摘要
本文通过建立航天器在空间作战的拦截模型,根据运动学的理论来设计航天器空间作战最优拦截轨道。应用拉格朗日极小值原理,以能量为目标函数,设计出最小能量入轨拦截(共面拦截)和最小能量碰撞拦截(异面拦截)两种拦截轨道,并通过算例进行了具体的计算和优化分析。最后比较两种拦截方式的优劣,根据现代战争的需要,可采用不同的拦截方案,如果需要实时拦截可采用碰撞拦截和区域拦截,如果需要高精度拦截且时间不限可采用入轨拦截。
In this paper, the intercept model of the spacecraft in space warfare was built and the optimization orbit was designed based on the theories of kinematics. According to the Lagrange minimum principle and as energy for objective function, the minimum energy orbit interception （coplanar interception） and the minimum energy impact interception （ non - coplanar interception） orbit were designed and at the same time two kinds of orbits were concretely calculated and analyzed by the example. Finally, two kinds of intercept ways were compared, different project can be adooted according to the need of modem war.
出处
《长春理工大学学报（自然科学版）》
2007年第2期51-54,共4页
Journal of Changchun University of Science and Technology(Natural Science Edition)
基金
航天科技创新基金资助项目(2005CH060001)
关键词
空间作战
拦截模型
能量最小
入轨拦截
碰撞拦截
space warfare
intercept model
minimum energy
orbit interception
impact interception
