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Fatigue test method for full-aircraft main operating system of aircraft

A control system and fatigue test technology, applied in the field of fatigue test of the main control system of the aircraft, can solve the problems of being too conservative, incomplete assessment, and difficult to evaluate the fatigue life of the main control system of the aircraft, so as to improve the reliability and reduce the test time. cost effect

Active Publication Date: 2012-09-19
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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AI Technical Summary

Problems solved by technology

Some fixed the aircraft control system and implemented a relatively conservative control load program block spectrum for testing, only assessing the fatigue performance of purely mechanical components; some implemented fatigue wear test load spectrum, only assessing the static / dynamic performance indicators of the control system and system wear and tear, and did not assess the fatigue performance of the system under emergency control conditions; some of them used several fatigue tests of key components of the control system to replace the fatigue test of the main control system of the whole machine and carried out under the machine. These tests were all independent tests. The test results are either too conservative, or the assessment is not comprehensive, and cannot truly reflect the fatigue performance of the main control system of the aircraft, which is both a structure and a mechanism, and the reliability of the test results is reduced
Based on such test results, it is difficult to give an accurate assessment of the fatigue life of the main control system of the entire aircraft

Method used

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  • Fatigue test method for full-aircraft main operating system of aircraft
  • Fatigue test method for full-aircraft main operating system of aircraft

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0025] Embodiment 1 (taking the fatigue test of the main control system of the whole machine as an example)

[0026] 1. Filter the measured data of the load and displacement of the aircraft control system: respectively select the main parameters of the filter and the threshold value of the filter for the measured data of the aileron, horizontal tail and rudder control systems of the aircraft, and perform filter processing; before the filter processing, the measured data Perform preprocessing, that is, use the program to remove some obvious abnormal data such as bit errors and jump points.

[0027] 2. Compile the total spectrum of ground measurement and the total spectrum of air measurement: data processing is performed on the control load and displacement measurement data after filtering, and at the same time solve the frequency problem of the measurement spectrum caused by control displacement; The load and control displacement filtering data are counted at the peak / valley va...

Embodiment 2

[0039] Embodiment 2 (Taking the same test of the main control system of the whole machine and the fatigue of the body as an example)

[0040] 1. Compilation of the fatigue test load spectrum of the main control system of the whole machine: The process of preparing the fatigue test load spectrum of the main control system of the whole machine is the same as the steps 1 to 5 in the first embodiment above.

[0041] 2. Carry out the fatigue test of the main control system of the whole machine:

[0042] (1) State of the test piece: on the fatigue testing machine, the fatigue test of the main control system of the whole aircraft is carried out with the main control system components and their supporting parts that meet the installation conditions.

[0043] (2) Load Spectrum Implementation:

[0044] a. Through routine inspection of the system, it is determined that the control room adjusts the force arm state of the horizontal tail control system and the speed state of the rudder co...

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Abstract

The invention belongs to a fatigue life determining technology for an operating system of an aircraft and relates to a fatigue test method for a full-aircraft main operating system of the aircraft. According to the fatigue test method, the fatigue coordination loading of an operating load and an operating displacement can be carried out, a fatigue test including the operating load and an operating displacement spectrum on the full-aircraft main operating system of the aircraft can be implemented, and meanwhile, the problem of simultaneous test of aircraft body fatigue on the same fatigue testing machine is taken into account, so that the fatigue properties of components and supporting parts of the full-aircraft main operating system and static performance indicators of the full-aircraft main operating system are all actually assessed; the actual loaded conditions of the main operating system of the aircraft under normal operating and emergency operating conditions are more truly reflected, the fatigue properties of the structure and mechanism of the main operating system of the aircraft are embodied; and the test cost is reduced, and the reliability of a test result is improved.

Description

technical field [0001] The invention belongs to the fatigue life determination technology of an aircraft control system, and relates to a fatigue test method for the main control system of the whole aircraft. Background technique [0002] Due to the limited test conditions and test scale, the existing fatigue tests of the main control system of the whole aircraft do not involve the compilation of the actual measurement data of the control load and displacement of the whole aircraft, so that the components of the main control system of the whole aircraft and their supporting parts Fatigue performance and static performance indicators of the whole aircraft control system have been actually assessed, without considering the state of the aircraft control system, or the same test as the fatigue of the aircraft body. Some fixed the aircraft control system and implemented a relatively conservative control load program block spectrum test, which only examined the fatigue performance...

Claims

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Application Information

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IPC IPC(8): G01M13/00G01M99/00
Inventor 卢京明张联营
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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