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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Passive instrumentation and stimuli generation for Saturn IB equipment checkout - nondestructive testing
Liquid hydrogen fluid mechanics low-gravity problems of Saturn V/S-IVB and control measures
Design considerations of central programmer, common address, and data return bus
Feasibility of hydrogen gas leak detector for use on in-flight experiments to be conducted with Saturn IB
Function and strength testing of liquid hydrogen metal flex hose for service module fuel cell of Saturn IB program
Diffusion bonding of titanium sandwich structure for Saturn tank wall application
No abstract available
The J-2X Upper Stage Engine (USE) will be the first new human-rated upper stage engine since the Apollo program of the 1960s. It is designed to carry the Ares I and Ares V into orbit and send the Ares V to the Moon as part of NASA's Constellation Program. This paper will provide an overview of progress on the design, testing, and manufacturing of this new engine in 2009 and 2010. The J-2X embodies the program goals of basing the design on proven technology and experience and seeking commonality between the Ares vehicles as a way to minimize risk, shorten development times, and live within current budget constraints. It is based on the proven J-2 engine used on the Saturn IB and Saturn V launch vehicles. The prime contractor for the J-2X is Pratt & Whitney Rocketdyne (PWR), which is under a design, development, test, and engineering (DDT&E) contract covering the period from June 2006 through September 2014. For Ares I, the J-2X will provide engine start at approximately 190,000 feet, operate roughly 500 seconds, and shut down. For Ares V, the J-2X will start at roughly 190,000 feet to place the Earth departure stage (EDS) in orbit, shut down and loiter for up to five days, re-start on command and operate for roughly 300 seconds at its secondary power level to perform trans lunar injection (TLI), followed by final engine shutdown. The J-2X development effort focuses on four key areas: early risk mitigation, design risk mitigation, component and subassembly testing, and engine system testing. Following that plan, the J-2X successfully completed its critical design review (CDR) in 2008, and it has made significant progress in 2009 and 2010 in moving from the drawing board to the machine shop and test stand. Post-CDR manufacturing is well under way, including PWR in-house and vendor hardware. In addition, a wide range of component and sub-component tests have been completed, and more component tests are planned. Testing includes heritage powerpack, turbopump inducer water flow, turbine air flow, turbopump seal testing, main injector and gas generator, injector testing, augmented spark igniter testing, nozzle side loads cold flow testing, nozzle extension film cooling flow testing, control system testing with hardware in the loop, and nozzle extension emissivity coating tests. In parallel with hardware manufacturing, work is progressing on the new A-3 test stand to support full duration altitude testing. The Stennis A-2 test stand is scheduled to be turned over to the Constellation Program in September 2010 to be modified for J-2X testing also. As the structural steel was rising on the A-3 stand, work was under way in the nearby E complex on the chemical steam generator and subscale diffuser concepts to be used to evacuate the A-3 test cell and simulate altitude conditions.
Summary of activities and operations in development of Saturn I, Saturn IB, and Saturn V launch vehicles
Qualification testing of polyurethane elastomeric material for Saturn IB and Saturn V launch vehicles
In the sixties, Chrysler was NASA's prime contractor for the Saturn I and IB test launch vehicles. The company installed and operated at Huntsville what was known as the Saturn I/IB Development Breadboard Facility. "Breadboard," means an array of electrical and electronic equipment for performing a variety of development and test functions. This work gave Chrysler a broad capability in computerized testing to assure quality control in development of solid-state electronic systems. Today that division is manufacturing many products not destined for NASA, most of them being associated with the company's automotive line. A major project is production and quality-control testing of the "lean-burn" engine, one that has a built-in Computer to control emission timing, and allow the engine to run on a leaner mixture of fuel and air. Other environment-related products include vehicle emission analyzers. The newest of the line is an accurate, portable solid state instrument for testing auto exhaust gases. The exhaust analyzers, now being produced for company dealers and for service
Saturn I, IB, and V launch vehicle progress - second stage launching, static test failure, fabrication progress, and fuel tank hydrostatic pressure test
Checkout and launch operations for the four Skylab flights, plus checkout for a fifth vehicle on rescue status during the last mission, were complex and demanding. Preparations began well before the launch of the last Apollo moon mission in December 1972, and had to be performed without interference with the ongoing program. Three major new flight modules were used in Skylab, each of which imposed specific requirements on Kennedy Space Center. A major facilities modification program resulted in the ability to launch the three Saturn IB Skylab vehicles from Saturn V facilities. This provided large cost savings, but imposed the usual problems caused by first-time use of a new system.
Acceptance test firing of Saturn flight stage S-IB-2
Testing and evaluation of 2-inch duo-check valve for Saturn IB program
Payload capabilities of Saturn IB-Centaur for launch opportunities to Mars in 1971, 1973, and 1975 and to Venus in 1972 and 1973
Engineers at MSFC designed, developed, and tested propulsion systems that helped launch Saturn I, IB, and V boosters for the Apollo missions. After the Apollo program, Marshall was responsible for the design and development of the propulsion elements for the Shuttle launch vehicle, including the solid rocket boosters, external tank and main engines. Each of these systems offered new propulsion technological challenges that pushed engineers and administrators beyond Saturn. The technical challenges presented by the development of each of these propulsion systems helped to establish and sustain a culture of engineering conservatism and was often accompanied by a deep level of penetration into contractors that worked on these systems.
Stress analysis for determining structural reliability of weight optimized mounting panel for Saturn launch vehicles