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Dynamic Blade Shapes for Improved Helicopter Rotor Aeromechanics

Award Information
Agency: Department of Defense
Branch: Army
Contract: W911W6-08-C-0061
Agency Tracking Number: A072-013-0971
Amount: $729,977.00
Phase: Phase II
Program: SBIR
Solicitation Topic Code: A07-013
Solicitation Number: 2007.2
Timeline
Solicitation Year: 2007
Award Year: 2008
Award Start Date (Proposal Award Date): 2008-09-09
Award End Date (Contract End Date): 2010-09-09
Small Business Information
2629 Townsgate Road Suite 105
Westlake Village, CA 91361
United States
DUNS: 005100560
HUBZone Owned: No
Woman Owned: Yes
Socially and Economically Disadvantaged: Yes
Principal Investigator
 Rohit Jain
 Member Technical Staff
 (805) 371-7500
 rkj@hypercomp.net
Business Contact
 Vijaya Shankar
Title: Vice-President
Phone: (805) 371-7556
Email: vshankar@hypercomp.net
Research Institution
N/A
Abstract

HyPerComp Inc. is teaming with NextGen Aeronautics and the Rotorcraft Center at the University of Maryland (UMCP) to explore the use of dynamic blade shapes (morphing) for improved rotor performance. In the ongoing Phase-I of this project we are investigating open-loop morphing of leading-edge, trailing-edge, and twist of the UH60A rotor using a comprehensive, coupled CFD-CSD software suite. For high-speed forward flight, about 3% power-saving using trailing-edge deflection and about 3% improvement in the rotor lift-to-drag ratio using active twist was demonstrated. For the high-thrust case, about 7% power-saving was obtained using leading-edge nose droop on the retreating side. A novel, comprehensive analysis approach using full CFD has been developed and shown to work efficiently in modeling morphing rotor dynamics. In the proposed Phase-II study we seek to complete this investigation, leading to a full rounded understanding of morphing rotorcraft design. We will address a broader set of flight conditions and morphing concepts. Full CFD-CSD analyses will be supplemented with industry standard comprehensive analyses coupled with acoustics, vibrations and aero-elastic effects thus accentuating the impact of this work. A paper study of actuator design and requirements will be made, and an existing morphing rotor prototype will be adapted to create a bench test model to demonstrate practical considerations.

* Information listed above is at the time of submission. *

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