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Multi-operating-condition failure load based composite structure uncertainty optimization method

A composite material and optimization method technology, applied in design optimization/simulation, special data processing applications, instruments, etc., can solve problems such as conservative structure and large safety factor, achieve good fatigue resistance and improve efficiency

Active Publication Date: 2018-05-08
BEIHANG UNIV
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  • Application Information

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Problems solved by technology

The traditional method of composite material structure design based on safety factor adopts too large safety factor, and the designed structure is too conservative. Therefore, how to comprehensively consider the uncertain factors in composite material design and study its influence on the strength of composite material structure becomes a structural problem. key to design

Method used

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  • Multi-operating-condition failure load based composite structure uncertainty optimization method
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  • Multi-operating-condition failure load based composite structure uncertainty optimization method

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Embodiment

[0089] In order to fully understand the characteristics of the invention and its applicability to engineering practice, the invention optimizes the design of the proposed aircraft composite material stiffened panel wall panel structure. The aircraft skin rib panel is subjected to two load conditions, namely compression condition and shear condition, the design loads are 98kN and 121.0kN respectively, and the safety factor is 1.1. The model and loading conditions are as follows Figure 1-Figure 4 shown.

[0090] The composite material adopts carbon fiber fabric material, and the interval boundaries of its properties are listed in Table 1.

[0091] Table 1 Interval boundaries of uncertain variables

[0092] elastic parameters

lower bound

Upper Bound

Intensity parameter

lower bound

Upper Bound

E. 1 (GPa)

43 . 859

62 . 112

x t (MPa)

417.131

542.420

E. 2 (GPa)

43 . 85 9

62 . 112

x c (MPa)

120 . 781

...

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Abstract

The invention discloses a multi-operating-condition failure load based composite structure uncertainty optimization method. The method includes steps: (1) subjecting an established finite element model to model correction and confirmation under an uncertainty condition; (2) subjecting a composite to safety coefficient based two-stage optimization, wherein first-stage optimization refers to composite super layer optimization aiming at structural weight, and second-stage optimization refers to stacking sequence optimization aiming at structural bearing capacity; (3) on the basis of an uncertainty parameter range quantified in the step (1), performing bearing capacity reliability analysis on a scheme optimized in the step (2) to obtain reliability of structure bearing capacity under differentoperating conditions; (4) subjecting the composite to reliability based optimization, taking bearing reliability of the scheme optimized in the step (3) as a constraint pair, performing super layer optimization aiming at weight reduction, and performing second-stage stacking sequence optimization aiming at structure bearing capacity lower bound maximization.

Description

technical field [0001] The invention relates to the field of optimization design methods for composite material structures, in particular to an uncertain optimization method for composite material structures based on multi-working-condition failure loads. Background technique [0002] Due to the advantages of high specific strength, high specific modulus, and designable strength, composite structures are widely used in the design of aerospace structures. The application site is also gradually expanded from the secondary load-bearing structure to the main load-bearing structure. The inherent material dispersion of composite materials greatly increases the difficulty and workload of structural design compared with traditional metal structures. The traditional safety factor-based composite structure design method adopts a relatively large safety factor, and the designed structure is too conservative. Therefore, how to comprehensively consider the uncertain factors in the desig...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/23
Inventor 王晓军石庆贺马雨嘉罗振先
Owner BEIHANG UNIV
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