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CubeSat electrical power supplies optimization — Comparison between conventional and optimal design methodology | IEEE Conference Publication | IEEE Xplore

CubeSat electrical power supplies optimization — Comparison between conventional and optimal design methodology


Abstract:

Satellites and space application devices demands high efficiency with size, volume, mass and losses reduced simultaneously due to low power generation in space orbit and ...Show More

Abstract:

Satellites and space application devices demands high efficiency with size, volume, mass and losses reduced simultaneously due to low power generation in space orbit and the relation between mass and the overall space mission cost. To minimize costs and promote high access to universities, small companies and institutes a nanosatellite was developed in early 2000, the CubeSat class. Therefore the need to save energy is mandatory in all systems due to low power generation and reduced size. This work focuses in the electrical power supply (EPS), system responsible to generate, store, conditioning and supply electrical power for the whole satellite. Thus is presented a comparison between a conventional power converter design and an optimization design methodology for boost power converters in order to improve efficiency, to reduce volume and mass for 1U CubeSat EPS. Results have shown the method effectiveness and efficiency maximization was achieved respecting the 1U CubeSat constraints.
Date of Conference: 20-23 November 2016
Date Added to IEEE Xplore: 09 March 2017
ISBN Information:
Conference Location: Curitiba, PR, Brazil

I. Introduction

Since early 2000 CubeSat class is democratizing the space acess. This nanosatellite topology was created with the main goals the integration among researchers, students, professors and companies looking to low cost space mission; simplicity in the design; use of radio amateur frequency band and space qualification of the future small payloads [1] [2]. The standard size measures 10 cm each edge and weighs less than 1.3 kg, being called 1 unity (1U) [1]. Furthermore, launch costs are directly related to satellite mass and volume. So this topology have the opportunity to be launched into space orbit as a piggyback due to low mass and volume consequently minimizing launch costs.

References

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