Device and method for testing starting force and rotating force parameters of automatic inclinator of helicopter

Abstract

The invention discloses a helicopter automatic inclinator starting force and rotating force parameter testing device and method, and the device comprises a fixing system which comprises a supporting table plate; the centering system comprises a centering shaft; the supporting arm comprises a front-end connecting rod, a middle-end connecting rod, a rear-end connecting rod and a tooth-shaped mechanism, and the front-end connecting rod is slidably connected with a torque bolt; the rotating system comprises a mounting frame fixed to the bottom face of the supporting table plate, a speed reducer is mounted on the mounting frame, an input shaft of the speed reducer is fixedly connected with a motor, a center rotating shaft is rotationally connected to the bottom of a shaft hole in the centering shaft, and the center rotating shaft is connected with an output shaft of the speed reducer through a torque sensor. The testing device is simple in structure and convenient to operate, the helicopter automatic inclinator is driven by the rotating system and the supporting arm to conduct starting torque and rotating torque parameter testing, the torque direction and value accuracy can be improved, and a more accurate basis is provided for performance evaluation of the helicopter automatic inclinator.

Description

Technical Field

[0001] The invention relates to the technical field of helicopter inclinometer performance testing, in particular to a helicopter automatic inclinometer starting force and rotation force parameter testing device and method. Background Art

[0002] The automatic tilt mechanism is an important component of helicopter control and is crucial to the flight stability and maneuverability of the helicopter. The automatic tilt mechanism adjusts the helicopter's attitude to achieve flight adjustments, making the helicopter highly flexible and maneuverable. The performance of the automatic tilt mechanism directly affects the flight safety of the helicopter. However, the current automatic tilt mechanism starting force and rotation force tests rely on manual operation, and the test results are easily affected by the traction force direction and speed, resulting in poor consistency in its starting / rotation torque performance.

[0003] Based on the above technical problems, the present invention provides a helicopter automatic tilt device starting force and rotation force parameter testing device and method Summary of the invention

[0004] The purpose of the present invention is to provide a device and method for testing the parameters of the starting force and the rotational force of an automatic tilt device of a helicopter, so as to solve the problems existing in the prior art.

[0005] To achieve the above object, the present invention provides the following solution: The present invention provides a helicopter automatic tilt device starting force and rotation force parameter testing device, comprising:

[0006] A fixing system, the fixing system comprising a supporting table top, a top surface of the supporting table top having a plurality of fixing components installed at equal intervals in the circumferential direction;

[0007] A centering system, the centering system comprising a centering shaft fixedly connected to the center position of the supporting table board, and an axis hole is opened at the center position of the centering shaft;

[0008] The support arm comprises a front connecting rod, a middle connecting rod, a rear connecting rod and a toothed mechanism, wherein the toothed mechanism is rotatably connected to the top end of the shaft hole, the front connecting rod and the rear connecting rod are rotatably connected to the two ends of the middle connecting rod respectively, the other end of the rear connecting rod is rotatably connected to the toothed mechanism, and a torque pin is slidably connected to the front connecting rod;

[0009] A rotation system, the rotation system includes a mounting frame fixed to the bottom surface of the support table top, a reducer is installed on the mounting frame, the reducer input shaft is fixedly connected to a motor, the bottom of the shaft hole on the centering shaft is rotatably connected to a central shaft, the central shaft is connected to the reducer output shaft through a torque sensor, the reducer is fixed to the mounting frame through a fixing member, and the central shaft is axially connected to the toothed mechanism;

[0010] Among them, locking components are respectively arranged between the front end connecting rod and the torque pin, between the front end connecting rod and the middle end connecting rod, between the rear end connecting rod and the middle end connecting rod, and between the rear end connecting rod and the toothed mechanism.

[0011] According to the helicopter automatic inclinator starting force and rotational force parameter testing device provided by the present invention, three groups of first ribs are fixedly connected to the outer wall of the centering shaft, the three groups of first ribs are fixed on the outer wall of the centering shaft at equal intervals in the circumferential direction, and the first ribs are fixedly connected to the supporting table board.

[0012] According to the helicopter automatic recliner starting force and rotational force parameter testing device provided by the present invention, the fixing assembly includes second ribs, and the second ribs are provided in twelve groups. The twelve groups of the second ribs are axially fixed at equal intervals on the top surface of the support table board, and the second ribs are limitedly matched with the lower end surface of the fixed ring of the automatic recliner.

[0013] According to the helicopter automatic inclinator starting force and rotational force parameter testing device provided by the present invention, the mounting frame includes a fixed plate, and side mounting plates are vertically fixedly connected to both sides of the top surface of the fixed plate, the side mounting plates are fixedly connected to the bottom surface of the supporting table board, and reinforcing ribs are arranged between the supporting table board and the side mounting plates.

[0014] According to the helicopter automatic tilt device starting force and rotation force parameter testing device provided by the present invention, the fixing member includes a positioning plate, the fixing plate is fixedly connected to a fixing block, and the fixing plate is fixedly connected to the fixing block.

[0015] According to the helicopter automatic tilt device starting force and rotation force parameter testing device provided by the present invention, a protective cover is installed on the central rotating shaft.

[0016] According to the helicopter automatic inclinator starting force and rotational force parameter testing device provided by the present invention, a through hole is opened at the center of the support table, a bearing is installed in the through hole, and the central rotating shaft is fixed to the bearing.

[0017] A method for testing the parameters of the starting force and rotational force of an automatic tilt device of a helicopter comprises the following steps;

[0018] S1, the front connecting rod, the middle connecting rod and the rear connecting rod of the supporting arm are kept parallel to the supporting table board, the torque pin is perpendicular to the supporting table board, and the motor is in a stopped state;

[0019] S2, drive the motor to run, making the speed reducer run at V redu , the running time is set to 301s, and the reducer drives the arm to rotate through the central shaft;

[0020] S3, record the data T output by the torque sensort1 ;

[0021] S4. According to the distance between the tested automatic tilter shoulder fork ear and the center of the automatic tilter, adjust the distance between the front connecting rod, the middle connecting rod, and the rear connecting rod so that the torque pin can be inserted between the two fork ears of the automatic tilter shoulder;

[0022] S5, drive the motor to run, so that the speed of the reducer is V redu , the running time is set to 300s; record the data T output by the torque sensor t2 ;

[0023] S6, calculating the automatic tilt device starting force parameter according to the following formula:

[0024] SF=T t2 -T t1 ;

[0025] The automatic tilt mechanism rotation force parameters are calculated according to the following formula:

[0026] RF=(∑(T t2 -T t1 )) / 300;

[0027] Among them, SF is the starting force parameter, RF is the rotation force parameter; T t1 is the no-load output torque value (t1 = 1 ~ 301s), T t2 is the torque value output by the load (t2=1~301s).

[0028] The present invention discloses the following technical effects:

[0029] When the present invention is working, first the support arm is in a no-load state, the motor drives the reducer to output the rotation speed, and at the same time drives the support arm to rotate through the central shaft, and obtains the data of the torque sensor in the no-load state, and then connects the torque pin to the automatic inclinometer to obtain the value of the torque sensor in the load state, and calculates the rotation force parameters and starting force parameters of the automatic inclinometer through the two data.

[0030] The invention has a simple structure and is easy to operate. It drives the helicopter automatic tilt device to perform starting torque and rotation torque parameter tests through a rotating system and a support arm, thereby improving the torque direction and numerical accuracy, and providing a more accurate basis for the performance evaluation of the helicopter automatic tilt device. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0032] Figure 1 The structure of the helicopter automatic tilt device starting force and rotation force parameter test device of the present invention is shown in FIG. Figure I ;

[0033] Figure 2 The structure of the helicopter automatic tilt device starting force and rotation force parameter test device of the present invention is shown in FIG. Figure II ;

[0034] Figure 3 It is a structural schematic diagram of the support arm of the present invention;

[0035] Figure 4 It is a structural schematic diagram of the rotation system of the present invention;

[0036] Figure 5 It is a structural schematic diagram of the centering system of the present invention;

[0037] Figure 6 It is a schematic structural diagram of the holding system of the present invention.

