The performance characteristics and mission capabilities of the nuclear rocket engine.
Nuclear rocket engine design for near-optimum vehicle performance for mission capability
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Nuclear rocket engine design for near-optimum vehicle performance for mission capability
Rocket measurement of quiet D-region electron number density profiles near sunrise
Maksutov-Cassegrain type telescope for rocket mounting, design and performance
Upper ionospheric electron density measurement by signals propagated between two parts of high altitude rocket
Silicon semiconductor combustion pressure transducer for high temperature HF pressure measurements within liquid rocket motor chambers
Rocket observations of lowest ionosphere at sunrise and sunset
Directional neutron detector using liquid scintillator for low mev energy range for rocket and satellite experiments
Short duration technique providing simulation of thermodynamic properties and composition of exhaust products of liquid and solid propellant rocket engines
Rocket and balloon-borne exposure study of terrestrial microorganism survival in space
Rocket nozzle effect on acoustic losses from model motor chambers oscillating in first longitudinal mode
Prediction of large rocket nozzle material performance using semiempirical technique, noting mathematical models for internal and external heat and mass transfer
Third 260-inch diameter solid propellant rocket engine test firing
Rocket observations of energy spectra of auroral electrons
Simultaneous recording of rocket trajectory and rapid auroral variations using high sensitivity image orthicon TV system
Mathematical model for thermal and chemi- ionization processes in turbulent nonequilibrium afterburning rocket exhausts plume, studying neutral and charged species distribution
Rocket engine turbopump assembly test capability design, facilities, cryogenic systems, control requirements, computer simulation, activation and checkout
Recirculation zone in fluid mechanics experiments on cylindrical cavity simulating gas-core nuclear rocket as heavy gas reservoir, discussing flow patterns
MIRA 150A variable thrust rocket engine applied to manned lunar exploration flying systems