Space New Technologies
Reza Amjadifard; Ehsan Mousivand; Farhad Bagheroskuee; Shahab Karbasian; Ehsan Kosari
Articles in Press, Accepted Manuscript, Available Online from 09 April 2024
Abstract
The prioritization and verification of space emerging technologies is a multi-step, iterative process that needs to collective intelligence (the participation of all stakeholders), as well as the use of analytical methods to identify requirements. This process begins with identifying specialists who ...
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The prioritization and verification of space emerging technologies is a multi-step, iterative process that needs to collective intelligence (the participation of all stakeholders), as well as the use of analytical methods to identify requirements. This process begins with identifying specialists who have enough knowledge and experience regarding to each technology, and followed by extracting and evaluating the necessary data, prioritizing technology options, identifying challenging technologies and the essential acquisition strategy, and finally prioritizing them. In this article, we implemented a method to identify and prioritize some space technologies which could be used in the electrical power subsystem (EPS) of a satellite. Based on the results, it would be possible to choose the best method to access the required technology; national development or benefiting of available technology in the market. To evaluate the suggested method, the power subsystem components are divided into three categories: electrical power generation sources, energy storage sources, and power electronic circuits. Applying the proposed method shows that the selected technologies are those is recently used in space. This method can also be applied to other subsystems.
Space systems design (spacecraft, satellites, space stations and their equipment)
Omid Shekoofa; Farhad Bagheroskouei; Reza Amjadifard
Volume 15, Issue 3 , September 2022, , Pages 93-108
Abstract
In this paper, the feasibility and performance of using solar arrays equipped with sun concentrators, along with other conventional solar array structures, in CubeSats, is investigated for the first time. For this purpose, seven different structures of solar arrays have been defined and implemented for ...
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In this paper, the feasibility and performance of using solar arrays equipped with sun concentrators, along with other conventional solar array structures, in CubeSats, is investigated for the first time. For this purpose, seven different structures of solar arrays have been defined and implemented for more than 24 different CubeSat configurations from 0.25U to 27U. Then, by calculating important system-level parameters such as power generation density, power generation cost, reliability of solar arrays, and also a newly proposed parameter, called shape fit factor, the performance of these structures for the introduced configurations are evaluated and compared. To this end, and by considering rational coefficients, a cost function consisting of the four above-mentioned parameters is defined as the degree of merit of different solar array structures used in each CubeSat configuration. The results show that alongside the use of deployable solar arrays, using concentrating solar arrays can provide new capabilities for CubeSats to overcome the challenge of generating sufficient power.
O. Shekoofa; M. Taherbane
Volume 2, Issue 2 , July 2009, , Pages 39-49
Abstract
This paper intends to study the impacts of orbit parameters change and evaluate their importance in Electrical Power Subsystem (EPS) design. Two main objectives have been followed in this research: 1) understanding the impacts of the orbital parameters change and the mechanisms of their interactions ...
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This paper intends to study the impacts of orbit parameters change and evaluate their importance in Electrical Power Subsystem (EPS) design. Two main objectives have been followed in this research: 1) understanding the impacts of the orbital parameters change and the mechanisms of their interactions with the EPS design and operation, 2) evaluation of the importance of their effects. To this end, a typical cube satellite has been considered in different LEO orbits, to investigate the impacts of variation in the main orbit parameters e. g. altitude and inclination angle. Then the sizing, operation and performance of power sources have been evaluated via comparing the results of in-orbit simulations of EPS operation. In addition, some indirect impacts of the orbit parameters change are evaluated, by analysis and calculation of the interaction between EPS and other subsystems such as Telecommunication and Telemetery (TMTC), Attitude Determination and Control Subsystem (ADCS) and Thermal Control. The results show how the sizing and operation of solar array and battery are under the influence of orbit parameters change via certain factors such as orbit period, duration and the fraction of eclipse to sunlit phases, received solar irradiance by solar panels, and received thermal fluxes from the sun. According to the acquired results, any altitude increment leads to have better margins in power source sizing but there is an optimum value for inclination angle from this point of view.
