An Optimal Actuator Placement Methodology for Active Control of Helicopter Airframe Vibrations

David E. Heverly II; K.W. Wang; Edward C. Smith

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An Optimal Actuator Placement Methodology for Active Control of Helicopter Airframe Vibrations

机译：主动控制直升机机体振动的最佳执行器放置方法

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Active control of helicopter vibrations, with actuators in the airframe structure, is appealing in terms of simplicity, air- worthiness, and effectiveness. The actuator locations of current active control systems are centrally located in the cabin or near the main rotor. A new actuator placement methodology is proposed and explored in this research. The approach uses an optimization process to distribute a set of actuators at optimal locations throughout the airframe. A reduced-order airframe dynamic model is utilized for the design methodology synthesis and system analysis. Oscillatory loads at the main rotor hub and at the horizontal tail surface excite the airframe model.

机译：主动控制直升机的振动，并在机身结构中配备执行器，在简单性，适航性和有效性方面颇具吸引力。当前主动控制系统的执行器位置位于机舱的中央或主旋翼附近。在这项研究中提出并探索了一种新的执行器放置方法。该方法使用优化过程将一组执行器分配到整个机身的最佳位置。降阶机体动力学模型用于设计方法综合和系统分析。主旋翼毂和水平尾翼表面的振动负载激发了机身模型。

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《Journal of the American Helicopter Society》 |2001年第4期|p.251-261|共11页
作者
David E. Heverly II; K.W. Wang; Edward C. Smith;
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正文语种 eng
中图分类航空;
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1. New Methodology for Optimal Placement of Piezoelectric Sensor/Actuator Pairs for Active Vibration Control of Flexible Structures [J] . Ali H. Daraji, Jack M. Hale, Jianqiao Ye Journal of Vibration and Acoustics . 2018,第1期

机译：用于柔性结构主动振动控制的压电传感器/执行器对最佳放置的新方法
2. Optimal Placement of Piezoelectric Actuated Trailing-Edge Flaps for Helicopter Vibration Control [J] . S. R. Viswamurthy, Ranjan Ganguli Journal of Aircraft . 2009,第1期

机译：用于直升机振动控制的压电致动后缘襟翼的最佳放置
3. Optimal placement of piezoelectric actuators on plate structures for active vibration control via modified controlmatrix and singular value decomposition approach using modified heuristic genetic algorithm [J] . Chhabra Deepak, Bhushan Gian, Chandna Pankaj Mechanics of Advanced Materials and Structures . 2016,第1a6期

机译：通过改进的控制矩阵和奇异值分解方法，采用改进的启发式遗传算法，将压电致动器最佳地放置在板结构上，以进行主动振动控制
4. Optimal Actuator Placement and Active Structure Design for Control of Helicopter Airframe Vibrations [C] . David E. Heverly II, K. W. Wang, Edward C. Smith AHS International forum . 2002

机译：控制直升机机体振动的最佳执行器位置和主动结构设计
5. Optimal actuator placement and active structure design for control of helicopter airframe vibrations. [D] . Heverly, David Ellsworth, II. 2002

机译：最佳的执行器位置和主动结构设计可控制直升机机身的振动。
6. A Novel Hybrid Error Criterion-Based Active Control Method for on-Line Milling Vibration Suppression with Piezoelectric Actuators and Sensors [O] . Xingwu Zhang, Chenxi Wang, Robert X. Gao, 2016

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7. OPTIMAL PLACEMENT AND ACTIVE VIBRATION CONTROL OF COMPOSITE PLATES INTEGRATED PIEZOELECTRIC SENSOR/ACTUATOR PAIRS [O] . Vu Van Tham, Tran Huu Quoc, Tran Minh Tu 2018

机译：复合板集成压电传感器/执行器对的最佳放置和主动振动控制

An Optimal Actuator Placement Methodology for Active Control of Helicopter Airframe Vibrations

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