Adjustment can be accomplished by electric propulsion systems limited to thrust levels in millipounds; near polar 750-nautical-mi orbit with precession error of 0.029°/day is chosen; perturbation equations of motion are used to derive total impulse required to correct error; spiraling operation or altitude change can accomplish correction with 2050-lb-sec total impulse for 670-lb satellite; 5-mlb resistojet requires 11.3 days whereas 300- μlb ion engine requires 79.1 days for same correction; methods of inclination adjustment and providing constant precession bias require more total impulse and are therefore less efficient than spiraling approach.
Orbit adjustment of sun-synchronous satellites with electric propulsion
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 5 , n 7
1968
4 pages
Article (Journal)
English
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