高超声速飞行器热结构多学科可靠性优化双层序贯高效算法

doi:10.7527/S1000-6893.2025.32060

Abstract

Abstract:

The hot structure of hypersonic aircraft operates in a complex service environment. During the structural design process， employing a multi-disciplinary fine optimization design method that considers multi-field coupling can ensure the superior performance and reliability of the aircraft structure under various complex operating conditions. To address the issues of low efficiency and convergence challenges associated with traditional multi-disciplinary optimization algorithms and reliability optimization algorithms， this paper proposes a double-layer sequential optimization algorithm designed specifically for multi-disciplinary reliability optimization of aircraft structures. By decomposing the multi-disciplinary optimization into a primary optimization problem and several subordinate optimization problems associated with individual constraints， the algorithm achieves decoupling of the constraints within the multi-disciplinary optimization framework， thereby enhancing optimization efficiency and significantly mitigating the substantial computational cost incurred by multi-disciplinary coupling analysis during the design optimization process. Subsequently， reliability optimization is performed on the multidisciplinary optimal design points. By employing a double-layer nesting method， deterministic optimization is decoupled from reliability analysis， greatly enhancing the efficiency of reliability optimization. The two-layer sequential optimization algorithm extends multidisciplinary optimization into the realm of aircraft structural reliability optimization， not only expediting the optimization process but also enhancing the practicality and efficacy of the design. Finally， a case study on the optimization of hypersonic airfoil structures is presented to validate the validity of the proposed method and the enhancement in optimization efficiency of multidisciplinary reliability-based design for aircraft structures.

Key words: hypersonic aircraft structure, hot structure, multi-disciplinary coupling, two-layer sequential optimization algorithm, reliability-based optimization

CLC Number:

V222

Qiang QIN, Yongxiang MU, Yusheng XU, Zhiping QIU, Xiaojun WANG. A double-layer sequential efficient algorithm for multidisciplinary optimization of hypersonic aircraft hot structures[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(24): 232060.

Figures/Tables 22

Fig.1

Fig.2

Fig.3

Fig.4

Fig.5

Fig.6

Fig.7

Fig.8

Fig.9

Table 1

Hypersonic airfoil structure parameter information

参数名称	数值
弹性模量（ $20 ℃$ ）/GPa	110
弹性模量（ $200 ℃$ ）/GPa	97
弹性模量（ $400 ℃$ ）/GPa	78
泊松比	0.31
密度/（kg∙m^-3）	4 450
边界条件	根部固定
翼展/mm	924
翼根弦长/mm	1 520
翼尖弦长/mm	960
后掠角/（°）	40

Table 1

Fig.10

Fig.11

Fig.12

Fig.13

Fig.14

Table 2

Table 3

Table 4

Table 5

Central value and radius of interval variable

变量	区间中心	区间半径
$E 20 ℃$ /GPa	110	11
$E 200 ℃$ /GPa	97	9.7
$E 400 ℃$ /GPa	78	7.8
$σ m a x$ /MPa	145	14.5
$V c r$ /（m·s^-1）	1 388	138.8
$f 1$ /Hz	3.027	0.302 7

Table 5

Table 6

Comparison of results of two-layer sequential reliability optimization and traditional reliability optimization

优化变量	最优设计点/mm		优化后结构质量/kg
优化变量	双层序贯优化	传统可靠性优化	双层序贯优化	传统可靠性优化
$x 1$	2.382 7	2.403 3	17.57	17.60
$x 2$	1.810 1	1.796 6
$x 3$	1.273 9	1.323 7
$x 4$	0.526 9	0.530 4

Table 6

Table 7

Fig.15

References 32

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优化变量	最优设计点/mm		优化后结构质量/kg
优化变量	序贯优化	传统优化	序贯优化	传统优化
x₁	2.174 3	2.186 8	16.92	16.96
x₂	1.836 9	1.752 2
x₃	1.212 5	1.312 7
x₄	0.501	0.5

可靠性指标	结构强度	颤振速度	一阶模态频率
双层序贯优化	0.989 1	0.999 7	0.998 6
可靠性约束	≥0.99	≥0.99	≥0.99

A double-layer sequential efficient algorithm for multidisciplinary optimization of hypersonic aircraft hot structures

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