The use of lunar-swingby maneuvers to transfer a spacecraft from an equatorial orbit to a polar orbit has been investigated in order to verify the technical feasibility of the NASA/ESA equatorial science phase (ESP)/Cluster mission. The solar aspect angle constraints of the spacecraft spin-axis and the dependence of the total Delta-V cost of the transfer on the initial ESP orbital parameters (particularly perigee radius and inclination) have been studied. The results indicate that a satisfactory ESP-to-Cluster orbit transfer can be achieved using a double lunar-swingby sequence.
Large inclination change using lunar-swingby techniques
AIAA/AAS Astrodynamics Conference ; 1988 ; Minneapolis, MN, United States
1988-01-01
Conference paper
No indication
English
Large inclination change using lunar-swingby techniques
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