Acoustic Stability Prediction In Solid Rocket Motors

Award Information
Agency:
Department of Defense
Branch
Navy
Amount:
$79,970.00
Award Year:
2010
Program:
SBIR
Phase:
Phase I
Contract:
N68936-10-C-0048
Award Id:
98407
Agency Tracking Number:
N101-040-1047
Solicitation Year:
n/a
Solicitation Topic Code:
NAVY 10-040
Solicitation Number:
n/a
Small Business Information
1802 N. Carson Street, Suite 200, Carson City, NV, 89701
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
083152975
Principal Investigator:
Anthony Dang
Principal Research Scient
(775) 882-1966
anthony@seainc.com
Business Contact:
Douglas Coats
President
(775) 882-1966
doug@seainc.com
Research Institution:
n/a
Abstract
The ability for engineers to assess the impact of their preliminary design of solid rocket motor (SRM) performance and combustion stability is the focus of this proposal. The SRMs of the future will be designed for increased performance. Since ballistic excursions, instabilities, and sporadic forces on rocket motors have catastrophic results, Software and Engineering Associates, Inc. (SEA) has made considerable effort developing and maintaining codes for SRM performance and stability analysis. SEA has incorporated the Standard Stability Prediction (SSP) code into their Solid Performance Program (SPP), and will use these codes to improve the prediction of motor ballistic performance and stability of SRM grain designs. The modeling of the oscillatory forces on a motor given the change in pressure will be added to SPP. New and innovative methodologies will be implemented into SPP/SSP for analyzing strain augmented burning and multi-dimensional combustion stability in SRMs. These innovative technologies include using existing grain design technology, grid generation, a steady state Navier-Stokes (NS) solver and/or an Euler CFD code, and an acoustics eigensolver and linear stability analysis coupled with a structural solver. Investigation will center on the impact of strain augmented burning on ballistic performance and instabilities coupled with vortical flow.

* information listed above is at the time of submission.

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