Fatigue test equipment for lower rotor inclinator of helicopter

Abstract

The utility model relates to fatigue testing equipment for a lower rotor inclinator of a helicopter, belongs to the technical field of helicopters, and solves the problem that a common fatigue testing machine cannot simulate the real stress condition of the lower rotor inclinator. The device comprises a main body rack, a rotating device, a force applying device and a control device, the main body rack comprises a working table and a supporting beam, and the supporting beam is located above the working table and can reciprocate up and down relative to the working table; the rotating device is arranged on the workbench, and the rotating device can drive the outer ring of the lower rotor wing inclinator to rotate; the force application device is arranged on the supporting beam and can apply pulling force or pushing force to the inner ring of the lower rotor wing inclinator. The control device can control the rotating device and the force application device and collect test data. According to the utility model, the rotating device is adopted to drive the outer ring to rotate, the force application device is adopted to apply force to the inner ring, the real stress condition of the lower rotor inclinator in the flight process is simulated, and the fatigue test accuracy is improved.

Description

Technical Field

[0001] This utility model relates to the field of helicopter technology, and in particular to a fatigue testing device for a helicopter lower rotor swashplate. Background Technology

[0002] In helicopters, the swashplate is a special device used to control the rotor's vertical, horizontal, and lateral movements. The swashplate is connected to the rotor shaft via a spherical sleeve and can slide up and down on the shaft. The outer ring of the swashplate is connected to the collective pitch control stick and cyclic pitch control stick (also called the control stick) in the cockpit via a control lever. The inner ring of the swashplate is connected to the rotor blades via a pitch control stick, enabling pitch control of the blades. When the pilot operates the collective pitch control stick, the movement of the stick, through the control stick system, causes the swashplate to move vertically along the rotor's main shaft. This action causes the pitch of each blade to increase or decrease simultaneously, thus changing the rotor's lift and causing the helicopter to ascend or descend. When the pilot operates the cyclic pitch control stick, the system causes the swashplate to tilt around the spherical sleeve. This action causes the pitch of each blade to change periodically during rotation, creating aerodynamic asymmetry in the rotor and consequently tilting the rotor's plane of rotation. The direction of the horizontal component of the rotor thrust changes accordingly, thus enabling the helicopter to fly forward, backward, left, and right.

[0003] The rotor blades generate lift and drag during rotation, and these forces are transmitted to the inner ring via the pitch control link. Simultaneously, the inner ring and pitch control link experience centrifugal force during high-speed rotation. Furthermore, forces applied by the pilot through the control system are also transmitted to the outer ring.

[0004] When the outer ring of the lower rotor swashplate fractures due to fatigue, the swashplate will become unresponsive to the lower rotor, resulting in a loss of control. Therefore, verifying the fatigue life of the lower rotor swashplate is a crucial technical problem that must be solved. Because the lower rotor swashplate experiences complex stresses, currently used domestic fatigue testing machines cannot accurately simulate the actual stress conditions of the lower rotor swashplate. Utility Model Content

[0005] Based on the above analysis, the present invention aims to provide a fatigue testing device for a helicopter lower rotor swashplate, in order to solve the problem that current fatigue testing machines cannot effectively simulate the actual stress conditions of the lower rotor swashplate.

[0006] This utility model provides a fatigue testing device for a helicopter lower rotor swashplate, including a main frame, a rotating device, a force-applying device, and a control device. The main frame includes a worktable and a support beam, the support beam being located above the worktable and capable of reciprocating up and down relative to the worktable. The rotating device is mounted on the worktable and can drive the outer ring of the lower rotor swashplate to rotate. The force-applying device is mounted on the support beam and can apply tension or thrust to the inner ring of the lower rotor swashplate. The control device can control the output force and / or torque of the rotating device and the force-applying device, and can also collect the values ​​of the tension or thrust applied by the force-applying device, as well as the rotational speed and rotational torque of the rotating device.

[0007] Furthermore, the main frame also includes a limiting shaft and a spherical bearing, the limiting shaft being fixedly mounted on the support beam, and the spherical bearing being mounted on the limiting shaft.

