Parametric entry corridors for lunar/mars aerocapture missions
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Parametric entry corridors for lunar/mars aerocapture missions by Lisa Ling

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Published by National Aeronautics and Space Administration, Lyndon B. Johnson Space Center in Houston, Tex .
Written in English


  • Aerocapture.,
  • Aerobrake.,
  • Corridors.

Book details:

Edition Notes

StatementLisa Ling, Franco M. Baseggio, Douglas P. Fuhry.
SeriesNASA technical memorandum -- 102178.
ContributionsBaseggio, Franco M., Fuhry, Douglas P., Lyndon B. Johnson Space Center.
The Physical Object
Pagination1 v.
ID Numbers
Open LibraryOL16109901M

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  Identifying method of entry and exit conditions for aerocapture with near minimum fuel consumption Aerospace Science and Technology, Vol. 58 Entry System Options for Human Return from the Moon and MarsCited by: Abstract and Figures A parametric study has been conducted of aerocapture for missions to Venus, examining the entry corridor width as a function of entry velocity, vehicle aerodynamics, and.   Earth atmospheric entry studies for manned Mars missions. M. E. Tauber, Entry System Options for Human Return from the Moon and Mars. Z. R. Putnam, Parametric study of manned aerocapture. II - Mars entry. J. E. Lyne, Cited by: Close Drawer Menu Close Drawer Menu Menu. Home; Journals. AIAA Journal; Journal of Aerospace Information Systems; Journal of Air Transportation; Journal of Aircraft; Journal of .

AIAA Atmospheric Flight Mechanics Conference August , San Francisco, CA. Earth entry system options for human return missions from the Moon and Mars . When this load limit was applied, numerical studies showed that an aerobrake with an L/D of could provide an entry corridor width of at least 1 degree for all Mars aerocaptures considered with. Mars Exploration John A. Christian*, Aerocapture and entry-from-orbit analyses of 10 and 15 m diameter aeroshells For the purposes of this study, an entry-from-orbit velocity of 4 km/s is targeted in order to determine the entry corridor based on: (a) the lift-down trajectory with the most shallow flight path angle that allows for entry. This paper considers constraints imposed by entry corridor, deceleration loads, and aerodynamic heating on aerocapture for two vehicle control techniques: lift modulation and drag modulation. Feasibility charts are presented to graphically visualize the aerocapture design space spanning interplanetary trajectory and vehicle performance.

  1. Introduction. Numerous scenarios have been proposed for human missions to Mars but there is currently no consensus on the best one,,,,,,,.The most detailed scenario is the NASA reference mission, but it is also known for its ing to the NASA study, there is a long list of technologies that have to be developed and matured before the first mission can be undertaken. Aerocapture has previously been identified as a critical technology for manned Mars missions. A wide range of parking orbits is available into which an aerobraking vehicle could be captured, and.   Eyman and Repic have presented approach navigation accuracy estimates for aerocapture and computed the corresponding entry corridors in the background of manned Mars and Venus mission. Lyne et al. [11], [12], [13] have computed the entry corridor and conducted a parametric study of aerocapture for manned Mars missions.   A study on aerocapture corridor over a range of entry velocities (6–9 km/s) suggests that a hypersonic L/D of is sufficient for a Martian aerocapture.