Solid Propellant Admittance Measurements by the Driven Tube Method.
Interim scientific rept. Jun 74-Jul 75,
GEORGIA INST OF TECH ATLANTA SCHOOL OF AEROSPACE ENGINEERING
Pagination or Media Count:
Progress made during the second year of an investigation on the application of the impedance tube technique in the measurement of the response function of a burning solid propellant, subjected to oscillating flow conditions, is described in this report. Modifications to the originally proposed measurement technique are outlined and the admittances of a number of different solid propellants measured at low pressures and over frequency ranges of interest in solid propellant instability are presented. Also discussed in this report are the results of analytical studies concerned with 1 determination of the behavior of a standing wave in a tube containing a steady flow and a steady temperature gradient 2 the dependence of the standing wave structure upon the boundary condition at the propellant surface and the characteristics of the steady axial temperature profile in the burner tube 3 the use of acoustic pressure data in the determination of the propellant response factor and 4 the development of a non-linear regression technique for the improvement of the accuracy of the measured propellant response factor. Finally, the measured low pressure propellant response factor data is analyzed and its possible dependence upon particle gas phase attenuation and the propellant self-driving is discussed. Author
- Combustion and Ignition
- Solid Rocket Propellants