CanX-4/-5 is a formation flying technology demonstration mission that shall demonstrate sub-meter formation tracking control. The key to this precision control is carrier phase differential GPS state estimation, which enables centimeter-level relative state estimation. In this thesis, the formation flying controller design is reviewed in detail, and an innovative closed-loop formation reconfiguration strategy is presented. In addition, the designs of both coarse- and fine-mode relative state estimators are presented. Formation flying simulations demonstrate the efficacy of the proposed control and coarse estimation. Furthermore, hardware tests are performed to test the computational efficiency of the control algorithms and to validate the fine-mode relative navigation filter.

CanX-4/-5 is a formation flying technology demonstration mission that shall demonstrate sub-meter formation tracking control. The key to this precision control is carrier phase differential GPS state estimation, which enables centimeter-level relative state estimation. In this thesis, the formation flying controller design is reviewed in detail, and an innovative closed-loop formation reconfiguration strategy is presented. In addition, the designs of both coarse- and fine-mode relative state estimators are presented. Formation flying simulations demonstrate the efficacy of the proposed control and coarse estimation. Furthermore, hardware tests are performed to test the computational efficiency of the control algorithms and to validate the fine-mode relative navigation filter.

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A novel continuous low-thrust fuel-efficient model predictive control strategy for multi-satellite formations flying in low earth orbit is presented. State prediction relies on a full nonlinear relative motion model, based on quasi-nonsingular relative orbital elements, including earth oblateness effects and, through state augmentation, differential drag. The optimal control problem is specically designed to incorporate latest theoretical results concerning maneuver optimality in the state-space, yielding to a sensible total delta-V reduction, while assuring feasibility and stability though imposition of a Lyapunov constraint. The controller is particularly suitable for networked architectures since it exploits the predictive strategy and the dynamics knowledge to provide robustness against feedback losses and delays. The Networked MPC is validated through real missions simulation scenarios using a high-fidelity orbital propagator which accounts for high-order geopotential, solar radiation pressure, atmospheric drag and third-body effects.

京都大学 / 新制・課程博士 / 博士(理学) / 甲第23007号 / 理博第4684号 / 新制||理||1672(附属図書館) / 京都大学大学院理学研究科物理学・宇宙物理学専攻 / (主査)教授 嶺重 慎, 准教授 前田 啓一, 教授 太田 耕司 / 学位規則第4条第1項該当 / Doctor of Science / Kyoto University / DFAM

This thesis proposes a distributed robust control approach for low-thrust nanosatellite formation flying. The presented control approach is the further development of an already existing approach which combines robust control and distributed control using the consensus approach. The adjustments presented in this thesis are intended to enable the usage of the control approach in nanosatellite missions such as the upcoming NetSat mission. Stability criteria, optimization goals and constraints such as the limited maximum thrust are formulated with the help of Linear Matrix Inequalities (LMIs). In addition, the presented control approach includes methods for exploiting the maximum thrust and for collision avoidance. Due to the design as a distributed controller based on the consensus approach, a satellite formation can be maintained even in the case of the failure of the propulsion system and/or Attitude Determination and Control System (ADCS) of a single satellite. To verify the design of the control approach, simulations of the formation scenarios planned for the NetSat mission are performed with a satellite formation simulation framework based on Orekit and MATLAB®.