Accession Number : AD0821304
Title : FEASIBILITY DEMONSTRATION OF A ROCKET ENGINE ABLATION GAUGE.
Descriptive Note : Final rept. Nov 66-May 67 on Task 3,
Corporate Author : TRW SYSTEMS GROUP REDONDO BEACH CA
Personal Author(s) : Harman, Randall W.
Report Date : OCT 1967
Pagination or Media Count : 82
Abstract : The gauging technique employs trace quantities of two radioactive compounds embedded in the nozzle at selected locations. The compounds are selected so that one ablates and the other erodes in the same manner as the adjacent nozzle material. Recession depths are determined by measuring the decrease in radiation intensity external to the nozzle shell. A carbon phenolic MX4926, is the nozzle material used in this program. Equipment was fabricated, assembled, and tested to demonstrate the gauging technique on a rocket engine. Instrumentation and hardware were provided to gauge concurrent erosion and ablation at up to six locations about the rocket nozzle. Recession sensor needles were molded from mascerated carbon fabric and phenolic resin and embedded in the nozzles. Gauging feasibility was demonstrated during engine tests with needles having radiotracer additives.
Descriptors : (*ROCKET NOZZLES, ABLATION), CAPTIVE TESTS, LIQUID PROPELLANT ROCKET ENGINES, CONVERGENT DIVERGENT NOZZLES, EROSION, PYROLYSIS, MEASURING INSTRUMENTS, DETECTORS, FEASIBILITY STUDIES, RADIATION MEASURING INSTRUMENTS, DETECTORS, CARBON COMPOUNDS, PHENOLIC PLASTICS, RADIOACTIVE ISOTOPES, TRACER STUDIES, TIN, INDIUM COMPOUNDS, CHLORIDES, SCANDIUM COMPOUNDS, OXIDES.
Subject Categories : Liquid Propellant Rocket Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE