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Optimization of an Active Twist Rotor Blade Planform for Improved Active Response and Forward Flight PerformanceA study was conducted to identify the optimum blade tip planform for a model-scale active twist rotor. The analysis identified blade tip design traits which simultaneously reduce rotor power of an unactuated rotor while leveraging aeromechanical couplings to tailor the active response of the blade. Optimizing the blade tip planform for minimum rotor power in forward flight provided a 5 percent improvement in performance compared to a rectangular blade tip, but reduced the vibration control authority of active twist actuation by 75 percent. Optimizing for maximum blade twist response increased the vibration control authority by 50 percent compared to the rectangular blade tip, with little effect on performance. Combined response and power optimization resulted in a blade tip design which provided similar vibration control authority to the rectangular blade tip, but with a 3.4 percent improvement in rotor performance in forward flight.
Document ID
20140011914
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Sekula, Martin K (NASA Langley Research Center Hampton, VA, United States)
Wilbur, Matthew L. (Army Research Lab. Hampton, VA, United States)
Date Acquired
September 18, 2014
Publication Date
January 22, 2014
Subject Category
Air Transportation And Safety
Aircraft Design, Testing And Performance
Report/Patent Number
NF1676L-16800
Meeting Information
Meeting: Decennial AHS Aeromechanics Specialists'' Conference
Location: San Francisco, CA
Country: United States
Start Date: January 22, 2014
End Date: January 24, 2014
Sponsors: American Helicopter Society, Inc.
Funding Number(s)
WBS: WBS 432938.11.01.07.43.40.08
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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