coupled effects between orbit and attitude for passive solar sail control
- Paper number
IAC-08.C1.7.1
- Author
Dr. yunfeng Gao, Tsinghua University, China
- Coauthor
Prof. Colin R. McInnes, University of Strathclyde, United Kingdom
- Year
2008
- Abstract
It is well known that the coupling between the orbit and attitude of solar sails is more significant than that of other spacecraft. This paper will discuss the orbit-attitude interactions under different circumstances. Firstly, a solar sail model with one main sail and four vanes is proposed, where the small vanes are designed to provide passive control. Secondly, the orbit-attitude coupled equations of motion for this solar sail model are investigated, and the coupling between attitude and orbit are investigated in detail by considering the effect of both the main sail and vanes. Thirdly, the equilibrium solution of the coupled equations is obtained, and then the coupled equations are linearized near the equilibrium solution. The stability of the sail orbit and attitude is discussed, and the maximum real part of all eigenvalues used as an index to measure instability. The orbit and attitude are unstable without control, but the attitude may be stabilized with passive control with some specially designed shape. The stability of the orbit is more complex, because it depends not only on the orbit or the attitude of the sail, but also on the central body (Sun or Earth-centred orbits). The orbit of the sail around the Sun is not stable, even when the attitude is stable. As the sail orbits the Earth, the solar pressure force is small compared to the gravitational force of the Earth, therefore the orbit stability of the sail is strongly influenced by the Earth’s gravity gradient. Finally, two examples are presented: the mission GeoSail with an Earth-centred solar sail and the displaced Sun-centred orbits. The eigenvalues evaluated in different conditions, and the results of the interactions between the orbit and attitude are shown.- Abstract document
- Manuscript document
IAC-08.C1.7.1.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.