Flights to asteroids from the orbit of an artificial earth satellite with a perturbational-aerodynamical impulse maneuver near Mars

Details Flights to asteroids from the orbit of an artificial earth satellite with a perturbational-aerodynamical impulse maneuver near Mars Flights to asteroids from the orbit of an artificial earth satellite with a perturbational-aerodynamical impulse maneuver near Mars

Jun 1992

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1992kosis..30..333l&link_type=abstract

Kosmicheskie Issledovaniya (ISSN 0023-4206), vol. 30, no. 3, p. 333-342.

Computer Science

Asteroid Belts, Earth-Mars Trajectories, Mars Environment, Satellite Orbits, Satellite Perturbation, Aerodynamic Coefficients, Orbit Perturbation, Spacecraft Maneuvers

Scientific paper

A spacecraft leaves the low orbit of an artificial earth satellite and, approaching Mars, descends, making the first half of a perturbational maneuver. Then the spacecraft slows down somewhat while flying in the Martian atmosphere at a constant altitude with a constant L/D(sc) less than 2.4. On some spacecraft launch dates in the time span from 1970 to 2020 a velocity impulse to about 2 km/s may be required upon exit from the atmosphere in the case of an optimal choice of dates for earth-Mars and Mars-asteroids flights. Then the spacecraft ascends over Mars, completing the second half of the perturbational maneuver. On the spacecrafts approach to the target asteroid, impulse equalization of the velocities of the spacecraft and the asteroid occurs. The sum of the three impulses - at the earth, Mars, and the asteroid - is usually 2 to 3 km/s less than the sum of the impulses required with direct optimal-trajectory earth-asteroid flights on the best dates in the same launch time span.

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