A class of globally stabilizing feedback controllers for the orbital rendezvous problem

Abstract

Summary The development of feedback control systems for autonomous orbital rendezvous is a key technological challenge for next‐generation space missions. This paper presents a new class of control laws for the orbital rendezvous problem. The controllers belonging to this class are guaranteed to globally asymptotically stabilize the relative dynamics of two satellites in circular or elliptic orbits. The proposed design procedure builds on control techniques for nonlinear systems in cascade form, by exploiting the geometric properties of the orbital element description of the satellite motion. A numerical simulation of a formation flying mission demonstrates the effectiveness of this approach for long‐range and low‐thrust rendezvous operations. Copyright © 2017 John Wiley & Sons, Ltd.

Diseño de misión, síntesis de factores operacionales y representaciones del segmento espacial, caso FACSAT y EMFF

“…Otro método para la representación de los sistemas en órbita es planteado en Leomanni et al (2017), donde los elementos orbitales son los parámetros específicos con los que se modelan los cuerpos en órbita y se definen los controladores para el seguimiento de formaciones con las estimaciones cualitativas de robustez características del sistema.…”

Finite‐time attitude tracking control and vibration suppression for flexible spacecraft

“…[3][4][5] Hence, it is important to realize high-accuracy attitude tracking for flexible spacecraft. [6][7][8] Many methods have been proposed to deal with the problem of flexible vibration for flexible spacecraft. [9][10][11] There are two main types of approaches to eliminate the flexible vibration, namely, passive vibration suppression and active vibration suppression.…”

“…However, high‐attitude tracking control performance is essential for many space missions such as Earth observation, satellite surveillance, navigation, and spacecraft formation flying 3‐5 . Hence, it is important to realize high‐accuracy attitude tracking for flexible spacecraft 6‐8 …”

Satellite Relative Motion Modeling and Estimation via Nodal Elements

“…References [17,18] present impulsive maneuvering strategies able to minimize collision risk for spacecraft in close formation. Feedback solutions to the continuous-thrust orbital transfer and rendezvous control problems have been proposed in [21][22][23][24]. State estimation with ROE has been investigated in [25,26].…”