[0038] Among them, 1. Support table; 2. Centering shaft; 3. Shaft hole; 4. Front end connecting rod; 5. Middle end connecting rod; 6. Rear end connecting rod; 7. Tooth mechanism; 8. Torque pin; 9. Reducer; 10. Motor; 11. Center shaft; 12. Torque sensor; 13. Locking member; 14. First rib; 15. Second rib; 16. Fixed plate; 17. Side mounting plate; 18. Reinforcing rib; 19. Positioning plate; 20. Fixed block; 21. Protective cover; 22. Bearing. DETAILED DESCRIPTION

[0039] 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.

[0040] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0041] Reference Figure 1-Figure 6The present invention provides a helicopter automatic tilt device starting force and rotation force parameter testing device, comprising:

[0042] The fixing system includes a support table 1, and a plurality of fixing components are installed at equal intervals on the top surface of the support table 1;

[0043] A centering system, the centering system comprises a centering shaft 2 fixedly connected to the center position of the supporting table board 1, and an axis hole 3 is opened at the center position of the centering shaft 2;

[0044] The support arm includes a front connecting rod 4, a middle connecting rod 5, a rear connecting rod 6 and a toothed mechanism 7. The toothed mechanism 7 is rotatably connected to the top of the shaft hole 3. The front connecting rod 4 and the rear connecting rod 6 are rotatably connected to the two ends of the middle connecting rod 5 respectively. The other end of the rear connecting rod 6 is rotatably connected to the toothed mechanism 7. The front connecting rod 4 is slidably connected to a torque pin 8.

[0045] The rotation system includes a mounting frame fixed to the bottom surface of the support table 1, a reducer 9 is mounted on the mounting frame, a motor 10 is fixedly connected to the input shaft of the reducer 9, a central rotating shaft 11 is rotatably connected to the bottom of the shaft hole 3 on the centering shaft 2, the central rotating shaft 11 is connected to the output shaft of the reducer 9 through a torque sensor 12, the reducer 9 is fixed to the mounting frame through a fixing member, and the central rotating shaft 11 is axially connected to the toothed mechanism 7;

[0046] Among them, locking components 13 are respectively arranged between the front end connecting rod 4 and the torque pin 8, between the front end connecting rod 4 and the middle end connecting rod 5, between the rear end connecting rod 6 and the middle end connecting rod 5, and between the rear end connecting rod 6 and the gear mechanism 7.

[0047] In this embodiment, the locking member 13 is selected according to actual needs. A spiral adjustable type is adopted between the middle-end connecting rod 5 and the front-end connecting rod 4 and the rear-end connecting rod 6, which can adjust the friction between the middle-end connecting rod 5 and the front-end connecting rod 4 and the rear-end connecting rod 6, thereby ensuring the connection stability between the two. A bolt locking method is adopted between the front-end connecting rod 4 and the torque pin 8. A sliding connection is adopted between the torque pin 8 and the front-end connecting rod 4. A sliding groove is provided on the torque pin 8, and a shrinkage seam is provided on the top of the sliding groove. The compression of the shrinkage seam is controlled by bolts, thereby ensuring the connection stability between the torque pin 8 and the front-end connecting rod 4.

[0048] When the present invention is working, first the support arm is in a no-load state, the motor 10 drives the reducer 9 to output the rotation speed, and at the same time drives the support arm to rotate through the central shaft 11, and obtains the data of the torque sensor 12 in the no-load state, and then connects the torque pin 8 to the automatic recliner to obtain the value of the torque sensor 12 in the load state, and calculates the rotation force parameters and starting force parameters of the automatic recliner through the two data.

[0049] The invention has a simple structure and is easy to operate. It drives the helicopter automatic tilt device to perform starting torque and rotation torque parameter tests through a rotating system and a support arm, thereby improving the torque direction and numerical accuracy, and providing a more accurate basis for the performance evaluation of the helicopter automatic tilt device.

[0050] According to a further optimization scheme, three groups of first ribs 14 are fixedly connected to the outer wall of the centering shaft 2 . The three groups of first ribs 14 are fixed on the outer wall of the centering shaft 2 at equal intervals in the circumferential direction. The first ribs 14 are fixedly connected to the supporting table top 1 .

[0051] According to a further optimized solution, the fixing assembly includes second ribs 15, and twelve groups of second ribs 15 are provided. The twelve groups of second ribs 15 are axially fixed to the top surface of the supporting table top 1 at equal intervals, and the second ribs 15 are limitedly matched with the lower end surface of the fixed ring of the automatic tilt device.

[0052] According to a further optimized solution, the mounting frame includes a fixing plate 16 , and side mounting plates 17 are vertically fixedly connected to both sides of the top surface of the fixing plate 16 . The side mounting plates 17 are fixedly connected to the bottom surface of the supporting table board 1 , and reinforcing ribs 18 are provided between the supporting table board 1 and the side mounting plates 17 .

[0053] According to a further optimized solution, the fixing member includes a positioning plate 19 , a fixing block 20 is fixedly connected to the fixing plate 16 , and the fixing plate 16 is fixedly connected to the fixing block 20 .

[0054] According to a further optimized solution, a protective cover 21 is installed on the central rotating shaft 11 .

[0055] According to a further optimized solution, a through hole is provided at the center of the support table top 1 , a bearing 22 is installed in the through hole, and the center shaft 11 is fixed to the bearing 22 .

[0056] A method for testing the parameters of the starting force and rotational force of an automatic tilt device of a helicopter comprises the following steps;

[0057] S1, the front connecting rod 4, the middle connecting rod 5, and the rear connecting rod 6 in the supporting arm are kept parallel to the supporting table board 1, the torque pin 8 is perpendicular to the supporting table board 1, and the motor 10 is in a stopped state;

[0058] S2, drive motor 10 to run, so that reducer 9 runs at a speed of V redu , the running time is set to 301s, and the reducer 9 drives the support arm to rotate through the central shaft 11;

[0059] S3, record the data T output by the torque sensor 12 t1 ;

[0060] S4. According to the distance between the tested automatic tilter shoulder fork ear and the center of the automatic tilter, adjust the distance between the front connecting rod 4, the middle connecting rod 5, and the rear connecting rod 6 so that the torque pin 8 can be inserted between the two fork ears of the automatic tilter shoulder;

[0061] S5, drive motor 10 to run, so that reducer 9 runs at a speed of V redu , the running time is set to 300s; record the data T output by the torque sensor 12 t2 ;

[0062] S6, calculating the automatic tilt device starting force parameter according to the following formula:

[0063] SF=T t2 -T t1 ;

[0064] The automatic tilt mechanism rotation force parameters are calculated according to the following formula:

[0065] RF=(∑(T t2 -T t1 )) / 300;

[0066] Among them, SF is the starting force parameter, RF is the rotation force parameter; T t1 is the no-load output torque value (t1 = 1 ~ 301s), T t2 is the torque value output by the load (t2=1~301s).

[0067] In the description of the present invention, it should be understood that the terms "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside" and "outside" etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present invention.

[0068] The embodiments described above are only descriptions of the preferred modes of the present invention, and are not intended to limit the scope of the present invention. Without departing from the design spirit of the present invention, various modifications and improvements made to the technical solutions of the present invention by ordinary technicians in this field should all fall within the protection scope determined by the claims of the present invention.

Claims

1. A helicopter automatic tilt device starting force and rotation force parameter test device, characterized in that: include: A fixing system, the fixing system comprising a supporting table top (1), a top surface of the supporting table top (1) being provided with a plurality of fixing components at equal intervals in the circumferential direction; A centering system, the centering system comprising a centering shaft (2) fixedly connected to the center position of the supporting table top (1), and an axis hole (3) is provided at the center position of the centering shaft (2); A support arm, the support arm comprises a front end connecting rod (4), a middle end connecting rod (5), a rear end connecting rod (6) and a toothed mechanism (7), the toothed mechanism (7) is rotatably connected to the top end of the shaft hole (3), the front end connecting rod (4) and the rear end connecting rod (6) are rotatably connected to the two ends of the middle end connecting rod (5), the other end of the rear end connecting rod (6) is rotatably connected to the toothed mechanism (7), and a torque pin (8) is slidably connected to the front end connecting rod (4); A rotation system, the rotation system comprising a mounting frame fixed to the bottom surface of the support table (1), a reducer (9) being mounted on the mounting frame, the input shaft of the reducer (9) being fixedly connected to a motor (10), the bottom of the shaft hole (3) on the centering shaft (2) being rotatably connected to a central rotating shaft (11), the central rotating shaft (11) being connected to the output shaft of the reducer (9) via a torque sensor (12), the reducer (9) being fixed to the mounting frame via a fixing member, and the central rotating shaft (11) being axially connected to the toothed mechanism (7); Wherein, locking components (13) are respectively arranged between the front end connecting rod (4) and the torque pin (8), between the front end connecting rod (4) and the middle end connecting rod (5), between the rear end connecting rod (6) and the middle end connecting rod (5), and between the rear end connecting rod (6) and the toothed mechanism (7).

2. The helicopter automatic tilt device starting force and rotation force parameter testing device according to claim 1 is characterized in that: The outer wall of the centering shaft (2) is fixedly connected with three groups of first ribs (14), and the three groups of first ribs (14) are fixed on the outer wall of the centering shaft (2) at equal intervals in the circumferential direction, and the first ribs (14) are fixedly connected to the supporting table top (1).

3. The helicopter automatic tilt device starting force and rotation force parameter testing device according to claim 1, characterized in that: The fixing assembly comprises second ribs (15), and the second ribs (15) are provided in twelve groups. The twelve groups of the second ribs (15) are axially fixed at equal intervals on the top surface of the supporting table board (1), and the second ribs (15) are limitedly matched with the lower end surface of the fixed ring of the automatic tilt device.

4. The helicopter automatic tilt device starting force and rotation force parameter testing device according to claim 1, characterized in that: The mounting frame comprises a fixing plate (16), and side mounting plates (17) are vertically fixedly connected to both sides of the top surface of the fixing plate (16); the side mounting plates (17) are fixedly connected to the bottom surface of the supporting table board (1), and reinforcing ribs (18) are provided between the supporting table board (1) and the side mounting plates (17).

5. The helicopter automatic tilt device starting force and rotation force parameter testing device according to claim 4 is characterized in that: The fixing member comprises a positioning plate (19), a fixing block (20) is fixedly connected to the fixing plate (16), and the fixing plate (16) is fixedly connected to the fixing block (20).

6. The helicopter automatic tilt device starting force and rotation force parameter testing device according to claim 1, characterized in that: A protective sleeve (21) is installed on the central rotating shaft (11).

7. The helicopter automatic tilt device starting force and rotation force parameter testing device according to claim 1, characterized in that: A through hole is provided at the center of the support table top (1), a bearing (22) is installed in the through hole, and the central rotating shaft (11) is fixed to the bearing (22).

8. A method for testing the starting force and rotational force parameters of a helicopter automatic tilt mechanism, based on a device for testing the starting force and rotational force parameters of a helicopter automatic tilt mechanism according to any one of claims 1 to 7, characterized in that: The method comprises the following steps: S1, the front connecting rod (4), the middle connecting rod (5), and the rear connecting rod (6) in the supporting arm are kept parallel to the supporting table board (1), the torque pin (8) is perpendicular to the supporting table board (1), and the motor (10) is in a stopped state; S2, drive motor (10) to run, so that reducer (9) runs at a speed of V redu , the running time is set to 301s, and the reducer (9) drives the support arm to rotate through the central shaft (11); S3, recording the data T output by the torque sensor (12) t1 ; S4, according to the distance between the tested automatic tilter shoulder fork ear and the center of the automatic tilter, adjust the distance between the front connecting rod (4), the middle connecting rod (5), and the rear connecting rod (6) so that the torque pin (8) can be inserted between the two fork ears of the automatic tilter shoulder; S5, the driving motor (10) is running, so that the speed reducer (9) runs at a speed of V redu , the running time is set to 300s; record the data T output by the torque sensor (12) t2 ; S6, calculating the automatic tilt device starting force parameter according to the following formula: SF=T t2 -T t1 ; The automatic tilt mechanism rotation force parameters are calculated according to the following formula: RF=(∑(T t2 -T t1 )) / 300; Among them, SF is the starting force parameter, RF is the rotation force parameter; T t1 is the no-load output torque value (t1 = 1 ~ 301s), T t2 is the torque value output by the load (t2=1~301s).

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