阅读说明：本技术 一种直升机航向锁尾试验装置及其方法 (Helicopter course tail locking test device and method thereof ) 是由 董鹰 张伟 成奕东 石祥坤 王嘉 于 2020-04-30 设计创作，主要内容包括：本发明属于航空技术领域,公开了一种直升机航向锁尾试验装置及其方法,包括：底座、定位轴、第一深沟球轴承、旋转盘、限位片；直升机固定在旋转盘上；底座固定在地面上,底座中心处设置有钻孔,第一深沟球轴承嵌入在钻孔中,定位轴安装在深沟球轴承内；底座上表面绕圆心设置有至少一圈圆孔,每个圆孔内嵌入一个万向球轴承；旋转盘同轴安装在底座的上方,且旋转盘的下表面与底座上的多个万向球轴承的上表面接触；限位片固定于底座的上表面,且限位片上方伸出部分处于旋转盘的上方,与旋转盘之间留有间隙,装置结构简单,可应用于所有的直升机/无人直升机,其尺寸可根据直升机/无人直升机尺寸进行适配。(The invention belongs to the technical field of aviation, and discloses a helicopter course tail locking test device and a method thereof, wherein the helicopter course tail locking test device comprises the following steps: the device comprises a base, a positioning shaft, a first deep groove ball bearing, a rotating disc and a limiting sheet; the helicopter is fixed on the rotating disc; the base is fixed on the ground, a drill hole is formed in the center of the base, the first deep groove ball bearing is embedded into the drill hole, and the positioning shaft is installed in the deep groove ball bearing; at least one circle of round holes are arranged on the upper surface of the base around the circle center, and a universal ball bearing is embedded into each round hole; the rotating disc is coaxially arranged above the base, and the lower surface of the rotating disc is in contact with the upper surfaces of the universal ball bearings on the base; the limiting piece is fixed on the upper surface of the base, the extending part above the limiting piece is positioned above the rotating disk, and a gap is reserved between the extending part and the rotating disk.)

1. The utility model provides a helicopter course lock tail test device which characterized in that, the device includes: the device comprises a base (4), a positioning shaft (5), a first deep groove ball bearing (6), a rotating disc (3) and a limiting piece (2);

the helicopter is fixed on the rotating disc (3);

the positioning device comprises a base (4), a drill hole, a first deep groove ball bearing (6), a positioning shaft (5) and a second deep groove ball bearing (6), wherein the base (4) is fixed on the ground, the center of the base (4) is provided with the drill hole, the first deep groove ball bearing (6) is embedded into the drill hole, and the positioning shaft (5) is installed in the deep groove ball bearing (6);

at least one circle of round holes are formed in the upper surface of the base around the circle center, and a universal ball bearing (7) is embedded in each round hole;

the rotating disc (3) is coaxially arranged above the base (4), and the lower surface of the rotating disc (3) is in contact with the upper surfaces of the universal ball bearings on the base (4);

the limiting piece is fixed on the upper surface of the base (4), and the extending part above the limiting piece is positioned above the rotating disk, and a gap is reserved between the limiting piece and the rotating disk.

2. A helicopter course lock tail test device as claimed in claim 1, said device further comprising: a second deep groove ball bearing;

the center of the rotating disc is provided with a drill hole, the second deep groove ball bearing is embedded into the drill hole, and the positioning shaft is installed in the second deep groove ball bearing.

3. The helicopter course lock tail test device of claim 1, wherein the base is a metal disc and the rotating disc is a metal disc.

4. The helicopter course lock tail test device of claim 1, characterized by that, the height of a plurality of universal ball bearings is the same.

5. The helicopter course lock tail test device of claim 1, wherein the number of the limiting pieces is four, and eight countersunk head screws are respectively fixed on the upper surface of the base at intervals of 90 degrees.

6. The helicopter course lock tail test device of claim 1, wherein the base upper surface is provided with two circles of round holes around the center of a circle, eight round holes per circle, and the round holes are evenly distributed.

7. A helicopter heading tail-lock test method applied to the test device as claimed in any one of claims 1-5, the method comprising:

fixing the helicopter on the upper surface of the rotating disc;

when the helicopter is started and the rotor rotates, if the counter torque of the rotor is not equal to the counter force of the tail rotor, the helicopter rotates in the yaw direction to drive the rotating disk to rotate together;

and the helicopter stops rotating by adjusting the main pitch and the tail pitch of the rotor wing, so that a group of angle matching data of the main pitch and the tail pitch is obtained.

8. A helicopter heading tail-lock test method applied to the test device as claimed in any one of claims 1-5, the method comprising:

fixing the helicopter on the upper surface of the rotating disc;

when the helicopter is started and the rotors rotate, if the reactive torques of the two main propellers of the double rotors are not equal, the helicopter rotates in the yaw direction to drive the rotating disk to rotate together;

the helicopter stops rotating by adjusting the two main pitches of the double rotors, so that differential matching data of the two main pitches are obtained.

