Aircraft landing gear buffer sealing performance test device
By introducing an adjusting block, a fixed frame, and a lifting assembly into the aircraft landing gear buffer sealing performance test device, and by using a stabilizer bar and an electric telescopic cylinder to improve the stability of the test bench, the problem of shaking during test bench height adjustment was solved, and the accuracy and flexibility of the test results were achieved.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-04-18
- Publication Date
- 2026-04-07
AI Technical Summary
In the prior art, the test bench of the aircraft landing gear buffer sealing performance test device has poor stability during height adjustment, which makes it easy to shake during the adjustment or test process, affecting the accuracy of the test results.
A lifting assembly is adopted, which includes adjusting blocks, a fixed frame, a stabilizer bar, an electric telescopic cylinder, a first support frame, a second support frame, and a translation component. The stability of the fixed frame is improved by the stabilizer bar, and the electric telescopic cylinder is used to push the support frame to support the test platform. The height can be precisely adjusted by using a scale.
It effectively solves the stability problem when adjusting the height of the test bench, ensures the accuracy of the test results, and facilitates the testing needs of different types of landing gear buffers.
Smart Images
Figure CN224095321U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the technical field of design and development of high-performance sealing components and sealing performance testing devices, and in particular to a sealing performance testing device for aircraft landing gear buffers. Background Technology
[0002] The buffer is a key component of the landing gear, and its sealing device design plays an important role in the performance of the buffer, the safety of aircraft operation, and the availability rate. However, it is difficult to accurately derive the performance parameters of hydraulic reciprocating seals theoretically, and it is also difficult to comprehensively and reasonably evaluate the product quality in production practice. Only some very limited and indirect results with poor certainty can be obtained from the use process. In view of this situation, it is necessary to conduct sealing performance tests on the dynamic and static sealing components of the buffer. There are very few reference materials and standards for sealing performance tests of reciprocating machinery in China, making such tests quite difficult. The relevant testing equipment urgently needs to be developed.
[0003] To address the aforementioned issues, existing patent (CN06353043A) discloses a testing device for the sealing performance of an aircraft landing gear buffer. This device includes a servo cylinder mounted on a test bench, a piston rod reciprocating under hydraulic drive, a test cylinder, an actuator, and a detection mechanism. One end of the piston rod passes through the servo cylinder. A cylindrical boss is located in the middle of the piston rod within the servo cylinder, dividing the inner cavity of the servo cylinder into a left cavity and a right cavity. The ends of the left and right cavities are respectively provided with a first drive oil inlet / outlet and a second drive oil inlet / outlet. One end of the piston rod is connected to the actuator via a ball joint. A first groove is formed in the middle of the inner cylindrical surface of the test cylinder, and the actuator is housed within this groove. A gap exists between the first groove and the outer wall of the actuator, forming a hydraulic oil cavity. A hydraulic oil inlet and a circulating oil return port are respectively provided on both sides of the hydraulic oil cavity. The end of the actuator away from the piston rod is connected to the detection mechanism, and a displacement sensor is installed at the end of the detection mechanism.
[0004] However, in the aforementioned prior art, the stability of the test bench is poor when adjusting the height, and it is prone to shaking during the adjustment or testing process, which affects the accuracy of the test results. Utility Model Content
[0005] The purpose of this invention is to provide a test device for the sealing performance of aircraft landing gear buffers, which solves the technical problem in the prior art that the test bench has poor stability during height adjustment and is prone to shaking during adjustment or testing, thus affecting the accuracy of the test results.
[0006] To achieve the above objectives, this utility model employs an aircraft landing gear buffer sealing performance testing device, comprising an adjusting block and an adjusting mechanism. The adjusting mechanism includes a fixed frame, a stabilizing rod, and a lifting assembly. The fixed frame is fixedly connected to the adjusting block and located above it. The stabilizing rod is fixedly connected to the fixed frame and located within it. The lifting assembly includes an electric telescopic cylinder, a first support frame, a second support frame, a test bench body, and a translation component. The electric telescopic cylinder is rotatably connected to the stabilizing rod and located outside it. The bottom of the first support frame is rotatably connected to the fixed frame and located outside the electric telescopic cylinder, with its output end rotatably connected to the middle of the first support frame. The bottom of the second support frame is slidably connected to the fixed frame and located within the first support frame, with its middle section rotatably connected to the middle of the first support frame. The test bench body is slidably connected to the top of the first support frame and located above it, with its top section rotatably connected to the top of the second support frame. The translation component is fixedly connected to the adjusting block and located below it.
[0007] The lifting assembly further includes a mounting base and a scale. The mounting base is detachably connected to the adjusting block and is located outside the adjusting block. The scale is fixedly connected to the mounting base and is located above the mounting base.
[0008] The translation component includes a base plate and a mounting plate. The base plate is slidably connected to the adjusting block and is located below the adjusting block. The mounting plate is fixedly connected to the base plate and is located outside the base plate.
[0009] The translation component further includes a motor, a drive rod, and a moving block. The motor is fixedly connected to one end of the drive rod and is located on the side of the base plate adjacent to the mounting plate. The other end of the drive rod is rotatably connected to the base plate and is located inside the base plate. The surface of the drive rod has threads. The moving block is fixedly connected to the adjusting block and is located outside the drive rod.
[0010] The translation component further includes a sliding block and a limiting rod. The sliding block is fixedly connected to the adjusting block and is located outside the limiting rod. The limiting rod is fixedly connected to the base plate and passes through the sliding block.
[0011] This utility model discloses an aircraft landing gear buffer sealing performance testing device. In specific use, the stabilizer bar enhances the stability of the fixed frame structure, the electric telescopic cylinder pushes the first support frame upward, and the first support frame cooperates with the second support frame to lift the test bench body upward, thereby realizing stable lifting and lowering adjustment of the test bench body. This method can effectively solve the problem of poor stability when adjusting the height of the test bench. Attached Figure Description
[0012] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.
[0013] Figure 1 This is a schematic diagram of the structure of an aircraft landing gear buffer sealing performance testing device according to the present invention.
[0014] Figure 2 This is a perspective view of a test device for the sealing performance of an aircraft landing gear buffer according to the present invention.
[0015] Figure 3 This is a top view of a test device for the sealing performance of an aircraft landing gear buffer according to this utility model.
[0016] Figure 4 This is the utility model Figure 3 A cross-sectional view of the AA line structure.
[0017] 101-Adjusting block, 102-Fixed frame, 103-Stabilizing rod, 104-Electric telescopic cylinder, 105-First support frame, 106-Second support frame, 107-Test bench body, 108-Mounting base, 109-Scale, 110-Base plate, 111-Mounting plate, 112-Motor, 113-Drive rod, 114-Moving block, 115-Sliding block, 116-Limiting rod. Detailed Implementation
[0018] The embodiments of the present invention are described in detail below. Examples of the embodiments are shown in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the present invention, but should not be construed as limiting the present invention.
[0019] Please see Figures 1-4 ,in Figure 1 This is a schematic diagram of the structure of an aircraft landing gear buffer sealing performance testing device according to the present invention. Figure 2This is a perspective view of a test device for the sealing performance of an aircraft landing gear buffer according to this utility model. Figure 3 This is a top view of a test device for the sealing performance of an aircraft landing gear buffer according to this utility model. Figure 4 This is the utility model Figure 3 A cross-sectional view of the AA line structure.
[0020] This utility model provides a test device for the sealing performance of aircraft landing gear buffers, including an adjustment block 101 and an adjustment mechanism. The adjustment mechanism includes a fixed frame 102, a stabilizer bar 103, and a lifting assembly. The lifting assembly includes an electric telescopic cylinder 104, a first support frame 105, a second support frame 106, a test bench body 107, a translation component, a mounting base 108, and a scale 109. The translation component includes a base plate 110, a mounting plate 111, a motor 112, a drive rod 113, a moving block 114, a sliding block 115, and a limiting rod 116. The aforementioned solution solves the problem of poor stability during test bench height adjustment, which easily causes shaking during adjustment or testing, affecting the accuracy of test results.
[0021] In this specific embodiment, the adjustment mechanism includes a fixed frame 102, a stabilizing rod 103, and a lifting assembly. The fixed frame 102 is fixedly connected to the adjusting block 101 and is located above the adjusting block 101. The stabilizing rod 103 is fixedly connected to the fixed frame 102 and is located inside the fixed frame 102. The lifting assembly includes an electric telescopic cylinder 104, a first support frame 105, a second support frame 106, a test bench body 107, and a translation component. The electric telescopic cylinder 104 is rotatably connected to the stabilizing rod 103 and is located outside the stabilizing rod 103. The bottom of the first support frame 105 is rotatably connected to the fixed frame 102 and is located outside the electric telescopic cylinder 104. The output end of the electric telescopic cylinder 104 is rotatably connected to the middle of the first support frame 105. The bottom of the second support frame 106 is connected to the fixed frame 102. The test bench body 107 is slidably connected to the top of the first support frame 105 and located above the first support frame 105. The test bench body 107 is rotatably connected to the top of the second support frame 106 and located above the first support frame 105. The translation member is fixedly connected to the adjustment block 101 and located below the adjustment block 101. The stabilizing rod 103 enhances the stability of the fixed frame 102 structure. The electric telescopic cylinder 104 pushes the first support frame 105 upward. The first support frame 105 cooperates with the second support frame 106 to lift the test bench body 107 upward, thereby achieving stable lifting and lowering adjustment of the test bench body 107. This method can effectively solve the problem of poor stability when adjusting the height of the test bench.
[0022] The lifting assembly also includes a mounting base 108 and a scale 109. The mounting base 108 is detachably connected to the adjusting block 101 and is located outside the adjusting block 101. The scale 109 is fixedly connected to the mounting base 108 and is located above the mounting base 108. The mounting base 108 is bolted to the outside of the adjusting block 101, so that the mounting base 108 can be installed and removed as needed. The scale 109 is used to read the working height of the test bench body 107.
