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Dynamic Blade Shapes for Improved Helicopter Rotor Aeromechanics

Award Information
Agency: Department of Defense
Branch: Army
Contract: W911W6-08-C-0008
Agency Tracking Number: A072-013-0971
Amount: $119,990.00
Phase: Phase I
Program: SBIR
Solicitation Topic Code: A07-013
Solicitation Number: 2007.2
Solicitation Year: 2007
Award Year: 2007
Award Start Date (Proposal Award Date): 2007-10-09
Award End Date (Contract End Date): 2008-04-30
Small Business Information
31255 Cedar Valley Drive Suite 327
Westlake Village, CA 91362
United States
DUNS: 005100560
HUBZone Owned: No
Woman Owned: Yes
Socially and Economically Disadvantaged: Yes
Principal Investigator
 Kuo-Yen Szema
 Senior Scientist
 (818) 865-3710
Business Contact
 Vijaya Shankar
Title: Vice President
Phone: (818) 865-3713
Research Institution

HyPerComp Inc. is teaming with NextGen Aeronautics and the Rotorcraft Center at the University of Maryland to explore the use of dynamic blade shapes (morphing) for improved rotor performance. Team members complement HyPerComp’s core expertise in modeling and simulation of the rotors, NextGen’s vast experience in actuator design and fabrication, and consultation from University of Maryland on dynamic blade shapes and smart materials. We propose a high-fidelity CFD-based investigation of five different dynamic blade shape concepts for rotor performance improvement: (1) camber variation; (2) trailing edge deflection; (3) leading edge droop; (4) blade twist distribution; and (5) tip geometry (sweep, anhedral, and planform taper). The Phase-I study would be performed for the Black Hawk UH-60A rotor. Hovering, steady-level high-speed forward, and high-thrust forward flights will be studied. Loosely coupled CFD-CSD (aero-elastic) simulations of the isolated rotor (no fuselage) will be performed to compute trimmed solutions and rotor performance. Phase-I study would conclude with the documentation of the effect of the different dynamic blade shapes on rotor performance and the down-selection of the most effective ones. For those concepts, a preliminary study of the physical realizability in terms of actuation mechanism concepts, power, stroke, and frequency will be performed.

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

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