Aircraft landing gear multi-attitude simulation system

Abstract

The invention provides an aircraft landing gear multi-attitude simulation system, and relates to the technical field of landing gear system verification equipment. The aircraft landing gear multi-attitude simulation system comprises a rack, a simulation mechanism and a roll actuating device. Wherein 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 an undercarriage mounting disc which is arranged on the mounting seat and is used for mounting the undercarriage system. The roll actuating device comprises two linear power output units, the two linear power output units are arranged on the two opposite sides of the sliding frame respectively, the fixed ends of the two linear power output units are hinged to the sliding frame, and the telescopic ends of the two linear power output units are hinged to the mounting base. The multi-attitude simulation system for the aircraft landing gear can better simulate the condition that the aircraft wheel touches the ground in a side-tipping and side-deviation state.

Description

Technical Field

[0001] The present invention relates to the technical field of landing gear system verification equipment, and in particular to a multi-attitude simulation system for aircraft landing gear. Background Art

[0002] The dynamic response of aircraft landing gear during approaching the runway, taxiing and braking 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 during approaching the runway, taxiing and braking. After the development of the aircraft landing gear system is completed, it is necessary to conduct pre-test simulations to verify whether the function of the landing gear meets the index requirements.

[0003] At present, when the landing gear system is tested and simulated, the landing gear system is fixedly installed on the basket assembly, and a simulated load is applied to the basket assembly by a load simulation cylinder, so as to test the landing gear system.

[0004] However, the above-mentioned simulation device cannot simulate a state in which the wheels of the landing gear system touch the ground in a tilted manner, that is, in a state in which the axes of the wheels are inclined relative to the horizontal plane. Summary of the invention

[0005] To this end, the present invention proposes an aircraft landing gear multi-attitude simulation system, which can better simulate the state of the wheels touching the ground in a tilting manner.

[0006] The technical solution of the present invention is as follows: An aircraft landing gear multi-attitude simulation system, comprising: frame; The simulation mechanism comprises a sliding frame movably mounted on the frame, a mounting seat pivotally mounted on the sliding frame, and a landing gear mounting plate mounted on the mounting seat and used for mounting a landing gear system; The roll actuation device includes two linear power output units, which are arranged on two opposite sides of the mounting seat, and 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.

[0007] Furthermore, it also includes a roll actuation device; the roll actuation device includes a power unit arranged on the mounting seat, and a transmission unit arranged between the output end of the power unit and the landing gear mounting plate; the output end of the power unit is driven by the transmission unit to drive the landing gear mounting plate to rotate on the mounting seat.

[0008] Furthermore, the power unit is a first motor arranged on the mounting seat, and the transmission unit includes a driving gear that can be driven to rotate by the first motor, and a driven gear fixedly mounted on the landing gear mounting plate, and the driving gear is meshed with the driven gear.

[0009] Furthermore, the mounting seat includes a top plate in the shape of a circular ring, an outer ring body connected to the outer edge of the top plate and extending downward, and an inner ring body connected to the inner edge of the top plate and extending 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 seat 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 helical gears respectively.

[0012] Furthermore, the driven gear and the landing gear mounting plate are integrally formed.

[0013] Furthermore, the sliding frame is provided with two connecting parts, and the two connecting parts respectively include two clamping plates arranged at an interval, and the two clamping plates are provided with opposite through holes; the mounting seat is provided with two connecting plates opposite to the two connecting parts, and the two connecting plates can be inserted between the corresponding two clamping plates, and the connecting plates are provided with through holes opposite to the through holes; pivot shafts are inserted in the through holes and the through holes, and the pivot shaft is fixedly inserted in the through holes and can rotate in the through holes.

