Experimental titanium crossbeam manufacturing technology Final report, 1 Jul. 1964 - 30 Oct. 1965
Titanium sine wave beam concept for Saturn V launch vehicle
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Titanium sine wave beam concept for Saturn V launch vehicle
Bending effects on pilot control of simulated flexible Saturn V launch vehicle
Orbital space station design for permanent residence within earth-orbital payload capacity of Saturn V launch vehicle
Nose fairing cone shape effect on Saturn V launch vehicle performance
Piloted simulation of manual guidance techniques for upper stages of Saturn V launch vehicle
Integral sensor telemetry system for factory-stage checkout of Saturn-type launch vehicle
Qualification testing of polyurethane elastomeric material for Saturn IB and Saturn V launch vehicles
Apollo Saturn-204/LM-1 launch vehicle operational flight trajectory
Trajectory and dynamics analyses of Saturn 1B launch vehicle for Apollo-Saturn 205/CSM-101 mission
Saturn/Centaur launch windows for orbits synchronous with lunar period
Root mean square fluctuating buffet pressures for Mercury/Atlas and Apollo/Saturn configurations correlated with Mach number, angle of attack, and streamwise location
Structural dynamics of Saturn I and Saturn V dynamic models - effect of ground wind on launch vehicles
Simulation investigation of loads incurred during first stage piloted flight of Saturn V launch vehicle encountering measured winds
Flight evaluation of vehicle bending data for saturn i launch vehicle - structural vibration, dynamic response
Application of integral sensor transmitters to factory stage checkout of Saturn type vehicle
Manufacture engineer role in producing space vehicles, noting S-IC stage of Saturn V launch vehicle
NASA's Global Exploration Strategy requires safe, reliable, robust, efficient transportation to support sustainable operations from Earth to orbit and into the far reaches of the solar system. NASA selected the Ares I crew launch vehicle and the Ares V cargo launch vehicle to provide that transportation. Guiding principles in creating the architecture represented by the Ares vehicles were the maximum use of heritage hardware and legacy knowledge, particularly Space Shuttle assets, and commonality between the Ares vehicles where possible to streamline the hardware development approach and reduce programmatic, technical, and budget risks. The J-2X exemplifies those goals. It was selected by the Exploration Systems Architecture Study (ESAS) as the upper stage propulsion for the Ares I Upper Stage and the Ares V Earth Departure Stage (EDS). The J-2X is an evolved version ofthe historic J-2 engine that successfully powered the second stage of the Saturn I launch vehicle and the second and third stages of the Saturn V launch vehicle. The Constellation architecture, however, requires performance greater than its predecessor. The new architecture calls for larger payloads delivered to the Moon and demands greater loss of mission reliability and numerous other requirements associated with human rating that were not applied to the original J-2. As a result, the J-2X must operate at much higher temperatures, pressures, and flow rates than the heritage J-2, making it one of the highest performing gas generator cycle engines ever built, approaching the efficiency of more complex stage combustion engines. Development is focused on early risk mitigation, component and subassembly test, and engine system test. The development plans include testing engine components, including the subscale injector, main igniter, powerpack assembly (turbopumps, gas generator and associated ducting and structural mounts), full-scale gas generator, valves, and control software with hardware-in-the-loop. Testing expanded in 2007, accompanied by the refinement of the design through several key milestones. This paper discusses those 2007 tests and milestones, as well as updates key developments in 2008.
Radio interference from Saturn V launch vehicle fluorescent work lamps