COMBUSTION INSTABILITY OF NON-ALUMINIZED PROPELLANTS - THE INFLUENCE OF PROPELLANT FORMULATION

Authors
  1. Smith, D.L.
  2. Christie, F.
  3. Clark, M.N.
Corporate Authors
Defence Research Establishment Valcartier, Valcartier QUE (CAN);American Inst of Aeronautics and Astronautics, New York NY (US)
Abstract
The severity of longitudinal combustion instability was measured for a number of nonaluminized propellant formulations. All the formulations contained ammonium perchlorate and hydroxyl-terminated polybutadiene binder; most contained a burning rate modifier, either iron oxide or catocene. The propellants were tested at 70F to initiate instability. The criterion used to measure the level of instability was the percentage increase in time-averaged pressure between stable and unstable operation at a given stable pressure.
Report Number
PAPER-77-900 — Reprint 4192
Date of publication
01 Jan 1977
Number of Pages
4
Reprinted from
Proceedings of AIAA/SAE 13th Propulsion Conference held July 11-13, 1977, p 1-4
DSTKIM No
77-04035
CANDIS No
100719
Format(s):
Hardcopy

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