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44 Channels Multi-sensors Interface CMOS IC for Telemetry Application Read chapter Read first chapter

2020 | OriginalPaper | Chapter

Mission and Control Configuration for Spin to Three-Axis Stabilization for Small Satellite

Authors : A. L. Satheesha, S. Kannan, M. P. Ramachandran

Published in: Advances in Small Satellite Technologies

Publisher: Springer Singapore

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Abstract

Describes the mission, control and attitude determination meant for spin stabilization to three-axis stabilization by using momentum bias system. Advantage of the proposed minimal configuration is better for small satellite using off-the-shelf component. There is clear advantage to spin up and spin down of the wheel in this configuration. Attitude determination is now simpler and reliable for the payload pointing to earth or solar panel tracking the sun when the pitch is held to orbit normal.

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previous chapter Real-Time Autonomous Navigation Scheme for Pointing Small Data Relay Satellite to LEO Using NavIC and GNSS Measurements
next chapter Slew Rate and Control Constrained Spacecraft Attitude Maneuver with Reaction Wheel Failure
Literature
1.
Boshuizen C, Mason J, Klupar P, Spanhake S Results from the planet labs flock constellation. In: 28th annual AIAA/USU conference on small satellites
2.
Natarajan P, Pandey PN, Agrwal VK, Malik NK (2007) Autonomous spin axis and spin rate control for hamsat. In: 58th international astronautical congress
3.
Thompson RH Magnetometer bias determination and spin-axis attitude estimation for the AMPTE mission. J Guid 7(4)
Metadata
Title
Mission and Control Configuration for Spin to Three-Axis Stabilization for Small Satellite
Authors
A. L. Satheesha
S. Kannan
M. P. Ramachandran
Copyright Year
2020
Publisher
Springer Singapore
Book
Advances in Small Satellite Technologies

Print ISBN: 978-981-15-1723-5

Electronic ISBN: 978-981-15-1724-2

Copyright Year: 2020

DOI
https://doi.org/10.1007/978-981-15-1724-2_11

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