1436 results about "Landing gear" patented technology

An undercarriage, a middle large rotor and a middle large motor are connected to the lower portion of a fuselage body and sequentially connected to the top of a middle small tower, and the right front portion, the left front portion, the left rear portion and the right rear portion of the fuselage body are correspondingly connected with a right front fuselage arm, a left front fuselage arm, a left rear fuselage arm, a right rear fuselage arm and a power assembly. The connecting line of the rotating centers of the rotors of the four power assemblies is square or rectangular, the rotating directions of the rotors of the power assemblies at the same opposite angles are the same, the rotating directions of the rotors of the power assemblies at different opposite angles are opposite, and the rotating faces of the two rotors opposite to the middle large rotor in rotating direction incline around the axes of the respective arms. The included angle between the rotating surfaces of the two rotors and the horizontal plane is an acute angle beta, the rotating surfaces of the two rotors with the same rotating direction as the middle large rotor incline around respective arm axes, the included angle between the rotating surfaces of the two rotors and the horizontal plane is an acute angle theta, beta is larger than theta, the reaction torque and the horizontal component torque of the rotors jointly drive the aircraft to steer, and the aircraft has the advantages of being long in endurance time, large in load and high in wind resistance. And a universal flight platform is formed.

The invention discloses an aircraft landing gear shimmy test bed and a test method, the aircraft landing gear shimmy test bed comprises a main body rack, a hanging basket system, a large flywheel, a flywheel driving system, an excitation device and a follow-up displacement measurement system.The aircraft landing gear shimmy test bed can simulate the shimmy of an aircraft after undercarriages of different design configurations are subjected to interference excitation force or interference torque in the process of takeoff, taxiing, landing and the like of the aircraft; the control effect of the shimmy damping system on the stability of the undercarriage has short excitation time so as to simulate real working conditions, the shimmy stability performance of the undercarriage can be accurately detected, excitation is continuously carried out under the condition that the test state is continuously changed, and the working efficiency is greatly improved. The follow-up displacement measuring system designed by the invention can enable the exciting force and the center of the axle to be always kept on the same horizontal plane, can apply torque control and torque excitation control, is suitable for undercarriage shimmy tests with different axle heights, different tire diameters and different excitation modes, and has certain universality.

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 invention belongs to the technical field of aviation accessory production, and particularly relates to an automatic stamping system for undercarriage supporting rod piece production, the system comprises an outer supporting pipe stamping processing assembly, an inner supporting pipe stamping processing assembly, a lug stamping processing assembly, a connecting seat stamping processing assembly and a stamping assembling assembly which are sequentially arranged along a production line; the outer supporting pipe stamping machining assembly is used for stamping machining of an outer supporting pipe component, the inner supporting pipe stamping machining assembly is used for stamping machining of an inner supporting pipe component, the lug stamping machining assembly is used for stamping machining of a lug component, and the connecting base stamping machining assembly is used for stamping machining of a connecting base component. And the stamping and assembling assembly is used for stamping, riveting and assembling the outer supporting pipe component, the inner supporting pipe component, the lug base component, the rectangular spring component and the connecting base component through rivets to obtain the combined undercarriage supporting rod piece. The punching and polishing device can meet the requirements for automatic punching and punching, punching and polishing of main components in the side supporting rod of the combined undercarriage and overall automatic punching and assembling.

Disclosed here is a landing gear support fixture for an aircraft under test having a landing gear. The disclosed landing gear support fixture includes: an axle attachment assembly that is compatibly shaped, sized, and configured to mate with and attach to at least one axle of the landing gear of the aircraft under test; a support platform to support the axle attachment assembly, wherein the support platform is in a fixed position relative to a stationary reference foundation; and a force sensor couplable between the axle attachment assembly and the support platform to provide sensor output associated with load imparted by the landing gear of the aircraft under test.

The invention provides an undercarriage system modeling method based on a natural language demand text, and relates to the technical field of model-based computer aided design, and the method comprises the steps: S1, constructing a SysML meta-model knowledge base and an undercarriage system model knowledge base; s2, analyzing the natural language demand text, and generating a structured demand text of the undercarriage system; s3, mapping a structured demand text entity of the undercarriage system into a node type of a semantic graph; and S4, in combination with a historical model template and real-time retrieval, generating an undercarriage system SysML model according to the semantic map obtained in the step S3, and performing undercarriage system engineering analysis through the undercarriage system SysML model, thereby improving the efficiency and quality of aviation equipment development. On the basis of a retrieval enhancement generation technology and an intention routing mechanism, the modeling efficiency and accuracy of the undercarriage system are remarkably improved; a graph neural network and a semantic vector space model are adopted to realize deep fusion and conflict resolution of cross-domain knowledge; and through an incremental learning mechanism, model continuous evolution and design experience closed-loop iteration are supported.

The invention relates to the technical field of aircraft maintenance, and particularly discloses a guide supporting structure for replacing large components of an aircraft. The longitudinal supporting seat can be movably arranged on the vehicle body in the horizontal direction; the linkage operation adjusting mechanism is arranged on the side wall of the longitudinal supporting seat and is used for providing two independent transmission powers with variable speeds for the longitudinal supporting seat; the lifting mechanism can be movably arranged on the longitudinal supporting seat in a sleeving mode in a lifting mode, the lifting mechanism is further provided with a rotatable retainer, the retainer is used for fixing an aircraft landing gear in a disassembly and assembly state, and lifting power of the lifting mechanism and rotating power of the retainer both come from the longitudinal supporting seat. According to the invention, multi-degree-of-freedom adjustment in a limited space is realized, and meanwhile, a guide supporting structure with high positioning precision and operation convenience is taken into account, so that the safety and efficiency of replacement operation of large components of an aircraft are improved.

The invention relates to the technical field of wireless power transmission, in particular to an unmanned aerial vehicle omnibearing wireless power transmission system based on a biorthogonal DD type coil, which comprises a transmitting end and a receiving end, the transmitting end comprises two transmitting coils which are mutually orthogonal, each transmitting coil is driven by a half-bridge inverter, and an LCC compensation network is connected between the transmitting coil and the half-bridge inverter; each transmitting coil is a DD-type coil formed by reversely connecting two D-type coils in series; the receiving end comprises a receiving coil, and the receiving coil is formed by connecting two rectangular coils in series in the same direction; the receiving coil is mounted on an undercarriage of the unmanned aerial vehicle; a target magnetic field is realized by controlling current in the two transmitting coils; according to the invention, the utilization rate of the magnetic field is improved while omnibearing wireless power transmission is realized.

The invention aims to solve the technical problems of insufficient redundant architecture design, low fault diagnosis and switching efficiency and low system integration in the prior art, and provides a front wheel steering engine redundancy control system and method for an unmanned aerial vehicle. A double-ARM architecture cooperative control strategy is adopted, redundant fault-tolerant control of a mechanical coupling single-shaft driving system is achieved, two ARM chips independently drive two motors respectively, the motors are meshed through precision gears to form a mechanical coupling output structure used for driving a corresponding gear set, the gear set is in transmission connection with a gear mechanism, and the gear mechanism is in transmission connection with the gear mechanism. The steering wheel is matched with a nose landing gear of the unmanned aerial vehicle to realize steering; and each ARM chip is provided with a CAN port and an RS485 communication serial port and establishes a parallel data receiving mechanism.

