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Viewing 164041 to 164070 of 176058
1961-01-01
Technical Paper
610102
G. J. Pietrangeli, E. V. Nice
SUMMARY Trip time requirements between points on earth can be reduced by use of hypersonic aircraft if the range is sufficiently large so as to minimize the effect on average speed of the time of acceleration and deceleration. See Fig. 1. The objective of this study is to determine if it is technically feasible to use airbreathing propulsion systems to provide an intercontinental vehicle which will bring virtually all major cities of the world within two hours flying time of each other. An extensive study of various propulsion and performance aspects of a single-stage long range Mach 7 delta wing trans port, Fig. 2, 30,000 lb payload (125 passengers and cargo), has been completed. The study encompasses consideration of the propulsive performance of a hypersonic ramjet design featuring lift augmentation. Particular attention is given to the influence of geometry, equivalence ratio, diffuser recovery characteristics, and boundary layer bleed on this performance.
1961-01-01
Technical Paper
610103
R. C. Hawkins
1961-01-01
Technical Paper
610096
R. B. Brown
1961-01-01
Technical Paper
610097
E. D. Ranard, B. J. Davison
1961-01-01
Technical Paper
610099
David D. Kurtovich, George E. Hays
1961-01-01
Technical Paper
610098
F. W. Kolk
1961-01-01
Technical Paper
610092
Max F. Grandey, Edward H. Wehner
1961-01-01
Technical Paper
610095
Richard A. Houghton, Henry S. Beers
Future retrieval requirements for aircraft, missiles, and returning space vehicles have been matched against possible future retrieval systems to determine the most effective and flexible solution in terms of technical feasibility and economics. It has been found that primary vehicle requirements can be met using existing transport aircraft and a VTOL, possibly a retrieval adaptation of the planned Tri-Service VTOL transport. Great economies can be realized if “line” techniques for pick-up of objects by conventional aircraft in flight can be further developed. Long range amphibious aircraft and surface ships, some of the latter with hydrofoil capability, would provide the necessary versatility to meet the variety of future retrieval requirements.
1961-01-01
Technical Paper
610094
Helmut Hoeppner
1961-01-01
Technical Paper
610089
J. M. Smith, L. Washington
1961-01-01
Technical Paper
610090
G. W. Weber
1961-01-01
Technical Paper
610091
J. R. FULTZ
1961-01-01
Technical Paper
610084
W. A. Heacock
1961-01-01
Technical Paper
610085
Eugene O. Clay
1961-01-01
Technical Paper
610086
Allyn B. Hazard
1961-01-01
Technical Paper
610087
H. F. Glassner, L A. Tucker, L. R. Baessler
1961-01-01
Technical Paper
610081
J. J. Kaufman
1961-01-01
Technical Paper
610080
J. H. Beveridee, D. F. Vanica
1961-01-01
Technical Paper
610082
E. E. Roberts
1961-01-01
Technical Paper
610083
H. L. Woodlief, C . C . Mercier
1961-01-01
Technical Paper
610077
Harvey W. Fritz
1961-01-01
Technical Paper
610079
E. Z. ANDERSON
Abstract The performance characteristics of three booster configurations with a nuclear-powered upper stage designed to soft land on the moon are discussed. These booster configurations are the Saturn C-2, the Saturn C-2 with a solid-propellant booster stage, and the Saturn C-3. The nuclear stage thrust, specific impulse, and propellant loading were varied parametrically for the Saturn C-3 configuration. The engine for the nuclear stage was based on the KIWI-type reactor using liquid hydrogen as a working fluid. The payload capabilities for all three configurations were determined for the case of a chemical stage carried in the payload being used for landing on the moon and for the return trip to an earth orbit. For the Saturn C-3 configuration, two other methods were studied for landing on the moon and returning to an earth orbit.
1961-01-01
Technical Paper
610078
Michel E. Maes
1961-01-01
Technical Paper
610074
Burke B. Cochran
1961-01-01
Technical Paper
610072
Kenneth L. Wadlin, Joseph N. Kotanchik
1961-01-01
Technical Paper
610073
B. E. Farwell, R. S. Carey, D. E. Deutsch

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