基于速度增益制导的大椭圆转移中段制导方法研究  

Research on Midcourse Guidance Method of Large Elliptic Transfer Orbits Based on Velocity Gain Gudance

作　　者：任金磊 李君[1] 庄学彬[1] 李罗钢[1] 谢泽兵[1] 

机构地区：[1]中国运载火箭技术研究院研究发展中心,北京100076

出　　处：《导弹与航天运载技术》2016年第5期96-99,108,共5页Missiles and Space Vehicles

摘　　要：针对大椭圆转移中初始偏差和长时间飞行中摄动因素导致的方法偏差较大的现象,需进行中段轨道修正。基于显式制导的思路,采用速度增益制导,研究了考虑项摄动有限推力条件下的中段轨道修正方法,并通过优化修正时间设计了终端偏差小、燃料消耗少的中段修正优化轨道。针对不同初始偏差工况通过数学建模仿真进行了验证,结果表明该方法可行。For the phenomenon of large deviation caused by initial deviation and a long-time flight perturbation factors, mid-course trajectory correction is an essential technique to ensure the completion of elliptic transfer. Based on explicit guidance theory, this paper use velocity gain guidance, considering perturbation on finite-thrust condition in the midcourse orbit correction method, and a fixed optimization orbit with small terminal deviation and less-used fuel is designed through optimizing fixed time. In the end, mathematical modeling is carried out for different working conditions of the initial deviation to validate the result of this method feasible.

关 键 词：速度增益 显式制导 中段修正 轨道优化 

分 类 号：V448.11[航空宇航科学与技术—飞行器设计]