658results about "Alighting gear" patented technology

The invention relates to the field of aviation noise control, and provides an aircraft landing gear noise reduction device and method based on micro metal wire spiral winding. The device part comprises a metal wire and a metal wire fixing buckle, the metal wire is fixed through the metal wire fixing buckle, and meanwhile the size and material parameters of the metal wire are designed in a targeted mode. In the method part, the designed metal wire is wound on a cylindrical bluff body part, possibly generating vortex shedding and vortex-fixing interference, on the nose gear in a spiral winding manner, and the two ends and the axial interval position of the metal wire are fixed through the metal wire fixing buckles, so that the metal wire is ensured to be fastened. Therefore, through the wound metal wires, single-frequency noise in the over-top direction caused by falling of a towing rod vortex can be effectively eliminated, broadband noise is reduced, and the noise control capability of an airplane is improved. The method is suitable for various civil aircraft types, and has the advantages of being simple in structure, remarkable in noise reduction effect, high in practicability, high in adaptability and the like.

The present invention discloses a flapping-wing aircraft capable of catapult takeoff and having a sweep-torsion mechanism, belonging to the field of aircraft technology. The aircraft comprises: a fuselage frame, left and right flapping wings, a passive torsion mechanism, a sweep mechanism, a catapult takeoff mechanism, a transmission flapping mechanism, and a tail rudder, wherein: a passive torsion mechanism and a sweep mechanism are provided at the roots of the left and right flapping wings, the catapult takeoff mechanism is provided in the middle of the fuselage, and a hip joint, thigh, ankle joint, calf, foot, and toe joint are provided from top to bottom, the inner and outer sides of the hip joint are controlled by a servo motor for relative rotation, the ankle joint and toe joint are provided with elastic energy storage torsion springs, a synchronous pulley and its drive mechanism are provided between the outer side of the hip joint and the outer side of the ankle joint to control the relative rotation between the thigh and the calf, and perform energy storage for catapult takeoff. In summary, the aircraft can perform catapult takeoff flight, and can perform passive torsion and sweeping motions during the flapping of the wings, which helps to increase the flapping wing lift and the overall payload of the aircraft.

The invention provides an undercarriage system scheme design method based on heterogeneous design simulation data management, which comprises the following steps of: firstly, analyzing, abstracting and standardizing different types of heterogeneous design and simulation data in a development process of an undercarriage system, and constructing a uniform abstract data model; secondly, according to the defined semantic rules, an undercarriage semantic ontology model is constructed, then the semantic rules are loaded through a semantic reasoning engine, and processed data are associated; according to the research and development process of the undercarriage system and the semantic association relationship between the data, data storage and display are realized; after data abstract analysis, semantic association and unified storage are completed, functional information, design information and simulation information are further derived based on an undercarriage semantic ontology and a reasoning result, so that an undercarriage system development scheme driven by requirements is constructed. According to the method, multi-source heterogeneous design and simulation data generated in the research and development process of the undercarriage system can be effectively managed, and a design scheme of the undercarriage system is constructed on the basis of the multi-source heterogeneous design and simulation data.

The invention discloses an electromagnet electromagnetic ultrasonic thickness measurement method and system based on an anti-collision unmanned aerial vehicle, and relates to the field of nondestructive testing, and the method comprises the steps: obtaining the coordinates of a preset detection point, controlling the flight path of the unmanned aerial vehicle, and determining the safety position information of the unmanned aerial vehicle located near the preset detection point; the motion of the multi-degree-of-freedom mechanical arm is controlled through a servo motor and an encoder, contact impact is reduced through a buffer mechanism, and attitude information of the electromagnetic ultrasonic sensor unit aligned with the surface of the to-be-detected object is determined; the magnetic attraction force is adjusted in real time through a closed-loop feedback system, and a linear frequency modulation pulse is adopted as an excitation signal to obtain an echo signal containing acoustic-electromagnetic coupling interference; acoustic-electromagnetic coupling interference is corrected and processed in an auxiliary mode through a multi-mode signal separation algorithm and machine learning, and final thickness data is obtained; and transmitting the final thickness data to a cloud platform, and providing a data visualization interface and an alarm function on the cloud platform. According to the invention, accurate thickness detection and remote monitoring of a complex structure material can be realized.

