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The deformable mirror demonstration mission (DeMi) CubeSat: optomechanical design validation and laboratory calibration

Author(s)
Douglas, Ewan S.; Cahoy, Kerri L.; Barnes, Derek; Haughwout, Christian; Holden, Bobby G.; Stein, Abigail J.; Allan, Gregory; Furesz, Gabor; Egan, Mark; do Vale Pereira, Paula; Grunwald, Warren; Gubner, Jennifer; ... Show more Show less
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Abstract
© COPYRIGHT SPIE. Downloading of the abstract is permitted for personal use only. Coronagraphs on future space telescopes will require precise wavefront correction to detect Earth-like exoplanets near their host stars. High-actuator count microelectromechanical system (MEMS) deformable mirrors provide wavefront control with low size, weight, and power. The Deformable Mirror Demonstration Mission (DeMi) payload will demonstrate a 140 actuator MEMS Deformable Mirror (DM) with 5:5 μm maximum stroke. We present the flight optomechanical design, lab tests of the flight wavefront sensor and wavefront reconstructor, and simulations of closed-loop control of wavefront aberrations. We also present the compact flight DM controller, capable of driving up to 192 actuator channels at 0-250V with 14-bit resolution. Two embedded Raspberry Pi 3 compute modules are used for task management and wavefront reconstruction. The spacecraft is a 6U CubeSat (30 cm x 20 cm x 10 cm) and launch is planned for 2019.
Date issued
2018-08-21
URI
https://hdl.handle.net/1721.1/137956
Department
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics; MIT Kavli Institute for Astrophysics and Space Research; Massachusetts Institute of Technology. Department of Earth, Atmospheric, and Planetary Sciences
Publisher
SPIE
Citation
Douglas, Ewan S., Cahoy, Kerri L., Barnes, Derek, Haughwout, Christian, Holden, Bobby G. et al. 2018. "The deformable mirror demonstration mission (DeMi) CubeSat: optomechanical design validation and laboratory calibration."
Version: Final published version

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