[0014] Furthermore, the mounting seat 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 the present invention are: The aircraft landing gear multi-attitude simulation system provided by the present invention has a simulation mechanism and a roll actuating device arranged on a frame, and two linear power output units can drive the mounting seat to rotate around its pivot axis through the extension and retraction of their telescopic ends, thereby driving the landing gear system on the landing gear mounting plate to rotate, causing the wheel to roll; and the landing gear system can touch the ground as the sliding frame descends, completing the test simulation of the wheel touching the ground in a roll manner. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0018] Figure 1A three-dimensional diagram of an aircraft landing gear multi-attitude simulation system provided by an embodiment of the present invention; Figure 2 A three-dimensional diagram of a simulation mechanism provided by an embodiment of the present invention; Figure 3 for Figure 2 A partial enlarged view of the middle A; Figure 4 A three-dimensional diagram of a simulation mechanism provided by an embodiment of the present invention from another angle; Figure 5 A cross-sectional view of a pivot shaft mounting structure provided by 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 pivot shaft mounting structure provided by an embodiment of the present invention; Figure 8 A cross-sectional view of a rotation-stopping mechanism provided in an embodiment of the present invention; Fig. 9 A schematic diagram of the cooperation between the anti-rotation plate and the landing gear mounting plate provided in an embodiment of the present invention; In the figure: 100, frame; 110, guide rail; 200, simulation mechanism; 210, sliding frame; 211, slider; 212, connecting part; 213, clamping plate; 220, mounting seat; 222, top plate; 223, outer ring body; 224, inner ring body; 230, landing gear mounting plate; 231, connecting plate; 232, second anti-rotation surface; 240, pivot shaft; 201, guide hole; 202, threaded hole; 300, roll actuating device ; 310, linear power output unit; 400, support member; 410, base block; 411, first wedge surface; 420, support rod; 430, push plate; 431, push rod; 432, second wedge surface; 500, lateral actuation device; 510, power unit; 520, driving gear; 530, driven gear; 600, anti-rotation mechanism; 610, second motor; 620, shaft; 630, anti-rotation disk; 631, first anti-rotation surface. 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 multi-attitude simulation system, referring to Figure 1 and Figure 2As shown, it includes a frame 100, a simulation mechanism 200 and a roll actuating device 300. The simulation mechanism 200 includes a sliding frame 210 movably arranged on the frame 100, a mounting seat 220 pivoted on the sliding frame 210, and a landing gear mounting plate 230 arranged on the mounting seat 220 and used for mounting a landing gear system.

[0021] The roll actuation device 300 includes two linear power output units 310, which are arranged on two opposite sides of the mounting seat 220, and 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 seat 220.

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

[0023] For specific structure, refer to Figure 1 As shown, a plurality of guide rails 110 are provided on the frame 100, and a plurality of sliders 211 are provided on the sliding frame 210, which can slide on each guide rail 110, so that the sliding frame 210 can rise or fall relative to the frame 100. In addition, two first hydraulic cylinders are provided on the frame 100, which are disposed on two opposite sides of the sliding frame 210. The cylinder rods of the two first hydraulic cylinders can push the sliding frame 210 upward, so that the sliding frame 210 can rise to a predetermined height on the frame 100, thereby driving the landing gear system to descend from the predetermined height and touch the ground, simulating the touchdown state of the landing gear system.

[0024] In this embodiment, reference Figures 2 to 4 As shown, two connecting parts 212 are provided on the sliding frame 210, and the two connecting parts 212 respectively include two clamping plates 213 spaced apart on the bottom end surface of the sliding frame 210, and opposite through holes are provided on the two clamping plates 213. Corresponding to the two connecting parts 212, two connecting plates 231 are provided on the mounting seat 220, and the two connecting plates 231 are respectively provided with through holes. The two connecting plates 231 can be correspondingly inserted between the two clamping plates 213 of the corresponding connecting parts 212, and the through holes are opposite to the two through holes. The aforementioned pivot shaft 240 is fixedly inserted in the through holes on the connecting plates 231 and can rotate in the two through holes.

[0025] In this embodiment, a spline groove is provided on the inner wall of the through hole, and a spline matching therewith is provided on the outer periphery of the pivot shaft 240, so that the pivot shaft 240 can rotate with the connecting plate 231, that is, with the mounting seat 220, so as to determine the rotation angle of the mounting seat 220 by detecting the rotation angle of the pivot shaft 240, that is, to determine the roll angle of the wheel. In this embodiment, the diameter of the above-mentioned through hole is larger than the diameter of the through hole, and bearings are respectively installed between the pivot shaft 240 and the two through holes. When installing the pivot shaft 240, the through hole can be firstly placed opposite to the two through holes, and then the pivot shaft 240 can be inserted into the through hole, and then the bearings can be respectively installed between the pivot shaft 240 and the two through holes. It should be noted that the bearing is not shown in the drawings of this embodiment because it does not affect the understanding.

[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, and the guide holes 201 are evenly arranged and spaced around the inner wall of the through hole, and a support member 400 is provided in each guide hole 201. Each support member 400 includes a base block 410 and a support rod 420 rotatably arranged on the base block 410, and each support member 400 can slide along the radial direction of the through hole so that each support rod 420 supports or is separated from the pivot shaft 240. That is, in this embodiment, each support member 400 replaces the bearing installed between the pivot shaft 240 and the through hole.

[0027] In this embodiment, by providing each support member 400 instead of a bearing, the installation of the aircraft landing gear multi-attitude simulation system is more convenient. The reason is that compared with the solution of installing a bearing between the pivot shaft 240 and the through hole, when installing the bearing, since the bearing must be in interference connection with the pivot shaft 240 and the inner wall of the through hole, the installation of the bearing is more difficult. By providing each support member 400, it is easier to support the pivot shaft 240 by pushing each support member 400 to move along the radial direction of the through hole, and since the pivot shaft 240 does not need to rotate quickly, supporting the pivot shaft 240 by each support rod 420 can also meet the rotation requirement of the pivot shaft 240.

[0028] In this embodiment, reference Figures 5 to 7 As shown, the end surface of each base block 410 away from the support rod 420 is a first wedge surface 411. A push plate 430 is connected to the end surface of each clamping plate 213. A push rod 431 corresponding to each base block 410 is provided on the end surface of the push plate 430. A second wedge surface 432 that fits the first wedge surface 411 of the corresponding base block 410 is provided on each push rod 431. By providing the push plate 430, each support member 400 can be moved radially along the through hole by moving the push plate 430 along the axial direction of 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 surface of the clamping plate 213, and through holes corresponding to the threaded holes 202 are provided on the push plate 430, so that bolts can pass through the through holes and be screwed to the threaded holes 202 respectively; after the pivot shaft 240 is inserted into the through hole, the push plate 430 can be moved close to the clamping plate 213 by alternately rotating the bolts, so as to push the support members 400 to support the pivot shaft 240.

[0030] In this embodiment, a first permanent magnet is provided on the first wedge surface 411, and a second permanent magnet capable of being attracted to the first permanent magnet is provided on each second wedge surface 432, so that when the push plate 430 is moved away from the clamping plate 213, the support member 400 is still attached to the push rod 431 and away from the pivot shaft 240 through the attraction of the second permanent magnet and the first permanent magnet. The first permanent magnet and the second permanent magnet are not shown in the drawings of this embodiment because it does not affect understanding.

[0031] refer to Figure 2 and Figure 4 As shown, the linear power output unit 310 of this embodiment is a second hydraulic cylinder, the fixed end of the linear power output unit 310 is the cylinder barrel of the second hydraulic cylinder, and 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 ear seats are provided on the sliding frame 210, and two front ear seats are provided on the mounting seat 220, the cylinder barrel of the second hydraulic cylinder is hinged to the corresponding rear ear seats, and the cylinder rod of the second hydraulic cylinder is hinged to the corresponding front ear seats.

[0032] Through the two second hydraulic cylinders, the mounting seat 220 can be rotated around the pivot shaft 240 to a corresponding angle by extending the cylinder rods of the two second hydraulic cylinders to different lengths, thereby making the wheel have a corresponding roll angle.

