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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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Analyzing emergency deceleration and descent of XB-70-1 airplane due to engine damage resulting from structural failure for supersonic transport data
Inapplicability of Baldwin correlation for determining causes of lunar crater emergence
Concepts for improving probability of human survival in aircraft emergency conditions
Data compilation for aircraft design improvement to enhance human survival in emergencies
Comparison of calculated and measured fast-neutron fluxes emerging from HB-6 beamhole of Plum Brook reactor
Hypothetical emergence mechanism of lunar maria
Space emergency reentry vehicle - NASA Faculty Systems Engineering Institute Conference, University of Houston, June-August 1967
Radiological control procedures for transportation, handling, and storage of SNAP 27 thermoelectric generator in radiological emergencies
Human survival in flight emergencies involving commercial and general aviation aircraft
Emergency evaporative coolant liquid cooled garment system
Aerial capsule emergency separation device using jettisonable towers
Design and specifications of emergency escape system for spacecraft structures
Evaluation of storable propellants as sources of H2, O2, potable H2O, and heat for use in emergency life support system
Emergency surface decompression and treatment procedures for project Tektite aquanauts, determining safe interval and schedules for return to habitat on ocean floor
A fixed-base piloted simulator investigation has been made of the feasibility of using any of several manual guidance and control techniques for emergency lunar escape to orbit with very simplified, lightweight vehicle systems. The escape-to-orbit vehicles accommodate two men, but one man performs all of the guidance and control functions. Three basic attitude-control modes and four manually executed trajectory-guidance schemes were used successfully during approximately 125 simulated flights under a variety of conditions. These conditions included thrust misalinement, uneven propellant drain, and a vehicle moment-of-inertia range of 250 to 12,000 slugs per square foot. Two types of results are presented - orbit characteristics and pilot ratings of vehicle handling qualities.
A thermally insulative inflatable garment designed specifically as a lightweight low storage volume emergency suit for subzero weather survival is reported. Testing confirms that the inflatable suit design satisfies the objectives for a subject standing at rest with environmental temperatures down to -450 F if the garment is inflated with Freon.