A device for testing the function of aircraft landing gear

Abstract

The invention discloses a device for testing the landing gear of an aircraft, comprising a frame, a fixing frame being provided at the upper end of the frame, an oil cylinder being provided on the fixing frame, a fixing support plate being provided at one side of the fixing frame, a fixing hook being provided on the frame at the lower end of the fixing support plate, a servo motor being provided at the bottom of the frame, and a reducer being provided at the output end of the servo motor; the device of the design is easy to operate, effectively improves work efficiency, and improves safe production.

Description

Technical Field

[0001] The present invention relates to the technical field of landing gear equipment, and in particular to a device for testing the function of an aircraft landing gear. Background Art

[0002] The landing gear is an accessory device at the bottom of the aircraft that is used to support the aircraft during takeoff, landing or ground (or water) taxiing and is used for moving on the ground (or water). The landing gear is the only component that supports the entire aircraft, so it is an integral part of the aircraft; without it, the aircraft cannot move on the ground. Since the aircraft flies very fast, the landing gear needs to be retracted during the flight. Today's landing gear retraction and extension systems all use hydraulics as the main power. The hydraulic retraction and extension system has a relatively complex structure and is not suitable for small aircraft. Therefore, a landing gear with a simple structure is required. During the production process of aircraft landing gear, the landing gear needs to be tested for drop shock impact strength.

[0003] The existing landing gear has certain drawbacks when in use. The existing landing gear is subjected to high-speed impact force at the moment of landing, which will cause the landing gear to produce a large range of elastic impact displacement and vibration of several hundred millimeters. In addition to the linear sliding displacement along the main axis of the landing gear, the buffer installed on the landing gear will also produce strong lateral shaking and elastic rotation displacement. The test environment is harsh, which is not convenient for users to conduct tests, and thus inconvenient, which brings certain impacts during use. Therefore, those skilled in the art provide a device with aircraft landing gear test function to solve the problems raised in the above background technology. Summary of the invention

[0004] The object of the present invention is to provide a device for testing the function of an aircraft landing gear, so as to solve the problems raised in the above background technology.

[0005] To achieve the above-mentioned purpose, the present invention provides the following technical solution: a device for testing the function of an aircraft landing gear, comprising a frame, a fixing frame is provided at the upper end of the frame, a cylinder is provided on the fixing frame, a fixed support plate is provided on one side of the fixing frame, a fixing hook is provided on the frame at the lower end of the fixed support plate, a servo motor is provided at the bottom of the frame, and a reducer is provided at the output end of the servo motor.

[0006] Preferably, a support sleeve is provided at the lower end of the oil cylinder.

[0007] Preferably, a shift fork mounting plate is provided at the upper end of the reducer, a shift fork is provided on the shift fork mounting plate, and a center sleeve is provided in the middle of the shift fork mounting plate.

[0008] Preferably, a torque sensor is provided at the output end of the reducer.

[0009] Preferably, a support protective sleeve is provided at the bottom of the frame on one side of the reducer, and a pull ring is provided on one side of the support protective sleeve.

[0010] The working process of a device for testing the function of an aircraft landing gear. The device has four working stages:

[0011] The first stage is to use a pressure-pressing vehicle to lift the landing gear to the highest position, and then use the oil cylinder to press the landing gear down for 67-70mm and stop, keeping the pressure unchanged; then use the pressure-pressing vehicle to press the landing gear to 380Bar and stop, and use the oil cylinder to keep pressing for 15 minutes without releasing pressure. This stage is used to detect whether there is oil leakage in the landing gear;

[0012] In the second stage, the gear is lowered by 100mm per minute during the 400mm stroke and by 3mm per minute during the 30mm stroke. During the lowering process, the waste oil in the landing gear is discharged through the diverter valve.

[0013] In the third stage, the device can be used as a three-point fixed suspension landing gear. The landing gear at the bottom of the device can be rotated 0-10° clockwise / counterclockwise under force. The maximum torque when tightened to 10° does not exceed 1050N, and then the rebound force is released and is not greater than 335N. During this whole process, the torque value and the landing gear rebound time can be displayed;

[0014] In the fourth stage, the landing gear is driven by the reducer and can rotate 58-62 degrees clockwise / counterclockwise starting from 0 degrees, and there is no resistance during rebound.

[0015] Beneficial effects: Compared with the prior art, the beneficial effects of the present invention are: the equipment designed is easy to operate, effectively improves work efficiency and improves production safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 This is a structural schematic diagram of a device for testing the aircraft landing gear function proposed by the present invention.

[0017] In the attached drawings: frame 1; fixed frame 2; oil cylinder 3; fixed support plate 4; fixed hook 5; servo motor 6; reducer 7; support sleeve 8; fork mounting plate 9; fork 10; center sleeve 11; torsion sensor 12; support protection sleeve 13; pull ring 14. DETAILED DESCRIPTION

[0018] The technical solution of this patent is further described in detail below in conjunction with specific implementation methods.

[0019] Example

[0020] Please refer to the drawings in the specification. In an embodiment of the present invention, a device for testing the landing gear function of an aircraft includes a frame 1, a fixing frame 2 is provided at the upper end of the frame 1, a cylinder 3 is provided on the fixing frame 2, a fixing support plate 4 is provided on one side of the fixing frame 2, a fixing hook 5 is provided on the frame 1 at the lower end of the fixing support plate 4, a servo motor 6 is provided at the bottom of the frame 1, and a reducer 7 is provided at the output end of the servo motor 6.

[0021] Furthermore, a support sleeve 8 is provided at the lower end of the oil cylinder 3 .

[0022] Furthermore, a shift fork mounting plate 9 is provided at the upper end of the reducer 7 , a shift fork 10 is provided on the shift fork mounting plate 9 , and a center sleeve 11 is provided in the middle of the shift fork mounting plate 9 .

[0023] Furthermore, a torque sensor 12 is provided at the output end of the reducer 7 .

[0024] Furthermore, a support protective cover 13 is provided at the bottom of the frame 1 on one side of the reducer 7 , and a pull ring 14 is provided on one side of the support protective cover 13 .

[0025] The working process of a device for testing the function of an aircraft landing gear. The device has four working stages:

[0026] The first stage is to use a pressure-pressing vehicle to lift the landing gear to the highest position, and then use the oil cylinder to press the landing gear down for 67-70mm and stop, keeping the pressure unchanged; then use the pressure-pressing vehicle to press the landing gear to 380Bar and stop, and use the oil cylinder to keep pressing for 15 minutes without releasing pressure. This stage is used to detect whether there is oil leakage in the landing gear;

[0027] In the second stage, the gear is lowered by 100mm per minute during the 400mm stroke and by 3mm per minute during the 30mm stroke. During the lowering process, the waste oil in the landing gear is discharged through the diverter valve.

[0028] In the third stage, the device can be used as a three-point fixed suspension landing gear. The landing gear at the bottom of the device can be rotated 0-10° clockwise / counterclockwise under force. The maximum torque when tightened to 10° does not exceed 1050N, and then the rebound force is released and is not greater than 335N. During this whole process, the torque value and the landing gear rebound time can be displayed;

[0029] In the fourth stage, the landing gear is driven by the reducer and can rotate 58-62 degrees clockwise / counterclockwise starting from 0 degrees, and there is no resistance during rebound.

[0030] The beneficial effects of the present invention are: the designed tooling is easy to operate, effectively improves work efficiency, and improves production safety.

[0031] Function of the oil cylinder: landing gear oil discharge test, landing gear pressure maintenance test.

[0032] Function of the fixed bracket: landing gear simulation installation.

[0033] Function of the fixed support plate: the landing gear is installed vertically.

[0034] Function of the fixed hook: to ensure that the landing gear does not move up and down or left and right.

[0035] Function of servo motor: drive the reducer to ensure the rotation angle.

[0036] The function of the reducer is to amplify the torque of the servo motor and reduce the speed. This ensures that there is enough force to rotate the landing gear.

[0037] Function of the support sleeve: to avoid the oil drain hole of the landing gear.

[0038] Function of the lever mounting plate: fix the rotating lever.

[0039] Function of the lever: Landing gear torque test, move the landing gear to rotate a certain angle.

[0040] Function of the center sleeve: Ensure that the landing gear is installed vertically and horizontally up and down and left and right.

[0041] Torque sensor function: measure the torque of the landing gear's rotation angle.

[0042] Function of the support and protection cover: Simulate the installation of the landing gear and ensure that the landing gear does not shake left and right during downward pressure.

[0043] Function of the pull ring: simulate the installation of the landing gear and ensure that the landing gear does not shake back and forth during the downward pressure test.

[0044] The above specific embodiments further illustrate the purpose, technical solutions and beneficial effects of the present invention in detail. It should be understood that the above are only specific 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.

[0045] In the description of the present invention, it is necessary to understand that the terms indicating orientation or positional relationship are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0046] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0047] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inside", "outside", etc. indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, or the positions or positional relationships in which the product of the invention is usually placed when in use. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific position, be constructed and operated in a specific position, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", "third", etc. are only used to distinguish the description, and cannot be understood as indicating or implying relative importance.

[0048] In addition, the terms "horizontal", "vertical", "overhanging" and the like do not mean that the components are required to be absolutely horizontal or overhanging, but can be slightly tilted. For example, "horizontal" only means that its direction is more horizontal than "vertical", and does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0049] In the present invention, unless otherwise clearly specified and limited, a first feature being above or below a second feature may include the first and second features being in direct contact, or may include the first and second features not being in direct contact but being in contact through another feature between them. Moreover, a first feature being above, above, and above a second feature includes the first feature being directly above and obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. A first feature being below, below, and below a second feature includes the first feature being directly below and obliquely below the second feature, or simply means that the first feature is lower in level than the second feature.

Claims

1. A device for testing the function of aircraft landing gear, Features: It comprises a frame, a fixing frame is provided at the upper end of the frame, a cylinder is provided on the fixing frame, a fixing support plate is provided on one side of the fixing frame, a fixing hook is provided on the frame at the lower end of the fixing support plate, a servo motor is provided at the bottom of the frame, and a reducer is provided at the output end of the servo motor; A support sleeve is provided at the lower end of the oil cylinder; The upper end of the reducer is provided with a shift fork mounting plate, the shift fork mounting plate is provided with a shift fork, and the middle of the shift fork mounting plate is provided with a center sleeve; The output end of the reducer is provided with a torque sensor; A support protective sleeve is provided at the bottom of the frame on one side of the reducer, and a pull ring is provided on one side of the support protective sleeve; Oil cylinder function: landing gear oil discharge test, landing gear pressure maintenance test; Function of the fixed frame: landing gear simulation installation; Function of fixed support plate: vertical installation of landing gear; Function of the fixed hook: to ensure that the landing gear does not move up and down or left and right; Function of servo motor: drive the reducer to ensure the rotation angle; The function of the reducer is to amplify the torque of the servo motor and reduce the speed; to ensure that there is enough force to rotate the landing gear; Function of the support sleeve: To avoid the oil drain hole of the landing gear; Function of the lever mounting plate: fix the rotating lever; Function of the lever: Landing gear torque test, move the landing gear to rotate a certain angle; Function of the center sleeve: to ensure that the landing gear is installed vertically and horizontally up and down and left and right; Torque sensor function: measure the torque of the landing gear's rotation angle; Function of the support and protection cover: Simulate the installation of the landing gear and ensure that the landing gear does not shake left and right during downward pressure; Function of the pull ring: simulate the installation of the landing gear and ensure that the landing gear does not shake back and forth during the downward pressure test.

2. The working process of the device for testing the function of an aircraft landing gear according to claim 1, Features: This device has 4 working stages: The first stage is to use a pressure-pressing vehicle to lift the landing gear to the highest position, and then use the oil cylinder to press the landing gear down for 67-70mm and stop, keeping the pressure unchanged; then use the pressure-pressing vehicle to press the landing gear to 380Bar and stop, and use the oil cylinder to keep pressing for 15 minutes without releasing pressure. This stage is used to detect whether there is oil leakage in the landing gear; In the second stage, the gear is lowered by 100mm per minute during the 400mm stroke and by 3mm per minute during the 30mm stroke. During the lowering process, the waste oil in the landing gear is discharged through the diverter valve. In the third stage, the device can be used as a three-point fixed suspension landing gear. The landing gear at the bottom of the device can be rotated 0-10° clockwise / counterclockwise under force. The maximum torque when tightened to 10° does not exceed 1050N, and then the rebound force is released and is not greater than 335N. During this whole process, the torque value and the landing gear rebound time can be displayed; In the fourth stage, the landing gear is driven by the reducer and can rotate 58-62 degrees clockwise / counterclockwise starting from 0 degrees, and there is no resistance during rebound.

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