Helicopter main reducer rotor loader debugging and load calibration device, test system and use method

Abstract

The invention relates to the technical field of helicopter testing, in particular to a helicopter main reducer rotor loader debugging and load calibration device, a testing system and a using method. A helicopter main speed reducer rotor loader debugging and load calibration device comprises a loading assembly which is suitable for being connected with a main rotor loader, the main rotor loader is suitable for being arranged on the periphery of a gearbox input shaft in a sleeving mode, the loading assembly comprises a force application device, and the force application device is connected with the loading assembly. And the force applicator is used for applying tension or pressure to the main rotor loader. The invention provides a helicopter main speed reducer rotor loader debugging and load calibration device, a test system and a use method, and aims to solve the problems that after a main rotor loader replaces a main speed reducer to start a test, the main rotor loader needs to be debugged before the main rotor loader replaces the main speed reducer to carry out the test; and the problem that the main rotor loader is damaged due to large downward force or displacement of the oil cylinder during main rotor load debugging is avoided.

Description

Technical Field

[0001] The present invention relates to the technical field of helicopter testing, and in particular to a helicopter main reducer rotor loader debugging and load calibration device, a testing system and a use method. Background Art

[0002] After the helicopter's main reducer tester is installed, static and dynamic load testing of the rotor loader is required, as well as combined speed testing of the top gearbox, motor, and rotor loader. The main reducer, the test object, is complex and expensive, and its testing requires the completeness of all subsystems. To reduce test risk and ensure safe main reducer testing, a device is required to replace the main reducer for rotor loader load calibration and speed testing.

[0003] The main rotor loader is a key device for simulating the loads on the main reducer's rotor shaft. The shaft's internal structure can withstand significant upward axial loads, but only minimal downward axial loads. To prevent damage to the main rotor loader due to excessive downward force or displacement of the cylinder during main rotor load testing, the loader must be debugged before testing. Currently, no such debugging equipment is available. Summary of the Invention

[0004] In view of this, the present invention provides a helicopter main reducer rotor loader debugging and load calibration device, a test system and a method of use, so as to solve the problem that in order to prevent the main rotor loader from replacing the main reducer to start the test, it is necessary to debug the main rotor loader before the main rotor loader replaces the main reducer to replace the main reducer, so as to avoid the oil cylinder from having a large downward force or displacement during the main rotor load debugging, thereby causing damage to the main rotor loader, and there is currently no relevant debugging equipment.

[0005] In a first aspect, the present invention provides a helicopter main reducer rotor loader debugging and load calibration device, comprising:

[0006] A loading assembly, wherein the loading assembly is suitable for being connected to a mounting seat and a main rotor loader respectively, the main rotor loader being suitable for being sleeved on the outer periphery of the gearbox input shaft, the mounting seat being connected to the side of the gearbox facing away from the main rotor loader, the loading assembly includes a force applicator, and the force applicator applies a preset force to the mounting seat and the main rotor loader respectively.

[0007] Through the action of the force applicator, when the mounting base is stable as a support, the main rotor loader is used to act on the gearbox output shaft to simulate the axial force exerted on the output shaft. The mounting base and the main rotor loader are dynamically debugged by the force applicator, and the debugged main rotor loader is used to replace the main reducer for subsequent tests.

[0008] In an optional embodiment, the number of the loading assemblies is two groups, and the two groups of loading assemblies are symmetrically arranged on both sides of the main rotor loader. Each of the loading assemblies includes a force applicator, and the force applicator is suitable for being fixed on the crossbeam.

[0009] In an optional embodiment, each of the loading components further includes a force transmission rod group, each of the force transmission rod group includes a first force transmission rod, one end of the first force transmission rod is connected to the force applying end of the force applicator, and the other end of the first force transmission rod is connected to the side wing of the main rotor loader through a connecting member.

[0010] In an optional embodiment, each of the force transmission rod groups further includes a second force transmission rod, one end of the second force transmission rod is connected to the first force transmission rod, and the other end of the second force transmission rod is suitable for connection to the mounting seat.

[0011] In an optional embodiment, the force transmission rod group further includes a third force transmission rod, one end of the third force transmission rod is connected to the second force transmission rod, and the other end of the third force transmission rod is connected to the mounting seat.

