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Geometric control and differential flatness of a quadrotor UAV with a cable-suspended load

机译:带有电缆悬吊负载的四旋翼无人机的几何控制和微分平坦度

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A quadrotor with a cable-suspended load with eight degrees of freedom and four degrees underactuation is considered and a coordinate-free dynamic model, defined on the configuration space SE(3)×S2, is obtained by taking variations on manifolds. The quadrotor-load system is established to be a differentially-flat hybrid system with the load position and the quadrotor yaw serving as the flat outputs. A nonlinear geometric control design is developed, that enables tracking of outputs defined by (a) quadrotor attitude, (b) load attitude, and (c) position of the load. In each case, the closed-loop system exhibits almost-global properties. Stability proofs for the controller design, as well as simulations of the proposed controller are presented.
机译:考虑具有八自由度和四度欠驱动的悬索负载的四旋翼,并通过以下公式获得在配置空间SE(3)×S 2 上定义的无坐标动态模型。在歧管上进行变化。将四旋翼负载系统建立为差速混合动力系统,其中负载位置和四旋翼偏航用作平坦输出。开发了一种非线性几何控制设计,该设计能够跟踪由(a)四旋翼姿态,(b)载荷姿态和(c)载荷位置定义的输出。在每种情况下,闭环系统都具有几乎全局的特性。给出了控制器设计的稳定性证明以及所提出控制器的仿真。

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