Advanced Flow Analysis Tools for Transient Solid Rocket Motor Simulations

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$100,000.00
Award Year:
2011
Program:
STTR
Phase:
Phase I
Contract:
NNX11CI37P
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
Robyn Remotigue
Engineering Research Center
Mississippi State, MS, 39762-39762
() -
Nonprofit college or university
Abstract
The challenges of designing, developing, and fielding man-rated propulsion systems continue to increase as NASA's mission moves forward with evolving solid propulsion requirements. Recent developments in simulating solid rocket motor environments include Lagrangian particle tracking, particle combustion models, dynamic particle drag and breakup models, and two phase impingement phenomena. These advances are demonstrating success in numerically simulating solid motor environments, but evolutionary innovations leading to more realistic simulations are required. In particular, transient ignition phenomena, such as grain surface heating, initiation of surface reactions, and transition to steady burning, have not yet been addressed. Consideration of these transient flow aspects is extremely important for analyzing ignition delay, pressure buildup, nonuniform grain recession, and overall combustion behavior. Our research will combine existing two phase flow tools for solid motors with a grain heating and ignition model to produce software tools for simulating transient ignition phenomena and the subsequent flow development. These products will ultimately provide NASA with the important capability to simultaneously analyze solid propellant ignition and combustion, heat transfer, and grain burnback within a unified framework. We will demonstrate feasibility using a two phase solid propellant ignition model for a simple grain shape in the TRL range of 3-4.

* information listed above is at the time of submission.

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