[0023] Secondly, the translation component includes a base plate 110 and a mounting plate 111. The base plate 110 is slidably connected to the adjusting block 101 and is located below the adjusting block 101. The mounting plate 111 is fixedly connected to the base plate 110 and is located outside the base plate 110. The base plate 110 is used to support the adjusting block 101, and the mounting plate 111 is used to fix the base plate 110 to the working environment.
[0024] Meanwhile, the translation component also includes a motor 112, a drive rod 113, and a moving block 114. The motor 112 is fixedly connected to one end of the drive rod 113 and is located on the side of the base plate 110 adjacent to the mounting plate 111. The other end of the drive rod 113 is rotatably connected to the base plate 110 and is located inside the base plate 110. The surface of the drive rod 113 is threaded. The moving block 114 is fixedly connected to the adjusting block 101 and is located outside the drive rod 113. The motor 112 drives the drive rod 113 to rotate, and the drive rod 113 drives the moving block 114 to move within the base plate 110. The moving block 114 drives the adjusting block 101 to translate on the surface of the base plate 110.
[0025] In addition, the translation component also includes a sliding block 115 and a limiting rod 116. The sliding block 115 is fixedly connected to the adjusting block 101 and is located outside the limiting rod 116. The limiting rod 116 is fixedly connected to the base plate 110 and passes through the sliding block 115. When the adjusting block 101 moves, it drives the sliding block 115 to move. The sliding block 115 slides outside the limiting rod 116 to ensure that the adjusting block 101 can perform translation operations stably.
[0026] Using the aircraft landing gear buffer sealing performance testing device of this embodiment, by setting the fixed frame 102, the stabilizer bar 103, and the lifting assembly, in specific use, the stabilizer bar 103 enhances the stability of the fixed frame 102 structure, the electric telescopic cylinder 104 pushes the first support frame 105 upward, and the first support frame 105, in conjunction with the second support frame 106, lifts the test bench body 107 upward, realizing stable lifting and lowering adjustment of the test bench body 107, and can be quickly adjusted using the scale 109. The working height of the test bench body 107 is read. When the test bench body 107 needs to be moved and adjusted, the motor 112 drives the drive rod 113 to rotate. The drive rod 113 drives the moving block 114 to move within the base plate 110. The moving block 114 drives the adjusting block 101 to translate on the surface of the base plate 110, thereby realizing the translation operation of the test bench body 107. This allows for stable adjustment of the working height of the test bench, ensuring the accuracy of the test results and facilitating the testing needs of different types of landing gear buffers.
[0027] The above-disclosed embodiments are merely preferred embodiments of the present utility model and should not be construed as limiting the scope of the present utility model. Those skilled in the art can understand that implementing all or part of the above-described embodiments and making equivalent changes in accordance with the claims of the present utility model are still within the scope of the utility model.
Claims
1. A testing device for the sealing performance of an aircraft landing gear buffer, comprising an adjusting block, characterized in that, It also includes adjustment mechanisms; The adjustment mechanism includes a fixed frame, a stabilizing rod, and a lifting assembly. The fixed frame is fixedly connected to the adjusting block and located above the adjusting block. The stabilizing rod is fixedly connected to the fixed frame and located within the fixed frame. The lifting assembly includes an electric telescopic cylinder, a first support frame, a second support frame, a test bench body, and a translation component. The electric telescopic cylinder is rotatably connected to the stabilizing rod and located outside the stabilizing rod. The bottom of the first support frame is rotatably connected to the fixed frame and located outside the electric telescopic cylinder, and the output end of the electric telescopic cylinder is rotatably connected to the middle of the first support frame. The bottom of the second support frame is slidably connected to the fixed frame and located within the first support frame, and the middle of the second support frame is rotatably connected to the middle of the first support frame. The test bench body is slidably connected to the top of the first support frame and located above the first support frame, and the test bench body is rotatably connected to the top of the second support frame. The translation component is fixedly connected to the adjusting block and located below the adjusting block.
2. The aircraft landing gear buffer sealing performance testing device as described in claim 1, characterized in that, The lifting assembly also includes a mounting base and a scale. The mounting base is detachably connected to the adjusting block and is located outside the adjusting block. The scale is fixedly connected to the mounting base and is located above the mounting base.
3. The aircraft landing gear buffer sealing performance testing device as described in claim 2, characterized in that, The translation component includes a base plate and a mounting plate. The base plate is slidably connected to the adjusting block and is located below the adjusting block. The mounting plate is fixedly connected to the base plate and is located outside the base plate.
4. The aircraft landing gear buffer sealing performance testing device as described in claim 3, characterized in that, The translation component also includes a motor, a drive rod, and a moving block. The motor is fixedly connected to one end of the drive rod and is located on the side of the base plate adjacent to the mounting plate. The other end of the drive rod is rotatably connected to the base plate and is located inside the base plate. The surface of the drive rod has threads. The moving block is fixedly connected to the adjusting block and is located outside the drive rod.
5. The aircraft landing gear buffer sealing performance testing device as described in claim 4, characterized in that, The translation component also includes a sliding block and a limiting rod. The sliding block is fixedly connected to the adjusting block and is located outside the limiting rod. The limiting rod is fixedly connected to the base plate and passes through the sliding block.