Accession Number : AD0602698

Title :   APPLICATION OF NEAR OPTIMUM GUIDANCE EQUATIONS OVER TWO BOOSTER PROPULSION STAGES OF ANY SPACE BOOSTER,

Corporate Author : AEROSPACE CORP EL SEGUNDO CALIF

Personal Author(s) : Perkins,F. M.

Report Date : 15 JUL 1964

Pagination or Media Count : 13

Abstract : The purpose of this document is to present additional equations that are necessary to simplify the application of the single pitch program across two thrust stages. These guidance equations could then be mechanized for explicit guidance during the guidance phase of the first stage and, in addition, for the entire second stage; or, alternatively, they could be used on a general-purpose computer before flight to determine the nominal optimum pitch-time equation that could then be flown open-loop up to the initiation of the final propulsive stage--which would then be flown closedloop, using the explicit solution obtained in AD-602 651. (Author)

Descriptors :   (*GUIDANCE, EQUATIONS), (*ASCENT TRAJECTORIES, OPTIMIZATION), (*BOOSTER ROCKETS, THRUST), SECOND-STAGE MOTORS, STAGING, GUIDED MISSILE TRAJECTORIES, PITCH (MOTION), COMMAND GUIDANCE, SPACE PROPULSION, FUEL CONSUMPTION, BALLISTICS, VACUUM, PROPELLANT BURN OUT

Distribution Statement : APPROVED FOR PUBLIC RELEASE