Trajectories and orbital maneuvers for the ISEE-3/ICE comet mission

Details Trajectories and orbital maneuvers for the ISEE-3/ICE comet mission Trajectories and orbital maneuvers for the ISEE-3/ICE comet mission

Aug 1984

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1984asdy.confq....f&link_type=abstract

American Institute of Aeronautics and Astronautics and American Astronautical Society, Astrodynamics Conference, Seattle, WA, Au

Astronomy and Astrophysics

Astronomy

Comets, International Sun Earth Explorer 3, Orbital Maneuvers, Space Missions, Spacecraft Trajectories, Trajectory Analysis, Escape Velocity, Geomagnetic Tail, Spacecraft Maneuvers, Spacecraft Orbits

Scientific paper

The ISEE-3/ICE spacecraft, (launched in 1978), and expected to obtain the first measurements of comet Giacobinni-Zinner in September 1985, has undertaken a combination of propulsive maneuvers, lunar swing-bys, and solar perturbations to produce its present trajectory profile. ISEE-3 is a drum-shaped, spin-stabilized spacecraft equipped with a redundant pair of high-resolution sun sensors, a medium-gain S-band antenna, a hydrazine propulsion system and a science experiment payload. After being placed into a sun-earth libration halo orbit in late 1978, ISEE-3 was retargeted to the geomagnetotail in mid-1982 and became the first spacecraft to explore the geomagnetic tail between 80 and 237 earth radii in 1983. These types of maneuvers may prove important for future scientific missions planned as follow-ons to ISEE-3/ICE, such as a joint NASA/ISAS project spacecraft scheduled for Shuttle launch in 1991, and a possible encounter with two comets in 1996 anad 1998.

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