Accession Number:

AD0736049

Title:

The Response of a Burning Solid Propellant Surface to Thermal Radiation

Descriptive Note:

Technical rept.,

Corporate Author:

UTAH UNIV SALT LAKE CITY DEPT OF CHEMICAL ENGINEERING

Report Date:

1971-08-01

Pagination or Media Count:

167.0

Abstract:

A new technique for the study of processes related to propellant combustion instability has been employed in which burning rate variations produced by a periodic radiant heat flux are measured. The phase angle between the perturbing flux and the burning rate response and the dependence of the magnitude of the response on the driving frequency are obtained. As the frequency of the perturbing flux increases, magnitude of the reaction is observed to first increase and then to pass through a maximum. In general, the experimental results tend to confirm the theoretical models for transient burning rate response, although the observed maximums in the response functions appear to occur at higher frequencies than is predicted by the simpler gas-phase models. Author

Subject Categories:

  • Combustion and Ignition
  • Solid Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE