57results about "Arresting gear" patented technology

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 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.

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 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.

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.

A landing gear (1), an unmanned aerial vehicle, an aircraft (11), a landing pad system, a perch system and a method. The landing gear (1) is configured to be arranged on the back of the aircraft (11), and the landing gear (1) comprises a connector and locking members, wherein a first end of the connector is configured to be connected to the back of the aircraft (11); and a plurality of locking members are provided on a side portion of the connector, and the locking members are configured to fit with a locking mechanism in an aircraft perch apparatus (6).

The application discloses a hanging rope type air base unmanned plane recovery device, which comprises a fixing mechanism, a mechanical arm and a hanging rope mechanism. The mechanical arm can make linear reciprocating motion in the vertical direction, and when the unmanned plane comes from above or below the recovery device, the recovery mechanism can adjust its height to align with the hook of the unmanned plane. By controlling the recovery mechanism to actively dock with the hook of the unmanned plane, the docking success rate is improved, and the unmanned plane recovery efficiency is improved.

The utility model discloses an automatic locking hook device of an aircraft arresting cable in the technical field of aircraft arresting cables, which comprises an arresting cable, the arresting cable is provided with a locking hook unit, the locking hook unit comprises an elastic locking structure and a connecting structure, the connecting structure is used for connecting the elastic locking structure with the arresting cable, and the locking hook unit is connected with the arresting cable. The elastic locking structure is used for locking the aircraft tail hook and the arresting cable under the action of the force of the aircraft tail hook; by arranging the lock hook unit, the unhooking rate of the tail hook and the arresting cable of the aircraft can be reduced, and then the problems that the risk of landing failure is increased, and the flight safety and the operation efficiency are threatened due to unhooking of the tail hook and the arresting cable are solved.

A drone takeoff and landing system according to an embodiment comprises: a drone including a through-hole; and a landing pad including an extension member which can pass through the through-hole, wherein, when the extension member of the landing pad passes through the through-hole of the drone, an eddy current may occur between the through-hole and the extension member to cause magnetic braking of the drone.

The present application relates to unmanned aerial vehicle pickup and delivery systems, and more particularly to a method for landing an unmanned aerial vehicle (UAV) on a UAV support mechanism, the method comprising: navigating the UAV toward the UAV support mechanism; receiving a signal from a guidance array of the UAV support mechanism; navigating the UAV to a landing area of the UAV support mechanism; guiding a reduced-width portion of the UAV between opposing rails of the UAV support structure and engaging the UAV with the UAV support mechanism; and moving the UAV from the landing area toward a return area of the UAV support mechanism.

The present application relates to unmanned aerial vehicle capture technical field, especially to a kind of unmanned aerial vehicle capture equipment with protection function.The present application provides a kind of unmanned aerial vehicle capture equipment with protection function without using unmanned aerial vehicle capture.A kind of unmanned aerial vehicle capture equipment with protection function, including placement cylinder, including catcher, controller and camera, placement cylinder inside slidingly connected with controller, controller is installed with catcher, catcher is installed with camera.Through camera monitoring surrounding environment, when unmanned aerial vehicle appears, people aim at unmanned aerial vehicle through controller control catcher, then implement capture through catcher, when not using, can be received into placement cylinder with controller, catcher and camera, avoid its with outside excessive contact, cause damage, through baffle close placement cylinder, prevent rain, insect, garbage etc. Into placement cylinder inside erosion catcher, controller and camera.

An aircraft tow vehicle comprises a turntable lifting unit configured to automatically rotate and lift for attachment to a nose landing gear of an aircraft. A gate coupled to the turntable lifting unit automatically unlocks, opens to receive the nose landing gear, closes to secure the nose landing gear, and locks. A sensor system 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 while automatically adjusting a position of the tow vehicle relative to the nose landing gear. A moving floor adjusts to accommodate different nose wheel sizes. A nose wheel adapter automatically positions itself to hold down the nose landing gear when weight is detected on the moving floor.

The present application relates to the technical field of aircraft recovery, in particular to a fixed-wing unmanned aircraft net recovery device, which comprises a support, a recovery net, four deceleration tow ropes and four damping output mechanisms, four pulleys are installed on the support, one end of each of the four deceleration tow ropes is connected to a damping output mechanism, the other end of each of the four deceleration tow ropes is connected to a corresponding corner of the recovery net after passing through a corresponding pulley, the recovery device further comprises two net tensioning ropes arranged on the front side of the recovery net, one end of each of the two net tensioning ropes is connected to the left side and the right side of the recovery net respectively, and the other end of each of the two net tensioning ropes is fixed relative to the ground, the two net tensioning ropes and the four deceleration tow ropes are in a tensioned state, and the recovery net is suspended in the air in a ">" shape. The recovery device can adopt a larger recovery net, and can avoid the middle and lower parts of the recovery net from being in a sagging state, ensure a good wrapping and restraining effect, and the height of the net supporting rod is low, and the structure of the device is more compact and simplified.

The present invention relates to a vehicle arresting system comprising an arrester bed of compressible foam material having bulk compressive strength and a central longitudinal axis extending from a front end to an opposite rear end, the arrester bed comprising an assembly of prefabricated blocks arranged in an even number of linear lanes of the prefabricated blocks, half of the sets being positioned to the left of the central longitudinal axis of the arrester bed and half of the sets being positioned to the right, each linear lane of the prefabricated blocks being inclined at an angle α toward the central longitudinal axis of the arrester bed, where 0°<α≦30°.

The invention provides a fixed-wing unmanned aerial vehicle stopping method and system, electronic equipment and a storage medium. The problem that multiple defects exist when a traditional fixed-wing unmanned aerial vehicle stopping system stops a fixed-wing unmanned aerial vehicle is effectively solved. The method comprises the steps that a cooperative control module receives various unmanned aerial vehicle parameter data from an unmanned aerial vehicle flight control system and an external ejection system so as to calculate theoretical stopping force and an expected stopping distance, and a pre-stored stopping execution module is lifted according to a lifting strategy in a lifting instruction; the stopping execution module stops the to-be-stopped fixed-wing unmanned aerial vehicle entering the parking lot after being lifted, and various stopping data generated by the stopping execution module and the to-be-stopped fixed-wing unmanned aerial vehicle in the stopping process are monitored in real time; the cooperative control module also calculates a blocking force according to the various blocking data, and generates an adjustment instruction based on the blocking force to decelerate the to-be-blocked fixed-wing unmanned aerial vehicle until the blocking is successful.

This can improve the stability of the aircraft during takeoff or landing. [Solution] An assistance device according to one embodiment is an assistance device for assisting at least one of the takeoff and landing of an aircraft at the port of the aircraft, comprising a linear member having a first end connected to the port and a second end including a connecting portion connectable to the aircraft, and a levitation means for raising the connecting portion.