Study Of Low Thrust Station Keeping Maneuver Planning For Solar Power Satellite On Geostationary Orbit

Solar Power Satellite (SPS) received extensive global attention because of its highefficiency. It is an important direction of renewable energy in the future, as it has noenvironmental pollution and it is sustainable development. By the state of the art, GEOis the best orbit for SPS to run. When the SPS run in the space, it is perturbed by thesum of the luni-solar attraction potential, the solar radiation pressure pseudo potentialand the part of the Earth’s gravity potential coming from the asymmetric massrepartition. In order to keep the SPS in a prescribed scope around the keeping station, itis needed to make control maneuver planning based on the electric thrust.As SPS has the characteristics of big flexibility, large area, small density andlimited bearing capacity, the large pulse thrust isn’t fit for it. While the electric thrust hasthe advantages of high impulse, low fuel consumption, small vibration and accuratelycontrolled, it becomes the key technique to maintain SPS orbit. The electric thrust has acontinuous function and small amplitude, this leads to the dynamic equation is differentfrom the large pulse thrust situation, so it has important engineering value to study thekeeping maneuver planning based on the electric thrust. In this paper, the study mainlyincludes:The motion of the SPS can be described by the rate of change of the equinoctialorbital parameters under the influence of the forces acting on the satellite. Assumingthat the functions of the forces are continuously differentiable and expanding intoTaylor series up to the first order around the nominal operating point, we obtain thelinear orbit dynamics model.Considered of the constraints of fixed point accuracy and thruster system theproblem of station keeping can be formulated as a constrained linear quadratic optimalcontrol problem. To write explicitly control inputs into the functions of state and its rate,we introduce the Lyapunov transformation. Then, we solve the optimal problem bydirect methods, we parameterize and disperse the problem by the differential inclusionapproach, the optimal control problem can be translated in a quadratic programmingproblem with constraints only on the state variables.At last, we set the initial values of constraints, such as state variables aroundaccuracy and so on, we can get the simulation analysis results by matlab. It proves thecorrectness of the control maneuver planning, the SPS orbit can be controlled in adesignated target of0.1degree range accuracy, which satisfies the engineeringrequirements.