Approximate optimal atmospheric entry trajectories

Author:

SPEYER J.1,WOMBLE M.1

Affiliation:

1. MIT, CAMBRIDGE, MASS.

Publisher

American Institute of Aeronautics and Astronautics

Reference24 articles.

1. Note that the multiplie["S can be normalized in both (32) and (33) by defining two constants _e1 . P1iP3 and E.:2: p2/p3. The functional dependencc-lJeiwee CL and c0 most be given explicitly. \\"hi!e a ge,11.er-al New tooian polar has been found too complex. an elliptic polar was successfully carded through n the analysis.7A simpler form will be used in the following analysis,54 l Optimal lirt coefficient for- parabolic lift-drag polar

2. • -l1-2slny+ [ I - >2) (38)

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1. Reentry Debris Envelope Model for a Disintegrating, Deorbiting Spacecraft Without Heat Shields;AIAA Atmospheric Flight Mechanics Conference and Exhibit;2005-06-19

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