[0033] In this embodiment, a second encoder is provided on the mounting seat 220, and the second encoder is used to detect the rotation angle of the pivot shaft 240. The roll angle of the wheel can be adjusted and determined according to the rotation angle of the pivot shaft 240, so that the wheel reaches the roll angle required for the test. It should be noted that the second encoder can adopt 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 yaw actuation device 500; the yaw actuation device 500 includes a power unit 510 arranged on the mounting seat 220, and a transmission unit arranged between the output end of the power unit 510 and the landing gear mounting plate 230; the output end of the power unit 510 is driven by the transmission unit to drive the landing gear mounting plate 230 to rotate on the mounting seat 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 also rotate accordingly, causing the wheels on the landing gear system to deflect. This allows the aircraft landing gear multi-attitude simulation system of this embodiment to simulate the situation where the wheels touch the ground in a deflected manner. Wherein, the deflection of the wheels refers to the axis of the wheels not being perpendicular to the flight direction of the aircraft.

[0036] refer to Figure 2 and Figure 4 As shown, the power unit 510 of this embodiment is a motor arranged on the mounting seat 220, which is called the first motor in this embodiment, and the transmission unit includes a driving 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, and the driving gear 520 is meshed with the driven gear 530. That is, in this embodiment, the first motor drives the driving gear 520 to rotate, and the driving gear 520 drives the driven gear 530 to rotate, thereby driving the landing gear mounting plate 230 to rotate, so that the wheel deflects.

[0037] In this embodiment, the driving gear 520 and the driven gear 530 are both 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 a sprocket, or a synchronous belt and a synchronous wheel, which have the same principle and are not 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 and the landing gear mounting plate 230 can also be independently formed, and the driven gear 530 is fixedly sleeved on the landing gear mounting plate 230.

[0039] refer to Figure 2 and Figure 4 As shown, the mounting seat 220 of this embodiment includes a top plate 222 in the shape of a circular ring, an outer ring body 223 connected to the outer side of the top plate 222 and extending downward, and an inner ring body 224 connected to the inner side of the top plate 222 and extending downward, and a support bearing is sleeved on the inner ring body 224. The aforementioned landing gear mounting plate 230 is annular and sleeved on 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, a rotation-stopping mechanism for limiting the rotation of the landing gear mounting plate 230 is further provided on the mounting seat 220 to prevent the landing gear mounting plate 230 from unexpectedly rotating when the wheel touches the ground. Specifically, when the wheel touches the ground in a tilted and sideways state, the landing gear mounting plate 230 will be subjected to a reaction force that causes it to rotate, and when the reaction force exceeds the bearing capacity of the motor shaft of the first motor, the landing gear mounting plate 230 will cause unexpected rotation.

[0041] In this embodiment, there are two anti-rotation mechanisms provided on the mounting seat 220, and the 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. Figure 8 and Fig. 9 As shown, the first anti-rotation mechanism 600 of this embodiment includes a second motor 610, a shaft 620 and an anti-rotation disk 630; wherein, the second motor 610 is arranged on the top plate 222, the shaft 620 is arranged on the mounting seat 220 and can be driven to rotate by the second motor 610, and the anti-rotation disk 630 is fixedly sleeved on the shaft 620.

