Accession Number : AD0742253
Title : Development of a Rocket Motor Burn Rate Measurement System.
Descriptive Note : Final rept. 15 Jul 70-14 Apr 71,
Corporate Author : HERCULES INC CUMBERLAND MD ALLEGANY BALLISTICS LAB
Personal Author(s) : Schuemann,W. C. ; Zajdel,L. S. ; Rice,J. H.
Report Date : OCT 1971
Pagination or Media Count : 106
Abstract : The technique chosen to develop into a microwave burn rate sensor was that of the microwave interferometer. Microwave engery is beamed through a 'window' in the rocket motor case and into the propellant. At the burning propellant surface, this microwave energy is reflected and beamed back through the 'window' to a detector system. At this detector system, the combination of transmitted and reflected energy produces a standing wave of energy which is monitored by the detectors. As the burning surface moves, the standing wave will also move a proportional amount. Thus, by monitoring the motion of the standing wave, the motion of the burning surface is obtained. (Author)
Descriptors : (*SOLID ROCKET PROPELLANTS, *BURNING RATE), MEASUREMENT, MICROWAVE EQUIPMENT, INTERFEROMETERS, THERMAL ANALYSIS, WAVEGUIDE WINDOWS, CAPTIVE TESTS, TEST METHODS
Subject Categories : Combustion and Ignition
Solid Rocket Propellants
Distribution Statement : APPROVED FOR PUBLIC RELEASE