The correction of quasi-static wavefront errors within a coronagraphic optical system will be a key challenge to overcome in order to directly image exoplanets in reflected light. These quasi-static errors are caused by mid to high-order surface errors on the optical elements as a result of manufacturing processes. Using high-order wavefront sensing and control (HOWFSC) techniques that do not introduce non-common path aberrations, the quasi-static errors can be corrected within the desired region of interest designated as the dark hole. For the future Habitable Worlds Observatory (HWO), HOWFSC algorithms will be key to attaining the desired contrasts. To simulate the performance of HOWFSC with space rated processors, optical models for a 6 m class space-borne observatory and a coronagraph have been developed. Phenomena such as the Talbot effect and beamwalk are included in the simulations using combinations of ray-based modeling and end-to-end propagation techniques. After integrating the optical models with the embedded processors, simulations with realistic computation times can be performed to understand the computational hardware performance that will be needed to maintain the desired contrasts. Here, the details of the optical models are presented along with the HOWFSC methods utilized. Initial results of the HOWFSC methods are also included as a demonstration of how system drifts will degrade the contrast and require dark hole maintenance.
The PICTURE-C balloon mission launched on its second flight from Fort Sumner, NM on September 28, 2022. During this flight, PICTURE-C, which consists of a 60 cm off-axis telescope feeding a vector vortex coronagraph, demonstrated the first high-contrast dark hole from an observatory in a near-space environment. The coronagraph achieved a modest broadband (20%) contrast ratio of 5 x 10-6 , with performance limited by dynamic pointing transients. The low-order wavefront control system achieved optical pointing stabilization of one milliarcseconds RMS for intervals of up to 30 seconds between these transients. This paper will summarize the second flight results and present the development path for PICTURE-D, the next generation direct imaging balloon mission.
Future large space telescope missions for directly imaging exoplanets with internal coronagraphs will require picometer level low-order wavefront control to reach the 1e-10 starlight suppression required to detect terrestrial exoplanets. This paper aims to characterize the reflective Lyot-stop Low-Order Wavefront Sensor (LLOWFS) for the application where a transmissive focal plane mask is used, such as the Vector Vortex Coronagraph (VVC). This paper first defines the control requirements for such a mission based on the low-order tolerance of the VVC. The LLOWFS performance is then derived through optical simulation and compared to the requirements. The performance is calculated as a function of the target star brightness and aperture size and the final closed-loop stability is simulated using varying models for telescope pointing jitter and wavefront drift.
Extreme wavefront correction is required for coronagraphs on future space telescopes to reach 10-8 or better starlight suppression for the direct imaging and characterization of exoplanets in reflected light. Thus, a suite of wavefront sensors working in tandem with active and adaptive optics are used to achieve stable, nanometerlevel wavefront control over long observations. In order to verify wavefront control systems, comprehensive and accurate integrated models are needed. These should account for any sources of on-orbit error that may degrade performance past the limit imposed by photon noise. An integrated model of wavefront sensing and control for a space-based coronagraph was created using geometrical raytracing and physical optics propagation methods. Our model concept consists of an active telescope front end in addition to a charge-6 vector vortex coronagraph instrument. The telescope uses phase retrieval to guide primary mirror bending modes and secondary mirror position to control the wavefront error within tens of nanometers. The telescope model is dependent on raytracing to simulate these active optics corrections for compensating the wavefront errors caused by misalignments and thermal gradients in optical components. Entering the coronagraph, a self-coherent camera is used for focal plane wavefront sensing and digging the dark hole. We utilize physical optics propagation to model the coronagraphy’s sensitivity to mid and high-order wavefront errors caused by optical surface errors and pointing jitter. We use our integrated models to quantify expected starlight suppression versus wavefront sensor signal-to-noise ratio.
The Planetary Imaging Concept Testbed Using a Recoverable Experiment - Coronagraph (PICTURE C) is a high-altitude balloon-borne observatory that used a vector vortex coronagraph to image dust and debris disks around nearby stars, as well as develop and test technology necessary for direct imaging of exoplanets from a flight platform. The balloon flight environment presents several challenges: an ambient pressure and temperature of approximately 4 Torr and 220-240 K, combined with significant and varying solar irradiance, lead to time-dependent and anisotropic thermal deformation of the optics and their supporting structure. In order to characterize how these effects limit the ultimate performance of the mission, we present a finite-element model of the flight instrument, implemented in Thermal Desktop, which takes into account the interactions with the environment. We present the comparison of this thermal model with flight data.
The Planetary Imaging Concept Testbed Using a Recoverable Experiment - Coronagraph (PICTURE-C) mission is designed to directly image debris disks and exozodiacal dust around nearby stars from a high-altitude balloon using a 60 cm diameter off-axis telescope and a vector vortex coronagraph. During its second flight from Fort Sumner, New Mexico, on September 28, 2022, PICTURE-C successfully used its high and low-order wavefront control systems to perform focal plane wavefront correction for the first time on an observatory in a near-space environment. The coronagraph achieved a modest broadband (20%) contrast of 5 × 10 − 6, with performance limited by dynamic pointing transients. The low-order wavefront control system achieved optical pointing stabilization of 1 milliarcseconds (mas) root mean squared (RMS) over 30 second timescales.
The Planetary Imaging Concept Testbed Using a Recoverable Experiment Coronagraph (PICTURE C) is a high-altitude balloon-borne observatory that uses a vector vortex coronagraph to image debris disks and exo-zodiacal dust around nearby stars. The engineering flight of PICTURE-C launched in September of 2019, successfully demonstrated several key technologies needed for the upcoming science flight, currently scheduled for September of 2022. The flight environment presents several challenges in thermal and mechanical effects. Low ambient pressure and temperature, approximately 4 Torr and 240 K respectively, combined with significant and varying solar irradiance, lead to time-dependent and anisotropic thermal deformation of the optics and their supporting structure. A constantly swaying observatory in a 1g environment, and the mechanical strains of a pointing system keeping the instrument on target lead to both a sag and flexing of the support structure. In order to characterize how these effects limit the ultimate performance of the mission, we present a finite-element model of the flight instrument, implemented in COMSOL, which takes into account the interactions with the environment. We present the comparison of this thermal model with the temperature data available from flight 1.
Exceptional wavefront correction is required for coronagraphs on future space observatories to reach 10-10 contrasts for direct imaging of rocky exoplanets around Sun-like stars. This picometer level wavefront correction must be stable over long periods of time and should be limited only by photon noise and wavefront sensing architecture. Thus, wavefront errors that arise from optical surface errors, thermal gradients, pointing induced beamwalk, and polarization aberration must be tightly controlled. A self-coherent camera (SCC) allows for image plane correction of mid-spatial frequency errors and a continuous means of dark-hole maintenance. By introducing a reference pinhole at the Lyot stop of a coronagraph, coherent starlight can be interfered with image plane speckles while leaving incoherent planet light untouched. A coronagraph model was created using High Contrast Imaging in Python (HCIPy) to simulate the SCC. Using these tools, realistic input disturbances can be introduced to analyze wavefront sensor performance. Using our model, we first demonstrate the necessity of a complimentary low-order wavefront sensor (LOWFS) to be paired with the SCC. Next, we discuss considerations when creating the modified Lyot stop of an SCC. Finally, a tolerance analysis of the SCC in the presence of optical surface errors, beamwalk due to pointing errors, photon noise, and detector read noise is presented.
The Planetary Imaging Concept Testbed Using a Recoverable Experiment - Coronagraph (PICTURE-C) mission will directly image debris disks and exozodiacal dust around nearby stars from a high-altitude balloon using a vector vortex coronagraph. The first flight of PICTURE-C launched from the NASA Columbia Scientific Balloon Facility (CSBF) in Ft. Sumner, NM on September 28, 2019. This flight successfully demonstrated many key technologies for exoplanetary direct imaging missions and all hardware components for the second, sciencefocused flight of PICTURE-C, which had been scheduled for the fall of 2021, but was delayed due to inclement weather until 2022. We present laboratory demonstrations of the flight 2 coronagraph, which uses a high-order 952 actuator MEMS deformable mirror to create a high-contrast dark zone at the 10-7 level. The performance of the low-order and high-order wavefront control systems is demonstrated and compared with model predictions.
We describe a multichannel camera operating in the visible to near-infrared wavelengths (450 to 900 nm) with an etendue of 0.08 cm2 sr that can be used to image extended sources across multiple optical bands, capable of 3σ detection of 20 Rayleigh signal in 120 s. It has an angular resolution of 0.1 deg and a 35 deg × 25 deg field of view, employing a charge-coupled device detector in a compact 1U CubeSat compatible form factor (10 × 10 × 8 cm3). The design uses commercial off-the-shelf components while offering versatility using a mosaic of bandpass filters to select different spectral channels to address a wide range of remote sensing needs. The specific implementation described here covers the application of the instrument to explore the neutral sodium and potassium atom density distribution in the atmospheres of the Earth or the Moon.
The Planetary Imaging Concept Testbed Using a Recoverable Experiment - Coronagraph (PICTURE-C) mission will directly image debris disks and exozodiacal dust around nearby stars from a high-altitude balloon using a vector vortex coronagraph. The first flight of PICTURE-C launched from the NASA Columbia Scientific Balloon Facility in Ft. Sumner, NM on September 28, 2019 and ew for a total of 20 hours, with 16 hours at float altitude above 110,000 ft. This flight successfully demonstrated many key technologies for exoplanetary direct imaging missions and all hardware components for the second, science-focused flight of PICTURE-C scheduled for the fall of 2021. These technologies include a vector vortex coronagraph, high and low-order deformable mirrors and a high speed low-order wavefront control system. The experiment also demonstrated a 60 cm off-axis telescope with a hexapod-actuated secondary mirror that aligned itself automatically during flight. This paper details the flight performance of PICTURE-C, focusing on the operation of the low-order wavefront control system and the influence of high-frequency structural vibrations. We present new structural modifications that have been made to reduce these vibrations and laboratory demonstrations of the flight 2 coronagraph, which uses a high-order 952 actuator MEMS deformable mirror to create a high-contrast dark zone.
The vector vortex coronagraph (VVC) is a leading choice for future space-based exoplanet direct imaging missions due to its simplicity and high throughput. The construction of the VVC as an azimuthally rotating half-wave plate implies a differential influence on the two orthogonal circular polarization states of incident starlight - particularly on the mapping of deformable mirror (DM) actuators to the final image plane. Traditional electric field conjugation (EFC) coupled with the VVC is capable of digging a high-contrast dark zone in one circular polarization, but the dark zone is not preserved in the orthogonal state. This paper presents an extension to the traditional EFC algorithm to find DM actuator solutions that produce a dark zone simultaneously in both circular polarizations. This dual-polarization EFC can be used in conjunction with low-leakage VVC architectures to perform high-contrast polarimetric measurements using a single coronagraph.
The Planetary Imaging Concept Testbed Using a Recoverable Experiment-Coronagraph (PICTURE-C) experiment is a balloon-borne observatory for high-contrast imaging of debris disks and exoplanets around nearby stars. This experiment will use a 10,000-pixel Microwave Kinetic Inductance Detector (MKID) instrument as its science camera. The PICTURE-C MKID Camera is an integral field spectrograph (IFS) with a bandpass of λ = 540 − 660 nm that sits behind a modest adaptive optics system and coronagraph which promise to achieve contrast ratios down to 10-7 from 1.7 to 10 λ/D (0.35” to 2.1”). The MKIDs are photon counting detectors promising a resolution R up to 20 for the PICTURE-C mission. The ability to count photons with microsecond time resolution will allow the MKID camera to double as a Focal Plane Wavefront Sensor (FPWFS), helping to discriminate between speckles and circumstellar objects in real time and in post-processing. The intrinsic spectral resolution of the detectors will allow for further characterization of the debris disks and exoplanets around the stars targeted during its flight. The visible light observations taken with this instrument will complement infrared observations taken from the ground and serve to demonstrate MKIDs utility in a space-like environment. For this poster, we will introduce and discuss the PICTURE-C MKID Camera.
Deformable mirrors (DMs) are a critical technology to enable coronagraphic direct imaging of exoplanets with current and planned ground- and space-based telescopes as well as future mission concepts, such as the Habitable Exoplanet Observatory and the Large UV/Optical/IR Surveyor. The latter concepts aim to image exoplanet types ranging from gas giants to Earth analogs. This places several requirements on the DMs such as requires a large actuator count (≳3000), fine surface height resolution (≲10 pm), and radiation hardened driving electronics with low mass and volume. We present the design and testing of a flight-capable, miniaturized DM controller. Having achieved contrasts on the order of 5 × 10 − 9 on a coronagraph testbed in vacuum in the high contrast imaging testbed facility at NASA’s Jet Propulsion Laboratory (JPL), we demonstrate that the electronics are capable of meeting the requirements of future coronagraph-equipped space telescopes. We also report on functionality testing on-board the high-altitude balloon experiment “Planetary Imaging Concept Testbed Using a Recoverable Experiment – Coronagraph,” which aims to directly image debris disks and exozodiacal dust around nearby stars. The controller is designed for the Boston Micromachines Corporation Kilo-DM and is readily scalable to larger DM formats. The three main components of the system (the DM, driving electronics, and mechanical and heat management) are designed to be compact and have low-power consumption to enable its use not only on exoplanet missions, but also in a wide-range of applications that require precision optical systems, such as direct line-of-sight laser communications. The controller is capable of handling 1024 actuators with 220 V maximum dynamic range, 16-bit resolution, 14-bit accuracy, and 1 kHz operating frequency. The system fits in a 10 × 10 × 5 cm3 volume, weighs <0.5 kg, and consumes <8 W. We have developed a turnkey solution reducing the risk for future missions, lowering their cost by significantly reducing volume, weight, and power consumption of the wavefront control hardware.
The Planetary Imaging Concept Testbed Using a Recoverable Experiment - Coronagraph (PICTURE-C) mission will directly image debris disks and exozodiacal dust around nearby stars from a high-altitude balloon using a vector vortex coronagraph. PICTURE-C employs both image-plane wavefront sensing for high-order wave- front control and a reflective Lyot-stop sensor for low-order wavefront control. Since both of these systems lie downstream from the coronagraph's deformable mirror, and since both must run simultaneously, they must be calibrated as to not interfere with each other. The deformable mirror probe patterns required for image-plane sensing appear as wavefront errors to the low-order sensor. This paper presents simulations of low and high-order wavefront sensing for PICTURE-C and calibration techniques for decoupling the two sensors.
The Planetary Imaging Concept Testbed Using a Recoverable Experiment - Coronagraph (PICTURE-C) is a direct imaging experiment designed to observe exozodiacal dust and debris disks that orbit nearby stars from a high-altitude balloon platform. The experiment consists of a vector vortex coronagraph and a multi stage adaptive optics system with multiple wavefront sensors and two deformable mirrors. This paper details the hardware and software implementation of one of the DM interfaces used in the PICTURE-C low-order wavefront control system. We discuss the algorithm used to drive a commercial o_-the-shelf DM with an actuation resolution of 14-bits to meet the PICTURE-C requirement of 16-bits. The algorithm utilizes fast temporal dithering in the form of pulse density modulation to reduce the quantization error of the DM actuation. The described DM control mechanism can operate at a framerate of ~500 Hz with an equivalent actuation resolution of 16-bits with minimal computational load on the deployed processor.
The Planetary Imaging Concept Testbed Using a Recoverable Experiment - Coronagraph (PICTURE-C) mission will directly image debris disks and exozodiacal dust around nearby stars from a high-altitude balloon using a vector vortex coronagraph. The first flight of PICTURE-C was recently rescheduled by NASA for September, 2019. This paper describes preparations for the first flight of PICTURE-C, including the final mission design, flight integration process and observation plan. Laboratory measurements of the low-order wavefront control system and coronagraph performance are also presented.
The Planetary Imaging Concept Testbed Using a Recoverable Experiment - Coronagraph (PICTURE-C) mission will directly image debris disks and exozodiacal dust around nearby stars from a high-altitude balloon using a vector vortex coronagraph. One of the many starlight leakage sources that can degrade the performance of the coronagraph is polarization aberration induced by the reflective optical coatings. A polarization ray trace of the PICTURE-C telescope and coronagraph is combined with a physical optics wavefront propagation simulation to quantify the expected amount of coronagraph leakage due to polarization aberration. The simulations show the leakage is below the budgeted contrast of 1 × 10 − 8.
A NASA sounding rocket for high-contrast imaging with a visible nulling coronagraph, the Planet Imaging Concept Testbed Using a Rocket Experiment (PICTURE) payload, has made two suborbital attempts to observe the warm dust disk inferred around Epsilon Eridani. The first flight in 2011 demonstrated a 5 mas fine pointing system in space. The reduced flight data from the second launch, on November 25, 2015, presented herein, demonstrate active sensing of wavefront phase in space. Despite several anomalies in flight, postfacto reduction phase stepping interferometer data provide insight into the wavefront sensing precision and the system stability for a portion of the pupil. These measurements show the actuation of a 32 × 32-actuator microelectromechanical system deformable mirror. The wavefront sensor reached a median precision of 1.4 nm per pixel, with 95% of samples between 0.8 and 12.0 nm per pixel. The median system stability, including telescope and coronagraph wavefront errors other than tip, tilt, and piston, was 3.6 nm per pixel, with 95% of samples between 1.2 and 23.7 nm per pixel.
The Planetary Imaging Concept Testbed Using a Recoverable Experiment - Coronagraph (PICTURE-C) mission will directly image debris disks and exozodiacal dust around three nearby stars from a high-altitude balloon using a vector vortex coronagraph. We present experimental results of the PICTURE-C low-order wavefront control (LOWFC) system utilizing a Shack-Hartmann (SH) sensor in an instrument testbed. The SH sensor drives both the alignment of the telescope secondary mirror using a 6-axis Hexapod and a surface parallel array deformable mirror to remove residual low-order aberrations. The sensor design and actuator calibration methods are discussed and the preliminary LOWFC closed-loop performance is shown to stabilize a reference wavefront to an RMS error of 0.30 ± 0.29 nm.
The Planetary Imaging Concept Testbed Using a Recoverable Experiment - Coronagraph (PICTURE-C) mission will directly image debris disks and exozodiacal dust around nearby stars from a high-altitude balloon using a vector vortex coronagraph. Four leakage sources owing to the optical fabrication tolerances and optical coatings are: electric field conjugation (EFC) residuals, beam walk on the secondary and tertiary mirrors, optical surface scattering, and polarization aberration. Simulations and analysis of these four leakage sources for the PICTUREC optical design are presented here.
The Planetary Imaging Concept Testbed Using a Recoverable Experiment - Coronagraph (PICTURE-C) mission will directly image debris disks and exozodiacal dust around nearby stars from a high-altitude balloon using a vector vortex coronagraph. The PICTURE-C low-order wavefront control (LOWC) system will be used to correct time-varying low-order aberrations due to pointing jitter, gravity sag, thermal deformation, and the gondola pendulum motion. We present the hardware and software implementation of the low-order ShackHartmann and reflective Lyot stop sensors. Development of the high-speed image acquisition and processing system is discussed with the emphasis on the reduction of hardware and computational latencies through the use of a real-time operating system and optimized data handling. By characterizing all of the LOWC latencies, we describe techniques to achieve a framerate of 200 Hz with a mean latency of ∼378 μs
A NASA sounding rocket for high contrast imaging with a visible nulling coronagraph, the Planet Imaging
Coronagraphic Technology Using a Reconfigurable Experimental Base (PICTURE-B) payload has made two
suborbital attempts to observe the warm dust disk inferred around Epsilon Eridani. We present results from the
November 2015 launch demonstrating active wavefront sensing in space with a piezoelectric mirror stage and a
micromachine deformable mirror along with precision pointing and lightweight optics in space.
We describe a set of numerical approaches to modeling the performance of space flight high-contrast imaging payloads. Mission design for high-contrast imaging requires numerical wavefront error propagation to ensure accurate component specifications. For constructed instruments, wavelength and angle-dependent throughput and contrast models allow detailed simulations of science observations, allowing mission planners to select the most productive science targets. The PICTURE family of missions seek to quantify the optical brightness of scattered light from extrasolar debris disks via several high-contrast imaging techniques: sounding rocket (the Planet Imaging Concept Testbed Using a Rocket Experiment) and balloon flights of a visible nulling coronagraph, as well as a balloon flight of a vector vortex coronagraph (the Planetary Imaging Concept Testbed Using a Recoverable Experiment - Coronagraph, PICTURE-C). The rocket mission employs an on-axis 0.5m Gregorian telescope, while the balloon flights will share an unobstructed off-axis 0.6m Gregorian. This work details the flexible approach to polychromatic, end-to-end physical optics simulations used for both the balloon vector vortex coronagraph and rocket visible nulling coronagraph missions. We show the preliminary PICTURE-C telescope and vector vortex coronagraph design will achieve 10-8 contrast without post-processing as limited by realistic optics, but not considering polarization or low-order errors. Simulated science observations of the predicted warm ring around Epsilon Eridani illustrate the performance of both missions.
