Increasing computation speed for accurate determination of spacecraft orbits with large eccentricities.

Details Increasing computation speed for accurate determination of spacecraft orbits with large eccentricities. Increasing computation speed for accurate determination of spacecraft orbits with large eccentricities.

Dec 1994

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1994kosis..32r...3l&link_type=abstract

Kosmicheskie Issledovaniia, Tom 32, Vyp. 6, p. 3 - 15

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Computation

Artificial Satellites: Orbits, Celestial Mechanics: Numerical Methods

Scientific paper

The problem arose with regard to a project of a space mission to the vicinity of the collinear libration point L2 in the Sun - Earth system with a close flyby near the Moon (project "Relict-2"). At the initial part of the space trajectory the spacecraft performs 2.5 revolutions around the Earth in the orbit with a perigee close to the Earth surface and an apogee in the vicinity of the Moon's orbit. The computational time of PC, required for calculating such a trajectory by numerical integration within a given accuracy and with account for a complicated gravity effect of the Earth, proves to be large. Solving boundary control problems in real time needs multiple computations of such trajectories. In view of this, the problem of increasing the computational speed becomes rather urgent. A technique of splitting the trajectory into segments is proposed to solve this problem.

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