科研之友
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摘要
In this paper, a hybrid control method for partially liquid-filled spacecraft maneuvers is proposed. This control scheme integrates the command input shaping technique and the feedback linearization method to guarantee the implementation of the maneuver task for spacecraft to yield the desirable suppression of liquid fuel slosh. The coupled slosh spacecraft in attitude maneuver carrying a sloshing liquid is considered as a multibody system with the sloshing motion modeled as a spherical pendulum. Nonlinearly coupled equations of attitude and orbital motion are presented for the partially liquid-filled spacecraft undergoing fuel slosh. A feedback linearization approach is applied to transform the nonlinear system dynamics into a linear system ( inverse dynamics of the original system or so-called dynamics inversion) to compute the input corresponding to the reference output. Dynamic inversion and input shaping techniques are used to design a controller for the reference tacking maneuver of spacecraft with fuel sloshing. Numerical simulation results are presented to confirm the effectiveness of the proposed hybrid control method.
- 出版日期2014-3
- 单位北京理工大学
