Space station Zero-Propellant Maneuver guidance trajectories compared to eigenaxis

Author

Bedrossian, Nazareth ; Bhatt, Sagar

Author_Institution

Manned Space Syst., Charles Stark Draper Lab., Inc., Houston, TX

fYear

2008

fDate

11-13 June 2008

Firstpage

4833

Lastpage

4838

Abstract

The zero-propellant maneuver (ZPM) guidance concept has been used on November 5, 2006, and March 3, 2007 to reorient the International Space Station (ISS) 90 deg and 180 deg respectively with control moment gyroscopes (CMGs) without using any propellant. It will be shown that there are multiple ZPM trajectories that can perform the maneuver non- propulsively. Performing the same maneuver using an eigenaxis path would saturate the CMGs, requiring thrusters to regain attitude control. A condition is derived to explain why the CMGs saturate along the eigenaxis path. Flight results from the two ZPM demonstrations are presented.

Keywords

aerospace control; attitude control; position control; International Space Station; attitude control; control moment gyroscopes; eigenaxis; space station zero-propellant maneuver guidance trajectories; Attitude control; Costs; Gyroscopes; International Space Station; Laboratories; Nonlinear dynamical systems; Propulsion; Space stations; Space vehicles; Vehicle dynamics;

fLanguage

English

Publisher

ieee

Conference_Titel

American Control Conference, 2008

Conference_Location

Seattle, WA

ISSN

0743-1619

Print_ISBN

978-1-4244-2078-0

Electronic_ISBN

0743-1619

Type

conf

DOI

10.1109/ACC.2008.4587259

Filename

4587259