Aircraft landing gear grounding speed simulation system and method

Abstract

The invention provides an aircraft landing gear grounding speed simulation system and method, and relates to the technical field of landing gear verification equipment. The aircraft landing gear grounding speed simulation system comprises a rack, a simulation assembly and a lifting mechanism. Wherein the simulation assembly comprises a power unit and a sliding seat which are arranged on the rack, the power unit can drive the sliding seat to ascend, the sliding seat comprises an undercarriage mounting part and a bearing part, the undercarriage mounting part is used for mounting an undercarriage, and a plurality of layers of balancing weights are stacked on the bearing part. The lifting mechanism comprises a driving assembly and a lifting unit which are arranged on the rack, the lifting unit can be driven by the driving assembly to descend or ascend on the rack, and the lifting unit comprises a supporting plate which can be inserted between any two adjacent layers of balancing weights. The aircraft landing gear grounding speed simulation system can well simulate the grounding state of the landing gear, and provides data for optimization of the landing gear.

Description

Technical Field

[0001] The present invention relates to the technical field of landing gear verification equipment, and in particular to a system and method for simulating the touchdown speed of an aircraft landing gear. Background Art

[0002] The dynamic response of aircraft landing gear during the taxiing and braking process is one of the important topics in the study of aircraft landing gear dynamics. It mainly studies the dynamic characteristics of the landing gear structure and braking system during the taxiing and braking process and its failure mechanism.

[0003] Among them, the load of the aircraft landing gear will increase sharply at the moment of touching the ground, so the state of the aircraft landing gear at the moment of touching the ground is related to the safety of the landing gear and the aircraft. However, the current landing gear state simulation equipment can often only simulate the state of the landing gear after touching the ground, and lacks the state simulation of the landing gear at the moment of touching the ground. The optimization of the landing gear lacks data in this regard. Summary of the invention

[0004] To this end, the present invention proposes an aircraft landing gear touchdown speed simulation system and simulation method, so as to better simulate the touchdown state of the landing gear.

[0005] The technical solution of the present invention is as follows: In a first aspect, the present invention provides an aircraft landing gear touchdown speed simulation system, comprising: frame; A simulation component, the simulation component comprises a power unit and a sliding seat arranged on the frame, the power unit can drive the sliding seat to rise, and the sliding seat comprises a landing gear mounting portion and a bearing portion, the landing gear mounting portion is used to mount the landing gear, and a plurality of layers of counterweight blocks are stacked on the bearing portion; A lifting mechanism, the lifting mechanism comprising a driving assembly and a lifting unit arranged on the frame, the lifting unit can be driven by the driving assembly to descend or ascend on the frame, and the lifting unit comprises a supporting plate that can be inserted between any two adjacent layers of the counterweight blocks; The pallet can be inserted under several layers of the counterweight blocks, and can be driven by the driving assembly to lift each of the counterweight blocks to leave a counterweight block of a predetermined weight on the sliding seat; and the power unit can drive the sliding seat to rise a predetermined distance so that the landing gear can touch the ground as the sliding seat falls.

[0006] Furthermore, the bearing portion includes a sliding frame which is slidably provided on the frame, and the landing gear mounting portion includes a mounting plate which is fixedly provided on the bottom end of the sliding frame.

[0007] Furthermore, the power unit is two first hydraulic cylinders fixed on the frame and disposed on both sides of the sliding frame. The sliding frame is provided with two support plates, and the telescopic rods of the two first hydraulic cylinders can support the two support plates accordingly.

[0008] Furthermore, weighing sensors are respectively installed on the telescopic rods of the two first hydraulic cylinders.

[0009] Furthermore, the driving assembly includes a fixed seat, a lifting plate and a driving unit; the fixed seat is fixed on the frame, and a nut is fixed on the fixed seat, the lifting plate can be lifted and lowered on the fixed seat, and the driving unit includes a first motor and a ball screw, the first motor is arranged on the lifting plate, the ball screw is arranged on the lifting plate and can be driven to rotate by the first motor, and the ball screw is threadedly connected to the nut.

[0010] Furthermore, a plurality of supporting grooves are respectively provided on the bottom surface of each of the counterweight blocks, and each of the supporting grooves has an opening located on the side of the counterweight block; the lifting unit includes a plurality of rotary power output devices arranged on the lifting plate, and each of the supporting plates is respectively arranged on the output end of the rotary power output device, and each of the supporting plates can be driven by the rotary power output device to rotate from the opening and be inserted into the corresponding supporting groove, or to be removed from the supporting groove.

[0011] Furthermore, two brake plates are fixedly arranged on the frame, and the two brake plates are disposed on two opposite sides of the sliding seat, and brakes capable of clamping or releasing the corresponding brake plates are respectively fixedly arranged on two opposite sides of the sliding seat.

[0012] Further, the bearing part is fixedly provided with a plurality of guide rods, and each of the counterweight blocks is provided with a guide through hole which is slidably mounted on each of the guide rods; the frame is fixedly provided with a plurality of guide rods, and the guide rods of the bearing part correspond one to one with the guide rods of the frame in the vertical direction; The support plate can be inserted under several layers of the counterweight blocks, and the support plate drives the counterweight blocks to move along the guide rods of the load-bearing portion. The counterweight blocks are separated from the guide rods of the load-bearing portion and move along the guide rods of the frame until they move to a predetermined position.

[0013] Furthermore, the frame is provided with a plurality of second hydraulic cylinders, and the sliding seat is provided with a plurality of connecting plates, the telescopic end of each second hydraulic cylinder is connected to each connecting plate in a one-to-one correspondence, and each second hydraulic cylinder can apply downward pressure to the connecting plate.

[0014] On the other hand, the present invention provides a method for simulating the touchdown speed of an aircraft landing gear, which uses the above-mentioned aircraft landing gear touchdown speed simulation system and includes the following steps: Mounting the landing gear to be tested on the landing gear mounting portion of the sliding seat; After the telescopic rod of the first hydraulic cylinder pushes the sliding seat to a predetermined height, the sliding seat is fixed, and a part of the counterweight is lifted by the lifting mechanism, so that a counterweight of a predetermined weight is left on the sliding seat; After the telescopic rod of the first hydraulic cylinder is retracted to the lowest end, the sliding seat is released, so that the landing gear falls with the sliding seat and touches the ground; After the landing gear touches the ground, each second hydraulic cylinder applies pressure to the sliding seat.

[0015] The working principle and beneficial effects of the present invention are: The aircraft landing gear touchdown speed simulation system provided by the present invention is provided with a simulation component and a lifting mechanism on a frame, wherein the lifting mechanism can lift a part of the counterweight blocks on the sliding seat, so that the counterweight blocks of a predetermined weight are left on the sliding seat to simulate the weight of the aircraft, and after the power unit drives the sliding seat to rise to a predetermined height on the frame, the landing gear can fall freely with the sliding seat and touch the ground, thereby completing the simulation of the landing gear touchdown state and providing data for the optimization of the landing gear. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0017] Figure 1 A three-dimensional diagram of an aircraft landing gear touchdown speed simulation system provided by an embodiment of the present invention; Figure 2 A front view of an aircraft landing gear touchdown speed simulation system provided by an embodiment of the present invention; Figure 3 for Figure 1 A partial enlarged view of the middle A; Figure 4 A three-dimensional diagram of a lifting mechanism provided by an embodiment of the present invention; Figure 5 An exploded view of the cooperation of two counterweight blocks provided in an embodiment of the present invention; Figure 6 for Figure 5 A partial enlarged view of point B in the middle; Figure 7 An exploded view of a counterweight provided in an embodiment of the present invention.

