Accession Number:

AD0483646

Title:

TECHNIQUES FOR THE CONTINUOUS MEASUREMENT OF SOLID PROPELLANT BURNING RATES.

Descriptive Note:

Final rept.,

Corporate Author:

PURDUE UNIV LAFAYETTE IN JET PROPULSION CENTER

Personal Author(s):

• Osborn, J. R.
• Burick, R. J.
• Ho, P. Y.

Report Date:

1966-02-01

Pagination or Media Count:

29.0

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

Descriptors:

• (*SOLID ROCKET PROPELLANTS
• BURNING RATE)
• (*SERVOMECHANISMS
• MEASURING INSTRUMENTS)
• TRANSDUCERS
• RADIOACTIVE ISOTOPES
• ULTRASONIC RADIATION
• INSTRUMENTATION
• SOLID PROPELLANT ROCKET ENGINES
• VELOCITY
• FEEDBACK
• MICROWAVE EQUIPMENT
• DIELECTRIC AMPLIFIERS
• COMBUSTION CHAMBERS
• DISTORTION
• GAMMA RAYS
• AMPLIFIERS
• EXPERIMENTAL DATA
• PRESSURE
• CALIBRATION
• POSITIONING DEVICES(MACHINERY)
• COBALT

Subject Categories:

• Solid Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE