阅读说明：本技术 跷跷板式旋翼疲劳试验装置及其工作方法 (Seesaw type rotor wing fatigue test device and working method thereof ) 是由 李宜恒 王华明 范瑶 朱清华 于 2020-05-07 设计创作，主要内容包括：本发明提供了一种跷跷板式旋翼疲劳试验装置及其工作方法,该装置包括框架单元以及固定在框架单元内部的桨根固定单元、激振力单元和离心力单元。试验电机通过变频器进行转速调整后带动偏心轮转动,经过连杆机构,带动激振盒,使其根据试验输入需求产生模拟旋翼各种工况下的挥舞力矩和摆振力矩载荷；同时通过手拉葫芦进行离心力施加,离心力通过钢丝绳连杆机构传至钢丝绳滑轮组,进而传递在桨叶试验件；最后通过动态应变测量系统监测剖面的各通道的振幅,得到旋翼疲劳试验的相应数据。本发明针对旋翼机常用的跷跷板式旋翼进行设计,具有结构简单,使用方便可靠等优点。(The invention provides a seesaw type rotor wing fatigue test device and a working method thereof. The test motor drives the eccentric wheel to rotate after rotating speed adjustment is carried out through the frequency converter, and drives the excitation box through the link mechanism, so that the excitation box can generate flapping moment and shimmy moment loads under various working conditions of the simulation rotor wing according to test input requirements; meanwhile, centrifugal force is applied through the chain block, and the centrifugal force is transmitted to the steel wire rope pulley block through the steel wire rope connecting rod mechanism and then transmitted to the blade test piece; and finally, monitoring the amplitude of each channel of the section by a dynamic strain measurement system to obtain corresponding data of a rotor wing fatigue test. The invention is designed aiming at the common seesaw type rotor wing of the rotorcraft, and has the advantages of simple structure, convenient and reliable use and the like.)

1. The utility model provides a seesaw formula rotor fatigue test device which characterized in that: the device comprises a frame unit, and a paddle root fixing unit, an exciting force unit and a centrifugal force unit which are fixed in the frame unit;

the propeller root fixing unit consists of an annular groove flange plate and an inclined plane plate, the annular groove flange plate is connected with the rotor hub and the inclined plane plate, and the blade test piece is arranged in the middle of the annular groove flange; the inclined plane plate is connected with the annular ring flange and the frame unit, and the pre-cone angle of the seesaw type rotor wing is simulated and counteracted;

the centrifugal force unit provides a centrifugal force load under a simulated real working condition and comprises a chain block, a force sensor, a steel wire rope connecting rod mechanism and a steel wire rope pulley block which are sequentially connected, wherein the chain block and the steel wire rope connecting rod mechanism are fixedly connected with the frame unit, and the steel wire rope pulley block is connected with the exciting force unit;

the excitation force unit simulates flapping moment and shimmy moment loads borne by the rotor under various working conditions and comprises an excitation box, a connecting rod mechanism, an eccentric wheel and a test motor with a frequency converter, which are connected in sequence, wherein the excitation box is connected with a steel wire rope pulley block.

2. A teeterboard rotor fatigue test apparatus as defined in claim 1, wherein: the steel wire rope connecting rod mechanism is composed of a base, a supporting strip and a connecting box section which are sequentially connected, the base is installed on the frame unit through bolts and is connected with the connecting box through the supporting strip, and the connecting box is simultaneously connected with the force sensor and the steel wire rope pulley block.

3. A teeterboard rotor fatigue test apparatus as claimed in claim 1 or claim 2, wherein: the steel wire rope connecting rod mechanism is provided with a ball bearing, and the ball bearing controls the steel wire rope connecting rod mechanism to rotate in a vertical plane.

4. A teeterboard rotor fatigue test apparatus as defined in claim 1, wherein: the frame unit comprises a test frame and a plurality of inclined support structures for fixing the test frame.

5. A teeterboard rotor fatigue test apparatus as defined in claim 1, wherein: and vibration excitation box baffles are arranged on two sides of the vibration excitation box and vertically limit the up-and-down reciprocating motion of the vibration excitation box.

6. A teeterboard rotor fatigue test apparatus as defined in claim 1, wherein: and a protective net is arranged on the outer side of the frame unit.

7. A working method of a seesaw type rotor wing fatigue test device is characterized by comprising the following steps:

1) fixing the test frame on the ground, mounting a blade test piece in the blade root fixing unit, attaching a corresponding strain gauge to the blade test piece according to requirements, and externally connecting a dynamic strain measurement system;

2) the test motor drives the eccentric wheel to rotate after rotating speed adjustment is carried out through the frequency converter, and drives the excitation box through the link mechanism, so that the excitation box can generate flapping moment and shimmy moment loads under various working conditions of the simulation rotor wing according to test input requirements;

3) meanwhile, centrifugal force is applied through the chain block, the magnitude of the centrifugal force is measured through a force sensor connected between the chain block and a steel wire rope connecting rod mechanism, the centrifugal force is transmitted to a steel wire rope pulley block through the steel wire rope connecting rod mechanism and then transmitted to a blade test piece, and the steel wire rope connecting rod mechanism enables the connecting rod mechanism to rotate in a vertical plane through installing a ball bearing;

4) and monitoring the amplitude of each channel of the section by using a dynamic strain measurement system to obtain corresponding data of a rotor wing fatigue test.

Technical Field

The invention provides a seesaw type rotor wing fatigue test device and a working method thereof, relates to a seesaw type rotor wing and blade fatigue test technology, and is suitable for the fields of rotor wing blade fatigue tests and aeronautical navigation of a gyroplane.

Background

In the flight process of the rotor type aircraft, the rotor bears the complex alternating load effect, the fatigue problem is very prominent, and the safety, reliability and economy of the rotorcraft are directly influenced. The seesaw type rotor wing is suitable for the gyroplane, and the seesaw type rotor wing fatigue test is an important basis for the gyroplane to obtain evidence for airworthiness and the rotor wing to be in fixed life.

At present, most of rotor fatigue tests are devices for helicopter rotor fatigue tests, and the common characteristics of the devices are that the rotor fatigue test system and the devices are too complex due to the complex working condition of the helicopter rotor, the manufacturing cost and the test cost are too high, and the manufacturing period and the test period are very long. And too complicated system leads to each simulation load part to have great mutual interference in rotor fatigue test, leads to rotor fatigue test result and decide the life analysis inaccurate, directly influences the test result.

Therefore, the conventional rotor fatigue testing device has the following defects:

1. the design of the test device is complex;

2. the manufacturing cost and the test cost are high, and the period is long;

3. because of the defects, the traditional rotor wing fatigue test device is not suitable for rotor wing fatigue test and blade life-fixing analysis in the process of aeronautical evidence collection of the gyroplane.

Disclosure of Invention

The invention provides a seesaw type rotor wing fatigue test device and a working method thereof in order to solve the problems in the prior art, and the seesaw type rotor wing fatigue test device is designed aiming at a seesaw type rotor wing commonly used by a rotorcraft, and has the advantages of simple structure, convenience and reliability in use and the like.

The invention provides a seesaw type rotor wing fatigue test device which comprises a frame unit, and a propeller root fixing unit, an exciting force unit and a centrifugal force unit which are fixed in the frame unit.

The propeller root fixing unit consists of an annular groove flange plate and an inclined plane plate, the annular groove flange plate is connected with the rotor hub and the inclined plane plate, and the blade test piece is arranged in the middle of the annular groove flange; the inclined plane plate is connected with the annular ring flange and the frame unit, and the pre-cone angle of the seesaw type rotor wing is simulated and counteracted.

The centrifugal force unit provides a centrifugal force load under a simulated real working condition and comprises a chain block, a force sensor, a steel wire rope connecting rod mechanism and a steel wire rope pulley block which are sequentially connected, wherein the chain block and the steel wire rope connecting rod mechanism are fixedly connected with the frame unit, and the steel wire rope pulley block is connected with the exciting force unit.

The excitation force unit simulates flapping moment and shimmy moment loads borne by the rotor under various working conditions and comprises an excitation box, a connecting rod mechanism, an eccentric wheel and a test motor with a frequency converter, which are connected in sequence, wherein the excitation box is connected with a steel wire rope pulley block.

