The navigation and control of the space shuttle during atmospheric entry are discussed. A functional flow diagram presenting the basic approach to the deobit 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. (Author)
Deorbit Targeting
1973
26 pages
Report
No indication
English
NTRS | 1973
|Spacecraft Deorbit Point Targeting Using Aerodynamic Drag
Online Contents | 2017
|