The mathematical model of reentry maneuvering trajectory is established. The fitting expression of aerodynamic coefficient function on velocity, attack of Angle and altitude is presented.
An optimal guidance law for reentry vehicle with high altitude maneuvering on downward phase is studied.
研究了在降弧段进行高空机动的再入飞行器最优制导律。
3
The optimal high altitude guidance law with reentry constraint condition is derived by using the optimal control theory, and the algorithm of time to go is also given.