This chapter presents an evaluation of actuation concepts that underlie active blade twist technology and aspects of integral twist actuation and rotor optimisation. It thus provides a reference in the design of advanced rotary unmanned aerial vehicles (RUAVs). The chapter explores the following themes: actuation concepts, and integral twist actuation. There have been considerable efforts in the helicopter community to control the sources of fuselage vibration and rotor noise. The integral twist actuation concept, which uses active materials technology, has shown promising benefits in hover testing with small‐scale models. Advanced active rotor blade technology requires a sensing/actuation system. The smart hybrid active rotor control system (SHARCS) project demonstrated simultaneous reduction of vibration and noise in helicopters using a hybrid system that integrates three independent active control systems on the helicopter blade: active pitch link (APL), actively controlled flap (ACF) and actively controlled flap (ACT).


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    Title :

    Active Blade Twist in Rotary UAVs using Smart Actuation


    Contributors:


    Publication date :

    2017-04-03


    Size :

    21 pages




    Type of media :

    Article/Chapter (Book)


    Type of material :

    Electronic Resource


    Language :

    English








    Hover Testing of a Smart Rotor With Induced-Strain Actuation of Blade Twist

    Chen, P. / Chopra, I. / American Institute of Aeronautics and Astronautics| ASME| ASCE | British Library Conference Proceedings | 1995