[0012] In an optional embodiment, a first force sensor is provided at the connection between the first force transmission rod and the force applying end, and a second force sensor is provided at the connection between the second force transmission rod and the third force transmission rod.

[0013] In a second aspect, the present invention further provides a testing system, comprising the above-mentioned helicopter main reducer rotor loader debugging and load calibration device.

[0014] In an optional embodiment, it further includes a mounting seat, a gearbox, a main rotor loader and a crossbeam, the gearbox is fixedly connected to the mounting seat, the main rotor loader is sleeved on the outer periphery of the gearbox input shaft, and the crossbeam is located above the main rotor loader.

[0015] In an optional embodiment, the central axis of the main rotor loader coincides with the central axis of the gear box, and the central axis of the gear box coincides with the central axis of the mounting seat.

[0016] In a third aspect, the present invention also provides a method for using a helicopter main reducer rotor loader debugging and load calibration device, wherein a force applicator applies tension or pressure to the main rotor loader, and the force applicator dynamically debugs the main rotor loader. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the specific embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0018] Figure 1 Schematic diagram of a helicopter main reducer rotor loader debugging and load calibration device in a debugging state according to an embodiment of the present invention;

[0019] Figure 2 The present invention is a schematic diagram of a helicopter main reducer rotor loader debugging and load calibration device in a calibration state according to an embodiment of the present invention.

[0020] Explanation of the accompanying drawings: 1. Gearbox; 2. Main rotor loader; 3. Mounting base; 4. Crossbeam; 5. Force applicator; 6. First force transmission rod; 7. Second force transmission rod; 8. Third force transmission rod; 9. Base; 10. First force sensor; 11. Second force sensor; 12. Connector. DETAILED DESCRIPTION

[0021] To make the purpose, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are 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 those skilled in the art without making creative efforts shall fall within the scope of protection of the present invention.

[0022] The following combination Figures 1 to 2 , describing embodiments of the present invention.

[0023] According to an embodiment of the present invention, a helicopter main reducer rotor loader debugging and load calibration device is provided, comprising: a loading assembly adapted to be connected to a mounting base 1 and a main rotor loader 2, respectively; the main rotor loader 2 being adapted to be sleeved around the outer periphery of an input shaft of a gearbox 1; the mounting base 1 being connected to the side of the gearbox 1 facing away from the main rotor loader 2; and a force applicator 5 adapted to apply a preset force to each of the mounting base 1 and the main rotor loader 2. Specifically, the force applicator 5 is a telescopic cylinder.

[0024] Through the action of the force applicator 5, when the mounting base 1 is stabilized as a support, the main rotor loader 2 is used to act on the output shaft of the gearbox 1 to simulate the axial force exerted on the output shaft. The mounting base 1 and the main rotor loader 2 are dynamically debugged by the force applicator 5, and the debugged main rotor loader replaces the main reducer for subsequent tests.

[0025] In one embodiment, Figure 1 、 Figure 2 As shown, there are two sets of loading assemblies, which are symmetrically arranged on both sides of the main rotor loader 2. Each loading assembly includes a force applicator 5, which is suitable for being fixed to the crossbeam 4. The force applicator 5 is fixed by the crossbeam 4, and the fixing base of the force applicator 5 is fixed to the crossbeam 4. The telescopic end of the force applicator 5 is arranged away from the crossbeam 4. The cooperation of the two force applicators 5 can simulate the bending moment and torque of the output shaft of the gearbox 1.

[0026] In one embodiment, Figure 1 As shown, each loading assembly further includes a dowel rod assembly, each dowel rod assembly comprising a first dowel rod 6. One end of the first dowel rod 6 is connected to the force-applying end of the force applicator 5, and the other end of the first dowel rod 6 is connected to the side wing of the main rotor loader 2 via a connector 12. Through the arrangement of the dowel rod assembly, the first dowel rod 6 transmits the force generated by the force applicator 5 to the main rotor loader 2. Specifically, the connector is a pin.

[0027] In one embodiment, Figure 1 As shown, each dowel rod group further includes a second dowel rod 7, one end of which is connected to the first dowel rod 6, and the other end of which is adapted to be connected to the mounting base 3. Through the cooperation between the first dowel rod 6 and the second dowel rod 7, the mounting base 3 supports the dowel rod group.

