摘要
使被动寻的导弹在较低的平飞弹道情况下 ,以较小的俯冲过载和最佳攻击姿态精确命中目标 .采用带落角约束的变结构导引律 ,对弹目距离及距离变化率进行估计 ,克服被动寻的导弹不能测距的约束 ,同时使切换开关增益随时间自适应变化以减小俯冲过载 .利用某型在研被动寻的导弹的气动参数 ,对此变结构导引律进行了数学仿真 ,仿真结果表明 ,在较低的平飞弹道约束条件下及过载要求范围内 ,该导引律能以期望落角命中静止与机动的坦克目标 。
To design a variable structure proportional navigation law for the passive homing missile so that the missile can hit the target with minimum miss-distance and desired impact attitude angle within required overload when it flies at lower trajectory. The variable structure proportional navigation with terminal angular constraint is utilized, and estimation about the distance rate and distance between missile and target is made, which broke the constraint that passive homing missile can't measure out the distance and distance rate. The switch gain to vary adaptively with time avoids larger overload. The mathematical simulation was finished by some studied passive homing missile's dynamic model and simulation results show that the navigation law of passive homingmissile can make missile get required missdistance and desired impact attitude angle against maneuvering and nonmaneuvering tank with lower trajectory and within the maximum overload, also this guidance law is much robust to the estimation error of distance and distance rate.
出处
《弹道学报》
EI
CSCD
北大核心
2001年第1期16-20,共5页
Journal of Ballistics
关键词
落角约束
变结构比例导引
被动寻的导弹
命中误差
反坦克导弹
terminal impact angular constraint, variable structure proportional navigation, passive homing missile
