Rachel Morgan, MIT Department of Aeronautics and Astronautics; Sophia Vlahakis, MIT Department of Aeronautics and Astronautics; Greg Allan, MIT Department of Aeronautics and Astronautics; Paula do Vale Pereira, MIT Department of Aeronautics and Astronautics; Jennifer Gubner, MIT Department of Aeronautics and Astronautics; Christian Haughwout, MIT Department of Aeronautics and Astronautics; Bobby Holden, MIT Department of Aeronautics and Astronautics; Thomas Murphy, MIT Department of Aeronautics and Astronautics; Yinzi Xin, MIT Department of Aeronautics and Astronautics; Kerri Cahoy, MIT Department of Aeronautics and Astronautics; Ewan Douglas, Steward Observatory, University of Arizona; John Merk, Aurora Flight Sciences; Danilo Roascio, Aurora Flight Sciences; Mark Egan, MIT Kavli Institute; Gabor Furesz, MIT Kavli Institute
Keywords: adaptive optics, MEMS, deformable mirrors, cubesats
Abstract:
The Deformable Mirror Demonstration Mission (DeMi) CubeSat payload is a miniature space telescope designed to demonstrate Microelectromechanical Systems (MEMS) Deformable Mirrors (DMs) technology in space for the first time. MEMS DMs can provide high-precision wavefront control with a small form-factor, low power device. This makes them a key technology option for future space telescopes requiring adaptive optics for applications such as high-contrast imaging or optical communications.
The DeMi payload contains a 140-actuator MEMS DM from Boston Micromachines Corporation that can be measured with both an image plane wavefront sensor and a Shack Hartmann wavefront sensor (SHWFS). The key DeMi payload requirements are to measure individual actuator wavefront displacement contributions to a precision of 12 nm and correct both static and dynamic wavefront errors in space to less than 100 nm RMS error. The DeMi mission will raise the Technology Readiness Level (TRL) of MEMS DM technology from a 5 to at least a 7.
This paper summarizes the DeMi optical payload design, calibration, integration and environmental testing results, and payload data from in-space operations. Ground testing data shows that the DeMi SHWFS can measure individual actuator deflections on the MEMS DM to within 10 nm of interferometric calibration measurements and can meet the 12 nm precision requirement for actuator deflection voltages between 0-120 V. Initial data from space operations show the MEMS DM actuating in space with a median agreement between individual actuator measurements from space and equivalent ground testing data of 12 nm. Data from wavefront control experiments show the DeMi payload correcting wavfront errors in space to less that 150 nm RMS.
Date of Conference: September 14-17, 2021
Track: Optical Systems & Instrumentation