Multi-attitude simulation system for aircraft landing gear

Abstract

The application provides an airplane landing gear multi-posture simulation system, and relates to the technical field of landing gear system verification equipment; the airplane landing gear multi-posture simulation system comprises a rack, a simulation mechanism and a roll actuating device. The simulation mechanism comprises a sliding frame which is arranged on the rack in a liftable manner, a mounting seat which is pivoted on the sliding frame, and a landing gear mounting disc which is arranged on the mounting seat and used for mounting a landing gear system. The roll actuating device comprises two linear power output units which are arranged on two opposite sides of the sliding frame, the fixed ends of the two linear power output units are respectively hinged to the sliding frame, and the telescopic ends of the two linear power output units are respectively hinged to the mounting seat. The airplane landing gear multi-posture simulation system can better simulate the condition that the wheels touch the ground in a roll and a side slip state.

Description

Technical Field

[0001] This invention relates to the field of landing gear system verification equipment technology, specifically to an aircraft landing gear multi-attitude simulation system. Background Technology

[0002] The dynamic response of aircraft landing gear during runway approach, taxiing, and braking is one of the important topics in aircraft landing gear dynamics research. It mainly studies the dynamic characteristics of landing gear structure during runway approach, taxiing, and braking. After the aircraft landing gear system is developed, it needs to be tested and simulated in advance to verify whether the landing gear function meets the requirements.

[0003] Currently, during landing gear system testing and simulation, the landing gear system is fixedly mounted on the basket assembly, and a load simulation cylinder applies simulated loads to the basket assembly to conduct experiments on the landing gear system.

[0004] However, the aforementioned simulation equipment cannot simulate the landing gear system's wheels touching the ground in a tilted manner, that is, when the wheel's axis is tilted relative to the horizontal plane. Summary of the Invention

[0005] Therefore, this invention proposes an aircraft landing gear multi-attitude simulation system to better simulate the state of the aircraft wheels touching the ground in a tilted manner.

[0006] The technical solution of the present invention is as follows: An aircraft landing gear multi-attitude simulation system includes: frame; The simulation mechanism includes a sliding frame that is vertically mounted on the frame, a mounting base that is pivotally mounted on the sliding frame, and a landing gear mounting plate that is mounted on the mounting base and is used to mount the landing gear system. The tilting actuation device includes two linear power output units, which are respectively disposed on two opposite sides of the mounting base. The fixed ends of the two linear power output units are respectively hinged to the sliding frame, and the telescopic ends of the two linear power output units are respectively hinged to the mounting base.

[0007] Furthermore, it also includes a lateral deflection actuation device; the lateral deflection actuation device includes a power unit disposed on the mounting base, and a transmission unit disposed between the output end of the power unit and the landing gear mounting plate; driven by the transmission unit, the output end of the power unit can drive the landing gear mounting plate to rotate on the mounting base.

[0008] Furthermore, the power unit is a first motor mounted on the mounting base, and the transmission unit includes a drive gear that can be driven to rotate by the first motor, and a driven gear fixedly mounted on the landing gear mounting plate, wherein the drive gear meshes with the driven gear.

[0009] Furthermore, the mounting base includes an annular top plate, an outer ring body that connects to the outer side of the top plate and extends downward, and an inner ring body that connects to the inner side of the top plate and extends downward. A support bearing is sleeved on the inner ring body, and the landing gear mounting plate is annular and sleeved on the support bearing.

[0010] Furthermore, the mounting base is also provided with a first encoder for detecting the rotation angle of the first motor shaft.

[0011] Furthermore, the driving gear and the driven gear are both helical gears.

[0012] Furthermore, the driven gear is integrally formed with the landing gear mounting plate.

[0013] Furthermore, the sliding frame is provided with two connecting parts, each of which includes two spaced-apart clamps, and the two clamps are provided with opposing through holes; the mounting base is provided with two connecting plates opposite to the two connecting parts, and the two connecting plates can be inserted between the corresponding two clamps, and the connecting plates are provided with through holes opposite to the through holes; a pivot shaft is inserted into the through hole and the through hole, and the pivot shaft is fixedly inserted into the through hole and can rotate within the through hole.

[0014] Furthermore, the mounting base is also provided with a second encoder for detecting the rotation angle of the pivot shaft.

[0015] Furthermore, the linear power output unit is a hydraulic cylinder.

[0016] The working principle and beneficial effects of this invention are as follows: The multi-attitude simulation system for aircraft landing gear provided by the present invention, by setting a simulation mechanism and a tilting actuation device on the frame, allows two linear power output units to drive the mounting base to rotate around its pivot axis through the extension and retraction of its telescopic ends, thereby driving the landing gear system on the landing gear mounting plate to rotate and causing the wheels to tilt; and the landing gear system can touch the ground as the sliding frame descends, completing the test simulation of the wheels touching the ground in a tilting manner. Attached Figure Description

[0017] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments.

[0018] Figure 1A perspective view of an aircraft landing gear multi-attitude simulation system provided in an embodiment of the present invention; Figure 2 A perspective view of the simulation mechanism provided in an embodiment of the present invention; Figure 3 for Figure 2 A magnified view of a section at point A in the middle; Figure 4 A perspective view of the simulation mechanism provided in an embodiment of the present invention from another angle; Figure 5 This is a cross-sectional view of the pivot shaft mounting structure provided in an embodiment of the present invention; Figure 6 for Figure 5 A magnified view of a section at point B in the middle; Figure 7 An exploded view of the pivot shaft mounting structure provided in an embodiment of the present invention; Figure 8 A cross-sectional view of the anti-rotation mechanism provided in an embodiment of the present invention; Figure 9 This is a schematic diagram illustrating the cooperation between the anti-spinning disc and the landing gear mounting plate according to an embodiment of the present invention; In the diagram: 100, frame; 110, guide rail; 200, simulation mechanism; 210, sliding frame; 211, slider; 212, connecting part; 213, clamping plate; 220, mounting base; 222, top plate; 223, outer ring; 224, inner ring; 230, landing gear mounting plate; 231, connecting plate; 232, second anti-rotation surface; 240, pivot shaft; 201, guide hole; 202, threaded hole; 300, tilting actuation device. 310, Linear power output unit; 400, Support component; 410, Base block; 411, First wedge surface; 420, Support rod; 430, Push plate; 431, Push rod; 432, Second wedge surface; 500, Lateral deflection actuation device; 510, Power unit; 520, Drive gear; 530, Driven gear; 600, Anti-rotation mechanism; 610, Second motor; 620, Shaft; 630, Anti-rotation disc; 631, First anti-rotation surface. Detailed Implementation

[0019] The technical solutions of the present invention will be clearly and completely described below with reference to the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0020] This embodiment provides an aircraft landing gear multi-attitude simulation system, referencing... Figure 1 and Figure 2As shown, it includes a frame 100, a simulation mechanism 200, and a tilting actuation device 300. The simulation mechanism 200 includes a sliding frame 210 that is elliptically mounted on the frame 100, a mounting base 220 pivotally mounted on the sliding frame 210, and a landing gear mounting plate 230 mounted on the mounting base 220 for mounting the landing gear system.

[0021] The tilting actuation device 300 includes two linear power output units 310, which are respectively disposed on two opposite sides of the mounting base 220. The fixed ends of the two linear power output units 310 are respectively hinged to the sliding frame 210, and the telescopic ends of the two linear power output units 310 are respectively hinged to the mounting base 220.

[0022] Based on the above structure, in the aircraft landing gear multi-attitude simulation system of this embodiment, by adjusting the extension length of the telescopic ends of the two linear power output units 310, the mounting base 220 can rotate around its pivot axis 240. The landing gear system mounted on the landing gear mounting plate 230 will also rotate with the mounting base 220, causing the landing gear system's wheels to roll. Here, wheel roll refers to the wheel axis not being parallel to the horizontal plane.

[0023] In terms of specific structure, refer to Figure 1 As shown, the frame 100 is provided with several guide rails 110, and the sliding frame 210 is provided with several sliders 211 that can slide on each guide rail 110, so that the sliding frame 210 can rise or fall relative to the frame 100. Furthermore, the frame 100 is provided with two first hydraulic cylinders located on opposite sides of the sliding frame 210. The cylinder rods of the two first hydraulic cylinders can push the sliding frame 210 upwards, so that the sliding frame 210 can rise to a predetermined height on the frame 100, thereby causing the landing gear system to descend from that predetermined height and touch the ground, simulating the ground contact state of the landing gear system.

[0024] In this embodiment, reference Figures 2 to 4 As shown, the sliding frame 210 has two connecting portions 212, and each connecting portion 212 includes two clamping plates 213 spaced apart on the bottom end surface of the sliding frame 210. The clamping plates 213 have opposing through holes. Corresponding to the two connecting portions 212, the mounting base 220 has two connecting plates 231, each with a through hole. The two connecting plates 231 can be inserted into the two clamping plates 213 of the corresponding connecting portions 212, with the through holes opposite to the two through holes. The aforementioned pivot shaft 240 is fixedly inserted into the through hole on the connecting plate 231 and can rotate within the two through holes.

[0025] In this embodiment, a spline groove is provided on the inner wall of the through hole, and a matching spline is provided on the outer periphery of the pivot shaft 240, allowing the pivot shaft 240 to rotate with the connecting plate 231, i.e., with the mounting base 220. This facilitates determining the rotation angle of the mounting base 220, i.e., the tilt angle of the wheel, by detecting the rotation angle of the pivot shaft 240. In this embodiment, the diameter of the aforementioned through hole is larger than the diameter of the through hole, and bearings are installed between the pivot shaft 240 and the two through holes respectively. When installing the pivot shaft 240, the through hole can be aligned with the two through holes first, then the pivot shaft 240 can be inserted into the through hole, and then the bearings can be installed between the pivot shaft 240 and the two through holes respectively. It should be noted that, for the sake of clarity, the bearings are not shown in the accompanying drawings of this embodiment.

[0026] In some embodiments, reference Figures 5 to 7 As shown, a plurality of guide holes 201 are provided on the inner wall of the through hole. Each guide hole 201 is circumferentially uniform and spaced apart from the inner wall of the through hole. A support member 400 is provided within each guide hole 201. Each support member 400 includes a base block 410 and a support rod 420 rotatably mounted on the base block 410. Each support member 400 can slide radially along the through hole, allowing the support rod 420 to support or disengage from the pivot shaft 240. In this embodiment, the support member 400 replaces the bearings installed between the pivot shaft 240 and the through hole.

[0027] In this embodiment, the installation of the aircraft landing gear multi-attitude simulation system is facilitated by using support members 400 instead of bearings. This is because, compared to installing bearings between the pivot shaft 240 and the through hole, installing bearings is more difficult because the bearings need to be interference-fitted with both the pivot shaft 240 and the inner wall of the through hole. However, by using support members 400, the support rods 420 can easily support the pivot shaft 240 by pushing the support members 400 radially along the through hole. Since the pivot shaft 240 does not need to rotate rapidly, supporting it with the support rods 420 also meets the rotation requirements of the pivot shaft 240.

[0028] In this embodiment, reference Figures 5 to 7 As shown, the end face of each base block 410 away from the support rod 420 is a first wedge-shaped surface 411. A push plate 430 is connected to the end face of each clamping plate 213. A push rod 431 corresponding to each base block 410 is provided on the end face of the push plate 430. Each push rod 431 has a second wedge-shaped surface 432 that fits against the first wedge-shaped surface 411 of the corresponding base block 410. By providing this push plate 430, each support member 400 can be moved radially along the through hole by moving the push plate 430 axially along the through hole.

