Abstract: Halo orbit locates about the libration point in the Sun-Earth system and has no orbital plane focusing the Earth, which makes the attitude description and dynamics modeling for Halo-orbit spacecraft is quite different from that for the usual satellite around the Earth. Two different schemes of attitude description were proposed for the spacecraft in the three axis stabilization, sun-orienting scheme (Scheme I, using the Sun and Earth attitude sensors) and rotating-reference scheme (Scheme II, using the Star attitude sensor). So the attitude dynamics can be modeled from the different orbital coordinates defined by the two schemes. The upper limits of relative errors for the two schemes were estimated theoretically: no more than 5% for Scheme I, and 0.005% for Scheme II. A controller was designed for the attitude stabilization to validate the feasibility of the schemes. The research shows that Scheme II is set as the normal mode with the astronomical ephemeris periodically corrected, while Scheme I is used as the alternate device for the failure mode.