A high cycle fatigue test device for the tail horizontal shaft of a helicopter transmission system

Abstract

The present invention discloses a high-cycle fatigue test device for the tail horizontal axis of a helicopter transmission system, comprising: a vibration table, a tabletop articulated transition section, a loading end fixed support, a main beam, a torsion locking device, a ground articulated transition section and a ground support seat, wherein the main beam has a mounting end and a transmission end; the ground articulated transition section is installed on a side of the bottom of the main beam close to the mounting end, and is connected to the ground support seat; the tabletop articulated transition section is installed on a side of the bottom of the main beam close to the transmission end, and is connected to the vibration table; the torsion locking device is installed on a side of the top of the main beam close to the mounting end, and is used to support an axial end of the tail horizontal axis; in the present invention, the tabletop articulated transition section and the ground articulated transition section are both connected in a hinged manner, and only transmit force in the excitation direction of the vibration table, so that the gravity of the test piece and the test device will not generate an overturning moment on the vibration table.

Description

Technical Field

[0001] The invention belongs to the technical field of tail horizontal shaft high cycle fatigue testing, and in particular relates to a tail horizontal shaft high cycle fatigue testing device for a helicopter transmission system. Background Art

[0002] The tail shaft of a helicopter's transmission system is a critical component, frequently subjected to alternating loads. Vibration fatigue testing of the tail shaft is used to determine its fatigue life under varying alternating loads, or to determine its fatigue limit within a specified lifespan. It can also be used for failure analysis and verification of design improvements.

[0003] When performing a vibration fatigue test on the tail shaft of a helicopter transmission system using a conventional fatigue test fixture on a vibration table, the length of the tail shaft far exceeds the table size. This generates a considerable overturning moment during the test, distorting the output waveform and even damaging the table. Furthermore, conventional fatigue test fixtures are unable to simulate the working environment of the tail shaft, resulting in the failure to obtain fatigue test results under the working conditions of the tail shaft. Summary of the Invention

[0004] In order to overcome the above-mentioned defects in the prior art, the present invention aims to solve the problem that the vibration table generates a considerable overturning moment during the horizontal axis vibration fatigue test. To achieve the above-mentioned object, the present invention provides the following technical solutions:

[0005] A high-cycle fatigue test device for the tail horizontal axis of a helicopter transmission system comprises: a vibration table, a tabletop articulated transition section, a loading end fixed support, a main beam, a torsion locking device, a ground articulated transition section, and a ground support seat, wherein the main beam has a mounting end and a transmission end;

[0006] The ground hinged transition section is installed on one side of the bottom of the main beam close to the installation end and is connected to the ground support seat;

[0007] The table top hinged transition stage is installed on the bottom of the main beam near the transmission end and is connected to the vibration table;

[0008] The twist locking device is installed on one side of the top of the main beam close to the mounting end, and is used to support an axial end of the tail horizontal shaft;

[0009] The loading end fixed support is installed on one side of the top of the main beam close to the transmission end, and is used to support an axial end of the tail horizontal shaft;

[0010] The vibration table is used to provide vibration force to the tail horizontal axis.

[0011] Furthermore, the table top articulated transition section includes: a table top transition section and an articulated seat, the table top transition section is rotatably connected to the articulated seat; the table top transition section is fixedly connected to the vibration table, and the articulated seat is fixedly connected to the main beam.

[0012] Furthermore, the loading end fixed support includes: a fixed support and an adapter flange, the fixed support is fixedly connected to the main beam, and the adapter flange is connected to an axial end of the tail horizontal axis.

[0013] Furthermore, the twist locking device is also used to apply torque to the tail horizontal shaft.

[0014] Furthermore, the twist locking device comprises: a twist support, a twist mandrel and an adapter flange, wherein the twist mandrel is rotatably mounted on the twist support, and the twist mandrel is fixedly connected to the adapter flange;

[0015] The torsion support is fixedly connected to the main beam, and the adapter flange is fixedly connected to the tail horizontal shaft.

[0016] Furthermore, the twist locking device further comprises: a pin for fixedly connecting the twist mandrel and the twist support.

[0017] Furthermore, the pin has two predetermined positions; in one predetermined position, the relative positions of the twisting mandrel and the twisting support are fixed; in the other predetermined position, the twisting mandrel can rotate in the twisting support.

