弹道导弹是用火箭发动机推进，在控制系统作用下按预定的弹道飞行至预定攻击的目标。
According to a predetermined trajectory, ballistic missile with rocket engine propulsion takes a flight to intended targets under the action of the control system.
针对控制系统采用侧喷流发动机和栅格舵的新型小型多级固体运载火箭开展六自由度弹道仿真研究。
This article studies the six-degree-of-freedom trajectory simulation of small multiple stage solid launch vehicles with control systems using lateral jet thrusters and grid fins.
从弹道稳定性的要求出发，对制导控制系统相关参数选择的原则给出了定量的结果。
According to the requirement of trajectory stability, the quantitative principle of related parameter choosing is presented.
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