Protection against malfunctions in flight control system is provided by redundant flight control system with automatic and manual switchover provisions from primary to secondary system; malfunctions of other vital systems of launch vehicle require abort, and manually initiated crew escape means are provided; operation of flight control switchover mechanism for several classes of malfunctions, and criteria developed for judging conditions under which switchover can be accomplished; on-board and ground warning displays for nonflight control malfunctions and time sequence of escape events for critical malfunction.
Malfunction protection in gemini launch vehicle
Symposium Ballistic Missile Space Technology -- Trans
8th Symposium on Ballistic Missile and Space Technology ; 1963 Reliability
1963
45 pages
Conference paper
English
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NTRS | 1964
|Gemini Launch Vehicle Development
NTRS | 1966
|Development of launch vehicle malfunction effects model
TIBKAT | 1965