Fatigue testing device for helicopter propeller clamp assembly

Abstract

The utility model relates to a fatigue testing device for a helicopter propeller clamp assembly, belongs to the technical field of unmanned helicopters, and solves the problem that a universal fatigue testing machine cannot completely simulate the real stress condition of a thrust bearing in the propeller clamp assembly. The device comprises a main body bracket, a positioning and locking unit, a variable pitch unit, a force application unit and a data processing unit, the positioning and locking unit is used for installing and locking a to-be-detected paddle clamp assembly body; the variable pitch unit is used for simulating the reciprocating swing of a variable pitch rocker arm and a propeller clamp when the helicopter flies; the force application unit is used for simulating centrifugal force formed by rotation of the blades in the rotation process; and the data processing unit is used for recording sensor data in real time and sending a control instruction to control the variable pitch unit and the force application unit to operate. According to the utility model, the variable pitch unit and the force application unit are adopted, various load working conditions of the to-be-tested part are fully simulated, and the accuracy of the fatigue life test of the paddle clamp assembly is improved.

Description

TECHNICAL FIELD

[0001] The utility model relates to unmanned helicopter technical field especially, relates to a fatigue testing device of helicopter paddle clamp assembly. BACKGROUND

[0002] Paddle clamp assembly is the key position of helicopter, the centrifugal force is close to 3.5 tons in the normal rotation process of unmanned aerial vehicle paddle, and the severe wear of the thrust bearing raceway in paddle clamp assembly can cause paddle clamp stagnation, the hinge moment becomes large, and further causes the situation that each passage control amount becomes large, the variable pitch movement of paddle is high frequency, reciprocating, small angle movement, and the variable pitch movement angle is only about ±10 °, so how to verify the fatigue life in paddle clamp assembly is the technical problem that must be solved at present, and the thrust bearing in paddle clamp assembly is relatively complex, and the current domestic fatigue testing machine can not completely simulate the real stress condition of the component, so the test device for the fatigue life of paddle clamp assembly is designed. SUMMARY

[0003] In view of the above analysis, the utility model embodiment aims at providing a fatigue testing device of helicopter paddle clamp assembly to solve the problem that the general fatigue testing machine can not completely simulate the real stress condition of the thrust bearing in paddle clamp assembly.

[0004] On the one hand, the utility model provides a fatigue testing device of helicopter paddle clamp assembly, including main body support, positioning locking unit, variable pitch unit, force unit and data processing unit, the positioning locking unit is arranged on the main body support, is used for installing and locking the helicopter paddle clamp assembly to be detected, the variable pitch unit is arranged on the main body support and is located one side of the positioning locking unit, is used for driving the paddle clamp assembly movement to simulate the reciprocating swing of variable pitch rocker arm and paddle clamp when helicopter flies, the force unit is arranged on the main body support and is located above the positioning locking unit, is used for exerting the pulling force to the paddle clamp assembly to simulate the centrifugal force formed by the rotation of paddle in the rotation process, the data processing unit is used for recording sensor data in real time, and sends control instruction and controls the variable pitch unit and force unit runs.

[0005] Further, the positioning locking unit includes a mounting shaft, the mounting shaft is vertically rotatably arranged on the main body support, and the mounting shaft can be fixedly connected with the paddle clamp in the paddle clamp assembly.

[0006] Further, the positioning locking unit further includes a tapered roller bearing and a bearing seat, the bearing seat is fixedly arranged on the main body support, the tapered roller bearing is arranged on the bearing seat, and the lower end of the mounting shaft is arranged in the tapered roller bearing.

[0007] Further, the positioning locking unit further comprises a locking nut, which is sleeved on the mounting shaft and located above the tapered roller bearing, and is used for axially limiting the mounting shaft.

[0008] Further, the pitch changing unit comprises a cam mechanism and a guide rod, one end of the guide rod is hinged with the cam mechanism, and the other end of the guide rod is hinged with a pitch changing rocker arm of the paddle clamp assembly.

[0009] Further, the cam mechanism can drive the pitch changing rocker arm to reciprocate within a range of ±10° through the guide rod.

[0010] Further, the pitch changing unit further comprises a counterforce seat, a motor and a speed reducer, the counterforce seat is fixedly arranged on the main body support, the motor and the speed reducer are arranged on a side of the counterforce seat away from the positioning locking unit, the cam mechanism is arranged on the other side of the counterforce seat, and the cam mechanism is connected with an output end of the speed reducer.

[0011] Further, the pitch changing unit further comprises a motor controller and a horizontal force sensor, the motor controller is used for controlling the rotating speed of the motor, and the horizontal force sensor can detect the force borne by the pitch changing rocker arm in real time.

[0012] Further, the force applying unit comprises an electric cylinder, and an output end of the electric cylinder is fixedly connected with a pitch changing shaft of the paddle clamp assembly.

[0013] Further, the force applying unit further comprises an axial force sensor, which is used for detecting the axial force borne by the paddle clamp assembly in real time.

[0014] Compared with the prior art, the utility model can realize at least one of the following beneficial effects:

[0015] (1) The utility model adopts a pitch changing unit and a force applying unit, fully simulates various load conditions of a paddle clamp assembly to be measured, and improves the accuracy of fatigue life test of the paddle clamp assembly.

[0016] (2) The cam mechanism of the pitch changing unit drives the rocker arm to make a pitch changing movement, simulates the reciprocating force of the pitch changing pull rod borne by the paddle clamp assembly, monitors the horizontal force borne by the rocker arm in real time through the horizontally arranged force sensor, improves the simulation authenticity of the force borne by the thrust bearing in the paddle clamp assembly, and thus the performance of the helicopter paddle clamp assembly can be more accurately tested.

[0017] The above technical solutions can be combined with each other to realize more optional combination solutions. Other features and advantages of the present application will be described in the subsequent specification, and some advantages can be apparent from the specification or can be understood by implementing the present application. The purposes and other advantages of the present application can be realized and obtained through the contents specifically indicated in the specification and the drawings. BRIEF DESCRIPTION OF DRAWINGS

[0018] The drawings are only for the purpose of illustrating specific embodiments and are not considered as limiting the present application, and in the whole drawings, the same reference signs represent the same parts.

[0019] Figure 1 It is a structural schematic view of the fatigue test device of the helicopter blade clamp assembly of the present application.

[0020] Figure 2 It is a structural schematic view of the blade clamp assembly to be tested.

[0021] Figure 3 It is a sectional view of the blade clamp assembly to be tested.

[0022] Figure 4 It is a partial enlarged view of the blade clamp assembly to be tested mounted on the fatigue test device.

[0023] Figure 5 It is a sectional view of the positioning and locking unit.

[0024] Reference signs:

[0025] 100-blade clamp assembly; 101-variable pitch shaft; 102-variable pitch rocker arm; 103-blade mounting bolt; 104-blade anti-sway bolt; 105-blade clamp; 106-thrust bearing; 10-main body support; 11-leg; 12-workbench; 13-column; 14-cross beam; 15-screw rod; 20-positioning and locking unit; 21-mounting shaft; 22-locking nut; 23-conical roller bearing; 24-bearing seat; 30-variable pitch unit; 31-motor controller; 32-motor; 33-reducer; 34-counterforce seat; 35-cam mechanism; 36-guide rod; 37-horizontal force sensor; 40-force applying unit; 41-electric cylinder driver; 42-electric cylinder controller; 43-electric cylinder; 44-axial force sensor. DETAILED DESCRIPTION

[0026] The preferred embodiments of the present application will be specifically described below in combination with the drawings, wherein the drawings constitute a part of the present application and are used to explain the principles of the present application together with the embodiments of the present application, and are not used to limit the scope of the present application.

[0027] Example 1

[0028] One specific embodiment of the utility model, such as Figure 1 As shown, a kind of fatigue testing device of helicopter paddle clamp assembly is disclosed, including main support 10, positioning locking unit 20, variable pitch unit 30, force unit 40 and data processing unit.

[0029] Wherein main support 10 provides support for entire fatigue testing device, positioning locking unit 20 is arranged on main support 10, for installation and locking the helicopter paddle clamp assembly 100 to be detected.Variable pitch unit 30 is arranged on main support 10 and located at the side of positioning locking unit 20, for driving paddle clamp assembly 100 movement to simulate the small angle reciprocating swing of variable pitch rocker arm 102 and paddle clamp 105 when helicopter flies.For simulating centrifugal force formed by paddle blade rotation in the rotation process of paddle clamp assembly 100, force unit 40 is arranged on main support 10 and located above positioning locking unit 20.By long-time loading stress load, the fatigue condition of paddle clamp assembly 100 can be tested.Data processing unit is mainly used for real-time recording of the sensor data of each device, and sends each control instruction to control variable pitch unit and force unit to run, to form component test record and as fatigue test basis.

[0030] The utility model relates to the part to be measured is the paddle clamp assembly 100 of helicopter, as shown in Figures 2-3 Paddle clamp assembly 100 includes variable pitch shaft 101, variable pitch rocker arm 102, paddle blade mounting bolt 103, paddle blade swing reduction bolt 104, paddle clamp 105 and thrust bearing 106.

[0031] Paddle clamp 105 includes hollow shaft section and lug section, wherein lug section is the U-shaped structure formed by hollowing the middle part of the end of a shaft, including two axially extending lugs, two first threaded holes are respectively arranged on the two lugs, for installing paddle blade through paddle blade mounting bolt 103.Two second threaded holes are further arranged on one side lug, for connecting with paddle blade through paddle blade swing reduction bolt 104.Hollow shaft section has a cylindrical cavity recessed from end to inside, thrust bearing 106 is arranged in the cavity, variable pitch shaft 101 is rotatably arranged in the cylindrical cavity through the thrust bearing 106.The end of variable pitch shaft 101 is provided with two radially extending third threaded holes, for connecting with the hub of helicopter.Variable pitch rocker arm 102 is fixedly arranged at the end of hollow shaft section, and can drive paddle clamp 105 to rotate around the axis of variable pitch shaft 101.

[0032] In actual use, variable pitch shaft 101 is fixed on the hub of helicopter;Variable pitch rocker arm 102 controls paddle clamp 105 to drive paddle blade to rotate around variable pitch shaft 101, and does reciprocating variable pitch movement.

[0033] The utility model discloses, main body support 10 includes support leg 11, workbench 12, stand 13, crossbeam 14 and screw rod 15, wherein, workbench 12 is supported by four support legs 11, and the both sides fixed of workbench 12 are provided with stand 13 respectively, two through -holes are provided on crossbeam 14, are respectively set in the top of two stands, and crossbeam 14 can move up and down along stand 13.

[0034] Screw rod 15 is arranged on the outside of two stands 13, the bottom of screw rod 15 is connected with driving element (for example servo motor) through workbench 12, and the top end of screw rod 15 is connected with crossbeam 14 through nut. Driving element can control crossbeam 14 to move up and down by driving screw rod 15.

[0035] Main body support 10 adopts welded frame, and the rising and falling of crossbeam 14 is realized through motor pulley and screw rod 15. Main body support 10 is provided with rising and falling buttons, and operation is more convenient.

[0036] Referring to Figure 1 And Figure 5 Positioning locking unit 20 includes mounting shaft 21, locking nut 22, tapered roller bearing 23 and bearing seat 24. Wherein, bearing seat 24 is fixedly arranged on the workbench 12 of main body support 10, tapered roller bearing 23 has two, and is arranged on bearing seat 24 respectively, and baffle ring is arranged between the two tapered roller bearings 23. The lower end of mounting shaft 21 is arranged in tapered roller bearing 23, locking nut 22 is sleeved on mounting shaft 21 and located above tapered roller bearing 23, the outer periphery of locking nut 22 is matched with the upper surface of bearing seat 24, the inner periphery of locking nut 22 is matched with the stepped surface on mounting shaft 21, and locking nut 22 is matched with the stepped surface on mounting shaft 21 for limiting the axial position of mounting shaft 21.

[0037] Mounting shaft 21 is vertically rotatably arranged on the workbench 12 of main body support 10, and the upper end of mounting shaft 21 is provided with two fourth threaded holes, the positions of the two fourth threaded holes are matched with the two first threaded holes on paddle clamp 105 of paddle clamp assembly 100, and the two fourth threaded holes can be fixedly connected with paddle clamp 105 through bolts.

[0038] Referring to Figure 4 The variable distance unit 30 of the utility model includes counterforce seat 34, motor controller 31, motor 32, speed reducer 33, cam mechanism 35, guide rod 36 and horizontal force sensor 37.

[0039] The counterforce seat 34 comprises a mounting plate at the bottom, a vertical support plate and reinforcing ribs at the two sides. The motor controller 31, the motor 32 and the speed reducer 33 are arranged on the vertical support plate of the counterforce seat 34 away from the positioning and locking unit 20, the cam mechanism 35 is arranged on the other side of the vertical support plate of the counterforce seat 34, and the cam mechanism 35 is connected with the output end of the speed reducer 33.

[0040] One end of the guide rod 36 is hinged with the output end of the cam mechanism 35, and the other end of the guide rod 36 is hinged with the variable-pitch rocker arm 102 of the paddle clamp assembly 100.

[0041] The motor 32 drives the cam mechanism 35 to rotate through the speed reducer 33, and the cam mechanism 35 can drive the variable-pitch rocker arm 102 to reciprocate within a range of ±10° through the guide rod 36.

[0042] The motor controller 31 is used for controlling the rotating speed of the motor 32, and the horizontal force sensor 37 can detect the force borne by the variable-pitch rocker arm 102 in real time.

[0043] The eccentricity of the output end of the cam mechanism 35 relative to the axis of the cam is adjustable, and the adjustment range is ±12.5mm. A certain eccentricity corresponds to the movement of the variable-pitch rocker arm 102 within a certain angle, and the motor 32 is internally integrated with a rotating speed sensor, which can transmit the rotating speed signal to a computer to display and record process data in real time.

[0044] Referring to Figure 1 The force applying unit 40 is fixedly arranged on the cross beam 14 of the main support 10 and located above the positioning and locking unit 20. The force applying unit 40 comprises an electric cylinder driver 41, an electric cylinder controller 42, an electric cylinder 43 and an axial force sensor 44, and the output end of the electric cylinder 43 is fixedly connected with the variable-pitch shaft 101 of the paddle clamp assembly 100. The electric cylinder 43 is internally integrated with a displacement meter, which can detect the displacement of the output end of the electric cylinder 43 in real time. The axial force sensor 44 is used for detecting the axial force borne by the paddle clamp assembly 100 in real time. The electric cylinder 43 can provide a pulling force or a pushing force of 50KN.

[0045] When the fatigue testing device is used to perform fatigue testing on the paddle clamp assembly 100 of the helicopter, the electric cylinder 43 of the force applying unit 40 is fixedly connected with the third threaded hole of the variable-pitch shaft 101 through bolts. The guide rod 36 of the variable-pitch unit 30 is hinged with the variable-pitch rocker arm 102 and driven by the motor 32 to drive the paddle clamp assembly 100 to reciprocate at a small angle around the variable-pitch shaft 101. The variable-pitch unit 30 is used to perform variable-pitch movement and the force applying unit 40 is used to apply axial force, so as to simulate the actual force borne by the paddle clamp assembly 100 of the helicopter, thereby performing fatigue testing to test the service life.

[0046] The axial tension (compression) force of the force applying unit 40 can be controlled by a programmable script to meet the test requirements of different regular loads, thereby simulating the centrifugal force (force range: 0-50KN) of the blade. The device can display the applied axial tension (compression) force in real time on the computer and has the function of recording and storing test process data.

[0047] The pitch changing unit 30 can drive the blade clamp assembly 100 to make reciprocating pitch changing motion at a constant speed of not less than 650 RPM. The device can display the rotating speed in real time on the computer, and can display the horizontal force borne by the pitch changing rocker arm 102 in real time on the computer, and has the function of recording and storing test process data.

[0048] The data processing unit can adopt a conventional hardware system and software system, as long as it can realize the reception and processing of data of various sensors, and the control of the motor controller 31 and the electric cylinder controller 42. Further, the data processing unit can also accept input control instructions and manipulate the entire fatigue test device according to the instructions, and can display and save various data generated during the test for subsequent analysis.

[0049] The helicopter blade clamp assembly fatigue test device of the utility model can simulate the stress condition of the blade clamp assembly under different working conditions through the control of the motor controller 31 and the electric cylinder controller 42, thereby obtaining the fatigue life of the part through the fatigue test method, and improving the system stability of the helicopter.

[0050] In addition, through the cam mechanism of the pitch changing unit, high-frequency, reciprocating, small-angle pitch changing motion of the blade can be realized; through the force applying unit, the simulation of the centrifugal force generated by the motion of the blade can be realized, thereby improving the simulation authenticity of the stress condition of the thrust bearing in the blade clamp assembly, so that the performance of the helicopter blade clamp assembly can be tested more accurately.

[0051] The above is only a preferred specific embodiment of the utility model, but the protection scope of the utility model is not limited to this, any person skilled in the art can easily think of changes or replacements within the technical range disclosed by the utility model, which should be covered in the protection scope of the utility model.

Claims

1. A fatigue testing device for a helicopter pylon assembly, comprising: The utility model relates to a kind of variable-pitch test device for helicopter rotor, including main body support, positioning locking unit, variable-pitch unit, force unit and data processing unit;The positioning locking unit is arranged on the main body support, for installing and locking the paddle clamp assembly body to be detected;The variable-pitch unit is arranged on the main body support and is located in the side of the positioning locking unit, for driving the paddle clamp assembly body movement to simulate the reciprocating swing of variable-pitch rocker arm and paddle clamp when helicopter flies;The force unit is arranged on the main body support and is located above the positioning locking unit, for exerting tension to the paddle clamp assembly body to simulate centrifugal force formed by blade rotation in the process of rotation;The data processing unit is used for real-time recording sensor data, and sends control instruction to control the variable-pitch unit and force unit operation.

2. The fatigue testing device for a helicopter pylon assembly according to claim 1, characterized in that, The positioning locking unit includes a mounting shaft that is vertically and rotatably arranged on the main body support, and the mounting shaft is fixedly connected with the paddle clamp in the paddle clamp assembly body.

3. The fatigue testing apparatus for a helicopter pylon assembly according to claim 2, characterized in that, The positioning locking unit further includes a tapered roller bearing and a bearing seat, the bearing seat is fixedly arranged on the main body support, the tapered roller bearing is arranged on the bearing seat, and the lower end of the mounting shaft is arranged in the tapered roller bearing.

4. The fatigue testing apparatus for a helicopter pylon assembly according to claim 3, characterized in that, The positioning locking unit further includes a locking nut, which is sleeved on the mounting shaft and located above the tapered roller bearing, for axially limiting the mounting shaft.

5. The fatigue testing apparatus for a helicopter pylon assembly of claim 1, wherein, The variable-pitch unit includes a cam mechanism and a guide rod, one end of the guide rod is hingedly connected with the cam mechanism, and the other end of the guide rod is hingedly connected with the variable-pitch rocker arm of the paddle clamp assembly body.

6. The fatigue testing apparatus for a helicopter pylon assembly according to claim 5, characterized in that, The cam mechanism can drive the variable-pitch rocker arm to reciprocate within a range of ±10° through the guide rod.

7. The fatigue testing device for a helicopter pylon assembly according to claim 6, characterized in that, The variable-pitch unit further includes a counter-force seat, a motor and a speed reducer, the counter-force seat is fixedly arranged on the main body support, the motor and the speed reducer are arranged on the side of the counter-force seat away from the positioning locking unit, the cam mechanism is arranged on the other side of the counter-force seat, and the cam mechanism is connected with the output end of the speed reducer.

8. The fatigue testing device for a helicopter pylon assembly according to claim 7, characterized in that, The variable-pitch unit further includes a motor controller and a horizontal force sensor, the motor controller is used to control the rotating speed of the motor, and the horizontal force sensor can detect the force received by the variable-pitch rocker arm in real time.

9. The fatigue testing apparatus for a helicopter pylon assembly of claim 1, wherein, The force unit includes an electric cylinder, and the output end of the electric cylinder is fixedly connected with the variable-pitch shaft of the paddle clamp assembly body.

10. The fatigue testing apparatus for a helicopter pylon assembly according to claim 9, characterized in that, The force unit further includes an axial force sensor, which is used to detect the axial force received by the paddle clamp assembly body in real time.

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