Examination of dynamic aspects of directing ferry to rendezvous with satellite and guidance philosophy for effecting this; 3-dimensional coordinate system is presented which is suited for analysis of rendezvous problem, since variables in dynamical equations are range, range-rate, and line-of-sight rate; rendezvous guidance philosophy proposed requires single thruster whose magnitude and direction are both control variables; by inverting solution to rocket equation explicit expression is derived for determining commanded thrust acceleration magnitude.
Guidance dynamics for terminal phase of rendezvous
Progress Astronautics Aeronautics
Progress in Astronautics and Aeronautics ; 13 ; p 887-907
1964
21 pages
Aufsatz (Zeitschrift)
Englisch
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Guidance Dynamics for the Terminal Phase of Rendezvous
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