Advanced Flow Analysis Tools for Transient Solid Rocket Motor Simulations

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX12CB09C
Agency Tracking Number: 100094
Amount: $749,819.00
Phase: Phase II
Program: STTR
Solicitation Topic Code: T9.01
Solicitation Number: N/A
Solicitation Year: 2010
Award Year: 2012
Award Start Date (Proposal Award Date): 2012-06-11
Award End Date (Contract End Date): 2014-09-10
Small Business Information
IL, Princeton, IL, 61356-1934
DUNS: 969308311
HUBZone Owned: N
Woman Owned: Y
Socially and Economically Disadvantaged: N
Principal Investigator
 Rex Chamberlain
 Principal Investigator
 (815) 872-0702
Business Contact
 Rex Chamberlain
Title: Business Official
Phone: (815) 872-0702
Research Institution
 Mississippi State University
 Angie Templeton
 Engineering Research Center
Mississippi State, MS, 39762-39762
 () -
 Domestic nonprofit research organization
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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