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Aircraft structure integrity detection method and system, storage medium and control method

A technology of integrity detection and aircraft structure, applied in random CAD, computer-aided design, instruments, etc., can solve the problems affecting the overall performance level of equipment, the inability to realize quantitative evaluation of equipment, and the inability to effectively consider the impact of overall integrity, etc., to achieve The effect of ensuring integrity and meeting service/usage requirements

Pending Publication Date: 2021-01-08
AIR FORCE UNIV PLA
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Problems solved by technology

As a result, quantitative evaluation of equipment integrity cannot be realized, so that the impact of design schemes on the overall integrity of equipment cannot be effectively considered during design, and further improvement of design schemes can be achieved, affecting the overall performance level of equipment

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  • Aircraft structure integrity detection method and system, storage medium and control method
  • Aircraft structure integrity detection method and system, storage medium and control method
  • Aircraft structure integrity detection method and system, storage medium and control method

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Embodiment Construction

[0061] In order to make the object, technical solution and advantages of the present invention more clear, the present invention will be further described in detail below in conjunction with the examples. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention.

[0062] Aiming at the problems existing in the prior art, the present invention provides an aircraft structural integrity detection method, system, storage medium and control method. The present invention will be described in detail below in conjunction with the accompanying drawings.

[0063] Such as figure 1 As shown, the aircraft structural integrity detection method provided by the invention comprises the following steps:

[0064] S101: Calculate the structural integrity of the aircraft. In engineering, the aircraft structural damage is used to measure the structural durability of the aircraft. The structural damage is ...

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Abstract

The invention belongs to the technical field of aircraft structure design and use, and discloses an aircraft structure integrity detection method and system, a storage medium and a control method; thedetection method includes calculating the aircraft structure integrity, measuring the structural durability of an aircraft by using the aircraft structure damage degree in engineering, and w herein the structural damage degree is a quantitative measure of durability damage generated when the structure reaches a specified time, and is generally represented by an average crack transcendental percentage of a structural detail group; calculating the availability of the aircraft; calculating the structural safety of the aircraft, wherein the structural safety of the aircraft is used for measuringthe structural safety of the aircraft; calculating the probability that the aircraft structure survival rate, the aircraft structure survival rate and the aircraft structure damage rate are two opposite events, wherein the sum of the probabilities is 1; calculating structural integrity. The invention provides a concept of structural integrity control, establishes a measurement method of structuralintegrity, and provides a structural integrity control concept and method for optimizing a structural integrity control scheme by taking structural integrity maximization as a target.

Description

technical field [0001] The invention belongs to the technical field of aircraft structure design and use, and in particular relates to an aircraft structural integrity detection method, system, storage medium and control method. Background technique [0002] At present, the concept of aircraft structural integrity was first proposed by the United States in 1954, and it was formed and developed along with a series of accidents in the US Air Force. In 1958, several B-47 aircraft were damaged due to fatigue problems, and the structural integrity of the aircraft began to be emphasized. In 1969, the F-111 aircraft suffered a serious accident after only 100 flight hours due to undetected cracks in the key joints of the wing. Since then, aircraft structural integrity has undergone long-term development, and the theory and methods of structural integrity have been established and gradually matured. [0003] The so-called aircraft structural integrity refers to the state in which t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15G06F30/20G06F111/04G06F111/08G06F119/02G06F119/18
CPCG06F30/15G06F30/20G06F2111/04G06F2111/08G06F2119/02G06F2119/18
Inventor 何宇廷
Owner AIR FORCE UNIV PLA
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