Solid propellant launch vehicle, Little Joe II, applied for flight testing launch escape system of Apollo space vehicle; components were combined into nonrecirculating hydraulic systems mounted on four missile fins; vehicle attitude is controlled with aerodynamic control surface on each of four fins; each control surface is powered by its own separate hydraulic system located within and on each fin; each complete fin system may be operated separately or four fins may be operated simultaneously by autopilot system; each complete fin is replaceable if hydraulic system malfunctions during vehicle checkout.
Nitrogen powers Little Joe's open hydraulic system
Hydraulics Pneumatics
Hydraulics and Pneumatics ; 19 , n 7
1966
5 pages
Aufsatz (Zeitschrift)
Englisch
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