Open AccessOutput feedback elliptical orbital rendezvous via state‐dependent Riccati differential equations
Author(s) -
Cui NaiGang,
Zhou Bin,
Duan GuangRen
Publication year - 2013
Publication title -
iet control theory and applications
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 1.059
H-Index - 108
eISSN - 1751-8652
pISSN - 1751-8644
DOI - 10.1049/iet-cta.2012.0907
Subject(s) - control theory (sociology) , riccati equation , rendezvous , observer (physics) , controller (irrigation) , spacecraft , mathematics , differential (mechanical device) , stability theory , state (computer science) , differential equation , computer science , control (management) , mathematical analysis , physics , algorithm , nonlinear system , quantum mechanics , astronomy , artificial intelligence , agronomy , biology , thermodynamics
This article studies spacecraft rendezvous with the target spacecraft in an arbitrary elliptical orbit. Based on the linearised Tschauner–Hempel equations, state‐dependent Riccati differential equation (RDE)‐based approaches are proposed to solve the problem. An observer‐based output feedback controller is established. To implement the proposed controller, only some forward‐type RDEs need to be integrated online, indicating that the controllers can be implemented online as long as some positive‐definite initial conditions are given. Moreover, it is shown analytically that the closed‐loop system under the proposed feedback controller is exponentially asymptotically stable. Numerical examples show the effectiveness of the proposed approach.