Fatigue test loading device for main landing gear of helicopter

Abstract

The utility model discloses a fatigue test loading device for a main landing gear of a helicopter, which comprises a base and a support, the support is arranged on the upper surface of the base, the base is provided with a supporting rod clamp used for being fixedly connected with a landing gear supporting rod, and the upper surface of the base is fixedly connected with an X-axis loading device and a Z-axis loading device; a Y-axis loading device is arranged at the top of the bracket; the X-axis loading device, the Z-axis loading device and the Y-axis loading device are respectively provided with a first connecting piece used for being connected with an undercarriage, and the undercarriage is provided with a loading device connecting piece used for being connected with the first connecting piece. The X-axis loading device and the Z-axis loading device which are fixed on the base and the Y-axis loading device which is arranged on the bracket are used for detecting the undercarriage after applying pulling force to the airplane wheel in the three-coordinate direction, and a flaw detection report is made, so that loading in the X direction, the Y direction and the Z direction can be realized.

Description

TECHNICAL FIELD

[0001] The utility model relates to equipment test technical field, concretely is a kind of fatigue test loading device of helicopter main landing gear. BACKGROUND

[0002] Main landing gear is an important component of helicopter structure, specifically, main landing gear is helicopter landing device, plays the role of absorbing energy in landing process in the process of helicopter landing, can reduce the impact effect on helicopter in landing process. Helicopter main landing gear needs to bear alternating load in the process of take-off and landing, and its fatigue performance directly affects the flight safety of helicopter. The loading device of the fatigue test of the existing helicopter main landing gear does not have multi-directional stress alternating loading, mostly uses single plane as loading direction, so that the actual stress condition of landing gear cannot be restored, and more objective fatigue test parameters cannot be obtained. SUMMARY

[0003] The utility model provides a kind of fatigue test loading device of helicopter main landing gear, it is to solve the technical problem that multi-directional alternating stress in prior art cannot be simultaneously detected.

[0004] The utility model provides a kind of fatigue test loading device of helicopter main landing gear, including base and support, the support is set on the upper surface of base, the support rod clamp for fixedly connecting landing gear support rod is provided on the base, the X-axis loading device and Z-axis loading device are fixedly connected on the upper surface of base;The Y-axis loading device is provided at the top of support;The X-axis loading device, the Z-axis loading device and the Y-axis loading device are respectively provided with first connecting piece for connecting landing gear, and landing gear is provided with loading device connecting piece for connecting first connecting piece.

[0005] Further, the structure of the X-axis loading equipment is same with the structure of the Z-axis loading device, including first base and first hydraulic device, the first base is fixedly connected to the edge of the base;The first hydraulic device one end is connected with the first base, and the other end of the first hydraulic device is fixedly connected with the first connecting piece.

[0006] Further, first sensor is connected between each first hydraulic device and corresponding first connecting piece.

[0007] Further, first hinged seat is fixedly connected between each first hydraulic device and the first base.

[0008] Further, the support top is provided with a sliding rail; one end of the sliding rail is provided with a motor, the other end of the sliding rail is provided with a bearing, a lead screw is arranged between the bearing and the motor, the sliding rail is slidingly provided with a sliding sleeve, and the lead screw is arranged in the sliding sleeve; the Y-axis loading device is fixedly connected to the bottom of the sliding sleeve.

[0009] Further, the Y-axis loading device comprises a rigid connecting piece fixedly connected to the bottom of the sliding sleeve, and a second hydraulic device fixedly connected to the bottom of the rigid connecting piece and fixedly connected with the first connecting piece.

[0010] Further, a first sensor is arranged between the second hydraulic device and the first connecting piece.

[0011] Further, the base is further provided with a shock rod testing device, the shock rod testing device comprises a hydraulic machine and a shock rod connecting seat, the hydraulic machine is arranged on the side of the base away from the first hydraulic device, and the shock rod connecting seat is fixedly connected to the output end of the hydraulic machine; a second sensor is fixedly connected between the output end of the hydraulic machine and the shock rod connecting seat.

[0012] Further, the loading device connecting piece comprises a wheel sleeve hoop and a plurality of second connecting pieces integrally formed with the wheel sleeve hoop; the plurality of second connecting pieces are respectively used for connecting the X-axis loading device, the Z-axis loading device and the Y-axis loading device, the wheel sleeve hoop is a semicircular metal hoop, and threaded connecting pieces are arranged at the two ends of the semicircular metal hoop; a first limiting hole is formed in each second connecting piece, a second limiting hole is formed in the first connecting piece, and the first limiting hole and the second limiting hole are fixedly connected.

[0013] The helicopter main landing gear fatigue test loading device has at least the following beneficial effects:

[0014] The helicopter main landing gear fatigue test loading device has at least the following beneficial effects: BRIEF DESCRIPTION OF DRAWINGS

[0015] Figure 1 The helicopter main landing gear fatigue test loading device has at least the following beneficial effects:

[0016] Figure 2This is a schematic diagram of the X-axis loading device of the fatigue testing loading device for helicopter main landing gear provided by this utility model;

[0017] Figure 3 This is a schematic diagram of the Z-axis loading device of the fatigue testing loading device for helicopter main landing gear provided by this utility model;

[0018] Figure 4 This is a schematic diagram of the loading device connector of the fatigue testing loading device for the main landing gear of a helicopter, as described in this utility model.

[0019] Figure 5 This is a schematic diagram of the loading device connector of the fatigue testing loading device for the main landing gear of a helicopter, as described in this utility model.

[0020] In the diagram: 1. Base; 2. Bracket; 21. Column; 22. Crossbeam; 23. Slide rail; 24. Motor; 25. Bearing; 26. Lead screw; 27. Sliding sleeve; 3. X-axis loading device; 31. First base; 32. First hydraulic device; 34. First sensor; 4. Z-axis loading device; 5. Y-axis loading device; 51. Second hydraulic device; 52. Rigid connector; 6. Loading device connector; 61. Wheel sleeve; 62. Second connector; 63. Threaded connector; 64. First limiting hole; 7. First connector; 71. Second limiting hole; 8. Shock absorber test device; 81. Hydraulic press; 82. Second base; 83. Second hinge seat; 84. Baffle; 85. Shock absorber connecting seat. Detailed Implementation

[0021] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0022] The main landing gear of a helicopter generally consists of a support rod, a shock absorber rod, a wheel connection assembly, and wheels.

[0023] Please see Figures 1-5 This utility model provides a fatigue testing loading device for helicopter main landing gear, including a base 1 and a bracket 2 disposed on the upper surface of the base 1. An X-axis loading device 3 and a Z-axis loading device 4 are disposed on the base 1; a Y-axis loading device 5 is disposed on the bracket. The X-axis loading device 3, the Z-axis loading device 4 and the Y-axis loading device 5 are respectively connected to the aircraft wheels through a plurality of first connecting parts 7. A support rod clamp for fixing and connecting support rods is disposed on the base 1.

[0024] Wherein, the X-axis and Z-axis are horizontal directions, the X-axis is along the advancing direction of the landing gear, and the Z-axis is perpendicular to the advancing direction of the landing gear; the mechanism of the X-axis loading device and the Z-axis loading device is the same, and the Y-axis is the direction perpendicular to the X-Y plane.

[0025] The X-axis loading device 3 comprises a first base 31 and a first hydraulic device 32; the first base 31 is arranged on the upper surface of the base 1 near one side edge; the first hydraulic device 32 is movably connected with the first base 31; and the first hydraulic device 32 is fixedly connected with the landing gear through the first connecting piece 7.

[0026] The bracket 2 is provided with a rigid connecting piece 52 at the top, and the Y-axis loading device 5 is fixedly connected to the bottom of the rigid connecting piece 21; the Y-axis loading device 5 comprises a second hydraulic device 51 and a first connecting piece; the second hydraulic device 51 is fixedly connected to the bottom end of the rigid connecting piece 52; and the first connecting piece 7 is fixedly connected to the bottom end of the second hydraulic device 51.

[0027] The machine wheel is provided with a loading device connecting piece 6, the loading device connecting piece 6 comprises a machine wheel sleeve hoop 61 and three second connecting pieces 62 integrally formed with the machine wheel sleeve hoop 61; the three second connecting pieces 62 are respectively used for connecting the X-axis loading device 3, the Z-axis loading device 4 and the Y-axis loading device 5; the machine wheel sleeve hoop 61 is two semicircular metal ring hoops, both ends of the two semicircular metal ring hoops are provided with threaded connecting pieces 63, and the threaded connecting pieces 63 are connected through high-strength screws; each second connecting piece 62 is a connecting piece, a first limiting hole 64 perpendicular to the connecting piece is formed in the connecting piece, the first connecting piece 7 is a connecting piece provided with a second limiting hole 71, and when the first limiting hole 64 and the second limiting hole 71 coincide, they are fixedly connected through a limiting screw pin; one of the second connecting pieces 62 is arranged at the top of the machine wheel sleeve hoop 61, one of the second connecting pieces 62 is arranged on the side wall in the rotating direction of the machine wheel sleeve hoop 61; one of the second connecting pieces 62 is arranged at the center of the circle and coincides with the machine wheel rotating shaft, and two thinner connecting pieces are arranged at the abutting positions of the two semicircular metal ring hoops.

[0028] The landing gear is detected by applying a pulling force to the machine wheel in the three-coordinate direction through the X-axis loading device 3 and the Z-axis loading device 4 fixed on the base 1 and the Y-axis loading device 5 arranged on the bracket, and a flaw detection report is made.

[0029] As an example, the first base 31 and the first hydraulic device 32 are connected through the first hinge seat. When the Y-axis loading device 5 exerts an upward pulling force on the wheel, it will cause a small upward displacement of the wheel. By adding the first hinge seat to the X-axis loading device 3 and the Z-axis loading device 4, the X-axis loading device and the Z-axis loading device are prevented from being damaged or generating errors due to the pulling force.

[0030] As an optional embodiment, the first connecting piece 7 and the first hydraulic device 32 are provided with a first sensor 34, and the second hydraulic device 51 and the first connecting piece 7 are connected with the first sensor 34. The first sensor 34 is a tension sensor for monitoring the pulling force value of the first hydraulic device 34 and the second hydraulic device 51 in real time.

[0031] As an optional embodiment, the support 2 includes a support column 21 arranged at the four corners of the base 1 and a cross beam 22 arranged at the top end of the support column 21. The two cross beams 22 are provided with a sliding rail 23, one of the cross beams 22 is provided with a motor 24 at the top end, and the other cross beam 22 is provided with a bearing 25 at the top end. A lead screw 26 is arranged between the bearing 25 and the motor 24. The sliding rail 23 is provided with a sliding sleeve 27, and the sliding rail 23 and the sliding sleeve 27 can slide relative to each other. The sliding sleeve 27 is provided with a threaded hole at the top, and the lead screw 26 is arranged in the threaded hole. The rigid connecting piece 52 is fixedly connected to the bottom of the sliding sleeve 27.

[0032] As an example:

[0033] The base 1 is also provided with a shock rod testing device 8, which includes a hydraulic machine 81, a second base 82, a second hinge seat 83, a baffle 84, and a shock rod connecting seat 85. The second base 82 is arranged on the side of the base 1 away from the first hydraulic device 32. The second hinge seat 83 is arranged at the top of the second base 82. The hydraulic machine 81 is fixedly connected to the second base 82 through the second hinge seat 83. The baffle 84 is hinged to the second hinge seat 83. The baffle 4 is arranged between the second base 82 and the hydraulic machine 81 for supporting the hydraulic machine 81 facing the shock rod. The shock rod connecting seat 85 is fixedly connected to the output end of the hydraulic machine 81. The shock rod is pressed by the hydraulic machine.

[0034] As an optional embodiment:

[0035] A second sensor is fixedly connected between the output end of the hydraulic machine 81 and the shock rod connecting seat 85. The second sensor is a pressure sensor for detecting the pressure value of the hydraulic machine 81 in real time.

Claims

1. A fatigue test loading device for a main landing gear of a helicopter, comprising a base (1) and a support (2) arranged on the upper surface of the base (1), the base (1) being provided with a support rod clamp for fixedly connecting a support rod of the landing gear, characterized in that, The bottom base (1) upper surface is fixedly connected with X-axis loading device (3) and Z-axis loading device (4), the support (2) top is provided with Y-axis loading device (5), the X-axis loading device (3), the Z-axis loading device (4) and the Y-axis loading device (5) are provided with first connecting piece (7) for connecting landing gear respectively, landing gear is provided with loading device connecting piece (6) for connecting first connecting piece (7).

2. A fatigue test loading device for a helicopter main landing gear as claimed in claim 1, characterised in that, The structure of the X-axis loading device (3) and the structure of the Z-axis loading device (4) are same, including first base (31) and first hydraulic device (32), the first base (31) is fixedly connected to the edge of the bottom base (1), one end of the first hydraulic device (32) is connected with the first base (31), the other end of the first hydraulic device (32) is fixedly connected with the first connecting piece (7).

3. A fatigue test loading device for a helicopter main landing gear as claimed in claim 2, characterised in that, Each first hydraulic device (32) is connected with corresponding first connecting piece (7) between the first sensor (34).

4. A fatigue test loading device for a helicopter main landing gear as claimed in claim 3, characterised in that, Each first hydraulic device (32) is fixedly connected with the first base (31) between the first hinge seat.

5. The fatigue test loading device for a helicopter main landing gear according to claim 1, wherein The support (2) top is provided with slide rail (23), one end of the slide rail (23) is provided with motor (24), the other end of the slide rail (23) is provided with bearing (25), the bearing (25) and the motor (24) are provided with screw rod (26) between, the slide rail (23) is slidably provided with slide sleeve (27), the screw rod (26) is provided in slide sleeve (27), the Y-axis loading device (5) is fixedly connected to the bottom of the slide sleeve (27).

6. A fatigue test loading device for a helicopter main landing gear as claimed in claim 5, characterised in that, The Y-axis loading device (5) includes rigid connecting piece (52) fixedly connected to the bottom of the slide sleeve (27), the rigid connecting piece (52) bottom is fixedly connected with second hydraulic device (51), the second hydraulic device (51) bottom is fixedly connected with the first connecting piece (7).

7. A fatigue test loading device for a helicopter main landing gear as claimed in claim 6, characterised in that, The first sensor (34) is provided between the second hydraulic device (51) and the first connecting piece (7).

8. The fatigue test loading device for a helicopter main landing gear according to claim 1, characterized in that, The bottom base (1) is further provided with shock rod testing device (8), the shock rod testing device (8) includes hydraulic machine (81) and shock rod connecting seat (85), the hydraulic machine (81) is arranged on the side of the bottom base (1) away from the first hydraulic device (32), the shock rod connecting seat (85) is fixedly connected to the output end of the hydraulic machine (81), the second sensor (86) is fixedly connected between the output end of the hydraulic machine (81) and the shock rod connecting seat (85).

9. The fatigue test loading device for a helicopter main landing gear according to claim 1, characterized in that, The loading device connector (6) comprises a wheel sleeve (61) and a plurality of second connectors (62) integrally formed with the wheel sleeve (61); the plurality of second connectors (62) are respectively used for connecting the X-axis loading device (3), the Z-axis loading device (4) and the Y-axis loading device (5), the wheel sleeve (61) is a semicircular metal ring, and both ends of the semicircular metal ring are provided with threaded connectors (63); a first limiting hole (64) is formed in each second connector (62), the first connector (7) is provided with a second limiting hole (71), and the first limiting hole (64) and the second limiting hole (71) are fixedly connected.

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