Technical Field

The invention belongs to the technical field of aviation, and particularly relates to a helicopter course tail locking test device and a method thereof.

Background

The matching of a main pitch and a tail pitch (dual-rotor pitch differential motion of a dual-rotor helicopter/unmanned helicopter) in the development of the existing helicopter/unmanned helicopter is generally realized by means of design, calculation, analysis, simulation, a simulator, special test equipment, a three-axis turntable and the like.

For helicopters/unmanned helicopters developed in folk in recent years, on one hand, the design, calculation and analysis capabilities are not enough, on the other hand, the cost of simulation, a simulator, special equipment, a three-axis turntable and the like is high, no better solution is provided for the matching problem of the main pitch and the tail pitch of the helicopters/unmanned helicopters before takeoff, the matching relation of the main pitch and the tail pitch is adjusted through trial flight in many cases, and the method has great potential safety hazards.

Disclosure of Invention

In view of the above problems, an object of the present invention is to provide a helicopter course locking tail test device and a method thereof, the device has a simple structure, can be applied to all helicopters/unmanned helicopters, can be adapted in size according to the sizes of the helicopters/unmanned helicopters, and has a great potential application prospect and a great market.

In order to achieve the purpose, the invention is realized by adopting the following technical scheme.

The first technical scheme is as follows:

a helicopter course tail-locking test device, the device includes: the device comprises a base 4, a positioning shaft 5, a first deep groove ball bearing 6, a rotating disc 3 and a limiting piece 2;

the helicopter is fixed on the rotating disc 3;

the base 4 is fixed on the ground, a drill hole is formed in the center of the base 4, the first deep groove ball bearing 6 is embedded into the drill hole, and the positioning shaft 5 is installed in the deep groove ball bearing 6;

at least one circle of round holes are formed in the upper surface of the base around the circle center, and a universal ball bearing 7 is embedded into each round hole;

the rotating disc 3 is coaxially arranged above the base 4, and the lower surface of the rotating disc 3 is in contact with the upper surfaces of a plurality of universal ball bearings on the base 4;

the limiting piece is fixed on the upper surface of the base 4, and the extending part above the limiting piece is positioned above the rotating disk, and a gap is reserved between the limiting piece and the rotating disk.

The first technical scheme of the invention has the characteristics and further improvements that:

(1) the device further comprises: a second deep groove ball bearing;

the center of the rotating disc is provided with a drill hole, the second deep groove ball bearing is embedded into the drill hole, and the positioning shaft is installed in the second deep groove ball bearing.

(2) The base is a metal disc, and the rotary disc is a metal disc.

(3) The heights of the universal ball bearings are the same.

(4) The number of the limiting pieces is four, and the limiting pieces are fixed on the upper surface of the base respectively by eight countersunk head screws at intervals of 90 degrees.

(5) The base upper surface is provided with two circles of round holes around the centre of a circle, eight round holes per circle, and evenly distributed.

The second technical scheme is as follows:

a helicopter course tail locking test method is applied to a test device in the technical scheme I and comprises the following steps:

fixing the helicopter on the upper surface of the rotating disc;

when the helicopter is started and the rotor rotates, if the counter torque of the rotor is not equal to the counter force of the tail rotor, the helicopter rotates in the yaw direction to drive the rotating disk to rotate together;

and the helicopter stops rotating by adjusting the main pitch and the tail pitch of the rotor wing, so that a group of angle matching data of the main pitch and the tail pitch is obtained.

The third technical scheme is as follows:

a helicopter course tail locking test method is applied to a test device in the technical scheme I and comprises the following steps:

fixing the helicopter on the upper surface of the rotating disc;

when the helicopter is started and the rotors rotate, if the reactive torques of the two main propellers of the double rotors are not equal, the helicopter rotates in the yaw direction to drive the rotating disk to rotate together;

the helicopter stops rotating by adjusting the two main pitches of the double rotors, so that differential matching data of the two main pitches are obtained.

The helicopter/unmanned helicopter is characterized in that the vertical movement of the helicopter/unmanned helicopter has a coupling effect with the course movement around the main rotor shaft in the process of controlling the increase or decrease of the main pitch, and the course movement can be generated when the helicopter/unmanned helicopter vertically rises or falls, so that the helicopter/unmanned helicopter does not need to firstly complete the matching relationship between the main pitch and the tail pitch (the differential motion of two different main pitches for a double-rotor helicopter/unmanned helicopter) in the design and ground test, the matching relation is verified through theoretical calculation and simulation on one hand and experiment on the other hand, the course locking tail test device of the helicopter/unmanned helicopter in the technical scheme of the invention can be applied to matching of main pitches and tail pitches of helicopters/unmanned helicopters of all types or differential matching of two main pitches of a dual-rotor helicopter/unmanned helicopter. Compared with the prior art, the invention has simple structure and no special material or equipment requirement, can be applied to all helicopters/unmanned helicopters, can be adapted according to the sizes of the helicopters/unmanned helicopters, is easy to popularize, has larger potential market and has larger economic benefit.

Drawings

FIG. 1 is a general diagram of a helicopter course tail locking test device;

FIG. 2 is a diagram illustrating an exemplary application of a helicopter heading tail-locking test device;

wherein, 1-countersunk head screw; 2-limiting sheet; 3-rotating the disc; 4-a base; 5-positioning the shaft; 6-deep groove ball bearing; 7-universal ball bearing.

Detailed Description

The invention provides a helicopter/unmanned helicopter course tail locking test device, which can be used for carrying out ground course tail locking test before flight on a newly researched or improved helicopter/unmanned helicopter. The device can be placed on the ground, and a helicopter/unmanned helicopter which needs to carry out a ground course debugging test is fixed on the upper surface of a rotating disk of the device, so that the device is used for carrying out a test on the matching relation between the total pitch of main propellers and the pitch of tail propellers of the helicopter/unmanned helicopter (for the twin-rotor helicopter/unmanned helicopter, the two main propellers are differential motions).

The device can fix the helicopter/unmanned helicopter on the test device, and the rotating disk on the test device is observed to adjust the tail pitch by increasing and decreasing the total pitch, so that the corresponding relation between any main pitch and the tail pitch is obtained (or the two main pitches of the dual-rotor helicopter/unmanned helicopter are respectively adjusted, so that the differential matching relation between the two main pitches is obtained).

The invention relates to a helicopter/unmanned helicopter course tail locking test device, which comprises a base 4, a positioning shaft 5, a deep groove ball bearing 6, a universal ball bearing 7, a rotating disk 3, a limiting plate 2 and a countersunk head screw 1, wherein the positioning shaft 5 is arranged on the base;

the base 4 is a metal disc and is placed on the ground, two deep groove ball bearings 6 are drilled in the circle center of the base 4, a positioning shaft 5 is installed in each deep groove ball bearing 6, two circles of round holes are respectively drilled in the upper surface of the base 4 around the circle center, eight round holes are drilled in each circle, sixteen universal ball bearings 7 are embedded in sixteen round holes of the base 4, the sixteen universal ball bearings 7 are guaranteed to roll flexibly, and the heights of the universal ball bearings 7 are consistent;

the rotary disk 3 is a metal disc, two deep groove ball bearings 6 are embedded into a hole drilled in the center of the rotary disk 3, the rotary disk 3 and the two deep groove ball bearings 6 embedded in the rotary disk are installed above the base 4 together, the base 4 and the rotary disk 3 are kept coaxial, the upper surfaces of sixteen universal ball bearings 7 are kept to be in contact with the lower surface of the rotary disk 3 and are used for supporting the rotary disk 3 and a helicopter/unmanned helicopter on the rotary disk 3, the four limiting pieces 2 are fixed to the upper surface of the base 4 at intervals of 90 degrees by eight countersunk head screws 1 respectively, the protruding portion above the limiting piece 4 is guaranteed to be located above the rotary disk 3, and a certain gap is reserved so that the rotary disk 3 can rotate freely around.

As shown in fig. 2, the helicopter/unmanned helicopter may be fixed on the upper surface of the rotating disk 3, when the helicopter/unmanned helicopter is started and the rotor rotates, if the counter torque of the rotor is not equal to the counter force of the tail rotor (or the counter torque of the two main propellers of the dual rotor), the helicopter may generate rotation in the yaw direction, and drive the rotating disk to rotate together, and the helicopter/unmanned helicopter may stop rotating by adjusting the main pitch and the tail pitch of the rotor (or the two main pitches of the dual rotor), so as to obtain a set of matching data of the main pitch and the tail pitch (or the differential matching data of the two main pitches), and in turn, collect enough data points, so as to gradually determine the matching curves of the different main pitches and the tail pitch (or the differential matching curves of the two main pitches), thereby being used for controlling the system.

The helicopter/unmanned helicopter is characterized in that the vertical movement of the helicopter/unmanned helicopter has a coupling effect with the course movement around the main rotor shaft in the process of controlling the increase or decrease of the main pitch, and the course movement can be generated when the helicopter/unmanned helicopter vertically rises or falls, so that the helicopter/unmanned helicopter does not need to firstly complete the matching relationship between the main pitch and the tail pitch (the differential motion of two different main pitches for a double-rotor helicopter/unmanned helicopter) in the design and ground test, the matching relation is verified through theoretical calculation and simulation on one hand and experiment on the other hand, the course tail locking test device for the helicopter/unmanned helicopter provided by the patent can be applied to matching of main pitches and tail pitches of all types of helicopters/unmanned helicopters or differential matching of two main pitches of a dual-rotor helicopter/unmanned helicopter.

Compared with the prior art, the invention has simple structure and no special material or equipment requirement, can be applied to all helicopters/unmanned helicopters, can be adapted according to the sizes of the helicopters/unmanned helicopters, is easy to popularize, has larger potential market and has larger economic benefit.