Accession Number:

AD0261589

Title:

COMPARISON OF SOLID PROPELLANT BURNING RATES IN STRANDS AND ROCKET MOTORS

Descriptive Note:

Corporate Author:

PRINCETON UNIV NJ

Personal Author(s):

Report Date:

1961-05-01

Pagination or Media Count:

102.0

Abstract:

The burning rate of a composite, solid propellant in a rocket motor was compared with results of research on the burning rate of a strand of composite, solid propellant which led to a theoretical burning rate law. The role of radiative energy feedback to the propellant surface was of special interest. A rocket motor incorporating interchangeable grains, and interchangeable nozzles, which allowed progressive burning between various pressure levels, was developed. In general, the burning rate in the rocket motor at any specified pressure was less than that of a strand burning at the same pressure. The energy feedback due to the presence of radiative heat flux, and its effect on the burning rate in a rocket motor, was investigated. In particular, the radiation flux from the central gas column incident upon the propellant surface was theoretically computed. Preliminary experimental results showed the radiation flux from the hot gas column to the propellant surface to be approximately twice that received from the flame zone.

Subject Categories:

  • Solid Propellant Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE