CONTINUOUS MEASUREMENT OF SOLID PROPELLANT BURNING RATES
Abstract
The basic operating principles of an experimental system for the direct and continuous measurement of solid propellant burning rates are presented. The system was designed and fabricated. A continuous burning rate measurement technique, termed the Servo-mechanism Technique, will be employed for obtaining erosive burning rate data for types BDI and BUU double-base propellants. A feasibility study was conducted for determining the adaptability of microwave techniques to the measurement of the burning rate of a solid propellant. It was concluded, because of the dependence of the microwave attenuation upon the combustion conditions present in a research rocket motor, that microwave techniques are not readily adaptable to such burning rate measurements. A feasibility study indicates that a technique employing ultrasonic pulses can be developed for obtaining direct measurements of the burning rate of a solid propellant. The technique is based on measuring the time for an ultrasonic pulse to travel through a propellant sample.
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1965
- Accession Number
- AD0616098
Entities
People
- J .r. Osborn
- P. Y. Ho
- R. J. Burick
Organizations
- Purdue University