[0029] refer to Figures 5 to 7As shown, in this embodiment, a plurality of threaded holes 202 are provided on the end face of the clamping plate 213, and a through hole is provided on the push plate 430 corresponding to each threaded hole 202, so that bolts can pass through the through holes and be screwed into the threaded holes 202 respectively; after the pivot shaft 240 is inserted into the through hole, the push plate 430 can be moved closer to the clamping plate 213 by alternately rotating each bolt, so as to push each support member 400 to support the pivot shaft 240.

[0030] In this embodiment, a first permanent magnet is provided on the first wedge-shaped surface 411, and a second permanent magnet capable of attracting the first permanent magnet is provided on each of the second wedge-shaped surfaces 432. This allows the support member 400 to remain attached to the push rod 431 and move away from the pivot axis 240 when the push plate 430 is moved away from the clamping plate 213, through the attraction between the second and first permanent magnets. For ease of understanding, the first and second permanent magnets are not shown in the accompanying drawings of this embodiment.

[0031] refer to Figure 2 and Figure 4 As shown, in this embodiment, the linear power output unit 310 is a second hydraulic cylinder. The fixed end of the aforementioned linear power output unit 310 is the cylinder barrel of the second hydraulic cylinder, while the telescopic end of the linear power output unit 310 is the cylinder rod of the second hydraulic cylinder. Corresponding to the two linear power output units 310, two rear lugs are provided on the sliding frame 210, and two front lugs are provided on the mounting base 220. The cylinder barrel of the second hydraulic cylinder is hinged to the corresponding rear lug, and the cylinder rod of the second hydraulic cylinder is hinged to the corresponding front lug.

[0032] By extending the cylinder rods of the two second hydraulic cylinders by different lengths, the mounting base 220 can be rotated around the pivot shaft 240 by a corresponding angle, thereby giving the machine wheel a corresponding tilt angle.

[0033] In this embodiment, a second encoder is provided on the mounting base 220. This second encoder is used to detect the rotation angle of the pivot shaft 240. The tilt angle of the machine wheel can be adjusted and determined according to the rotation angle of the pivot shaft 240 so that the machine wheel reaches the tilt angle required for testing. It should be noted that the second encoder can be an existing product, and its structure and working principle will not be described in detail here.

[0034] refer to Figure 2 and Figure 4 As shown, the aircraft landing gear multi-attitude simulation system of this embodiment also includes a lateral deflection actuation device 500; the lateral deflection actuation device 500 includes a power unit 510 disposed on the mounting base 220, and a transmission unit disposed between the output end of the power unit 510 and the landing gear mounting plate 230; driven by the transmission unit, the output end of the power unit 510 can drive the landing gear mounting plate 230 to rotate on the mounting base 220.

[0035] Based on the above structure, in the aircraft landing gear multi-attitude simulation system of this embodiment, the power unit 510 can drive the landing gear mounting plate 230 to rotate around its own axis through the transmission unit, and the wheels on the landing gear system will also rotate accordingly, causing the wheels on the landing gear system to deflect laterally. This allows the aircraft landing gear multi-attitude simulation system of this embodiment to also simulate the situation where the wheels touch the ground in a lateral manner. Lateral wheel deflection refers to the wheel's axis not being perpendicular to the aircraft's flight direction.

[0036] refer to Figure 2 and Figure 4 As shown, the power unit 510 in this embodiment is a motor mounted on the mounting base 220, referred to as the first motor in this embodiment. The transmission unit includes a drive gear 520 that can be driven to rotate by the first motor, and a driven gear 530 fixedly sleeved on the landing gear mounting plate 230. The drive gear 520 and the driven gear 530 mesh. That is, in this embodiment, the first motor drives the drive gear 520 to rotate, and the drive gear 520 drives the driven gear 530 to rotate, thereby driving the landing gear mounting plate 230 to rotate, causing the wheels to deflect laterally.

[0037] In this embodiment, both the driving gear 520 and the driven gear 530 are helical gears; in some embodiments, the driving gear 520 and the driven gear 530 may also be spur gears. In some embodiments, the transmission unit may also include a chain and sprockets, or a timing belt and timing pulleys, which have the same principle and will not be described in detail here.

[0038] In this embodiment, the driven gear 530 is integrally formed with the landing gear mounting plate 230. In some embodiments, the driven gear 530 may also be formed independently from the landing gear mounting plate 230, and the driven gear 530 may be fixedly sleeved on the landing gear mounting plate 230.

[0039] refer to Figure 2 and Figure 4 As shown, the mounting base 220 in this embodiment includes an annular top plate 222, an outer ring 223 that connects to the outer side of the top plate 222 and extends downward, and an inner ring 224 that connects to the inner side of the top plate 222 and extends downward. A support bearing is fitted onto the inner ring 224. The aforementioned landing gear mounting plate 230 is annular and fitted onto the support bearing. By providing the aforementioned support bearing, it is convenient for the first motor to drive the landing gear mounting plate 230 to rotate.

[0040] In some embodiments, the mounting base 220 is further provided with an anti-rotation mechanism to limit the rotation of the landing gear mounting disc 230, so as to prevent the landing gear mounting disc 230 from rotating unexpectedly when the wheels touch the ground. Specifically, when the wheels touch the ground in a tilted and lateral state, the landing gear mounting disc 230 will be subjected to a reaction force that causes it to rotate. When this reaction force exceeds the load-bearing capacity of the motor shaft of the first motor, it will cause the landing gear mounting disc 230 to rotate unexpectedly.

[0041] In this embodiment, there are two anti-rotation mechanisms mounted on the mounting base 220. These two anti-rotation mechanisms are used to limit the bidirectional rotation of the landing gear mounting plate 230. For ease of understanding, this embodiment refers to them as the first anti-rotation mechanism 600 and the second anti-rotation mechanism. (See reference...) Figure 8 and Figure 9 As shown, the first anti-rotation mechanism 600 of this embodiment includes a second motor 610, a shaft 620 and an anti-rotation disc 630; wherein, the second motor 610 is disposed on the top plate 222, the shaft 620 is disposed on the mounting base 220 and can be driven to rotate by the second motor 610, and the anti-rotation disc 630 is fixedly sleeved on the shaft 620.

[0042] Among them, a first anti-rotation surface 631 is provided on the outer periphery of the anti-rotation disk 630, along... Figure 9 In a clockwise direction, the distance between the first anti-rotation surface 631 and the axis of the shaft 620 gradually increases. A second anti-rotation surface 232 is provided on the inner wall of the landing gear mounting plate 230, along... Figure 9 In the clockwise direction, the distance between the second anti-rotation surface 232 and its axis gradually decreases.

[0043] Based on the above structure, when it is necessary to rotate the landing gear mounting plate 230, the second motor 610 can drive the anti-rotation plate 630 to rotate, so that the first anti-rotation surface 631 disengages from the second anti-rotation surface 232; after the landing gear mounting plate 230 is rotated into position, the second motor 610 can drive the anti-rotation plate 630 to rotate, so that the first anti-rotation surface 631 abuts against the second anti-rotation surface 232. At this time, due to the support of the shaft 620 on the anti-rotation plate 630, the landing gear mounting plate 230 can be prevented from rotating counterclockwise. Specifically, when the landing gear mounting disc 230 tends to rotate counterclockwise to reduce the distance between the second anti-rotation surface 232 and the shaft 620, the support distance of the first anti-rotation surface 631 to the second anti-rotation surface 232 remains unchanged, thus restricting the rotation of the landing gear mounting disc 230 in the counterclockwise direction; or, the landing gear mounting disc 230 can only rotate counterclockwise after the shaft 620 bends. Therefore, the first anti-rotation mechanism 600 can provide sufficient resistance to the counterclockwise rotation of the landing gear mounting disc 230.

[0044] The second anti-rotation mechanism is used to limit the clockwise rotation of the landing gear mounting plate 230. It has the same working principle as the first anti-rotation mechanism 600, and will not be described in detail here.

[0045] In this embodiment, a first encoder for detecting the rotation angle of the motor shaft of the first motor is also provided on the mounting base 220. This first encoder is used to detect the rotation angle of the motor shaft of the first motor and can calculate the rotation angle of the landing gear mounting plate 230, i.e., the lateral deflection angle of the wheels, based on the rotation angle of the motor shaft. It should be noted that this first encoder can be an existing product, and its structure and working principle will not be described in detail here.

[0046] Based on the above structure, the working process of the aircraft landing gear multi-attitude simulation system in this embodiment is as follows: the sliding frame 210 is raised to a predetermined height on the frame 100; the wheels are adjusted to the required roll angle and deflection angle; the wheels are allowed to fall freely with the sliding frame 210 and touch the ground to simulate the ground contact state of the landing gear system.

[0047] The above are merely 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 within the protection scope of the present invention.

Claims

1. A multi-attitude simulation system for aircraft landing gear, characterized in that, include: Rack (100); The simulation mechanism (200) includes a sliding frame (210) that is vertically mounted on the frame (100), a mounting base (220) that is pivotally mounted on the sliding frame (210), and a landing gear mounting plate (230) that is mounted on the mounting base (220) and used for mounting the landing gear system. The tilting actuation device (300) includes two linear power output units (310), which are respectively disposed on two opposite sides of the mounting base (220). The fixed ends of the two linear power output units (310) are respectively hinged to the sliding frame (210), and the telescopic ends of the two linear power output units (310) are respectively hinged to the mounting base (220). It also includes a lateral deflection actuator (500); the lateral deflection actuator (500) includes a power unit (510) disposed on the mounting base (220), and a transmission unit disposed between the output end of the power unit (510) and the landing gear mounting plate (230); driven by the transmission unit, the output end of the power unit (510) can drive the landing gear mounting plate (230) to rotate on the mounting base (220); The mounting base (220) includes an annular top plate (222), an outer ring (223) that connects to the outer side of the top plate (222) and extends downward, and an inner ring (224) that connects to the inner side of the top plate (222) and extends downward. A support bearing is fitted on the inner ring (224), and the landing gear mounting plate (230) is annular and fitted on the support bearing.

2. The aircraft landing gear multi-attitude simulation system according to claim 1, characterized in that, The power unit (510) is a first motor mounted on the mounting base (220). The transmission unit includes a drive gear (520) that can be driven to rotate by the first motor, and a driven gear (530) fixedly mounted on the landing gear mounting plate (230). The drive gear (520) meshes with the driven gear (530).

3. The aircraft landing gear multi-attitude simulation system according to claim 2, characterized in that, The mounting base (220) is also provided with a first encoder for detecting the rotation angle of the motor shaft of the first motor.

4. The aircraft landing gear multi-attitude simulation system according to claim 2, characterized in that, The driving gear (520) and the driven gear (530) are helical gears.

5. The aircraft landing gear multi-attitude simulation system according to claim 2, characterized in that, The driven gear (530) is integrally formed with the landing gear mounting plate (230).

6. The aircraft landing gear multi-attitude simulation system according to any one of claims 1 to 5, characterized in that, The sliding frame (210) is provided with two connecting parts (212), each of the two connecting parts (212) includes two spaced clamping plates (213), and the two clamping plates (213) are provided with opposing through holes; the mounting base (220) is provided with two connecting plates (231) opposite to the two connecting parts (212), the two connecting plates (231) can be inserted between the corresponding two clamping plates (213), the connecting plates (231) are provided with through holes opposite to the through holes; a pivot shaft (240) is inserted into the through hole and the through hole, and the pivot shaft (240) is fixedly inserted into the through hole and can rotate in the through hole.

7. The aircraft landing gear multi-attitude simulation system according to claim 6, characterized in that, The mounting base (220) is also provided with a second encoder for detecting the rotation angle of the pivot shaft (240).

8. The aircraft landing gear multi-attitude simulation system according to claim 1, characterized in that, The linear power output unit (310) is a hydraulic cylinder.

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