Journal ArticleDOI
Electromagnetic formation flight dynamics including reaction wheel gyroscopic stiffening effects
TLDR
In this paper, the equations of motion of a two-spacecraft formation flying array that uses electromagnets as relative position actuators were analyzed for stability and controllability.Abstract:
In this paper, we consider the equations of motion of a two-spacecraft formation flying array that uses electromagnets as relative position actuators. The relative positions of the spacecraft are controlled by the forces generated between the electromagnets on the two spacecraft, and the attitudes of the spacecraft are controlled using reaction wheels. The nonlinear equations of motion for this system are linearized about a nominal operating trajectory, taken to be a steady-state spin maneuver used for deep-space interferometric observation. The linearized equations are analyzed for stability and controllability. Although the open-loop system proves to be unstable, a controllability analysis indicates that the system is fully controllable with the given suite of actuators, and is therefore stabilizable. An optimal linear feedback controller is then designed, and the closed-loop dynamics are simulated. The simulations demonstrate that the closed-loop system is indeed stable, and that linear control is a very promising technique for electromagnetic formation flight systems, despite the nonlinearity of the dynamics.read more
Citations
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Journal ArticleDOI
Propellantless formation flight applications using electromagnetic satellite formations
TL;DR: In this paper, the applicability of EMFF as a means for attitude and translation control of multiple spacecraft maneuvering in close proximity is investigated, and the results of the analysis show the design of the proximity guidance, navigation, and control laws that allow for rapid inspection scenarios.
Journal ArticleDOI
Finite-time control for electromagnetic satellite formations
Guoqiang Zeng,Min Hu +1 more
TL;DR: In this paper, a robust sliding mode controller is designed to achieve trajectory tracking in the presence of model uncertainties and external disturbances, which combines the advantages of linear and terminal sliding mode controls, can guarantee the convergence of tracking errors in finite time rather than in the asymptotic sense.
Journal ArticleDOI
Coupled orbit-attitude dynamics and trajectory tracking control for spacecraft electromagnetic docking
TL;DR: The simplified electromagnetic force/torque model and coupled orbit-attitude dynamics modeling in spacecraft electromagnetic docking are investigated, and an improved sliding mode control scheme based on planned trajectory is proposed.
Journal ArticleDOI
Electromagnetic Formation Flight Testbed Using Superconducting Coils
Journal ArticleDOI
Observer-based control for spacecraft electromagnetic docking
TL;DR: It is proved via Lyapunov analysis that the intermediate observer-based controller can achieve the objective of spacecraft electromagnetic docking with input constraints and in the presence of uncertainties.
References
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Book
Control Engineering: A Modern Approach
TL;DR: This paper focuses on the development of a model for a feedback system that automates the very labor-intensive and therefore expensive and therefore time-heavy and expensive process of modeling.
Journal ArticleDOI
Electromagnetic Formation Flight for Multisatellite Arrays
Edmund Kong,Daniel W. Kwon,Samuel A. Schweighart,Laila Mireille Elias,Raymond J. Sedwick,David Miller +5 more
TL;DR: The use of propellant to maintain the relative orientation of multiple spacecraft in a sparse aperture telescope such as NASA's Terrestrial Planet Finder (TPF) poses several issues, such as fuel depletion, optical contamination, plume impingement, thermal emission, and vibration excitation as discussed by the authors.
Proceedings ArticleDOI
Dynamics and control of electromagnetic satellite formations
Umair Ahsun,David W. Miller +1 more
TL;DR: In this article, the dynamics for a general n-satellite electromagnetic formation (in 2D) is derived for deep space missions and then a non-linear control law using potential functions for the formation control and reconfiguration with collision avoidance is discussed.
Dissertation
Electromagnetic formation flight dipole solution planning
TL;DR: Thesis (Ph D) as mentioned in this paper, Massachusetts Institute of Technology, Dept of Aeronautics and Astronautics, 2005, Section 5.1.2.1