用转子动力学理论研究了再入航天器滚速变化引起的落点误差。
This paper researches into reentry vehicle impact errors which result from the roll velocity changes by use of rotor dynamic theory.
本文根据伴随系统理论，在某飞行器制导工具误差的精度评定中加以实际应用，求出落点偏差的协方差矩阵。
In this paper, the adjoint system theory is applied to the guidance accuracy assessment of the flying vehicle, and the covariance matrix of the impact point deviation is solved.
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