Mars Observer trajectory and orbit design

Details Mars Observer trajectory and orbit design Mars Observer trajectory and orbit design

Oct 1991

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1991jspro..28..515b&link_type=abstract

Journal of Spacecraft and Rockets (ISSN 0022-4650), vol. 28, Sept.-Oct. 1991, p. 515-521.

Computer Science

Mars Observer, Orbit Calculation, Orbit Insertion, Spacecraft Trajectories, Interplanetary Trajectories, Planetary Orbits, Spacecraft Maneuvers

Scientific paper

The Mars Observer launch, interplanetary, Mars orbit insertion, and mapping orbit designs are described. The design objective is to enable a near-maximum spacecraft mass to be placed in orbit about Mars. This is accomplished by keeping spacecraft propellant requirements to a minimum, selecting a minimum acceptable launch period, equalizing the spacecraft velocity change requirement at the beginning and end of the launch period, and constraining the orbit insertion maneuvers to be coplanar. The mapping orbit design objective is to provide the opportunity for global observation of the planet by the science instruments while facilitating the spacecraft design. This is realized with a sun-synchronous near-polar orbit whose ground-track pattern covers the planet at progressively finer resolution.

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