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Size optimization design method for aircraft thermal protection system based on section reliability

A design method and size optimization technology, applied in the field of structural optimization design of aircraft thermal protection system, can solve problems such as too conservative design concept

Active Publication Date: 2013-10-23
BEIHANG UNIV
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Problems solved by technology

In addition, the refinement requirements for the study of structural reliability make the traditional design concept based on the safety factor method appear too conservative

Method used

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  • Size optimization design method for aircraft thermal protection system based on section reliability
  • Size optimization design method for aircraft thermal protection system based on section reliability
  • Size optimization design method for aircraft thermal protection system based on section reliability

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Embodiment Construction

[0074] The present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0075] In order to introduce the present invention in detail, the definition and algorithm of interval analysis operations used in the present invention are firstly introduced. Let R be the field of real numbers, for two given real numbers and but:

[0076] x I = [ x ¯ , x ¯ ] = { x ∈ R | x ¯ ≤ x ≤ x ¯ }

[0077] It is called bounded closed interval, also called interval number, or interval for short. which said x is the lower bound or lower endpoint of the interval, called is the upper bound or upper endpoint of the interval. If ...

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Abstract

A size optimization design method for an aircraft thermal protection system based on section reliability comprises the following steps: 1. mathematical modeling, according to the structural form of the thermal protection system, determining a size related design variable, and according to the temperature requirement, establishing a heat proof structure weight reduction optimization model; 2. describing the material, external load and uncertainty in an initial / boundary value condition by utilizing the section in a quantifying manner; 3. carrying out reliability switch on the temperature constraint condition containing an uncertain parameter based on a section possibility degree; 4. utilizing the section limited volume method, realizing quickly solving of the structure transient temperature response range, and changing a two-layer nesting optimization problem into a conventional single-layer optimization problem; 5. carrying out programming calculation on switched single-layer optimization problem containing the reliability restraint, and determining an optimal solution to reaching an optimal weight reduction effect. The invention can systematically solve the thermal protection system structure optimization problem containing multisource section uncertainty, improves the computational efficiency, and ensures the reliability and the safety of the structure use.

Description

technical field [0001] The invention relates to the field of structural optimization design methods for aircraft thermal protection systems, in particular to a thermal protection system size design method based on interval heat conduction analysis and interval reliability optimization. Background technique [0002] With the rapid development of my country's space technology, spacecraft entering orbit or returning to the ground must pass through the atmosphere, especially in the return section, which will suffer from severe aerodynamic heating. Each part of the spacecraft structure has different temperature requirements, and most of the instruments and equipment are required to be within a certain temperature range, so a thermal protection system must be used to control the temperature of the spacecraft. Generally speaking, the greater the thickness of the thermal protection system, the better the thermal protection capability; but on the other hand, the increase in structura...

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Application Information

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IPC IPC(8): G06F17/50
Inventor 王冲王晓军邱志平黄仁许孟辉李云龙
Owner BEIHANG UNIV
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