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.

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.

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.

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.

The invention relates to a ramp of a catapult and to a catapult. The catapult comprises a carriage (4) for fastening an aircraft (5). The carriage (4) is supported on a ramp (1). The ramp is formed of one or more ramp elements (1a-1m). The ramp element comprises four frame plates, namely two parallel side plates (20a, 20b), a top plate (21) and a bottom plate (22). The frame plates are separate pieces which are connected at fastening points (25) to each other by means of mechanical fastening elements (26).

The invention relates to a ramp of a catapult and to a catapult. The catapult comprises a carriage (4) for fastening an aircraft (5). The carriage (4) is supported on a ramp (1). The ramp is formed of one or more ramp elements (1a-1m). The ramp element comprises four frame plates, namely two parallel side plates (20a, 20b), a top plate (21) and a bottom plate (22). The frame plates are separate pieces which are connected at fastening points (25) to each other by means of mechanical fastening elements (26).

The invention relates to a launching cylinder of a catapult and to a catapult. The launching cylinder comprises a frame inside which are a pneumatic pressure space for launching purpose and a hydraulic pressure space for returning purpose. The pressure spaces are separated from each other by means of a piston assembly.