فهرست مقالات Satellite attitude

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  1 - Impulsive Control of Attitude Satellite With Quaternion ‎Parameters
  M. R. Niknam N. Abdi Sobouhi
  10.30495/ijim.2022.58349.1481
  This article uses impulsive control along with quaternion parameters instead of Euler angles in kinematics equations of satellite. ‎The quaternion parameters are applied to overcome singularity problem in the numerical solution. ‎It is assumed that the satellite چکیده کامل

  This article uses impulsive control along with quaternion parameters instead of Euler angles in kinematics equations of satellite. ‎The quaternion parameters are applied to overcome singularity problem in the numerical solution. ‎It is assumed that the satellite is subjected to deterministic external perturbations. ‎At first, ‎the chaotic behavior of system is investigated when there is no control on the system. ‎Then, ‎impulsive control is used to stabilize the satellite attitude around the equilibrium point of origin. ‎Finally, ‎simulation results are given to visualize the effectiveness and feasibility of the proposed ‎method. پرونده مقاله
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  2 - Three-axis optimal control of satellite attitude based on Ponteryagin maximum ‎principle‎
  M. R. Niknam K. Kheiri A. Heydari
  A long time ago, since the launch of the first artificial satellite in 1957, controling attitude of satellites has been considered by the designers and engineers of aerospace industry. Considering the importance of this issue various methods of control in response to th چکیده کامل

  A long time ago, since the launch of the first artificial satellite in 1957, controling attitude of satellites has been considered by the designers and engineers of aerospace industry. Considering the importance of this issue various methods of control in response to this need have been presented and analyzed until now. In this paper, we propose and analyze a three-axis optimal control on the six-dimensional system which describes the kinetic and kinematic equations of a satellite subjected to deterministic external perturbations which induce chaotic motion. At first, the chaotic behavior of system using Lyapunov exponents (LE) and numerical simulations is investigated when no control is affected. Then, a three-axis optimal control is presented by the Pontryagin maximum principle (PMP). This optimal control stabilizes the satellite attitude around the equilibrium point of origin. Finally, we give some simulation results to visualize the effectiveness and feasibility of the proposed ‎method.‎ پرونده مقاله