NASA NTRS · 19740004400
Deorbit targeting
Abstract
The navigation and control of the space shuttle during atmospheric entry are discussed. A functional flow diagram presenting the basic approach to the deorbit targeting problem is presented. The major inputs to be considered are: (1) vehicle state vector, (2) landing site location, (3) entry interface parameters, (4) earliest desired time of landing, and (5) maximum cross range. Mathematical models of the navigational procedures based on controlled thrust times are developed.
Keep this discovery
Explore connections, maps & timelines
Tempelman, W. H.. 1973-06-01. Deorbit targeting. https://ntrs.nasa.gov/citations/19740004400
Cite the original work for its findings. Save a collection to share your selection of sources.