Improving Nanosatellite Imaging And Atmospheric Sensing -Books Pdf

Improving Nanosatellite Imaging and Atmospheric Sensing
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Introduction,Adaptive Optics overview,In space applications. Approach CubeSat Deformable Mirror Demonstration,Mission Goals. Payload and experiment design,Flight mission,Laboratory validation. 2 SSC16 WK 13 8 7 2016,Introduction Adaptive Optics. Adaptive optics correct optical MEMS deformable mirrors. distortions Electrostatic actuators no,Deformable mirror actuators hysteresis.
change the shape of the mirror, surface to match the incoming Smaller size weight power and. wavefront cost for same number of,actuators compared to. piezoelectric or electroceramic,Ideal for use in constrained. environment e g space,telescope but have not been,space qualified. 3 SSC16 WK 13 8 7 2016,Adaptive Optics Applications in Space.
High contrast imaging,Counteract jitter,thermal gradients. mechanical,misalignment surface,1 Hz timescale,More actuators allows. for higher spatial,frequency correction,Nanosatellites validate. technology MEMS DM,for implementation on Coronagraph Image Plane. future space telescopes Higher spatial frequency more actuators farther from. image center,Traub Oppenheimer 2010,4 SSC16 WK 13 8 7 2016.
Adaptive Optics Applications in Space,Atmospheric sensing. with intersatellite,optical occultation,Correct for scintillation Neutral. and distortions to Atmosphere,Direction of,sound lower into the better. atmosphere correction,1 kHz timescale,Nanosatellites. technology validation Strong turbulence,correction needed.
and measurement, platform Atmospheric turbulence worse near the surface left more actuators. allow for better matched correction right,5 SSC16 WK 13 8 7 2016. Introduction,Adaptive Optics overview,In space applications. Approach CubeSat Deformable Mirror Demonstration,Mission Goals. Payload and experiment design,Flight mission,Laboratory validation.
6 SSC16 WK 13 8 7 2016,CubeSat Deformable Mirror Demonstration. Notional rendering of 6U demonstration CubeSat, DeMi Mission Goals Image Credit Aurora Flight Sciences. Characterize and calibrate the,performance of a MEMS. deformable mirror over a long,duration on orbit mission. Measure mirror surface to 100 nm,Demonstrate the use of these.
mirrors as intended for high Payload Requirements and Specs. contrast imaging Subsystem Requirement, Correct in situ aberrations to 100 Attitude knowledge 0 1 degrees. Attitude stability 20 arcsec over 1 ms,Baseline orbit ISS 404x424 km. Power 10 W, Target stars Vega Arcturis Sirius Datarate 50 kbps. Canopis Alpha Centauri,2U for optics,5 8 minute orbit averaged access Volume. 0 5 1U for driver,opportunities,Mass 1 5 kg,7 SSC16 WK 13 8 7 2016.
DeMi Payload Design,2U Optical payload BMC Mini Multi. Mirror Form,Mirror BMC Multi 140 actuators Factor, Alternate Kilo 952 actuators with custom driver developed by. Mirror Characterization,Payload Layout,Green External source. Blue Internal source,Marinan 2016,2 sources aperture laser. 2 detectors focal plane wavefront,8 SSC16 WK 13 8 7 2016.
DeMi Experiment Architectures,0 Internal source wavefront sensor. Open loop mirror characterization closed loop correction. Experiment run periodically throughout mission life. Beampath in red,A Marinan MIT,9 SSC16 WK 13 8 7 2016. DeMi Experiment Architectures,1 Internal source focal plane image. Closed loop correction with focal plane sensor, Experiment run periodically throughout mission life. Beampath in red,A Marinan MIT,10 SSC16 WK 13 8 7 2016.
DeMi Experiment Architectures,2 External object focal plane image. Closed loop image correction with focal plane sensor. Experiment of opportunity bright star in view,Beampath in red. A Marinan MIT,11 SSC16 WK 13 8 7 2016,Introduction. Adaptive Optics overview,In space applications,Approach CubeSat Deformable Mirror Demonstration. Mission Goals,Payload and experiment design,Flight mission.
Laboratory validation,12 SSC16 WK 13 8 7 2016,CubeSat Payload In lab Validation. To scale optical payload,Some modifications for mirror. detector packaging,Mini deformable mirror 32,Wavefront reconstruction and. control software drivers,written in MATLAB on,desktop computer. Non flight configuration,Overall goal for setup,Verify wavefront sensor.
measurement precision inform Laboratory hardware setup with key system elements. Marinan 2016,performance of payload in LEO,Demonstrate closed loop control. 13 SSC16 WK 13 8 7 2016,Open Loop Laboratory Validation. Payload wavefront sensor left showing behavior consistent with. Zygo interferometer measurements right, Shack Hartmann wavefront sensor 4 lenslets samples per actuator. 80 nm deflection at 20 stroke, Noisier than Zygo measurements less controlled environment noise in. wavefront sensor measurement, 32 phase maps of influence function for each actuator poke.
left computed with wavefront sensor right from Zygo interferometer. Note each subplot shows entire mirror surface,Marinan 2016 0 07. 14 SSC16 WK 13 8 7 2016,Closed Loop Laboratory Validation. Control law implemented,Wavefront sensor sending,feedback to deformable. Image correction,aberration with plastic,plate observed in focal. Mirror responding as,expected no observed,system instabilities Marinan 2016.
Slow static correction,2 3 second iterations,converges after 35. Limited in correction Marinan 2016,capability 6 actuators. across limited spatial Left Initial focal plane image. frequency Middle Focal plane image with aberration. Right Focal plane image after correction,15 SSC16 WK 13 8 7 2016.


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