Flight control system is rate plus position multirate sampled-data control system; missile can be launched on moment's notice; control of Minuteman I is achieved by vectoring four nozzles on each of three stages; Minuteman II is controlled by vectoring four nozzles on each of stages one and three and by injecting liquid into exhaust stream of stage two; to control thrust vector throughout boost, control system uses digital computer angular accelerometer, three thrust vector control units, and three digital resolvers. SAE -- Paper 650598.
Functional design of minuteman flight control system
SAE-NASA -- Aerospace Vehicle Flight Control Conference -- Proc
Proceedings of the SAE-NASA -- Aerospace Vehicle Flight Control Conference ; 1965 Control
1965
10 pages
Aufsatz (Konferenz)
Englisch
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Engineering Index Backfile | 1963
|Boundary-layer transition from Minuteman flight tests.
AIAA | 1968
|Minuteman missile transportation system
Engineering Index Backfile | 1961
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