Zero-propellant maneuver guidance

Author

Bedrossian, Nazareth S. ; Bhatt, Sagar ; Kang, Wei ; Ross, I. Michael

Volume

29

Issue

5

fYear

2009

Firstpage

53

Lastpage

73

Abstract

This article deals with a zero-propellant maneuver guidance (ZPM) architecture to provide large-angle ISS (International Space Station) rotations. ZPM guidance commands are designed to avoid CMG (control moment gyroscope) momentum saturation. CMG desaturation is required to maintain spacecraft control capability and the manipulator´s direction. The ZPM momentum-optimal trajectories were developed using computational dynamic optimization, these optimal trajectories are used to shape the command to a standard feedback controller. Using ZPM, the need for thrusters as backup to momentum-storage actuators for rotational control is minimized.

Keywords

angular momentum; attitude control; feedback; gyroscopes; optimisation; space vehicles; vehicle dynamics; CMG desaturation; International Space Station; computational dynamic optimization; control moment gyroscope; feedback controller; large-angle ISS rotations; manipulator direction; momentum-optimal trajectories; momentum-storage actuators; rotational control; spacecraft control capability; zero-propellant maneuver guidance architecture; Attitude control; Control systems; Electric motors; International Space Station; Jacobian matrices; Rotors; Space vehicles; Spinning; Torque; Wheels;

fLanguage

English

Journal_Title

Control Systems, IEEE

Publisher

ieee

ISSN

1066-033X

Type

jour

DOI

10.1109/MCS.2009.934089

Filename

5256357