固冲动力导弹纵向通道控制弹机一体化设计

A Longitudinal Channel Control of Integrated Missile and Engine Design Method for A solid propellant rocket ramjet engine missile

摘要:

以固体冲压发动机为动力的导弹武器，其弹道规划中应充分考虑发动机工作的经济性以及进气道的安全性，根据实时飞行状态调节燃气流量实现燃料最优控制，同时限制补燃室压强以满足进气道裕度要求。本文，提出了一种基于速度控制策略设计的导弹纵向通道弹机一体化控制系统，建立发动机及导弹控制线性化数学模型，设计控制律并进行数学仿真，仿真结果表明本文设计的纵向控制系统可实现导弹能量管理需求，并对进气道进行保护，满足固冲发动机的使用要求。

Abstract:

For a solid propellant rocket ramjet engine missile, the economical efficiency of engine and reliability of inlet should be fully considered in trajectory planning. According to the real time flight state, trajectory planning should fulfill the requirements as regulating gas flow for optimize control, and limit the pressure of afterburning chamber to satisfy the needs of supersonic inlet safety margin. In this paper, one method is proposed with velocity control strategy for integrated missile and engine system. Based on mathematical linearization control model of missile and engine, the control rate is well designed and following the model is simulated. As a result, the simulation results show that the longitudinal channel control system from this paper can realize energy control for missile, and the inlet can be protected to meet ramjet engine’s requirements.