Site accessibility and characteristic velocity requirements for direct-descent lunar landings

A direct descent is one in which the main descent propulsion system burns continuously from lunar approach to touchdown. The characteristic velocity requirement for direct lunar descents is presented as a function of the landing site location relative to the normal impact point. Results are included...

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Bibliographic Details
Main Author: Weyers, Vernon J
Corporate Authors: United States National Aeronautics and Space Administration, Lewis Research Center
Format: Government Document Book
Language:English
Published: Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce], [1970]
Series:NASA technical note ; D-5923
Subjects:
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100 1 |a Weyers, Vernon J  |? UNAUTHORIZED 
245 1 0 |a Site accessibility and characteristic velocity requirements for direct-descent lunar landings  |c Vernon J. Weyers. 
260 |a Washington, D.C. :  |b National Aeronautics and Space Administration :  |b [For sale by the Office of Technical Services, Dept. of Commerce],  |c [1970] 
300 |a 24 p.:  |b ill. ;  |c 26 cm 
490 1 |a NASA technical note ;  |v NASA TN D-5923 
500 |a Major NASA subject terms: Descent trajectories, lunar landing, lunar landing sites, velocity, cryogenics, lunar topography, mission planning, specific impulse, storable propellants 
500 |a Prepared at Lewis Research Center 
500 |a "July 1970."--Cover 
504 |a Includes bibliographical references (p. 24) 
520 |a A direct descent is one in which the main descent propulsion system burns continuously from lunar approach to touchdown. The characteristic velocity requirement for direct lunar descents is presented as a function of the landing site location relative to the normal impact point. Results are included for translunar trip times of 60, 75, and 90 hours, for specific impulses representative of both Earth storable and cryogenic propulsion systems, for landing sites located anywhere on the lunar surface, and for ignition thrust-to-Earth weight ratios between 0.12 and 10.0. The data presented are useful in determining approximate performance capability and in evaluating tradeoffs during preliminary mission planning studies 
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630 0 0 |a Trajectories 
650 0 |a Low temperature engineering 
650 0 |a Lunar landing sites 
650 0 |a Speed 
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710 2 |a Lewis Research Center 
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