[0028] In one embodiment, Figure 1 As shown, the dowel rod assembly further includes a third dowel rod 8, one end of which is connected to the second dowel rod 7, and the other end of which is connected to the mounting base 3. It should be noted that the third dowel rod 8 is rotatably connected to the mounting base 3 via a pin, so that the mounting base 3 supports the dowel rod assembly.

[0029] In this embodiment, the helicopter main reducer rotor loader debugging and load calibration device has a debugging state and a calibration state: in the debugging state, Figure 1As shown, the force applicator 5 transmits an axial force to the first force transmission rod 6, so that the main rotor loader 2 is subjected to axial force and torque. The end of the third force transmission rod 8 facing away from the second force transmission rod 7 is fixedly connected to the main frame, so that the main frame applies a horizontal force to the main rotor loader 2 through the third force transmission rod 8, so that the main rotor loader 2 is subjected to shear force. It should be noted that the axial force and the horizontal force can be applied separately or together. In the calibration state, it is necessary to remove the connector connecting the first force transmission rod 6 to the main rotor loader 2, and directly connect the first force transmission rod 6 to the second force transmission rod 7. The third force transmission rod 8 is fixedly connected to the mounting base 3. The adjacent force transmission rods are fixedly connected by bolts to calibrate the force through the loading of the force applicator 5. It should be noted that the main rotor loader of this embodiment can be debugged not only statically but also dynamically (such as rotation). The debugging state is only once. After the debugging state is completed, the force needs to be recalibrated at regular intervals (debugging first and then calibration, and the calibration state is multiple times).

[0030] In one embodiment, Figure 2 As shown, in the calibration state, a first force sensor 10 is installed at the connection between the first force transmission rod 6 and the force-applying end, and a second force sensor is installed at the connection between the second force transmission rod 7 and the third force transmission rod 8. The first force sensor senses the magnitude of the output force at the force-applying end, while the second force sensor senses the force between the second force transmission rod 7 and the third force transmission rod 8. It is important to note that the first and second force sensors 10 are fixed to the force transmission rods to avoid reciprocating installation and removal of the force sensors, allowing calibration without disassembly, reducing labor intensity and avoiding safety hazards.

[0031] A testing system comprises the above-mentioned helicopter main reducer rotor loader debugging and load calibration device.

[0032] In one embodiment, Figure 2 As shown, it also includes a mounting base 3, a gearbox 1, a main rotor loader 2 and a crossbeam 4. The gearbox 1 is fixedly connected to the mounting base 3, the main rotor loader 2 is sleeved on the outer periphery of the input shaft of the gearbox 1, and the crossbeam 4 is located above the main rotor loader 2. The mounting base 3 provides support for the gearbox 1, the crossbeam 4 serves to fix the recording components, and the main rotor loader 2 serves to transmit force. It should be noted that, as Figure 2 As shown, the main rotor loader 2 is movably connected to the crossbeam 4 via a pin shaft, that is, the main rotor loader 2 can rotate relative to the crossbeam 4.

[0033] In one embodiment, Figure 2 As shown, the central axis of the main rotor loader 2 coincides with the central axis of the gearbox 1, and the central axis of the gearbox 1 coincides with the central axis of the mounting base 3, so as to avoid distortion in force transmission and ensure the coaxiality requirements among the three.

[0034] A method for using a helicopter main reducer rotor loader debugging and load calibration device comprises the following steps:

[0035] 1) In the debugging state, install the connector 12, connect the first dowel rod 6 to the force applicator 5 and the main rotor loader 2 respectively, and the force applicator 5 transmits an axial force to the first dowel rod 6, so that the main rotor loader 2 is subjected to axial force and torque. The end of the third dowel rod 8 facing away from the second dowel rod 7 is fixedly connected to the main frame, so that the main frame applies a horizontal force to the main rotor loader 2 through the third dowel rod 8, so that the main rotor loader 2 is subjected to shear force;

[0036] 2) In the calibration state, remove the connector 12, connect the first force transmission rod 6 to the force applicator 5 and the first force transmission rod 6 respectively, verify the maximum axial force load on the main rotor loader 2 through the telescopic movement of the force applicator 5, verify the maximum bending moment load through the action of the two force applicators 5, connect the first force sensor and the second force sensor in series, and collect the standard force value by applying different forces.

