Accession Number : AD0801119
Title : PEGASUS STRUCTURAL TEST. NOSE CONE SEPARATION - PITCH ROCKET COVER EJECTION,
Corporate Author : LOCKHEED MISSILES AND SPACE CO INC SUNNYVALE CA
Personal Author(s) : Konle, W. R.
Report Date : 24 APR 1961
Pagination or Media Count : 4
Abstract : The effect of the Thiokol TX7-1 rocket motors on the pitch rocket cover and the nose cone - heat shield separation was evaluated. The pitch rocket cover test indicated that the Thiokol rocket exhaust was adequate to effectively jettison the pitch rocket cover. The nose cone - heat shield test proved that the Thiokol rocket motors provided sufficient thrust and that the angular mounting of the motors gave sufficient lateral displacement to the nose cone to move it out of the programed flight path of the capsule.
Descriptors : (*SOLID PROPELLANT ROCKET ENGINES, STRUCTURAL PROPERTIES), (*HYPERSONIC TEST VEHICLES, STRUCTURAL PROPERTIES), ROCKET COMPONENTS, ROCKET NOSES, NOSE CONES, HEAT SHIELDS, SEPARATION, EJECTION, STAGING, ROCKET TRAJECTORIES, ROCKETS, CAPTIVE TESTS, PERFORMANCE(ENGINEERING).
Subject Categories : Research and Experimental Aircraft
Solid Propellant Rocket Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE