Low thrust insertion into orbit around Mars

Details Low thrust insertion into orbit around Mars Low thrust insertion into orbit around Mars

Jan 1987

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1987aiaa.meett....p&link_type=abstract

AIAA, Aerospace Sciences Meeting, 25th, Reno, NV, Jan. 12-15, 1987. 6 p.

Computer Science

Interplanetary Spacecraft, Low Thrust, Mars (Planet), Mars Observer, Orbital Maneuvers, Planetary Orbits, Elliptical Orbits, Insertion, Interplanetary Navigation, Rocket Firing, Selection

Scientific paper

The aspects of the low-thrust insertion of the Mars Observer spacecraft from its approach trajectory into an orbit around Mars, using four 110-lb(f) thrusters, are discussed. The strategy includes insertion into an elliptical capture orbit (4100 x 20,000 km), targeting for a 4150-km periapsis to compensate for reduction in periapsis altitude during burn, initiating the burn at about 20 deg before the periapsis (or 40 deg, if half-system capability is to be used), and minimizing the finite burn penalty by pitching the spacecraft during the burn to align the thrust vector parallel to the negative velocity vector.

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