摘要
针对现有火箭弹头锥摆动方法不适用于库存火箭弹的问题,提出基于引信头锥摆动的弹道修正方法。该方法通过电机驱动控制引信头锥摆角改变全弹气动外形,产生二维弹道修正所需附加修正力及力矩,达到修正弹道落点的目的。气动仿真结果表明:阻力系数仿真值与风洞试验值的相对误差不超过20%,且弹道仿真结果与原火箭弹的方向、距离误差对比表明,头锥摆动式弹道修正引信的修正能力可以基本满足二维弹道修正的要求。
The current rockets trojectory correction method of nose cone swinging is not suitable for stock rockets,aimming at this problem,a new trajectory correction method based on fuze nose cone swinging was proposed.A electric motor controled and changed the swing angle of fuze nose cone,and the aerodynamic configration of rockets was changed as well,thus,correction force could be produced to correct trajectory.Aerodynamic simulation results showed that the drag coefficient of simulation was in good consistency with wind tunnel test results,and the comparison on simulation results and actual range or side error of rockets proved that the trajectory correction based on fuze nose cone swinging could satisfy the requirements of rockets two-dimensional trajectory correction.
出处
《探测与控制学报》
CSCD
北大核心
2011年第4期23-27,33,共6页
Journal of Detection & Control
关键词
火箭弹
弹道修正
引信头锥
rockets
trajectory correction
fuze nose cone
