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Performance of Swashplateless Ultralight Helicopter Rotor with Trailing-edge Flaps for Primary Flight ControlThe objective of present study is to evaluate the rotor performance, trailing-edge deflections and actuation requirement of a helicopter rotor with trailing-edge flap system for primary flight control. The swashplateless design is implemented by modifying a two-bladed teetering rotor of an production ultralight helicopter through the use of plain flaps on the blades, and by replacing the pitch link to fixed system control system assembly with a root spring. A comprehensive rotorcraft analysis based on UMARC is carried out to obtain the results for both the swashplateless and a conventional baseline rotor configuration. The predictions show swashplateless configuration achieve superior performance than the conventional rotor attributed from reduction of parasite drag by eliminating swashplate mechanic system. It is indicated that optimal selection of blade pitch index angle, flap location, length, and chord ratio reduces flap deflections and actuation requirements, however, has virtually no effect on rotor performance.
Document ID
20050182117
Acquisition Source
Headquarters
Document Type
Preprint (Draft being sent to journal)
Authors
Shen, Jin-Wei
(Maryland Univ. College Park, MD, United States)
Chopra, Inderjit
(Maryland Univ. College Park, MD, United States)
Date Acquired
August 23, 2013
Publication Date
January 1, 2003
Subject Category
Aircraft Design, Testing And Performance
Meeting Information
Meeting: American Helicopter Society Annual Forum
Location: Phoenix, AZ
Country: United States
Start Date: May 1, 2003
Sponsors: American Helicopter Society, Inc.
Distribution Limits
Public
Copyright
Public Use Permitted.
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