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Continuous Solar Observation from Low Earth Orbit with a Two-Cubesat Constellation.

Record Type:	Language materials, printed : Monograph/item
Title/Author:	Continuous Solar Observation from Low Earth Orbit with a Two-Cubesat Constellation./
Author:	Kampmeier, Jennifer Lauren.
Published:	Ann Arbor : ProQuest Dissertations & Theses, : 2018,
Description:	79 p.
Notes:	Source: Masters Abstracts International, Volume: 57-06.
Contained By:	Masters Abstracts International57-06(E).
Subject:	Aerospace engineering. -
Online resource:	http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=10746150
ISBN:	9780438044586

Continuous Solar Observation from Low Earth Orbit with a Two-Cubesat Constellation.
Kampmeier, Jennifer Lauren.

Continuous Solar Observation from Low Earth Orbit with a Two-Cubesat Constellation. - Ann Arbor : ProQuest Dissertations & Theses, 2018 - 79 p.

Source: Masters Abstracts International, Volume: 57-06.

Thesis (M.S.)--University of Colorado at Boulder, 2018.

The goal of this work is to assess the feasibility of using a two-CubeSat constellation to make continuous solar science measurements from low Earth orbit. There is a growing interest in using CubeSats for scientific missions since they are relatively inexpensive, can be manufactured quickly, and they have a standard form factor. CubeSats have increased access to space, and there is a growing interest in the solar science community to be able to conduct remote sensing solar science missions from a CubeSat platform. By using a constellation separated by differential drag, this mission concept enables continuous measurements of the sun, allowing scientists to have a complete record despite the spacecraft's eclipse periods. In this thesis, I have developed a two-body propagator that takes various inputs for starting altitude, density model, attitude, and spacecraft configuration to enable investigation over a large trade space. Following the model development, I ran a series of simulations to explore the feasibility of this concept, finding that there are many combinations of parameters that produce a feasible mission design. I show that the model is validated by altitude decay data from the MinXSS CubeSat, I will discuss areas of the design that require further study, and I explore the logical next steps for future development of this concept.

ISBN: 9780438044586Subjects--Topical Terms:

686400
Aerospace engineering.

Continuous Solar Observation from Low Earth Orbit with a Two-Cubesat Constellation.
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520 $a The goal of this work is to assess the feasibility of using a two-CubeSat constellation to make continuous solar science measurements from low Earth orbit. There is a growing interest in using CubeSats for scientific missions since they are relatively inexpensive, can be manufactured quickly, and they have a standard form factor. CubeSats have increased access to space, and there is a growing interest in the solar science community to be able to conduct remote sensing solar science missions from a CubeSat platform. By using a constellation separated by differential drag, this mission concept enables continuous measurements of the sun, allowing scientists to have a complete record despite the spacecraft's eclipse periods. In this thesis, I have developed a two-body propagator that takes various inputs for starting altitude, density model, attitude, and spacecraft configuration to enable investigation over a large trade space. Following the model development, I ran a series of simulations to explore the feasibility of this concept, finding that there are many combinations of parameters that produce a feasible mission design. I show that the model is validated by altitude decay data from the MinXSS CubeSat, I will discuss areas of the design that require further study, and I explore the logical next steps for future development of this concept.
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