适用于复杂流动的热气动弹性降阶建模方法

doi:10.7527/S1000-6893.2022.26807

Abstract

Abstract:

For aerothermoelastic problems dominated by complex flow on hypersonic vehicles， an unsteady aerodynamic Reduced-Order Modeling （ROM） method suitable for time-varying thermal modal shapes was developed， based on which a fluid-thermal-structural coupling framework using spatial and temporal data exchanging strategy was finally constructed. Above framework was applied to predict time-varying flutter boundary of an air intake compression surface installed on hypersonic vehicle forebody in actual aerodynamic heating process. As is shown in the results， modal frequencies and modal shapes varied greatly with time when the compression surface was exposed in extremely uneven heat flow， and proposed ROM method is suitable for such variation of modal shapes， which means repetitive CFD calculation of unsteady aerodynamic force can be saved. By adopting proposed ROM， generalized aerodynamic force can be calculated with high confidence and time consumption is several orders of magnitude lower than traditional methods. Aerothermoelastic analysis of compression surface revealed that flutter dynamic pressure was reduced to 0.64% of the value at initial time after reaching thermal equilibrium， which significantly narrows flight envelop of hypersonic vehicle. The proposed method effectively alleviates the contradiction between efficiency and accuracy of aerothermoelastic analysis， and improves the engineering feasibility of aerothermoelastic analysis.

Key words: hypersonic vehicles, aerothermoelasticity, reduced order model, fluid-thermal-solid coupling, flutter, thermal mode, forebody compression surface

CLC Number:

V211.3

Ziyi WANG, Weiwei ZHANG, Lei LIU, Xiaofeng YANG. Reduced order aerothermoelastic framework suitable for complex flow[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(4): 126807-126807.

Figures/Tables 29

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T/K	弹性模量/GPa	热膨胀系数/（10^-6 K^-1）	比热容/（J·kg^-1·K^-1）	热传导系数/（W·m^-1·K^-1）
273	170	14.0	440
293				60.4
373	166	14.4	450
393				55.9
473	158	14.7	475
503				50.9
573	152	15.0	495
643				45
673	142	15.5	505
773	135	15.8	530
873	128	16.1	555
973	115	16.4	575
1 073	108	16.7	615
1 173	94	17	650
1 273	78	17.3	710

变量	ROM-AMS	传统ROM	相对误差/%
q_f /MPa	0.066 9	0.064 5	3.72
H_f /km	28.53	28.76	-0.800
f_f /Hz	123.67	123.16	0.414

变量	ROM-AMS	传统ROM	相对误差/%
q_f /MPa	0.015 2	0.015 0	1.33
H_f /km	38.78	38.89	-0.283
f_f /Hz	82.98	82.88	0.121

流程	耗时/min
流程	传统ROM	ROM-AMS
耗时总计/h	1 547	58
热模态分析	0.2×35	0.2×35
CFD求解获取训练数据	2 652×35	3 468×1
气动力建模	0.02×35	0.03×1
颤振分析	0.2×35	0.2×35

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Reduced order aerothermoelastic framework suitable for complex flow

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