Helicopter main gear reducer rotor loader commissioning and load calibration device, testing system and usage method

Abstract

This invention relates to the field of helicopter testing technology, specifically to a helicopter main gearbox rotor loader adjustment and load calibration device, testing system, and method of use. The helicopter main gearbox rotor loader adjustment and load calibration device includes: a loading assembly adapted to connect to the main rotor loader, the main rotor loader adapted to be sleeved on the outer periphery of the gearbox input shaft, and the loading assembly including a force applicator to apply tension or pressure to the main rotor loader. This invention provides a helicopter main gearbox rotor loader adjustment and load calibration device, testing system, and method of use to solve the problem that, in order to prevent the main rotor loader from replacing the main gearbox during testing, it is necessary to adjust the main rotor loader before testing, avoiding damage to the main rotor loader caused by large downward forces or displacements in the cylinders during main rotor load adjustment.

Description

Technical Field

[0001] This invention relates to the field of helicopter testing technology, specifically to a helicopter main gear reducer rotor loader debugging and load calibration device, testing system, and usage method. Background Technology

[0002] After the main gearbox test unit for the helicopter is installed, static and dynamic load adjustments to the rotor loader, as well as joint speed adjustments to the top gearbox, motor, and rotor loader, are required. The main gearbox is the test object; its structure is complex and expensive, and adjustments to it can only be carried out after all subsystems are complete. To reduce test risks and ensure the safety of main gearbox adjustments, a device is needed to replace the main gearbox for rotor loader load calibration and speed adjustments.

[0003] The main rotor loader is a key device for simulating the rotor shaft load of the main reducer. The main reducer rotor shaft has an internal structure capable of withstanding large upward axial loads, but only small downward axial loads. To prevent the main rotor loader from replacing the main reducer during testing, it needs to be calibrated beforehand to avoid damage caused by excessive downward force or displacement in the hydraulic cylinders during load calibration. Currently, there is no suitable calibration equipment available. Summary of the Invention

[0004] In view of this, the present invention provides a helicopter main gear reducer rotor loader debugging and load calibration device, testing system and usage method, to solve the problem that in order to prevent the main rotor loader from replacing the main gear reducer in the test, it is necessary to debug the main rotor loader before the test, so as to avoid the main rotor loader being damaged by a large downward force or displacement of the cylinder during the main rotor load debugging. Currently, there is no relevant debugging equipment.

[0005] In a first aspect, the present invention provides a device for adjusting and calibrating the rotor loader of a helicopter main gearbox, comprising:

[0006] A loading assembly is adapted to be connected to a mounting base and a main rotor loader respectively. The main rotor loader is adapted to be sleeved on the outer periphery of the gearbox input shaft. The gearbox is connected to the mounting base on the side opposite to the main rotor loader. The loading assembly includes a force applicator, which applies a preset force to the mounting base and the main rotor loader respectively.

[0007] When the mounting base is stably supported by the force applicator, the main rotor loader acts on the output shaft of the gearbox to simulate the axial force on the output shaft. The force applicator dynamically adjusts the mounting base and the main rotor loader. The adjusted main rotor loader replaces the main reducer for subsequent tests.

[0008] In one alternative implementation, the number of loading components is two sets, which are symmetrically arranged on both sides of the main rotor loader. Each loading component includes a force applicator adapted to be fixed to the crossbeam.

[0009] In one alternative embodiment, each loading component further includes a force transmission rod group, each force transmission rod group including a first force transmission rod, one end of the first force transmission rod being connected to the force application end of the force applicator, and the other end of the first force transmission rod being connected to the side wing of the main rotor loader via a connector.

[0010] In one alternative embodiment, each of the force transmission rod assemblies further includes a second force transmission rod, one end of which is connected to the first force transmission rod, and the other end of which is adapted to be connected to the mounting base.

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

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

[0013] Secondly, the present invention also provides a testing system, including the aforementioned helicopter main gear reducer rotor loader debugging and load calibration device.

[0014] In one alternative embodiment, the system further includes a mounting base, a gearbox, a main rotor loader, and a crossbeam. The gearbox is fixedly connected to the mounting base, 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 one alternative embodiment, the central axis of the main rotor loader coincides with the central axis of the gearbox, and the central axis of the gearbox coincides with the central axis of the mounting base.

[0016] Thirdly, the present invention also provides a method for using a helicopter main gear reducer rotor loader adjustment and load calibration device, wherein a force applicator applies tension or pressure to the main rotor loader, and the force applicator dynamically adjusts the main rotor loader. Attached Figure Description

[0017] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0018] Figure 1 This is a schematic diagram of a helicopter main gear reducer rotor loader debugging and load calibration device in the debugging state according to an embodiment of the present invention.

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

[0020] Explanation of reference numerals in the attached 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. Connecting component. Detailed Implementation

[0021] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, 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, 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 following is combined Figures 1 to 2 The following describes embodiments of the present invention.

[0023] According to an embodiment of the present invention, in one aspect, a helicopter main gear reducer rotor loader adjustment 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 adapted to be sleeved on the outer periphery of the input shaft of a gearbox 1, the mounting base 1 being connected to the side of the gearbox 1 opposite to the main rotor loader 2, and the loading assembly including a force applicator 5, the force applicator 5 applying a preset force to the mounting base 1 and the main rotor loader 2 respectively. Specifically, the force applicator 5 is a telescopic hydraulic cylinder.

[0024] When the mounting base 1 is stably supported by the force applicator 5, the main rotor loader 2 acts on the output shaft of the gearbox 1 to simulate the axial force on the output shaft. The force applicator 5 dynamically adjusts the mounting base 1 and the main rotor loader 2. The adjusted main rotor loader replaces the main reducer for subsequent tests.