The invention discloses an adjusting device and aircraft landing gear auxiliary mounting equipment, and relates to the technical field of aircraft manufacturing equipment.The adjusting device comprises a first adjusting mechanism, a second adjusting mechanism, a fixing mechanism and a driving mechanism; the first adjusting mechanism is provided with a first seat body; the second adjusting mechanism is provided with a second seat body and a third seat body, the second seat body is rotatably mounted on the first seat body along the axis in the vertical direction, and the third seat body is rotatably mounted on the second seat body along the axis in the left-right direction; the fixing mechanism is mounted on the third seat body and is used for being fixedly connected with an aircraft landing gear; and the driving mechanism is in driving connection with the second seat body and the third seat body so as to adjust the position and the posture of the fixing mechanism in the space. According to the technical scheme provided by the invention, the technical effect of adjusting the attitude of the aircraft landing gear is achieved through the second seat body and the third seat body which are rotationally arranged.

The invention relates to the technical field of unmanned aerial vehicle photovoltaic frame cleaning, and discloses a combined blowing and spraying photovoltaic panel cleaning system carried on an unmanned aerial vehicle, which comprises an undercarriage, a water tank and a plurality of sensors arranged on the undercarriage, and a pressurization system connected with the undercarriage, the composite blowing and spraying subsystem is arranged on the undercarriage; the pipeline system is used for water flow transportation and is arranged on the undercarriage; the combined blowing and spraying subsystem comprises a spraying system support fixedly installed on the undercarriage, a spraying turret movably arranged on the triangular support and a monitoring camera arranged on the spraying turret, wherein the spraying system support extends in the direction away from the undercarriage and forms a triangular support. The initial positioning coordinates are corrected by presetting the light reflection judgment threshold value and the water mist judgment threshold value in combination with the current temperature and the vertical distance of the photovoltaic panel, so that the unmanned aerial vehicle is prevented from swinging and shifting, and the risk of collision with the photovoltaic panel is reduced.

An aerial vehicle includes a hull containing the main processor, energy storage, support components such as sensors, wireless communication, and landing gear. Attached to the hull are at least three thrust or propulsion units each with two degrees of freedom from the hull allowing them to orient independently in any direction and apply thrust independently from the hull or any other thrust or propulsion unit. In some embodiments, a mount for auxiliary attachments is included or the auxiliary system is built into the hull. Components like the energy storage, auxiliary attachments, and / or propulsion units may also be replaceable as required.

The invention discloses an unmanned aerial vehicle undercarriage load prediction model training method and device, equipment and a storage medium, and relates to the technical field of computers. According to the method, a model is trained according to a flight parameter data sequence of a whole landing period and undercarriage load data, flight parameters of time sequences before and after a landing process are covered, multi-source time sequence data fusion is adopted, and the flight parameter data sequence of the whole landing period is also adopted for prediction during prediction. The method is suitable for structural damage accumulation and fatigue life analysis; target type flight parameters are screened out through the Pearson correlation coefficient and mutual information, principal component analysis is carried out on the target type flight parameters, and the accuracy of real time sequence characteristics is improved; moreover, the sample size is expanded through the time sequence condition generative adversarial network, different landing stages are dynamically adapted in combination with the multi-stage long-short-term memory neural network sub-model, the prediction reliability under the complex working condition is improved, and the accuracy of landing gear load prediction is improved.

The invention discloses a novel tilting dual-rotor unmanned aerial vehicle, which belongs to the technical field of unmanned aerial vehicles, and comprises a wing body fusion fuselage and two outer wing sections, the two tilting rotor assemblies are used for providing power, controlling rolling, pitching and yawing in a vertical flight mode and controlling yawing in a horizontal flight mode, the two pitching and rolling rudder assemblies are used for controlling pitching and rolling in a horizontal flight state, and the two tilting rotor assemblies are symmetrically arranged in front of the wing body fusion fuselage; the pitching rolling rudder assembly is arranged in the middle of the outer wing section; the outer wing section is of a structure capable of being folded in the tail direction, so that the center of gravity is moved backwards to the position behind a stop point of the tail after the outer wing section is folded, and the unmanned aerial vehicle stably stops on a rod-shaped object with the diameter being 13 cm or less under the unpowered condition. On one hand, the problems that a tailstock type unmanned aerial vehicle is difficult to take off and land and a traditional unmanned aerial vehicle needs an undercarriage to take off and land are solved, and the problems that an existing unmanned aerial vehicle needs to be additionally provided with a parking actuator and needs to be parked with power are solved.

