Accession Number : AD0511037
Title : Advanced Maneuvering Propulsion System (Lockheed Propellant Feed System Design). Volume II -- Propulsion Stage System Design.
Descriptive Note : Final rept. 1 Dec 67-31 Dec 69.
Corporate Author : ROCKETDYNE CANOGA PARK CALIF
Report Date : SEP 1970
Pagination or Media Count : 314
Abstract : This volume provides the details of the selected propellant feed system design. The recommended configuration, consisting of a 1.41 ellipsoidal oxidizer tank, a 1.41 ellipsoidal fuel tank with a short cylindrical section and a conical/cylindrical shell has a mass fraction of 0.854, a dry weight of 2028 lb and a delta V capability of 20,197 to 21,765 ft/sec (with a 2000 lb payload) which varied over this range depending on the duty cycle and thrust level used. With prior knowledge of the duty cycle to be performed, i.e. if the mission is known after achieving orbit, the delta V capability rises to 22,800 ft/sec with the same payload weight. Extended mission capability to 180 days is also presented. A summary of the design, assembly plans, performance data and reliability data are given followed by design details, structural analyses and manufacturing plans for each selected vehicle subsystem.
Descriptors : (*LIQUID PROPELLANT ROCKET ENGINES, PROPELLANT CONTROL), STRESSES, PROPELLANT TANKS, SLOSHING, INTERFACES, MISSION PROFILES, PURGING, THERMAL INSULATION, DESIGN, RELIABILITY, VENTS, STRUCTURAL PROPERTIES, ASSEMBLY, PNEUMATIC DEVICES, MANUFACTURING, LAUNCHING, PRESSURIZATION, BAFFLES, SHELLS(STRUCTURAL FORMS) (U) *CONTROLLABLE-THRUST ROCKET MOTORS, *CRYOGENIC PROPELLANTS, LIQUEFIED GASES, FLUORINE, HYDROGEN, ADVANCED WEAPONS, HELIUM, MANEUVERING SATELLITES, ACCELERATION, PAYLOAD, LIFE EXPECTANCY, HAZARDS, ELLIPSOIDS, STARTING, MANEUVERABILITY, DETECTORS, POLAR ORBIT TRAJECTORIES, ASCENT TRAJECTORIES, ATTITUDE CONTROL SYSTEMS, THRUST VECTOR CONTROL SYSTEMS
Subject Categories : Liquid Propellant Rocket Engines
Liquid Rocket Propellants
Distribution Statement : APPROVED FOR PUBLIC RELEASE