The invention discloses an unmanned aerial vehicle inspection device and method for electric power inspection, and relates to the technical field of electric power inspection. A mounting base is fixed to the front side of the unmanned aerial vehicle body, a second camera is mounted on the front side of the mounting base, a buffer assembly is mounted on the lower side of the unmanned aerial vehicle body, and the cable is shot by arranging the second camera; the moving assembly comprises fixing frames, a T-shaped block, a threaded rod, a limiting rod and a first motor, the two corresponding fixing frames are fixed to the lower side of the unmanned aerial vehicle body, the T-shaped block is arranged between the two fixing frames, a threaded hole is formed in the edge of the right side of the T-shaped block, and the threaded rod is in threaded connection with the interior of the threaded hole; and the threaded rod is rotationally connected to the interior of the fixing frame on the right side, a first motor is installed on the lower side of the fixing frame on the right side, residues attached to the surface of the cable can be cleaned, and meanwhile damage points of the cable can be marked.

A pin for a pinned joint includes a hollow body with a first and second end caps coupled to first and second ends, respectively. The body and the end caps at least partially define a cavity within the body, wherein at least one aperture extends through the hollow body. A main piston is slidably disposed within the cavity and divides the cavity into a first chamber proximate to the first end and a second chamber proximate to the second end and fluidly isolated from an environment around the body. A lubricant is disposed within the first chamber. The main piston moves toward the first end of the body when a pressure in the second chamber is greater than a pressure of the environment. Movement of the main piston toward the first end of the body discharges lubricant through the at least one aperture.

The invention provides an aircraft ground steering system and an aircraft ground steering control method, which can realize steering and runway separation of an aircraft under a low-speed condition even if a front wheel turning system cannot work normally, and can inhibit or avoid additional weight increase. The aircraft ground steering system comprises a turning hand wheel assembly used for controlling a front wheel turning system to achieve steering of an aircraft when the aircraft slides on the ground at a low speed; the brake system comprises a brake control part, and the brake control part is used for controlling the brake pressure of the left main undercarriage wheel and the brake pressure of the right main undercarriage wheel; and a standby turning control unit capable of switching to a standby mode in which the brake pressure of the left main landing gear wheel and the brake pressure of the right main landing gear wheel are controlled via a brake control unit according to the angle of the hand wheel of the turning hand wheel assembly operated by a pilot.

The landing chassis structure of the surveying unmanned aerial vehicle comprises an installation base, an unmanned aerial vehicle body is connected to the top of the installation base in an inserted mode, and supporting rods are fixedly connected to the front sides and the rear sides of the left side wall and the right side wall of the installation base. Top plates are arranged on the left side and the right side of the lower portion of the mounting base, connecting bases are fixedly connected to the front sides and the rear sides of the tops of the top plates on the left side and the right side, and the connecting bases on the left side and the right side are fixedly connected with the supporting rods on the left side and the right side; the unmanned aerial vehicle connecting mechanism comprises a mounting bin, a gear driven screw rod, a threaded sleeve, a mounting plate, a clamping tenon and a gear driving rod, the landing chassis structure for surveying the unmanned aerial vehicle is reasonable in structural design, the unmanned aerial vehicle can be quickly and conveniently mounted on the landing chassis, time and labor are saved, and the buffering performance of the landing chassis on landing impact force can be effectively improved; and the landing stability of the unmanned aerial vehicle is improved.

The utility model provides an unmanned aerial vehicle hoisting device, which relates to the technical field of unmanned aerial vehicle transportation, and comprises an unmanned aerial vehicle main body, the bottom of the unmanned aerial vehicle main body is fixedly connected with a frame, two clamping plates are arranged in the frame, the bottoms of the two clamping plates are respectively provided with grabbing plates and adjusting assemblies which are symmetrically arranged, and the adjusting assemblies are respectively arranged on the two clamping plates. The height position of the grabbing plate is adjusted. According to the device, the size of the goods loading shelf can be adjusted according to the actual size of goods through the adjusting assembly, so that the goods of different sizes can be loaded and fixed, the practical performance of the device is improved, manual secondary fixing is not needed, the stability is high, and the safety risk of high-altitude object throwing is avoided; buffering can be provided during landing through the buffering assembly, the situation that the unmanned aerial vehicle body is damaged due to the fact that large impact is generated during landing due to the influence of the self weight is avoided, and the situation that goods are damaged and extra damage is caused due to the fact that ground protrusions collide with the goods is avoided.

Systems, devices, and methods for a ground support system for an unmanned aerial vehicle (UAV) including: at least one handling fixture, where each handling fixture is configured to support at least one wing panel of the UAV; and at least one dolly, where each dolly is configured to receive at least one landing pod of the UAV, and where each landing pod supports at least one wing panel of the UAV; where the at least one handling fixture and the at least one dolly are configured to move and rotate two or more wing panels to align the two or more wing panels with each other for assembly of the UAV; and where the at least one dolly further allows for transportation of the UAV over uneven terrain.

The invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle for pesticide spraying in agriculture and forestry, which comprises an unmanned aerial vehicle frame provided with a plurality of groups of arms, each arm is provided with a wing, and the unmanned aerial vehicle further comprises a controller for controlling the rotation of the wings; the rack is used for supporting the unmanned aerial vehicle rack, the rack comprises supporting legs connected with the unmanned aerial vehicle rack, and adjusting assemblies are arranged in the supporting legs; the fixing assembly is used for fixing the adjusting rod arranged in a sliding mode; when the unmanned aerial vehicle lands on a slope, the base making contact with the slope firstly is squeezed by the gravity of the unmanned aerial vehicle frame, the adjusting rods move upwards, the first air bags are squeezed, internal air is exhausted into the first air bags corresponding to the other adjusting rods, the other first air bags are expanded, and the adjusting rods not making contact with the slope are pushed to stretch out to make contact with the slope; after all the adjusting rods make contact with the slope through the base, the base extrudes the second air bag, air in the second air bag pushes the fixing block into the fixing groove, and the adjusting rods and the supporting legs are fixed in a limited mode.

The invention relates to the technical field of undercarriages, in particular to a folding undercarriage device of a low-altitude aircraft, which comprises an aircraft body, a pesticide spraying mechanism for crop fertilization is arranged on the aircraft body, a height-adjustable undercarriage mechanism is arranged at the lower end of the aircraft body, and a landing buffer mechanism is arranged on the undercarriage mechanism. The landing buffering mechanism is used for reducing impact on the undercarriage mechanism at the moment of landing, a linkage auxiliary mechanism is arranged on the aircraft body, the undercarriage mechanism comprises a fixing plate body, and the fixing plate body is detachably installed on the aircraft body. By arranging the undercarriage mechanism and adopting a dynamic folding design, after taking off, the second-stage frame body retracts to drive the telescopic joint to be shortened, so that the overall height is reduced, air turbulence during flight can be effectively reduced, meanwhile, the first-stage frame body rotates to be parallel to the fuselage, the cross sectional area of the undercarriage mechanism is greatly reduced, and the overall height is reduced. And the wind resistance loss during high-speed flight can be obviously reduced.

An unmanned aerial vehicle vibration reduction support for geographical surveying and mapping relates to the technical field of geographical surveying and mapping unmanned aerial vehicles and comprises an unmanned aerial vehicle body, a surveying and mapping assembly is arranged on the unmanned aerial vehicle body, four connecting arms are evenly arranged on the side face, propellers are arranged at the tops of the connecting arms, and supporting legs are arranged at the bottoms of the connecting arms; the lower bottoms of the supporting legs are fixedly connected with a buffering support. The buffering support comprises an outer cylinder, a supporting rod and a footstand. The top of the outer cylinder is fixedly connected with the supporting leg, the lower portion of the outer cylinder is provided with an opening, the upper end of the supporting rod extends into the outer cylinder along the opening, the lower end of the supporting rod is connected with the footstand, the portion, extending into the outer cylinder, of the supporting rod is sleeved with a piston, the outer ring of the piston is in sliding fit with the inner wall of the outer cylinder, and the space between the top face of the piston and the outer cylinder is filled with hydraulic oil. The hydraulic oil communicates with a hydraulic oil tank located on the unmanned aerial vehicle body through the oil hole. A compression spring is arranged between the top face of the piston and the top of the inner cavity of the outer cylinder. And the speed that the compression spring is extruded or rebounded is reduced under the action of the hydraulic oil, so that the effect of stabilizing vibration reduction is achieved.

