Novel Experimental and Numerical Methods for the Aeromechanical Design of Flapping Wing Hovering MAVs

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA9550-06-C-0086
Agency Tracking Number: F064-021-0260
Amount: $99,935.00
Phase: Phase I
Program: STTR
Awards Year: 2006
Solicitation Year: 2006
Solicitation Topic Code: AF06-T021
Solicitation Number: N/A
Small Business Information
CONTINUUM DYNAMICS, INC.
34 Lexington Avenue, Ewing, NJ, 08618
DUNS: 096857313
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Glen Whitehouse
 Associate
 (609) 538-0444
 glen@continuum-dynamics.com
Business Contact
 Barbara Agans
Title: Administrator
Phone: (609) 538-0444
Email: barbara@continuum-dynamics.com
Research Institution
 NEW MEXICO STATE UNIV.
 James Allen
 P.O. Box 30001
Las Cruces, NM, 88003
 (505) 646-6546
 Nonprofit college or university
Abstract
Recent developments have made clear the strong potential of Micro Air Vehicles (MAVs) for a wide range of surveillance and tactical reconnaissance functions, particularly if the challenging but critical hovering capability can be achieved. Implementation of a practical hovering air vehicle at very small scales, however, requires breakthroughs in understanding of the complex flow environment of such vehicles as well as development of practical design and analysis tools for this regime. The proposed effort will support these objectives by advancing the fundamental understanding of the relationship between wing kinematics and forces – including low Re and wing flexibility effects – with the ultimate goal of developing aerodynamic/aeroelastic models for use in simulation and design. This will permit generation of viable aerodynamic flight control schemes for flapping wing MAVs operating in gusty conditions. The effort will build on mutually supporting capabilities of the team members, and will feature application of a suite of both established and evolving computational modeling tools for complex vortex-dominated flows at low Re as well as use of advanced experimental methods for flow diagnostics and aeroelastically scaled models. The project will also leverage a strong foundation of experience in support of design software for vertical flight vehicles.

* information listed above is at the time of submission.

Agency Micro-sites

US Flag An Official Website of the United States Government