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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.
Aeronautical and Navigational Electronics, IRE Transactions on (Volume:ANE-7 , Issue: 4 )
Date of Publication: Dec. 1960