This invention relates to the field of unmanned aerial vehicle (UAV) technology and discloses a multi-functional UAV. The UAV includes a stabilizing support mechanism installed at the bottom of each of its four rotor arms. This stabilizing support mechanism can stably support the UAV in soft sand. An auxiliary mechanism is rotatably connected to the top of each stabilizing support mechanism. This auxiliary mechanism assists in supporting the stabilizing support mechanism and improves its cushioning capacity. A secondary support mechanism is detachably connected to the bottom of the UAV. This secondary support mechanism protects the bottom of the UAV and prevents it from tipping over on uneven ground. Through the cooperation of the stabilizing support mechanism and the auxiliary mechanism, the UAV can utilize its own gravity to stabilize itself in sandy or soft soil terrain, preventing it from sinking or tipping over. Furthermore, the structure is purely mechanical, simple, and low-cost, and is relatively reliable in extreme environments.

The invention discloses an unpowered landing device special for a saucer-shaped aircraft, belongs to the technical field of saucer-shaped aircrafts, and aims to solve the problems that a traditional landing device is large in occupied space, complex to operate and free of autonomous speed and direction control. The device comprises an annular umbrella cloth storage container, cylindrical umbrella cloth, a rotatable ring, a hanging ring, a flexible hanging wire, a supporting pulley, a limiting device, an air leakage opening and an arc-shaped plate. The annular umbrella cloth storage container and the outer edge of the saucer-shaped aircraft are fixed or integrally designed, the upper edge of cylindrical umbrella cloth is bonded with a rotatable ring, the lower edge is bonded with the outer side of a hanging ring, and a flexible hanging wire is connected with the rotatable ring and the inner side of the hanging ring through a limiting device; the rotatable ring is supported by more than three supporting pulleys, is connected with an external power device through a clutch mechanism, and can drive the cylindrical umbrella cloth to be spirally stored; after the external power is cancelled, the gravity of the hanging ring drives the cylindrical umbrella cloth to unfold without jamming, and the opening and closing degree of the air outlet are adjusted in cooperation with the arc-shaped plate, so that the falling speed and the drifting direction are autonomously controlled. The device is high in adaptability, high in reliability and suitable for unpowered safe landing of the saucer-shaped aircraft in the vertical non-straight-through airflow state of the saucer body.

A wheel suspension for a vehicle includes: - a guide tube (10) that can be mounted on or is mounted on a vehicle chassis in an operating position or is permanently connected to or belonging to a vehicle chassis and assumes the operating position, which in its operating position has a guide tube axis extending vertically or inclined relative to a vertical direction according to a nominal guide tube angle with respect to a vehicle standing on a horizontal flat surface; - a wheel fork (3) having two fork legs (4), which is mounted on the vehicle chassis at least at one bearing area at least by means of the guide tube (10) in its operating position; - Bearing devices at free end areas of the fork legs for the rotary bearing of a wheel (2) between them. It is proposed that the wheel fork (3) is or can be mounted in a relatively movable manner radially outside on the guide tube (10) by means of its bearing area (5, 6).

The invention belongs to the technical field of aircraft hydraulic systems, and relates to a long-life and high-reliability sealing structure of an aircraft undercarriage, which realizes oil-gas mixed sealing of an aircraft undercarriage buffer under multiple working conditions through the structural design of fluorinated silicone rubber, nitrile rubber and modified polytetrafluoroethylene materials. Modified polytetrafluoroethylene and nitrile rubber are used on a dynamic sealing surface for combined action, and meanwhile, the wear resistance of the modified polytetrafluoroethylene and the high elasticity of the nitrile rubber are fully utilized, so that the service life of the sealing device under a high-pressure and high-speed dynamic sealing working condition and zero leakage of air seal under a low-temperature and low-pressure static sealing working condition are ensured. The elastic body on the movable sealing surface adopts a T-shaped structure, so that the elastic body torsion failure possibly caused by the undercarriage buffer under a long-stroke working condition and the extrusion failure under high pressure are prevented; and the elastomer for the static sealing surface is made of fluorosilicone rubber, so that the low-temperature performance of the sealing device is ensured. The sealing device can achieve a good sealing effect under the working conditions of oil-gas mixing, long stroke, high pressure, wide temperature range and the like confronted by the sealing of the undercarriage buffer of the aircraft.

A wheel suspension for a vehicle comprises: - a guide tube (10) which assumes an operating position and, in the operating position, can be mounted or is mounted on a vehicle chassis or is fixedly connected thereto or is part thereof and which has, in the operating position on or as part of the vehicle chassis with respect to a vehicle standing on a level horizontal underlying surface, a guide tube axis extending vertically or at an incline with respect to a vertical direction in accordance with a target guide tube angle; - a wheel fork (3) which has two fork blades (4) and is mounted on the vehicle chassis in at least one mounting region at least by means of the guide tube (10) in the operating position thereof; and - mounting devices, at free end regions of the fork blades, for rotatably mounting a running wheel (2) between the fork blades. According to the invention, the wheel fork (3) is relatively movably mounted or can be relatively movably mounted radially outside on the guide tube (10) by means of the mounting region (5, 6) of the wheel fork.

The invention relates to the technical field of unmanned aerial vehicles, and particularly discloses an unmanned aerial vehicle capable of landing and buffering, which comprises a fuselage shell, connecting arms are fixedly connected to the opposite angles of the side surfaces of the fuselage shell, and fan blade protection rings are fixedly connected to the ends, away from the fuselage shell, of the connecting arms. A driving motor is fixedly connected to the inner wall of the fan blade protection ring through a support, a driving shaft of the driving motor is fixedly connected with flying fan blades, a mounting frame is fixedly connected to the bottom of the fuselage shell, a damping device is fixedly connected to the bottom of the inner wall of the mounting frame, and a buffering mechanism is fixedly connected to the end, away from the supporting frame, of a fixing rod. According to the unmanned aerial vehicle capable of landing and buffering, the buffering mechanism is arranged, so that the impact force generated when the unmanned aerial vehicle descends can be buffered, and the damping device is arranged, so that the buffered vehicle body can be further damped; damage of parts in the unmanned aerial vehicle caused by violent vibration during descending is avoided.

An aircraft (101) includes a ground manoeuvre control unit (226) for automatically controlling ground manoeuvres. The aircraft (101) has control mechanisms (230) such as a rudder, nose wheel steering, spoilers, wheel brakes (110a and 110b) and the like for controlling motion of the aircraft (101). The control unit (226) is configured to receive lateral input demands (220) concerning lateral motion of the aircraft (e.g. heading control) and longitudinal input demands (222) concerning longitudinal motion of the aircraft (e.g. deceleration). The control unit (226) passes on the input demands (220, 222) as output demands (228) to the relevant control mechanisms (230) of the aircraft (101) with, if so required, a modification which prioritises one of the lateral input demand (220) and longitudinal input demand (222) based on the risk of a lateral runway excursion and the risk of a longitudinal runway excursion (232).

The invention discloses an unmanned aerial vehicle self-adaptive landing system and a control method. The system includes a flexible deformable landing gear body, a sensor module, a fluid control module, and a control unit. The undercarriage body contains a flexible chamber filled with a controllable fluid. During landing, the control unit instructs the fluid control module to dynamically adjust the fluid in the chamber based on pressure data monitored by the sensor module, so that the undercarriage main body actively deforms to adapt to an irregular ground profile. Point contact is converted into surface contact, so that landing impact load is effectively dispersed, and stress concentration is avoided; and through an automatic attitude leveling function after landing, the stability and safety of landing of the unmanned aerial vehicle in complex terrains are remarkably improved, and the operation range and autonomy of the unmanned aerial vehicle are expanded.