[0018] Furthermore, the articulated transition section includes: a fixed seat, a transition ear and a transition seat, the transition seat is fixedly connected to the ground support seat, the fixed seat is fixedly connected to the main beam, the transition ear is installed on the fixed seat, the transition seat is provided with an transition sleeve, and the transition ear is rotatably connected to the transition sleeve.

[0019] Furthermore, the articulated transition section also includes: a vibration seat and a vibration adapter seat, the vibration adapter seat is arranged on one side of the fixed seat and fixedly connected, a pin shaft is installed on the vibration adapter seat, the vibration seat is fixedly connected to the pin shaft, and a limiting groove is provided in the adapter sleeve, and the two ends of the vibration seat are respectively located in the limiting grooves on both sides thereof.

[0020] Furthermore, the pin shaft is rotatably connected to the vibration adapter.

[0021] The technical effects and advantages of the present invention are as follows:

[0022] In the present invention, the tabletop hinged transition section and the ground hinged transition section are both connected by hinges, which only transmit the force in the excitation direction of the vibration table, so that the gravity of the test piece and the test device will not generate an overturning moment on the vibration table.

[0023] Other features and advantages of the present invention will be described in the following description, and in part will become apparent from the description, or will be understood by practicing the present invention. The purpose and other advantages of the present invention can be realized and obtained by the structures pointed out in the description and the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 This is a schematic structural diagram of a high-cycle fatigue test device for the tail horizontal shaft of a helicopter transmission system according to the present invention;

[0025] Figure 2 This is a schematic structural diagram of a tabletop articulated transition section in a high-cycle fatigue test device for a tail horizontal shaft of a helicopter transmission system according to the present invention;

[0026] Figure 3 The present invention is a schematic structural diagram of a loading end fixed support in a high cycle fatigue test device for a tail horizontal shaft of a helicopter transmission system.

[0027] Figure 4 The present invention is a schematic structural diagram of a torsion locking device in a high-cycle fatigue test device for a tail horizontal shaft of a helicopter transmission system.

[0028] Figure 5 The present invention is a schematic structural diagram of a ground articulated transition section in a high-cycle fatigue test device for a tail horizontal shaft of a helicopter transmission system.

[0029] In the figure: 1-vibration table, 2-table top articulated transition section, 3-loading end fixed support, 4-tail horizontal axis, 5-main beam, 6-torsion locking device, 7-ground articulated transition section, 8-ground support seat, 9-table top transition section, 10-pin, 11-articulated seat 11, 12-fixed support, 13-adaptation flange, 14-torsion support, 15-torsion mandrel, 16-adaptation flange, 17-fixed seat, 18-adaptation ear, 19-pin, 20-adaptation sleeve, 21-vibration seat, 22-adaptation seat, 23-pin, 24-vibration adapter. DETAILED DESCRIPTION

[0030] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. 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 making creative efforts are within the scope of protection of the present invention.

[0031] In addition, in the present invention, the terms "first", "second" and other similar words are not intended to imply any order, quantity and importance, but are only used to distinguish different elements.

[0032] In this embodiment, a high-cycle fatigue test device for the tail horizontal axis of a helicopter transmission system is disclosed, comprising: a vibration table 1, a tabletop articulated transition section 2, a loading end fixed support 3, a main beam 5, a torsion locking device 6, a ground articulated transition section 7 and a ground support seat 8, wherein the main beam 5 has a mounting end and a transmission end; the ground articulated transition section 7 is installed on the side of the bottom of the main beam 5 close to the mounting end, and is connected to the ground support seat 8; the tabletop articulated transition section 2 is installed on the side of the bottom of the main beam 5 close to the transmission end, and is connected to the vibration table 1; the torsion locking device 6 is installed on the side of the top of the main beam 5 close to the mounting end, for supporting an axial end of the tail horizontal axis 4, and for applying torque to one end of the tail horizontal axis 4; the loading end fixed support 3 is installed on the side of the top of the main beam 5 close to the transmission end, for supporting an axial end of the tail horizontal axis 4; the vibration table 1 is used to provide vibration force to the tail horizontal axis 4.

[0033] Specifically:

[0034] One end of the main beam 5 is mounted on 8 via 7, and the other end of the main beam 5 is mounted on the vibration table 1 via 2. The main beam 5 is equipped with a loading-end fixed support 3 and a torsion locking device 6. These support 3 and the torsion locking device 6 secure the tail horizontal shaft 4, thereby generating a vibration torque through the vibration table 1 for vibration fatigue testing. The vibration torque generated by the vibration table 1 is transmitted sequentially through the tabletop hinged transition section 2, the main beam 5, and the loading-end fixed support 3, ultimately to one end of the tail horizontal shaft 4.

