摘要
主要进行变体飞行器机翼机械机构的动力学建模与控制系统设计。首先基于拉格朗日方程，建立了“滑动蒙皮”中改变机翼面积的两个四杆机构动力学数学模型，并与ADAMS动力学仿真结果进行了对比，验证了数学模型的正确性；对四杆机构的非线性动力学方程进行线性化，并设计了反馈控制器，以实现期望的机翼面积变化。最后通过仿真验证了控制系统设计的有效性。
Mechanism dynamic modeling of morphing aircraft wing and control system design were proposed in the paper. Firstly, the Lagrange equation was used to establish the mathematics model of two four-bar mechanism which changed the wing area in ＂flexible skin＂ . The results of the dynamic equation were compared to the ADAMS simulation results, which validating the correctness of the established model. And then, the nonlinear dynamic equation of four-bar mechanism was linearized, and the feedback controller was desgined to realize anticipant change of wing aera.Lastly, validity of the control system was validated through simulation.
关键词
变体飞行器
四杆机构
动力学分析
反馈线性化
morphing aircraft
four-bar mechanism
dynamic analysis
feedback linearization
