摘要
研究了机翼变形角误差对空空导弹发射后截获性能的影响。根据某型导弹挂机后计算的载机机体坐标系与导弹弹体坐标系的相对角误差量,仿真计算了机翼变形角误差对导弹发射后截获概率的影响。仿真结果表明,机翼变形角误差对导弹发射后截获性能影响大,必须对其进行补偿,否则载机在大机动情况下发射导弹,导弹将不能截获目标。并据此提出了对机翼变形角误差的补偿方法和解决途径。研究结果对空空导弹的工程研制具有参考价值。
The effects of wing distortion angle error on the target acquisition performance of lock-on-after- launch missile were studied. Based on the calculated relative angle error between airplane body coordinate and missile body coordinate after a certain missile was mounted, the effects of wing distortion angle error on the target acquisition performance of lock-on-after-launch were simulated. The simulation results show wing distortion angle error influences the target acquisition performance of lock-on-after-launch greatly. The effects must be compensated, otherwise the missile will not capture the target after launched when the airplane is maneuvering largely. The compensation method and solution are proposed, and the research results have reference value for missile engineering development.
出处
《科学技术与工程》
北大核心
2013年第1期258-261,共4页
Science Technology and Engineering
关键词
机翼变形误差
中制导
发射后截获
导引头
wing distortion error middle guidance lock-on-after launch seeker
