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本文对飞机飞行控制系统耦合弹性结构模态导致的伺服弹性稳定性问题进行分析;对解决电传民机伺服弹性稳定性的结构滤波器设计技术进行了研究,阐述了工程实际应用的结构滤波器验证技术。
In this paper, the problem of servo elasticity stability caused by coupled elastic structure modal of aircraft flight control system is analyzed. The structural filter design technique to solve the servo stability of electric civil aircraft is studied, and the structural filter Validation techniques.