Choice of the optimal angular position of a spacecraft in the constant-solar-orientation flight segment

Details Choice of the optimal angular position of a spacecraft in the constant-solar-orientation flight segment Choice of the optimal angular position of a spacecraft in the constant-solar-orientation flight segment

Jan 1987

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1987kosis..25...23i&link_type=abstract

Kosmicheskie Issledovaniia (ISSN 0023-4206), vol. 25, Jan.-Feb. 1987, p. 23-29. In Russian.

Physics

Angular Momentum, Attitude (Inclination), Satellite Attitude Control, Solar Orbits, Solar Power Satellites, Spacecraft Orbits, Axes Of Rotation, Gravitational Effects, Magnetic Effects, Optimization, Orbital Mechanics

Scientific paper

The orientation which assures minimum angular momentum due to gravitational and magnetic disturbances is determined for a typical spacecraft with solar panels (e.g., Soyuz or Mir). These disturbances are assumed to act on the spacecraft in an arbitrary unshaded orbit for maximum illumination of the solar panels. Attention is given to cases when the panels are fixed rigidly to the spacecraft and rotate with respect to a single axis.

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