Advanced Flow Analysis Tools for Transient Solid Rocket Motor Simulations

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$749,819.00
Award Year:
2012
Program:
STTR
Phase:
Phase II
Contract:
NNX12CB09C
Award Id:
n/a
Agency Tracking Number:
100094
Solicitation Year:
2010
Solicitation Topic Code:
T9.01
Solicitation Number:
n/a
Small Business Information
IL, Princeton, IL, 61356-1934
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
Y
Duns:
969308311
Principal Investigator:
Rex Chamberlain
Principal Investigator
(815) 872-0702
rex@tetraresearch.com
Business Contact:
Rex Chamberlain
Business Official
(815) 872-0702
rex@tetraresearch.com
Research Institution:
Mississippi State University
Angie Templeton
Engineering Research Center
Mississippi State, MS, 39762-39762
() -
Domestic nonprofit research organization
Abstract
The goals of reducing total cost and increasing reliability and safety of access to space continue to be top priorities for NASA. The most immediate propulsion launch challenge involves increasing lift weight from 70 to 130 metric tons by developing the heavy lift Space Launch System (SLS). Solid rocket motor analysis tools are needed to simulate ignition and propellant recession during the burn, but current models are limited in their ability to capture ignition transients or large grain deformations during motor operation. We propose to advance propellant surface heating, ignition, and burning models as well as surface mesh recession algorithms to address a strong need for improved ignition physics and grain burn back and to deliver a unique and powerful software tool for current and next generation solid rocket motor simulations. The Phase I products have already been fielded by NASA for ignition calculations involving the Launch Abort System Jettison Motor and RSRMV. While these calculations are still in the preliminary stages, continued innovation of this successful technology strongly suggests that our research products will provide NASA with the important capability to simultaneously analyze solid propellant heat transfer, combustion, and grain burn back within a single framework. Validation of the integrated tools to a TRL of 5 will be accomplished using available motor data provided by ATK while phased releases of the new software capabilities will allow NASA immediate access to incremental updates as soon as they are available. Advancing this simulation capability will provide a large benefit to NASA because of its compatibility with NASA's mission and expertise.

* information listed above is at the time of submission.

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