Computer Science
Scientific paper
Jun 1993
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1993jpmc.confv....e&link_type=abstract
AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit, 29th, Monterey, CA, June 28-30, 1993, 12 p.
Computer Science
Booster Rocket Engines, Solid Propellant Ignition, Solid Propellant Rocket Engines, Space Shuttles, Transient Response, Computerized Simulation, Ignition Temperature, Solid Propellant Combustion
Scientific paper
Prediction of the ignition transient for the Advanced Solid Rocket Motor (ASRM) for the Space Shuttle presents an unusual set of modelling challenges because of its high length-to-diameter ratio and complex internal flow environment. A review of ignition modelling experience on the Shuttle Redesigned Solid Rocket Motor (RSRM), which is similar in size and configuration to the ASRM, reveals that classical igniter design theory and modelling methods under-predict, by a factor of two, the measured pressure and thrust rise rates experienced on the RSRM. This paper (1) reviews the Titan and Shuttle SRM test experience, (2) presents the results of 0-Dimensional (0-D) and 1-Dimensional (1-D) analysis of the RSRM and ASRM motors, and (3) addresses the need for advanced analysis techniques, as they relate to ASRM ignition transient modelling requirements and igniter design drivers.
Eagar M. A.
Luke G. D.
Stockham L. W.
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