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MPC Control of Satellite Formation in the Context of Three Body Problem
Darvish, Kourosh | 2014
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- Type of Document: M.Sc. Thesis
- Language: Farsi
- Document No: 46751 (45)
- University: Sharif University of Technology
- Department: Aerospace Engineering
- Advisor(s): Pourtakdoust, Hossein
- Abstract:
- In this thesis the problem of spacecrafts formation control for halo orbit around the second libration point (L2) of the Sun-Earth Three Body (TB) system is investigated. Station keeping, reconfiguration and precision formation control of spacecrafts on halo orbits are performed via the use of the nonlinear Integral Sliding Mode (ISM) method, optimal closed loop Linear Quadratic regulator (LQR) approach as well as the Model Prodective Control (MPC). In this regard the nonlinear relative dynamics of deputy-chief spacecrafts are derived within the concept of both circular and elliptical three body problem; as well the perturbation model of the Moon and the linear model of restricted three problem are derived. Also at the end of the modeling section, four body problem (4BP) is derived. In Order to control the system, continuous controls of LQR and nonlinear control of sliding mode are investigated and performed on different phases of the mission. In progress the designed controls are discretized, and measurement noises of the system states as well the Moon perturbations are considered. On the other side, control signals are saturated to be a close approximation of the real system. In addition, model predictive control is investigated and performed on the system, so that finally a comprehensive comparison between different controllers and amount of fuel consumption is accomplished. As well, the designed controls based on CRTBP and ERTBP models are applied on 4BP to specify the effect of different models
- Keywords:
- Model Predictive Control ; Sliding Mode Control ; Linear Quadratic Requlator (LQR) ; Halo Orbits ; Spacecraft Formation ; Libration Points
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