高超声速边界层转捩对旋转飞行器自由飞运动的影响研究

This project will stduy the motion and aerodynamic characteristics affected by boundary layer transition for the hypersonic spinning re-entry vehicle which is artificially fixxed definite number tripped thread that can produce the change of laminar to turbulent on the 10-deg half-angle cone surface by the wind-tunnel free-flight testing which the motion freedom is not limited. Then we will put forward the restraining method for the dynamic unstable motion ofthe uncontrolled hypersonic spinning re-entry vehicle by analyzing the relationship laws between the flow induced by the boundary layer transition、free flight motion and the aerodynamic force..The study is very important to assure the security for the hypersonic spinning re-entry vehicle which is not controlled，which will provide actual guidance for the control system and aerodynamic shape design for the hypersonic uncontrolled spinning re-entry vehicle.

针对高超声速旋转再入飞行器无控自由飞行时可能出现的由边界层非对称转捩引起的动态不稳定运动问题，通过在飞行器模型表面相应轴向位置布置人工绊线促使边界层发生固定强迫转捩，采用运动自由度不受约束的风洞模型自由飞试验技术研究边界层非对称与对称转捩对高超声速旋转飞行器无控自由飞行运动特性和气动特性影响规律，进而分析高超声速旋转飞行器自由飞行时边界层转捩绕流流场与飞行器的自由飞运动、以及所受气动力三者相互影响、相互耦合的规律，提出抑制高超声速旋转飞行器自由飞行状态可能出现的动态不稳定运动的措施。.项目的研究成果对于保证高超声速旋转再入飞行器无控自由飞行安全有重要意义，可为高超声速无控旋转再入飞行器的总体设计与主动控制提供指导与参考。

针对高超声速旋转再入飞行器无控自由飞行时可能出现的由边界层非对称转捩引起的动态不稳定运动问题，通过在飞行器模型表面相应轴向位置布置人工绊线促使边界层发生固定强迫转捩，采用运动自由度不受约束的风洞模型自由飞试验技术研究边界层非对称与对称转捩对高超声速旋转飞行器无控自由飞行运动特性和气动特性影响规律。研究表明：（1）有转捩绊线旋转模型的初始激励角振幅明显大于无转捩绊线旋转模型的初始激励角振幅，但有绊线旋转模型的俯仰角（随时间推移有逐渐衰减的趋势，而无转捩绊线的旋转模型则相反）。（2）有转捩绊线的旋转钝锥在“宏观”条件相同的情况下，飞行中有“激励稳定”的绕流流场，产生动态稳定的自由飞运动，而无转捩绊线的旋转钝锥自由飞行中则有“激励不稳定”的绕流流场，产生动态不稳定的自由飞运动。