2643 results about "Landing gear" patented technology

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 relates to an aircraft nose landing gear taxiing and shimmy simulation test bed. The test bed comprises a test device main body structure, a power execution control mechanism, a vibration excitation mechanism and a vibration detection system. The method solves the problems of determination, contrast evaluation and detection analysis of the shimmy influence factors of the nose landing gear of the aircraft. The torsion steering engine is added, so that the turning condition of a ground plane can be simulated. The height-adjustable supporting cross beam can adapt to undercarriages of different sizes only by replacing the undercarriage clamp instead of replacing the whole frame, so that the use cost is greatly reduced. And more accurate data are provided for the design of the nose landing gear of the aircraft.

A ground detection system for an aircraft based on capacitive sensing. The system comprises an electrode mounted to an aircraft landing gear. As the aircraft landing gear approaches the ground, the electrode and the ground together form a variable capacitor having a capacitance that depends on a distance of the electrode from the ground. Signal processing electronics are used to measure the capacitance and, on the basis of the measured capacitance, determine a distance of the aircraft from the ground.

The invention provides an aircraft landing gear dismounting and mounting device, belongs to the technical field of aviation equipment, and solves the problem that in the prior art, landing gear dismounting and mounting equipment is difficult to meet the requirements for efficient, accurate and flexible dismounting and mounting in the modern aviation maintenance field. Comprising a frame, a moving frame is arranged on the inner side of the frame, and the moving frame is driven by a first driving device; a moving plate is arranged on the frame and is driven by a second driving device; an arc-shaped guide rail is arranged on the movable plate, a supporting frame is arranged on the arc-shaped guide rail, a lifting device and a fixing device are arranged on the supporting frame, and a clamp is arranged on the top of the lifting device. According to the undercarriage disassembling and assembling device, through cooperative operation of the first driving device, the second driving device and the lifting device, all-directional flexible adjustment of the tool on the X axis, the Y axis and the Z axis is achieved. Due to the design of the arc-shaped guide rail, the supporting frame can flexibly rotate within a certain angle range, and the adaptability and flexibility of the device are further enhanced.

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 a rocket-boosted warplane ultra-short-distance launching take-off system and method. The system comprises a chassis, a high-precision track, a hydraulic lifting mechanism and a rocket sled. The rear end of the high-precision track is connected with the top of the chassis in a vertically swinging mode, the front end of the high-precision track is driven by a hydraulic lifting mechanism to ascend and descend, and the rear portion of the high-precision track is provided with a check block. The bottom of the rocket sled is provided with a sliding block used for being in sliding fit with the high-precision track. The mounting interface is used for being connected with a warplane undercarriage through an electronic lock, and the electronic lock is used for timing when a rocket engine is started, unlocking when the rocket engine reaches the working time and sending a separation success signal after being separated from a warplane. Small-overload ultra-short-distance take-off of the fighter is achieved, the volume of ground take-off facilities of the fighter is effectively reduced, the requirement for ground conditions is lowered, the flexibility and convenience of deployment are effectively improved, and the structure or a power system of the fighter is not greatly changed.

The utility model discloses a landing lever locking device and an unmanned aerial vehicle. The landing lever locking device comprises an unmanned aerial vehicle body. The foot stool assembly comprises a sliding rail seat, a lifting rod and a locking device, and the lifting rod is connected to the sliding rail seat in a sliding mode. The lock catch device comprises a lock box, a sliding block and a driver, the lock box is provided with a vertically-through box lock hole, the sliding block can be connected into the lock cavity in a left-right sliding mode, the sliding block is provided with a vertically-through lock catch hole, the lock catch hole comprises a sliding lock hole and a fastening hole communicated with the sliding lock hole, at least one clamping section is arranged on the side wall of the fastening hole, and the output end of the driver is connected to the sliding block. And the inner wall of the fastening hole is matched with the outer wall of the lifting rod. The lock box is arranged on the unmanned aerial vehicle body, the rising and falling rod is slidably connected to the lock box lock hole and the sliding lock hole, the inner wall of the fastening hole is matched with the outer wall of the rising and falling rod, and the sliding block can be inserted into the rising and falling rod in the radial direction under the driving condition of the driver and is inserted into and clamped to the outer wall of the rising and falling rod through the clamping section. The purpose of clamping the lifting rod can be achieved only by driving the sliding block to move rightwards through the driver.

The invention discloses an MBSE-based aircraft undercarriage system model integration method, and belongs to the technical field of system engineering. The method comprises the following steps: constructing an aircraft undercarriage system architecture, a classification mapping of simulation design information and a GOPPRR-E element model, and a meta-model library; constructing an architecture model according to a demand-function-logic-physical process, and generating a Simulink simulation model according to the architecture; a simulation model semantic mapping rule is constructed according to an OSLC specification, and design information is analyzed to establish an integrated data model; and a Simulink simulation tool integration adapter is constructed, and a tool interoperation service based on Web is provided. According to the method, a multidisciplinary model can be accurately constructed, uniform expression of architecture and simulation models and semantic consistency of heterogeneous models are realized, two-way transmission of cross-domain information and interoperation between tools are supported, the problem of interoperation between architecture modeling and simulation modeling tools in aircraft undercarriage system design is effectively solved, and the design efficiency is improved.

The invention relates to a test device and method for testing the performance of an elevator speed governor, and the device comprises a test rack which is internally provided with a lifting channel for testing; the main rope is hung and wound on the traction machine; the undercarriage is arranged on one side of the traction machine and connected to the main rope, and the car frame is arranged below the undercarriage and connected with the undercarriage through a detacher; the counterweight frame is arranged on the other side of the traction machine and is connected to the main rope; the speed limiter is arranged at the top of the test rack; the rope gripper is arranged at the top of the test rack; and the data acquisition unit is used for acquiring the running speed of the lift car frame, the wheel speed of the speed limiter, the lifting force of the speed limiting rope, an electrical action signal and a mechanical action signal. The performance of the speed governor can be tested under the working conditions that the lift car frame freely falls when running at a rated speed and the lift car frame falls downwards at different accelerations in a static state.

The invention relates to a tilting rotor unmanned aerial vehicle, in particular to an unmanned aerial vehicle combining a flying wing type structure and a multi-shaft tilting rotor. A completely fused flying wing type fuselage is formed by a low-speed wing shape, and no other fuselage characteristics exist except that bilaterally symmetrical wings are directly connected and fused in the middle; a left tilting rotor frame and a right tilting rotor frame are mounted at the left end and the right end of the flying wing type fuselage respectively; at least one to at most six brackets extend from the front part and the rear part respectively, and symmetrical tilting rotor frames are mounted on the brackets; motors and paddles are mounted on all the tilting rotor frames; and an undercarriage is mounted below the flying wing type fuselage. During tilting, a single motor and a single blade are not tilted, but a plurality of power units formed by one or more motors and blades are tilted in groups through a tilting rotor frame. Therefore, the structure is simplified, and the safety and the maneuverability are improved. The landing gear has two types, one type is a foot type landing gear suitable for vertical take-off and landing in a soft site, and the other type is a wheel type landing gear suitable for short-track take-off and landing in a hardened site.

The invention discloses a method for simulating bottom bending tensile stress of an airport rigid pavement slab under the action of aircraft wheel loads. The method comprises the following steps: establishing an airport rigid pavement three-dimensional refined finite element model and an airport rigid pavement two-dimensional simplified finite element model; selecting aircraft wheel sliding load of the aircraft type main landing gear; obtaining an equivalent airplane wheel sliding load; obtaining an equivalent airplane wheel sliding load calculation formula under the random transverse action position of the airplane wheel; and obtaining the bottom bending-tensile stress value of the pavement slab under the airplane wheel sliding load. According to the method, by establishing the rigid pavement two-dimensional simplified finite element analysis model, rapid prediction of the airport rigid pavement slab bottom stress response under the aircraft wheel load effect is achieved. According to the method, the bending-tensile stress of the slab bottom is quickly and accurately calculated according to different pavement structure parameters and the transverse action position of the airplane wheel. The method effectively overcomes the defects of complex modeling, high calculation cost and the like of traditional rigid pavement refined simulation, has the characteristics of simplicity and convenience in modeling and quickness in calculation, and remarkably improves the airport engineering design and analysis efficiency.

