The results of a detailed preliminary design study of the Exosat attitude control and velocity impulse systems are reported. Essential requirements of pointing and measuring the attitude of the satellite, imposed by the scientific payload are established, requirements for attitude control sensor configurations are stated. Results are presented of a feasibility study of the application of a monopropellant hydrazine propulsion subsystem for both attitude and orbit control functions.
Exosat Attitude Control and Velocity Impulse Systems
1974
650 pages
Report
Keine Angabe
Englisch
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