Accession Number : ADA307603
Title : Flight-Test Temperature Data for an Altair-IIC1 Rocket Motor.
Descriptive Note : Technical note,
Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY RESEARCH CEN TER
Personal Author(s) : Rapter, James L.
PDF Url : ADA307603
Report Date : AUG 1965
Pagination or Media Count : 29
Abstract : Comparison of chamber wall temperatures obtained from flight data and static tests at altitude shows some differences. The flight data indicate maximum chamber wall temperatures of 800 F as compared with maximum temperatures of 400 F for static tests on the chamber wall at simulated altitude. Comparison of static data for a foil wrapped and a nonwrapped chamber indicates foil wrapping causes an increase in temperature from 400 F to 700 F. Flight temperatures are sufficiently high to cause epoxy resin boiloff, charring of the chamber wall, and resultant loss of chamber structural strength.
Descriptors : *SOLID PROPELLANT ROCKET ENGINES, *THERMAL STRESSES, SIMULATION, FLIGHT TESTING, TEMPERATURE, STRUCTURAL PROPERTIES, STRENGTH(MECHANICS), WALLS, EPOXY RESINS, CHAMBERS, STATIC TESTS, CHARRING, BOILOFF.
Subject Categories : Solid Propellant Rocket Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE