VABS Enabled Design Environment for Efficient High-Fidelity Composite Rotor Blade and Wing Section Design

Award Information
Agency: Department of Defense
Branch: Army
Contract: W911W6-09-C-0016
Agency Tracking Number: A082-022-0411
Amount: $119,999.00
Phase: Phase I
Program: SBIR
Awards Year: 2008
Solicitation Year: 2008
Solicitation Topic Code: A08-022
Solicitation Number: 2008.2
Small Business Information
1500 Bull Lea Road, Suite 203, Lexington, KY, 40511
DUNS: 790637867
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: Y
Principal Investigator
 Patrick Hu
 Senior Scientist
 (859) 699-0441
Business Contact
 Patrick Hu
Title: President and Chairman
Phone: (859) 699-0441
Research Institution
This SBIR aims at developing a high-fidelity, yet efficient and easy-to-use, composite rotor blade and wing section design environment to facilitate rapid and confident aeromechanics assessment during conceptual design stages. A well-known technical barrier for composite rotor blade and wing section design is the lack of an efficient, user friendly, high-fidelity design tool to realistically represent the blade section at the conceptual level. This limitation prevents designers from accurately yet efficiently generating sectional properties, easily invoking comprehensive analyses, and rapidly and confidently predicting the stress distribution. As a result, aeromechanical analysis (e.g. for stability, loads, and vibration) is unfortunately left out of the conceptual design phase. In order to overcome this technical barrier and limitation, we propose to improve the functionalities of VABS (Variational Asymptotic Beam Section analysis), the best proven technology for realistic composite rotor blade analysis, and seamlessly integrate it with a versatile CAD environment, a robust optimizer, and a general-purpose postprocessor, all of which are specially tailored for blade and wing section design. We will create the initial capability in Phase I, leading to the full capability of a VABS enabled design environment for efficient high-fidelity composite rotor blade and wing section design in Phase II.

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

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