Structural-Acoustic Simulations in Early Airframe Design

Award Information
Agency:
National Aeronautics and Space Administration
Branch:
N/A
Amount:
$99,993.00
Award Year:
2007
Program:
SBIR
Phase:
Phase I
Contract:
NNL07AA78P
Agency Tracking Number:
065931
Solicitation Year:
2006
Solicitation Topic Code:
A2.03
Solicitation Number:
N/A
Small Business Information
Michigan Engineering Services, LLC
2890 Carpenter Road, Suite 1900, Ann Arbor, MI, 48108-1100
Hubzone Owned:
N
Socially and Economically Disadvantaged:
N
Woman Owned:
Y
Duns:
134722656
Principal Investigator
 Geng Zhang
 Principal Investigator
 (734) 477-5710
 gengzhang@miengsrv.com
Business Contact
 Christina Vlahopoulos
Title: Business Official
Phone: (734) 358-0777
Email: christinavl@miengsrv.com
Research Institution
N/A
Abstract
The structural design during the early development of an aircraft focuses on strength, fatigue, corrosion, maintenance, inspection, and manufacturing. Usually the acoustic requirements are met after the design of the fuselage structure has been completed. Ideally the structural-acoustic concerns should enter the design cycle early and they should be considered along with other main design disciplines within a Multi-disciplinary Design Optimization (MDO) environment. The proposing firm is uniquely positioned for developing technology which will bring structural-acoustic simulations early in the airframe design process because of their Energy Finite Element Analysis (EFEA) product for structural-acoustic simulations of large systems, and their development of a general purpose code for Multi-disciplinary Design Optimization under Uncertainty (MDO-U). The proposed Phase I project will demonstrate the feasibility of including structural-acoustic simulations in early airframe design. An adjoint sensitivity formulation will be implemented in the EFEA for enabling the utilization of the EFEA within a design optimization environment. In a case study a representative airframe structure will be optimized simultaneously for two different disciplines, using common design variables. An impact type of concern (representative of impact applications for rotorcraft and aircraft, and of shock applications for launch vehicle dynamics) and a structural-acoustic performance due to structure-borne and air-borne excitations (representative to aircraft, rotorcraft, and launch vehicle applications) will be considered. The MDO-U and the EFEA codes will be utilized in the case study, which will demonstrate the feasibility and the value of bringing structural-acoustics early in the design cycle.

* information listed above is at the time of submission.

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