To deal with the strong coupling dynamics existed in high angle of attack maneuvers,an incremental nonlinear dy-namic inversion( INDI) control is proposed in this paper. The flight control system for missiles is divided into fast angular ve-locity loop with high bandwidth and slow angular loop with low bandwidth,then the incremental dynamic inversion control law is proposed to cancel its coupling dynamics for each loop,respectively. Thus,the decoupling control is achieved. Simulation of typical working condition shows that the proposed incremental nonlinear inversion decoupling control law can greatly improve the stability control performance with strong coupling dynamics. Compared to traditional PID control,the INDI control can com-pletely eliminate low-frequency oscillation and overshoot of overload response. At the same time,it also enables the roll angle response to accurately track command.
关键词
自动驾驶仪/耦合/增量非线性动态逆/解耦控制
Key words
autopilot/coupling/incremental nonlinear dynamic inversion/decoupling control
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