Aero-elastic stability design of spinning ballistic missile with sliding mode control

Spin is an effective way against the laser anti-missile in the first boosting phase. Owing to missile spin, the frequencies of bending vibration decrease in value by spinning speed, and the spinning speed cannot be keep absolute constant in flight. Therefore a time-varying filter network based on the parallel differential spectrum (PD) theory is applied to adapt to the change of vibration frequency. Considering control couplings, motion couplings and other effects introduced by spin, a sliding mode control system is designed to achieve the missile´s steady flight. The research results show that the configuration of the nonlinear controller is restricted by the stability requirement of elastic vibrations, and it must match with the filter network. In this paper, some meaningful conclusions are drawn.