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Ignition transient analysis of solid rocket motorMeasurement data on the performance of Space Shuttle Solid Rocket Motor show wide variations in the head-end pressure changes and the total thrust build-up during the ignition transient periods. To analyze the flow and thermal behavior in the tested solid rocket motors, a 1-dimensional, ideal gas flow model via the SIMPLE algorithm was developed. Numerical results showed that burning patterns in the star-shaped head-end segment of the propellant and the erosive burning rate are two important factors controlling the ignition transients. The objective of this study is to extend the model to include the effects of aluminum particle commonly used in solid propellants. To treat the effects of aluminum-oxide particles in the combustion gas, conservation of mass, momentum, and energy equations for the particles are added in the numerical formulation and integrated by an inter-phase-slip algorithm.
Document ID
19920006646
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Han, Samuel S.
(Tennessee Technological Univ. Cookeville, TN, United States)
Date Acquired
September 6, 2013
Publication Date
October 1, 1991
Publication Information
Publication: Alabama Univ., Research Reports: 1991 NASA(ASEE Summer Faculty Fellowship Program
Subject Category
Spacecraft Propulsion And Power
Accession Number
92N15864
Funding Number(s)
CONTRACT_GRANT: NGT-01-008-021
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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