Orbital and attitude control of a spacecraft around an asteroid

Author

Reyhanoglu, Mahmut ; Kamran, Niloofar N. ; Takahiro, Kuhara

Author_Institution

Phys. Sci. Dept., Embry-Riddle Aeronaut. Univ., Daytona Beach, FL, USA

fYear

2012

fDate

17-21 Oct. 2012

Firstpage

1627

Lastpage

1632

Abstract

The objective of this paper is to design an effective control scheme for an asteroid orbiting satellite. The paper first introduces the dynamics formulation of such satellites and then provides a framework for the control system design. The control objective is to achieve a nadir pointing attitude on a circular equatorial orbit. Lyapunov-based nonlinear feedback laws are constructed to control the rotational and translational motion of the satellite so that the control objective is achieved. Computer simulations are carried out to illustrate the effectiveness of the control laws.

Keywords

Lyapunov methods; artificial satellites; attitude control; control system synthesis; motion control; nonlinear control systems; space vehicles; vehicle dynamics; Lyapunov-based nonlinear feedback laws; asteroid orbiting satellite; circular equatorial orbit; control system design; dynamics formulation; nadir pointing attitude; nonlinear control; rotational motion control; spacecraft attitude control; spacecraft orbital control; translational motion control; Angular velocity; Attitude control; Dynamics; Equations; Orbits; Space vehicles; Vectors; Nonlinear control; asteroid; spacecraft;

fLanguage

English

Publisher

ieee

Conference_Titel

Control, Automation and Systems (ICCAS), 2012 12th International Conference on

Conference_Location

JeJu Island

Print_ISBN

978-1-4673-2247-8

Type

conf

Filename

6393101