摘要
针对大气层外高速飞行的目标,提出了一种可用于动能拦截器助推段的导引方法.建立了拦截器和目标的运动模型,在分析可拦截约束条件的基础上推导出转移轨道计算方法,同时通过对拦截器可发射区域中的转移轨道优化得到满足约束条件的有效发射区域,并以点火时刻待增速度为性能指标来寻优计算获得发射参数.仿真结果表明,该方法能有效实现拦截器助推段的制导控制.
A guidance method used in boost phase for mtercepting the high-speed target in outer space was presented. After constructing the model of motion of the target and the kinetic kill vehicle （KKV）, constraints of interception were analyzed and the computing method of orbit transfer was also derived. Then orbit transfer was optimized to get valid launching areas satisfying the constraints. Moreover, KKV＇ s required velocity increase at firing time was selected as the specific performance index to optimize the computed launch parameters. Simulation results show that this method can implement efficiently KKV＇s guidance during the boost phase.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2007年第2期310-315,共6页
Journal of Aerospace Power
基金
国家自然科学基金重点项目(60434010)资助
关键词
航空
航天推进系统
动能拦截器
转移轨道
待增速度
发射参数
aerospace propulsion system
kinetic kill vehicle（KKV）
orbit transfer
required velocity increase
launch parameters
