Publication Date:
2019-07-13
Description:
It is pointed out that a large class of future spacecraft, referred to as large space structures (LSS), will require advanced stationkeeping thrust subsystems. The present investigation is concerned with the performance requirements of such advanced stationkeeping thrust subsystems. An analytical model is employed to evaluate the sensitivity of the total stationkeeping thrust-system mass, for geosynchronous spacecraft, to variations in the mission parameters and thrust-system performance, taking into account ion propulsion thrust systems. The model is formulated for geosynchronous missions and considers only the N-S orbit perturbations due to sun-moon forces and the E-W orbit perturbations due to solar pressure, since these are the dominant orbit perturbations of LSS missions. The thrust system is scaled in relation to the performance capabilities of the existing 8- and 30-cm diameter ion-thruster technology and consists of separate N-S and E-W thrusters.
Keywords:
SPACECRAFT DESIGN, TESTING AND PERFORMANCE
Type:
AIAA PAPER 82-1872
,
Japan Society for Aeronautical and Space Sciences, and DGLR, International Electric Propulsion Conference; Nov 17, 1982 - Nov 19, 1982; New Orleans, LA
Format:
text
