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.
Deorbit targeting
1973-06-01
Report
No indication
English
NTIS | 1973
|Spacecraft Deorbit Point Targeting Using Aerodynamic Drag
Online Contents | 2017
|