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ASRM Multi-Port Igniter Flow Field AnalysisThe Advanced Solid Rocket Motor (ASRM) program was initiated by NASA in response to the need for a new generation rocket motor capable of providing increased thrust levels over the existing Redesigned Solid Rocket Motor (RSRM) and thus augment the lifting capacity of the space shuttle orbiter. To achieve these higher thrust levels and improve motor reliability, advanced motor design concepts were employed. In the head end of the motor, for instance, the propellent cast has been changed from the conventional annular configuration to a 'multi-slot' configuration in order to increase the burn surface area and guarantee rapid motor ignition. In addition, the igniter itself has been redesigned and currently features 12 exhaust ports in order to channel hot igniter combustion gases into the circumferential propellent slots. Due to the close proximity of the igniter ports to the propellent surfaces, new concerns over possible propellent deformation and erosive burning have arisen. The following documents the effort undertaken using computational fluid dynamics to perform a flow field analysis in the top end of the ASRM motor to determine flow field properties necessary to permit a subsequent propellent fin deformation analysis due to pressure loading and an assessment of the extent of erosive burning.
Document ID
19950017219
Acquisition Source
Headquarters
Document Type
Conference Paper
Authors
Kania, Lee (Sverdrup Technology, Inc. Huntsville, AL., United States)
Dumas, Catherine (Sverdrup Technology, Inc. Huntsville, AL., United States)
Doran, Denise (NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1993
Publication Information
Publication: Eleventh Workshop for Computational Fluid Dynamic Applications in Rocket Propulsion, Part 1
Subject Category
Fluid Mechanics And Heat Transfer
Accession Number
95N23639
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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