Controlling the rotation of a spacecraft by means of solar radiation pressure forces.
Abstract
Three-dimensional motion of the Small Space Lab (SSL)
spacecraft about its centre of mass under the solar radiation
torques is considered. The centre of mass of the spacecraft moves
in a circular heliocentric orbit. The spacecraft has an axially
symmetrical solar stabilizer and eight solar paddles arranged
like a windmill. The paddle's slope angles are made controllable.
In the design condition, the spacecraft fore-and-aft axis should
be directed to the Sun and its spin rate should have a value
required.
The equations in evolutionary variables are studied. The
dynamical model takes into account an effect of re-radiating
solar electromagnetic energy by the thin films of the stabilizer.
A phenomenology model of re-radiation torque is suggested. It is
shown, that the re-radiation torque leads to nutation damping.
An algorithm to control the solar paddles is developed.
It provides bringing the spacecraft to the nominal Sun-pointing
orientation with a given spin rate. The algorithm requires no
synchronization with the spacecraft's spin rate and only the mean
deviation of the fore-and-aft axis from the direction to the Sun
has to be input. Thus, the algorithm may readily be implemented
on board.
The results of numerical simulation are presented.
V.V.Beletsky, A.V.Grushevsky, E.L.Starostin.
J. Comput. Syst. Sci. Int., 1994, 32, No.3, pp. 70-76;
translation from Izv. Ross. Akad. Nauk, Tekh. Kibern. 1993, No.1, 32-38, ISSN 1064-2307.