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Design of the VISORS and SWARM-EX Propulsion Systems

2022-12-01 , Hart, Samuel T. , Lightsey, E. Glenn

The Georgia Tech (GT) Space Systems Design Lab (SSDL) will deliver 3-D printed cold gas propulsion systems for the VISORS and SWARM-EX CubeSat formation flying missions. This report provides an overview of the working principle of these and past propulsion systems designed by the SSDL. Further information is provided about the specific designs of each of these systems and the problems encountered throughout the design process. Additionally, recommendations for improvements to future designs are outlined. An analysis of the effects of temperature on these systems is also presented.

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Line of Sight Observational and Inertial Sensing Requirements for Multi-UAV Tracking subject to GNSS Denial

2022-08 , Bouhall, Matthew M.

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The Attitude and Determination Control System (ADCS) for the Orbital Calibration 2 Mission (OrCa2)

2022-06 , DiStasio, Luke

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Investigation and Analysis into Establishing a Cislunar PNT System and Performing a Soft Landing on the Lunar Surface

2022-05-01 , Ramanathan, Keshav

With an expected increase in human activity in and around the lunar environment, Georgia Tech, along with GTRI, has proposed two projects to get involved in this sector. One project focuses on Cislunar PNT, which attempts to establish a satellite architecture for PNT in the Cislunar environment. The other project is Lunar ISRU, which desires to soft land a spacecraft on the lunar surface to perform energy capture resource utilization. For an initial phase I study, the Space Systems Design Laboratory (SSDL) team investigated currently proposed requirements and architectures from literature for a Cislunar PNT architecture. Additionally, analysis was performed to simulate a transfer from a NRHO orbit to the lunar surface through an intermediate low lunar parking orbit for Lunar ISRU. From this research, the goal for a more detailed analysis is to create a navigation algorithm simulation package to apply to the chosen system architecture for Cislunar PNT and achieve an optimal and efficient landing for the Lunar ISRU spacecraft on the Moon’s surface

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Best Practices and Considerations for Planning and Conducting Integration of University CubeSats

2022-12-01 , Rawson, William

This paper seeks to serve as a resource for students entering the integration phase of a CubeSat project by compiling best practices and practical considerations from several projects in the Space Systems Design Lab at the Georgia Institute of Technology. The integration phase can be a particular challenge for university CubeSat programs given the value of practical experience in performing these activities and the challenge of managing a student workforce with constant turnover. The topics covered include best practices for planning the integration phase of a project, considerations when performing integration activities, and the characteristics of good assembly procedures. Although the focus is on spacecraft-level integration of CubeSats in a university setting, many of the considerations are applicable outside the academic setting and to subsystem-level integration activities as well. Finally, a case study will be presented illustrating the planning of integration activities for the VISORS mission, a two 6U CubeSat formation-flying mission

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Impacts of Altitude on Expectation Maximization-based Data Association and Orbit Estimation

2022-08 , Sakson, Daniel

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Considering the Effects of Radiation and the Space Environment on Small Satellites

2022-05 , Tokarz, Ariel

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Numerical Optimization of Satellite Avoidance Maneuvers

2022-12-01 , Sheikh, Firas

This paper investigates the numerical optimization of a collision avoidance maneuver and phase return for a satellite in a constellation network. The time until collision and return time are varied, and three impulse maneuvers are assumed. The total Delta-V is minimized while avoiding the collision by 1 km or greater and returning to the original satellite orbit phase. For this analysis, the Clohessy-Wiltshire (CW) solutions were utilized to linearize the system of equations for relative orbital motion without perturbation assumptions. Results demonstrated that a greater time until collision generally produces minimized Delta-V options but longer total maneuver times as a tradeoff.

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Integration and Testing of a 2U Cold-Gas Propulsion System for the SunRISE Mission

2022-08-01 , Shirazi, Kian E.

The Georgia Tech (GT) Space Systems Design Laboratory (SSDL) is building six identical cold-gas propulsion systems to provide the necessary maneuvering capabilities required by the SunRISE mission. The mission plans to observe low frequency emissions from the Sun by utilizing an array of CubeSats that will formation fly to create a large radio telescope in space. The cold-gas system design is based on the lab’s heritage design used for previous missions, namely BioSentinel, which leverages additive manufacturing to create a highly optimized propulsion system for the CubeSat form factor. The unique system consists of mainly a singular printed multifunctional structure encompassing tanks, plumbing, and nozzles, and utilizes a two-phase propellant to maximize the amount of propellant stored in the restricted volume and hence the total impulse provided by the system. This report provides a brief overview of the system design and its purpose in the SunRISE mission, while detailing the integration process and extensive testing campaign each flight unit goes through before they are delivered for integration with the spacecraft.

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Development of a Lunar Mission Operations Center for the NASA JPL Lunar Flashlight Mission

2022-05-01 , Medisetti, Jishnu , Lightsey, E. Glenn

With advancements in small satellite technology being seen, these low cost, small form factor systems are being considered for interplanetary missions. NASA’s Jet Propulsion Laboratory’s (JPL) mission, Lunar Flashlight is a 6U CubeSat which aims to orbit the Lunar South pole and detect craters for water ice. This mission is a technology demonstration which hopes to prove the viability of low cost CubeSats for interplanetary missions. This low resource model for satellites extends to its mission operations as well. Georgia Institute of Technology’s Space System Design Laboratory has been contracted to perform mission operations for Lunar Flashlight. The operations team was able to develop and expand the capabilities Georgia Tech Mission Operations Center (MOC) to support this Lunar mission. Hardware integration was established to connect various operations machines to each other and the Deep Space Network. Interfaces were defined between the operations team and external parties including the Mission Design and Navigation team at JPL. Using the certified MOC, the operations team was also successfully able to perform and complete their first operational readiness test which simulated the first phase of the Lunar Flashlight mission.

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