 provides power and communication to the launch container 400 from a vehicle, operating terminal, or other wired connection. In various embodiments, the electrical components, including the connector 450, wiring, and circuitry, may include standard components suitable for automotive or military vehicle electronic systems.

[0033] refer to Figure 5A An embodiment of a cassette 500 that secures the UAV 502 in a storage position will now be described. The cassette 500 includes a housing 510 having: an exterior adapted to be securely fitted into a cavity (or recess) of a launch container; and an interior 512 adapted to house the UAV 502 and cassette components (also referred to herein as the launch mechanism and related components) therein and to allow the UAV 502 and other cassette components to move between a storage position and a launch position as described herein. In the storage position, the cover is closed, and the UAV 502 is held on a bracket 522. The bracket 522 is configured to securely hold the UAV 502 and includes a release mechanism comprising a release arm 524 adapted to hold the UAV 502 in the bracket when engaged and to release the UAV 502 when the release arm 524 is opened. The bracket 522 is coupled to the cassette housing 510 at a first hinge point 530 and to an actuator assembly 532 at a second hinge point 534. In the illustrated embodiment, actuator assembly 532 includes a lead screw stepper motor mounted at a first end to housing 510. When activated via connector 540, the lead screw stepper motor traverses helical shaft 536 to open cover 520, thereby moving UAV 502 to the launch position.

[0034] Figure 5BThe diagram illustrates an implementation of the launch / release position. As illustrated, a lead screw stepper motor (DC) has traversed the helical shaft 536 to open the cover 520 and position the UAV 502 for launch. In the release position, the bracket 522 is in a second position, pivoting about a hinge point 530 connected to the housing 510 and a hinge point 534 connected to the actuator assembly 532. As illustrated, hinge point 530 is connected to the housing 510 via mounting members 570, which also pivotally connect one end of the helical shaft 536 to the housing 510 at hinge point 572.

[0035] The solenoid 560 is positioned below the bracket and is operable to engage or disengage the release arm 524. In other embodiments, the release arm may be controlled by other machines and components, such as microactuators or... Figure 11 The mechanical release assembly is illustrated in the embodiment. UAV 502 is positioned in bracket 522 and held in place by release arm 524 when in the closed position. When UAV 502 is positioned in bracket 522, UAV 502 is charged by a power source connected to UAV 502 via connector 540 and / or operatively controlled by an operator using an operating terminal. In one embodiment, bracket 522 includes charging contacts that engage with corresponding charging contacts on UAV 502. In other embodiments, bracket 522 may include an inductive charging pad, connector, or other mechanism facilitating charging of UAV 502. In the launch position, UAV 502 can continue charging and is also available for operator control, including commands to launch UAV 502. Actuator assembly 532 opens and / or closes cover 520 during operation and positions bracket 522 and UAV 502 between the storage position and the launch position. When the housing 500 is positioned within the launch canister housing, the actuator assembly 532 can be calibrated / tested to achieve the correct angle before takeoff when the cover 520 is open (e.g., to avoid collisions or interference between launch canister components and the propeller rotor of the UAV 502). Connector 540 provides connections to the launch canister, vehicle, and / or operating terminal, providing connections to power, control units, and communication components. The housing 500 may include one or more weather-resistant components, such as heating wires and / or cooling fans.

[0036] In various implementations, the operator can instruct the UAV 502 to launch and perform flight missions under operator control via an operating terminal or a pre-programmed flight scenario. The UAV 502 can return to the launch container and land on the tray 522. While the UAV is in the tray 522, a solenoid can close the release arm 524, which securely holds the UAV 502 in place. The actuator assembly 532 can then be instructed to close the cover 520 and move to a storage position until the next flight. The UAV 502 can be recharged while stored in the tray 522. In some implementations, the UAV 502 can communicate with the launch container and / or the operating terminal to download flight information, including acquired images, via connector 540.

[0037] refer to Figure 6 Another embodiment of the launch mechanism in the released position will be described. In this embodiment, the cartridge assembly 600 is illustrated in the released position, ready to launch a UAV 602 held in a carrier 622 by a release arm 624. The cartridge assembly 600 includes a top 604 forming the top of the cartridge, including an opening formed thereon and extending through an upper portion 606 for allowing the carrier 622 and UAV 602 to pass between the released and stored positions. The cover 620 is hinged to the cartridge at the upper portion 606 at a cover hinge point 628. The carrier 622 rotates through the opening with the aid of a spring 629 that pushes the cover upward. The carrier is slidably hinged to the cover 620 along a carrier slide 626. This design is suitable for breaking free ice and obstacles positioned on the outside of the cover. In one embodiment, the cover hinge 628 is provided with play in the vertical direction, and the spring 629 is biased to push upward. If actuator assembly 632 receives a command to move to the release position but fails to open cover 620 due to obstruction, this movement will translate into an upward force on cover 620. Play around hinge 628 will allow the motor to slightly push the front of the cover, causing obstructions to move, for example, breaking ice or removing dirt from the top. In the illustrated embodiment, top 604 includes a mounting arm 670 providing a hinge point 630 (for connecting the end of arm 640) and a hinge point 672 (for connecting the end of auger 636). Hinge point 634 connects arm 640 to actuator assembly 632.

[0038] Figure 7Electrical and processing components for a vehicle launch system according to various embodiments of the present disclosure are illustrated. System 700 includes launch box electrical components 710 and an operation terminal 750. Launch box electrical components 710 facilitate the operation of the launch box, including storage, charging, release, launch, and communication with a UAV supported on an inserted housing. In various embodiments, launch box electrical components 710 include a controller 712, a power supply 714, a housing 716 having electrical components connected to launch box electrical components 710, a communication component 722, an optional sensor 718, and an optional temperature controller 720.

[0039] The controller 712 may be implemented as one or more microprocessors, microcontrollers, application-specific integrated circuits (ASICs), programmable logic devices (PLDs) (e.g., field-programmable gate arrays (FPGAs), complex programmable logic devices (CPLDs), field-programmable system-on-a-chip (FPSCs), or other types of programmable devices), or other processing means for controlling the operation of the launch box.

[0040] The power source 714 may be implemented, for example, as one or more batteries and / or power supplies to allow the use of the transmitter housing and to charge the UAV connected thereto. In some embodiments, the power source 714 is connected to a vehicle power supply that provides power to the transmitter housing.

[0041] The communication component may include a wired interface and a wireless interface. The wired interface may include a communication link with the operating terminal 750 and the vehicle, and may be implemented as one or more physical network or device connection interfaces. The wireless interface may be implemented as one or more WiFi, Bluetooth, cellular, infrared, radio, and / or other types of network interfaces for wireless communication, and may facilitate communication with the operating terminal, the vehicle, the UAV, and other wireless devices. In some embodiments, the communication component 722 includes an antenna for communicating with the UAV during flight.

[0042] In various embodiments, controller 712 is operable to provide control signals to each of the plurality of cartridges 716 inserted into the launch box (e.g., by connecting cartridge electrical components to connector interfaces of launch box electrical components 710). In various embodiments, controller 712 provides control signals to cartridges 716 to provide actuator / carrier 730 control (e.g., movement to a storage or launch position; to close or open a release arm). Carrier communication component 732 provides communication between controller 712 and the carried UAV. In various embodiments, controller 712 facilitates communication between operating terminal 750 and the carried UAV. Launch box electrical components 710 may also include an optional temperature controller 720 for controlling heating and cooling components (if implemented in the launch box). Optional sensors 718 may be configured for additional environmental feedback.

[0043] The operating terminal 750 is operable to communicate with and control the operation of the transmitter 710. The operating terminal 750 includes a processor 760, a memory 770, a display 780, a user input / output unit 790, and a communication unit 792. The processor 760 may be implemented as one or more microprocessors, microcontrollers, application-specific integrated circuits (ASICs), programmable logic devices (PLDs) (e.g., field-programmable gate arrays (FPGAs), complex programmable logic devices (CPLDs), field-programmable system-on-a-chip (FPSCs), or other types of programmable devices), or other processing means for controlling the operating terminal. In this respect, the processor 760 can execute machine-readable instructions (e.g., software, firmware, or other instructions) stored in the memory 770.

[0044] Memory 770 may be implemented as a machine-readable medium storing various machine-readable instructions and data. For example, in some embodiments, memory 770 may store an operating system and one or more applications as machine-readable instructions that can be read and executed by processor 760 to perform the various operations described herein. In some embodiments, memory 770 may be implemented as non-volatile memory (e.g., flash memory, hard disk drive, solid-state drive, or other non-transitory machine-readable medium), volatile memory, or a combination thereof.

[0045] The memory 770 includes a UAV interface 772 and a transmitter housing interface 774. The transmitter housing interface 774 includes status, configuration, and control features that may include all control features disclosed herein. For example, the transmitter housing interface 774 may include identification of the housing and UAV coupled to the transmitter housing, storage / launch status and control, UAV charging status and flight plan, control, and information. The UAV interface 772 facilitates communication with the UAV before, during, and after flight, and may include a flight controller for controlling the UAV during flight, and an interface for downloading and storing images and other data acquired by the UAV during flight.

[0046] The communication component 792 may include wired and wireless interfaces. The wired interface may be implemented as one or more physical network or device connection interfaces (e.g., Ethernet and / or other protocols) configured to connect the operating terminal 750 to the transmitter housing 710. The wireless interface may be implemented as one or more WiFi, Bluetooth, cellular, infrared, radio, and / or other types of network interfaces for wireless communication. In some embodiments, the operating terminal 750 includes a wireless interface for communicating with the transmitter housing and for direct communication with one or more UAVs.

[0047] Display 780 presents information to the user of operating terminal 750. In various embodiments, display 780 may be implemented as a liquid crystal display (LCD), an organic light-emitting diode (OLED) display, and / or any other suitable display. User input / output component 790 receives user input to operate features of the operating terminal 750 and may include a flight controller for one or more UAVs.

[0048] Figures 8A to 8I Various views illustrating implementations of the launch box 800 and boxes (802A and 802B) in the storage position (802B) and launch position (802A) are shown. Box 802A illustrates a UAV 804 ready for launch in a bracket 806. Figure 9 An embodiment of the external connector 900 and the corresponding mating connector 902 is illustrated.

[0049] refer to Figure 10A method 100 for using a vehicle launch device will now be described according to one or more embodiments. In step 1002, a launch box is mounted on the outer surface of a vehicle, such as the top of a military vehicle. In some embodiments, the launch box is wired to receive power from a vehicle power source and to communicate with an operating terminal located inside the vehicle. In step 1004, a plurality of boxes are inserted into the launch box. Each box may include a UAV in a storage position. In some embodiments, the launch box may be adapted to hold 4-6 boxes. When the boxes are inserted, the UAVs are electrically connected to the launch box, and in step 1006, the launch box may provide associated configuration data to the operating terminal. The configuration data may include identification of the boxes and UAVs loaded into the launch box and the current status of the UAVs, such as charge percentage and current flight plan. In step 1008, the operating terminal is used to prepare one or more UAVs for flight, including charging the UAVs and configuring the UAVs for their next mission.

[0050] In step 1010, the operating terminal (located inside the vehicle) sends a command to the launch container to prepare one or more UAVs for launch, and the launch container instructs the launch mechanism of the corresponding compartment to move from its storage position to its launch position. In step 1012, one or more UAVs are released from their carriers and launched for flight, as instructed by the operating terminal. During flight, in step 1014, the operator can use the operating terminal to control and / or monitor the UAVs. In step 1016, each UAV returns to its carrier, and the launch container returns the UAVs to their storage position for protection, charging, and communication with the operating terminal. In step 1018, the UAVs can download flight data and other acquired information to the operating terminal.

[0051] refer to Figure 11 An embodiment in which the housing 1100 of the UAV 1102 is secured using a mechanical release assembly 1160 will now be described. In the illustrated embodiment, the mechanical release assembly 1160 is connected to the actuator assembly 1132 and is operable to release the spring to open the release arm 1124. For example, when the bracket 1122 passes a certain point, the hook is operable to latch and release the spring.

[0052] In various implementations, the launch container can be adapted for use with other UAV types, such as quadcopters. Quadcopters have a larger coverage area than single-rotor UAVs and can be implemented in launch container designs with fewer boxes to accommodate the larger coverage area. In one implementation, the quadcopter is stored vertically in a storage location and held in place by a bracket and release mechanism that center the quadcopter in place. Depending on the size of the quadcopter, the box and cover will be larger, and in one implementation, the actuator arm is adapted to position the quadcopter on the side of the arm. In some designs, the launch container will be larger to accommodate larger UAVs and multiple boxes arranged in a row.

[0053] Where applicable, the various embodiments provided by this disclosure may be implemented using hardware, software, or a combination of hardware and software. Furthermore, where applicable, without departing from the spirit of this disclosure, the various hardware and / or software components described herein may be combined into composite components including software, hardware, and / or both. Where applicable, without departing from the spirit of this disclosure, the various hardware and / or software components described herein may be divided into sub-components including software, hardware, or both. Additionally, where applicable, it is contemplated that software components may be implemented as hardware components, and vice versa.

[0054] According to the software disclosed herein, non-transitory instructions, program code, and / or data may be stored on one or more non-transitory machine-readable media. It is also contemplated that the software identified herein may be implemented using one or more general-purpose or special-purpose computers and / or computer systems that are networked and / or otherwise configured. Where applicable, the order of the various steps described herein may be changed, combined into compound steps, and / or divided into sub-steps to provide the features described herein.

[0055] The above embodiments are illustrative but not limiting of the invention. It should also be understood that numerous modifications and variations are possible according to the principles of the invention. Therefore, the scope of the invention is defined only by the following claims.

Claims

1. A system for storing and remotely launching unmanned aerial vehicles, the system comprising: A housing having multiple recesses formed therein; and A plurality of boxes, each adapted to be securely inserted into one of the recesses, and comprising: A housing having an opening formed on its top; A bracket adapted to hold the aircraft; An arm having a first end attached to the bracket and a second end rotatably connected to the housing; An actuator that can operate the arm to move between a storage position and a launch position, in which the bracket is positioned inside the housing, and in the launch position, the arm extends through the opening to position the bracket outside the housing and enable the aircraft to launch; A lid, rotatably connected to the housing by a lid hinge and adapted to cover the opening in the storage position, the lid hinge having clearance in the vertical direction; and A spring configured to push the cover upward toward the cover hinge to break the obstacle when the actuator is activated to move the arm to the launch position and an upward force is generated because the cover failed to open due to an obstacle, the upward force allows the cover to be moved upward by the spring at the cover hinge with vertical clearance and break the obstacle. The actuator is part of an actuator assembly configured to receive a command to move to the launch position, wherein if the cover fails to open due to the obstruction, the movement of the actuator is converted into an upward force on the cover, wherein the vertical clearance causes the actuator to push one end of the cover, thereby removing the obstruction and allowing the cover to open; The movement of the arm from its storage position to its launch position includes rotating a bracket to move the aircraft from its vertical position away from its launch position; and The bracket includes a release mechanism adapted to hold the aircraft in the bracket during the storage position and during the rotation of the bracket between the storage position and the launch position, the release mechanism being adapted to release the aircraft when the bracket is in the launch position.

2. The system according to claim 1, wherein, The aircraft includes a single rotor located at the top of the aircraft in the launch position.

3. The system according to claim 2, wherein, The aircraft is a quadcopter stored on the side of the arm in the storage location.

4. The system according to claim 1, wherein, The movement of the bracket from the storage position to the launch position causes the bracket to engage the cover, thereby rotating the cover when the bracket is slidably engaged with the cover along the bracket slider. In the launch position, at least a portion of the bracket extends laterally beyond the opening.

5. The system of claim 1, further comprising a cover adapted to cover the opening at the storage location, wherein, As the bracket slides on the bracket slider positioned inside the cover, the movement of the bracket from the storage position to the launch position causes the bracket to rotate. The housing further includes a communication component operable to facilitate communication with an operating terminal, and the release mechanism is adapted to open in response to a command received from the operating terminal, and the bracket further includes a connector for communicatively connecting the supported aircraft to the operating terminal.

6. The system according to claim 1, wherein, Each of the plurality of boxes is removable; At the launch position, at least a portion of the aircraft extends laterally beyond the opening.

7. The system according to claim 1, wherein, The bracket is connected to the interior of the cover and covers at least a portion of the cover, and keeps the cover open when in the launch position; wherein the bracket has a charging point coupled to a power source and is operable to charge the aircraft when engaged with the bracket, and wherein the power source includes at least one of a battery and a vehicle power source.

8. The system according to claim 1, in, Each housing also includes a first connector, and each of the plurality of recesses includes a second connector adapted to mate with the first connector of each housing inserted therein to form a connection, wherein the connection provides power, control and / or communication from the housing to the housing inserted therein.

9. The system according to claim 1, in, The bracket is positioned on one side of the inner surface of the cover; The housing includes a weather-resistant component, which includes a heating wire and / or a cooling fan; and the arm is adapted to break up ice formed on a corresponding box among the plurality of boxes.

10. The system according to claim 1, wherein the system comprises: A launching device comprising a housing and a plurality of boxes, the launching device being adapted to be mounted on the outer surface of a ground vehicle, each box including a launching mechanism comprising an arm of the box, and the launching mechanism being operable to move the aircraft between the storage position and the launching position; and An operating terminal that is communicatively connected to the transmitting device and operable to control the transmitting mechanism of each cartridge.

11. The system according to claim 10, wherein, The operating terminal includes an aircraft flight controller and / or a camera controller; and wherein the operating terminal is operable from inside the ground vehicle to send commands to the launching device to instruct the launching mechanism of any of the boxes to move to the launching position.

12. The system according to claim 10, wherein, In the storage location of any of the plurality of boxes, the aircraft within the box is protected from environmental conditions and connected to a power source to facilitate charging.

13. The system according to claim 10, wherein, Each of the plurality of boxes also includes a box connector adapted to mate with a corresponding transmitter connector to provide power and communication between the transmitter and each of the plurality of boxes; and The transmitting device further includes electronic components, which include control elements operable to control the operation of each of the plurality of boxes inserted into the transmitting device.

14. The system according to claim 10, wherein, For each of the plurality of boxes, the tray is operable to charge the supported aircraft; The bracket is slidably hinged to the cover along the bracket sliding member; The launching mechanism is operable to rotate the bracket through the opening to open the cover with the help of the spring that pushes the cover upward; The bracket is connected to the corresponding box at the first hinge point; and The launching mechanism includes a lead screw stepper motor connected to the corresponding box at the second hinge point, and a helical shaft mounted to the corresponding box at the first end.

15. The system according to claim 10, wherein, The release mechanism is operable to hold the supported aircraft in the closed position and release the supported aircraft in the open position for launch; and The system also includes a solenoid operable to selectively open and close the release mechanism.

16. A method for operating the system according to claim 1, the method comprising: Insert the first box into the first recess of the plurality of recesses; Position the first aircraft on the first bracket of the first box; as well as The first aircraft is moved along a first path through the opening of the box between the storage location inside the first box and the launch location outside the housing.

17. The method of claim 16, further comprising: The housing is mounted onto the outer surface of a ground vehicle; Commands are received from an operating terminal located inside the ground vehicle and communicatively connected to the housing to move the first aircraft from the storage location to the launch location; Receive commands from the operating terminal; In response to the command, the actuator is moved to open the cover, but the cover fails to open due to an obstruction. The movement of the actuator is converted into an upward force on the cover, wherein the vertical clearance will cause the actuator to push one end of the cover, thereby removing the obstruction and allowing the cover to open. Remove the obstruction and open the cover; and In response to the command, the first aircraft is launched.

18. The method of claim 16, further comprising: Insert the second box into the second recess of the plurality of recesses; Position the second aircraft on the second bracket of the second box; The second aircraft is moved along a second path through the opening of the second box between a second storage position inside the second box and a second launch position outside the housing; And to selectively launch one of the first and second aircraft.

19. A method for storing and remotely launching an unmanned aerial vehicle, the method comprising: The first aircraft is stored in a first storage location within a first outer casing of the launching device, the launching device comprising: A housing having an opening formed on its top; A bracket that holds the first aircraft; An arm having a first end attached to the bracket and a second end rotatably connected to the housing; An actuator is provided that can move the arm between a first storage position and a first launch position, wherein in the first storage position the bracket is positioned inside the housing, and in the first launch position the arm extends through the opening to position the bracket outside the housing and enable the first aircraft to launch. A lid, rotatably connected to the housing by a lid hinge and adapted to cover the opening in the first storage position, the lid hinge having clearance in the vertical direction; and A spring, when the actuator is activated to move the arm to the launching position and an upward force is generated because an obstacle prevents the cover from opening, pushes the cover upward toward the cover hinge to break the obstacle. This upward force allows the cover to be moved upward by the spring at the cover hinge, which has vertical clearance, and to break the obstacle. Move the first aircraft to the first launch position and position the first aircraft outside the first outer shell of the launch device; Moving the first aircraft to the first launch position includes: The actuator is moved to open the cover, but the cover fails to open due to an obstruction. The movement of the actuator translates into an upward force on the cover, wherein the vertical clearance causes the actuator to push one end of the cover, thereby removing the obstruction and allowing the cover to open; and Remove the obstruction and open the cover; The process of moving the first aircraft to the first launch position also includes rotating the first aircraft away from its vertical position when it is stored in the rotating carrier by the release mechanism of the carrier; and The process of moving the first aircraft to the first launch position also includes moving the bracket that holds the first aircraft to engage the bracket with the cover to separate the cover from the first housing or to rotate the cover when the bracket is slidably engaged with the cover along the bracket slide.

20. The method of claim 19, further comprising: The launching device is mounted on the outer surface of the vehicle; as well as The command is received from an operating terminal located inside the vehicle to move the first aircraft from the first storage location to the first launch location.

21. The method according to claim 19, wherein, Storing the first aircraft in the first storage location includes: positioning the first aircraft on a first launch mechanism, the first launch mechanism being operable to move the first aircraft between the first storage location and the first launch location; and Moving the first aircraft to the first launch position includes activating the first launch mechanism in response to a command received from an operating terminal communicatively connected to the launch device.

22. The method according to claim 19, wherein, The first storage location for storing the first aircraft within the first outer casing of the launching device includes: The first aircraft is supported in the first box by positioning it on the first bracket, and the release arm of the release mechanism on the first bracket is activated to hold the first aircraft on the first bracket. Insert the first box into the first housing of the transmitting device; Electrically connect the first aircraft to the launching device; and Deactivate the release arm on the first bracket to release the first aircraft for flight; The first bracket is connected to the first box at a first hinge point and to the actuator assembly at a second hinge point; and the method further includes: activating the actuator assembly by pivoting the first bracket about the first hinge point to open the cover of the box and move the first aircraft to the first launch position.

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