TECHNIQUES FOR THE CONTINUOUS MEASUREMENT OF SOLID PROPELLANT BURNING RATES.
Abstract
The subject report summarizes the results of a two-year program to develop a technique for the direct and continuous measurement of the burning rate of solid rocket propellants under simulated motor conditions. The technique involves a closed loop servomechanism which positions a solid propellant sample within a two-dimensional combustion chamber. In order to provide a feedback signal to the servomechanism three different transducer systems were investigated; (1) a microwave technique, (2) ultrasonic techniques, and (3) a radioactive isotope system. The most promising of the aforementioned transducer systems, the radioactive isotope system, was developed for determining the relative position of the burning surface of a sample of solid propellant. The subject measurement technique is currently being utilized in an investigation to determine the erosive burning rate characteristics of cast double-base propellants. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1966
- Accession Number
- AD0483646
Entities
People
- J .r. Osborn
- P. Y. Ho
- R. J. Burick
Organizations
- Purdue University