Output attitude tracking of a formation of spacecraft
نویسندگان
چکیده
This paper will consider the control of spacecraft in a leader-follower formation using attitude measurements only. To analyze the formation under non vanishing disturbances, the concept of uniform practical exponential stability is defined. To ease the Lyapunov analysis a new theorem is provided, giving sufficient conditions for systems that present a cascaded structure to satisfy this definition. Finally, output control is applied to both the leader and follower spacecraft and the stability of the overall system is analyzed through the application of this new result.
منابع مشابه
Active Vibration Suppression of a Nonlinear Flexible Spacecraft
In this article, the issue of attitude control and active vibration suppression of a nonlinear flexible spacecraft is assessed through piezoelectric patches as actuator and sensors. Two controller loops are applied: the inner loop, to make the panel vibration damped through piezoelectric patches; and the outer loop, to perform spacecraft maneuver using the reaction wheel acting on the hub. An o...
متن کاملDesign of Nonlinear Robust Controller and Observer for Control of a Flexible Spacecraft
Two robust nonlinear controllers along with a nonlinear observer have been developed in this study to control a 1D nonlinear flexible spacecraft. The first controller is based on dynamic inversion, while the second one is composed of dynamic inversion and µ-synthesis controllers. The extension of dynamic inversion approach to flexible spacecraft is impeded by the non-minimum phase characteristi...
متن کاملQuaternion-based Finite-time Sliding Mode Controller Design for Attitude Tracking of a Rigid Spacecraft during High-thrust Orbital Maneuver in the Presence of Disturbance Torques
In this paper, a quaternion-based finite-time sliding mode attitude controller is designed for a spacecraft performing high-thrust orbital maneuvers, with cold gas thrusters as its actuators. The proposed controller results are compared with those of a quaternion feedback controller developed for the linearized spacecraft dynamics, in terms of settling time, steady-state error, number of thrust...
متن کاملDecentralized attitude alignment control of spacecraft within a formation without angular velocity measurements ⋆
Abstract: In this paper, we consider the coordinated attitude control problem without velocity measurements. Based on the recently introduced unit quaternion output feedback for the attitude tracking of a rigid body, we present a class of decentralized coordinated control laws to solve the alignment problem for a group of spacecraft within a formation without velocity measurements. The approach...
متن کاملOutput attitude tracking of formation of spacecraft
In this paper we will consider the control of spacecraft in a leader-follower formation using attitude measurements only. To analyze the formation under nonvanishing disturbances, we make use of the concept of uniform semiglobal practical exponential stability. To ease the Lyapunov analysis a new theorem is provided, giving sufficient conditions for systems presenting a cascaded structure to sa...
متن کامل