Material Characterization for Hypersonic Vehicles by the Fast Mutipole Boundary Element Method

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNL07AB79P
Agency Tracking Number: 065853
Amount: $100,000.00
Phase: Phase I
Program: SBIR
Awards Year: 2007
Solicitation Year: 2006
Solicitation Topic Code: A2.01
Solicitation Number: N/A
Small Business Information
Avant Analysis Technology
39 Hickory Circle, Ithaca, NY, 14850-9610
DUNS: 132282091
HUBZone Owned: N
Woman Owned: Y
Socially and Economically Disadvantaged: N
Principal Investigator
 Yu Mukherjee
 Principal Investigator
 (607) 277-4648
 xieyu9@hotmail.com
Business Contact
 Yu Mukherjee
Title: owner
Phone: (607) 277-4648
Email: xieyu9@hotmail.com
Research Institution
N/A
Abstract
Hypersonic aircraft are subjected to extreme conditions with respect to mechanical thermal and acoustic loads. Materials with complex microstructure, such as Functionally Graded (FGM) and honeycomb, are expected to play a key role in such vehicles. Detailed numerical stress and thermal analysis of such materials, with conventional Finite Element Methods (FEM), is extremely difficult. The Fast Multipole Boundary Element Method (FMBEM) is a very promising candidate for carrying out such calculations efficiently and accurately. This is an O(N) method (where N is the size of a problem) with respect to both matrix formulation and solution of linear systems. It is proposed that two user-friendly software packages based on the FMBEM, to be called AvantFGM and AvantHoneycomb, will be developed in this proposed Phase I project. These packages will be used to carry out mechanical and thermal characterization of these complex materials. The output of these packages will deliver material properties as functions of spatial coordinates, which can then be used to carry out conventional FEM analyses of aircraft components of complex geometrical shape. Plans for Phase II call for development of fully functioning commercial software capable of analyzing many realistic situations pertaining to hypersonic aircraft. Phase III will be concerned with further development of the software to include damage accumulation (due to, for example, mechanical, creep and thermo-acoustic fatigue) and risk analysis.

* information listed above is at the time of submission.

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