Lyapunov-Floquet Control of Satellite Relative Motion in Elliptic Orbits

被引：16

作者：

Sherrill, Ryan E. ^{[1
]}

Sinclair, Andrew J. ^{[2
]}

Sinha, S. C. ^{[3
]}

Lovell, T. Alan ^{[4
]}

机构：

[1] Auburn Univ, Auburn, AL USA

[2] Auburn Univ, Aerosp Engn, Auburn, AL 36849 USA

[3] Auburn Univ, Mech Engn, Auburn, AL 36849 USA

[4] Air Force Res Lab, Space Vehicles Directorate, Kirtland AFB, NM 87117 USA

来源：

IEEE TRANSACTIONS ON AEROSPACE AND ELECTRONIC SYSTEMS | 2015年 / 51卷 / 04期

关键词：

STATE TRANSITION MATRIX; FEEDBACK-CONTROL; ELEMENTS; LAW;

D O I：

10.1109/TAES.2015.140281

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

This paper proposes a method for continuous-thrust control of satellite formations in elliptic orbits. A previously calculated Lyapunov-Floquet transformation relates the linearized equations of relative motion for elliptic chief orbits to the Hill-Clohessy-Wiltshire equations describing circular chiefs. Using a control law based on Lyapunov-Floquet theory, a time-varying feedback gain is computed that drives a deputy satellite toward rendezvous with an elliptic chief. This control law stabilizes the relative motion across a wide range of chief eccentricities.

引用

页码：2800 / 2810

页数：11

共 38 条

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