TY - JOUR
T1 - Comparison of Peak Power Tracking Based Electric Power System Architectures for CubeSats
AU - Edpuganti, Amarendra
AU - Khadkikar, Vinod
AU - Zeineldin, Hatem
AU - Moursi, Mohamed Shawky El
AU - Al Hosani, Mohamed
N1 - Funding Information:
Manuscript received July 31, 2020; revised November 30, 2020; accepted January 15, 2021. Date of publication January 29, 2021; date of current version May 19, 2021. Paper 2020-SECSC-0835.R1, presented at the 2020 IEEE International Conference on Power Electronics, Smart Grid and Renewable Energy, Kochi, India, Jan. 2–4, and approved for publication in the IEEE TRANSACTIONS ON INDUSTRY APPLICATIONS by the Renewable and Sustainable Energy Conversion Systems Committee of the IEEE Industry Applications Society. This work was supported by the Masdar Institute (now Khalifa University), Abu Dhabi, UAE under Cooperative Agreement between the Masdar Institute and the Massachusetts Institute of Technology (MIT), Cambridge, MA, USA under Grant 02/MI/MIT/CP/11/07633/GEN/G/00. (Corresponding author: Amaren-dra Edpuganti.) Amarendra Edpuganti is with the Advanced Power and Energy Center, Electrical Engineering and Computer Science Department, Khalifa University, Abu Dhabi, UAE (e-mail: [email protected]).
Publisher Copyright:
© 1972-2012 IEEE.
PY - 2021/5/1
Y1 - 2021/5/1
N2 - CubeSats have been widely used for space research due to lower cost and faster development. The electric power system (EPS) is one of the key subsystems of CubeSat which powers all the other subsystems. One of the important steps in the EPS design is the selection of EPS architecture which should be done considering overall efficiency, battery size, reliability, and simplicity of control. In the literature, a general comparison between different architectures is performed without considering the mission parameters, power generation profile, and load profile based on the operational modes. Thus, the best possible EPS architecture may not be selected in the design phase. Therefore, the main objective of this article is to develop a systematic methodology to compare various peak power tracking EPS architectures of CubeSat in terms of orbital efficiency for all possible modes of operation, component count, reliability, and battery size to meet the required number of cycles of charge/discharge for the given mission duration. The proposed methodology has been demonstrated using the real data and scenarios of MYSAT-1, which is a 1U CubeSat developed and launched by Khalifa University. The results demonstrate that EPS architecture with series-connected maximum power tracking converters for solar panels and unregulated dc-bus has the highest efficiency for all operating modes, lower component count, higher reliability, and minimum battery capacity or longer lifetime for the same battery specifications.
AB - CubeSats have been widely used for space research due to lower cost and faster development. The electric power system (EPS) is one of the key subsystems of CubeSat which powers all the other subsystems. One of the important steps in the EPS design is the selection of EPS architecture which should be done considering overall efficiency, battery size, reliability, and simplicity of control. In the literature, a general comparison between different architectures is performed without considering the mission parameters, power generation profile, and load profile based on the operational modes. Thus, the best possible EPS architecture may not be selected in the design phase. Therefore, the main objective of this article is to develop a systematic methodology to compare various peak power tracking EPS architectures of CubeSat in terms of orbital efficiency for all possible modes of operation, component count, reliability, and battery size to meet the required number of cycles of charge/discharge for the given mission duration. The proposed methodology has been demonstrated using the real data and scenarios of MYSAT-1, which is a 1U CubeSat developed and launched by Khalifa University. The results demonstrate that EPS architecture with series-connected maximum power tracking converters for solar panels and unregulated dc-bus has the highest efficiency for all operating modes, lower component count, higher reliability, and minimum battery capacity or longer lifetime for the same battery specifications.
KW - CubeSat
KW - dc-dc converters
KW - electric power system (EPS)
KW - nanosatellites
UR - http://www.scopus.com/inward/record.url?scp=85100461511&partnerID=8YFLogxK
U2 - 10.1109/TIA.2021.3055449
DO - 10.1109/TIA.2021.3055449
M3 - Article
AN - SCOPUS:85100461511
SN - 0093-9994
VL - 57
SP - 2758
EP - 2768
JO - IEEE Transactions on Industry Applications
JF - IEEE Transactions on Industry Applications
IS - 3
M1 - 9340300
ER -
