针对于中制导发动机关机后具有较长被动飞行距离的拦截问题，两飞行器间的重力差必须合理考虑。
For long-range targeting applications with significant ballistic coasting after burnout, the difference between the gravitational accelerations must be taken account.
根据滚转火箭弹的动力学方程，给出了在弹体坐标系下无控低速滚转火箭弹在被动飞行段的锥形运动方程组。
The nonlinear coning motion equations in body coordinates on the force moment coefficients of low speed spinning rocket were obtained based on the dynamics equations.
建立了有内导向瓣周边式对接机构的两空间飞行器对接过程的动力学模型，建模中将对接系统简化为主动飞行器、被动飞行器和主动捕获环三体问题。
The mathematical models of docking dynamics in the process of capture are established for two spacecrafts with inner guide petal peripheral docking mechanisms.
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