High-Fidelity Multiphysics Simulations of Nozzle Erosion

Award Information
Agency:
Department of Defense
Branch
Missile Defense Agency
Amount:
$99,999.00
Award Year:
2010
Program:
STTR
Phase:
Phase I
Contract:
HQ0006-10-C-7390
Award Id:
94854
Agency Tracking Number:
B09B-009-0003
Solicitation Year:
n/a
Solicitation Topic Code:
MDA 09T009
Solicitation Number:
n/a
Small Business Information
P. O. Box 3001, Champaign, IL, 61826
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
792045713
Principal Investigator:
MarkBrandyberry
Chief Operating Officer
(217) 766-2567
mdbrandy@illinoisrocstar.com
Business Contact:
WilliamDick
Chief Executive Officer
(217) 417-0885
wdick@illinoisrocstar.com
Research Institute:
University of Illinois
Kathy Young
OSPRA, 1901 S. First
Champaign, IL, 61820
(217) 333-2187

Abstract
A collaborative effort is proposed between IllinoisRocstar LLC and the University of Illinois to develop and commercialize a computational framework to investigate nozzle erosion in solid-propellant rocket motors (SRM) and tangential instability modes in liquid rocket engines (LRE). For SRM, highly resolved simulations will be performed to understand the effects of turbulent inlet conditions, as well as nozzle vectoring, on nozzle erosion. The thermal boundary layer is captured along the nozzle walls to compute the heat flux and erosion rates. To optimize the computational resources, the SRM nozzle configuration is studied by itself and appropriate inflow conditions are imposed. Two complementary formulations to apply these inlet conditions are described: the first is based on extracting the flow field from the full motor configuration for turbulent flows; while the second invokes a multiscale asymptotic analysis of turbulent flows inside rocket motor. Preliminary results suggest that specifying turbulent, rather than uniform, inlet conditions has a significant effect on nozzle erosion. For LRE, a full three-dimensional configuration is proposed to investigate tangential instabilities.

* information listed above is at the time of submission.

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