Design of Electrical Power Systems for Satellites

Kapoor, Aashna; Rajak, A. R. Abdul

doi:10.1007/978-981-15-4775-1_33

Cited by 1 publication

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“…Once the power profile is known, the required solar array power production and the power and stored energy of the secondary battery (𝑃 SA , 𝑃 B , and 𝐸 B , respectively) must be calculated to size the EPS. The simplest and widely used approach to obtain 𝑃 SA is described in [8], and has been 2.2 Models implemented in many works, such as [74], [76], [78]- [82]. This method is based on calculating the mean power consumption over a complete operational orbit and considers: 1) the battery works only during eclipse periods and 2) the battery is fully recharged during daylight.…”

Section: Preliminary Design Of Satellite's Electrical Power Subsystemmentioning

confidence: 99%

Analysis and simulation of electric power systems for aerospace Applications

Marín Coca

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The Electrical Power Subsystem (EPS) plays a critical role in satellite design, providing the required electrical energy to operate all on-board systems. Their reliability and efficiency are essential for the success of a space mission, as any failure in this system can have catastrophic consequences. Consequently, a detailed and accurate design of the power subsystem is essential, taking into account several scenarios and contingencies that may arise during the mission. To achieve a reliable and efficient design, accurate models of the main components are required. These models facilitate both preliminary designs and complex simulations, allowing a comprehensive assessment of the performance of the power subsystem under different operational conditions. Within this context, this research proposes novel models and methods to improve the accuracy and reliability of the design of the power subsystem, with a specific focus on secondary energy sources.The first contribution presents a new methodology for conducting preliminary designs of electrical power subsystems in satellites, considering different architectures, variable efficiencies, and the utilization of batteries during both eclipse and daylight periods. The second contribution encompasses new models for Li-ion batteries. On the one hand, analytical solutions for a linear model of Li-ion batteries are developed. These solutions offer a straightforward and user-friendly approach to estimate battery performances under several conditions. This feature makes analytical solutions an indispensable tool for preliminary designs and for advanced simulations in which the batteries Depth of Discharge (DoD) is limited to increase their life-cycle. On the other hand, a new model for the open circuit voltage of Li-ion batteries is proposed. This contribution enables a more precise representation of the Li-ion batteries' static charging/discharging behavior for high DoD applications.

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Section: Preliminary Design Of Satellite's Electrical Power Subsystemmentioning

confidence: 99%

Analysis and simulation of electric power systems for aerospace Applications

Marín Coca

View full text Add to dashboard Cite

show abstract

Design of Electrical Power Systems for Satellites

Cited by 1 publication

References 4 publications

Analysis and simulation of electric power systems for aerospace Applications

Analysis and simulation of electric power systems for aerospace Applications

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