CN-121973949-A - Life test method for angle compensator of high-pressure pipeline of airplane

CN121973949ACN 121973949 ACN121973949 ACN 121973949ACN-121973949-A

Abstract

The invention provides a life test method of an angle compensator of an aircraft high-pressure pipeline, which comprises the following steps of repeating a life test for preset life test times, wherein the preset life test times are determined according to an aircraft service life a, a working time b of the angle compensator in each flight cycle, a working time c of the angle compensator additionally added in the whole aircraft service life and a fatigue dispersion coefficient d of the angle compensator, and in each life test, the angle compensator is controlled to be at a maximum test angle, and the working pressure of the angle compensator is increased to the maximum pressure for only part of time. The actual working condition is simulated, the safety margin is considered, and the development risk is reduced.

Inventors

ZHOU XIAOLI
REN XIAOCHAO
CHEN XUPENG

Assignees

太原航空仪表有限公司

Dates

Publication Date: 20260505
Application Date: 20251227

Claims (8)

1. The service life test method of the angle compensator of the high-pressure pipeline of the aircraft is characterized by comprising the following steps of: The life test is repeated for preset life test times, wherein the preset life test times are determined according to the service life a of the aircraft, the working times b of the angle compensator in each flight cycle, the working times c of the angle compensator additionally added in the service life of the whole aircraft and the fatigue dispersion coefficient d of the angle compensator; in each life test, the test procedure control scheme was: s1, when the angle compensator is at a minimum angle and the working pressure of the angle compensator is lowest, the working pressure of the angle compensator is raised to the maximum pressure; S2, after the maximum pressure is maintained for at least a preset time period, the angle compensator starts to deflect until the maximum test angle is reached; S3, controlling the working pressure of the angle compensator to start to release pressure, controlling the angle compensator to keep at least a preset time length under a maximum test angle after the pressure release is finished, and controlling the angle compensator to deflect to a minimum angle.
2. The method of claim 1, wherein the aircraft life is the number of flight cycles.
3. The method for testing the service life of the angle compensator of the high-pressure pipeline of the airplane according to claim 2, the life test number n= (a+b+c) d.
4. The method for testing the life of the angle compensator of the high-pressure pipeline of the airplane according to claim 1, wherein the installation direction of the angle compensator of the high-pressure pipeline of the airplane is kept unchanged in all life tests.
5. The method of claim 1, wherein the angle compensator is maintained at a minimum angle for at least 2 seconds.
6. The method of claim 1, wherein the angle compensator is maintained at a maximum angle for at least 2 seconds.
7. The method of claim 1, wherein the maximum period of each life test is no more than 7 seconds.
8. The method for testing the life of the angle compensator of the high-pressure pipeline of the airplane according to claim 1, wherein the preset time period is 1 second.

Description

Life test method for angle compensator of high-pressure pipeline of airplane Technical Field The invention belongs to the technical field of tests of angle compensators of high-pressure pipelines of airplanes, and particularly relates to a life test method of an angle compensator of an airplane high-pressure pipeline. Background As the compensating device of the high-pressure pipeline of the aircraft, the angle compensator is used for compensating the angle of the displacement of the pipeline caused by the change of temperature and pressure, the product of the type is widely applied to the high-pressure pipeline of the aircraft in a compact structure and a long service life, and is generally welded with the installation form of the pipeline, so the service life of the type compensator is the same as the service life of the aircraft, and how to verify that the angle compensator has the same service life as the aircraft becomes a key technology for developing the product. The conventional verification method uses the synchronization of the pressure cycle and the displacement cycle as the verification conditions, namely, when the pressure of the angle compensator is maximum, the compensation angle is the most severe working condition of the angle compensator when the angle compensator works, as shown in fig. 1, if the working condition is used as the test verification working condition, the assessment is too severe. Taking the flight cycle of the service life 48000 of the airplane as an example, the service life test times of the angle compensator of the high-pressure pipeline is about 30 ten thousand times, and the probability of the severe working condition that the pressure and the compensation angle are the maximum is lower, but the traditional test method is examined under the working condition, so that the design and manufacturing difficulty is increased, and even no design scheme capable of realizing the test is available. Based on the characteristic that the angle compensator is checked under the most severe working condition, the technical scheme generally does not meet the requirements of the whole service life and the safety coefficient, so the current test scheme generally adopts 4 points uniformly distributed on the circumference to carry out a test, the total test times reach the requirements of the service life, and the test method does not simulate the actual working condition of the angle compensator in a high-temperature high-pressure pipeline and has the risk of over-check or under-check. Disclosure of Invention The invention provides a life test method for an angle compensator of an aircraft high-pressure pipeline, which collects and sorts load working condition parameters of the angle compensator of the aircraft high-pressure pipeline, takes about 80% working condition of the angle compensator of the aircraft high-pressure pipeline as test condition, calculates test times under the test condition, increases safety margin, determines final test requirements, simulates actual working condition, considers the safety margin, and reduces development risk. The invention provides a life test method of an angle compensator of an aircraft high-pressure pipeline, which comprises the following steps: The life test is repeated for preset life test times, wherein the preset life test times are determined according to the service life a of the aircraft, the working times b of the angle compensator in each flight cycle, the working times c of the angle compensator additionally added in the service life of the whole aircraft and the fatigue dispersion coefficient d of the angle compensator; in each life test, the test procedure control scheme was: s1, when the angle compensator is at a minimum angle and the working pressure of the angle compensator is lowest, the working pressure of the angle compensator is raised to the maximum pressure; S2, after the maximum pressure is maintained for at least a preset time period, the angle compensator starts to deflect until the maximum test angle is reached; S3, controlling the working pressure of the angle compensator to start to release pressure, controlling the angle compensator to keep at least a preset time length under a maximum test angle after the pressure release is finished, and controlling the angle compensator to deflect to a minimum angle. Optionally, the aircraft life is the number of flight cycles. Optionally, the number of life tests n= (a+b+c) d. Alternatively, the aircraft high pressure line angle compensator mounting direction remains unchanged throughout all life tests. Optionally, the angle compensator is maintained at a minimum angle for at least 2 seconds. Optionally, the angle compensator is maintained at the maximum angle for at least 2 seconds. Alternatively, the maximum period of each life test does not exceed 7 seconds. Optionally, the preset duration is 1 second. The invention provides a life test method of an angle compensator of an airc