The utility model discloses a road crack patrol unmanned aerial vehicle capable of spraying marks, and relates to the technical field of unmanned aerial vehicles. The utility model provides a road crack inspection unmanned aerial vehicle capable of spraying marks, which comprises an unmanned aerial vehicle frame, four rotating rotors which are distributed at equal intervals are rotatably connected to the top end of the unmanned aerial vehicle frame, undercarriages which are transversely symmetrical are fixedly connected to the bottom end of the unmanned aerial vehicle frame, and the road crack inspection unmanned aerial vehicle further comprises a mounting frame which is fixedly connected to the bottom end of the unmanned aerial vehicle frame. The bottom end of the mounting frame is rotatably connected with a spraying cylinder, the bottom end of the unmanned aerial vehicle frame is fixedly connected with a storage cylinder, the storage cylinder communicates with the spraying cylinder through a hose, the bottom end of the mounting frame is fixedly connected with a driving motor, and an output shaft of the driving motor is connected with the spraying cylinder. Rotor wings are rotated to drive the device to fly to inspect cracks on a road, when the cracks are detected, the spraying barrel rotates downwards to adjust the angle, then paint is sprayed to the cracks for marking, and accurate guidance is provided for follow-up maintenance work.

The invention provides a main landing gear cabin door mechanism, an aircraft and a folding and unfolding method. The main undercarriage cabin door mechanism comprises a left cabin door and a right cabin door, one end of the left cabin door is provided with a first retractable driving mechanism, one end of the right cabin door is provided with a second retractable driving mechanism, and a small cabin door is hinged to the side, close to the right cabin door, of the left cabin door; the small cabin door and the left cabin door are provided with third folding and unfolding driving mechanisms which can respectively drive the small cabin door and the left cabin door to rotate; in the first position, the left cabin door and the right cabin door are both in a vertical state, and the small cabin door and the left cabin door are folded and overlapped; and at the second position, the left cabin door, the small cabin door and the right cabin door are horizontally positioned on the same plane. The small cabin door can be independently retracted and folded, after the cabin door is opened, the folded small cabin door can reduce the windward area of the cabin door in the put-down state, the pneumatic load borne by the cabin door is reduced, and the design of a driving mechanism for retracting and releasing the cabin door is lighter.

The invention discloses an undercarriage retracting and releasing mechanism wear prediction method based on digital twinning, and the method comprises the steps: firstly building an undercarriage three-dimensional model containing geometric dimensions and material characteristics, building a multi-body dynamics simulation model, and simulating the stress and wear process of a pin shaft under the actual working condition; and adopting an Archard wear calculation model considering key parameters to calculate the wear of the pin shaft in the simulation model in real time. On the basis, uncertainty analysis of parameters in Archard is carried out, the parameters are considered to obey normal distribution, and a prediction model under multivariate uncertainty is established by setting reasonable mean values and standard deviations. And finally, based on the digital twin model, by using a particle filtering method, initializing a particle swarm, changing a particle weight by virtue of a state and an observation equation, re-sampling to approach a real state, iteratively updating a curve, calibrating model parameters and a state, improving prediction precision, improving prediction accuracy and reliability, discovering a potential wear problem in advance, and providing a basis for a maintenance plan.

