Session
Weekend Session 5: Science/Mission Payloads - Research & Academia II
Location
Utah State University, Logan, UT
Abstract
Flying beyond Earth's sphere of influence has been part of the main goals in space exploration. Efforts of the Artemis program now encompass different classes of missions, including CubeSats. With the challenges of deep space as mission drivers, planning, designing, launching, and operating a CubeSat for a Moon mission is proving to be a step up in difficulty. In this context, SelenITA Mission is conceived as a science mission supporting the Artemis efforts, planned to operate at Low-Lunar Orbit (LLO), flying below 200 km gathering space weather and geophysics observations, marking the first Brazilian mission to the Moon. This paper outlines the engineering challenges encountered this far in the development of SelenITA. It presents the aspects of lunar orbits and the effects of Moon's potential field on a 12U CubeSat in LLO. A Reference Scenario is established, followed by an exploration of the extreme lunar environment's effect on the satellite's thermal, radiation, and power aspects. Communication limitations in the cislunar environment are analyzed, and strategies for the Attitude and Orbit Control Subsystem are discussed. The paper also addresses the challenges associated with delivery, uncertainties, and supply chain. A conceptual overview of the system is presented, concluding with the future steps.
Engineering Challenges of a CubeSat Mission Around the Moon: First Steps on the Path to SelenITA
Utah State University, Logan, UT
Flying beyond Earth's sphere of influence has been part of the main goals in space exploration. Efforts of the Artemis program now encompass different classes of missions, including CubeSats. With the challenges of deep space as mission drivers, planning, designing, launching, and operating a CubeSat for a Moon mission is proving to be a step up in difficulty. In this context, SelenITA Mission is conceived as a science mission supporting the Artemis efforts, planned to operate at Low-Lunar Orbit (LLO), flying below 200 km gathering space weather and geophysics observations, marking the first Brazilian mission to the Moon. This paper outlines the engineering challenges encountered this far in the development of SelenITA. It presents the aspects of lunar orbits and the effects of Moon's potential field on a 12U CubeSat in LLO. A Reference Scenario is established, followed by an exploration of the extreme lunar environment's effect on the satellite's thermal, radiation, and power aspects. Communication limitations in the cislunar environment are analyzed, and strategies for the Attitude and Orbit Control Subsystem are discussed. The paper also addresses the challenges associated with delivery, uncertainties, and supply chain. A conceptual overview of the system is presented, concluding with the future steps.
