Physics
Scientific paper
Aug 1990
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1990esabu..63...66r&link_type=abstract
ESA Bulletin (ISSN 0376-4265), no. 63, Aug. 1990, p. 66-69.
Physics
Spacecraft Orbits, Swingby Technique, Trajectory Optimization, Ulysses Mission, Mission Planning, Orbit Calculation, Satellite Attitude Control, Spacecraft Maneuvers, Transfer Orbits
Scientific paper
The establishment of the Ulysses' nonecliptic solar-polar orbit is discussed. The Ulysses probe will have an earth departure velocity of 11.4 km/s with a maximum ecliptic inclination of 23 deg, and the effective initial heliocentric velocity when the launcher is standing on the launch pad is 29.8 km/s in the ecliptic plane. Ulysses will use Jupiter in order to deflect its trajectory and thereby change the direction of its initial heliocentric angular momentum due to the orbital velocity of the earth (29.8 km/s) without using propellant, thereby conserving fuel reserves for contingencies and enhancement of the scientific mission. The basic swing-by analysis is discussed and an optimization of the trajectory is analyzed. The attitude and orbit control system is described, and orbit maneuvers are considered.
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