Steering testing device for nose landing gear of small aircraft

Abstract

The invention discloses a small aircraft nose landing gear steering testing device, and belongs to the technical field of aircraft nose landing gear steering testing, the small aircraft nose landing gear steering testing device comprises a steering testing mechanism, the steering testing mechanism comprises a mounting frame, the top end of the steering testing mechanism is rotatably provided with a turntable main body through a bearing, and the bottom end of the turntable main body is provided with a first rotating rod main body; a mounting frame is mounted at the top end of the steering test mechanism, an aircraft nose landing gear main body is arranged in the mounting frame, positioning frames are mounted at the two ends of the bottom end in the mounting frame, and first grooves are formed in the top ends of the side walls of one ends of the positioning frames. The fixing device has the beneficial effects that the connecting rod slides to drive the first positioning plate and the first non-slip mat to slide so as to position and fix the aircraft nose landing gear main body, and meanwhile, through the design of the first non-slip mat, the positioning and fixing effect of the first positioning plate and the first non-slip mat on the aircraft nose landing gear main body is better; therefore, the nose landing gear main body of the aircraft is prevented from shaking during steering.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft front landing gear steering test, and particularly relates to a small aircraft front landing gear steering test device. Background Art

[0002] Small helicopters are highly sensitive and accurate, and they are safe and reliable during flight. They are widely used in urban traffic monitoring, agricultural and forestry sowing, spraying, complex terrain mapping, etc. Small helicopters are manufactured based on reduced-scale large helicopters. They have most of the characteristics of large helicopters, and are more sensitive. They are suitable for UAV (unmanned aerial vehicle) research. The front landing gear of a small aircraft refers to the component of the landing gear. It is a ground support component installed under the nose of the aircraft. It is composed of the front wheel, strut, shock absorber, steering device, shimmy damper, brake, retractable device and guard plate. When the aircraft moves on the ground, the front landing gear not only supports a small part of the gravity load, but also plays a guiding role. Therefore, before the aircraft takes off, the steering of the front landing gear of the small aircraft needs to be tested.

[0003] When the steering of the front landing gear of a small aircraft is tested, the maintenance personnel usually rotate the front landing gear of the small aircraft to perform the steering test. This test data is not accurate enough, which poses a safety hazard. At the same time, the front landing gear of the small aircraft and the steering test device cannot be positioned and fixed, which easily causes the front landing gear of the small aircraft to shake during the steering test, thereby affecting the test effect of the steering test device. Summary of the invention

[0004] The purpose of the present invention is to provide a steering test device for the front landing gear of a small aircraft, so as to solve the problem raised in the above-mentioned background technology that when the front landing gear of a small aircraft is tested for steering, the steering test is performed by maintenance personnel by rotating the front landing gear of the small aircraft. Such test data is not accurate enough, thus posing a safety hazard. At the same time, the front landing gear of the small aircraft and the steering test device cannot be positioned and fixed, which easily causes the front landing gear of the small aircraft to shake during the steering test, thereby affecting the test effect of the steering test device.

[0005] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: a small aircraft front landing gear steering test device, comprising a steering test mechanism, which comprises a mounting frame, a turntable body is rotatably mounted on the top of the steering test mechanism through a bearing, and a first rotating rod body is mounted on the bottom of the turntable body, a mounting frame is mounted on the top of the steering test mechanism, and the aircraft front landing gear body is arranged inside the mounting frame, positioning frames are mounted on both ends of the bottom end of the mounting frame, and a first groove is provided on the top of a side wall of one end of the positioning frame, an inner wall support plate of the steering test mechanism, and a torque sensor is mounted on the top of the support plate, a second rotating rod body is mounted inside the torque sensor, and a second gear body is mounted on the top of the second rotating rod body, a single-chip microcomputer is mounted on the inner wall of the steering test mechanism, and a display screen body is mounted on the outer wall of the steering test mechanism;

[0006] A positioning and fixing mechanism, comprising a first through hole, the first through hole being opened on the side walls of the positioning frame and the mounting frame, a connecting rod penetrating the mounting frame being arranged inside the first through hole, a first positioning plate being installed at one end of the connecting rod, and a second positioning plate being installed at one end of the connecting rod away from the first positioning plate;

[0007] The rotating mechanism comprises a mounting plate, the mounting plate is mounted on the side walls at both ends of the mounting frame, a driving motor is mounted on one end of the mounting plate, and a driving shaft is mounted on the output end of the driving motor through a coupling, and a cam body is mounted on the outer wall of the driving shaft;

[0008] The supporting and fixing mechanism comprises a fixing rod, which is installed on the outer wall of the steering test mechanism. A second groove is opened inside the fixing rod, and a turntable body is installed inside the second groove through ball rotation. A threaded hole is opened inside the turntable body, and a threaded rod is threadedly connected inside the threaded hole. The bottom end of the threaded rod is rotatably installed with a limit plate through a bearing.

[0009] Furthermore, a first gear body is installed at the bottom end of the first rotating rod body, and the first gear body and the second gear body are meshed with each other.

[0010] Furthermore, a first spring body is installed on the side wall at one end of the interior of the positioning frame, and one end of the first spring body is fixedly connected to the side wall of the first positioning plate.

[0011] Furthermore, a second spring body is installed on the side wall at one end of the second positioning plate, and one end of the second spring body away from the second positioning plate is fixedly connected to the side wall of the positioning frame.

[0012] Furthermore, a first anti-skid pad is installed at one end of the first positioning plate, and the first anti-skid pad and the first positioning plate are welded into an integrated structure.

[0013] Furthermore, a sliding rod is installed at the top end of the second groove, and a sliding sleeve is sleeved on the outer wall of the sliding rod, and the outer wall of the sliding sleeve is fixedly connected to the outer wall of the threaded rod.

[0014] Furthermore, the outer wall of the turntable body is installed with a handle body, and the outer wall of the handle body is installed with a protective pad.

[0015] Furthermore, a second anti-skid pad is installed at the bottom end of the limiting plate, and an outer wall of the second anti-skid pad is installed with anti-skid patterns.

[0016] Furthermore, the output end of the torque sensor is electrically connected to the input end of the single-chip microcomputer through a wire, and the output end of the single-chip microcomputer is electrically connected to the input end of the display screen body through a wire.

[0017] Compared with the prior art, the present invention has the following beneficial effects:

[0018] (1) The small aircraft front landing gear steering test device is configured by inserting the aircraft front landing gear body into the interior of the positioning frame, and starting the driving motor to drive the driving shaft and the cam body to rotate. The cam body is designed, and the first through hole cooperates with the connecting rod, so that the second positioning plate is squeezed by the cam body to drive the second positioning plate and the connecting rod to slide inside the first through hole, so that the connecting rod slides to drive the first positioning plate and the first anti-skid pad to slide to position and fix the aircraft front landing gear body. At the same time, the design of the first anti-skid pad makes the first positioning plate and the first anti-skid pad have a better positioning and fixing effect on the aircraft front landing gear body, thereby preventing the aircraft front landing gear body from shaking when turning.

[0019] (2) The front landing gear steering test device of a small aircraft is firstly connected by a threaded hole and a threaded rod, and the sliding rod and the sliding sleeve cooperate with each other, and the turntable body is driven to rotate by turning the handle body, so that the turntable body rotates to drive the threaded rod to rise and fall inside the threaded hole through the sliding sleeve and the sliding rod, so that the threaded rod can be raised and lowered to drive the limit plate to rise and fall at the same time, so that the limit plate can be raised and lowered to fit the ground, and the second anti-slip pad is designed to make the limit plate have a better positioning and fixing effect on the steering test mechanism.

[0020] (3) The front landing gear steering test device for a small aircraft is designed with a torque sensor, and the first gear body and the second gear body are meshed with each other, so that when the front landing gear body of the aircraft is performing a steering test, the front landing gear body of the aircraft drives the turntable body, the first rotating rod body and the first gear body to rotate simultaneously, and the first gear body and the second gear body are meshed with each other, so that the first gear body rotates to drive the second gear body to rotate simultaneously, so that the second gear body rotates to drive the second rotating rod body to rotate and perform a steering test through the torque sensor. At the same time, when the torque sensor is performing a steering test, the data is analyzed by the single-chip microcomputer, and the data is transmitted to the display screen body through the single-chip microcomputer, so that the data is displayed on the display screen body. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a cross-sectional structural schematic diagram of a small aircraft front landing gear steering test device of the present invention;

[0022] Figure 2 This is a schematic diagram of the internal structure of the installation frame of the small aircraft front landing gear steering test device of the present invention;

[0023] Figure 3 It is a schematic diagram of the main structure of the front landing gear steering test device of a small aircraft according to the present invention;

[0024] Figure 4 It is a schematic diagram of the positioning frame structure of the front landing gear steering test device of a small aircraft according to the present invention;

[0025] Figure 5 It is a schematic diagram of the structure of the rotating mechanism of the front landing gear steering test device of a small aircraft of the present invention;

[0026] Figure 6 This is a schematic diagram of the internal structure of the positioning frame of the small aircraft front landing gear steering test device of the present invention.

[0027] Figure 7 The figure is a schematic diagram of the internal structure of the supporting and fixing mechanism of the small aircraft front landing gear steering test device of the present invention.

[0028] In the accompanying drawings, the components represented by the reference numerals are listed as follows:

[0029] 1. Steering test mechanism; 101. Mounting frame; 102. Front landing gear body of aircraft; 103. Positioning frame; 1031. First groove; 104. Turntable body; 105. First rotating rod body; 106. First gear body; 107. Support plate; 108. Torque sensor; 109. Second rotating rod body; 1010. Second gear body; 1011. Single chip microcomputer; 1012. Display screen body;

[0030] 2. Positioning and fixing mechanism; 201. first through hole; 202. connecting rod; 203. first positioning plate; 204. first anti-slip pad; 205. first spring body; 206. second positioning plate; 207. second spring body;

[0031] 3. Rotating mechanism; 301. Mounting plate; 302. Driving motor; 303. Driving shaft; 304. Cam body;

[0032] 4. Support and fixation mechanism; 401. Fixing rod; 402. Second groove; 403. Turntable body; 4031. Handle body; 404. Threaded hole; 405. Threaded rod; 406. Limiting plate; 4061. Second anti-slip pad; 407. Sliding rod; 408. Sliding sleeve. DETAILED DESCRIPTION

[0033] The following will be combined with the drawings in 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.

[0034] Embodiment 1, as Figure 1-7 As shown, it includes a steering test mechanism 1, which includes a mounting frame 101, a turntable body 104 is rotatably mounted on the top of the steering test mechanism 1 through a bearing, and a first rotating rod body 105 is mounted on the bottom of the turntable body 104, the mounting frame 101 is mounted on the top of the steering test mechanism 1, and the aircraft front landing gear body 102 is arranged inside the mounting frame 101, and positioning frames 103 are installed at both ends of the bottom end of the mounting frame 101, and a first groove 1031 is opened on the top of the side wall of one end of the positioning frame 103, and the steering test mechanism 1 The inner wall supports a plate 107, and a torque sensor 108 is installed on the top of the support plate 107, a second rotating rod body 109 is installed inside the torque sensor 108, and a second gear body 1010 is installed on the top of the second rotating rod body 109, a single-chip computer 1011 is installed on the inner wall of the steering test mechanism 1, a display screen body 1012 is installed on the outer wall of the steering test mechanism 1, and a first gear body 106 is installed on the bottom end of the first rotating rod body 105, and the first gear body 106 and the second gear body 1010 are meshed with each other;

[0035] The output end of the torque sensor 108 is electrically connected to the input end of the single chip microcomputer 1011 through a wire, and the output end of the single chip microcomputer 1011 is electrically connected to the input end of the display screen body 1012 through a wire.

[0036] The specific working principle is that when it is necessary to perform a steering test on the front landing gear of a small aircraft, first, through the design of the torque sensor 108, and through the mutual engagement of the first gear body 106 and the second gear body 1010, when the front landing gear body 102 of the aircraft is performing the steering test, the front landing gear body 102 of the aircraft drives the turntable body 104, the first rotating rod body 105 and the first gear body 106 to rotate at the same time, and through the mutual engagement of the first gear body 106 and the second gear body 1010, the first gear body 106 rotates to drive the second gear body 1010 to rotate at the same time, so that the second gear body 1010 rotates to drive the second rotating rod body 109 to rotate and perform the steering test through the torque sensor 108. At the same time, when the torque sensor 108 performs the steering test, the data is analyzed by the single-chip microcomputer 1011, and the data is transmitted to the display screen body 1012 through the single-chip microcomputer 1011, so that the data is displayed through the display screen body 1012.

[0037] Embodiment 2, as Figure 1-7 As shown, the positioning and fixing mechanism 2 includes a first through hole 201, which is provided on the side walls of the positioning frame 103 and the mounting frame 101, a connecting rod 202 penetrating the mounting frame 101 is provided inside the first through hole 201, and a first positioning plate 203 is installed at one end of the connecting rod 202, and a second positioning plate 206 is installed at one end of the connecting rod 202 away from the first positioning plate 203, and a first spring body 205 is installed on the side wall at one end of the positioning frame 103, and one end of the first spring body 205 is fixedly connected to the side wall of the first positioning plate 203;

[0038] The side wall at one end of the second positioning plate 206 is installed with a second spring body 207, and the end of the second spring body 207 away from the second positioning plate 206 is fixedly connected to the side wall of the positioning frame 103, and the first anti-skid pad 204 is installed at one end of the first positioning plate 203, and the first anti-skid pad 204 and the first positioning plate 203 are a welded integrated structure, and through the design of the first anti-skid pad 204, the positioning and fixing effect of the first positioning plate 203 is better through the first anti-skid pad 204;

[0039] The rotating mechanism 3 includes a mounting plate 301, which is mounted on the side walls at both ends of the mounting frame 101. A driving motor 302 is mounted on one end of the mounting plate 301, and a driving shaft 303 is mounted on the output end of the driving motor 302 through a coupling. A cam body 304 is mounted on the outer wall of the driving shaft 303. Through the design of the cam body 304, the second positioning plate 206 can be better positioned and fixed by rotating the cam body 304.

[0040] The specific working principle is that, first, when it is necessary to position and fix the front landing gear body 102 of the aircraft, the front landing gear body 102 of the aircraft is inserted into the interior of the positioning frame 103, and the driving motor 302 is started to drive the driving shaft 303 and the cam body 304 to rotate, and through the design of the cam body 304, and through the first through hole 201 and the connection rod 202 cooperate with each other, the second positioning plate 206 is squeezed by the cam body 304 to drive the second positioning plate 206 and the connection rod 202 to slide inside the first through hole 201, so that the connecting rod 202 slides to drive the first positioning plate 203 and the first anti-skid pad 204 to slide to position and fix the front landing gear body 102 of the aircraft, and at the same time, through the design of the first anti-skid pad 204, the first positioning plate 203 and the first anti-skid pad 204 can better position and fix the front landing gear body 102 of the aircraft, thereby preventing the front landing gear body 102 of the aircraft from shaking when turning.

[0041] Embodiment 3, as Figure 1 and Figure 7 As shown, the support fixing mechanism 4 includes a fixing rod 401, which is mounted on the outer wall of the steering test mechanism 1, a second groove 402 is provided inside the fixing rod 401, and a turntable body 403 is rotatably mounted inside the second groove 402 through a ball bearing, a threaded hole 404 is provided inside the turntable body 403, and a threaded rod 405 is threadedly connected inside the threaded hole 404, and a limit plate 406 is rotatably mounted on the bottom end of the threaded rod 405 through a bearing;

[0042] A sliding rod 407 is installed at the top of the second groove 402, and a sliding sleeve 408 is sleeved on the outer wall of the sliding rod 407. The outer wall of the sliding sleeve 408 is fixedly connected to the outer wall of the threaded rod 405. A handle body 4031 is installed on the outer wall of the turntable body 403, and a protective pad is installed on the outer wall of the handle body 4031.

[0043] A second anti-skid pad 4061 is installed at the bottom end of the limiting plate 406 , and an outer wall of the second anti-skid pad 4061 is installed with anti-skid grooves.

[0044] The specific working principle is that when the steering test mechanism 1 needs to be supported and fixed, it is first threadedly connected through the threaded hole 404 and the threaded rod 405, and through the cooperation of the sliding rod 407 and the sliding sleeve 408, and the turntable body 403 is driven to rotate by rotating the handle body 4031, so that the rotation of the turntable body 403 drives the threaded rod 405 to rise and fall inside the threaded hole 404 through the sliding sleeve 408 and the sliding rod 407, so that the threaded rod 405 can be raised and lowered to drive the limit plate 406 to rise and fall at the same time, so that the limit plate 406 can be raised and lowered to fit the ground, and through the design of the second anti-slip pad 4061, the positioning and fixing effect of the limit plate 406 on the steering test mechanism 1 is better.

[0045] Finally, it should be noted that the above content is only used to illustrate the technical solution of the present invention, rather than to limit the scope of protection of the present invention. Simple modifications or equivalent substitutions of the technical solution of the present invention by ordinary technicians in this field do not deviate from the essence and scope of the technical solution of the present invention.

