Development of swashplateless helicopter blade pitch control system using the limited angle direct-drive motor (LADDM)

Author:

Wang Jian,Wang Haowen,Wu Chao

Publisher

Elsevier BV

Subject

Mechanical Engineering,Aerospace Engineering

Reference25 articles.

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2. Wind-tunnel testing of rotor with individually controlled trailing-edge flaps for vibration reduction;Roget;J Aircr,2008

3. Daniel P, Li L, Friedmann P.P. Helicopter noise reduction by actively controlled flaps. Proceedings of the 11th AIAA/CEAS aeroacoustics conference; 2005 May 23–25; Monterey, CA. Reston, VA: AIAA; 2005. p. 1–21.

4. Analysis and testing of Mach-scaled rotor model with trailing-edge flaps;Koratkar;J AIAA,2000

5. Helicopter rotor in-plane stability enhancement using trailing-edge flaps;Maurice;J Guid Control Dyn,2013

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