旋转导弹姿态稳定控制方法研究

摘要

旋转导弹往往采用初始静不稳定的结构形式使得在攻击目标时具有较大的过载能力,如何能够保证旋转导弹平稳地度过静不稳定段是导弹正常飞行的关键.采用姿态稳定控制方法对初始段进行控制,使导弹顺利度过静不稳定段,通过数学仿真及半实物仿真验证了该控制方法的有效性.基于正交试验设计的仿真试验表明,在各种气动干扰因素影响下,旋转导弹均能实现较高的姿态控制精度.%Spinning missile generally adopts initial unsteady structure to make it endure much higher overload. It is necessary for a spinning missile to get through the unsteady period successfully. The attitude stabilization control method is designed for spinning missile. The design of attitude stabilization control method is given and math simulation is completed. The availability is validated by simulation data at different interference backgrounds.