Modal analysis, development and modal testing of a nanosatellite structure

An evolution is undergoing in the satellite industry towards “SmallSat” development and is becoming a passion for CubeSat developers and educational institutes as an easy and economical access to space. The development of CubeSat structures using 3D printed materials are even more cost-effective and...

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Main Author: Balaraman, Rajesh Kumar
Other Authors: Sunil Chandrakant Joshi
Format: Thesis-Master by Coursework
Language:English
Published: Nanyang Technological University 2019
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Online Access:http://hdl.handle.net/10356/78962
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Institution: Nanyang Technological University
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spelling sg-ntu-dr.10356-789622023-03-11T17:31:45Z Modal analysis, development and modal testing of a nanosatellite structure Balaraman, Rajesh Kumar Sunil Chandrakant Joshi School of Mechanical and Aerospace Engineering Technical University of Munich MSCJoshi@ntu.edu.sg Engineering::Aeronautical engineering::Materials of construction Engineering::Materials::Mechanical strength of materials An evolution is undergoing in the satellite industry towards “SmallSat” development and is becoming a passion for CubeSat developers and educational institutes as an easy and economical access to space. The development of CubeSat structures using 3D printed materials are even more cost-effective and are extending more opportunities for the educational CubeSat research program. This work describes the fine tuning of Aluminum-ULTEM design of the CubeSat structure, the modal analysis of the structure for the integrity against vibrations during the launch, the development of the satellite vibration model and, the experimentation to verify the modal analysis. A detailed literature survey is carried out for the selection of design approach, materials, manufacturing and geometry optimization for the modelling of the CubeSat structure. The requirement for static and dynamic load tests in launch environment is discussed. The preliminary design of Aluminum-ULTEM structure is fine-tuned for easy assembly and disassembly of the subsystems stacked inside the CubeSat structure. The finalized design model is needed to be analyzed to verify the structural integrity using finite element analysis (FEA) tool, ABAQUS. The natural frequency, sine vibration and random response spectrum analyses are performed at a given acceleration and PSD values during the launching stage. The dummy subsystems characterized from the actual subsystems are designed, developed and assembled inside the structure for modal testing while maintaining the center of gravity within the geometric center. The assembled model is then tested to prove the integrity of Aluminum-ULTEM structure for the given vibration loads at the space environment using vibration shaker. The structure parts are examined to find the defects using electronic microscope. The validation of analyses and tests results confirm that the Aluminum-ULTEM structure has no defects and withholds the integrity of structure during the flight condition. This qualifies the Aluminum-ULTEM CubeSat structure for the launch and flight in the first instance. Master of Science (Aerospace Engineering) 2019-11-13T05:25:22Z 2019-11-13T05:25:22Z 2019 Thesis-Master by Coursework http://hdl.handle.net/10356/78962 en 106 p. application/pdf Nanyang Technological University
institution Nanyang Technological University
building NTU Library
continent Asia
country Singapore
Singapore
content_provider NTU Library
collection DR-NTU
language English
topic Engineering::Aeronautical engineering::Materials of construction
Engineering::Materials::Mechanical strength of materials
spellingShingle Engineering::Aeronautical engineering::Materials of construction
Engineering::Materials::Mechanical strength of materials
Balaraman, Rajesh Kumar
Modal analysis, development and modal testing of a nanosatellite structure
description An evolution is undergoing in the satellite industry towards “SmallSat” development and is becoming a passion for CubeSat developers and educational institutes as an easy and economical access to space. The development of CubeSat structures using 3D printed materials are even more cost-effective and are extending more opportunities for the educational CubeSat research program. This work describes the fine tuning of Aluminum-ULTEM design of the CubeSat structure, the modal analysis of the structure for the integrity against vibrations during the launch, the development of the satellite vibration model and, the experimentation to verify the modal analysis. A detailed literature survey is carried out for the selection of design approach, materials, manufacturing and geometry optimization for the modelling of the CubeSat structure. The requirement for static and dynamic load tests in launch environment is discussed. The preliminary design of Aluminum-ULTEM structure is fine-tuned for easy assembly and disassembly of the subsystems stacked inside the CubeSat structure. The finalized design model is needed to be analyzed to verify the structural integrity using finite element analysis (FEA) tool, ABAQUS. The natural frequency, sine vibration and random response spectrum analyses are performed at a given acceleration and PSD values during the launching stage. The dummy subsystems characterized from the actual subsystems are designed, developed and assembled inside the structure for modal testing while maintaining the center of gravity within the geometric center. The assembled model is then tested to prove the integrity of Aluminum-ULTEM structure for the given vibration loads at the space environment using vibration shaker. The structure parts are examined to find the defects using electronic microscope. The validation of analyses and tests results confirm that the Aluminum-ULTEM structure has no defects and withholds the integrity of structure during the flight condition. This qualifies the Aluminum-ULTEM CubeSat structure for the launch and flight in the first instance.
author2 Sunil Chandrakant Joshi
author_facet Sunil Chandrakant Joshi
Balaraman, Rajesh Kumar
format Thesis-Master by Coursework
author Balaraman, Rajesh Kumar
author_sort Balaraman, Rajesh Kumar
title Modal analysis, development and modal testing of a nanosatellite structure
title_short Modal analysis, development and modal testing of a nanosatellite structure
title_full Modal analysis, development and modal testing of a nanosatellite structure
title_fullStr Modal analysis, development and modal testing of a nanosatellite structure
title_full_unstemmed Modal analysis, development and modal testing of a nanosatellite structure
title_sort modal analysis, development and modal testing of a nanosatellite structure
publisher Nanyang Technological University
publishDate 2019
url http://hdl.handle.net/10356/78962
_version_ 1761781291493097472