Magnetostrictively actuated control flaps for vibration reduction in helicopter rotors
- Univ. of California, Los Angeles, CA (United States). Mechanical, Aerospace and Nuclear Engineering Dept.
High vibration levels can impose constraints on helicopter operations and hinder passenger acceptance. Vibration reduction using blade root pitch control introduces a significant power penalty and may adversely affect the airworthiness of the flight control system. Comparable levels of vibration reduction can be achieved using considerably less power through an actively controlled trailing edge flap mounted on the blade. Such a device would have no effect on helicopter airworthiness since it is controlled by a loop separate from the primary flight control system which utilizes the swashplate. Control flap actuation using the magnetostrictive material Terfenol-D is studied in this paper by designing a minimum weight actuator, subject to a set of actuation and stress constraints. The resulting device is capable of producing vibration reduction in excess of 90% at cruise conditions.
- OSTI ID:
- 395215
- Report Number(s):
- CONF-940691-; ISBN 1-56676-171-9; TRN: IM9648%%338
- Resource Relation:
- Conference: 2. international conference on intelligent materials, Williamsburg, VA (United States), 5-8 Jun 1994; Other Information: PBD: 1994; Related Information: Is Part Of Second international conference on intelligent materials: Proceedings; Rogers, C.A.; Wallace, G.G. [eds.]; PB: 1410 p.
- Country of Publication:
- United States
- Language:
- English
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