Date of Award

5-2024

Document Type

Thesis

Degree Name

Master of Science (MS)

Department

Aerospace, Physics, and Space Sciences

First Advisor

Paula do Vale Pereira

Second Advisor

Eric D. Swenson

Third Advisor

Ryan T. White

Fourth Advisor

Ratneshwar Jha

Abstract

Following recommendations from the 2023-2032 Planetary Science and Astrobiology Decadal Survey, we propose a novel Pre-Phase A level Uranus exploration mission concept that is centered on using swarms of small spacecraft to observe the Uranus system. This mission could act as a supplement to the Flagship Uranus Orbiter and Probe mission detailed in said Decadal Survey. We propose launching a 4,500 kg spacecraft on an Earth-Jupiter-Uranus gravity assist transfer trajectory with a transfer time of six years, launching in 2033 and arriving at Uranus in 2039. This shorter transfer time and accelerated development timeline would allow for an earlier arrival date than a traditional flagship spacecraft. Arriving by 2039 would make it possible to observe the changing of the Uranian seasons from solstice to equinox, helping us better understand the atmospheric dynamics, as well as take advantage of a unique planetary alignment for an efficient interplanetary transfer. To maintain the quality of data collection while minimizing mass, we propose that the spacecraft be composed of a carrier spacecraft with a 3,848 kg wet mass, which would be used primarily for communications and orbital transfers, and a swarm of CubeSats with a combined wet mass of 640 kg, which would house the instrumentation. The swarm of 16 CubeSats of approximately 40 kg each would be divided into 4 groups of 4 identical spacecraft. Each group will be equipped with specialized instrumentation, exploring Uranus more extensively and performing planned plunges into its atmosphere. This spatial distribution of the instrumentation would allow for measurements that require multiple perspectives of observation, such as radio occultation and precision gravity measurements. The results shown in this Thesis demonstrate that a high level analysis of such a deep space small satellite mission converges to a viable solution.

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