CN215794524U

CN215794524U - Dynamic characteristic test fixture for aileron control system

Info

Publication number: CN215794524U
Application number: CN202120627703.2U
Authority: CN
Inventors: 崔保中; 徐坚; 孙曦; 张峰; 莫斌
Original assignee: Shaanxi Aircraft Industry Co Ltd
Current assignee: Shaanxi Aircraft Industry Co Ltd
Priority date: 2021-03-26
Filing date: 2021-03-26
Publication date: 2022-02-11
Anticipated expiration: 2031-03-26

Abstract

The utility model belongs to the technical field of aviation, and relates to a dynamic characteristic test fixture for an aileron control system. The device comprises a steering rod, aileron rotating end face teeth, fastening bolts, connecting end face teeth, fastening bolts, a torque coupler, a torque sensor and a hydraulic servo actuator. When the hydraulic servo actuator works, the steering wheel on the steering column is firstly detached, the connecting end face teeth are meshed with the rotary end face teeth of the ailerons and are fastened through the fastening bolts, then the torque coupler is fastened at the other end of the connecting end face teeth, the position of the hydraulic servo actuator is adjusted, and the square tenon on the torque coupler is inserted into the square hole on the end face of the torque sensor to transmit torque. When the hydraulic servo actuator is not in work, the square tenon on the torque connector is separated from the end face of the torque sensor, the fastening bolt is removed to loosen the torque connector and the teeth of the connecting end face, the steering wheel is restored to be installed, and the hydraulic servo actuator is removed. The utility model overcomes the defects of more dynamic characteristic clamp parts, difficult coaxiality adjustment, inconvenient disassembly and assembly, large abrasion and the like of the traditional aileron control system.

Description

Dynamic characteristic test fixture for aileron control system

Technical Field

The utility model belongs to the technical field of aviation, and particularly relates to a dynamic characteristic test fixture for an aileron control system.

Background

During the ground semi-physical test dynamic test of the airplane control system, the step and frequency sweep test must be carried out on the aileron control system so as to detect the dynamic characteristic of the aileron control system. The method for testing the step and the sweep frequency of the aileron control system is to use an actuator to send a step and sweep frequency signal on a steering wheel and use a sensor to measure the dynamic characteristics of the aileron control system on a control plane. In order to accurately measure the dynamic characteristics of the aileron steering system, the aileron steering wheel and the actuator are connected together during the test, which requires the actuator and the steering wheel to rotate coaxially, otherwise the test piece is abraded and deformed. The common method is to use a special clamp with a specific size as shown in fig. 1, and since a person involved in the test needs to adjust the position of the bending rod of the No. 6 part and the position of the coupler 7 to keep the same axis with the rotation center of the steering wheel when the person installs and adjusts the coaxiality of the No. 3 steering wheel and the No. 9 hydraulic servo actuator; in addition, the position of the No. 9 hydraulic servo actuator must be adjusted to be coaxial with the rotation center of the steering wheel, so that the installation and debugging links of the original clamp are more, the coaxiality of the steering wheel and the No. 9 swinging cylinder cannot be well maintained, the abrasion of each connecting piece is serious, the test data is unstable, and the test data is inconvenient to interpret; meanwhile, the fixture has the advantages of more mounting parts, more debugging parts, time and labor waste, increased unreliability and reduced test efficiency.

SUMMERY OF THE UTILITY MODEL

In order to overcome the defects in the prior art, the utility model provides the dynamic characteristic test fixture for the aileron control system, which is simple in coaxiality adjustment, convenient to disassemble and assemble, time-saving, labor-saving, quick in connection, stable and reliable.

An aileron control system dynamic behavior testing fixture comprising: the device comprises a steering column, aileron rotating end face teeth, a first fastening bolt, connecting end face teeth, a second fastening bolt, a torque coupler, a torque sensor and a hydraulic servo actuator;

the end of the steering column is provided with the rotary end face teeth of the ailerons;

the connecting end face teeth are meshed with the tooth parts of the flap rotating end face teeth; and the coupling end face teeth and the flap rotating end face teeth are fixed by the first fastening bolts;

the bottom of the coupling end face tooth is connected with the bottom of the torque coupler through a second fastening bolt;

the torque coupler bottom is connected with the torque sensor top;

and the bottom of the torque sensor is connected with a shaft of the hydraulic servo actuator through a second fastening bolt.

Further, a first flange plate is arranged at the bottom of the tooth of the connecting end surface; the bottom of the torque coupler is provided with a first disc, and the first flange plate at the bottom of the coupling end face tooth is fixedly connected with the first disc at the bottom of the torque coupler through a second fastening bolt.

Further, a first circular disc is arranged at the bottom of the torque coupler, and a square tenon is arranged in the center of the first circular disc; a boss is arranged in the center of the torque sensor, and a square hole matched with the square tenon is formed in the center of the boss; the square falcon and the square hole are used for cooperating the transmission moment of torsion.

Furthermore, the bottom of the torque sensor is provided with a second disc, a shaft of the hydraulic servo actuator is provided with a second flange plate, and the second flange plate and the second disc are fixedly connected through a second fastening bolt.

Further, the number of the coupling end face teeth is the same as that of the flap rotary end face teeth.

Further, the coupling face teeth have the same pitch as the flap rotary face teeth.

Compared with the prior art, the utility model has the beneficial effects that: by adopting the utility model, when the aileron control system is used for a step and frequency sweep test, only the steering wheel of the steering column 1 needs to be removed, the connecting end face teeth 4 are fastened on the aileron rotating end face teeth 2 through the first fastening bolts 3, and the torque generated by the hydraulic servo actuator 8 is transmitted to the aileron control system through the connection of the torque connector 6 and the torque sensor 7, so that the coaxial rotation of the hydraulic servo actuator 8 and the steering wheel can be kept, and the mechanical abrasion is reduced; in addition, the utility model reduces mechanical parts and one-time coaxiality adjustment, and only needs to adjust the rotation center of the hydraulic servo actuator 8 to be consistent with the rotation center of the steering wheel, thereby saving time and labor.

The dynamic characteristic clamp of the set of auxiliary wing control system can meet the operation requirements of different operators, is simple and feasible to install, improves the stability and consistency of test data, and can improve the test efficiency and quality.

Drawings

FIG. 1 is a schematic structural view of an original special fixture;

FIG. 2 is a schematic view of a modified clamp;

FIG. 3 is a schematic view of the flap rotary face tooth 2;

fig. 4 is a schematic view of the coupling end face teeth 4;

FIG. 5 is a schematic view of the torque coupling 6;

fig. 6 is a schematic diagram of the torque sensor 7;

wherein: 1. the structure comprises a steering column, 2. aileron rotating end face teeth, 3. first fastening bolts, 4. connecting end face teeth, 5. second fastening bolts, 6. torque connectors, 7. torque sensors and 8. hydraulic servo actuators.

Detailed Description

As shown in fig. 2, a test fixture for dynamic characteristics of an aileron control system comprises a steering column 1, aileron rotating end face teeth 2, first fastening bolts 3, connecting end face teeth 4, second fastening bolts 5, a torque coupler 6, a torque sensor 7 and a hydraulic servo actuator 8, wherein before each clamp body is connected, a steering wheel of the steering column 1 is firstly detached, the connecting end face teeth 4 are fastened on the aileron rotating end face teeth 2 through the first fastening bolts 3, the connecting end face teeth 4 are fastened with the torque coupler 6 through the second fastening bolts 5, the torque coupler 6 is provided with a square tenon matched with the torque sensor 7, and torque generated by the hydraulic servo actuator 8 is transmitted to the aileron control system through the connection of the torque coupler 6 and the torque sensor 7 so as to finish step and frequency sweep tests.

As shown in fig. 3, an aileron rotary end face tooth 2 is arranged at the end of a steering column 1, and is connected with a steering wheel through a first fastening bolt 3, when the dynamic characteristic test of an aileron steering system is carried out, the steering wheel shown in fig. 1 is removed so as to expose the aileron rotary end face tooth 2, and a connecting end face tooth 4 is meshed with the aileron rotary end face tooth 2 and is fastened through the first fastening bolt 3; as shown in fig. 4, the number of teeth and the pitch of the coupling end face teeth 4 and the flap rotating end face teeth 2 are consistent, the two teeth can be tightly fitted without slipping after being fastened, the flap rotating end face teeth 2 and the coupling end face teeth 4 are made of high-quality alloy steel, and the stiffness and the strength can be well guaranteed after heat treatment to prevent torque transmission failure. As shown in fig. 5, the torque coupler 6 and the coupling end face teeth 4 are fastened by a flange coupling using a second fastening bolt 5; the torque connector 6 is made of high-quality alloy steel, rigidity and strength can be well guaranteed after heat treatment, failure of torque transmission can be prevented, a square tenon on the torque connector is matched with a square hole in the torque sensor 7 shown in fig. 6 to transmit torque, the torque sensor 7 is connected with a flange plate on the hydraulic servo actuator 8 through bolts, and the position of the hydraulic servo actuator 8 needs to be adjusted to meet the condition that the square tenon on the torque connector 6 and the square hole on the torque sensor 7 are matched.

When the hydraulic servo actuator 8 works, the hydraulic servo actuator generates rotating torque to drive the aileron control system to respond through the torque coupler 6 and the connecting end face teeth 4; when the device does not work, the square tenon and the square hole on the torque coupler 6 and the torque sensor 7 are separated, and the power source is cut.

Claims

1. The utility model provides an aileron operating system dynamic characteristic test fixture which characterized in that: the jig includes: the device comprises a steering column, aileron rotating end face teeth, a first fastening bolt, connecting end face teeth, a second fastening bolt, a torque coupler, a torque sensor and a hydraulic servo actuator;

the torque coupler bottom is connected with the torque sensor top;

2. The aileron control system dynamic behavior testing fixture of claim 1, wherein: the bottom of the connecting end face tooth is provided with a first flange plate; the bottom of the torque coupler is provided with a first disc, and the first flange plate at the bottom of the coupling end face tooth is fixedly connected with the first disc at the bottom of the torque coupler through a second fastening bolt.

3. The aileron control system dynamic behavior testing fixture of claim 1, wherein: the bottom of the torque coupler is provided with a first disc, and the center of the first disc is provided with a square tenon; a boss is arranged in the center of the torque sensor, and a square hole matched with the square tenon is formed in the center of the boss; the square falcon and the square hole are used for cooperating the transmission moment of torsion.

4. The aileron control system dynamic behavior testing fixture of claim 1, wherein: the bottom of the torque sensor is provided with a second disc, a shaft of the hydraulic servo actuator is provided with a second flange plate, and the second flange plate and the second disc are fixedly connected through a second fastening bolt.

5. The aileron control system dynamic behavior testing fixture of claim 1, wherein: the number of the coupling end face teeth is the same as that of the flap rotary end face teeth.

6. The aileron control system dynamic behavior testing fixture of claim 5, wherein: the coupling face teeth have the same pitch as the flap rotary face teeth.