一种等β值再入大气层弹道导弹弹头伴随重诱饵的设计方法  

A Designing Method for Company Heavy Decoy of Reentry Ballistic Missile by Using Identical β

作　　者：李宏[1] 杨英科[1] 孙仲康[1] 徐晖[1] 

机构地区：[1]国防科技大学电子工程学院

出　　处：《系统工程与电子技术》1998年第8期1-3,57,共4页Systems Engineering and Electronics

基　　金：国家自然科学基金;国防预研基金

摘　　要：本文从再入大气层弹道导弹弹头运动的解析解着手，找出了在再入点参数一定的情况下，决定弹头运动状态的唯一因素是弹头的弹道系数。为此，本文提出了一种设计弹头伴随重诱饵的方法。按此方法设计诱饵，可使得在整个再入段，诱饵即使不带小型发动机调整姿态，也能保持与弹头相同的运动状态，以此达到掩护弹头突防的目的。This paper is started with the closed form motion solution for ballistic missile to reenter the Earth's atomosphere. It is found when the parameters are unchanged at the point of reentry, the only cause to decide the motion of the missile is its trajectory coefficient, where a method is proposed to design heavy decoy flying together with a missile. The decoy designed by the method, even if there is not small engines with it to adjust its posture, will keep the same motion with the missile along the whole reentry trajectory so as to shield the missile to break through the defense.

关 键 词：弹道式 再入飞行器 弹道导弹 诱饵 弹道计算 

分 类 号：TJ761.3[兵器科学与技术—武器系统与运用工程] TJ760.2