2026-09-25T08:46:46Zhttps://dspace.mit.edu/server/oai/requestoai:dspace.mit.edu:1721.1/97252021-07-05T14:03:20Zcom_1721.1_7582com_1721.1_7581col_1721.1_131023
Seth Lloyd.
Kwon, Hyuk-Sang, 1971-
Massachusetts Institute of Technology. Department of Mechanical Engineering
2005-08-19T19:44:33Z
2005-08-19T19:44:33Z
1998
1998
http://hdl.handle.net/1721.1/9725
42686476
Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Mechanical Engineering, 1998.
Includes bibliographical references (leaves 53-54).
This thesis presents new methods for controlling spacecraft using Control-Moment Gyros (CMGs). CMGs generate torque to change and maintain a spacecraft's orientation. The CMG control system is used specifically to provide three-axis altitude stabilization, precision pointing control and maneuvering capability. Two types of CMGs are used in spacecraft attitude control purpose. Classified by the number of gimbals, they are Double Jimbal Control Moment Gyroscope (DGCMG) and Single Gimbal Control Moment Gyroscope (SGCMG). An SGCMG is often chosen as a torque actuator because an SGCMG has two major advantages over DGCMGs: the torque amplification feature and ease of manufacture. The technical literature discusses altitude control of large spacecraft using three or more SGCMGs. As a case study, the altitude control of rigid spacecraft using two SGCMGs is considered. In this paper, the simplified two-SGCMGs model was made and simulated. The system of interest is nonholonomic and the control strategy is related to motion planning. I demonstrate that often only two SGCMGs are necessary to control the altitude of a spacecraft. This is true when failure of one of the control momentum gyroscopes occurs, two actuators can be used to control the attitude of a rigid spacecraft and arbitrary reorientation maneuvers of the spacecraft can be accomplished. The control strategy where two SGCMGs arc used to control the attitude of the spacecraft was studied and presented.
by Hyuk-Sang Kwon.
S.M.
63 leaves
3580791 bytes
3580552 bytes
application/pdf
application/pdf
eng
Massachusetts Institute of Technology
M.I.T. theses are protected by copyright. They may be viewed from this source for any purpose, but reproduction or distribution in any format is prohibited without written permission. See provided URL for inquiries about permission.
http://dspace.mit.edu/handle/1721.1/7582
Mechanical Engineering
Attitude control of a spacecraft using two SGCMGs
Attitude control of a spacecraft using two single Gimbal control moment gyroscopes
Thesis
application/pdf
false
Publication
unknown
unknown
<Publication xmlns="https://www.openaire.eu/cerif-profile/1.1/" id="fa55758a-f68b-4325-8caf-9609d95edde1">
<Type xmlns="https://www.openaire.eu/cerif-profile/vocab/COAR_Publication_Types">http://purl.org/coar/resource_type/c_1843</Type>
<Language>eng</Language>
<Title>Attitude control of a spacecraft using two SGCMGs</Title>
<Subtitle>Attitude control of a spacecraft using two single Gimbal control moment gyroscopes</Subtitle>
<PublishedIn>
<Publication>
</Publication>
</PublishedIn>
<PublicationDate>1998</PublicationDate>
<Authors>
<Author>
<DisplayName>Kwon, Hyuk-Sang, 1971-</DisplayName>
<Affiliation>
<OrgUnit>
</OrgUnit>
</Affiliation>
</Author>
</Authors>
<Editors>
</Editors>
<Publishers>
<Publisher>
<DisplayName>Massachusetts Institute of Technology</DisplayName>
<OrgUnit />
</Publisher>
</Publishers>
<License>http://dspace.mit.edu/handle/1721.1/7582</License>
<Keyword>Mechanical Engineering</Keyword>
<Abstract>This thesis presents new methods for controlling spacecraft using Control-Moment Gyros (CMGs). CMGs generate torque to change and maintain a spacecraft's orientation. The CMG control system is used specifically to provide three-axis altitude stabilization, precision pointing control and maneuvering capability. Two types of CMGs are used in spacecraft attitude control purpose. Classified by the number of gimbals, they are Double Jimbal Control Moment Gyroscope (DGCMG) and Single Gimbal Control Moment Gyroscope (SGCMG). An SGCMG is often chosen as a torque actuator because an SGCMG has two major advantages over DGCMGs: the torque amplification feature and ease of manufacture. The technical literature discusses altitude control of large spacecraft using three or more SGCMGs. As a case study, the altitude control of rigid spacecraft using two SGCMGs is considered. In this paper, the simplified two-SGCMGs model was made and simulated. The system of interest is nonholonomic and the control strategy is related to motion planning. I demonstrate that often only two SGCMGs are necessary to control the altitude of a spacecraft. This is true when failure of one of the control momentum gyroscopes occurs, two actuators can be used to control the attitude of a rigid spacecraft and arbitrary reorientation maneuvers of the spacecraft can be accomplished. The control strategy where two SGCMGs arc used to control the attitude of the spacecraft was studied and presented.</Abstract>
<Access xmlns="http://purl.org/coar/access_right"
>
</Access>
</Publication>