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首页> 外文期刊>Fortschritt-Berichte VDI, Reihe 8. Mess-, Steuerungs- und Regelungstechnik >Implementation of an H_∞ Controller for the Helicopter BK 117
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Implementation of an H_∞ Controller for the Helicopter BK 117

机译：直升机BK 117的H_∞控制器的实现

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The active vibration reduction of rotor hub loads by means of piezoelectrically driven trailing edge flaps is addressed in the present work H_∞ control synthesis is used to develop a robust controller to be operated in different flight conditions, for instance different flight speeds, altitudes, and manoeuvres. Pre-flight specifications have been worked out for proving the controller on the BK 117 helicopter, That needs the analytical decomposition of the controller in an observer form with full state feedback, the decoupling of the individual internal loops, and the discretization of the observer-based controller. Open-loop flight measurements have been performed with 4/rev flap inputs in the multi-blade coordinates and reliable transfer functions have been identified at this particular frequency to assess the rotor model (used to design the controller) and investigate, whether the designed controller would be robust stable when it is operated on the real helicopter. Finally, the H_∞, vibration controller was tested in closed-loop showing robust stability and performance in on- and off-design flight conditions.
机译：在本工作中解决了通过压电驱动的后缘襟翼主动降低转子轮毂负载的问题。H_∞控制综合用于开发一种鲁棒的控制器，使其能够在不同的飞行条件下（例如，不同的飞行速度，高度和动作。为了在BK 117直升机上验证控制器，已经制定了飞行前规范，这需要以完整状态反馈，独立内部回路的解耦以及观察者的离散化的观察者形式对控制器进行分析分解。基于控制器。已经在多叶片坐标系中使用4 / rev襟翼输入进行了开环飞行测量，并且已经在该特定频率上确定了可靠的传递函数，以评估旋翼模型（用于设计控制器）并调查是否设计了控制器当它在真实的直升机上操作时，将具有强大的稳定性。最后，在闭环下对H_∞振动控制器进行了测试，显示出在设计上和设计外飞行条件下的鲁棒稳定性和性能。

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