BTT导弹控制系统设计与全弹道数字仿真

THE DESIGN OF A BTT MISSILE CONTROL SYSTEM AND FULL TRAJECTORY NUMERICAL SIMULATIONS

本文先用古典控制理论设计BTT导弹自动驾驶仪,采用比例导引规律,在导弹最大滚动角φ_(max)不作限制的条件下设计制导逻辑。然后,在不限制φ_(max)或限制φ_(max)≤±90°,有无偏航通道和是否考虑控制系统测量元件动态特性的不同组合条件下,进行全弹道数字仿真计算与分析。结果证明:设计的制导系统、制导逻辑和自动驾驶仪是合理的、正确的,具有工程应用价值。BTT导弹攻击范围大,跟踪性能好,在目标作较大机动时也能稳定击中目标。

This paper describes the design of a BTT missile autopilot by means of the classical control theory, and the guidance logic using the proportional guidance law without any constraint in the maximum roll angle of the missile. Full trajectory numerical simulations are computed and analyzed in the following different conditions of combination: wichout constraint in maximum roll angle or with constraint in the angle between -90 to +90 degree; with or without a yaw channal; with or without the consideration of the dynamics of sensors in the control system. The Tesults show that the designed guidance system, guidance logic and the autopilot are correct, reasonable and significant in practical engineering applications. They also verify that the BTT missiles have the characters of large attacking range, good tracking performance, and hitting the target stably when it's in larger maneuvering.