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The starting transient of solid propellant rocket motors with high internal gas velocitiesA comprehensive analytical model which considers time and space development of the flow field in solid propellant rocket motors with high volumetric loading density is described. The gas dynamics in the motor chamber is governed by a set of hyperbolic partial differential equations, that are coupled with the ignition and flame spreading events, and with the axial variation of mass addition. The flame spreading rate is calculated by successive heating-to-ignition along the propellant surface. Experimental diagnostic studies have been performed with a rectangular window motor (50 cm grain length, 5 cm burning perimeter and 1 cm hydraulic port diameter), using a controllable head-end gaseous igniter. Tests were conducted with AP composite propellant at port-to-throat area ratios of 2.0, 1.5, 1.2, and 1.06, and head-end pressures from 35 to 70 atm. Calculated pressure transients and flame spreading rates are in very good agreement with those measured in the experimental system.
Document ID
19740005393
Acquisition Source
Legacy CDMS
Document Type
Thesis/Dissertation
Authors
Peretz, A.
(Princeton Univ. NJ, United States)
Caveny, L. H.
(Princeton Univ. NJ, United States)
Kuo, K. K.
(Princeton Univ. NJ, United States)
Summerfield, M.
(Princeton Univ. NJ, United States)
Date Acquired
September 3, 2013
Publication Date
April 1, 1973
Subject Category
Propulsion Systems
Report/Patent Number
AMS-1100-T
NASA-CR-136274
AMS-1100
Accession Number
74N13506
Funding Number(s)
CONTRACT_GRANT: NGL-31-001-109
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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