Volume 34 Issue 6
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Article Navigation >  Chinese Journal of Space Science  > 2014  >  34(6): 872-880
Zhang Hui, Zhu Min, Zhou Jianliang, Wang Yong. Station-keeping control of solar sail Lissajous orbit with attitude angles amplitude constraint[J]. Chinese Journal of Space Science, 2014, 34(6): 872-880. doi: 10.11728/cjss2014.06.872
Citation: Zhang Hui, Zhu Min, Zhou Jianliang, Wang Yong. Station-keeping control of solar sail Lissajous orbit with attitude angles amplitude constraint[J]. Chinese Journal of Space Science, 2014, 34(6): 872-880. doi: 10.11728/cjss2014.06.872
shu

Station-keeping control of solar sail Lissajous orbit with attitude angles amplitude constraint

doi: 10.11728/cjss2014.06.872 cstr: 32142.14.cjss2014.06.872
  • 1.

    Department of Automation, University of Science and Technology of China, Hefei 230027

  • 2.

    Beijing Aerospace Control Center, Beijing 100094

  • Received Date: 2013-11-04
  • Rev Recd Date: 2014-06-22
  • Publish Date: 2014-11-15
    Abstract
  • The orbital dynamic equations of solar sail spacecraft have non-affine and nonlinear properties with attitude angles as the station-keeping control input. The linearization method has been widely used in settling down station-keeping problem of solar sail spacecraft orbit. However, the linear model, obtained from local linearization around the libration point, inherently has the approximate scope which results in the constraint of the orbit amplitude as well as the constraint of the attitude angles amplitude. In this paper, 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. Furthermore, the Linear Quadratic Regulator (LQR) controller considering maximum allowable orbit injection error is designed and applied to solar sail CR3BP nonlinear model. The numerical simulations indicate that Lissajous orbit injection error convergence as well as 20 years' orbit station-keeping with high precision have been realized.

     

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