In this research work, a structural optimization methodology is applied to generate a Frame model that meets CubeSat Design Standards. The frame is further subjected to software simulation that encapsulates worst case launch scenarios. The validity of the frame design has been demonstrated by quasi-static and modal analyses, with the results being verified analytically using direct stiffness approach. All subsystems in this study were modelled as remote masses at their Centre of Gravity (C.G) positions, considering their Moments of Inertia (M.I). The mass location analysis was done for a presumed internal configuration with the subsystems arranged such that the Centre of Gravity (C.G) and Moment of Inertia (M.I) values satisfy the launch vehicle constraints. The mass of the proposed structure has been reviewed to meet design mass requirements of a picosatellite structure as a subsystem with a mass less than 20 per cent of overall design mass of 1.33kg. The frame is modelled to bear the on-board electronics without transferring significant load to these delicate electronics that represent different subsystems. The failure analysis of the final structure design indicates very infinitesimal resultant displacement of 1.573 x 10-2mm which is far less than a millimetre and a Factor of safety of 2.06. The minimum natural frequency for the first mode of free vibration of the final design structure obtained to be 199.32 Hz indicating very high structural stiffness. The worst-case harmonic and random vibration analyses have been performed on the frame-PCBs assembly. The maximum structural responses- displacement and stress- at critical points on the Printed Circuit Boards (PCBs) yielded 3.733 x 10-4mm and 98666.7N/m2 respectively for harmonic excitation. and 1.715 x 10-1mm and 33090298N/m2 respectively for random vibration. The peak stress values compared to material yield stress indicate that the subsystems would remain safe under severe launch loading conditions.
| Published in | American Journal of Mechanical and Industrial Engineering (Volume 1, Issue 3) |
| DOI | 10.11648/j.ajmie.20160103.17 |
| Page(s) | 74-84 |
| Creative Commons |
This is an Open Access article, distributed under the terms of the Creative Commons Attribution 4.0 International License (http://creativecommons.org/licenses/by/4.0/), which permits unrestricted use, distribution and reproduction in any medium or format, provided the original work is properly cited. |
| Copyright |
Copyright © The Author(s), 2024. Published by Science Publishing Group |
Vibration, Simulation, Picosatellite Structure, Optimization, Analysis
| [1] | Sarafin, T. P, Larson W. J., Spacecraft Structures and Mechanisms-From Concept to Launch. Microcosm Press and Kluwer Academic Publishers, Torrance, CA, pp. 523-524, 1995 |
| [2] | Pierlot, G., OUFTI-1: Flight System Configuration and Structural Analysis, Aerospace and Mechanical Engineering Department, University of Liege, pp. 1-2, June 2009 |
| [3] | Cihan, M., A Methodology for the Structural Analysis of CubeSat, Istanbul Technical University, Faculty of Aeronautics and Astronautics, pp. 14-18, Jan. 2008. |
| [4] | Paluszek, M., De Castro, E., Hyland, D., The CubeSat book, Plainsboro, New Jersey, pp. 3, 2010. |
| [5] | Moustafa E., Abdul R. E., Zafar M., Emirates Aviation College CubeSat Project: Tuning of Natural Modes, Static and Dynamic Analyses of the Strength Model, Aeronautical Engineering Department, Emirates Aviation College, Dubai, UAE, pp. 29-32, 2011. |
| [6] | Srikanth R., Nagaraj S. N., Dynamic Analysis and Verification of Structurally Optimized Nano-Satellite Systems, Journal of Aerospace Science and Technology 1, doi: 10.17265/2332-8258/2015.02.005, pp. 78-90, 2015. |
| [7] | http://www.sapagroup.com/en/na/profiles/6061-t6-aluminium-properties/. Retrieved in June, 2014 |
| [8] | Munakata, R., CubeSat Design Specification, Revision 12, Calpoly SLO, pp. 7-9, 2009. |
| [9] | Stanislav, I. U., Dnepr Space Launch System (SLS) User Guide, completely revised issue 2, Moscow, pp. 54-56, Nov., 2001. |
| [10] | Wong, S., Whipple, L., Dolengewicz, J., The Next Generation CubeSat: A Modular and Adaptable CubeSat Frame Design, California Polytechnic State University, San Luis Obispo, pp. 40-41, 2010. |
| [11] | Wijker, J., Spacecraft Structures, Springer-Verlag Berlin Heidelberg, 15-16, 107-108, 2008. |
| [12] | Budynas, R. G., Nisbett, J. K., Shigley’s Mechanical Engineering Design-9th Ed. McGraw-Hill Companies, Inc., 1221 Avenue of Americas, New York, NY 10020, pp. 437-438, 2011. |
APA Style
Anselm Chukwuemeka Okolie, Spencer O. Onuh, Yusuf T. Olatunbosun, Matthew S. Abolarin. (2016). Design Optimization of Pico-satellite Frame for Computational Analysis and Simulation. American Journal of Mechanical and Industrial Engineering, 1(3), 74-84. https://doi.org/10.11648/j.ajmie.20160103.17
ACS Style
Anselm Chukwuemeka Okolie; Spencer O. Onuh; Yusuf T. Olatunbosun; Matthew S. Abolarin. Design Optimization of Pico-satellite Frame for Computational Analysis and Simulation. Am. J. Mech. Ind. Eng. 2016, 1(3), 74-84. doi: 10.11648/j.ajmie.20160103.17
Share This Article
Twitter
Linked In
Facebook
Copy