The invention discloses an unmanned aerial vehicle mounting device, and belongs to the technical field of unmanned aerial vehicles. In order to solve the problems that an existing product is inconvenient to unload, and potential safety hazards exist when goods are hoisted, the following technical scheme is provided, the unmanned aerial vehicle comprises an unmanned aerial vehicle body and a hanging part arranged on the unmanned aerial vehicle body, the hanging part comprises two supporting mechanisms and a suspension mechanism, the supporting mechanisms are arranged on the unmanned aerial vehicle body, and the suspension mechanism is arranged on the unmanned aerial vehicle body. And the left and right parts are symmetrically distributed below the unmanned aerial vehicle main body. According to the unmanned aerial vehicle, the mounting part is arranged to replace an existing support, stable suspension of goods is achieved under the condition that safe take-off and landing of the unmanned aerial vehicle body are guaranteed, and under the condition that a suspension mechanism in the mounting part is matched with a supporting mechanism, lifting of the unmanned aerial vehicle body can achieve locking and releasing of a suspension rope; and the supporting mechanism is further internally provided with a side position restraining assembly, so that the suspended goods can be subjected to side position restraining when the unmanned aerial vehicle main body runs.

The invention discloses an unmanned aerial vehicle with a protection structure, and relates to the technical field of unmanned aerial vehicles. The unmanned aerial vehicle with the protection structure comprises a vehicle body, vehicle arms are installed on the surface of the vehicle body, propeller protectors are installed on the surfaces of the vehicle arms, buffers are arranged at the bottoms of the propeller protectors, and anti-collision devices are installed at the bottoms of the vehicle arms, so that the purpose of providing protection and buffering when the unmanned aerial vehicle is accidentally collided is achieved; when the equipment is impacted, impact is dispersed through elastic deformation of the support structure, linkage energy absorption of related parts is matched, damage to the propeller due to local stress concentration is avoided, impact force can be relieved in a multi-layer mode through the synergistic effect of gas compression, spring contraction and part sliding in the face of vertical impact in the take-off and landing stage, impact damage to the machine body and the machine arms is reduced, and the service life of the equipment is prolonged. The deformation energy absorption of the anti-collision structure, the residual impact transmission unloading force and the assistance of the reset component fully weaken the collision energy and avoid the damage of the core structure.

This invention discloses a landing buffer device for unmanned aerial vehicles (UAVs), relating to the field of aviation equipment technology. By integrating the roller body and the sliding plate as two grounding structures onto the landing gear, the device can quickly switch operating modes according to ground conditions through the linkage of the piston cylinder and piston rod. On flat ground, the roller is used first to reduce gliding resistance, while on muddy or slippery ground, the sliding plate is used for grounding, effectively preventing roller jamming and enhancing all-terrain adaptability and landing safety. Simultaneously, the mechanical buffer composed of a second and third spring, combined with the hydraulic damping buffer composed of buffer components, forms a highly efficient double-layer energy-absorbing buffer structure, which to a certain extent alleviates the damage to the aircraft and equipment caused by landing impact, thus improving the landing safety of the UAV.

The utility model belongs to the technical field of unmanned aerial vehicles, in particular to a miniature reconnaissance unmanned aerial vehicle, which comprises an unmanned aerial vehicle body and a camera, the bottom of the unmanned aerial vehicle body is connected with a storage box, the bottom of the unmanned aerial vehicle body is provided with a connecting plate, the connecting plate is fixedly connected with a plurality of fins, and the fins are positioned in the storage box. A first motor is arranged in the storage box, and the output end of the first motor is connected with draft fan blades. The heat dissipation efficiency of the unmanned aerial vehicle can be improved by installing the fins and the draft fan blade clamps, firstly, the connecting plates and the fins are made of high-heat-conductivity materials, the connecting plates make contact with electronic elements generating heat on the unmanned aerial vehicle body, the heat can be transmitted to the fins through the connecting plates, the heat dissipation area is increased through the fins, and the heat dissipation efficiency of the unmanned aerial vehicle is improved. And then the first motor is started to drive the draft fan blades to rotate, the draft fan blades rotate to extract air around the fins, the extracted air flows through the fins to take away heat on the fins, and therefore the unmanned aerial vehicle is rapidly cooled.

