近程导弹初始姿态调整回路设计

Design of Initial Attitude Adjustment Loop of Short Range Missile

根据捷联惯导系统坐标变换原理,建立了近程导弹初始段姿态调整回路数学模型,并运用六自由度刚体弹道进行了弹道仿真.结果表明,初始段姿态调整回路能够保证导弹在较大的初始姿态散布和初始段弹道倾角迅速下降的条件下,以较高的精度在短时间内完成三个通道的姿态调整.

Based on SINS coordinate conversion principle,the math model of initial attitude adjustment loop of short range missile is established.The trajectory is emulated based on SDOF rigid body ballistic trajectory.The results indicate that the initial attitude adjustment loop is able to complete the attitude adjustment rapidly in a high accuracy,in the condition of a rather large effect of initial disturb and fast fall of trajectory pitch angle.