NASA NTRS · 19960012502
ASRM combustion instability studies
Abstract
The objectives of this task were to measure and compare the combustion response characteristics of the selected propellant formulation for the Space Shuttle Advanced Solid Rocket Motor (ASRM) with those of the current Redesigned Solid Rocket Motor (RSRM) formulation. Tests were also carried out to characterize the combustion response of the selected propellant formulation for the ASRM igniter motor.
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Strand, L. D.. 1992-02-01. ASRM combustion instability studies. https://ntrs.nasa.gov/citations/19960012502
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