Nozzleless Booster Performance Study

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Authors
  1. Farinaccio, R.
  2. Lessard, P.
Corporate Authors
Defence Research Establishment Valcartier, Valcartier QUE (CAN)
Abstract
A formulation based on HTPB/AP propellant with FEOOH/CuPht co-catalysts was developed as a potential candidate for use as a nozzleless booster propellant. This propellant exhibited qualities of high burn rate and good combustion stability with high mass flow necessary to cause exhaust gases to choke downstream in a cylindrical grain. Another consideration was that the pressure exponent was low enough to give a more uniform burn rate across a larger pressure regime. The propellant exhibited a burn rate of 30 mm/s at 6.89 MPa and a pressure exponent of 0.412. Tests of experimental motors have shown that the pressure and thrust are dependent on the ratio of the motors length to diameter (L/D). A prediction model yielded similar results as those obtained experimentally. However, it was shown that erosion effects and non-uniform burn rates along the axial length affect the overall ballistic performance and that the prediction model lacks these effects. The I-D model, in most part, overestimates the performance by omitting the 2D complexity of the problem.

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Keywords
Nozzleless boosters;Ducted rockets;Nozzleless rocket engines
Report Number
DREV-TR-2001-285 — Technical Report
Date of publication
01 May 2002
Number of Pages
49
DSTKIM No
CA020772
CANDIS No
517509
Format(s):
Document Image stored on Optical Disk

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