摘要
研究了变质心再入飞行器动力学模型以及精确制导两方面的问题.基于分析力学中的虚位移原理,设计了一种再入飞行器新型最优制导律。采用解析法预测弹道落点,通过对最优虚位移的搜索,求解出总升力的最佳方向.推导了变质心动力学模型,以质量块为制导控制系统的执行机构,实现变质心再入飞行器的机动飞行.研究发现:质心变化引起的附加力矩是气动稳定力矩系数的函数;该制导律对过载并无要求。仿真结果表明:平均计算3次解析弹道即可完成一次制导指令,经制导控制后最终落点误差在10 m以内.
The dynamics model and guidance problems for moving-mass reentry vehicle are studied in this paper. A new optimal guidance law is presented based on the virtual displacement principles. The optimal direction of the lateral force is searched by optimizing the solution of the virtual displacement and predicting the fall point with analytical method. The dynamics model for the vehicle is derived. The actuating mechanism adopting mass block as the guidance control system realizes the maneuver flight of moving-mass reentry vehicle. The study reveals that the aerodynamic trim torque caused by moving-mass is the function of aerodynamic steady torque coefficient. The simulation results show that three times of calculation on analytical trajectory in average can accomplish the guidance instruction once, and the error of final fall point is within 10 m.
出处
《哈尔滨工业大学学报》
EI
CAS
CSCD
北大核心
2009年第3期6-10,共5页
Journal of Harbin Institute of Technology
基金
国家自然科学基金资助项目(10572042)
关键词
再入飞行器
制导律
再入弹道
最优化
质量矩
变结构控制
reentry vehicle
guidance law
reentry trajectory
optimization
moving-mass
variable structure control
