Orbit Dynamics And Control Of Solar Sail Spacecraft

With the development of space technology, the deep space exploration has been identified as a key technology for future mission and has received significant attention in recent decades. However, the detection distance of the traditional spacecraft is lim-ited due to the relying on chemical fuel. The new continuous small thrust spacecraft concept has been proposed to settle the problem, such as nuclear propulsion, solar sail propulsion, solar photovoltaic, etc. The solar sail spacecraft potentially offer indefinite maneuvering capability by exploiting photos from the Sun as a means of propulsion. More and more attentions and researches have been paid on solar sail because of it-s significant advantages. Solar sail orbit dynamics and control technology is the key technology for us during the development of solar sail, and the related research is of great significant.Incorporating a solar sail model within the context of the circular restricted three-body problem, the dynamics of artificial Lagrange points is analyzed and proposed. As a result of the additional force, the displaced locations of artificial collinear Lagrangian points are determined and exploited for trajectory design. The Lissajous orbits and Halo orbits around the artificial collinear Lagrangian points are constructed. Further more, using the small deviation linearization method, the stability and controllability of the above orbits are analyzed.Spacecraft formation flying (SFF) is a concept that a group of satellites fly in for-mation to function as one whole system. Due to the advantages of SFF (i.e., increasing the resolution of scientific observations, reducing the cost and enhancing the overal-1system robustness), there has been a great of research focused on SFF in the past. To inherently get across the dependency on model accuracy as well as the drawbacks of previous SFF control methods, an active disturbance rejection formation-keeping control (ADRFC) approach is proposed and analyzed. The ADRFC is an error driven control method rather model based approach, which is the major point of departure between and earlier approaches. The nonlinear simulation results of SFF about the Halo orbit around the Sun-Earth L1point indicate that ADRFC is adequate for SFF of unstable orbits that take into the system uncertainties, initial injection errors and dis-turbances. The control precision of SFF using ADRFC has achieved and exceed the SFF precision standard of NASA.The orbital dynamic equations of solar sail spacecraft have non affine and nonlin-ear properties with attitude angles as the station-keeping control input. The linearliza-tion method has been widely used in settling down station-keeping problem of solar sail spacecraft orbit. However, the linear model, obtained from local linearzation around the libration point, inherently has the approximate scope which resulting in the con-straint of the orbit amplitude as well as the constraint of the attitude angles amplitude. In this dissertation, the model error of solar sail linear dynamic system is presented and the constraint of attitude angles amplitude is calculated. As a result of the controller amplitude constraint, the trajectory control ability is bounded, raising questions about the maximum allowable orbit injection error. Then, the controllability Gramian matrix is used to estimate the maximum allowable orbit injection error. Further more, the LQ controller considering maximum allowable orbit injection error is designed and applied to solar sail CR3BP nonlinear model.In order to further expand the solar sail application space and undertake the task with much more complicated and higher requirements, a class of hybrid solar sail have been proposed, which combines the advantages of both solar sails and solar electric propulsion. In order to get across the dependence on model accuracy of feedback linearization station-keeping control method of hybrid solar sail, an active disturbance rejection station-keeping controller (ADRSC) is proposed and analyzed using the input and output of dynamic system rather than model. The nonlinear simulation results in-dicate that high accurately station-keeping of hybrid solar sail about Halo orbit around artificial L1point has been obtained.