种高超声速飞行器热环境下气动弹性力学特性分析方法

• Format: Patent
• Language: Chinese
• Published: 04.07.2017
• Subjects: CALCULATING; CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION; COMPUTING; COUNTING; ELECTRIC DIGITAL DATA PROCESSING; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; IMAGE DATA PROCESSING OR GENERATION, IN GENERAL; PHYSICS; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS; TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE

本发明涉及种气动弹性分析方法，提供了种高超声速飞行器热环境下气动弹性力学特性分析方法。使用活塞理论对高超声速飞行器全机有限元模型进行频域非定常气动力计算，在此基础上考虑了在高超声速热环境中，模型受到的气动热效应，忽略气动热输入对气动力输入和弹性力输入的弱耦合效应，仅考虑气动热载荷作用下的结构温度的稳态特性，在进行定常气动力求解之后采用参考焓法求得飞行器表面的热流密度，进而计算出飞行器表面的稳态温度分布，并求得此时结构的实际等效刚度矩阵，并采用工程方法求解出临界颤振速度。本发明解决了气动热环境下超声速飞行器气动弹性分析问题，通过对颤振速度的分析从而提高高超声速飞行器气动弹性性能。 The invention relates to a pneumatic elastic analytical method, and provides a pneumatic elastic mechanical characteristic analytical method of a hypersonic speed aircraft in thermal environment. According to the method, the piston theory is used for carrying out frequency domain nonsteady aerodynamic calculation on a full-aircraft finite element model of the hypersonic speed aircraft; on the basis, the pneumatic thermal effect on the model in the hypersonic speed thermal environment is considered; the weak coupling effect of pneumatic thermal input in aerodynamic input and elastic force input is ignored; only the structure temperature steady-state characteristics under the pneumatic thermal load effect are considered; af