This is a terminal guidance technique for satellite rendezvous utilizing a constant thrust rocket motor, a computer, and attitude control. For any given thrust level, this technique can reduce the relative range to any desired value in a minimum of time for an interceptor on a collision course. In this paper, a terminal guidance law is formulated and mechanized. The generalized range performance trajectories and system errors are presented.
Published in:
Aeronautical and Navigational Electronics, IRE Transactions on
(Volume:ANE-7
,
Issue:
4
)
Date of Publication: Dec. 1960