[0025] In one embodiment, such as Figure 1 , Figure 2 As shown, there are two sets of loading components, symmetrically arranged on both sides of the main rotor loader 2. Each loading component includes a force applicator 5, which is adapted to be fixed on the crossbeam 4. The force applicator 5 is fixed by the crossbeam 4, and the mounting base of the force applicator 5 is fixed to the crossbeam 4. The telescopic end of the force applicator 5 is set away from the crossbeam 4. Through the cooperation of the two force applicators 5, the bending moment and torque of the output shaft of the gearbox 1 can be simulated.

[0026] In one embodiment, such as Figure 1 As shown, each loading component also includes a force transmission rod assembly, each force transmission rod assembly including 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 via a connector 12. Through the arrangement of the force transmission rod assembly, the force generated by the force applicator 5 is transmitted to the main rotor loader 2 by the first force transmission rod 6. Specifically, the connector is a pin.

[0027] In one embodiment, such as Figure 1 As shown, each force transmission rod assembly also includes 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 adapted to be connected to the mounting base 3. Through the cooperation of the first force transmission rod 6 and the second force transmission rod 7, the mounting base 3 supports the force transmission rod assembly.

[0028] In one embodiment, such as Figure 1 As shown, the force transmission rod assembly also includes 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 base 3. It should be noted that the third force transmission rod 8 is rotatably connected to the mounting base 3 via a pin, so that the mounting base 3 supports the force transmission rod assembly.

[0029] In this embodiment, the helicopter main gear reducer rotor loader debugging and load calibration device has a debugging state and a calibration state: in the debugging state, such as Figure 1As shown, the force applicator 5 transmits axial force to the first force transmission rod 6, causing the main rotor loader 2 to experience 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, causing the main rotor loader 2 to experience shear force. It should be noted that the axial force and horizontal force can be applied separately or together. In the calibration state, the connecting piece between the first force transmission rod 6 and the main rotor loader 2 needs to be removed, and the first force transmission rod 6 is directly connected to the second force transmission rod 7, and the third force transmission rod 8 is fixedly connected to the mounting base 3. Adjacent force transmission rods are fixedly connected by bolts, so that the force can be calibrated by loading through the force applicator 5. It should be noted that the main rotor loader in this embodiment can not only be statically debugged, but also dynamically debugged (e.g., rotated), and the debugging state is only performed once. After the debugging state is completed, the force needs to be recalibrated at regular intervals (debug first, then calibrate, and the calibration state is repeated multiple times).

[0030] In one embodiment, such as 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 application 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 detects the magnitude of the output force at the force application end, and the second force sensor detects the force between the second force transmission rod 7 and the third force transmission rod 8. It should be noted that the first force sensor 10 and the second force sensor are fixed to the force transmission rods to avoid repeated installation and removal of the force sensors, enabling calibration of the force sensors without disassembling them, thereby reducing the labor intensity of personnel and avoiding safety hazards.

[0031] A testing system includes the aforementioned helicopter main gear reducer rotor loader debugging and load calibration device.

[0032] In one embodiment, such as 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, meaning that the main rotor loader 2 can rotate relative to the crossbeam 4.

[0033] In one embodiment, such as 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 the force transmission being skewed and to ensure the coaxiality requirement among the three.

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

[0035] 1) In the debugging state, install the connector 12. The first force transmission rod 6 is connected to the force applicator 5 and the main rotor loader 2 respectively. The force applicator 5 transmits 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 away from the second force transmission rod 7 is fixedly connected to the main frame so that the main frame applies 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.

[0036] 2) Under calibration conditions, disconnect 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) The 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 in 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, and the speed debugging safety is guaranteed.

[0038] As an alternative implementation, the force applicator 5 can also be a telescopic servo motor, a telescopic cylinder, or other similar device.

[0039] Although embodiments of the invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the invention, and such modifications and variations all fall within the scope defined by the appended claims.

Claims

1. A device for debugging and calibrating the rotor loader of a helicopter main gearbox, characterized in that, include: The loading assembly is adapted to be connected to the mounting base (3) and the main rotor loader (2) respectively. The main rotor loader (2) is adapted to be sleeved on the outer periphery of the input shaft of the gearbox (1). The mounting base (3) is connected to the side of the gearbox (1) away from the main rotor loader (2). The loading assembly includes a force applicator (5). The force applicator (5) applies a preset value of force to the mounting base (3) and the main rotor loader (2) respectively. The number of loading components is two sets, and the two sets of loading components are symmetrically arranged on both sides of the main rotor loader (2). Each loading component includes a force applicator (5), which is adapted to be fixed on the crossbeam (4). Each of the loading components further includes a force transmission rod group, each of the force transmission rod groups includes 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 connector (12). Each of the force transmission rod groups further includes a second force transmission rod (7), one end of which is connected to the first force transmission rod (6), and the other end of which is adapted to be connected to the mounting base (3); The force transmission rod group also includes a third force transmission rod (8), one end of which is connected to the second force transmission rod (7), and the other end of which is connected to the mounting base (3); 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 (11) is provided at the connection between the second force transmission rod (7) and the third force transmission rod (8).

2. A testing system, characterized in that, The device includes the helicopter main gear reducer rotor loader debugging and load calibration device as described in claim 1.

3. The testing system according to claim 2, characterized in that, 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).

4. The testing system according to claim 3, characterized in that, 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).

5. A method for using a helicopter main gear reducer rotor loader adjustment and load calibration device, used with the helicopter main gear reducer rotor loader adjustment and load calibration device as described in claim 1, characterized in that, In the debugging state, the force applicator (5) applies a preset value of force to the mounting base (3) and the main rotor loader (2) respectively, and the force applicator (5) performs dynamic debugging on the main rotor loader (2).

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