[0037] The helicopter main reducer rotor loader debugging and load calibration device provided by the present invention has the following advantages: (1) a main rotor loader 2 is set to replace the main reducer for testing. Before the test, the main rotor loader 2 is protected by debugging and calibrating the load of the main rotor loader 2; (2) the rotor loader load and function are verified during the main reducer bench debugging; (3) during debugging, the rotor loader debugging and load calibration device can perform the main rotor loader speed debugging test. With the support of the rotor loader debugging and load calibration device, the deformation of the main rotor loader under centrifugal force can be reduced, thereby ensuring the safety of speed debugging.

[0038] As an alternative embodiment, the force applicator 5 may also be a telescopic servo motor, a telescopic cylinder or other devices.

[0039] Although the embodiments of the present invention have been described with reference to the accompanying drawings, those skilled in the art may make various modifications and variations without departing from the spirit and scope of the present invention. Such modifications and variations are all within the scope defined by the appended claims.

Claims

1. A helicopter main reducer rotor loader debugging and load calibration device, characterized in that: include: A loading assembly is provided, wherein the loading assembly is adapted to be connected to a mounting seat (1) and a main rotor loader (2) respectively, wherein the main rotor loader (2) is adapted to be sleeved on the outer periphery of an input shaft of a gearbox (1), and the mounting seat (1) is connected to a side of the gearbox (1) facing away from the main rotor loader (2). The loading assembly comprises a force applicator (5), and the force applicator (5) applies a preset value of force to the mounting seat (1) and the main rotor loader (2) respectively.

2. The helicopter main reducer rotor loader debugging and load calibration device according to claim 1, characterized in that: The number of the loading components is two groups, and the two groups of loading components are symmetrically arranged on both sides of the main rotor loader (2). Each of the loading components includes a force applicator (5), and the force applicator (5) is suitable for being fixed on the crossbeam (4).

3. The helicopter main reducer rotor loader debugging and load calibration device according to claim 2, characterized in that: Each of the loading assemblies further comprises a force transmission rod group, each of the force transmission rod groups comprises a first force transmission rod (6), one end of the first force transmission rod (6) is connected to the force application end of the force applicator (5), and the other end of the first force transmission rod (6) is connected to the side wing of the main rotor loader (2) through a connecting piece (12).

4. The helicopter main reducer rotor loader debugging and load calibration device according to claim 3, characterized in that: Each of the force transmission rod groups further comprises a second force transmission rod (7), one end of the second force transmission rod (7) is connected to the first force transmission rod (6), and the other end of the second force transmission rod (7) is suitable for connecting to the mounting seat (3).

5. The helicopter main reducer rotor loader debugging and load calibration device according to claim 4, characterized in that: The force transmission rod group further comprises a third force transmission rod (8), one end of the third force transmission rod (8) is connected to the second force transmission rod (7), and the other end of the third force transmission rod (8) is connected to the mounting seat (3).

6. The helicopter main reducer rotor loader debugging and load calibration device according to claim 5, characterized in that: A first force sensor (10) is provided at the connection between the first force transmission rod (6) and the force application end, and a second force sensor is provided at the connection between the second force transmission rod (7) and the third force transmission rod (8).

7. A testing system, characterized in that: The invention comprises the helicopter main reducer rotor loader debugging and load calibration device according to any one of claims 1 to 6.

8. The test system according to claim 7, characterized in that: The invention also comprises a mounting seat (3), a gear box (1), a main rotor loader (2) and a crossbeam (4); the gear box (1) is fixedly connected to the mounting seat (3); the main rotor loader (2) is sleeved on the outer periphery of the input shaft of the gear box (1); and the crossbeam (4) is located above the main rotor loader (2).

9. The test system according to claim 8, characterized in that: The central axis of the main rotor loader (2) coincides with the central axis of the gear box (1), and the central axis of the gear box (1) coincides with the central axis of the mounting seat (3).

10. A method for using a helicopter main reducer rotor loader debugging and load calibration device, for using the helicopter main reducer rotor loader debugging and load calibration device according to claim 1, characterized in that: In the debugging state, the force applicator (5) applies preset forces to the mounting seat (1) and the main rotor loader (2) respectively, and the force applicator (5) dynamically debugs the main rotor loader (2).

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