摘要
围绕空基助推段反导作战拦截弹制导问题,建立了空基动能拦截弹的时间最优控制模型。结合空基助推段反导作战任务的特殊性探讨了模型的边界条件和容许控制问题;提出了基于虚拟弧的拦截弹可行轨迹确定方法;进一步选取拦截弹飞行时间最小、拦截弹飞行距离最短和命中点拦截弹与目标弹道导弹的拦截角度最大为性能指标,给出了弹道形成制导律的计算方法;通过案例仿真验证了模型及算法的有效性。
On the problem of the interceptor guidance for air-based ballistic missile defense during the boost?phase,firstly,the time optimal control model is established,and the model constraints and controls is discussed combining the characters of the air-based ballistic missile defense task;secondly,the method for the interceptor feasible trajectory computing is put forward based on the Virtual arc;then the iterative computing method for trajectory-Shaping guidance law is designed based on the factors,viz.minimizing the interceptor flying time,minimizing the interceptor flying time distance and maximizing the confluence angle between the interceptor and the targeting ballistic missile at the hit point;lastly,the efficiency of the model and the arithmetic is validated by simulation.
出处
《空军工程大学学报（自然科学版）》
CSCD
北大核心
2013年第5期31-35,共5页
Journal of Air Force Engineering University(Natural Science Edition)
基金
国防科技重点实验室基金资助项目
关键词
弹道形成
空基助推段反导
拦截弹制导律
trajectory-shaping
air-based missile defense during boost-phase
interceptor cuidance law