Claims

1. A small aircraft front landing gear steering test device, characterized in that: include A steering test mechanism (1) comprises a mounting frame (101), a turntable body (104) being rotatably mounted on the top of the steering test mechanism (1) via a bearing, and a first turning rod body (105) being mounted on the bottom of the turntable body (104), a mounting frame (101) being mounted on the top of the steering test mechanism (1), and an aircraft front landing gear body (102) being arranged inside the mounting frame (101), positioning frames (103) being mounted on both ends of the bottom of the mounting frame (101), and a side wall of one end of the positioning frame (103) being A first groove (1031) is provided at the top end, the inner wall of the steering test mechanism (1) supports a plate (107), and a torque sensor (108) is installed at the top end of the support plate (107), a second rotating rod body (109) is installed inside the torque sensor (108), and a second gear body (1010) is installed at the top end of the second rotating rod body (109), a single chip computer (1011) is installed at the inner wall of the steering test mechanism (1), and a display screen body (1012) is installed at the outer wall of the steering test mechanism (1); A positioning and fixing mechanism (2), comprising a first through hole (201), the first through hole (201) being formed on the side walls of the positioning frame (103) and the mounting frame (101), a connecting rod (202) penetrating the mounting frame (101) being arranged inside the first through hole (201), a first positioning plate (203) being mounted on one end of the connecting rod (202), and a second positioning plate (206) being mounted on one end of the connecting rod (202) away from the first positioning plate (203); The rotating mechanism (3) comprises a mounting plate (301), the mounting plate (301) being mounted on the side walls at both ends of the mounting frame (101), a driving motor (302) being mounted on one end of the mounting plate (301), and a driving shaft (303) being mounted on the output end of the driving motor (302) via a coupling, and a cam body (304) being mounted on the outer wall of each of the driving shafts (303); The supporting and fixing mechanism (4) comprises a fixing rod (401), wherein the fixing rod (401) is mounted on the outer wall of the steering test mechanism (1), a second groove (402) is provided inside the fixing rod (401), and a turntable body (403) is rotatably mounted inside the second groove (402) via a ball bearing, a threaded hole (404) is provided inside the turntable body (403), and a threaded rod (405) is threadedly connected inside the threaded hole (404), and a limit plate (406) is rotatably mounted on the bottom end of the threaded rod (405) via a bearing.

2. The small aircraft front landing gear steering test device according to claim 1, characterized in that: A first gear body (106) is installed at the bottom end of the first rotating rod body (105), and the first gear body (106) and the second gear body (1010) are meshed with each other.

3. The small aircraft front landing gear steering test device according to claim 1, characterized in that: A first spring body (205) is installed on the side wall at one end of the interior of the positioning frame (103), and one end of the first spring body (205) is fixedly connected to the side wall of the first positioning plate (203).

4. The small aircraft front landing gear steering test device according to claim 1, characterized in that: The side walls at one end of the second positioning plate (206) are all installed with a second spring body (207), and one end of the second spring body (207) away from the second positioning plate (206) is fixedly connected to the side wall of the positioning frame (103).

5. The small aircraft front landing gear steering test device according to claim 1, characterized in that: A first anti-skid pad (204) is installed at one end of the first positioning plate (203), and the first anti-skid pad (204) and the first positioning plate (203) are a welded integrated structure.

6. The small aircraft front landing gear steering test device according to claim 1, characterized in that: A sliding rod (407) is installed at the top end of the second groove (402), and a sliding sleeve (408) is sleeved on the outer wall of the sliding rod (407), and the outer wall of the sliding sleeve (408) is fixedly connected to the outer wall of the threaded rod (405).

7. The small aircraft front landing gear steering test device according to claim 1, characterized in that: The outer wall of the turntable body (403) is installed with a handle body (4031), and the outer wall of the handle body (4031) is installed with a protective pad.

8. The small aircraft front landing gear steering test device according to claim 1, characterized in that: A second anti-skid pad (4061) is installed at the bottom end of the limiting plate (406), and an outer wall of the second anti-skid pad (4061) is installed with anti-skid patterns.

9. The small aircraft front landing gear steering test device according to claim 1, characterized in that: The output end of the torque sensor (108) is electrically connected to the input end of the single-chip computer (1011) through a wire, and the output end of the single-chip computer (1011) is electrically connected to the input end of the display screen body (1012) through a wire.

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