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The Design and Development of the Electrical Power System for the LightCube 1U CubeSat.

紀錄類型:	書目-語言資料,手稿 : Monograph/item
正題名/作者:	The Design and Development of the Electrical Power System for the LightCube 1U CubeSat./
作者:	Barakat, Raymond.
面頁冊數:	1 online resource (121 pages)
附註:	Source: Masters Abstracts International, Volume: 85-11.
Contained By:	Masters Abstracts International85-11.
標題:	Electrical engineering. -
電子資源:	click for full text (PQDT)
ISBN:	9798382331904

The Design and Development of the Electrical Power System for the LightCube 1U CubeSat.
Barakat, Raymond.

The Design and Development of the Electrical Power System for the LightCube 1U CubeSat. - 1 online resource (121 pages)

Source: Masters Abstracts International, Volume: 85-11.

Thesis (M.S.)--Arizona State University, 2024.

Includes bibliographical references

The LightCube mission is a CubeSat whose goal is to allow users to manually flash a light that is observable by the naked eye. LightCube required the design of custom electronics because of its small size and unique mission. The majority of the volume of LightCube was taken up by the payload electronics, precluding any use of most off the shelf CubeSat components. A custom EPS system was designed and developed by students at ASU to meet all the power requirements of LightCube. The satellite's solar panels were constrained to a 1U size and the batteries were given a limited volume. The EPS was architected with these constraints in mind to optimize for the space given. It consists of a charging circuit, two converters, voltage and current measuring circuits, and a separate battery board which includes a battery fuel gauge, current sensor, inhibit circuitry, temperature sensor, heater, and optional linear battery charger. One of the underlying goals of this design was to make the EPS and battery board as simple as possible. The design was intentionally simple and left out other features such as a microcontroller for ease and speed of development as well as minimize complexity to lower the risk of catastrophic failure due to radiation or other space events.

Electronic reproduction.
Ann Arbor, Mich. :
ProQuest,
2024

Mode of access: World Wide Web

ISBN: 9798382331904Subjects--Topical Terms:

596380
Electrical engineering.
Subjects--Index Terms:

Charging circuitIndex Terms--Genre/Form:

554714
Electronic books.

The Design and Development of the Electrical Power System for the LightCube 1U CubeSat.
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504 $a Includes bibliographical references
520 $a The LightCube mission is a CubeSat whose goal is to allow users to manually flash a light that is observable by the naked eye. LightCube required the design of custom electronics because of its small size and unique mission. The majority of the volume of LightCube was taken up by the payload electronics, precluding any use of most off the shelf CubeSat components. A custom EPS system was designed and developed by students at ASU to meet all the power requirements of LightCube. The satellite's solar panels were constrained to a 1U size and the batteries were given a limited volume. The EPS was architected with these constraints in mind to optimize for the space given. It consists of a charging circuit, two converters, voltage and current measuring circuits, and a separate battery board which includes a battery fuel gauge, current sensor, inhibit circuitry, temperature sensor, heater, and optional linear battery charger. One of the underlying goals of this design was to make the EPS and battery board as simple as possible. The design was intentionally simple and left out other features such as a microcontroller for ease and speed of development as well as minimize complexity to lower the risk of catastrophic failure due to radiation or other space events.
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538 $a Mode of access: World Wide Web
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650 4 $a Aerospace engineering. $3 686400
650 4 $a Alternative energy. $3 1241221
653 $a Charging circuit
653 $a CubeSat
653 $a Power systems
653 $a Satellites
653 $a Solar panels
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