再入航天器滚速变化引起的落点误差分析  

ANALYSIS OF REENTRY VEHICLE IMPACT ERROR RESULTING FROM ROLL VELOCITY CHANGES

作　　者：杨辉耀[1] 

机构地区：[1]西安第二炮兵工程学院

出　　处：《中国空间科学技术》1997年第6期50-56,共7页Chinese Space Science and Technology

摘　　要：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。通过分析一般攻角方程，给出了再入航天器的进动规律和配平攻角，据此，求出了不旋转航天器的落点误差；将轨迹分段后，推出了常值滚转速率航天器的平均落点误差；在滚速过零一周范围内，通过确定过零高度，分析了过零误差机理，并对该误差进行了计算；最后，分析了低空联锁共振现象，给出了发生联锁共振的条件和误差计算公式，并得出了几个重要结论。This paper researches into reentry vehicle impact errors which result from the roll velocity changes by use of rotor dynamic theory.The roll regularity and balance attackangle are presented through analysis of general attackangle equation,and the impact dispersion of nonspinning vehicle is got.Steady roll impact error can be obtained when the reentry trajectory is divided into many sections.Rollpasszero(RPZ) impact error is analyzed and calculated on the basis of RPZ height.The roll resonance phenomena are discussed.The conditions of roll resonance and dispersion calculation formula are given also.Finally,Several important conclusions are presented.

关 键 词：滚动 落点偏差 再入航天器 滚速变化 

分 类 号：V412.44[航空宇航科学与技术—航空宇航推进理论与工程]