The problem of landing site coverage of orbiting vehicles with maneuvering capability is analysed in this report. The first part deals with the determination of the latitude coverage of a landing site per orbital period for the re-entry vehicle with a given maneuver capability defined by a rectangularly shaped "landing footprint." The second part relates the required latitude coverage to guarantee that within a specific waiting time in orbit the vehicle would attain a position from which it could be deboosted from orbit and subsequently land at a preselected location.
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