Accession Number:

ADA109058

Title:

Determination of the Combustion Mechanisms of Aluminized Propellants

Descriptive Note:

Annual rept. 1 Oct 80-30 Sep 81

Corporate Author:

PURDUE UNIV LAFAYETTE IN SCHOOL OF AERONAUTICS AND ASTRONAUTICS

Report Date:

1981-10-26

Pagination or Media Count:

11.0

Abstract:

This research project is concerned with determining the mechanisms governing the formation and combustion of metalagglomeratemetal oxide particles throughout the solid rocket motor, that is, surfacenear surface, cavity, and nozzle regions. Also of concern is the influence these particles have on propellant combustion characteristics and motor performance. The efforts of this past year were directed toward developing the experimental equipment needed for determining particle size distributions at and near the propellant surface. A solid propellant strand window bomb with a servo controlled positioning device was constructed and operated. Also, the interface of this equipment with data recording and reduction equipment was accomplished. The laser imaging device to be used to measure particle size distributions is undergoing calibration tests. Author

Subject Categories:

  • Combustion and Ignition
  • Solid Propellant Rocket Engines
  • Solid Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE