Starting from the mathematical model of a pseudo AO A three-loop autopilot,this paper analyzes the system stability boundary and provides an empirical formula for the maximum allowable instability of the airframe.Based on engineering applications,a simple analytical relationship between control parameters and closed-loop poles is established,and the predictive correction of control parameters is performed.The case analysis shows that this method is convenient and effective,with fast convergence speed,and is suitable for the design of three-loop autopilot for aircraft with rapidly changing static stability.
维普
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