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针对高超声速可重复运载器RLV(Reusable Launch Vehicles)的再入飞行问题,利用数值预测校正方法与准平衡滑翔条QEGC(Quasi-Equilibrium Glide Condition)相结合的方法在线设计同时满足热流、法向过载和动压等轨迹约束与末端精度要求的倾侧角制导律.建立三自由度动力学方程,确定初始条件、末端精度要求和轨迹约束要求;然后详细阐述预测校正方法和准平衡滑翔条件的原理,再利用预测校正方法设计制导律,用QEGC把约束转换为对倾侧角制导律的上界,通过限制倾侧角的幅值来限制约束.最后在计算机上进行制导仿真,并考虑初始条件不确定性,进行蒙特卡洛仿真,通过分析仿真结果,证明利用预测校正方法结合准平衡滑翔条件可以快速的设计出满足末端精度要求和轨迹约束的制导律,并对初始条件不确定性有较好的鲁棒性.
Aiming at the problem of re-entry flight of Reusable Launch Vehicles (RLV), the method of numerical prediction and correction combined with Quasi-Equilibrium Glide Condition (QEGC) is designed online to satisfy both heat flow and normal overload And dynamic pressure and other trajectory constraints and tip accuracy requirements of the roll angle guidance law to establish a three-degree-of-freedom dynamics equation to determine the initial conditions, the end of the precision requirements and trajectory constraints requirements; and then elaborated the predictive correction method and the principle of the quasi-balance gliding conditions, Then the guidance law is designed by using the predictive correction method, and the constraint is transformed into the upper bound of the roll angle guidance law by QEGC, and the constraint is restrained by limiting the amplitude of the roll angle.Finally, the guidance simulation is performed on the computer and the initial condition uncertainty , The Monte Carlo simulation is carried out. The simulation results show that using the predictive correction method combined with the quasi-equilibrium gliding conditions, the guidance law satisfying the end precision and the trajectory constraints can be quickly designed and the uncertainty of the initial conditions is good. Great.