A storage and order picking system (10) is disclosed, comprising: a drone (22) equipped for transporting a load carrier (32) and comprising a landing gear (62); and a guide frame (44) comprising at least one rail (68) extending in a longitudinal direction (X), preferably comprising an inlet section (72) and an outlet section (74) adjoining thereto, wherein the landing gear (62) and the at least one rail (68) are configured to couple to each other in order to move the drone (22) guided along the at least one rail (68); and wherein the at least one rail (68) is arranged in an area within the system (10) through which the drone is moved to perform an intralogistics function.

A craft is provided comprising: a propulsion system; a fuselage coupled with the propulsion system, wherein the fuselage is configured to carry a payload and fuel for the propulsion system; and a pre-assembled wing coupled with the fuselage; wherein the craft is designed to take-off without using a runway and does not have landing gear to land.

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.

The invention relates to the technical field of aeronautical manufacturing and robot assembly, and discloses an aeronautical landing gear cable teleoperation collaborative assembly system and method, and the system comprises a master end interaction subsystem, a slave end assembly subsystem and a central control processing subsystem. The method comprises the following steps: acquiring multi-modal data through an environment monitoring camera, a six-dimensional force sensor and a touch sensor, and realizing space-time registration and state estimation by using Kalman filtering; and planning an optimal path by using a genetic algorithm based on the digital twinborn model and providing augmented reality guidance. And the system calculates visual confidence in real time, and adaptively switches a vision dominant control mode according to the visual confidence: when the vision is limited, the rigidity of the mechanical arm is automatically reduced, the force feedback weight is enhanced, and an operator is assisted to complete compliant operation in a blind area. According to the invention, the problems of sensing shielding and precise control of flexible cable assembly in a narrow cabin are solved, and the safety and efficiency of assembly operation are improved.

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.

Disclosed here is an aircraft landing gear support fixture suitable for supporting a grounded aircraft for testing purposes. The support fixture includes a strut having a longitudinal strut axis, an upper strut end, and a lower strut end. The upper strut end has attachment structure that is compatibly shaped, sized, and configured to attach the strut to the aircraft in lieu of a landing gear strut of the aircraft. The support fixture also includes a support platform to support the strut, wherein the support platform is in a fixed position relative to a stationary reference foundation. A strut force sensor is coupled between the lower strut end and the support platform to provide sensor output associated with load imparted by the strut. The strut, the strut force sensor, and the support platform are coupled together and arranged to inhibit movement of the strut along the longitudinal strut axis.

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 discloses a multi-degree-of-freedom adjustable undercarriage disassembling and assembling device which comprises a movable base, a lifting mechanism, a fine adjustment mechanism, a support adjusting mechanism, a control cabinet and four axle supports. According to the multi-degree-of-freedom adjustment undercarriage dismounting and mounting device, horizontal movement is achieved through the movable base, lifting movement is achieved through the lifting mechanism, angle adjustment is achieved through the fine adjustment mechanism, and therefore three-dimensional movement of an undercarriage in the mounting process and accurate alignment with a standard mounting angle are achieved, and the problem that manual angle adjustment is difficult is solved; the disassembly and assembly processes of the undercarriage are more efficient and convenient; the support adjusting mechanism is used for adjusting the distance between the four axle supports, so that the four axle supports can be suitable for most undercarriages of common models, and the operation cost of airlines and maintenance factories is greatly reduced.