The invention belongs to the technical field of alloy steel, and relates to composite reinforced high-toughness steel and a preparation method thereof. The steel comprises the following chemical components in percentage by weight: 6.0%-9.4% of Ni, 7.6%-8.9% of Co, 0.8%-3.8% of Cr, 1.0%-2.6% of Mo, 0-0.9% of W, 0.05%-0.60% of V, 0-0.10% of Nb and the balance of Fe. C and Al are added to serve as strengthening elements, and the balance is Fe and impurity elements. When 0.14% < = C < 0.20%, 1.2% < = Al < = 1.6%, 1.0% < = Mo + W / 2 < = 2.0%; when 0.20% < = C < = 0.35%, 0.6% < = Al < = 1.3%, and 2.0% < = Mo + W / 2 < = 3.0%. The alloy is subjected to vacuum induction melting or multi-time melting, homogenizing diffusion annealing and forging rolling to form a material, so that the tensile strength of the steel reaches 2200-2350 MPa or above, the yield strength reaches 2000-2150 MPa or above, and the steel has excellent strength, plasticity and toughness matching and can be used for components such as engine shafts, aircraft landing gears, high-performance shells, frame beams and molds.

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 utility model discloses an undercarriage drop test stand, which comprises a vertical track support, a vertical pulley assembly is arranged on the vertical track support, the vertical pulley assembly moves up and down along the vertical track support, and a cantilever pulley track assembly is fixedly connected to the vertical pulley assembly. The cantilever pulley track assembly moves up and down along the vertical track support along with the vertical pulley assembly, a horizontal pulley assembly is connected to the cantilever pulley track assembly in a sliding mode, an undercarriage mounting base is arranged on the lower side of the horizontal pulley assembly, and the undercarriage mounting base directly faces an inclined plane base plate arranged on the ground. According to the invention, impact generated by vertical falling of the undercarriage can be simulated, horizontal displacement generated by falling contact with a slope can also be simulated, various simulation test environments are provided, and the damage degree of the undercarriage and the stability of a connection area of the undercarriage and an aircraft main body are judged according to recorded test data.

The invention provides a broadband sound absorption structure suitable for undercarriage cabin door noise reduction and a design method, and belongs to the field of aircraft noise reduction. The sound absorption structure comprises a plurality of perforated plate type Helmholtz cavity unit cells and a plurality of embedded pipe type Helmholtz cavity unit cells. In the perforated plate type unit cells, one or more first through holes are formed in the perforated plate. And in the embedded pipe type unit cells, the embedded pipes penetrate through the perforated holes in the perforated plates and extend into the cavities. Cavities of the two single cells face the same direction, and the perforated plate forms a curved surface conformal with an undercarriage cabin door. The effective length of the neck of the perforated plate is increased by using the embedded pipe, the low-frequency sound absorption performance is improved, the sound absorption performance and the sound absorption bandwidth of the middle-frequency band are improved by using the perforated plate type Helmholtz cavity, meanwhile, the curved surface conformal design is highly matched with the special-shaped cabin door structure, and the sound absorption performance is improved. The low-frequency and medium-frequency sound absorption performance can be guaranteed, and meanwhile the light and thin requirements of an aircraft can be met; and a pure passive mechanical structure is adopted, so that the control complexity and stability risks of an active noise reduction system can be avoided.

The invention discloses an aircraft front wheel electrical zero calibration method, device and equipment and a medium, relates to the technical field of aircraft front wheel control, is applied to ground comprehensive maintenance equipment, and comprises the steps that a target angle instruction is used for controlling a scale line of a rotating sleeve in a nose landing gear to be aligned with a scale line of a front supporting column outer cylinder; a front wheel shimmy damping instruction is sent to a front wheel operation control box of the aircraft, so that the front wheel operation control box controls front wheels to keep stable; the current angle information of the front wheel angle sensor is determined as current electrical zero position reference information; the front wheel and the rotating sleeve are controlled to rotate through a front wheel rotating instruction, and if the deflection angle of the scale mark of the rotating sleeve is matched with the front wheel rotating instruction, it is judged that front wheel electrical zero calibration of the aircraft is completed. And the accuracy and simplicity of the electrical zero calibration of the airplane front wheel are improved.

