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由于高超声速飞行器弹性机体/发动机的高度一体化设计,使得此类飞行器的动力学建模与控制较为复杂,而作为控制的基础以及面向控制的总体优化设计都需要建立高精度的动力学模型。首先,建立了考虑气动加热和变截面惯性矩影响的高超声速飞行器自由梁结构弹性模型,分析了气动加热和变截面惯性矩对飞行器振型的影响,得出了气动加热对振型影响非常小且振型引起的攻角变化很小,变截面惯性矩对飞行器的振型影响较大且振型引起的攻角变化较大的结论。然后,建立了考虑气动加热和变截面惯性矩影响的自由梁高超声速飞行器动力学模型,对考虑气动加热和忽略气动加热、恒截面惯性矩和变截面惯性矩对应的动力学模型进行了零极点分布对比分析,得出了气动加热对飞行器的纵向动态特性影响很小,变截面惯性矩自由梁对应的高超声速飞行器在特征点处开环不稳定性更大和非最小相位行为约束变弱的结论。
Due to the highly integrated design of the hypersonic aircraft elastic body / engine, the dynamics modeling and control of such aircraft are complicated. As the basis of control and the overall control design, a high-precision dynamic model needs to be established. Firstly, the elastic model of hypersonic free-form beam considering aerodynamic heating and moment of inertia of variable section is established. The influence of aerodynamic heating and inertial moment of variable section on the vibration mode of the aircraft is analyzed. It is concluded that the effect of aerodynamic heating on the vibration mode is very small And the modal angle caused by the change is small, the variable cross-section of the moment of inertia on the aircraft shape and shape of the larger impact angle changes caused by larger conclusions. Then, the dynamic model of a free-flight hypersonic vehicle considering the influence of aerodynamic heating and the change of moment of inertia of variable section is established. The dynamic model of aerodynamic heating and neglecting aerodynamic heating, constant moment of inertia and variable moment of inertia is established. The results show that the aerodynamic heating has little effect on the longitudinal dynamic characteristics of the aircraft, and the conclusion is drawn that the hypersonic vehicle with the variable cross-section moment of inertia corresponding to the larger open-loop instability at the feature point and the weaker constraint of the non-minimum phase behavior .