[0018] In the figure: 100, frame; 110, column; 120, beam; 130, guide rail; 140, brake plate; 200, simulation component; 210, power unit; 211, first hydraulic cylinder; 220, sliding seat; 221, sliding frame; 222, mounting plate; 230, counterweight; 240, guide column; 241, fixed section; 242, guide section; 201, supporting groove; 202, through hole; 203, guide hole; 204, limit groove; 300, lifting mechanism; 310, driving assembly; 311, fixing seat; 312, lifting plate; 313, nut; 314, driving unit; 315, first motor; 316, ball screw; 320, lifting unit; 321, rotary power output device; 322, supporting plate; 400, limit rod; 410, thrust end; 420, elastic member; 500, brake; 600. Second hydraulic cylinder. DETAILED DESCRIPTION

[0019] The following will be combined with the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0020] This embodiment provides an aircraft landing gear touchdown speed simulation system, referring to Figure 1 and Figure 2 As shown, it includes a frame 100, a simulation component 200 and a lifting mechanism 300. The simulation component 200 includes a power unit 210 and a sliding seat 220 arranged on the frame 100, the power unit 210 can drive the sliding seat 220 to rise, and the sliding seat 220 includes a landing gear mounting part and a bearing part, the landing gear mounting part is used to install the landing gear, and a plurality of layers of counterweights 230 are stacked on the bearing part.

[0021] The lifting mechanism 300 includes a driving assembly 310 and a lifting unit 320 disposed on the frame 100. The lifting unit 320 can be driven by the driving assembly 310 to descend or ascend on the frame 100. The lifting unit 320 includes a support plate 322 that can be inserted between any two adjacent layers of counterweight blocks 230.

[0022] Based on the above structure, the aircraft landing gear touchdown speed simulation system of this embodiment can lift part of the counterweight 230 on the sliding seat 220 by the lifting mechanism 300, so that the counterweight 230 of a predetermined weight remains on the sliding seat 220, so as to better simulate the load applied to the landing gear when the landing gear touches the ground, and the power unit 210 can drive the sliding seat 220 to rise to a predetermined height, and then the landing gear can fall and touch the ground with the sliding seat 220, thereby completing the simulation of the landing gear touchdown state, so as to provide data for the optimization of the landing gear.

[0023] For specific structure, refer to Figure 1 As shown, the rack 100 of this embodiment includes two columns 110 and a crossbeam 120 connected between the top ends of the two columns 110. The two columns 110 respectively include a main body and two legs arranged at the bottom end of the main body in a herringbone shape. Obviously, the structure of the rack 100 is not limited to this, as long as it can provide a mounting base for other components and has sufficient strength.

[0024] refer to Figure 1 and Figure 3 As shown, the bearing part of this embodiment includes a sliding frame 221 which is slidably provided on the frame 100. The sliding frame 221 has two accommodating cavities with open tops, and counterweights 230 are stacked and arranged in the two accommodating cavities.

[0025] In this embodiment, reference Figure 1 and Figure 3 As shown, a plurality of guide rails 130 are fixedly mounted on the two uprights 110, and a slider that can slide on each guide rail 130 is fixedly mounted on the sliding frame 221; wherein the length direction of each guide rail 130 is parallel to the height direction of the rack 100. By sliding each slider on the corresponding guide rail 130, the sliding frame 221 can be raised or lowered relative to the rack 100.

[0026] refer to Figure 2 As shown, the power unit 210 of this embodiment is two first hydraulic cylinders 211 fixed on the frame 100 and disposed on both sides of the sliding frame 221. Two support plates are provided on the sliding frame 221, and the telescopic rods of the two first hydraulic cylinders 211 can support the two support plates accordingly. In this embodiment, by providing the power unit 210, the telescopic rods of the two first hydraulic cylinders 211 can extend upward and abut against the corresponding support plates. Thereafter, the continued extension of the telescopic rods of the two first hydraulic cylinders 211 can drive the sliding seat 220 to rise. When the sliding seat 220 needs to fall freely, the telescopic rods of the two first hydraulic cylinders 211 can be retracted in advance.

[0027] In this embodiment, weighing sensors are respectively provided on the telescopic rods of the two first hydraulic cylinders 211 to weigh the sliding seat 220, so as to ensure that the weight of the sliding seat 220 is the required weight and ensure the reliability of the simulation result. It should be noted that the weighing sensor can adopt an existing product, and its structure and working principle will not be repeated here.

[0028] In some embodiments, the number of the first hydraulic cylinders 211 may be one, three, four or more. In some embodiments, the power unit 210 may also be a cylinder or the like.

[0029] refer to Figure 2 As shown, the landing gear mounting portion of this embodiment includes a mounting plate 222 fixed on the bottom end of the sliding frame 221, and the landing gear can be mounted on the mounting plate 222, so as to fix the landing gear on the sliding seat 220. It should be noted that the fixing of the landing gear on the mounting plate 222 can refer to the prior art, and will not be described in detail here.

[0030] In this embodiment, reference Figure 1 and Figure 2 As shown, corresponding to the two groups of counterweight blocks 230, lifting mechanisms 300 are respectively provided on two opposite sides of each group of counterweight blocks 230; the working principles of each lifting mechanism 300 are relatively opposite, and this embodiment will take one group as an example to introduce it.

[0031] refer to Figure 1 , Figure 2 and Figure 4 As shown, the driving assembly 310 of this embodiment includes a fixing seat 311, a lifting plate 312 and a driving unit 314. The fixing seat 311 is fixed on the frame 100, and a nut 313 is provided on the fixing seat 311. The lifting plate 312 is escalably provided on the fixing seat 311. Specifically, in this embodiment, a slider is fixed on the fixing seat 311, and a guide rail 130 is fixed on the lifting plate 312, so that the lifting plate 312 can rise or fall relative to the fixing seat 311 and the frame 100.

[0032] In this embodiment, reference Figure 4As shown, the driving unit 314 includes a first motor 315 and a ball screw 316. The first motor 315 is arranged on the lifting plate 312, the ball screw 316 is arranged on the lifting plate 312 and can be driven to rotate by the first motor 315, and the ball screw 316 is screwed with the nut 313. Specifically, in this embodiment, a first pulley is fixedly sleeved on the output shaft of the first motor 315, and a second pulley coaxial with and fixedly connected to the ball screw 316 is provided on the lifting plate 312, and a belt is provided between the first pulley and the second pulley. It should be noted that the first motor 315 can also directly drive the ball screw 316 to rotate, or drive the ball screw 316 to rotate through a gear or a sprocket, which has the same working principle.

[0033] Based on the above structure, when the motor shaft of the first motor 315 rotates, the ball screw 316 will be driven to rotate through the transmission of the first pulley and the second pulley. When the ball screw 316 rotates, it will have an axial displacement relative to the nut 313 along the ball screw 316, so that the lifting plate 312 rises or falls along the height direction of the frame 100.

[0034] refer to Figure 4 and Figure 5 As shown, in this embodiment, two supporting grooves 201 are respectively provided on the bottom surface of the counterweight 230 corresponding to each lifting plate 312, and each supporting groove 201 has an opening located on the side of the counterweight 230. A lifting unit 320 is respectively provided on each lifting plate 312, and each lifting unit 320 includes two rotary power output devices 321 fixed on the lifting plate 312. Specifically in this embodiment, the rotary power output device 321 is a second motor. In some embodiments, the rotary power output device 321 can also be a rotary cylinder, etc.

[0035] In this embodiment, reference Figure 4 As shown, the above-mentioned supporting plates 322 are respectively fixed on the output ends of the rotary power output devices 321. When the rotary power output devices 321 drive the corresponding supporting plates 322 to rotate, the supporting plates 322 can be rotated from the above-mentioned openings to be inserted into the supporting grooves 201, or rotated out of the supporting grooves 201. When the supporting plates 322 are rotated and inserted into the supporting grooves 201, that is, the supporting plates 322 are inserted between two adjacent counterweights 230, when the driving assembly 310 drives the lifting unit 320 to rise, the counterweights 230 and the counterweights 230 thereon can be lifted, so that the counterweights 230 and the counterweights 230 thereon are separated from the sliding seat 220, and the counterweights 230 of a predetermined weight are left on the sliding seat 220.

[0036] In this embodiment, by setting the above-mentioned lifting unit 320, the support plate 322 can be inserted between any two adjacent counterweight blocks 230, so that the lifting mechanism 300 can more conveniently lift any number of counterweight blocks 230 to leave a predetermined weight of counterweight blocks 230 on the sliding seat 220.