The steel wire rope connecting rod mechanism is further improved and consists of a base, a supporting strip and a connecting box section which are sequentially connected, the base is installed on the frame unit through bolts and is connected with the connecting section box through the supporting strip, and the connecting section box is simultaneously connected with the force sensor and the steel wire rope pulley block. The steel wire rope connecting rod mechanism is provided with a ball bearing, and the ball bearing controls the steel wire rope connecting rod mechanism to rotate in a vertical plane.

In a further improvement, the frame unit comprises a test frame and a plurality of inclined support structures for fixing the test frame.

The vibration excitation box is further improved, vibration excitation box baffles are arranged on two sides of the vibration excitation box, and vertical limiting is carried out on the vertical reciprocating motion of the vibration excitation box.

In a further improvement, a protective net is arranged outside the frame unit.

The invention also provides a working method of the seesaw type rotor wing fatigue test device, which comprises the following steps:

1) the test frame is fixed on the ground, the paddle test piece is installed in the paddle root fixing unit, the corresponding strain gauge is attached to the paddle test piece according to requirements, and the paddle test piece is externally connected with a dynamic strain measurement system.

2) The test motor drives the eccentric wheel to rotate after rotating speed adjustment is carried out through the frequency converter, and the vibration box is driven through the link mechanism, so that the vibration box can generate flapping moment and pendulum vibration moment loads under various working conditions of the simulation rotor wing according to test input requirements.

3) Meanwhile, centrifugal force is applied through the chain block, the magnitude of the centrifugal force is measured through a force sensor connected between the chain block and a steel wire rope connecting rod mechanism, the centrifugal force is transmitted to a steel wire rope pulley block through the steel wire rope connecting rod mechanism and then transmitted to the paddle test piece, the steel wire rope connecting rod mechanism enables the connecting rod mechanism to rotate in a vertical plane through installing a ball bearing, the vibration amplitude of the end portion of the paddle test piece, which is transmitted to the force sensor and the chain block, is effectively weakened, and the influence on experiment safety and load simulation is avoided.

4) And monitoring the amplitude of each channel of the section by using a dynamic strain measurement system to obtain corresponding data of a rotor wing fatigue test.

The invention has the beneficial effects that:

1. the rotor wing fatigue device is designed aiming at the see-saw rotor wing of the rotorcraft, has a relatively simple structure, is convenient and reliable to use, is convenient for disassembling and replacing fatigue-prone components or parts, can collect various strain values of the rotor wing, and records the cycle times and the test process;

2. can realize rotor centrifugal force load simulation and input through chain block, wire rope link mechanism to the effectual vibration of avoiding paddle test piece tip arouses after transmitting on force sensor and the chain block to swing by a wide margin, causes the influence to experimental security and load simulation.

3. The inclined plane board in the propeller root fixing unit can realize the offset of the rotor wing pre-cone angle, so that the rotor wing blades are in a horizontal state in a test, the position of the test design load application is convenient, and the fixed support boundary condition of the rotor wing of the rotorcraft during normal flight can be simulated.

Drawings

FIG. 1 is a main body diagram of a seesaw type rotor wing fatigue test device of the invention;

in the figure, a paddle root fixing unit 1, an excitation box 2, an excitation box baffle 3, a test motor 4, a force sensor 5, a chain block 6, an eccentric wheel 7, a test frame 8, an inclined support 9, a frequency converter 10, a link mechanism 11, a steel wire rope pulley block 12, a steel wire rope link mechanism 13 and a paddle test piece 14.

Fig. 2 is a schematic view of a root securing unit 1 according to the invention;

in the figure, a ring groove flange 15 and a bevel plate 16.

FIG. 3 is a schematic view of a wire rope linkage 13 of the present invention;

in the figure, the base 17, the support strip 18, the connection box 19.

FIG. 4 is a schematic diagram of an excitation force unit of the present invention;

in the figure, an excitation box 2, an excitation box baffle 3, a test motor 4, an eccentric wheel 7, a link mechanism 11, a steel wire rope pulley block 12 and a blade test piece 14 are arranged.

Detailed Description

The invention will be further explained with reference to the drawings.

The propeller root fixing unit 1 is used for fixing a propeller root part of a test piece propeller blade of the test device and simulating the real installation situation of the seesaw type rotor wing propeller root.

The excitation box 2, the test motor 4, the eccentric wheel 7, the frequency converter 10 and the link mechanism 11 jointly form an excitation force unit of the test device, and are used for simulating flapping moment and shimmy moment loads borne by the rotor under various working conditions in a test, as shown in fig. 4, wherein the excitation box 2, the link mechanism 11, the eccentric wheel 7 and the test motor 4 with the frequency converter are sequentially connected, and the excitation box 2 is connected with the steel wire rope pulley block 12.

The force sensor 5, the chain block 6, the steel wire rope pulley block 12 and the steel wire rope link mechanism 13 jointly form a centrifugal force unit of the test device, and the centrifugal force unit is used for simulating and recording the centrifugal force applied to the blades in the rotation of the rotor wing in the test.

The vibration excitation box baffles 3 are positioned on two sides of the vibration excitation box 2 and used for limiting vertical reciprocating motion of the vibration excitation box 2 in a test and preventing the vibration excitation box from deflecting due to the motion.

The test frame 8 and the inclined supports 9 jointly form a frame unit of the test device, and the frame unit is used for splicing the whole test device to enable each part to play respective roles.

The blade test piece 14 is a test piece of the test device.

As shown in FIG. 2, the blade root fixing unit 1 is a schematic diagram and consists of a ring groove flange 15 and an inclined plane plate 16, and a blade test piece is arranged in the middle of the ring groove flange 15. The ring channel flange 15 is used for connecting the rotor hub and the bevel board, and the rotor can carry out angle modulation. The ramp 16 is used to simulate and cancel the pre-cone angle of the actual see-saw rotor, leaving the blade level. Meanwhile, the inclined plane plate 16 is also connected with the annular groove flange 15 and the test frame 8 and bears the action of centrifugal force. The steel wire rope connecting rod mechanism is provided with a ball bearing, and the ball bearing controls the steel wire rope connecting rod mechanism to rotate in a vertical plane.

Fig. 3 is a schematic view of a wire rope link mechanism 13, which is composed of a base 17, a support strip 18 and a connection box section 19, and is used for preventing the vibration at the end of the blade test piece 14 from being transmitted to the force sensor 5 and the chain block 6 to cause large-amplitude swing, and thus, the influence on the experimental safety and the load simulation is avoided. The base is mounted on the test frame 8 by bolts and is connected with a connecting section box 19 by a support strip 18, and the connecting section box 19 is simultaneously connected with the force sensor 5 and the steel wire rope pulley block 12.

The specific working principle of the invention is as follows:

the fatigue test device is fixed on the ground through a test frame 8, a blade test piece 14 is installed on the blade root fixing unit 1, and the corresponding strain gauge is attached to the blade (and the hub) according to requirements and is externally connected with a dynamic strain measurement system.

The test motor 4 drives the eccentric wheel 7 to rotate after rotating speed adjustment is carried out through the frequency converter 10, and drives the excitation box 2 through the link mechanism 11, so that the excitation box can generate flapping moment and shimmying moment loads under various working conditions of the simulation rotor wing according to test input requirements.

Simultaneously, centrifugal force is applied through the chain block 6, the size of physical force is measured through the force sensor 5 connected between the chain block 6 and the steel wire rope connecting rod mechanism 13, the centrifugal force is transmitted to the steel wire rope pulley block 12 through the steel wire rope connecting rod mechanism 13 and then transmitted to the paddle test piece 14, the steel wire rope connecting rod mechanism 13 is provided with a ball bearing through installation, so that the connecting rod mechanism can rotate in a vertical plane, the vibration amplitude of the end part of the paddle test piece 14, transmitted to the force sensor 5 and the chain block 6, and the influence on experimental safety and load simulation is avoided.

Finally, based on the above, the amplitude of each channel of the profile can be monitored by a dynamic strain measurement system, and corresponding data of the rotor fatigue test can be obtained.

While the invention has been described in terms of its preferred embodiments, it will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention.