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Daniel Guggenheim School of Aerospace Engineering

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search.filters.applied.f.advisor: Lightsey, E. Glenn × End date: 2017 × Start date: 2017 × Item Type: Publication × search.filters.applied.f.isOrgUnitOfPublicationTitle: Space Systems Design Laboratory (SSDL) ×

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Flyby Trajectory Analysis and Thermal Simulation of a Venus Atmospheric Probe

2017-12-01 , Selvaratnam, Roshan

Cupid’s Arrow is a proposed interplanetary Venus mission aimed at sampling the noble gases in its atmosphere. These inert elements can provide an insight into the history of the planet’s formation and provide a reference for comparison with the Earth. The mission is comprised of a mothership and an atmospheric sample collection probe. This study is focused on the latter which will be deployed into Venus’ atmosphere and descend to an altitude of 120 km. The thermal environment of the Venusian exosphere is the primary driver of the probe design both in terms of its structure and material composition. The mission architecture being considered for this study takes advantage of a gravity assist flyby trajectory. The probe will be dropped off as a secondary payload en route to the spacecraft’s primary destination. The entry conditions at Venus and the trajectory of the probe relative to the mothership were determined using 2-body orbital mechanics. Using planar equations of motion, the probe’s entry into Venus’ atmosphere was simulated to predict the thermal environment that it would encounter. Initial results show a peak heat rate of approximately 220.3297 W/cm2 , a peak deceleration of 2.7654 Earth g’s and a total heat load of 15535 J/cm2 . The results of the thermal environment model and relative trajectory analysis were used to validate the baseline communications and TPS design. In addition to Venus, this mission concept could be used to explore other planetary atmospheres, especially those frequented by interplanetary flybys.

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User Guide and Status Update for Small Satellite Communication System at Georgia Tech

2017-04-28 , Choi, Thomas

The Georgia Institute of Technology (Georgia Tech) is scheduled to support five different small satellite missions within the next three-year frame (2017 to 2020). Because many missions will share the same ground station system, a flexible and reliable ground station system has been developed at Georgia Tech campus and Georgia Tech Research Institute facility since Fall 2015. In addition to the missions expected to fly, more mission concepts are being developed which could be funded and become actual flight missions. Proper trade study and budgeting is necessary to select a proper communication hardware and establish a link that is functional and efficient. This paper is written to provide a user guide for current and potential communication subsystem engineers for small satellite mission teams at Georgia Tech, who will utilize the ground station system, select flight hardware according to requirements, and test communication links.

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