Angular-momentum-based sizing of control moment gyro cluster for an agile spacecraft
File(s)
Accepted version
Author(s)
Mony, Abhilash
Hablani, Hari B
Paranjape, Aditya A
Type
Journal Article
Abstract
The sizing of a control moment gyro (CMG) cluster is covered sparsely in literature, but it is of considerable interest
2 to a practicing engineer. In this paper, the sizing of a cluster of four control moment gyros is investigated based on the
mission angular momentum requirement of a typical agile spacecraft. The CMG skew angle β and individual CMG
angular momentum h are determined as part of the sizing. The work focuses on the sizing of a minimally redundant
cluster of four CMGs in a pyramid and roof-type arrangement considering their external angular momentum
surfaces. Two approaches are discussed: the first considers maximum angular momentum about individual axis
separately, and the second considers the momentum requirement about two axes simultaneously. The internal
momentum surfaces of the CMG clusters are analyzed. Gimbal angle desaturation and the fuel consumed for it by
the roof-type and pyramid configurations are also examined. Both the four CMG clusters are able to meet the
maximum nonspherical angular momentum demanded by a typical mission about each axes. However, using method
1, the cluster is able to generate only 88% of the two-axis mission demand. The clusters meet the mission demand
completely with method 2 using 20% more angular momentum per CMG and an increase in skew angle by 8–11°
compared to method 1. The 20% increase in momentum increases power consumption by 11%. For a typical gimbal
angle desaturation, the roof-type cluster uses 8.5% more fuel than the pyramid arrangement. However, the former
has only one major internal singular surface in contrast with seven for the latter. This makes the roof-type
arrangement very desirable to keep the singularity avoidance algorithm simple and amenable with the CMGs
3 operating within the momentum capability, and achieve the required spacecraft agility.
2 to a practicing engineer. In this paper, the sizing of a cluster of four control moment gyros is investigated based on the
mission angular momentum requirement of a typical agile spacecraft. The CMG skew angle β and individual CMG
angular momentum h are determined as part of the sizing. The work focuses on the sizing of a minimally redundant
cluster of four CMGs in a pyramid and roof-type arrangement considering their external angular momentum
surfaces. Two approaches are discussed: the first considers maximum angular momentum about individual axis
separately, and the second considers the momentum requirement about two axes simultaneously. The internal
momentum surfaces of the CMG clusters are analyzed. Gimbal angle desaturation and the fuel consumed for it by
the roof-type and pyramid configurations are also examined. Both the four CMG clusters are able to meet the
maximum nonspherical angular momentum demanded by a typical mission about each axes. However, using method
1, the cluster is able to generate only 88% of the two-axis mission demand. The clusters meet the mission demand
completely with method 2 using 20% more angular momentum per CMG and an increase in skew angle by 8–11°
compared to method 1. The 20% increase in momentum increases power consumption by 11%. For a typical gimbal
angle desaturation, the roof-type cluster uses 8.5% more fuel than the pyramid arrangement. However, the former
has only one major internal singular surface in contrast with seven for the latter. This makes the roof-type
arrangement very desirable to keep the singularity avoidance algorithm simple and amenable with the CMGs
3 operating within the momentum capability, and achieve the required spacecraft agility.
Date Issued
2022-09
Date Acceptance
2022-03-24
Citation
Journal of Guidance, Control, and Dynamics: devoted to the technology of dynamics and control, 2022, 45 (9), pp.1627-1643
ISSN
0731-5090
Publisher
American Institute of Aeronautics and Astronautics
Start Page
1627
End Page
1643
Journal / Book Title
Journal of Guidance, Control, and Dynamics: devoted to the technology of dynamics and control
Volume
45
Issue
9
Copyright Statement
Copyright © 2022 by Abhilash Mony, ISRO Inertial Systems Unit. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. All requests for copying and permission to reprint should be submitted to CCC at www.copyright.com; employ the eISSN 1533-3884 to initiate your request. See also AIAA Rights and Permissions www.aiaa.org/randp.
Identifier
https://www.webofscience.com/api/gateway?GWVersion=2&SrcApp=PARTNER_APP&SrcAuth=LinksAMR&KeyUT=WOS:000803773200001&DestLinkType=FullRecord&DestApp=ALL_WOS&UsrCustomerID=a2bf6146997ec60c407a63945d4e92bb
Subjects
Engineering
Engineering, Aerospace
Instruments & Instrumentation
Science & Technology
SINGULARITY ANALYSIS
Technology
Publication Status
Published
Date Publish Online
2022-05-25