Guidance and robust control methods for the approach phase between two orbital vehicles with coupling between translational and rotational motions

Laura Sofia Urbina 1
1 LAAS-MAC - Équipe Méthodes et Algorithmes en Commande
LAAS - Laboratoire d'analyse et d'architecture des systèmes [Toulouse]
Abstract : The techniques related to formation flying and proximity operations of autonomous satellites belong to the most significant and challenging operational space technologies of the last years. In particular, they require full mastery of the close-range rendezvous and observation phases by an active satellite with a passive satellite, station or debris. The development of efcient and safe associated Guidance, Navigation and Control (GNC) systems relies on the knowledge of a dynamic model that achieves a good trade-off between low complexity and sufficient inclusion of the main dynamic and kinematic characteristics of this type of systems. The first part of this thesis is devoted to the development of a unified modeling of the relative coupled dynamics between a cooperative chaser satellite and a non-cooperative target satellite. Indeed, when two satellites are close to each other, they can no longer be treated as point masses because their shape and size affect the relative motion between the decentralized points, leading to a translational-attitude motions coupling. This development is addressed in a progressive way: the relative nonlinear translational motion is described under Keplerian assumptions in the target’s orbital reference frame, as well as the associated linearized model. Then, the nonlinear relative attitude model is presented by means of the Euler-Rodrigues parameters. Finally, the dual quaternion formalism is used to obtain the relative translational and attitude coupled model. The modeling phase concerning the linear relative translational motion has allowed us to highlight certain coordinates transformations leading to an interesting characterization of the chaser’s periodic trajectories and thus, to propose a first type of control lawfor the close-phase rendezvous and observation phases. All along this work, we consider a chaser satellite equipped with chemical thrusters under the classical hypothesis of impulsive thrusts. This type of dynamic systems gathering continuous dynamics and impulsive control naturally belongs to a particular class of dynamical hybrid systems. Several hybrid control laws are then proposed in order to stabilize the chaser on a periodic reference trajectory close to the target. The stability and convergence properties of these different laws are analysed and several numerical simulations show the strengths and weaknesses of each controller in terms of performance indices such as convergence time, consumption and safety constraints. In a second step, additional operational constraints (line-of-sight constraints for example) are taken into account by imposing a rectilinear (glideslope) direction to the chaser. This trajectory requires the chaser satellite to follow a straight line in any direction of the local reference frame and connecting the current location of the chaser to its final destination. Under the impulsive propulsion assumptions, the results in the literature for this type of approach have been generalized to elliptic orbits by identifying a newformulation of the problem including useful degrees of freedom, which allowminimizing the fuel consumption while controlling the humps of the trajectory outside the glideslope line by enclosing it in a user-defined approach corridor. Guidance laws are therefore synthetized via the solution of an SDP optimisation problem in the general case and via a linear programming when considering standard cases like the V-bar or R-bar approaches.
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Automatic. Université Paul Sabatier (Toulouse 3), 2017. English
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Laura Sofia Urbina. Guidance and robust control methods for the approach phase between two orbital vehicles with coupling between translational and rotational motions. Automatic. Université Paul Sabatier (Toulouse 3), 2017. English. 〈tel-01591851〉

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