Study for femto satellites using micro control moment gyroscope

Mark Post; Ralf Bauer; Junquan Li; Regina Lee

doi:10.1109/AERO.2016.7500721

Study for femto satellites using micro control moment gyroscope

Mark Post, Ralf Bauer, Junquan Li, Regina Lee

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution book

3 Citations (Scopus)

451 Downloads (Pure)

Abstract

Abstract— Femto-satellites can be used for distributed space missions that can require hundreds to thousands of satellites for real time, distributed, multi-point networks to accomplish remote sensing and science objectives. While suitable sensors are available using micro-electro-mechanical system technology, most femto-satellite designs have no attitude control capability due to the power and size constraints on attitude control actuators. A novel femto-satellite design that uses a micro-electro-mechanical system Control Moment Gyroscope is studied in this paper. We focus on the principal design, modelling, and discussion of the proposed Control Moment Gyroscope while detailing a controllable femto-satellite design that can make use of attitude control for simple sensing missions.

Original language	English
Title of host publication	2016 IEEE Aerospace Conference
Place of Publication	New York
Publisher	IEEE
Pages	1-8
Number of pages	8
Volume	2016
ISBN (Print)	9781479953806
DOIs	https://doi.org/10.1109/AERO.2016.7500721
Publication status	Published - 5 Mar 2016
Event	2016 IEEE Aerospace Conference - Yellowstone Conference Center, Big Sky, Montana, United States Duration: 5 Mar 2016 → 12 Mar 2016

Conference

Conference	2016 IEEE Aerospace Conference
Country/Territory	United States
City	Big Sky, Montana
Period	5/03/16 → 12/03/16

Keywords

femto-satellites
control moment gyroscope
micro electro mechanical system

Access to Document

10.1109/AERO.2016.7500721

Post-etal-2016-study-for-femto-satellites-using-micro-control-moment-gyroscopeAccepted author manuscript, 1.25 MB

Cite this

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title = "Study for femto satellites using micro control moment gyroscope",

abstract = "Abstract— Femto-satellites can be used for distributed space missions that can require hundreds to thousands of satellites for real time, distributed, multi-point networks to accomplish remote sensing and science objectives. While suitable sensors are available using micro-electro-mechanical system technology, most femto-satellite designs have no attitude control capability due to the power and size constraints on attitude control actuators. A novel femto-satellite design that uses a micro-electro-mechanical system Control Moment Gyroscope is studied in this paper. We focus on the principal design, modelling, and discussion of the proposed Control Moment Gyroscope while detailing a controllable femto-satellite design that can make use of attitude control for simple sensing missions.",

keywords = "femto-satellites, control moment gyroscope, micro electro mechanical system",

author = "Mark Post and Ralf Bauer and Junquan Li and Regina Lee",

note = "(c) 2016 IEEE. Personal use of this material is permitted. Permission from IEEE must be obtained for all other users, including reprinting/ republishing this material for advertising or promotional purposes, creating new collective works for resale or redistribution to servers or lists, or reuse of any copyrighted components of this work in other works; 2016 IEEE Aerospace Conference ; Conference date: 05-03-2016 Through 12-03-2016",

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AU - Post, Mark

AU - Bauer, Ralf

AU - Li, Junquan

AU - Lee, Regina

N1 - (c) 2016 IEEE. Personal use of this material is permitted. Permission from IEEE must be obtained for all other users, including reprinting/ republishing this material for advertising or promotional purposes, creating new collective works for resale or redistribution to servers or lists, or reuse of any copyrighted components of this work in other works

PY - 2016/3/5

Y1 - 2016/3/5

N2 - Abstract— Femto-satellites can be used for distributed space missions that can require hundreds to thousands of satellites for real time, distributed, multi-point networks to accomplish remote sensing and science objectives. While suitable sensors are available using micro-electro-mechanical system technology, most femto-satellite designs have no attitude control capability due to the power and size constraints on attitude control actuators. A novel femto-satellite design that uses a micro-electro-mechanical system Control Moment Gyroscope is studied in this paper. We focus on the principal design, modelling, and discussion of the proposed Control Moment Gyroscope while detailing a controllable femto-satellite design that can make use of attitude control for simple sensing missions.

AB - Abstract— Femto-satellites can be used for distributed space missions that can require hundreds to thousands of satellites for real time, distributed, multi-point networks to accomplish remote sensing and science objectives. While suitable sensors are available using micro-electro-mechanical system technology, most femto-satellite designs have no attitude control capability due to the power and size constraints on attitude control actuators. A novel femto-satellite design that uses a micro-electro-mechanical system Control Moment Gyroscope is studied in this paper. We focus on the principal design, modelling, and discussion of the proposed Control Moment Gyroscope while detailing a controllable femto-satellite design that can make use of attitude control for simple sensing missions.

KW - femto-satellites

KW - control moment gyroscope

KW - micro electro mechanical system

U2 - 10.1109/AERO.2016.7500721

DO - 10.1109/AERO.2016.7500721

M3 - Conference contribution book

SN - 9781479953806

VL - 2016

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BT - 2016 IEEE Aerospace Conference

PB - IEEE

CY - New York

T2 - 2016 IEEE Aerospace Conference

Y2 - 5 March 2016 through 12 March 2016

ER -

Study for femto satellites using micro control moment gyroscope

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Keywords

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