Attitude Control of Spinning Solar Sail Considering the Deformation by Solar Radiation Pressure
- Paper number
IAC-08.C1.7.8
- Author
Mr. Masayuki Sugita, Aoyama Gakuin University, Japan
- Coauthor
Dr. Ryu Funase, Japan Aerospace Exploration Agency (JAXA), Japan
- Coauthor
Dr. Yuichi Tsuda, Japan Aerospace Exploration Agency (JAXA), Japan
- Coauthor
Dr. Osamu Mori, Japan Aerospace Exploration Agency (JAXA), Japan
- Coauthor
Mr. Fuminori Hanaoka, University of Tokyo, Japan
- Coauthor
Dr. Junichiro Kawaguchi, Japan Aerospace Exploration Agency (JAXA), Japan
- Year
2008
- Abstract
Japan Aerospace Exploration Agency (JAXA) has been studying spinning solar sail as a promising way of orbital control for future interplanetary exploration. A squared-shape spinning type solar sail has been proposed for the mission, taking advantage of its simple structure. One of major problems to solve is attitude control of spinning huge and flexible membrane. However, the attitude control system of the solar sail, which controls the direction of the sail and thus the propulsive force, has not been much studied, although this constitutes the essential part of the orbital control using solar sail. In this paper, two attitude control systems were introduced. One is the method of using conventional chemical thruster. In particular, hybrid control law of Rhumb Line Control (RLC) and Active Nutation Control (ANC) was derived, which can control the direction of angular momentum of the spacecraft while damping the oscillatory motion of the membrane caused by impulsive torque of the thruster. The other is the method of using reflectivity control device (RCD) which controls optical parameters of the membrane. This method does not excite oscillation because it directly and smoothly controls the attitude motion of the membrane which constitutes most part of the total angular momentum of the spinning solar sail. The performance of the proposed methods was verified by numerical simulations. The simulations were conducted with a dynamics model of the flexible membrane using multi-particle model (MPM). The results show that both control systems can control the attitude of spacecraft with little oscillation, and the method of RCD showed much promise because it is fuel-free control system and less oscillatory than the former. In addition, considering the real space environment, it is expected that the membrane is deformed by solar radiation pressure. Also, the disturbance torque should be taken into consideration, which is caused by the offset between the center of gravity of the whole spacecraft and the sail itself and the diffuse reflection of sunlight. These effects of solar radiation pressure on the performance of the attitude control system has not been analyzed yet, so in this research, the effects were comprehensively evaluated by numerical simulations with improved MPM, which can incorporate these effects. It was confirmed that the above control systems are applicable even to the realistic situation.
- Abstract document
- Manuscript document
IAC-08.C1.7.8.pdf (🔒 authorized access only).
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