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摘要
Launching solar sails to low Earth orbit can provide cheap and frequent opportunities for test missions, orbit raising from low Earth orbit, or deorbiting space debris. This Paper considers the problem of attitude dynamics and control of a flexible solar sail under solar radiation pressure, aerodynamic forces, and gravity gradient torque. A geometrically nonlinear finite element method was used to study the effects of solar radiation pressure and aerodynamic forces on a flexible membrane, including the deformation-induced disturbance torque and changes of center of pressure. Then, an analytical method was applied to estimate the deformation of the membrane, and consequently the generated disturbance torque. The results showed that the analytical method could estimate the sail deformation very accurately. The problem of controllability of a sliding mass control mechanism in low Earth orbit was studied, and the controllable attitude regions were defined according to the mass of the sliding masses. A robust servomechanism linear quadratic regulator optimal control approach was applied to control the attitude of a flexible sail in low Earth orbit under the disturbance torques. The simulation results showed the efficacy and robustness of the controller in dealing with deformation-induced torques during orbit raising and deorbiting.
- 出版日期2018-8
- 单位清华大学
