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An accurate guidance algorithm for implementation onboard satellite launch vehicles

Mardani, M ; Sharif University of Technology | 2010

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  1. Type of Document: Article
  2. Publisher: 2010
  3. Abstract:
  4. An algorithm for guiding a launch vehicle carrying a small satellite to a sun synchronous LEO is presented. Before the launch, a nominal path and the corresponding nominal control law for the entire journey are computed. For each sampling instant during the guided flight, a linear equation approximately relating the differences between the actual and nominal values is considered, and a LeastSquares formula using data from on-line state measurements is applied to compute the actual control. The coefficient matrices of the Least-Squares formula can be determined by off-line computations. The method enjoys simplicity of implementation by onboard computers, as well as robust accuracy against strong winds and uncertainties in thrust magnitude
  5. Keywords:
  6. Disturbance rejection ; Optimal trajectory ; Satellites ; Accurate guidance ; Coefficient matrix ; Control laws ; Guidance system ; Least Square ; Off-line computation ; On-line state ; Onboard computers ; Optimal trajectories ; Satellite launch vehicles ; Small satellites ; Strong winds ; Launch vehicles ; Optimization ; Reception quality ; Remote control ; Vehicles ; Launching ; Accuracy assessment ; Algorithm ; Computer ; Linearity ; Space shuttle
  7. Source: Scientia Iranica ; Volume 17, Issue 2 D , JULY-DECEMBE , 2010 , Pages 175-188 ; 10263098 (ISSN)
  8. URL: http://en.journals.sid.ir/ViewPaper.aspx?ID=186686