Accession Number : ADA299084
Title : Launch Vehicle Abort Source Strength Model-Propellant Interaction Study.
Descriptive Note : Final technical rept. 10 Oct 92-10 May 93,
Corporate Author : MARTIN MARIETTA ASTRONAUTICS GROUP DENVER CO
Personal Author(s) : Prince, Stephen P.
PDF Url : ADA299084
Report Date : 13 MAR 1995
Pagination or Media Count : 103
Abstract : A series of tests involving the combustion of solid and liquid rocket propellants used to fuel the Titan II, Titan IV and Delta II launch vehicles was performed. The purpose of these tests was to obtain chemical combustion data to support modeling of launch vehicle accidents. Propellants tested were Aerozine-5O, dinitrogen tetroxide, RP- 1, liquid oxygen, PBAN, and Castor IVA. Tests were conducted in a 150-liter stainless steel combustion chamber in air at nominal pressure (0.8 atmospheres at Denver barometric conditions). Measurements of the chamber gas temperature and internal pressure were taken and gas samples were withdrawn and analyzed for combustion gases, unreacted propellants, unreacted oxygen and organic vapors. A witness plate was used to collect condensed residues. Results from these tests suggest different chemical fates of these propellants than those predicted by theory alone.
Descriptors : *GUIDED MISSILE LAUNCHERS, *COMBUSTION, *STRENGTH(GENERAL), *LIQUID ROCKET PROPELLANTS, *SOLID ROCKET PROPELLANTS, TEST AND EVALUATION, TEMPERATURE, MODELS, VAPORS, GASES, OXYGEN, CHEMISTRY, FUELS, SAMPLING, BAROMETRIC PRESSURE, NITROGEN OXIDES, CHAMBERS, LIQUID OXYGEN, INTERNAL PRESSURE, ACCIDENTS, TETROXIDES, COMBUSTION PRODUCTS.
Subject Categories : Guided Missile Launching and Basing Support
Liquid Rocket Propellants
Solid Rocket Propellants
Distribution Statement : APPROVED FOR PUBLIC RELEASE