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Fatigue characteristic analysis method and fatigue characteristic analysis system for thermal protection structure

A technology of thermal protection structure and fatigue characteristics, which is used in the testing of machine/structural components, analysis of materials, strength characteristics, etc., can solve the problem of high system complexity, short test duration, and difficulty in evaluating the reliability of thermal protection structures. problems, such as ease of implementation, improved reliability of analysis, and practical implementation

Active Publication Date: 2018-07-27
BEIJING AEROSPACE TECH INST
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Problems solved by technology

[0003] The traditional airflow pulsation pressure is mostly simulated by the shock tunnel. This type of test device has the problems of high system complexity and short test duration. It cannot truly simulate the service load conditions of the thermal protection structure, and it is also difficult to evaluate the thermal protection. The reliability of the structure

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  • Fatigue characteristic analysis method and fatigue characteristic analysis system for thermal protection structure
  • Fatigue characteristic analysis method and fatigue characteristic analysis system for thermal protection structure

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Embodiment Construction

[0033] In order to make the technical solutions and advantages of the present application clearer, the exemplary embodiments of the present application will be further described in detail below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present application, not all implementations. Exhaustive list of examples. And in the case of no conflict, the embodiments in this specification and the features in the embodiments can be combined with each other.

[0034] The main idea of ​​the present invention is based on the traditional fatigue test method, to conduct a more realistic alternating load fatigue test on the sandwich suture thermal protection structure composed of micro-nano-scale porous materials, combined with static tests, comprehensively The fatigue characteristics analysis of the sandwich stitched thermal protection structure composed of nanoscale porous materials not only improves the reliabi...

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Abstract

The present invention provides a fatigue characteristic analysis method for a thermal protection structure. The method comprises: carrying out static test on a plurality of specimens to be analyzed, and determining the maximum control load and the minimum control load for a fatigue test; based on the maximum control load and the minimum control load, carrying out fatigue test on the specimens to be analyzed at a predetermined alternating load period; and according to the fracture morphology comparison results of the specimens to be analyzed, determining the main damage load of the specimens tobe analyzed. With the technical scheme of the present invention, the use load condition of the thermal protection structure can be realistically simulated, such that the reliability of the analysis of the fatigue characteristic of the thermal protection structure can be improved, and the method and the system can provide advantages of practicality and convenient performing in the engineering evaluation of the thin-wall thermal protection structure.

Description

technical field [0001] This application relates to the field of aircraft performance analysis, in particular to a fatigue characteristic test analysis method and system that uses a fatigue test device to evaluate the performance of a sandwich stitched thermal protection structure against pulsating pressure loads. Background technique [0002] The aerodynamic heating problem faced by subsonic and supersonic aircraft with a flying Mach number less than 4 is not serious, so the outer surface of the aircraft is mostly a metal load-bearing structure. For structures designed with metal materials, their structural strength, stiffness, and toughness are relatively good, and it is not necessary to consider the influence of airflow pulsation pressure separately. Hypersonic vehicles fly in the atmosphere at high Mach numbers (Ma>5) for a long time, and the surface of the vehicle is faced with a severe aerodynamic heating environment. Traditional metal materials can no longer meet th...

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Application Information

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IPC IPC(8): G01N3/36G01M13/00
CPCG01M13/00G01N3/36G01N2203/0073
Inventor 宋月娥曹杰熊强马寅魏王洋韩乐李晶袁豪杰
Owner BEIJING AEROSPACE TECH INST