The disclosed invention comprises a spring-based launch device, and method of using the device within a system for launching an unmanned aerial vehicle (UAV) using constant torque springs to pull a carriage to accelerate a UAV to the necessary launch speed. A torque frame holds multiple constant torque springs attached to an adjustable power system, enabling a selectable number of springs to connect to a spool. The adjustable power system enables the launch speed of the UAV to vary based on its launch requirements. The spool is used to move a carriage at constant acceleration. The carriage holds the UAV and is pulled along rails until it hits a stop spring system, which stops the carriage, causing the aircraft to be launched off the carriage. Re-tensioning of the system occurs through a retraction mechanism which pulls the carriage back to a spring box, where it is positioned in tensioned configuration.

Adapter assemblies for aircraft and launchers for deploying aircraft are described herein. An example adapter assembly for an unmanned aerial vehicle (UAV) includes a first adapter to be removeably coupled to a first side of a fuselage of the UAV. The first adapter includes first and second posts to interface with a carriage of a launcher. The adapter assembly also includes second adapter to be removeably coupled to a second side of the fuselage of the UAV. The second adapter includes third and fourth posts to interface with the carriage of the launcher.

The invention relates to an emergency support robot for polar UAVs, belonging to the technical field of emergency support robots for polar UAVs. The technical problem to be solved is to improve the structure of the existing emergency support robots for polar UAVs. The technical scheme adopted is as follows: the robot is of a car body structure; a support table is arranged on the upper side of the chassis of the car body; a traveling mechanism is arranged on both sides of the chassis of the car body; the two sides of the support table are hinged with a pair of casings through hinged buckles and push rods; the casings are also provided with a wind power plant; the support table is provided with a launching guide rail.

In one embodiment, a wing for an unmanned aerial vehicle is described. The unmanned aerial vehicle includes a first body of the wing with a first end proximate a body of the vehicle. A second end is opposite the first end. A first joint is on the first end of the first main body of the wing. The joint rotatably couples the wing to the vehicle. A second joint is on the second end of the vehicle. A second body of the wing is rotatably coupled to the first body via the second joint.

An autonomous catapult-assisted take-off, recycling, and reuse device and method of a flapping-wing unmanned aerial vehicle (UAV) are provided. The device includes a base, an attitude adjusting mechanism, a catapult mechanism, a recycling mechanism, a control processing unit, a power supply module, and a sensor unit, where the attitude adjusting mechanism includes a connector, a counterweight, an adjusting motor, an attitude adjusting input gear, an attitude adjusting output gear, an attitude adjusting output gear shaft, and an installation platform; the catapult mechanism includes a catapult motor, a catapult motor frame, a pulley, a pull rope, a winch, a pull rope fixing part, a flapping-wing aircraft fixing part, two slide bars, two compression springs, and a catapult gear set; and the recycling mechanism includes a recycling motor, a recycling mechanical arm, a recycling platform, two sprockets, and a recycling gear set.

An autonomous catapult-assisted take-off, recycling, and reuse device and method of a flapping-wing unmanned aerial vehicle (UAV) are provided. The device includes a base, an attitude adjusting mechanism, a catapult mechanism, a recycling mechanism, a control processing unit, a power supply module, and a sensor unit, where the attitude adjusting mechanism includes a connector, a counterweight, an adjusting motor, an attitude adjusting input gear, an attitude adjusting output gear, an attitude adjusting output gear shaft, and an installation platform; the catapult mechanism includes a catapult motor, a catapult motor frame, a pulley, a pull rope, a winch, a pull rope fixing part, a flapping-wing aircraft fixing part, two slide bars, two compression springs, and a catapult gear set; and the recycling mechanism includes a recycling motor, a recycling mechanical arm, a recycling platform, two sprockets, and a recycling gear set.

An apparatus and method for continuous catapulting of unmanned aerial vehicles are disclosed, and relate to the technical field of aircraft catapulting and recovery. The apparatus consists of an unmanned aerial vehicle storage apparatus, an unmanned aerial vehicle conveying apparatus, an automatic unmanned aerial vehicle loading apparatus, tackles and a rotary tube-type multi-track unmanned aerial vehicle catapult. The present invention can increase catapulting efficiency of the unmanned aerial vehicles, and is suitable for rapidly forming a cluster of the unmanned aerial vehicles.

An apparatus and method for continuous catapulting of unmanned aerial vehicles are disclosed, and relate to the technical field of aircraft catapulting and recovery. The apparatus consists of an unmanned aerial vehicle storage apparatus, an unmanned aerial vehicle conveying apparatus, an automatic unmanned aerial vehicle loading apparatus, tackles and a rotary tube-type multi-track unmanned aerial vehicle catapult. The present invention can increase catapulting efficiency of the unmanned aerial vehicles, and is suitable for rapidly forming a cluster of the unmanned aerial vehicles.

Systems and methods include UAVs that serve to assist carrier personnel by reducing the physical demands of the transportation and delivery process. A UAV generally includes a UAV chassis including an upper portion, a plurality of propulsion members configured to provide lift to the UAV chassis, and a parcel carrier configured for being selectively coupled to and removed from the UAV chassis. UAV support mechanisms are utilized to load and unload parcel carriers to the UAV chassis, and the UAV lands on and takes off from the UAV support mechanism to deliver parcels to a serviceable point. The UAV includes computing entities that interface with different systems and computing entities to send and receive various types of information.

An aerial vehicle launcher including a rail having a first end and a longitudinal axis and a piston movable in a passageway formed in the rail, the piston connected to a carriage by at least two elongate flexible members. The carriage having a support device for releasably engaging the aerial vehicle. Upon the carriage and the aerial vehicle approaching one end of the rail, the support device controllably disengaging the aerial vehicle, permitting the aerial vehicle to be launched. A device is connected to a pressurized gas source, the device controllably providing pressurized gas from the pressurized gas source to the passageway for drivingly moving the piston, the carriage, and aerial vehicle along the rail for launching the aerial vehicle. The device includes a reservoir for holding pressurized gas, the reservoir being a conduit, the pressurized gas in the reservoir providing the driving force for launching the aerial vehicle.