[0037] In this embodiment, four guide rods are fixedly provided on the sliding frame 221, and guide through holes are provided on each counterweight block, which can be respectively mounted on each guide rod, so that each counterweight block is aligned by mounting each guide through hole on the corresponding guide rod. In some embodiments, the number of guide rods can also be two, three or other numbers; at the same time, in order to make the counterweight block 230 stably run to the predetermined position, a connecting beam is installed between the two columns 110 of the frame, a guide rod is installed under the connecting beam, and multiple guide rods are fixedly installed on the connecting beam, and the guide rods of the bearing part correspond to the guide rods of the connecting beam in the vertical direction, and the length direction of the guide rods extends in the vertical direction. When the sliding seat 220 is counterweighted, the driving assembly 310 drives the lifting unit 320 to descend, and the support plate 322 of the lifting unit 320 is inserted under several layers of counterweight blocks 230. The support plate 322 drives the counterweight blocks 230 to move along the guide rods of the bearing part. The support plate 322 continues to move vertically upward, and the counterweight blocks 230 are separated from the guide rods of the bearing part and move along the guide rods of the connecting beam until they move to a predetermined position. In some embodiments, reference may also be made to Figure 5 As shown, a through hole 202 is respectively opened on each counterweight block 230, and a guide column 240 is fixedly inserted in each through hole 202, and a guide hole 203 is respectively provided on the bottom end surface of each guide column 240, and each guide column 240 has a guide section 242 that can be inserted into the guide hole 203 on the adjacent upper counterweight block 230.

[0038] Specifically, the guide column 240 in this embodiment includes a fixed section 241 and a guide section 242 connected in series, wherein the fixed section 241 is used to be fixedly inserted in the through hole 202, and the guide section 242 protrudes upward from the counterweight block 230, and the diameter of the guide section 242 is smaller than the diameter of the fixed section 241. The guide section 242 can be inserted into the guide hole 203 on the bottom end surface of the other fixed section 241.

[0039] In this embodiment, by providing the above-mentioned guide hole 203 and guide section 242, the guide section 242 can be inserted into the guide hole 203 to align two upper and lower adjacent counterweights 230, that is, the counterweights 230 of each layer can be aligned.

[0040] refer to Figure 6 and Figure 7As shown, in this embodiment, a limiting groove 204 is respectively provided on the side wall of each guide section 242, and an avoidance hole opposite to the limiting groove 204 is provided on the side wall of the fixed section 241. A limiting rod 400 is slidably provided on the counterweight 230, and the limiting rod 400 has a bearing and thrust end 410 protruding from the side wall of the bearing groove 201, and an elastic member 420 is provided between the limiting rod 400 and the counterweight 230. The limiting rod 400 can be pushed by the elastic member 420 to be inserted into the limiting groove 204, and when the support plate 322 is rotated and inserted into the bearing groove 201, the bearing and thrust end 410 can be pushed to make the limiting rod 400 escape from the limiting groove 204.

[0041] That is to say, in this embodiment, when a counterweight block 230 is placed on the counterweight block 230 of the lower layer, the support plate 322 pushes the push-bearing end 410 of the limiting rod 400 on the counterweight block 230 of this layer, so that the guide section 242 on the counterweight block 230 of the lower layer can be inserted into the guide hole 203 on the counterweight block 230 of this layer. When the support plate 322 is released from the limiting groove 204, the limiting rod 400 is inserted into the limiting groove 204 of the guide section 242 on the counterweight block 230 of the lower layer under the push of the elastic member 420, thereby fixing the two layers of counterweight blocks 230. After the counterweight block 230 of the bottom layer is fixed to the sliding seat 220, the counterweight blocks 230 on the sliding seat 220 are fixed to the sliding seat 220 as a whole through the fixation between the two adjacent counterweight blocks 230. By fixing each counterweight block 230 to the sliding seat 220 , it is possible to avoid the counterweight block 230 bouncing up when the sliding seat 220 falls until the landing gear touches the ground.

[0042] In some embodiments, a counterweight block 230 capable of pressing the top layer and a pressure plate for fixing each counterweight block 230 relative to the sliding seat 220 may also be provided on the sliding seat 220, but the pressure plate needs to be able to move along the height direction of the frame 100 and also needs to be able to rotate. Compared with the solution of this embodiment, its structure is more complicated.

[0043] In this embodiment, the elastic member 420 is a spring sleeved on the rod and abutted between the rod and the counterweight 230. In some embodiments, the elastic member 420 may also be other elastic components.

[0044] In this embodiment, reference Figure 3 As shown, the frame 100 is fixed with brake plates 140 disposed on two opposite sides of the sliding seat 220, and the sliding seat 220 is provided with a brake 500 capable of holding or releasing the brake plates 140, so as to fix the sliding seat 220 on the frame 100 or release the sliding seat 220 from the frame 100. It should be noted that the brake 500 can adopt an existing product, and its structure and working principle are not described in detail here.

[0045] In this embodiment, a displacement sensor for detecting the displacement of the sliding seat 220 is provided on the frame 100. In this embodiment, by providing the displacement sensor, the instantaneous speed of the sliding seat 220 can be calculated by the real-time displacement of the sliding seat 220, so as to better simulate the touchdown state of the landing gear by making the instantaneous speed of the sliding seat 220 when touching the ground equal to the actual touchdown speed of the aircraft. It should be noted that the displacement sensor can adopt an existing product, and its structure and working principle will not be described in detail here. Since it does not affect the understanding, the displacement sensor is not shown in the drawings of this embodiment.

[0046] refer to Figure 1 and Figure 3 As shown, in this embodiment, four second hydraulic cylinders 600 are further provided on the frame 100, and four connecting plates are correspondingly provided on the sliding seat 220, the telescopic rods of each second hydraulic cylinder 600 are correspondingly connected to the four connecting plates, and each second hydraulic cylinder 600 can apply downward pressure to the connecting plates.

[0047] In some embodiments, the number of the second hydraulic cylinders 600 may be two, three, or other numbers.

[0048] In this embodiment, by providing the above-mentioned second hydraulic cylinders 600, the landing gear's touchdown state can be better simulated. Specifically, the counterweights 230 on the sliding seat 220 are used to simulate the equivalent mass of the aircraft, that is, the mass of the fuselage, wings, and buffer outer cylinders are converted to the mass of the landing gear, and the second hydraulic cylinders 600 are used to apply additional pressure to the landing gear, that is, the total pressure applied to the landing gear by the counterweights 230 and the second hydraulic cylinders 600 is equivalent to the pressure applied to the landing gear by the total weight of the aircraft. The counterweights 230 and the second hydraulic cylinders 600 apply pressure to the landing gear respectively, which is more similar to the actual landing gear touchdown state.

[0049] Based on the overall structure of the above-mentioned aircraft landing gear touchdown speed simulation system, this embodiment further provides an aircraft landing gear touchdown speed simulation method, which uses the above-mentioned aircraft landing gear touchdown speed simulation system and includes the following steps: Mounting the landing gear to be tested on the landing gear mounting portion of the sliding seat 220; After the telescopic rod of the first hydraulic cylinder 211 pushes the sliding seat 220 to rise to a predetermined height, the sliding seat 220 is fixed, and a portion of the counterweight 230 is lifted by the lifting mechanism 300, so that a counterweight 230 of a predetermined weight remains on the sliding seat 220; After the telescopic rod of the first hydraulic cylinder 211 is retracted to the lowest end, the sliding seat 220 is released, so that the landing gear falls with the sliding seat 220 and touches the ground; After the landing gear touches the ground, each second hydraulic cylinder 600 applies a predetermined pressure to the sliding seat 220 .

[0050] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. An aircraft landing gear touchdown speed simulation system, characterized in that: include: frame; A simulation component, the simulation component comprises a power unit and a sliding seat arranged on the frame, the power unit can drive the sliding seat to rise, and the sliding seat comprises a landing gear mounting portion and a bearing portion, the landing gear mounting portion is used to mount the landing gear, and a plurality of layers of counterweight blocks are stacked on the bearing portion; A lifting mechanism, the lifting mechanism comprising a driving assembly and a lifting unit arranged on the frame, the lifting unit can be driven by the driving assembly to descend or ascend on the frame, and the lifting unit comprises a supporting plate that can be inserted between any two adjacent layers of the counterweight blocks; The pallet can be inserted under several layers of the counterweight blocks, and can be driven by the driving assembly to lift each of the counterweight blocks to leave an integrated counterweight block of a predetermined weight on the sliding seat; and the power unit can drive the sliding seat to rise a predetermined distance so that the landing gear can touch the ground as the sliding seat falls.

