solar pressure produces short-period (24 h), long-period (approximately 1 year), and secular variations to the orbital elements of the SPS. If the SPS has the design capability to accommodate the orbit variations caused by the short-period perturbations, then the major impact of the solar radiation pressure is the change of the major axis of the orbit, which is cyclic over approximately 1 year and causes a change in the orbital mean motion with a resulting longitudinal drift of the SPS. Figure 7-19 shows the combined effects of the perturbations on the longitudinal position of the SPS. If station keeping maneuvers are conducted every 30 days, a velocity of approximately 3. 7 m/s will be required to correct the inclination, and a velocity of 14 m/s will be required to correct altitude and ellipicity of the operational orbit. 7.1. 5. 2 LEO TO GEO ORBITAL TRANSFER-MISSION AND PERFORMANCE ANALYSIS 7.1. 5.2.1 BACKGROUND Previous studies at MSFC, both in-house and contractual, have shown that high specific impulse, low thrust electric propulsion provides a significant economic advantage over present and projected chemical propulsion Figure 7-19. SPS longitude shift due to perturbations.
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