一种对基于耗尽关机多级固体火箭概念设计的改进方法(英文)

An Improved Method for Conceptual Design of Multi-stage Solid Rockets Based on Depleted Shutdown

由于维护简单和发射快速,弹道导弹多用固体火箭发动机,但繁杂的推力终止装置使各级装药不能耗尽并让结构增重。提出了一种对基于耗尽关机多级固体火箭概念设计的改进方法,此方法满足导弹系统主要的战技要求。为解决无推力终止装置的末速不准问题,可在末级发动机采用姿态调整装置,对射角进行调整,配合末速以满足射程要求。本方法还可抑制敌方反导探测。

Solid propellant rocket motors are preferred for most ballistic missiles because they need simple maintenance and can be launched quickly.But the conventional thrust termination devices limit the depletion of every stage's grain and increase some extra-weight.An improved method for designing a multi-stage solid rocket based depleted shutdown was provided.In order to solve the problem of lack of thrust termination devices,a device to adjust the burnout angle will match the final burnout velocity and satisfy the desired range.The method can also limit the detection from anti-ballistic missile system.