Катапульта для запуска летательного аппарата

Изобретение относится к области авиационной техники, в частности к пусковым устройствам беспилотных летательных аппаратов. Катапульта для запуска летательного аппарата содержит направляющую и разгонную тележку, соединенную силовым тросом через блоки и торцевую крышку рабочей камеры с поршнем пневматического разгонного цилиндра. Рабочая камера через клапан впуска подключена к баллону сжатого воздуха. Разгонная тележка зафиксирована спусковым механизмом с регулируемой пружиной натяга. В торцевой крышке рабочей камеры смонтирован частично перфорированный штуцер, внутри которого с зазором располагается силовой трос. Входная часть штуцера снабжена раструбом. Выход разгонного цилиндра выполнен в виде сквозного отверстия, диаметр которого не меньше диаметра поршня. Достигается повышение надежности катапульты за счет устранения ударных нагрузок торможения и создания условий для плавного разгона летательного аппарата без рывков. 1 з.п. ф-лы, 2 ил.

Универсальная катапульта для запуска БЛА

Универсальная катапульта для запуска БЛА относится к авиационному оборудованию для запуска беспилотных летательных аппаратов самолетного типа. Катапульта отличается тем, что содержит газогенератор. Газогенератор содержит камеру сгорания (1), агрегат (4) подачи жидкого моторного топлива, агрегат (3) подачи воздуха, главный клапан (2) с пневмоприводом и управляющий клапан (14). Газогенератор производит газ в камере сгорания (1) в замкнутом объеме при закрытом главном клапане (2). Газ производится как результат реакции жидкого моторного топлива и воздуха. Катапульта отличается тем, что газогенератор связан через быстроразъемное соединение (5) с рабочим цилиндром (7). Катапульта отличается тем, что рабочий цилиндр (7) содержит дроссельную шайбу-адаптер (6) и арматуру плавного разгона, включающую прочный корпус (9) и форсунки (8). Форсунки равномерно разнесены по длине и окружности рабочего цилиндра (7). Катапульта отличается тем, что в рабочий цилиндр (7) вместо поршня вставлен реактивный ускоритель ...

Пневматическая катапульта для взлета летательного аппарата и способ взлета летательного аппарата с пневматической катапульты

Группа изобретений относится к авиационной технике, в частности к устройствам и способам взлета беспилотных летательных аппаратов (ЛА). Пневматическая катапульта для взлета ЛА содержит герметичный рабочий цилиндр с камерой для сжатого газа с поршнем в виде цилиндрической стрелы, узел заправки сжатым газом, узел стыковки с ЛА, поворотные передние опоры и заднюю опору. Снизу стыковочного узла закреплен спусковой механизм, а на нижней поверхности его корпуса установлен сервопривод. Внутри корпуса установлен подпружиненный запорный крюк. Для взлета ЛА раскладывают передние опоры пневматической катапульты, устанавливают ЛА на стрелу, задвигают стрелу с установленным ЛА в рабочий цилиндр, заправляют полость рабочего цилиндра сжатым газом, запускают двигатель ЛА, воздействуют на курок спускового механизма в ручном или автоматическом режиме. После взлета ЛА подбирают стрелу и используют её для последующего запуска. Достигается упрощение конструкции пневматической катапульты и повышение надежности ...

Переносная складная установка для катапультирования малогабаритного беспилотного летательного аппарата

Изобретение относится к беспилотным летательным аппаратам. Переносная складная установка для катапультирования малогабаритного БПЛА содержит балку, состоящую из передней (1) и задней (2) балок, имеющих продольные направляющие пазы. Продольная балка оснащена рамной конструкцией (65), предназначенной для открывания фиксирующих замков (64). Передняя опора (5) выполнена из передних стоек (7), зафиксированных на опоре, соединенной с базовой трубой, на которой размещается тормозной амортизационный самолетный шнур (12) с узлами заделки (14), а также роликовый механизм (13) пускового и тормозного амортизационных самолетных шнуров. Задняя опора (21) выполнена в виде наклонной трубчатой стойки, присоединенной к задней балке (2) с помощью швеллеров. Тележка выполнена в виде каретки (10), оснащенной пусковым амортизационным самолетным шнуром, фиксирующими замками, ложементами (17), стартовым замком и упорными скобами для фиксации БПЛА. Достигается упрощение конструкции. 12 ил.

Modularized bow and arrow type unmanned aerial vehicle launching device using hyperelastic memory alloy wires

The invention discloses a modularized bow and arrow type fixed-wing unmanned aerial vehicle launching device utilizing a super-elastic memory alloy wire. The modularized bow and arrow type fixed-wing unmanned aerial vehicle launching device mainly comprises a slide way, a bow and arrow overall structure, the memory alloy wire, a stretching structure, a launching structure, a buffering structure, an L-shaped structure, a guide rail structure and a structure shaped like a Chinese character'zhong '. In combination with a modular bow and arrow form, the energy density during ejection is changed by changing the stretching distance, changing the deformation quantity of the super-elastic memory alloy wire and utilizing the resistance self-sensing characteristic of the memory alloy, so that the launching performance of the fixed-wing unmanned aerial vehicle is controlled. After the device is installed, the stretching structure is moved to a preset position along the guide rail, the launching structure ...

Adapter assemblies for aircraft and launchers for deploying aircraft

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.

НАЗЕМНЫЙ РОБОТОТЕХНИЧЕСКИЙ КОМПЛЕКС ТЕХНИЧЕСКОЙ РАЗВЕДКИ

Изобретение относится к беспилотной легкобронированной технике для проведения разведки. Наземный робототехнический комплекс (НРК) технической разведки содержит манипулятор, кевларовый корпус, пулемет НРК, прицельный комплекс, вращающееся контактное устройство, систему постановки дымовых завес, БПЛА, бензиновый двигатель, передатчик местоположения, блок управления, бронеколпаки. В кормовой части НРК размещена поворотная платформа, управляемая шаговым двигателем с блоком управления. К поворотной платформе прикреплена быстросъемными эксцентрическими крепежами пусковая платформа катапультного типа для осуществления пуска БПЛА самолетного типа. Достигается увеличение радиуса проводимой разведки. 2 ил.

Unmanned aerial vehicle water traction lifting device and recovery method

The invention discloses an unmanned aerial vehicle water traction lifting device, and belongs to the field of unmanned aerial vehicle recovery devices. Comprising an ejection assembly and a traction lifting rope, and the ejection assembly is arranged on the unmanned aerial vehicle; one end of the traction lifting rope is connected with the ejection assembly, and the other end is fixedly connected with the unmanned aerial vehicle; the ejection assembly is used for ejecting the ejection part outwards, the ejection part can pull the traction lifting rope to be unfolded towards the outer side of the unmanned aerial vehicle, and the ejection part can float on the water surface after being ejected. An unmanned aerial vehicle structure without a steel wire lifting ring is adopted, an ejection assembly and a high-strength traction lifting rope pulled out by an ejection piece are arranged on the unmanned aerial vehicle, in the environment of heavy stormy waves, it is guaranteed that an inflatable ...

Rotor wing unmanned aerial vehicle ejection height adjusting mechanism and control method

The invention discloses a rotor unmanned aerial vehicle ejection height adjusting mechanism and a control method, and belongs to the field of rotor unmanned aerial vehicles, the rotor unmanned aerial vehicle ejection height adjusting mechanism comprises a fuselage, the fuselage comprises a stand column, an air cap and a partition plate, the bottom of the side wall of the stand column is provided with a storage groove and a first electrified degaussing magnet, the top end of the stand column is connected with the partition plate, and the partition plate is fixed in the air cap; a receding groove is formed in the side wall of the hood, a first magnet is arranged on the top face of the partition plate, a resistance increasing device is arranged on the top edge of the side wall of the partition plate and comprises an upper speed reducing plate and a lower speed reducing plate, the bottom face of the upper speed reducing plate is connected with the rotor wing arm, a propeller is arranged on ...

Unmanned aerial vehicle

An unmanned aerial vehicle (UAV) adapted for transit in and deployment from a projectile casing is provided. The UAV includes a wing assembly coupled to the projectile casing and the wing assembly moveable between a closed position and a deployed position. The UAV further includes a propulsion system including at least one rotor disposed on the wing assembly to generate lift, wherein in the closed position, the wing assembly is substantially integral with the projectile casing and in the deployed position, the wing assembly is extended outwards from the projectile casing.

Catapult-assisted take-off unmanned aerial vehicle

The invention relates to the technical field of unmanned aerial vehicles, in particular to a catapult-assisted take-off unmanned aerial vehicle which comprises an unmanned aerial vehicle body, vector vehicle arms, a pressure damping mechanism, a camera system and a catapult system. The side face of the unmanned aerial vehicle body is provided with a vector rotating interface and connected with a vector vehicle arm through the vector rotating interface. The lower end face of the unmanned aerial vehicle body is provided with an ejection system interface and is connected with an ejection system through the ejection system interface. The pressure damping mechanism is arranged at the bottom of the unmanned aerial vehicle body and used for damping the unmanned aerial vehicle body; the camera system is installed at the lower end of the pressure damping mechanism and used for shooting the operation condition of the unmanned aerial vehicle. The vector rotating interface is used for controlling the ...

Apparatus and method for continuous launching of 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.

Autonomous catapult-assisted take-off, recycling, and reuse device and method of flapping-wing unmanned aerial vehicle (UAV)

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.

Design method for integrated launching and recycling system of unmanned aerial vehicle

The invention provides a design method of an integrated launching and recycling system of an unmanned aerial vehicle. The system comprises an energy absorption and release module, a guide rail module and a driving cable module. The energy absorption and release module comprises the steps that 1, an unmanned aerial vehicle integrated launching and recycling system structure is designed; 2, designing the launching and recycling process of the unmanned aerial vehicle and determining parameters; 3, designing a control strategy of an energy accumulator in the launching and recycling process of the unmanned aerial vehicle; and 4, designing the energy accumulator according to the control strategy of the energy accumulator. The hydraulic system is adopted for launching and recycling, and the middle-sized unmanned aerial vehicle launching and recycling device is suitable for launching and recycling of the middle-sized unmanned aerial vehicle with the weight of 400 kg and the speed of 140 km/h. The ...

Convertible unmanned vehicle

An unmanned vehicle having a launch configuration and one or more operational configurations. In the launch configuration, one or more engines resides within an engine bay. The unmanned vehicle is generally shaped like a projectile and can be launch from any tube-shaped deployment system using an initial propulsor. The engine bay can be opened, and the engines can be moved into a generally external position with respect to the engine bay for operation of said engines. In some embodiments, the one or more engines can pivot to direct thrust in multiple directions. In some embodiments, the unmanned vehicle includes flight control surfaces to further improve the flight characteristics of the vehicle.

Unmanned aerial vehicle cross-medium water entry launching test system

The invention discloses an unmanned aerial vehicle cross-medium water entry launching test system which is characterized by comprising a rack, a launching platform translation device, a launching platform lifting device, an unmanned aerial vehicle launching device and a launching platform rotating device. The unmanned aerial vehicle launching device is simple in structure, good in sealing performance and high in applicability, can meet different attitude requirements when an unmanned aerial vehicle enters water and is launched by adjusting the vertical direction, the front-back direction and the pitching angle of the launching platform, meanwhile, the launching device can achieve multi-stage speed regulation so as to meet the acceleration parameter requirements of unmanned aerial vehicles of different models, and the launching efficiency is improved. Test equipment with high precision and wide parameter adjustable range is provided for the cross-medium launching test of the unmanned aerial ...

Unpowered micro aircraft launching device based on multi-stage acceleration

The invention discloses an unpowered micro aircraft launching device based on multi-stage acceleration. The unpowered micro aircraft launching device comprises a lead screw bouncing mechanism, a multi-stage acceleration mechanism, a limiting mechanism and other mechanisms. The screw rod bomb-up mechanism is arranged at the top end of the rear part of the frame and is used for pushing the unpowered micro aircraft to continuously bomb up to the multi-stage acceleration mechanism; the multi-stage acceleration mechanism is arranged at the front part of the frame and is used for accelerating the launching of the unpowered micro aircraft pushed by the screw rod missile-loading mechanism; the limiting mechanisms are distributed on the frame, the lead screw missile-loading mechanism and the multi-stage acceleration mechanism and used for limiting the position of the unpowered micro aircraft and guaranteeing stable and continuous missile-loading launching of the unpowered micro aircraft. The launching ...

Hyperelastic energy storage ejection rotor unmanned aerial vehicle

The invention provides a hyperelastic ejection rotor unmanned aerial vehicle, which relates to the field of unmanned aerial vehicle design and comprises a vehicle body assembly, an elastic energy storage assembly, a deformation traction assembly and a high-energy-efficiency hyperelastic energy storage device combining a spring, a hyperelastic strain gauge and a hyperelastic rope, a hyperelastic strain gauge, a hyperelastic rope and an inner core spring in the elastic energy storage assembly are indirectly driven to generate elastic deformation through winding contraction of a winding contraction elastic rope in the deformation traction assembly so as to store potential energy, and instantaneous release of the potential energy stored by the elastic energy storage assembly is achieved through winding fracture of the winding contraction elastic rope. High driving force is provided for ejection lift-off by utilizing the strong counter-acting force of the ground to the unmanned aerial vehicle ...

System for detachably coupling an unmanned aerial vehicle within a launch tube

An unmanned aerial vehicle launch tube that has a tube, a sabot disposed in an interior of said tube, said sabot having a first clasp tab, and a clasp detachably coupled to said first clasp tab and contacting an inner circumferential wall of said tube so that said clasp is rotationally constrained by the inner circumferential wall and said first clasp tab.

Unmanned aerial vehicle capable of being launched underwater and unmanned aerial vehicle group underwater launching device

The invention discloses an unmanned aerial vehicle capable of being launched underwater and an unmanned aerial vehicle group underwater launching device.According to the unmanned aerial vehicle group launching device, a plurality of honeycomb-shaped regular hexagonal prisms are reasonably embedded into a plurality of cylindrical launching barrels of the launching device; wherein wings of the unmanned aerial vehicle and balance propellers are foldable and stored; the volume can be conveniently reduced, and the cylindrical launching tubes can be stacked and placed in the honeycomb-shaped regular hexagonal prism bodies of the cylindrical launching tubes; dozens of unmanned aerial vehicles can be stacked in the'honeycomb 'regular hexagonal prism body of each cylindrical launching cylinder; the wings and the balance propeller of the unmanned aerial vehicle can be folded and stored; the volume can be conveniently reduced and placed in the launching device; after symmetrical wings of the unmanned ...

Unmanned aerial vehicle bouncing device for surveying and mapping

The invention relates to the technical field of unmanned aerial vehicle bouncing devices, in particular to an unmanned aerial vehicle bouncing device for surveying and mapping. The invention provides an unmanned aerial vehicle bouncing device for surveying and mapping, which is suitable for a rotor unmanned aerial vehicle. An unmanned aerial vehicle bouncing device for surveying and mapping comprises a hangar, a top cover, guide rods, a lifting platform, a force storage mechanism and an ejection mechanism, the top cover is rotationally connected to the upper portion of the hangar, the guide rods are connected into the hangar, the lifting platform is slidably connected between the guide rods, the force storage mechanism is arranged in the hangar, and the ejection mechanism is arranged in the hangar. The lifting platform is pressed downwards through the pressing block, the first spring is compressed, the locking plate clamps the lifting platform, so that force is stored for ejection of the ...

AUTONOMOUS DRONE DIAGNOSIS

Fixed-wing unmanned aerial vehicle catapult-assisted take-off device and catapult-assisted take-

The invention discloses a fixed-wing unmanned aerial vehicle catapult-assisted take-off device and a catapult-assisted take-off method, and belongs to the field of unmanned aerial vehicles. The fixed-wing unmanned aerial vehicle catapult-assisted take-off device comprises a catapult base, a base is slidably connected to the catapult base, and an elastic inhaul cable is connected between the base and the tail end of The top face of the base is provided with a fixed check block and a movable check block which are oppositely arranged in the head-tail direction. The movable stop block is connected to the base in a pivoted mode, and an elastic piece used for enabling the movable stop block to turn over to the position below the top face of the base is arranged between the movable stop block and the base. The movable check block is further fixedly connected with a rigid inhaul cable, a switch device is fixedly installed at the head end of the ejection base, and an action execution part of the ...

UNMANNED AERIAL VEHICLE AND DELIVERY SYSTEM

Double-explosion spraying type folding wing unmanned aerial vehicle launching device

The invention belongs to the technical field of unmanned aerial vehicle launching equipment, and particularly relates to a double-explosion spraying type folding wing unmanned aerial vehicle launching device which is characterized in that a fixed seat is provided with a ventilation cavity, and a first gas tank and a second gas tank which are communicated with the ventilation cavity are detachably connected to the fixed seat at intervals; the fixing base is detachably connected with a launching cylinder which is located between the first gas tank and the second gas tank and communicated with the ventilation cavity, the folding wing unmanned aerial vehicle is located in the launching cylinder, a guide device used for being matched with the folding wing unmanned aerial vehicle is arranged in the launching cylinder, and the fixing base is detachably connected with two sets of launching valve bases. Spring plates matched with the first gas tank and the second gas tank are arranged between the ...

Unmanned aerial vehicle ejection power range extending system

The invention discloses an unmanned aerial vehicle ejection power range extending system. The system comprises a track; the movable pulley assembly comprises a movable pulley support and at least two movable pulleys arranged on the movable pulley support, and the movable pulley assembly is arranged on the track and can move on the track; the fixed pulley assembly comprises a fixed pulley support and at least one fixed pulley arranged on the fixed pulley support, and the fixed pulley assembly is fixedly arranged on one side of the movable pulley assembly in the arrangement direction of the track; one end of the cable is fixedly connected to the fixed pulley assembly; the other end of the cable is connected to a load, and when the driving piece drives the movable pulley assembly to move in the direction away from the fixed pulley assembly, the cable drives the load to move. According to the system, the movable pulley assembly is matched with the fixed pulley assembly, the range extending ...

Storage straight barrel launching vehicle-mounted ejection unmanned aerial vehicle

The storage straight barrel launching vehicle-mounted ejection unmanned aerial vehicle comprises a mounting barrel, an opening is formed in the top end of the mounting barrel, a bearing seat is arranged in the mounting barrel, a supporting rod is arranged at the top of the bearing seat, and an unmanned aerial vehicle body is arranged in the mounting barrel; the extending direction of the unmanned aerial vehicle body is consistent with the length direction of the mounting cylinder, rotating rods are rotationally connected to the peripheral side of the unmanned aerial vehicle body and are symmetrically arranged, and the extending direction of the rotating axis between the rotating rods and the unmanned aerial vehicle body is perpendicular to the extending direction of the unmanned aerial vehicle body; a spiral wing and a rotation driving piece used for driving the spiral wing to rotate are arranged at the end of the rotating rod, the top end of the supporting rod abuts against the unmanned ...

Flight control method for cylindrical folding wing unmanned aerial vehicle

The invention discloses a flight control method for a cylindrical folding wing unmanned aerial vehicle. The method comprises the steps that the unmanned aerial vehicle is powered on and detected; when the detection signal meets the emission requirement, an emission instruction is issued to a flight control system of the unmanned aerial vehicle; the launch canister carries the unmanned aerial vehicle to launch, and a first insertion part of an upper shell of the launch canister abuts against a second insertion part of a lower shell of the launch canister; after a preset time, the flight control system executes a separation instruction of the launch canister and controls a separation explosive bolt used for connecting the upper shell and the lower shell to explode, so that the lower shell is separated; detecting whether the lower shell is separated or not through a separation sensor, and if so, executing the following steps; the flight control system issues a throwing instruction to control ...

Reconfigurable deck and operation method thereof

The invention discloses a reconfigurable deck and an operation method thereof. The reconfigurable deck comprises a plurality of blocking modules and ejection modules. Each module is composed of an operation vehicle and three-folding type overturning folding decks arranged on the two sides of the operation vehicle. Guide rollers are mounted on two sides of a deck of the blocking module and are used for mounting a blocking lock; an ejection track is reserved in the middle of a deck of the ejection module; the stopping modules and the ejection modules are sequentially connected in an end-to-end mode, and after the three-folding type overturning folding decks are unfolded, the three-folding type overturning folding decks of the adjacent modules are fixedly connected into a whole to serve as a temporary taking-off, landing and recycling platform. Take-off recovery of the unmanned aerial vehicle can be met, and meanwhile the problems of airport insufficiency and rapid deployment are solved.

Vehicle-mounted unmanned aerial vehicle auxiliary take-off system and vehicle

The invention provides a vehicle-mounted unmanned aerial vehicle auxiliary take-off system and a vehicle, the system comprises a control device and an auxiliary take-off device, the auxiliary take-off device comprises a take-off base arranged on the vehicle and a connecting support arranged at the bottom of an unmanned aerial vehicle, and the take-off base is used for being in butt joint with the connecting support so that the unmanned aerial vehicle can park; wherein the take-off base is internally provided with a retracting and releasing assembly, the retracting and releasing assembly is arranged close to the contact position of the take-off base and the connecting support, and the retracting and releasing assembly is used for assisting butt joint of the connecting support and the take-off base so that the unmanned aerial vehicle can stop; or is used for being in contact with the connecting bracket and applying upward thrust to the connecting bracket so as to assist the unmanned aerial ...

Pneumatic ejection foldable unmanned aerial vehicle self-locking device and method

The invention relates to the technical field of unmanned aerial vehicles, and provides a pneumatic ejection foldable unmanned aerial vehicle self-locking device and method.The device comprises a locking baffle, a locking connecting piece, a locking support, a button connecting piece, a button support and a locking button. The locking baffle is used for limiting an unmanned aerial vehicle arm, the locking connecting piece is connected with the locking baffle and the button connecting piece, and meanwhile, the locking connecting piece is connected with the locking support to form a rotating pair; the button connecting piece penetrates through the button support and is connected with the two locking connecting pieces; the button support is coaxially assembled with the locking button, the machine body connecting piece and the locking stand column and connected with the machine body connecting piece through a bolt. A threaded hole is formed in the middle of the machine body connecting piece ...

Unmanned aerial vehicle launching system and vehicle

The invention provides an unmanned aerial vehicle launching system, relates to the technical field of unmanned aerial vehicle launching, and solves the technical problems of high cost and poor control precision of an ejection device in the prior art. The unmanned aerial vehicle launching system comprises an ejection frame and an ejection cabin, wherein the ejection cabin is arranged on the ejection frame in a sliding manner; a storage bin is arranged in the ejection cabin, a plunger water pump and an air compression pump are connected to the storage bin, the plunger water pump and the air compression pump inject water into the storage bin and pressurize the storage bin, and an ejection opening is formed in the side, located on the ejection frame, of the storage bin. The unmanned aerial vehicle launching system is low in cost and high in control precision.

Compressed gas ejection mechanism of electric firing and pipe firing unmanned aerial vehicle

The invention relates to the technical field of unmanned aerial vehicle launching, and discloses an electric launching tube launching unmanned aerial vehicle compressed gas ejection mechanism which comprises an ejection assembly, an ejector electric box, an unmanned aerial vehicle launching tube and an unmanned aerial vehicle adapter. The ejection assembly comprises a high-pressure gas cylinder, a high-pressure busbar, an inflation valve and a high-pressure electric explosion valve, the high-pressure gas cylinder is connected with the high-pressure electric explosion valve and the inflation valve through the high-pressure busbar, and the inflation valve is used for inflating and deflating the ejection assembly; the catapult electrical box collects parameters of the catapult assembly and controls the high-voltage electric explosion valve to quickly release internal compressed gas according to a launching instruction, and catapult releasing of the catapult load of the unmanned aerial vehicle ...