A Preliminary Architecture Optimization for In-Space Assembled Telescopes

Paper number

IAC-19,D1,2,2,x52358

Author

Mr. William Sanchez, United States, Massachusetts Institute of Technology (MIT)

Coauthor

Mr. Keenan Albee, United States, Massachusetts Institute of Technology (MIT)

Coauthor

Ms. Rosemary Davidson, United States, Massachusetts Institute of Technology (MIT)

Coauthor

Mr. Ryan de Freitas Bart, United States, Massachusetts Institute of Technology (MIT)

Coauthor

Mr. Alejandro Cabrales Hernandez, United States, Massachusetts Institute of Technology (MIT)

Coauthor

Prof. Jeffrey Hoffman, United States, Massachusetts Institute of Technology (MIT)

Year

2019

Abstract

The current trend towards larger diameter space-based and ground-based telescopes reflects both improvements in manufacturing abilities and the need for more light-gathering capability. Although ground telescopes can continue to grow in diameter using previous manufacturing and assembly techniques, space-based telescope mirror diameters are limited by the fairing size of a single launch vehicle. Looking towards the future, the demand for larger diameter primary mirrors is expected to quickly outgrow the size of a single launch vehicle fairing. In this case, the only viable option for a larger diameter space telescope will be on-orbit assembly. This paper provides a preliminary framework to optimize the architectural trade-space of in-space assembled telescopes as well as a metric to quantify the relative cost of the designs. Key parameters driving the architecture of such a system were identified and several variations of the parameters enumerated. These include primary mirror segment size, raft (i.e., unit of segments ready for assembly) geometry and configuration, in-space assembly location, and launch vehicle selection.

The results of the paper are presented through a Pareto Analysis which ultimately describes the optimal architecture against the trade-space considered. This includes design of fuel-efficient trajectories generated from the Circular Restricted Three-Body problem for transfer of components to the assembly and mission locations (e.g., Earth-Moon L1, Sun-Earth L2). Furthermore, an optimization scheme is demonstrated for launch vehicle packing/manifest with constraints on component selection, payload limitations for reaching the desired assembly point, and scheduling of launch vehicle and components.

Abstract document

IAC-19,D1,2,2,x52358.brief.pdf

Manuscript document

IAC-19,D1,2,2,x52358.pdf (🔒 authorized access only).

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