2. The aircraft landing gear touchdown speed simulation system according to claim 1, characterized in that: The bearing part comprises a sliding frame which is slidably arranged on the frame, and the landing gear mounting part comprises a mounting plate which is fixedly arranged on the bottom end of the sliding frame.

3. The aircraft landing gear touchdown speed simulation system according to claim 2, characterized in that: The power unit is two first hydraulic cylinders fixed on the frame and disposed on both sides of the sliding frame. The sliding frame is provided with two support plates. The telescopic rods of the two first hydraulic cylinders can support the two support plates correspondingly.

4. The aircraft landing gear touchdown speed simulation system according to claim 3, characterized in that: The telescopic rods of the two first hydraulic cylinders are respectively equipped with weighing sensors.

5. The aircraft landing gear touchdown speed simulation system according to claim 1, characterized in that: The driving assembly includes a fixed seat, a lifting plate and a driving unit; the fixed seat is fixed on the frame, and a nut is fixed on the fixed seat, the lifting plate can be lifted on the fixed seat, and the driving unit includes a first motor and a ball screw, the first motor is arranged on the lifting plate, the ball screw is arranged on the lifting plate and can be driven to rotate by the first motor, and the ball screw is threadedly connected to the nut.

6. The aircraft landing gear touchdown speed simulation system according to claim 5, characterized in that: A plurality of supporting grooves are respectively provided on the bottom surface of each of the counterweight blocks, and each of the supporting grooves has an opening located on the side of the counterweight block; the lifting unit includes a plurality of rotary power output devices arranged on the lifting plate, and each of the supporting plates is respectively arranged on the output end of the rotary power output device, and each of the supporting plates can be driven by the rotary power output device to rotate from the opening and be inserted into the corresponding supporting groove, or to be removed from the supporting groove.

7. The aircraft landing gear touchdown speed simulation system according to claim 1, characterized in that: Two brake plates are fixedly arranged on the frame, and the two brake plates are arranged on two opposite sides of the sliding seat, and brakes capable of tightening or loosening the corresponding brake plates are respectively fixedly arranged on the two opposite sides of the sliding seat.

8. The aircraft landing gear touchdown speed simulation system according to claim 1, characterized in that: The bearing part is fixedly provided with a plurality of guide rods, and each of the counterweight blocks is provided with a guide through hole which is slidably mounted on each of the guide rods; the frame is fixedly provided with a plurality of guide rods, and the guide rods of the bearing part correspond to the guide rods of the frame one by one in the vertical direction; The support plate can be inserted under several layers of the counterweight blocks, and the support plate drives the counterweight blocks to move along the guide rods of the load-bearing portion. The counterweight blocks are separated from the guide rods of the load-bearing portion and move along the guide rods of the frame until they move to a predetermined position.

9. The aircraft landing gear touchdown speed simulation system according to any one of claims 1 to 8, characterized in that: The frame is provided with a plurality of second hydraulic cylinders, and the sliding seat is provided with a plurality of connecting plates. The telescopic end of each second hydraulic cylinder is connected to each connecting plate in a one-to-one correspondence, and each second hydraulic cylinder can apply downward pressure to the connecting plate.

10. A method for simulating the touchdown speed of an aircraft landing gear, characterized in that: The aircraft landing gear touchdown speed simulation system according to any one of claims 1 to 9 is applied, and comprises the following steps: Mounting the landing gear to be tested on the landing gear mounting portion of the sliding seat; After the telescopic rod of the first hydraulic cylinder pushes the sliding seat to rise to a predetermined height, the sliding seat is fixed, and a part of the counterweight is lifted by the lifting mechanism, so that a counterweight of a predetermined weight is left on the sliding seat; After the telescopic rod of the first hydraulic cylinder is retracted to the lowest end, the sliding seat is released, so that the landing gear falls with the sliding seat and touches the ground; After the landing gear touches the ground, each second hydraulic cylinder applies a predetermined pressure to the sliding seat.

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