10.2514/6.2022-2584">
 

CubeSat Reference Mission Design for Operations at the Earth-Moon L3 Lagrange Point

Document Type

Conference Proceeding

Publication Date

1-3-2022

Abstract

The theoretical study of a CubeSat reference mission and system design is presented with an assessment of the environmental risk at the Earth-Moon L3 Lagrange point, as well as an examination of potential mission orbit designs, to include halo and Lissajous orbits. Specifically, the research will apply spacecraft systems engineering principles to develop the bus design of 12U and 27U CubeSats, with a focus on available onboard power assuming a baseline subsystem architecture, communication subsystem capabilities, and options for both attitude control and propulsion. Considerations for propulsion will be presented in terms of required ΔV to transfer to L3 from geostationary Earth orbit, inject into an orbit about L3 (either halo or Lissajous orbit), and maintain the L3-relative orbit for a mission duration of approximately two years. Although not specified, payload capacity will be measured in terms of available power and chassis volume within each CubeSat form factor.

Comments

Conference Session: In-Space Infrastructure and Miscellaneous Exploration Missions II

Source Publication

AIAA SCITECH 2022 Forum

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