The invention belongs to the field of electric vertical take-off and landing aircrafts, and discloses a novel vertical take-off and landing remote high-speed manned electric tilt-rotor aircraft structure which comprises an aircraft body, wings, a V-shaped empennage, six supporting arms, six tilt-rotor units, an energy system, an avionics system and an undercarriage. The six tilting rotor wing units are symmetrically installed on the wings and the V-shaped empennage through the six supporting arms. The aircraft is mainly characterized in that the design of six tilting rotor units is adopted, so that the aircraft has the advantages of vertical take-off and landing, high-speed forward flight, no structural'dead weight 'and useless power consumption; the design that the supporting arms extend out of the wings and the empennage to exceed the radius length of the rotors is adopted, and the downward projection of a rotor disc is not overlapped with the wings and the empennage in the vertical flight state, so that downward washing flow of the rotors cannot generate downward loads on the wings and the empennage, and power consumption for overcoming the downward loads is avoided; the design of the wings with high aspect ratio and winglets is adopted, so that the forward flying lift-drag ratio and the cruising efficiency are improved, and the aircraft has high-speed forward flying and remote flying capabilities; and the six tilting rotor units adopt the same tilting mechanism, so that the complexity of design and manufacturing is reduced.

A locking system for doors of a deployable aircraft landing gear system includes a spring-biased swing arm configured to be pivotally attached to a body of an aircraft and including a roller at a distal end of the swing arm. The swing arm is configured to engage with a portion of a first landing gear bay door to prevent the first landing gear bay door from opening.

A moving device includes: two leg portions each including an end-portion wheel and an intermediate wheel; a placement portion supported by the two leg portions; and a control unit configured to control the two leg portions. The moving device is configured such that, under a state of four-wheel ground contact in which the end-portion wheel and the intermediate wheel are in contact with the ground, when the end-portion wheel is moved from the boarding area to the step of the escalator and / or when the end-portion wheel is moved from the step to the landing area of the escalator, a wheel speed of the end-portion wheel is controlled by the control unit.

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.

A trailer landing gear deployment device for mechanically raising and lowering a trailer includes a trailer and a landing gear that can be raised and lowered relative to the trailer. A handle is mechanically coupled to the landing gear, which is selectively raised and lowered by rotation of the handle. A disk is rotatably coupled to a housing. An arm is coupled to the disk. The arm is couplable to the handle and rotates the handle when the disk is rotated. A motor is operably coupled to the disk wherein the motor is actuatable to rotate the disk. A power source is electrically coupled to the motor. A control panel is electrically coupled to the power source. The control panel is manipulatable to actuate the motor.

A dual-mode landing gear adapter enables rapid interchangeability between manual and powered operation for trailer landing gear extension and retraction. The adapter includes a gear shaft adapter having a first coupling end structured to securely engage the trailer's landing gear gearbox shaft, and an opposite second coupling end with axial slots configured for receiving a two-pin anchor. A manual crank and a drill head attachment each include a corresponding two-pin anchor for secure, selective coupling with the adapter. The drill head attachment further comprises a cylindrical collar structured to securely receive a standard electrically powered drill / driver, secured via a cotter pin or similar fastening device. The invention facilitates quick, secure switching between powered and manual operation without tools, ensuring convenience, safety, and operational flexibility. This adapter system reduces user effort, increases efficiency, and provides robust reliability under varying operational conditions common in commercial trucking and trailer applications.

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 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 utility model is applicable to the technical field of undercarriages, and provides an undercarriage angle measuring device, which comprises a laser displacement sensor and an angle sensor, the angle sensor is used for measuring the rotation angle of a rocker arm around a hollow rotating shaft, the angle measured by the angle sensor is alpha, and the rotation angle of an undercarriage piston rod is alpha / 2. According to the utility model, the laser displacement sensor and the angle sensor are integrated, so that the problem of undercarriage measurement in a complex shape and in a dynamic process is ingeniously solved. The device can accurately measure the rotation angle and the compression amount of the undercarriage piston rod at the same time, does not need complex installation, and is high in adaptability. The high-precision measurement of the laser displacement sensor ensures the accuracy of the expansion amount, and the angle sensor realizes the accurate measurement of the rotation angle through non-contact induction and isosceles triangle geometrical relationship calculation. The whole device is compact in structure and easy to install and maintain, and provides a reliable and accurate measurement means for the dynamic performance test of the undercarriage.

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.