Advances in Simulation of Non-symmetric/Fully 3-D Solid Propellant Rockets
- Paper number
IAC-08.C4.2.2
- Author
Mr. William Dick, University of Illinois, United States
- Coauthor
Dr. Mark Brandyberry, University of Illinois at Ubana-Champaign, United States
- Coauthor
Dr. Robert Fiedler, University of Illinois at Urbana-Champaign, United States
- Coauthor
Dr. Thomas Jackson, University of Illinois at Urbana-Champaign, United States
- Coauthor
Dr. Fady Najjar, IllinoisRocstar LLC, United States
- Year
2008
- Abstract
High-fidelity simulation of non-symmetric solid propellant (SP) rocket behavior and performance is numerically challenging, yet is critical for many current and future motor designs. This paper explores the performance of SP motors with off-axis nozzles, including fixed and thrust-vector control designs. The University of Illinois Center for Simulation of Advanced Rockets (CSAR) addresses the computational simulation of solid propellant rockets from first principles. Using a highly integrated structure/fluid/combustion interaction code --Rocstar--CSAR research faculty and staff have simulated a number of commercial and military solid propellant vehicles. Recently we have completed a simulation of the NASA Booster Separation Motor (BSM), whose nozzle is fixed at a significantly off-axis angle. Beginning in late 2006 CSAR researchers used the BSM to highlight the ability to model strongly off-axis flow behavior. To date we have simulated the flow characteristics of the motor at ignition. On-going work includes study of the propellant regression profiles and motor performance over time. The goal is a full ignition-to-tailoff simulation of motor behavior. The reusable solid rocket motor (RSRM) of the Space Shuttle has been the major simulation vehicle for CSAR. We recently reported the first complete ignition-to-tailoff simulation of the RSRM in normal, all-axial flow. Other solid propellant rockets have used for verification and validation of the CSAR integrated simulation. To explore our ability to resolve accident scenarios, the 1991 test-stand failure of the Titan IV PQM-1 rocket booster motor was used. The U.S. Air Force Ballistic Test and Evaluation System (BATES) test configuration was employed to study the effect of aluminum composition on motor efficiency and to validate particle transport and aluminum burning models in Rocstar. Simulation results and comparisons with test-stand and flight performance will be discussed. The authors will present the BSM and Titan IV thrust-vectored behavior, along with a general description of the simulation code and its application to SP motors.
- Abstract document
- Manuscript document
IAC-08.C4.2.2.pdf (🔒 authorized access only).
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