Download@article{10.11648/j.ajmie.20160103.17,
author = {Anselm Chukwuemeka Okolie and Spencer O. Onuh and Yusuf T. Olatunbosun and Matthew S. Abolarin},
title = {Design Optimization of Pico-satellite Frame for Computational Analysis and Simulation},
journal = {American Journal of Mechanical and Industrial Engineering},
volume = {1},
number = {3},
pages = {74-84},
doi = {10.11648/j.ajmie.20160103.17},
url = {https://doi.org/10.11648/j.ajmie.20160103.17},
eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ajmie.20160103.17},
abstract = {In this research work, a structural optimization methodology is applied to generate a Frame model that meets CubeSat Design Standards. The frame is further subjected to software simulation that encapsulates worst case launch scenarios. The validity of the frame design has been demonstrated by quasi-static and modal analyses, with the results being verified analytically using direct stiffness approach. All subsystems in this study were modelled as remote masses at their Centre of Gravity (C.G) positions, considering their Moments of Inertia (M.I). The mass location analysis was done for a presumed internal configuration with the subsystems arranged such that the Centre of Gravity (C.G) and Moment of Inertia (M.I) values satisfy the launch vehicle constraints. The mass of the proposed structure has been reviewed to meet design mass requirements of a picosatellite structure as a subsystem with a mass less than 20 per cent of overall design mass of 1.33kg. The frame is modelled to bear the on-board electronics without transferring significant load to these delicate electronics that represent different subsystems. The failure analysis of the final structure design indicates very infinitesimal resultant displacement of 1.573 x 10-2mm which is far less than a millimetre and a Factor of safety of 2.06. The minimum natural frequency for the first mode of free vibration of the final design structure obtained to be 199.32 Hz indicating very high structural stiffness. The worst-case harmonic and random vibration analyses have been performed on the frame-PCBs assembly. The maximum structural responses- displacement and stress- at critical points on the Printed Circuit Boards (PCBs) yielded 3.733 x 10-4mm and 98666.7N/m2 respectively for harmonic excitation. and 1.715 x 10-1mm and 33090298N/m2 respectively for random vibration. The peak stress values compared to material yield stress indicate that the subsystems would remain safe under severe launch loading conditions.},
year = {2016}
}
TY - JOUR T1 - Design Optimization of Pico-satellite Frame for Computational Analysis and Simulation AU - Anselm Chukwuemeka Okolie AU - Spencer O. Onuh AU - Yusuf T. Olatunbosun AU - Matthew S. Abolarin Y1 - 2016/10/31 PY - 2016 N1 - https://doi.org/10.11648/j.ajmie.20160103.17 DO - 10.11648/j.ajmie.20160103.17 T2 - American Journal of Mechanical and Industrial Engineering JF - American Journal of Mechanical and Industrial Engineering JO - American Journal of Mechanical and Industrial Engineering SP - 74 EP - 84 PB - Science Publishing Group SN - 2575-6060 UR - https://doi.org/10.11648/j.ajmie.20160103.17 AB - In this research work, a structural optimization methodology is applied to generate a Frame model that meets CubeSat Design Standards. The frame is further subjected to software simulation that encapsulates worst case launch scenarios. The validity of the frame design has been demonstrated by quasi-static and modal analyses, with the results being verified analytically using direct stiffness approach. All subsystems in this study were modelled as remote masses at their Centre of Gravity (C.G) positions, considering their Moments of Inertia (M.I). The mass location analysis was done for a presumed internal configuration with the subsystems arranged such that the Centre of Gravity (C.G) and Moment of Inertia (M.I) values satisfy the launch vehicle constraints. The mass of the proposed structure has been reviewed to meet design mass requirements of a picosatellite structure as a subsystem with a mass less than 20 per cent of overall design mass of 1.33kg. The frame is modelled to bear the on-board electronics without transferring significant load to these delicate electronics that represent different subsystems. The failure analysis of the final structure design indicates very infinitesimal resultant displacement of 1.573 x 10-2mm which is far less than a millimetre and a Factor of safety of 2.06. The minimum natural frequency for the first mode of free vibration of the final design structure obtained to be 199.32 Hz indicating very high structural stiffness. The worst-case harmonic and random vibration analyses have been performed on the frame-PCBs assembly. The maximum structural responses- displacement and stress- at critical points on the Printed Circuit Boards (PCBs) yielded 3.733 x 10-4mm and 98666.7N/m2 respectively for harmonic excitation. and 1.715 x 10-1mm and 33090298N/m2 respectively for random vibration. The peak stress values compared to material yield stress indicate that the subsystems would remain safe under severe launch loading conditions. VL - 1 IS - 3 ER -
Information
Email: