88results about "Arresting gear" patented technology

The present invention relates to a low-impact landing system for a rotary-wing aircraft, and includes a landing pad 110 having a landing surface 111 formed on the upper part for the rotary-wing aircraft 10 to land on, a tilt drive unit 120 disposed below the landing pad 110 to support the landing pad 110 and adjust the horizontal tilt of the landing pad 110 while driving in accordance with a control signal, a ground communication unit 130 that receives an aircraft tilt detection signal detected by an aircraft tilt sensor 15 disposed on the rotary-wing aircraft 10, and a drive control unit 140 that controls the tilt drive unit 120 in accordance with the received aircraft tilt detection signal so that the horizontal tilt of the landing pad 110 is adjusted and each landing gear 12 disposed below the rotary-wing aircraft 10 comes into contact with the landing surface 111 of the landing pad 110 at the same time.

A landing pad for a vertically landing aerial vehicle includes granules or other particulate material arranged in a container. The granules or other particulate material are dispersed, thereby permitting embedding of legs of the aerial vehicle within the granules or other particulate material and withdrawal of the legs from within the granules or other particulate material.

The invention discloses a stopping system for an airplane, an energy absorption device and a mechanical property testing method. The stopping system for the airplane comprises an energy absorption system, the energy absorption system comprises an energy absorption assembly, the energy absorption assembly comprises a plurality of energy absorption devices connected end to end, each energy absorption device comprises a sliding block with a pawl, a ratchet groove, a dowel bar and an elastic buffering piece, the dowel bar is connected with the sliding block with the pawl, and the elastic buffering piece is connected with the ratchet groove; the sliding block with the pawl is arranged in the ratchet groove and matched with the ratchet groove to form a moving pair, and the elastic buffering piece is used for being connected with the dowel bar and the ratchet groove. One energy absorption system is used for being installed on one pulley assembly; one end of the arresting cable is connected to the dowel bar of one energy absorption system through the pulley assembly, and the other end of the arresting cable is used for being connected with the dowel bar of the head energy absorption device of the other energy absorption system after passing through the other pulley assembly.

A takeoff and landing platform, a UAV, a takeoff and landing system, a storage device and a takeoff and landing control method are provided. The takeoff and landing platform includes: a bracket, one end of the bracket is fixed on a base, and another end thereof extends in a direction away from the base, and the bracket is provided with a vertical guide rail. Multiple UAVs may be vertically stacked on the bracket along the guide rail and take off from the bracket. Hence, the manpower investment and site investment are reduced for multiple UAVs to perform collaborative operations. It can not only reduce the cost of multiple UAV collaborative operations, but also improve the efficiency of multiple UAV collaborative operations.

The disclosure relates to a control device for an end effector, a system including the same, and a related method. End effectors and systems may capture, release, and / or create mating engagement between the end effector and a target object, such as for use in capture and firing, gripping, or pick-and-place applications. The end effector may tolerate position and rotational misalignment of the target object, and the end effector may include a plurality of rollers, one or more of which are arranged in a non-parallel plane with respect to one or more of the other rollers. A control device enables these and other end effectors to be operated in a system that can be used by a single operator in a handheld or wearable shape. The control device may include a drive system for power transmission, manual and automatic leveling or angle positioning mechanisms, and / or operator mounting features. Methods may involve performing capture and release, pick and place, and / or grip operations using the disclosed control device and one or more end effectors coupled thereto.

The application provides a shipborne helicopter quick clamping device capturing method, comprising the following steps: S1, capturing stroke is detected according to a displacement sensor, and S2 is executed; S2, stroke judgment is performed on the capturing stroke, when the capturing stroke is a short stroke, S3 is executed; when the capturing stroke is a medium stroke or a long stroke, S4 is executed; S3, when a mechanical arm is accelerated to a rated speed, a working condition one strategy is executed; S4, according to the medium stroke or the long stroke, buffer time and uniform motion buffer length of each stage are set, and S5 is executed; S5, according to the buffer time and the uniform motion buffer length of each stage, each stage buffer starting displacement corresponding to the speed of each stage is obtained, and S6 is executed; S6, real-time displacement monitoring is performed on the mechanical arm to obtain a real-time speed of the mechanical arm, and S7 is executed; S7, corresponding brake strategies are executed according to buffer point judgment and buffer interval judgment. The application can not only guarantee that the brake displacement has good control precision and stability, but also effectively suppress the brake pressure impact of the system.

An aircraft tow vehicle (100) comprises a turntable lifting unit (102) configured to automatically rotate and lift for attachment to a nose landing gear of an aircraft. A gate (204) coupled to the turntable lifting unit (102) automatically unlocks, opens to receive the nose landing gear, closes to secure the nose landing gear, and locks. A sensor system (104, 106) detects the nose landing gear. A controller receives data from the sensor system, processes the data to determine a position of the nose landing gear, and controls the turntable lifting unit (102) while automatically adjusting a position of the tow vehicle (100) relative to the nose landing gear. A moving floor (210) adjusts to accommodate different nose wheel sizes. A nose wheel adapter (212) automatically positions itself to hold down the nose landing gear when weight is detected on the moving floor (210).

The invention is notably directed to an aircraft carrier ground vehicle (10), which comprises a chassis (102), a landing platform (104), a coupling mechanism (106), and an actuation mechanism (108). The landing platform is designed to accommodate an aircraft (20). The coupling mechanism connects the landing platform to the chassis to form a kinematic pair, in which the landing platform is rotatably mounted on the chassis. The actuation mechanism is adapted to rotate the landing platform relative to the chassis, to allow an aircraft to land on the landing platform as the vehicle moves along a landing direction of the aircraft and compensate for an inclination angle of the aircraft on landing, in operation. The aircraft carrier ground vehicles may further be designed to allow taxiing and take-off of the aircraft. The invention is further directed to related aircraft carrier ground vehicle systems, which include several vehicles that are swarmed for landing an aircraft, as well as aircraft landing and take-off methods.

The invention provides a fixed-point overwater recovery method, system and device for an aircraft. The fixed-point overwater recovery method for the aircraft comprises the steps that a target landing area is determined according to initial position information, water surface information and wind field information of the aircraft; the aircraft is controlled to move to a first position in the target landing area, the first position refers to the position of the target height right above the central point in the target landing area, and a plurality of simulated landing points are calculated based on a landing point prediction algorithm and the wind field information; taking the simulated landing point closest to the central point in the plurality of simulated landing points as a second position, and controlling the aircraft to move from the first position to the second position; and in the process of controlling the aircraft to descend from the second position to the target water surface, the water surface control system adjusts the position of the floating platform according to the horizontal position difference between the aircraft and the floating platform, so that the aircraft lands on the floating platform. According to the embodiment of the invention, accurate aircraft water recovery can be realized.

The present application relates to a kind of rectification methods for the deformation of warship helicopter landing grid, comprising: 1, the measured subsidence of warship helicopter landing grid is measured in situ, the difference between the design subsidence and the measured subsidence is calculated, and the difference is used as the processing amount needed to sink;2, the lowest drain hole of warship helicopter landing grid is taken as the center to draw a bisecting line, and the bisecting line extends to the edge of warship helicopter landing grid along the drain hole;3, along the bisecting line, the warship helicopter landing grid is pressed down at equal depth, and the pressing depth is less than the processing amount needed to sink;4, after completing a circle of pressing down, the subsidence of warship helicopter landing grid is measured, if the subsidence meets the design subsidence requirement, the correction is completed;If the subsidence does not meet the design subsidence requirement, repeat steps 3-4.The present application avoids the problems of excessive concentration, omission and stress mutation in the pressing process by drawing the bisecting line and pressing each bisecting line, and is suitable for field operation.

The application discloses a sea surface multifunctional monitoring system based on hydrogen energy power, which comprises an inner cavity, an outer cavity, a solar panel, a hydrogen energy reaction cavity, a special electric air valve rod frame, a storage battery and a hydrological monitoring device; the hydrological monitoring device is used for monitoring environmental information; the outer cavity is initially filled with air, and the inner cavity is provided with the special electric air valve rod frame which is used for supporting the solar panel above the inner cavity and can adjust the working angle of the solar panel according to the environmental information; the solar panel is used for converting solar energy into electric energy, part of which is directly stored in the storage battery, and the other part of which is supplied to the hydrogen energy reaction cavity for generating hydrogen. The system can provide hydrogen energy for small and medium-sized ships. When the system finds a flying object that needs to be intercepted, the special electric air valve rod frame is precisely and directionally ejected by explosion under the adjustment of an intelligent controller.

The invention belongs to the technical field of unmanned aerial vehicle blocking net equipment, and relates to an open-type machine shed anti-unmanned aerial vehicle blocking protection device. The open-type machine shed anti-unmanned aerial vehicle blocking protection device is reliable in structure and convenient to install and maintain; the device can be quickly recovered after protection, and blocking protection is provided for the subsequent open-type machine shed to resist the unmanned aerial vehicle.

A building is disclosed and may include a truss-framed building structure, at least one of an internal shell and an external shell, and a suspended netting system disposed above and coupled to the truss-framed building structure. The at least one of the internal shell and the external shell may be coupled to the truss-framed building structure.

The utility model relates to the technical field of aircraft landing arresting, in particular to an embedded aircraft arresting device with a self-adaptive vector adjustment recovery function. The system comprises a lifting module, a blocking net module, a blocking net sliding block, a three-light pod module used for emitting guiding light and a monitoring unit used for capturing the position of an aircraft, the blocking net module comprises a blocking net main rope and a blocking net auxiliary rope, the blocking net main rope is fixed to the top of the lifting module, and the bottom of the lifting module is installed on a blocking platform. The arresting net sliding blocks are slidably connected to the arresting net main ropes, every two opposite arresting net sliding blocks are connected through the corresponding arresting net auxiliary ropes, the multiple arresting net auxiliary ropes intersect to form an arresting net, the monitoring units are connected to the arresting net sliding blocks, and the three-light pod module is connected to the top of the lifting module. According to the utility model, the problem of safe and stable arresting type recovery carrier landing, vehicle landing or landing of the aircraft in an ultra-short time under the whole environment condition is solved.

The invention belongs to the technical field of aircraft arresting, and particularly relates to a settling type aircraft arresting net. Due to the fact that the tunnel is arranged, when the equipment does not work, the equipment can completely settle underground, meanwhile, under the protection of the tunnel cover plate, various aircrafts, emergency vehicles and the like are allowed to normally pass in the layout area of the aircraft arresting net equipment, and the aircraft arresting net equipment does not become a barrier which is high and affects flight safety.

The present invention discloses a rotary ship-borne UAV arresting and recovery device, belonging to the technical field of arresting systems for assisting safe landing of carrier-based aircraft. The device comprises a circular platform for landing the ship-borne UAV and a skyhook arresting system T. The skyhook arresting system T comprises a skyhook bracket, a skyhook boom disposed transversely on the top of the skyhook bracket, and skyhook ropes for arresting the ship-borne UAV symmetrically disposed on the skyhook boom. Ground arresting devices D are symmetrically disposed on the circular platforms on both sides of the skyhook bracket. The ground arresting devices D comprise brake devices symmetrically disposed on both sides of the ship-borne UAV landing area, and the two brake devices are connected by arresting cables. The present invention can recover ship-borne UAVs from multiple directions on an aircraft carrier. Installing multiple devices on the deck of the ship can simultaneously recover multiple ship-borne UAVs from different directions, thereby improving the recovery efficiency of the ship-borne UAVs. The present invention also eliminates the need for the traditional complex hydraulic buffer system and the long landing arresting distance, thus saving space on the aircraft carrier deck.

The present invention relates to an aircraft landing apparatus enabling contactless sliding landing, the aircraft landing apparatus comprising: a lower speed-reducing panel that includes a plate-shaped lower panel body and a plurality of lower speed-reducing members each coupled to the upper surface of the lower panel body so as to protrude upward; and an upper speed-reducing panel that includes a plate-shaped upper panel body and a plurality of upper speed-reducing members each coupled to the lower surface of the upper panel body so as to protrude downward, wherein an aircraft passing between the lower speed-reducing panel and the upper speed-reducing panel is slowed down due to friction with the lower speed-reducing members and the upper speed-reducing members, and thus able to land.

The invention relates to a system, housed in a pit in an aircraft runway, comprising at least one immobilizing member (1) which comprises a framework (2) that is fixed relative to the walls of the pit, a receiving mat (3) intended to receive landing gear of the aircraft, drive means (4) for driving this mat relative to the framework, braking means (5) for braking this mat, and control means (8) able to activate the drive means in response to a first signal, then deactivate the drive means while activating the braking means in response to a second signal. The system according to the invention provides for the immobilization of an aircraft in difficulty without significant stresses being exerted on this aircraft, which remains in perfect flying condition. The invention makes it possible to do away with any subsequent operation for checking the integrity of the aircraft structure. Moreover, the invention makes it possible to avoid any technical unavailability of the runway. Lastly, the invention is applicable to the immobilization of aircraft during both the landing phase and the take-off phase thereof.

Various embodiments of the present disclosure provide a rotorcraft-assisted system and method for launching and retrieving a fixed-wing aircraft into and from free flight. The launch and retrieval system includes a modular multicopter, a storage and launch system, an anchor system, a flexible capture member, and an aircraft-landing structure. The multicopter is attachable to the fixed-wing aircraft to facilitate launching the fixed-wing aircraft into free, wing-borne flight. The storage and launch system is usable to store the multicopter (when disassembled) and to act as a launch mount for the fixed-wing aircraft by retaining the fixed-wing aircraft in a desired launch orientation. The anchor system is usable with the multicopter, the flexible capture member, and the aircraft-landing structure to retrieve the fixed-wing aircraft from free, wing-borne flight.

The invention belongs to the technical field of machine manufacturing, and relates to a settlement type aircraft arresting equipment guide belt mechanism which comprises a tunnel, a brake belt, a vertical shaft guide belt wheel, a first-stage transverse shaft guide belt wheel and a second-stage transverse shaft guide belt wheel. The vertical shaft belt guide wheel, the I-stage transverse shaft belt guide wheel and the II-stage transverse shaft belt guide wheel are all mounted in the tunnel, and the II-stage transverse shaft belt guide wheel is flush with the ground level; the brake band vertically penetrates through the vertical shaft band guide wheel, then is twisted to be horizontal and penetrates through the I-stage transverse shaft band guide wheel, and then the brake band is lifted and horizontally penetrates through the II-stage transverse shaft band guide wheel till the brake band reaches the ground level height. According to the guide belt mechanism of the settlement type aircraft arresting equipment, the problem that the settlement type aircraft arresting equipment cannot be normally connected due to the height difference between the two ends of a brake belt is effectively solved. By using the belt guiding mechanism, the brake belt is smoothly guided to the ground from the tunnel of the energy absorber, the normal work of the energy absorber is ensured, and powerful support is provided for putting settlement type aircraft arresting equipment into use in a military and civil dual-purpose airport.

This invention relates to the field of aircraft landing arresting devices, and discloses a non-preloaded arresting pressure relief cylinder and a non-preloaded arresting deceleration system, including a force-bearing rod, a main air cylinder, a piston, a guide rod, an upper baffle, a lower baffle, a one-way exhaust assembly, and a return air assembly. A piston is located at the lower end of the force-bearing rod, and the piston is fixedly connected to the rear end of the guide rod. The diameter of the front end of the guide rod is larger than the diameter of its rear end. The upper baffle is located inside the main air cylinder and has an upper limit flow hole. The diameter of the front end of the guide rod is equal to the diameter of the upper limit flow hole. The lower baffle is located at the lower end of the main air cylinder and has a one-way exhaust assembly and a return air assembly. Both the one-way exhaust assembly and the return air assembly are connected to the main air cylinder. The one-way exhaust assembly is used to discharge part of the gas inside the main air cylinder, and the return air assembly is used to fill the main air cylinder with gas. Compared with the prior art, this invention has the advantages of simple structure and high cost-effectiveness.

The invention is directed to an aircraft carrier ground vehicle, which comprises a chassis, a landing platform, a coupling mechanism, and an actuation mechanism. The landing platform is designed to accommodate an aircraft. The coupling mechanism connects the landing platform to the chassis to form a kinematic pair, in which the landing platform is rotatably mounted on the chassis. The actuation mechanism is adapted to rotate the landing platform relative to the chassis, to allow an aircraft to land on the landing platform as the vehicle moves along a landing direction of the aircraft and compensate for an inclination angle of the aircraft on landing, in operation. The aircraft carrier ground vehicles further allow taxiing and take-off of the aircraft. The invention is further directed to related aircraft carrier ground vehicle systems, which include several vehicles that are swarmed for landing an aircraft, and aircraft landing and take-off methods.

The invention relates to the field of aircraft blocking, and discloses a motorized fast arrangement blocking system which comprises at least two carrier loaders, winches rotationally arranged on the carrier loaders and supporting guide parts arranged at the bottom ends of the carrier loaders. And the flexible pieces between the carrier loaders are communicated through the supporting and guiding parts and form a blocking loop. The system is composed of at least two carrier loaders, through a flexible arrangement mode, building of the blocking system can be completed within a short time, the system is suitable for quick response under emergency conditions, compared with a runway blocking system in the prior art, the system can be quickly deployed on the edge of a runway or an unpaved overtravel area, and the service life of the runway blocking system is prolonged. In addition, for aircrafts specially working in the field, the endurance of the aircrafts is limited and needs to be supplemented, and the system can be rapidly deployed under the severe field conditions and stop the aircrafts, so that the deployment maneuverability of the aircraft stopping system is realized.

The application provides an emergency landing blocking method and device for a fixed-wing unmanned aerial vehicle, effectively solves the problem of poor blocking effect of the blocking technology of the fusion flexible blocking net and the electromagnetic brake, which leads to serious threat to landing safety. The method comprises the following steps: an intelligent cooperative control unit generates an emergency starting instruction to an executing mechanism according to a plurality of flight state signals of the fixed-wing unmanned aerial vehicle monitored by a state sensing module in real time; the executing mechanism executes a blocking strategy to block the fixed-wing unmanned aerial vehicle; a blocking signal of the executing mechanism in the blocking process and a landing signal of the fixed-wing unmanned aerial vehicle in the emergency landing process are acquired in real time, and the intelligent cooperative control unit generates an adjustment instruction in real time; the state data of the fixed-wing unmanned aerial vehicle after the executing mechanism executes the adjustment instruction are monitored in real time, it is determined that the emergency landing blocking is completed, and a reset operation is performed.

A differential-speed target precise docking and recovery system includes a braking and guiding system, a guiding arm, a control system, and an impact load isolation means. The braking and guiding system is configured to reduce target energy and includes a braking device and a docking device that is connected to the braking device. The impact load isolation means releases or optimizes a force applied on a mechanical arm during the docking and braking process of a target, and transfers or transmits a load from the target imposed on the system to a buffering system.

The invention relates to the field of tail propeller configuration fixed wing flight devices, in particular to an arresting hook system and a flight device. The arresting hook system comprises an arresting hook arm assembly, a buffering assembly and a retracting and releasing assembly, the arresting hook arm assembly comprises a mounting support, a swing arm and a hook head which are sequentially connected, the swing arm is rotationally connected with the mounting support, and the hook head is used for hooking an arresting rope; the buffer assembly is arranged opposite to the mounting support and comprises a mounting plate and a buffer piece arranged on the mounting plate, and the buffer piece makes contact with the swing arm when the hook head makes contact with the ground and swings to a preset position; the winding and unwinding assembly comprises a driving assembly and a winding and unwinding cable, the driving assembly is arranged on the mounting support, one end of the winding and unwinding cable is connected with the driving assembly, the other end of the winding and unwinding cable is connected with the swing arm after winding around a supporting device on the mounting plate, and the driving assembly can drive the winding and unwinding cable to drive winding and unwinding of the hook head. By means of the structure, the purposes of rapid upward swinging of the hook head, impact buffering and protection of the retracting and releasing assembly are achieved.

The application discloses a kind of small shipborne cluster unmanned aerial vehicle skyhook recovery control methods, belong to unmanned aerial vehicle control field;Specifically: for small shipborne cluster unmanned aerial vehicle, the relative position between unmanned aerial vehicle and ship, speed, heading and the attitude information of ship are obtained by differential satellite navigation, to guide unmanned aerial vehicle landing;The flight route in the process of unmanned aerial vehicle skyhook recovery is divided into three sections: approach segment flight control module controls unmanned aerial vehicle to reduce height and speed, aligns recovery device and enters follow-fly mode;The hooking point is constantly corrected by real-time attitude of ship in recovery section, and the lateral offset distance control and height control of unmanned aerial vehicle are constantly carried out by L1 guidance law and PID controller, to improve hooking accuracy;The state of unmanned aerial vehicle is monitored and judged at decision point and hooking point in flyback section, as long as entering flyback, reenter recovery mode by shortest route, to reduce recovery flight time, minimize the influence on subsequent unmanned aerial vehicle recovery in cluster.

The present invention discloses a drone and its takeoff and landing method, computer device, and storage medium. This method is applicable to a drone storage device and includes: when the drone takes off from the drone storage device, the camera module is used to identify and record the pit identification ID of the corresponding pit; when the drone returns for landing, the camera module is used to identify the two-dimensional code in the drone storage device, and confirm the pit identification of the corresponding pit based on the recorded pit identification ID; identify the pit identification to obtain the identification result of the corresponding pit identification; based on the identification result of the pit identification, construct the corresponding navigation information, and land in the corresponding pit based on the navigation information. The present invention can improve the takeoff and landing accuracy and recovery efficiency of the drone by identifying the pit identification of the drone storage device to read the position information therein, thereby constructing navigation information and enabling the drone to accurately land in their respective pits.