The concept of characteristics thrust is introduced herein as a means of classifying propulsion system tasks related particularly to geosynchronous communications spacecraft. Approximate analytical models are developed to permit estimation of characteristic thrust for injection error corrections, orbit angle re-location, north-south station keeping, east-west station keeping, spin axis precession control, attitude rate damping, and orbit raising applications. Performance assessment factors are then outlined in terms of characteristic power, characteristic weight, and characteristic volume envelope, which are related to the characteristic thrust. Finally, selected performance curves are shown for power as a function of spacecraft weight, including the influence of duty cycle on north-south station keeping, a 90 degree orbit angle re-location in 14 days, and finally comparison of orbit raising tasks from low and intermediate orbits to a final geosynchronous station. Power requirements range from less than 75 watts for north-south station keeping on small payloads up to greater than 15 KW for a 180 day orbit raising mission including a 28.5 degree plane change.
Propulsion requirements for communications satellites.
American Institute of Aeronautics and Astronautics, Communications Satellite Systems Conference ; 1972 ; Washington, DC
1972-04-01
Conference paper
No indication
English
Propulsion requirements for communications satellites
AIAA | 1972
|Ion propulsion for communications satellites
NTRS | 1984
|Electric propulsion for communications satellites
AIAA | 1978
|Electric propulsion for communications satellites
NTRS | 1978
|Propulsion requirements for drag-free satellites
AIAA | 1970
|