弹道式再入飞行器以配平攻角状态返回的轨道计算原理及相应的控制要求

弹道式再入飞行器一般为轴对称旋成体,但其质心可以偏离对称轴。我们称通过飞行器质心和对称轴的平面为飞行器的对称面。这种飞行器以配平攻角状态返回时,不仅要求其相对于地球的飞行速度矢量平行于飞行器的对称面、飞行攻角恰等于配平攻角,而且要求其相对于质心的转动角速度矢量垂直于飞行器的对称面,能使飞行器的姿态跟随飞行速度矢量的改变。基于上述考虑,本文给出了这种飞行器以配平攻角状态返回的轨道计算原理及相应的控制要求。

The Calculating Principle of Reentry Trajectory and the Corresponding Control Requirements for a Ballistic Reentry Vehicle in Trim Attack Angle

The shape of ballistic reentry vehicle generally is axial symmetry, but its mass center may be departure from the axis of its symmetry. The reentry motion of a ballistic reentry vehicle with trim attack angle requires not anly that its flight velocity vector relative to the earth must parallel to the symmetrical plane and the attack angle must equal to the trim angle. but also that its angular velocity vector relative to its mass center must cross the symmetrical plane at right angles and can make the vehicle attitude with the change of flight velocity vector. On the basis of above considerations, this paper gives the calculating principle of reentry trajectory and the corresponding control requirements for the vehicle.