Design of a control moment gyroscope for small satellites

The primary aim of this project is to design a Control Moment Gyroscope (CMG) prototype for single axis control of an agile small satellite. The design should be small, compact and lightweight. Miniature motors and aluminum material were used to reduce the size and weight of the prototype. The overa...

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Main Author: Tan, Calvin Xian Yang.
Other Authors: Low Kay Soon
Format: Final Year Project
Language:English
Published: 2013
Subjects:
Online Access:http://hdl.handle.net/10356/53551
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Institution: Nanyang Technological University
Language: English
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spelling sg-ntu-dr.10356-535512023-03-04T18:43:27Z Design of a control moment gyroscope for small satellites Tan, Calvin Xian Yang. Low Kay Soon Sunil Chandrakant Joshi School of Mechanical and Aerospace Engineering DRNTU::Engineering::Mechanical engineering::Control engineering The primary aim of this project is to design a Control Moment Gyroscope (CMG) prototype for single axis control of an agile small satellite. The design should be small, compact and lightweight. Miniature motors and aluminum material were used to reduce the size and weight of the prototype. The overall prototype has a dimension of 12.5 x 12.5 x 12.5 cm and weighs 1.6 kg, which is significantly smaller and lighter than conventional CMG. Testing of the prototype design was conducted to fine-tune the controller gain values in order to achieve optimal motor responses. Furthermore, gimbal rate testing was conducted to validate the frictional losses within the gearing system. The results indicated that frictional losses were minimal. The controller was also capable of executing gimbal angle command sequence specified by the user. Simulation results were obtained based on a small satellite mathematical model that used CMG actuation. Simulation results indicated that the satellite was capable of high slew rate (3o/s) using CMG actuators. Experimentation using ECP model 750 CMG was conducted to validate the mathematical model. Prior to experimentation, the setup was integrated to SIMULINK environment to enhance the usability of the data collected. Experimental results obtained were unable to fully validate the model due to the effect of friction. Future testing of the prototype design on an air-bearing table will be conducted to validate the mathematical model as well as the feasibility of the CMG design. Bachelor of Engineering (Aerospace Engineering) 2013-06-05T03:46:35Z 2013-06-05T03:46:35Z 2013 2013 Final Year Project (FYP) http://hdl.handle.net/10356/53551 en Nanyang Technological University 96 p. application/pdf
institution Nanyang Technological University
building NTU Library
continent Asia
country Singapore
Singapore
content_provider NTU Library
collection DR-NTU
language English
topic DRNTU::Engineering::Mechanical engineering::Control engineering
spellingShingle DRNTU::Engineering::Mechanical engineering::Control engineering
Tan, Calvin Xian Yang.
Design of a control moment gyroscope for small satellites
description The primary aim of this project is to design a Control Moment Gyroscope (CMG) prototype for single axis control of an agile small satellite. The design should be small, compact and lightweight. Miniature motors and aluminum material were used to reduce the size and weight of the prototype. The overall prototype has a dimension of 12.5 x 12.5 x 12.5 cm and weighs 1.6 kg, which is significantly smaller and lighter than conventional CMG. Testing of the prototype design was conducted to fine-tune the controller gain values in order to achieve optimal motor responses. Furthermore, gimbal rate testing was conducted to validate the frictional losses within the gearing system. The results indicated that frictional losses were minimal. The controller was also capable of executing gimbal angle command sequence specified by the user. Simulation results were obtained based on a small satellite mathematical model that used CMG actuation. Simulation results indicated that the satellite was capable of high slew rate (3o/s) using CMG actuators. Experimentation using ECP model 750 CMG was conducted to validate the mathematical model. Prior to experimentation, the setup was integrated to SIMULINK environment to enhance the usability of the data collected. Experimental results obtained were unable to fully validate the model due to the effect of friction. Future testing of the prototype design on an air-bearing table will be conducted to validate the mathematical model as well as the feasibility of the CMG design.
author2 Low Kay Soon
author_facet Low Kay Soon
Tan, Calvin Xian Yang.
format Final Year Project
author Tan, Calvin Xian Yang.
author_sort Tan, Calvin Xian Yang.
title Design of a control moment gyroscope for small satellites
title_short Design of a control moment gyroscope for small satellites
title_full Design of a control moment gyroscope for small satellites
title_fullStr Design of a control moment gyroscope for small satellites
title_full_unstemmed Design of a control moment gyroscope for small satellites
title_sort design of a control moment gyroscope for small satellites
publishDate 2013
url http://hdl.handle.net/10356/53551
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