The invention belongs to the technical field of aircraft assembly, and discloses an aircraft front wheel turning angle monitoring device and method, and the device comprises a mechanical sensing module, a signal processing module and a signal receiving device. The mechanical sensing module is detachably mounted on a shock strut of a nose landing gear of an aircraft, and the rotary motion of the shock strut is converted into a linear displacement signal through a gear transmission mechanism in the mechanical sensing module; the signal processing module analyzes the displacement signal into a front wheel turning angle electric signal; and the signal receiving device receives and displays the angle value. The invention further discloses a corresponding monitoring method. The device adopts a modular and non-invasive design, solves the problems that the turning angle of the front wheel cannot be monitored in real time and the over-limit risk exists in the aircraft traction process, has the advantages of being convenient and fast to install, accurate in measurement and wide in applicability, and remarkably improves the safety and the working efficiency of flight guarantee.

Systems for activating and deactivating an emergency landing gear system in an aircraft include a rotary toggle mechanism that actuates a switch. When the switch is actuated, the emergency landing gear system is activated and the operation of one or more other aircraft systems may be modified accordingly. The rotary toggle mechanism may be placed in three different states: a ready state, an active state, and a reset state. In the ready state, the switch is not actuated and the emergency landing gear system is not activated. In the active state the switch is actuated and the emergency landing gear system is activated. While the mechanism is in the active state the mechanism cannot be returned to the ready state without first passing through the reset state.

The application relates to a main landing gear cabin ventilation device and an airplane comprising the device. In the device, a ram air inlet is located on a ram air side of a skin; a main air supply pipeline is connected to the ram air inlet; a ventilation disc is located at the end of the main air supply pipeline and used for conveying ram air to a wheel assembly in the main landing gear cabin; a bypass pipeline is connected to the ram air inlet; a skin air outlet is located at the end of the bypass pipeline; a flow self-adjusting module is installed in the bypass pipeline; a throttle contraction structure defines a flow channel; an air bag is located in the flow channel; the flow area of the flow channel is changed by expansion or contraction of the air bag; one end of a heat pipe is connected to a wind collecting cover, and the other end of the heat pipe is inserted into the air bag and used for transmitting heat of the wheel assembly to the air bag so that the air bag is expanded or contracted. According to the above technical scheme, the following beneficial technical effects can be achieved: the main air supply pipeline flow can be automatically adjusted according to the temperature state of the wheel assembly, and the main landing gear cabin is cooled on demand.

The utility model relates to the technical field of aircraft, and disclose a kind of movable landing gear fairing, including landing gear and upper fairing, the one end of landing gear is provided with mounting hole, mounting hole is provided with multiple, and pass through upper fairing and enter aircraft, by the mounting hole and aircraft fixed connection, can be fixed by bolt or bolt etc. detachable fixed mode, the upper fairing is fixedly connected with aircraft. By adopting the structure form of one end without connection, the deformation of landing gear can be better absorbed, the inside is filled with foaming material with good compression, effectively supporting fairing, thereby improving stability, solving the problem that fairing is prone to deformation damage, and internal support is insufficient, and stability is poor.

The application provides an aircraft, comprising a fuselage, a bumper, a connecting mechanism and a landing gear, the cylinder body of the bumper is assembled to the fuselage; the connecting mechanism is hinged to the movable rod of the bumper and the fuselage; and the landing gear is foldably connected to the connecting mechanism. In this way, when the landing gear vibrates, the landing gear can transmit the vibration to the connecting mechanism to drive the connecting mechanism to rotate relative to the fuselage, and then drive the movable rod to slide in the cylinder body to achieve the effect of energy absorption and vibration reduction through the bumper. In addition, compared with the technical solution in the prior art that the bumper is synchronously folded with the landing gear, the aircraft provided by the embodiment of the application does not need to consider the influence of the weight of the bumper on the folding of the landing gear, the weight of the folding part is reduced, and no folding space needs to be reserved for the bumper after the landing gear is folded, which helps to reduce the volume of the aircraft.

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.

A towbarless tractor for towing an airplane having a nose landing gear includes a chassis, a body supported on the chassis, and a capture system. The capture system includes a lift body coupled to at least one of the body or the chassis, a cradle coupled to the lift body, and a side-shift actuator configured to selectively move the cradle along a lateral direction relative to the body.