The utility model relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle flight anti-collision device which comprises an unmanned aerial vehicle body, a protection assembly is arranged at the top of the unmanned aerial vehicle body, and a cushioning assembly is arranged at the bottom of the protection assembly. Meanwhile, the paddles are located in the holes, so that the safety is improved, meanwhile, a protection rod is clamped between a first protection plate and a second protection plate, the stability between the first protection plate and the second protection plate is improved, the device can be disassembled through a first fixing bolt and a second fixing bolt, and then the practicability is improved; and after the unmanned aerial vehicle body lands, due to the fact that a hinge rod is hinged between a second protection plate and a supporting seat, a moving block can abut against a damping spring, then pressure is buffered, meanwhile, a damping pad is arranged at the bottom of the supporting seat, and the safety after landing is improved.

The invention discloses an unmanned aerial vehicle front wheel turning and anti-swing electric actuating device, and relates to the technical field of unmanned aerial vehicles, the device comprises a motor, the motor serves as a power source to provide power for front wheel turning, a planetary reducer is arranged below the motor, and the output end of the motor is connected with the input end of the planetary reducer. By introducing intelligent control based on an improved deep reinforcement learning algorithm, the device can automatically adjust turning and shimmy damping parameters according to multi-dimensional information such as flight height, speed, attitude, ground friction force, gradient and the like acquired in real time, so that the device adapts to different flight and ground conditions, the universality and adaptability of the device are improved, and the device is suitable for popularization and application. The application range of the unmanned aerial vehicle is widened, manual intervention is reduced by means of the characteristic of automatically adjusting parameters by means of an intelligent algorithm, hysteresis and errors of manual operation are avoided, the automation degree and reliability of operation of the unmanned aerial vehicle are remarkably improved, and classified storage, encryption management and backup of various types of data are achieved by means of a data storage module.

The invention provides a unified electric control method and device for turning and shimmy damping of a front wheel of an airplane, and solves the technical problems of high complexity and poor adaptability. The device comprises a voltage sensor used for collecting a bus voltage value of a DC power supply loop of an inverter; the power switch device is used for controlling the switch-in and switch-out of the energy consumption resistor R1 in the power supply loop; the relay is used for controlling the on-off of a power supply loop between the direct-current power supply and the inverter; and the logic control module is used for responding to a control requirement, outputting a PWM signal according to a preset control strategy of the corresponding control mode and performing power supply loop control. A turning / shimmy damping unified electric control framework based on electric control is formed to be matched with a unified electric control strategy, a hydraulic shimmy damping device is simplified, and meanwhile the weight and cost of an undercarriage are reduced. Through control mode switching, a PWM technology is adopted to drive the front wheel to actively steer in a control state, and shimmy damping is provided in a non-control state.

The invention discloses a magnetic pole rotating type electromagnetic damping shimmy damper for a nose landing gear of an aircraft, and belongs to the technical field of vibration control of landing gears of aircrafts. The shimmy damper comprises a first stator disc and a second stator disc which are symmetrically arranged, a rotor disc, a plurality of pairs of permanent magnetic poles, a rotating shaft, a top cover, a base and a bearing. The rotor disc is in interference fit with the rotating shaft through the central square hole, the magnetic poles are circumferentially, uniformly and fixedly arranged on two sides of the rotor disc, and the magnetizing directions of the adjacent magnetic poles are opposite. An adjustable air gap is reserved between the stator disc and the magnetic pole. During working, shimmy motion of the nose landing gear is converted into rotation of the rotating shaft through the transmission mechanism, the rotor disc and the magnetic poles are driven to rotate, the stator disc cuts magnetic induction lines to generate eddy currents, damping torque is formed, kinetic energy is converted into heat energy, and efficient shimmy reduction is achieved. External power supply is not needed, the structure is compact, the weight is light, the problems of abrasion and maintenance of a traditional friction or oil damper are solved, and the damper is particularly suitable for a modern aircraft landing gear system.