Gravitational Orbit-Attitude Coupling for Very Large Spacecraft

Details Gravitational Orbit-Attitude Coupling for Very Large Spacecraft Gravitational Orbit-Attitude Coupling for Very Large Spacecraft

Oct 1983

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1983cemec..31..143s&link_type=abstract

Celestial Mechanics, Volume 31, Issue 2, pp.143-161

Physics

3

Scientific paper

Motion equations for the gravitationally coupled orbit-attitude motion of a spacecraft are presented. The gravitational force and torque are expanded in a Taylor series in the small ratio (spacecraft size/orbital radius). A recursive definition for higher moments of inertia is introduced which permits terms up tofourth order to be retained. The expressions are fully nonlinear in the attitude variables. A quasi-sunpointing (QSP) passive attitude-control mode is used to assess the effects of higher moments of inertia and gravitational coupling. The attitude motion is detectably coupled to the orbital motion. However, the higher moments of inertia influence only the attitude motion.

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