Solid Propellant Admittance Measurements by the Driven Tube Method.
Abstract
A driven tube burner has been developed and tested under both cold and hot flow conditions. The cold flow tests provided a check on the proper operation of the facility and the data reduction scheme. Temperature measurements of the gas inside the burner tube, taken during the burning of a solid propellant sample, indicate the presence of axial and radial temperature gradients in the burner. The effect of these gradients upon the quality of the measured admittance data is under investigation. Preliminary hot tests conducted to date confirmed the proper operation of the facility and its ability to provide good pressure amplitude and phase data. These data are now being used to compute the desired solid propellant admittances. In the analytical phase of this program, a most promising analytical technique for the determination of both the admittance and entropy perturbation at the propellant burning surface, from dynamic pressure and steady temperature measurements, has been developed. Also, the effect of the steady state temperature gradients upon the wave structure inside the burner tube has been investigated analytically.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1974
- Accession Number
- ADA004537
Entities
People
- A. Bell
- M. Salikuddin
- R. Daniel
- T. Zinn
Organizations
- Georgia Tech