[0042] A first anti-rotation surface 631 is provided on the outer circumference of the anti-rotation disk 630. Fig. 9 In the clockwise direction, the distance between the first anti-rotation surface 631 and the axis of the shaft body 620 gradually increases. A second anti-rotation surface 232 is provided on the inner wall of the landing gear mounting plate 230. Fig. 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 the landing gear mounting plate 230 needs to be rotated, the second motor 610 can drive the anti-rotation plate 630 to rotate so that the first anti-rotation surface 631 is separated from the second anti-rotation surface 232; after the landing gear mounting plate 230 is rotated into place, the second motor 610 can drive the anti-rotation plate 630 to rotate so that the first anti-rotation surface 631 is abutted against the second anti-rotation surface 232. At this time, due to the support of the shaft body 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 plate 230 has a tendency to rotate counterclockwise to reduce the distance between the second anti-rotation surface 232 and the shaft body 620, the supporting distance of the first anti-rotation surface 631 to the second anti-rotation surface 232 remains unchanged, thereby limiting the counterclockwise rotation of the landing gear mounting plate 230; in other words, the landing gear mounting plate 230 can rotate counterclockwise only after the shaft body 620 bends, therefore, the first anti-rotation mechanism 600 can provide sufficient resistance for the counterclockwise rotation of the landing gear mounting plate 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 seat 220. The 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, that is, the side slip angle of the wheel, according to the rotation angle of the motor shaft of the first motor. It should be noted that the first encoder can adopt 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 of this embodiment is: raising the sliding frame 210 on the frame 100 to a predetermined angle; adjusting the wheels to the required roll angle and yaw angle; and allowing the wheels to fall freely with the sliding frame 210 and touch the ground to simulate the touchdown state of the landing gear system.

[0047] 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 multi-attitude simulation system, characterized in that: include: Rack(100); The simulation mechanism (200) comprises a sliding frame (210) which is liftably arranged on the frame (100), a mounting seat (220) pivoted on the sliding frame (210), and a landing gear mounting plate (230) which is arranged on the mounting seat (220) and is used to mount a landing gear system; The roll actuation device (300) comprises two linear power output units (310), the two linear power output units (310) being arranged at two opposite sides of the mounting seat (220), and the fixed ends of the two linear power output units (310) being respectively hinged to the sliding frame (210), and the telescopic ends of the two linear power output units (310) being respectively hinged to the mounting seat (220).

2. The aircraft landing gear multi-attitude simulation system according to claim 1, characterized in that: It also includes a yaw actuation device (500); the yaw actuation device (500) includes a power unit (510) disposed on the mounting seat (220), and a transmission unit disposed between an output end of the power unit (510) and the landing gear mounting plate (230); the output end of the power unit (510) is driven by the transmission unit to drive the landing gear mounting plate (230) to rotate on the mounting seat (220).

3. The aircraft landing gear multi-attitude simulation system according to claim 2, characterized in that: The power unit (510) is a motor disposed on the mounting seat (220); the transmission unit comprises a driving gear (520) that can be driven to rotate by the motor, and a driven gear (530) fixedly sleeved on the landing gear mounting plate (230); the driving gear (520) meshes with the driven gear (530).

4. The aircraft landing gear multi-attitude simulation system according to claim 3, characterized in that: The mounting seat (220) comprises a top plate (222) in the shape of a circular ring, an outer ring body (223) connected to the outer side edge of the top plate (222) and extending downward, and an inner ring body (224) connected to the inner side edge of the top plate (222) and extending downward, wherein a support bearing is sleeved on the inner ring body (224), and the landing gear mounting plate (230) is annular and sleeved on the support bearing.

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

6. The aircraft landing gear multi-attitude simulation system according to claim 3, characterized in that: The driving gear (520) and the driven gear (530) are respectively helical gears.

7. The aircraft landing gear multi-attitude simulation system according to claim 3, characterized in that: The driven gear (530) and the landing gear mounting plate (230) are integrally formed.

8. The aircraft landing gear multi-attitude simulation system according to any one of claims 1 to 7, characterized in that: The sliding frame (210) is provided with two connecting parts (212), the two connecting parts (212) respectively include two spaced-apart clamping plates (213), and the two clamping plates (213) are provided with opposite through holes; the mounting seat (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), and the connecting plates (231) are provided with through holes opposite to the through holes; the through holes and the through holes are inserted with pivot shafts (240), and the pivot shaft (240) is fixedly inserted in the through holes and can rotate in the through holes.

9. The aircraft landing gear multi-attitude simulation system according to claim 8, characterized in that: The mounting seat (220) is also provided with a second encoder for detecting the rotation angle of the pivot shaft (240).

10. 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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