[0035] Further, see Figure 2 In one embodiment of the present invention, the table top articulated transition section 2 includes: a table top transition section 9 and an articulated seat 11, the table top transition section 9 and the articulated seat 11 are rotatably connected via a pin shaft 10; the table top transition section 9 is fixedly connected to the vibration table 1, and the articulated seat 11 is fixedly connected to the main beam 5; generally, the above three fixed connections are all made by bolts.

[0036] Further, see Figure 3 In one embodiment of the present invention, the loading end fixed support 3 includes: a fixed support 12 and an adapter flange 13, the fixed support 12 is fixedly connected to the adapter flange 13, the fixed support 12 is fixedly connected to the main beam 5, and the adapter flange 13 is connected to an axial end of the tail horizontal axis 4.

[0037] Further, see Figure 4 In one embodiment of the present invention, the twist locking device 6 is further used to apply torque to the tail horizontal shaft 4, specifically:

[0038] The torsion locking device 6 includes: a torsion support 14, a torsion mandrel 15 and an adapter flange 16, wherein the torsion support 14 is fixedly mounted on the main beam 5, the adapter flange 16 is fixedly connected to the tail horizontal shaft 4, the torsion mandrel 15 is rotatably mounted on the torsion support 14, and the torsion mandrel 15 is fixedly connected to the adapter flange 16; the torsion mandrel 15 is fixedly connected to the torsion support 14 by a pin, and the torsion mandrel 15 has several angular positions; when the torsion mandrel 15 is at each angular position, different magnitudes of torque are applied to the tail horizontal shaft 4 accordingly; and when the torsion mandrel 15 is at each angular position, corresponding pin holes are provided on the torsion support 14 to fix the torsion mandrel 15.

[0039] When in use, first rotate the torsion mandrel 15 of the torsion locking device 6 to a certain angle, then connect the torsion mandrel 15 and the adapter flange 16 through a pin to lock them, and transmit the torsion through the main beam 5 and the loading end fixed support 3, thereby completing the torsion of the tail horizontal shaft 4.

[0040] Further, see Figure 5 In one embodiment of the present invention, the articulated transition section 7 includes: a fixed seat 17, an adapter ear 18 and an adapter seat 22, the adapter seat 22 is fixedly connected to the ground support seat 8, the fixed seat 17 is fixedly connected to the main beam 5, the adapter ear 18 is installed on the fixed seat 17, and an adapter sleeve 20 is provided on the adapter seat 22, and the adapter ear 18 is rotatably connected to the adapter sleeve 20.

[0041] In addition, the articulated transition section 7 also includes: a vibration seat 21 and a vibration adapter seat 24, the vibration adapter seat 24 is arranged on one side of the fixed seat 17 and is fixedly connected, a rotatable pin shaft 23 is installed on the vibration adapter seat 24, the vibration seat 21 is fixedly connected to the pin shaft 23, and a limiting groove is provided in the adapter sleeve 20, and the two ends of the vibration seat 21 are respectively located in the limiting grooves on both sides thereof, thereby limiting the vibration amplitude of the vibration seat 21 by the limiting grooves.

[0042] During the test debugging, the torsion core rod 15 of the torsion locking device 6 is first rotated to a certain angle, and then the torsion core rod 15 and the adapter flange 16 are connected by pins to lock them, and the torsion is transmitted through the main beam 5 and the loading end fixed support 3, thereby completing the torsion of the tail horizontal shaft 4. During the test, the first-order modal bending frequency f1 of the tail horizontal shaft 4 is first obtained by frequency sweeping, and then the first-order modal bending frequency f1 of the tail horizontal shaft 4 is tested, and fatigue damage is found in the tail horizontal shaft 4. During the test, the excitation load of the vibration table is transmitted to the table top articulated transition section 2 and the ground articulated transition section 7. Since the table top articulated transition section 2 and the ground articulated transition section 7 adopt an articulated structure, the gravity of the tail horizontal shaft and the test device will not generate an overturning moment on the vibration table. By monitoring the acceleration signal of the vibration table surface, it is found that the vibration table output waveform is not distorted. Therefore, through this test device, the high-cycle fatigue test of the tail horizontal shaft in a torsion state can be completed.

[0043] Finally, it should be noted that the above is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A high cycle fatigue test device for the tail horizontal axis of a helicopter transmission system, characterized in that: include: A vibration table (1), a tabletop hinged transition section (2), a loading end fixed support (3), a main beam (5), a torsion locking device (6), a ground hinged transition section (7), and a ground support seat (8), wherein: The main beam (5) has a mounting end and a transmission end; The ground hinged transition section (7) is installed on one side of the bottom of the main beam (5) close to the installation end and is connected to the ground support seat (8); The tabletop hinged transition section (2) is installed on one side of the bottom of the main beam (5) close to the transmission end and is connected to the vibration table (1); The twist locking device (6) is installed on one side of the top of the main beam (5) close to the installation end, and is used to support an axial end of the tail horizontal shaft (4); The loading end fixed support (3) is installed on the top of the main beam (5) on one side close to the transmission end, and is used to support an axial end of the tail horizontal shaft (4); The vibration table (1) is used to provide vibration force to the tail horizontal shaft (4).

2. A helicopter transmission system tail horizontal shaft high cycle fatigue test device according to claim 1, characterized in that: The table top articulated transition section (2) comprises: a table top transition section (9) and an articulated seat (11), wherein the table top transition section (9) is rotatably connected to the articulated seat (11); the table top transition section (9) is fixedly connected to the vibration table (1), and the articulated seat (11) is fixedly connected to the main beam (5).

3. A helicopter transmission system tail horizontal shaft high cycle fatigue test device according to claim 1, characterized in that: The loading end fixed support (3) comprises: a fixed support (12) and a transition flange (13), wherein the fixed support (12) is fixedly connected to the main beam (5), and the transition flange (13) is connected to an axial end of the tail horizontal shaft (4).

4. A helicopter transmission system tail horizontal shaft high cycle fatigue test device according to claim 1, characterized in that: The twist locking device (6) is also used to apply torque to the tail horizontal shaft (4).

5. A helicopter transmission system tail horizontal shaft high cycle fatigue test device according to claim 4, characterized in that: The twist locking device (6) comprises: a twist support (14), a twist mandrel (15) and an adapter flange (16), wherein the twist mandrel (15) is rotatably mounted on the twist support (14), and the twist mandrel (15) is fixedly connected to the adapter flange (16); The torsion support (14) is fixedly connected to the main beam (5), and the adapter flange (16) is fixedly connected to the tail horizontal shaft (4).

6. A helicopter transmission system tail horizontal shaft high cycle fatigue test device according to claim 5, characterized in that: The twist locking device (6) further comprises a pin for fixedly connecting the twist mandrel (15) and the twist support (14).

7. A helicopter transmission system tail horizontal shaft high cycle fatigue test device according to claim 6, characterized in that: The pin has two predetermined positions; in one predetermined position, the relative positions of the twisting mandrel (15) and the twisting support (14) are fixed; in the other predetermined position, the twisting mandrel (15) can rotate in the twisting support (14).

8. A helicopter transmission system tail horizontal shaft high cycle fatigue test device according to any one of claims 1 to 7, characterized in that: The ground hinged transfer section (7) comprises: a fixed seat (17), a transfer ear (18) and a transfer seat (22), wherein the transfer seat (22) is fixedly connected to the ground support seat (8), the fixed seat (17) is fixedly connected to the main beam (5), the transfer ear (18) is mounted on the fixed seat (17), an transfer sleeve (20) is provided on the transfer seat (22), and the transfer ear (18) is rotatably connected to the transfer sleeve (20).

9. A helicopter transmission system tail horizontal shaft high cycle fatigue test device according to claim 8, characterized in that: The ground hinged adapter section (7) further comprises: a vibration seat (21) and a vibration adapter seat (24), wherein the vibration adapter seat (24) is arranged on one side of the fixed seat (17) and is fixedly connected, a pin shaft (23) is installed on the vibration adapter seat (24), the vibration seat (21) is fixedly connected to the pin shaft (23), a limiting groove is provided in the adapter sleeve (20), and the two ends of the vibration seat (21) are respectively located in the limiting grooves on both sides thereof.

10. A helicopter transmission system tail horizontal shaft high cycle fatigue test device according to claim 9, characterized in that: The pin shaft (23) is rotatably connected to the vibration adapter seat (24).

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