The PICTURE-C mission will fly a 60 cm off-axis unobscured telescope and two high-contrast coronagraphs in successive high-altitude balloon flights with the goal of directly imaging and spectrally characterizing visible scattered light from exozodiacal dust in the interior 1-10 AU of nearby exoplanetary systems. The first flight in 2017 will use a 10-4 visible nulling coronagraph (previously flown on the PICTURE sounding rocket) and the second flight in 2019 will use a 10-7 vector vortex coronagraph. A low-order wavefront corrector (LOWC) will be used in both flights to remove time-varying aberrations from the coronagraph wavefront. The LOWC actuator is a 76-channel high-stroke deformable mirror packaged on top of a tip-tilt stage. This paper will detail the selection of a complementary high-speed, low-order wavefront sensor (LOWFS) for the mission. The relative performance and feasibility of several LOWFS designs will be compared including the Shack-Hartmann, Lyot LOWFS, and the curvature sensor. To test the different sensors, a model of the time-varying wavefront is constructed using measured pointing data and inertial dynamics models to simulate optical alignment perturbations and surface deformation in the balloon environment.
An exoplanet mission based on a high-altitude balloon is a next logical step in humanity’s quest to explore Earthlike planets in Earthlike orbits orbiting Sunlike stars. The mission described here is capable of spectrally imaging debris disks and exozodiacal light around a number of stars spanning a range of infrared excesses, stellar types, and ages. The mission is designed to characterize the background near those stars, to study the disks themselves, and to look for planets in those systems. The background light scattered and emitted from the disk is a key uncertainty in the mission design of any exoplanet direct imaging mission, thus, its characterization is critically important for future imaging of exoplanets.
We present a monolithic multispectral camera (MMC) for high contrast direct imaging of inner exoplanetary environments. The primary scientific goal of the camera is to enable eight color characterization of jovian exoplanets and interplanetary dust and debris distributions around nearby stars. Technological highlights of the design include: 1. Diffraction limited resolution at 350 nm through active optical aberration correction; 2. Greater than million-to-one contrast at narrow star separation using interferometry and post-processing techniques; 3. Demonstration of deep broadband interferometric nulling and interband image stability through the use of monolithic optical assemblies; 4. Optimization of multispectral throughput while minimizing components.
The Planetary Imaging Concept Testbed Using a Rocket Experiment (PICTURE 36.225 UG) was designed
to directly image the exozodiacal dust disk of ǫ Eridani (K2V, 3.22 pc) down to an inner radius of 1.5 AU.
PICTURE carried four key enabling technologies on board a NASA sounding rocket at 4:25 MDT on October
8th, 2011: a 0.5 m light-weight primary mirror (4.5 kg), a visible nulling coronagraph (VNC) (600-750 nm), a
32x32 element MEMS deformable mirror and a milliarcsecond-class fine pointing system.
Unfortunately, due to a telemetry failure, the PICTURE mission did not achieve scientific success. Nonetheless,
this flight validated the flight-worthiness of the lightweight primary and the VNC. The fine pointing system,
a key requirement for future planet-imaging missions, demonstrated 5.1 mas RMS in-flight pointing stability.
We describe the experiment, its subsystems and flight results. We outline the challenges we faced in developing
this complex payload and our technical approaches.
We present progress in the development of the monolithic achromatic nulling interference coronagraph (MANIC),
a nulling optic designed to enable direct imaging of nearby Jupiter-like exoplanets. The experimental testbed
for measuring the optical path difference (OPD) between the two arms of the nuller and characterizing the
nuller's performance is described. The OPD measurement will be used to determine the relative thicknesses of
compensator plates needed to complete MANIC's fabrication. Demonstrating the performance of the monolith
will include sub-aperture nulling of laser and white-light sources using a single PZT-controlled delay line on one
half of a bisected input beam.
We report progress on a nulling coronagraph intended for direct imaging of extrasolar planets. White light is suppressed
in an interferometer, and phase errors are measured by a second interferometer. A 1020-pixel MEMS deformable mirror
in the first interferometer adjusts the path length across the pupil. A feedback control system reduces deflections of the
deformable mirror to order of 1 nm rms.
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