摘要
红外寻制导的导弹只能探测跟踪目标(飞机)的热辐射中心,即发动机尾喷流中心。它离飞机质心有一段距离h,为了有效地杀伤目标,提高杀伤概率,必须使命中点前移一段距离h,为此我们对此进行了研究。本文导出了空间飞行时实现超前偏置的相对运动方程和导引律,并提出简化导引律方案,探讨了控制系统实现的方法。
A proportional-navigation guidance law for leading of impact point in infrared hom-
ing gaidance is studied in this paper. For infrared homing guidance only can follow heat seek-
ing center of tail fireworks. In order to effectively hit the center of target and increase killing
probability, the impact point must move forwardly a length h equal to the distance betwen the
tail fireworks to the mass center of torgets.
This paper consists of fllowing contents:
To begin with, The precise formulas of plane and space proportional-navigation guidance
law for leading of tracking point are established.
Secondly, The formulas are reduced for convenience in practice. The reduced formulas are
calculated and compared with the precise one. The result shows that the proportional-naviga-
tion guidance law for leading of impact point surely moved impact point forwards. The reduced
formula of guidance law also works properly with little error, which is negligible. This is of im-
portance to design infrared homing guidance system.
出处
《航天控制》
CSCD
北大核心
1992年第4期1-8,15,共9页
Aerospace Control
基金
航天基金资助项目
关键词
红外制导
导引规律
比例导航
Infrared guidance
Guidance law
Proportional navigation
