NONLINEAR TRACKING ATTITUDE CONTROL OF SPACECRAFT ON TIME DEPENDENT TRAJECTORIES

TEKİNALP O., Gomroki M. M., Atas O.

AAS/AIAA Astrodynamics Specialist Conference, Colorado, United States Of America, 11 - 13 August 2015, vol.156, pp.1585-1597 identifier

  • Publication Type: Conference Paper / Full Text
  • Volume: 156
  • City: Colorado
  • Country: United States Of America
  • Page Numbers: pp.1585-1597
  • Middle East Technical University Affiliated: Yes

Abstract

The spacecraft attitude control is carried out using the to-go quatemion. A derivative of the to-go quaternion is derived where the desired attitude is a time dependent function. Based on this new attitude formulation, a proper state dependent coefficient matrix expression is obtained. Then the nonlinear tracking attitude control is realized using the state dependent Riccati equation method. The simulation results are given and discussed.