Aircraft control link wear test device

Abstract

The present invention discloses an aircraft control link wear test device, comprising: a base frame, a swinging motion mechanism, a rotating shaft mechanism, and an axial loading mechanism. The axial loading mechanism is used to apply an axial load to a push-pull rod. The rotating shaft mechanism includes a rotating shaft sleeved with a rod end joint bearing. The swinging motion mechanism is connected to the rotating shaft and drives the rotating shaft to rotate relative to the rod end joint bearing through reciprocating swinging. The aircraft control link wear test device can simulate the wear environment of a typical control link structure of a general aviation aircraft and conduct tests. It can provide effective data support for the operation and maintenance of general aviation aircraft and has the advantages of low cost, high reliability, high adaptability, convenient and accessible testing, safety, and high efficiency.

Description

Technical Field

[0001] The invention relates to the field of aerospace, and in particular provides an aircraft control link wear test device. Background Art

[0002] In general aviation aircraft control systems, rod end joint bearings are the key lubricating and anti-friction friction pairs of the control rod mechanism. Their service life is related to the load form, load size and wear state. Research on the wear reliability of the rod end joint bearing friction pairs of general aviation aircraft control systems is necessary to improve aircraft safety and can provide important parameters for aircraft design, aircraft use and aircraft maintenance.

[0003] Therefore, providing a friction and wear testing device has become an urgent problem to be solved. Summary of the Invention

[0004] In view of this, an object of the present invention is to provide an aircraft control link wear test device for simulating the actual working conditions of a test piece and conducting a wear test.

[0005] The technical solution provided by the present invention is: an aircraft control link wear test device, which is used to provide a wear test platform for an aircraft control link test piece, wherein the aircraft control link test piece includes a push-pull rod and a rod end joint bearing connected to the push-pull rod, and the aircraft control link wear test device includes a basic frame, a swinging motion mechanism, a rotating shaft mechanism and an axial loading mechanism, wherein the axial loading mechanism is installed above the basic frame, used to be connected to the free end of the push-pull rod and apply an axial load to the push-pull rod, the rotating shaft mechanism includes a rotating shaft fixing structure and a rotating shaft, the rotating shaft fixing structure is installed on the basic frame and is located on one side of the axial loading mechanism, the rotating shaft is rotatably installed on the rotating shaft fixing structure, and is used to cooperate with the rod end joint bearing of the aircraft control link test piece, the swinging motion mechanism is installed on the basic frame and is connected to the rotating shaft, and is used to drive the rotating shaft to rotate relative to the rod end joint bearing by swinging.

[0006] Preferably, the aircraft control link wear test device also includes a support structure, which is installed above the base frame and has two guide columns fixedly arranged thereon. The axial loading mechanism includes a push-pull rod adapter, a tension and pressure sensor, a loading plate, a loading flange connector and a loading electric cylinder, wherein the loading electric cylinder is fixed on the support structure, the output end of the loading electric cylinder is connected to one side of the loading plate through the loading flange connector, and the other side of the loading plate is connected to the push-pull rod adapter through the tension and pressure sensor, and both ends of the loading plate are installed on the guide columns to ensure the stability of load loading.

[0007] Further preferably, the support structure also includes load-bearing baffles and support beams to form a frame-type support structure.

[0008] Further preferably, a guide mechanism cooperating with the push-pull rod is fixedly provided on the support structure.

[0009] Further preferably, the rotating shaft fixing structure includes a mounting support, a load-bearing support and a deep groove ball bearing, wherein the mounting support is fixedly arranged above the base frame, the load-bearing support is installed on the mounting support, there are two deep groove ball bearings, which are fixed on the load-bearing support with upper and lower intervals, and the rotating shaft is rotatably connected to the two deep groove ball bearings. During the test, the rod end joint bearing is fitted on the rotating shaft and located between the two deep groove ball bearings.

[0010] Further preferably, the swing motion mechanism includes a reducer, a turntable, a connecting rod and a swing arm, wherein the reducer is fixed on the base frame, the turntable is connected to the output shaft of the reducer, one end of the swing arm is fixedly connected to the rotating shaft, and the other end is connected to the turntable through the connecting rod, for realizing reciprocating swing under the drive of the turntable, and realizing swinging wear of the rod end joint bearing through the rotating shaft.

[0011] Further preferably, a wedge-shaped groove is provided at the end of the swing arm, a mounting block is fixedly provided at the large end of the wedge groove, a fastening bolt is installed on the mounting block, and a wedge-shaped block that cooperates with the wedge-shaped groove is provided at the top of the rotating shaft. When the wedge-shaped block at the top of the rotating shaft is inserted into the wedge groove, the swing arm and the rotating shaft can be fastened by rotating the fastening bolt.

[0012] Further preferably, the basic frame includes a welding frame and a mounting base table fixedly installed above the welding frame.

[0013] The aircraft control link wear test device provided by the present invention can complete the wear test of the test piece. A constant or variable load can be applied to the test piece through the axial loading mechanism and transmitted to the rotating shaft. The reciprocating motion of the swinging motion mechanism can drive the rotating shaft to rotate, thereby realizing the swinging wear of the rod end joint bearing. The aircraft control link wear test device can simulate the actual working conditions of the aircraft control link, and can provide a test basis for the maintenance cycle and service life of the tie rod of the general aviation aircraft control system.

[0014] The aircraft control link wear test device provided by the present invention can simulate the wear environment of a typical control link structure of a general aviation aircraft and conduct tests, thereby providing effective data support for the operation and maintenance of general aviation aircraft. It has the advantages of low cost, high reliability, high adaptability, convenient test implementation, accessibility, safety, and high efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] The present invention will be further described in detail below with reference to the accompanying drawings and embodiments:

[0016] Figure 1 This is a schematic structural diagram of the aircraft control link wear test device provided by the present invention;

[0017] Figure 2 A schematic diagram of the basic framework;

[0018] Figure 3 It is a schematic diagram of the connection between the swing motion mechanism and the rotating axis mechanism;

[0019] Figure 4 It is a structural diagram of the rotating shaft mechanism;

[0020] Figure 5 This is a schematic diagram of the connection between the aircraft control link test piece and the supporting structure;

[0021] Figure 6 Schematic diagram of the connection between the axial loading mechanism and the supporting structure. DETAILED DESCRIPTION

[0022] The present invention will be further explained below with reference to specific embodiments, but the present invention is not limited thereto.

[0023] like Figures 1 to 6 As shown, the present invention provides an aircraft control link wear test device, which is used to provide a wear test platform for an aircraft control link test piece 4, wherein the aircraft control link test piece 4 includes a push-pull rod 402 and a rod end joint bearing 401 connected to the push-pull rod 402, and the aircraft control link wear test device includes a base frame 1, a swing motion mechanism 2, a rotation axis mechanism 3 and an axial loading mechanism 5, wherein the axial loading mechanism 5 is installed above the base frame 1, and is used to connect with the free end of the push-pull rod 402 and to push the push-pull rod 402 to the free end of the push-pull rod 402. 02 applies an axial load, the rotating shaft mechanism 3 includes a rotating shaft fixing structure and a rotating shaft 303, the rotating shaft fixing structure is installed on the basic frame 1 and is located on one side of the axial loading mechanism 5, the rotating shaft 303 is rotatably installed on the rotating shaft fixing structure, and is used to cooperate with the rod end joint bearing 401 of the aircraft control link test piece 4, the swinging motion mechanism 2 is installed on the basic frame 1, and is connected to the rotating shaft 303, and is used to drive the rotating shaft 303 to rotate relative to the rod end joint bearing 401 by swinging.

[0024] The aircraft control link wear test device can complete the wear test of the test piece. A constant or variable load can be applied to the test piece through the axial loading mechanism and transmitted to the rotating shaft. The reciprocating motion of the swinging motion mechanism can drive the rotating shaft to rotate relative to the rod end joint bearing, thereby realizing the swinging wear of the rod end joint bearing. The aircraft control link wear test device can simulate the actual working conditions of the aircraft control link and provide a test basis for the maintenance cycle and service life of the tie rod of the general aviation aircraft control system.

[0025] As an improvement of the technical solution, Figure 1 、 Figure 5 、 Figure 6 As shown, the aircraft control link wear test device also includes a support structure 6, which is installed above the basic frame 1 and has two guide columns 603 fixed thereon. The axial loading mechanism 5 includes a push-pull rod adapter 501, a pull-pressure sensor 502, a loading plate 503, a loading flange connector 504 and a loading electric cylinder 505, wherein the loading electric cylinder 505 is fixed on the support structure 6, and the output end of the loading electric cylinder 505 is connected to one side of the loading plate 503 through the loading flange connector 504, and the other side of the loading plate 503 is connected to the push-pull rod adapter 501 through the pull-pressure sensor 502, and both ends of the loading plate 503 are installed on the guide columns 603 to ensure the stability of load loading.

[0026] As an improvement of the technical solution, Figure 6 As shown, the support structure 6 further includes a load-bearing baffle 601 and a support beam 602, forming a frame-type support structure.

[0027] As an improvement of the technical solution, Figure 5 As shown, a guide mechanism 604 cooperating with the push-pull rod 402 is also fixedly provided on the support structure 6 .

[0028] As an improvement of the technical solution, Figure 3 、 Figure 4 As shown, the rotating shaft fixing structure includes a mounting support 301, a load-bearing support 302 and a deep groove ball bearing 304, wherein the mounting support 301 is fixedly arranged above the basic frame 1, the load-bearing support 302 is installed on the mounting support 301, there are two deep groove ball bearings 304, which are fixed on the load-bearing support 302 with an upper and lower interval, and the rotating shaft 303 is rotatably connected to the two deep groove ball bearings 304. During the test, the rod end joint bearing 401 is fitted on the rotating shaft 303 and is located between the two deep groove ball bearings 304.

[0029] As an improvement of the technical solution, Figure 3 、 Figure 4As shown, the swing motion mechanism 2 includes a reducer 201, a turntable 202, a connecting rod 203 and a swing arm 204, wherein the reducer 201 is fixed on the base frame 1, the turntable 202 is connected to the output shaft of the reducer 201, one end of the swing arm 204 is fixedly connected to the rotating shaft 303, and the other end is connected to the turntable 202 through the connecting rod 203, and is used to realize reciprocating swing under the drive of the turntable 202, and realize the swing wear of the rod end joint bearing 401 through the rotating shaft 303. The reducer plays a role in driving the turntable to rotate, and the turntable and the connecting rod can be adjusted according to the different angle requirements of the test piece to meet the adjustment of various swing angles.

[0030] As an improvement to the technical solution, a wedge-shaped groove is provided at the end of the swing arm 204, and a mounting block 205 is fixedly provided at the large end of the wedge groove. A fastening bolt is installed on the mounting block 205, and a wedge-shaped block that cooperates with the wedge-shaped groove is provided on the top of the rotating shaft 303. When the wedge-shaped block on the top of the rotating shaft 303 is inserted into the wedge groove, the swing arm 204 and the rotating shaft 303 can be fastened together by rotating the fastening bolt. The close fit between the wedge groove and the rotating shaft can eliminate the installation gap and error between the two and improve the swing angle accuracy.

[0031] As an improvement of the technical solution, the basic frame 1 includes a welding frame 101 and a mounting base table 102 fixedly installed above the welding frame 101 .

[0032] The detailed description of the present invention is written in a progressive manner, emphasizing the differences between the various implementation schemes, and similar parts thereof can be referenced to each other.

[0033] The embodiments of the present invention have been described in detail above with reference to the accompanying drawings. However, the present invention is not limited to the above embodiments. Various changes can be made within the knowledge of ordinary technicians in this field without departing from the scope of the present invention.

Claims

1. An aircraft control link wear test device, for providing a wear test platform for an aircraft control link test piece (4), wherein: The aircraft control link test piece (4) includes a push-pull rod (402) and a rod end joint bearing (401) connected to the push-pull rod (402), and is characterized in that: the aircraft control link wear test device includes a base frame (1), a swing motion mechanism (2), a rotation axis mechanism (3) and an axial loading mechanism (5), wherein the axial loading mechanism (5) is installed above the base frame (1) and is used to be connected to the free end of the push-pull rod (402) and apply an axial load to the push-pull rod (402), and the rotation axis mechanism (3) includes a rotation axis fixing structure and a rotation axis (3 03), the rotating shaft fixing structure is mounted on the base frame (1) and is located on one side of the axial loading mechanism (5), the rotating shaft (303) is rotatably mounted on the rotating shaft fixing structure, and is used to be sleeved with the rod end joint bearing (401) of the aircraft control link test piece (4), the swinging motion mechanism (2) is mounted on the base frame (1), and is connected to the rotating shaft (303), and is used to drive the rotating shaft (303) to rotate relative to the rod end joint bearing (401) by swinging, and the rotating shaft fixing structure includes a mounting support (301), a load-bearing support The base frame (301) and the deep groove ball bearing (304) are provided, wherein the mounting support (301) is fixedly arranged above the base frame (1), the load-bearing support (302) is mounted on the mounting support (301), the deep groove ball bearing (304) is two, and is fixed on the load-bearing support (302) at an upper and lower interval, the rotating shaft (303) is rotatably connected to the two deep groove ball bearings (304), and during the test, the rod end joint bearing (401) is fitted on the rotating shaft (303) and is located between the two deep groove ball bearings (304), and the swing motion mechanism (2) includes The invention comprises a reducer (201), a turntable (202), a connecting rod (203) and a swing arm (204), wherein the reducer (201) is fixed on the base frame (1), the turntable (202) is connected to the output shaft of the reducer (201), one end of the swing arm (204) is fixedly connected to the rotating shaft (303), and the other end is connected to the turntable (202) through the connecting rod (203), and is used for realizing reciprocating swing under the drive of the turntable (202), and realizing swing wear of the rod end joint bearing (401) through the rotating shaft (303).

2. The aircraft control link wear tester according to claim 1, characterized in that: The invention also includes a support structure (6), which is installed above the base frame (1) and has two guide columns (603) fixed thereon. The axial loading mechanism (5) includes a push-pull rod adapter (501), a tension pressure sensor (502), a loading plate (503), a loading flange connector (504) and a loading electric cylinder (505), wherein the loading electric cylinder (505) is fixed on the support structure (6), the output end of the loading electric cylinder (505) is connected to one side of the loading plate (503) through the loading flange connector (504), and the other side of the loading plate (503) is connected to the push-pull rod adapter (501) through the tension pressure sensor (502), and both ends of the loading plate (503) are installed on the guide columns (603) to ensure the stability of load loading.

3. The aircraft control link wear tester according to claim 2, characterized in that: The support structure (6) further comprises a load-bearing baffle (601) and a support beam (602), forming a frame-type support structure.

4. The aircraft control link wear tester according to claim 2, characterized in that: A guide mechanism (604) cooperating with the push-pull rod (402) is also fixedly provided on the support structure (6).

5. The aircraft control link wear tester according to claim 1, characterized in that: A wedge-shaped groove is provided at the end of the swing arm (204), a mounting block (205) is fixedly provided at the large end of the wedge-shaped groove, a fastening bolt is installed on the mounting block (205), and a wedge-shaped block that cooperates with the wedge-shaped groove is provided at the top of the rotating shaft (303). When the wedge-shaped block at the top of the rotating shaft (303) is inserted into the wedge-shaped groove, the swing arm (204) and the rotating shaft (303) can be fastened together by rotating the fastening bolt.

6. The aircraft control link wear tester according to claim 1, characterized in that: The basic frame (1) comprises a welding frame (101) and a mounting base table (102) fixedly mounted above the welding frame (101).

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