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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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Experimental investigation of engine dynamics and controls for 48-inch ramjet engine in free jet facility at Mach number 2.76 and altitudes 68,000 to 82,000 feet
The Laser Interferometer Space Antenna (LISA) is a joint NASA/ESA mission to detect and measure gravitational waves with periods from 1 s to 10000 s. The systems engineering challenges of developing a giant interferometer, 5 million kilometers on a side, an: numerous. Some of the key challenges are presented in this paper. The organizational challenges imposed by sharing the engineering function between three centers (ESA ESTEC, NASA GSFC, and JPL) across nine time zones are addressed. The issues and approaches to allocation of the acceleration noise and measurement sensitivity budget terms across a traditionally decomposed system are discussed. Additionally, using LISA to detect gravitational waves for the first time presents significant data analysis challenges, many of which drive the project system design. The approach to understanding the implications of science data analysis on the system is also addressed.
Engine-integrated secondary injection side-force generation for hydrogen-fueled rocket engine
High lift characteristics of variable-sweep transport model with blended engine-fuselage and engine-mounted horizontal tails
Low-speed characteristics of variable-sweep supersonic transport model with blended engine fuselage and engine-mounted tails
Surveys of engineering school needs in field of biomechanical and human factors engineering education
Computer and engine performance study of jet engine generalized parameter fuel control
Thermodynamic performance test analyses for Apollo spacecraft ascent, descent, and service propulsion system engines to define hypergol engine restart limits
Cold flow and hot firing test details for Apollo spacecraft ascent, descent, and service propulsion system engines to define hypergol engine restart limits
Fluid mechanics and engine dynamics and start-up experiments simulating thermal environment in nuclear light bulb engine
Coupled supersonic inlet-engine control using overboard bypass doors and engine speed to control normal shock position
Validating gas generator method of calculating jet engine thrust, and evaluation of XB-70-1 engine performance at ground static conditions
Engineering methods for predicting temperatures and velocities in vicinity of vertical lift engines of jet V/STOL aircraft operating near ground
Effects of engine inlet disturbances on engine stall performance
Supersonic inlet engine control using engine speed as primary variable for controlling normal shock position
Turbofan engine designs and tests for engine noise reduction
Low pressure turbofan rotor, stator, frame, and exhaust nozzle designs for turbofan engine noise reduction including acoustics and engine tests
A preliminary design study of a conceptual 6000-MW open-cycle gas-core nuclear rocket engine system was made. The engine has a thrust of 44,200 lb and a specific impulse of 4400 sec. The nuclear fuel is uranium-235 and the propellant is hydrogen. Critical fuel mass was calculated for several reactor configurations. Major components of the reactor (reflector, pressure vessel) and the waste heat rejection system were considered conceptually and were sized.