高超声速飞行器分离干扰的伴随方法分析

以大气层内高超声速飞行器级间分离过程为研究对象,采用伴随方法得到了由冲击力和气动干扰力矩引起的攻角的解析解。利用该解析解,得到了分离干扰引起的攻角的瞬时变化曲线。结果表明,在高超声速飞行器级间分离开始0.4s内,冲击力和气动干扰力矩对攻角有一定的影响,并且随干扰的增大而增大。本研究实现了预示高超声速飞行器分离过程风险的目的,对高超声速飞行器分离干扰策略的制定提供了理论依据。

Adjoint Methed Analysis of Hypersonic Vehicle Separation Interference

The hypersonic vehicle stage separation process in the atmosphere was researched. Adjoint method was introduced and the way to get the analytical solution of angle of attack caused by impact force and aerodynamic interference torque. Using the above solution ,the angle of attack change curve was obtained which was caused by separation interference. The results showed that impact force and aerodynamic interference torque had certain effect on angle of attack and increase with the increase of the interference in the beginning of the hypersonic vehicle stage separation 0.4 seconds. This study realized the predicted for the process of the hypersonic vehicle stage separation risk and provided a theoretical basis for the strategy formulation of the hypersonic vehicle separation interference.