当前位置: X-MOL 学术J. Astron. Telesc. Instrum. Syst. › 论文详情
Our official English website, www.x-mol.net, welcomes your feedback! (Note: you will need to create a separate account there.)
Optical calibration and first light for the deformable mirror demonstration mission CubeSat (DeMi)
Journal of Astronomical Telescopes, Instruments, and Systems ( IF 2.3 ) Pub Date : 2021-06-01 , DOI: 10.1117/1.jatis.7.2.024002
Rachel Morgan 1 , Ewan Douglas 2 , Gregory Allan 1 , Paula do Vale Pereira 1 , Jennifer Gubner 1 , Christian Haughwout 1 , Bobby Holden 1 , Thomas Murphy 1 , John Merk 3 , Mark Egan 4 , Gabor Furesz 4 , Danilo Roascio 3 , Yinzi Xin 1 , Kerri Cahoy 1
Affiliation  

Microelectromechanical systems (MEMS) deformable mirrors (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 high-contrast imaging of exoplanets with a coronagraph instrument. The Deformable Mirror Demonstration Mission (DeMi) CubeSat payload is a miniature space telescope designed to demonstrate MEMS DM technology in space for the first time. The DeMi payload contains a 50-mm primary mirror, an internal calibration laser source, a 140-actuator MEMS DM from Boston Micromachines Corporation, 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 of MEMS DM technology from a five to at least a seven for future space telescope applications. We summarize the DeMi optical payload design, calibration, optical diffraction model, alignment, integration, environmental testing, and preliminary data from in-space operations. Ground testing data show 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 mission requirement for actuator deflection voltages between 0 and 120 V. Payload data from throughout environmental testing show that the MEMS DM and DeMi payload survived environmental testing and provides a valuable baseline to compare with space data. 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.

中文翻译:

用于可变形反射镜演示任务 CubeSat (DeMi) 的光学校准和第一道光

微机电系统 (MEMS) 可变形反射镜 (DM) 可以通过小尺寸、低功耗设备提供高精度波前控制。这使它们成为未来太空望远镜的关键技术选择,这些望远镜需要使用自适应光学系统使用日冕仪对系外行星进行高对比度成像。变形镜演示任务 (DeMi) CubeSat 有效载荷是一种微型太空望远镜,旨在首次在太空中演示 MEMS DM 技术。DeMi 有效载荷包含一个 50 毫米主镜、一个内部校准激光源、一个来自波士顿微机械公司的 140 致动器 MEMS DM、一个图像平面波前传感器和一个 Shack-Hartmann 波前传感器 (SHWFS)。DeMi 有效载荷的关键要求是以 12 nm 的精度测量单个致动器波前位移贡献,并将空间中的静态和动态波前误差校正到小于 100 nm RMS 误差。DeMi 任务将把 MEMS DM 技术的技术准备水平从 5 级提高到至少 7 级,以用于未来的太空望远镜应用。我们总结了 DeMi 光学有效载荷设计、校准、光学衍射模型、对准、集成、环境测试以及来自太空操作的初步数据。地面测试数据表明,DeMi SHWFS 可以在 MEMS DM 上测量单个致动器偏转至干涉校准测量的 10 nm 范围内,并且可以满足 0 到 120 V 之间致动器偏转电压的 12 纳米精度任务要求。来自整个环境测试的有效载荷数据表明,MEMS DM 和 DeMi 有效载荷在环境测试中幸存下来,并提供了与空间数据进行比较的宝贵基线。来自太空操作的初始数据显示 MEMS DM 在太空中致动,空间中的单个致动器测量值与 12 nm 的等效地面测试数据之间的中值一致性。
更新日期:2021-06-30
down
wechat
bug