[0008] Furthermore, the inner ring of the lower rotor swashplate can be connected to the limiting shaft via the spherical bearing.

[0009] Furthermore, the force-applying device includes multiple force-applying components, including an electric cylinder, a force sensor, and a force-applying rod.

[0010] Furthermore, the electric cylinder is fixedly mounted above the support beam, and the output end of the electric cylinder extends downward through the support beam and is connected to one end of the force-applying rod through the force sensor. The other end of the force-applying rod is connected to the first connecting lug of the inner ring of the lower rotor swashplate.

[0011] Furthermore, the number of force-applying components is equal to the number of the first connecting lugs of the inner ring of the lower rotor swashplate.

[0012] Furthermore, the rotating device includes a first motor and a turntable. The first motor is fixedly disposed below the worktable, and the turntable is disposed above the worktable. The first motor is capable of driving the turntable to rotate.

[0013] Furthermore, a plurality of fixing posts are fixedly provided on the upper surface of the turntable, and a first connecting hole is provided on the fixing post. The distance from the first connecting hole to the upper surface of the turntable is between 1.5 and 2 times the distance from the second bolt hole on the second connecting lug of the outer ring of the lower rotor swashplate to the bottom surface of the outer ring.

[0014] Furthermore, the fixing post is provided in a one-to-one correspondence with the second connecting lug of the outer ring of the lower rotor swashplate.

[0015] Furthermore, the rotating device also includes a speed reducer, a coupling, and a first motor controller. The speed reducer is connected to the output end of the first motor, one end of the coupling is connected to the output end of the speed reducer, and the other end of the coupling is connected to the input shaft on the lower surface of the turntable. The first motor controller is used to control the speed of the first motor.

[0016] Compared with the prior art, the present invention can achieve at least one of the following beneficial effects:

[0017] (1) This utility model uses a rotating device to drive the outer ring of the lower rotor swashplate to rotate, and at the same time uses a force-applying device to apply tension or thrust to the inner ring of the lower rotor swashplate to make the lower rotor swashplate tilt, thereby simulating the relative motion of the inner and outer rings of the lower rotor swashplate during helicopter flight, so as to realize the simulation of the real force situation of the lower rotor swashplate and thus improve the accuracy of fatigue testing.

[0018] (2) This utility model realizes automatic control of the rotating device and the force application device through the control device, thereby simulating the change of force on the lower rotor swashplate during helicopter flight, and further improving the realism of the simulation; in addition, the control device can also realize the sensing and recording of the force on the lower rotor swashplate during the test, which is convenient for analyzing the test results.

[0019] (3) This utility model limits the inner ring of the lower rotor swashplate by using a limiting shaft and a spherical bearing, which can simulate the installation method of the lower rotor swashplate on the helicopter rotor shaft, so that this fatigue testing equipment can simulate the actual working state of the lower rotor swashplate and can move up and down, tilt and rotate relative to the limiting shaft.

[0020] In this invention, the above-described technical solutions can be combined with each other to achieve more preferred combinations. Other features and advantages of this invention will be set forth in the following description, and some advantages will become apparent from the description or be learned by practicing the invention. The objectives and other advantages of this invention can be realized and obtained from the description and accompanying drawings, which are particularly pointed out. Attached Figure Description

[0021] The accompanying drawings are for illustrative purposes only and are not intended to limit the scope of the invention. Throughout the drawings, the same reference numerals denote the same parts.

[0022] Figure 1 This is a schematic diagram of the structure of the lower rotor swashplate of a helicopter;

[0023] Figure 2This is a structural schematic diagram of the fatigue testing device for the helicopter lower rotor swashplate of this utility model;

[0024] Figure 3 for Figure 2 A cross-sectional view of the fatigue testing equipment in the image;

[0025] Figure 4 This is a partially enlarged schematic diagram showing the installation of the under-rotor swashplate to be tested onto the fatigue testing equipment of this invention.

[0026] Figure label:

[0027] 10-Main frame; 11-Support frame; 12-Worktable; 13-Screw; 14-Support beam; 15-Guide column; 16-Limit shaft; 20-Force application component; 21-Electric cylinder controller; 22-Electric cylinder; 23-Force sensor; 24-Force application rod; 30-Rotating device; 31-First motor; 32-Reducer; 33-Coupling; 34-Motor controller; 35-Turntable; 351-Fixed column; 100-Lower rotor swashplate; 110-Inner ring; 111-First connecting lug; 112-First bolt hole; 120-Outer ring; 121-Second connecting lug; 122-Second bolt hole; 130-Crossed roller bearing; 140-Variable pitch tie rod. Detailed Implementation

[0028] The preferred embodiments of the present invention will now be described in detail with reference to the accompanying drawings, which constitute a part of the present invention and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not intended to limit the scope of the present invention.

[0029] Example 1

[0030] A specific embodiment of this utility model is as follows: Figures 2-4 As shown, a fatigue testing device for a helicopter lower rotor swashplate is disclosed, used to test the lower rotor swashplate 100 of a helicopter.

[0031] The structure of the helicopter's lower rotor swashplate 100 to be tested in this utility model is as follows: Figure 1As shown, it includes an inner ring 110, an outer ring 120, and a crossed roller bearing 130. The inner ring 110 and outer ring 120 are connected as a single unit via the crossed roller bearing 130 and are rotatable relative to each other. The inner ring 110 has multiple first connecting lugs 111, each with a first bolt hole 112 for connection to the helicopter's pitch control rod 140. The outer ring 120 has multiple second connecting lugs 121, each with a second bolt hole 122 for connection to the helicopter's control rod. The inner ring 110 of the lower rotor swashplate 100 is connected to the helicopter's rotor shaft via a spherical sleeve, allowing the lower rotor swashplate 100 to tilt, rotate, and slide up and down on the rotor shaft relative to it.

[0032] The fatigue testing equipment for the helicopter lower rotor swashplate 100 of this utility model includes a main frame 10, a rotating device 30, a force application device, and a control device.

[0033] The main frame 10 provides support for the fatigue testing equipment and is connected to the rotating device 30 and the force application device. The control device is mainly used to send control commands and record sensor data from each device in real time.

[0034] See Figure 2 and Figure 3 The main frame 10 includes a support frame 11, a worktable 12, lead screws 13, a support beam 14, guide columns 15, a limiting shaft 16, and a spherical bearing. The support frame 11 is welded from steel pipes and is fastened to the worktable 12 with bolts. Two lead screws 13 and two guide columns 15 are connected to the upper surface of the worktable 12. The support beam 14 is sleeved on the upper part of the lead screws 13 and guide columns 15 and can be driven by the lead screws 13 to move up and down along the guide columns 15. The lead screws 13 can be kept in synchronous rotation by a timing belt and can be driven by an additional motor installed under the worktable 12 or manually rotated to make the support beam 14 connected to the lead screws 13 slide up and down along the guide columns 15, thereby adjusting the distance between the support beam 14 and the worktable 12. The limiting shaft 16 is fixedly mounted on the support beam 14 and extends downward from the bottom of the support beam 14. The spherical bearing is mounted on the limiting shaft 16. With this configuration, when the lead screw 13 drives the support beam 14 to move up and down, it can also move the limit shaft 16 up and down, thereby providing operating space for loading and unloading the lower rotor swashplate 100. At the same time, it can also adjust the height of the lower rotor swashplate 100 on the test equipment to facilitate the connection of the force application device and the rotation device 30.

[0035] The inner ring 110 of the lower rotor swashplate 100 can be connected to the limiting shaft 16 via a spherical bearing, thereby allowing the lower rotor swashplate 100 to tilt, rotate, and move up and down relative to the limiting shaft 16, thus simulating the working state of the lower rotor swashplate 100.

[0036] See Figures 2-4 The force-applying device is mounted on the support beam 14 and can apply tension or thrust to the inner ring 110 of the downward rotor swashplate 100. The force-applying device includes multiple force-applying components 20, each of which includes an electric cylinder 22, an electric cylinder controller 21, a force sensor 23, and a force-applying rod 24.

[0037] The electric cylinder 22 is fixedly mounted above the support beam 14 via a stop, and its output force is controlled by the electric cylinder controller 21. The output end of the electric cylinder 22 extends downward through the support beam 14 and is connected to one end of the force application rod 24 via the force sensor 23. The other end of the force application rod 24 is connected to the first connecting lug 111 of the inner ring 110 of the lower rotor swashplate 100. This transmits the pulling force of the electric cylinder 22 to the end face of the inner ring 110, causing the inner ring 110 and outer ring 120 of the lower rotor swashplate 100 under test to bear a preset axial load, thereby simulating the stress situation of the part under test on a helicopter.

[0038] The number of force-applying components 20 is equal to the number of first connecting lugs 111 of the inner ring 110 of the lower rotor swashplate 100. In this embodiment, two force-applying components 20 are provided.

[0039] In the preferred embodiment, the axial tension (compression) force of the electric cylinder 22 can be controlled by a programmable script to meet the test requirements of different load patterns in the later stages, thereby simulating the force of the helicopter's variable-pitch lever 140. Preferably, the force range is 0 to 1000 N; the actuator operating frequency is not less than 11 Hz.

[0040] The rotating device 30 is mounted on the worktable 12, and the rotating device 30 can drive the outer ring 120 of the lower rotor swashplate 100 to rotate.

[0041] See Figures 2-3 The rotating device 30 includes a motor controller 34, a first motor 31, a reducer 32, a coupling 33, and a turntable 35. The first motor 31 is fixedly mounted below the worktable 12. The reducer 32 is connected to the output end of the first motor 31, and the motor and reducer 32 are fastened together by bolts. The upper surface of the reducer 32 is fixed to the lower surface of the worktable 12 by bolts. One end of the coupling 33 is connected to the output end of the reducer 32, and the other end of the coupling 33 is connected to the input shaft on the lower surface of the turntable 35. The controller for the first motor 31 is mounted on the first motor 31 and is used to control the rotational speed of the first motor 31. The turntable 35 is located above the worktable 12, and the first motor 31 can drive the turntable 35 to rotate.

[0042] See Figure 4Multiple fixing posts 351 are fixedly installed on the upper surface of the turntable 35. The fixing posts 351 are corresponding one-to-one with the second connecting lugs 121 of the outer ring 120 of the lower rotor swashplate 100. The fixing posts 351 are provided with first connecting holes. The distance from the first connecting hole to the upper surface of the turntable 35 is between 1.5 and 2 times the distance from the second bolt hole 122 on the second connecting lug 121 of the outer ring 120 of the lower rotor swashplate 100 to the bottom surface of the outer ring 120.

[0043] With the above configuration, the lower rotor swashplate 100 can be suspended above the turntable 35, and its outer ring 120 can be continuously rotated by the turntable 35. At the same time, the lower rotor swashplate 100 can be tilted relative to the surface of the turntable 35, thereby simulating the movement of the lower rotor swashplate 100 during operation.

[0044] In a preferred embodiment, the rotating device 30 is capable of driving the test object (outer ring 120 of the lower rotor swashplate 100) to rotate at a constant speed of not less than 650 RPM.

[0045] The first motor 31 has an integrated speed sensor that can transmit speed signals to the control device for real-time display and recording of process data.

[0046] The control device can control the output force and / or torque of the rotating device 30 and the force-applying device. It can also collect feedback values ​​from the force sensor 23 and the speed sensor. The control device can display the applied axial tensile (compressive) force and rotational speed on a computer in real time, and has the function of recording and storing test process data.

[0047] The control device can use conventional hardware systems such as microcontrollers and industrial control computers that are already in use.

[0048] During testing, the force-applying device is connected and loaded through the first bolt hole 112 of the inner ring 110. The rotating device 30 is connected through the second bolt hole 122 of the outer ring 120 and applies rotational motion with the axis of the limiting shaft 16 as the axis. The lower rotor swashplate 100 is radially limited by the limiting shaft 16, and its inner ring 110 is assembled with the limiting shaft 16 through a spherical bearing. By applying a rotational speed through the rotating device 30 and applying a sinusoidal axial load of a certain frequency through the force-applying device, the stress condition of the lower rotor swashplate 100 during helicopter flight is simulated, thereby conducting a fatigue test to test its lifespan.

[0049] In summary, this utility model provides a fatigue testing device for a helicopter lower rotor swashplate, which can simulate the stress conditions of the swashplate during actual flight, thereby obtaining the fatigue life of the component through fatigue testing methods and improving the system stability of the helicopter.

[0050] The above description is only a preferred embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present utility model should be included within the protection scope of the present utility model.

Claims

1. A fatigue testing device for a helicopter lower rotor swashplate, characterized in that, The device includes a main frame, a rotating device, a force-applying device, and a control device. The main frame includes a worktable and a support beam, the support beam being located above the worktable and capable of reciprocating up and down relative to the worktable. The rotating device is mounted on the worktable and can drive the outer ring of the lower rotor swashplate to rotate. The force-applying device is mounted on the support beam and can apply tension or thrust to the inner ring of the lower rotor swashplate. The control device can control the output force and / or torque of the rotating device and the force-applying device, and can also collect the values ​​of the tension or thrust applied by the force-applying device, as well as the rotational speed and rotational torque of the rotating device.

2. The fatigue testing equipment for the helicopter lower rotor swashplate according to claim 1, characterized in that, The main frame also includes a limiting shaft and a spherical bearing. The limiting shaft is fixedly mounted on the support beam, and the spherical bearing is mounted on the limiting shaft.

3. The fatigue testing equipment for the helicopter lower rotor swashplate according to claim 2, characterized in that, The inner ring of the lower rotor swashplate can be connected to the limiting shaft via the spherical bearing.

4. The fatigue testing equipment for the helicopter lower rotor swashplate according to claim 1, characterized in that, The force-applying device includes multiple force-applying components, including an electric cylinder, a force sensor, and a force-applying rod.

5. The fatigue testing equipment for the helicopter lower rotor swashplate according to claim 4, characterized in that, The electric cylinder is fixedly mounted above the support beam. The output end of the electric cylinder extends downward through the support beam and is connected to one end of the force-applying rod through the force sensor. The other end of the force-applying rod is connected to the first connecting lug of the inner ring of the lower rotor swashplate.

6. The fatigue testing equipment for the helicopter lower rotor swashplate according to claim 5, characterized in that, The number of force-applying components is equal to the number of the first connecting lugs of the inner ring of the lower rotor swashplate.

7. The fatigue testing equipment for the helicopter lower rotor swashplate according to claim 1, characterized in that, The rotating device includes a first motor and a turntable. The first motor is fixedly installed below the worktable, and the turntable is installed above the worktable. The first motor can drive the turntable to rotate.

8. The fatigue testing equipment for the helicopter lower rotor swashplate according to claim 7, characterized in that, The upper surface of the turntable is fixedly provided with a plurality of fixing posts, and the fixing posts are provided with a first connecting hole. The distance from the first connecting hole to the upper surface of the turntable is 1.5 to 2 times the distance from the second bolt hole on the second connecting lug of the outer ring of the lower rotor swashplate to the bottom surface of the outer ring.

9. The fatigue testing equipment for the helicopter lower rotor swashplate according to claim 8, characterized in that, The fixed column is configured to correspond one-to-one with the second connecting lug on the outer ring of the lower rotor swashplate.

10. The fatigue testing equipment for the helicopter lower rotor swashplate according to any one of claims 7-9, characterized in that, The rotating device further includes a speed reducer, a coupling, and a first motor controller. The speed reducer is connected to the output end of the first motor, one end of the coupling is connected to the output end of the speed reducer, and the other end of the coupling is connected to the input shaft on the lower surface of the turntable. The first motor controller is used to control the speed of the first motor.

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