直接侧向力与气动力复合控制导弹脱靶量分析

大气层内姿控式直接侧向力控制导弹末制导系统存在气动力控制与复合控制之间的切换,在这种特殊情形下引入有限时间广义H2方法进行脱靶量分析.根据复合控制导弹末制导系统数学模型,研究了切换情形下的零效脱靶量与制导系统关键参数之间的关系,分析了直接侧向力启控时间、有效导航比、修正比例导引系数以及目标估计环节时间常数对零效脱靶量的影响.分析结果为制导末端直接侧向力启控时间的确定和修正比例导引律参数的选择提供了有力依据.

Miss distance analysis for missiles with lateral jets and aerodynamic surfaces

With consideration of the switch between aerodynamic control and blended control for missiles with lateral jets and aerodynamic surfaces,the relationship between the zero effort miss distance and the parameters of a generic homing guidance system based on finite-time generalized H2 method was developed. Effects of switch time,effective navigation ratio,amendatory proportional navigation coefficient,and target estimation time constant on the zero effort miss distance were analyzed. The analysis results can provide a basis for deter- mining the switch time of lateral thrust and guidance law parameters.