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Thermal Control for a 1000 km Orbit Microsatellite.
紀錄類型:
書目-語言資料,手稿 : Monograph/item
正題名/作者:
Thermal Control for a 1000 km Orbit Microsatellite./
作者:
Vadehra, Arujun Singh.
面頁冊數:
1 online resource (106 pages)
附註:
Source: Masters Abstracts International, Volume: 85-05.
Contained By:
Masters Abstracts International85-05.
標題:
Condensed matter physics. -
電子資源:
click for full text (PQDT)
ISBN:
9798380842730
Thermal Control for a 1000 km Orbit Microsatellite.
Vadehra, Arujun Singh.
Thermal Control for a 1000 km Orbit Microsatellite.
- 1 online resource (106 pages)
Source: Masters Abstracts International, Volume: 85-05.
Thesis (M.A.S.)--University of Toronto (Canada), 2023.
Includes bibliographical references
The Space Flight Laboratory, with its focus on the micro-space philosophy, strives to make space more accessible. This thesis describes the thermal design for a DEFIANT microsatellite, a prime example of the laboratory's modular spacecraft platforms. To be operated at an altitude of 1000 kilometers, this spacecraft pushes the limits of what the DEFIANT platform has achieved. The many stages of spacecraft thermal model development and testing are described. Reference thermal designs are presented that prove the viability of thermal control for the mission. This higher altitude mission also requires an active de-orbiting strategy. The impact this additional phase has on spacecraft lifetime thermal behavior is investigated. The challenges of multi-altitude thermal design are highlighted. Finalized thermal control for launch is detailed using findings from de-orbiting investigations. The unique aspects of this mission demonstrate the Laboratory's ability to innovate and redefine what can be achieved with small spacecraft.
Electronic reproduction.
Ann Arbor, Mich. :
ProQuest,
2024
Mode of access: World Wide Web
ISBN: 9798380842730Subjects--Topical Terms:
1148471
Condensed matter physics.
Subjects--Index Terms:
DeorbitIndex Terms--Genre/Form:
554714
Electronic books.
Thermal Control for a 1000 km Orbit Microsatellite.
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The Space Flight Laboratory, with its focus on the micro-space philosophy, strives to make space more accessible. This thesis describes the thermal design for a DEFIANT microsatellite, a prime example of the laboratory's modular spacecraft platforms. To be operated at an altitude of 1000 kilometers, this spacecraft pushes the limits of what the DEFIANT platform has achieved. The many stages of spacecraft thermal model development and testing are described. Reference thermal designs are presented that prove the viability of thermal control for the mission. This higher altitude mission also requires an active de-orbiting strategy. The impact this additional phase has on spacecraft lifetime thermal behavior is investigated. The challenges of multi-altitude thermal design are highlighted. Finalized thermal control for launch is detailed using findings from de-orbiting investigations. The unique aspects of this mission demonstrate the Laboratory's ability to innovate and redefine what can be achieved with small spacecraft.
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click for full text (PQDT)
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