CONTINUOUS MEASUREMENT OF THE BURNING RATES OF SOLID ROCKET PROPELLANTS.
PURDUE UNIV LAFAYETTE IND JET PROPULSION CENTER
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An experimental system for the direct and continuous measurement of solid rocket propellant burning rates was developed. A sample of solid propellant is bonded to a holder with an attached shaft which moves the propellant sample within a two-dimensional rocket motor. The flat burning surface of the propellant sample recedes normally as a servomechanism moves the propellant in a direction opposite to the receding propellant surface. The servomechanism operates in such a manner that the burning propellant surface is maintained at a fixed position within the rocket motor. Since the burning surface of the propellant remains fixed, the direct measurement of the velocity of the shaft yields the burning rate. The servomechanism incorporates a radioactive isotope feedback transducer system for detecting the position of the burning surface of the propellant sample. A collimated beam of gamma rays, provided by a 50 millicurie source of Cesium137, is transmitted through the rocket motor walls and is transformed into an electrical feedback signal by a scintillation probe coupled with a linear ratemeter. Author