为研究具有大离轴角及越肩发射能力的先进空空导弹初始段敏捷转弯方法，研究了装有反作用喷气控制系统的空空导弹的大角度姿态过失速机动控制律。
This paper investigates the large Angle attitude post stall maneuver control for the agile turn phase of an air-to-air missile that has high off-boresight capability and head reverse maneuverability.
新型精确制导导弹为了获得更大的机动性、敏捷性和更高的命中精度，大多采用了推力矢量控制或反作用推力控制。
Advanced agile missiles possess maneuverability, agility and accurate guidance performance by adopting thruster vector control or reaction control system thruster.
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