This PDF file contains the front matter associated with SPIE Proceedings Volume 8450, including the Title Page, Copyright information, Table of Contents, and Conference Committee listing.

Silicon Carbide (SiC) optical materials are being applied widely for both space based and ground based optical telescopes. The material provides a superior weight to stiffness ratio, which is an important metric for the design and fabrication of lightweight space telescopes. The material also has superior thermal properties with a low coefficient of thermal expansion, and a high thermal conductivity. The thermal properties advantages are important for both space based and ground based systems, which typically need to operate under stressing thermal conditions. The paper will review L-3 Integrated Optical Systems – SSG’s (L-3 SSG) work in developing SiC optics and SiC optical systems for astronomical observing systems. L-3 SSG has been fielding SiC optical components and systems for over 25 years. Space systems described will emphasize the recently launched Long Range Reconnaissance Imager (LORRI) developed for JHU-APL and NASA-GSFC. Review of ground based applications of SiC will include supporting L-3 IOS-Brashear’s current contract to provide the 0.65 meter diameter, aspheric SiC secondary mirror for the Advanced Technology Solar Telescope (ATST).

The LISA Optical Stability Characterization project is part of the LISA CTP activities to achieve the required Technonlogy Readiness Level (TRL) for all of the LISA technologies used. This activity aims demonstration of the Telescope Assembly (TA), with a structure based on CFRP technology, that a CTE of 10^-7 1/K can be achieved with measures to tune the CTE to this level. In addition the demonstration is required to prove that the structure exhibits highly predictable mechanical distortion characteristics when cooling down to -90°C, during outgassing in space and when going from 1g environment to 0g. This paper describes the test facilities as well as the first test results. A dedicated test setup is designed and realized to allow monitoring dimensional variations of the TA using three interferometers, while varying the temperature in a thermal vacuum chamber. Critical parameters of the verification setup are the length metrology accuracy in thermal vacuum and the thermal vacuum flexibility and stability. The test programme includes Telescope Assembly CTE measurements and thermal gradient characterization.

The Segmented Mirror Telescope (SMT) at the Naval Postgraduate School (NPS) in Monterey is a next-generation deployable telescope, featuring a 3-meter 6-segment primary mirror and advanced wavefront sensing and correction capabilities. In its stowed configuration, the SMT primary mirror segments collapse into a small volume; once on location, these segments open to the full 3-meter diameter. The segments must be very accurately aligned after deployment and the segment surfaces are actively controlled using numerous small, embedded actuators. The SMT employs a passive damping system to complement the actuators and mitigate the effects of low-frequency (<40 Hz) vibration modes of the primary mirror segments. Each of the six segments has three or more modes in this bandwidth, and resonant vibration excited by acoustics or small disturbances on the structure can result in phase mismatches between adjacent segments thereby degrading image quality. The damping system consists of two tuned mass dampers (TMDs) for each of the mirror segments. An adjustable TMD with passive magnetic damping was selected to minimize sensitivity to changes in temperature; both frequency and damping characteristics can be tuned for optimal vibration mitigation. Modal testing was performed with a laser vibrometry system to characterize the SMT segments with and without the TMDs. Objectives of this test were to determine operating deflection shapes of the mirror and to quantify segment edge displacements; relative alignment of λ/4 or better was desired. The TMDs attenuated the vibration amplitudes by 80% and reduced adjacent segment phase mismatches to acceptable levels.

The Atacama Large Millimeter Array (ALMA) consists of a large number of 12m diameter antennas that will operate up to 950GHz. The antenna must meet all primary operational performances also during solar observation. When the antenna is pointing directly the sun or when the sun is close to the boresight axis, the solar power concentrated by the mirrors cannot damage any part of the antenna. When the antenna is pointing toward the sun, the power absorbed by a black body positioned in the secondary focal area shall not exceed 0.3 W/cm2. To achieve these requirements, the primary surface of the antenna has a suitable surface scattering treatment. The same thing was done for the surface of the subreflector. Specific tests were performed on the panels surface and secondary mirror during the prototype and production phase in order to optimize the best behaviour. A particular care must be applied in the control of the secondary area, where the entire solar power spectrum, from the UV to the infrared, reflected by the primary mirror, can contribute to overheat reflecting areas support structures. In this report we provide a series of analysis and results obtained during the solar observation.

The completely open-foldable dome of the GREGOR telescope is a further development of the DOT dome, respectively 9 and 7 meter in diameter. New technical developments are implemented and tested at the GREGOR dome, that are important for the design of the much larger dome for the EST, which will be 28 meter in diameter. The GREGOR dome is the first with more than one clamp working simultaneously for closing the dome and bringing the membranes on the required high tension for storm resistance. The storm Delta with 245 km/h 1-minute mean maximum at the location of the GREGOR gave no problems nor did the storms afterwards. Opening and closing experiences are up to wind speeds of 90 km/h without problems. Good observing circumstances never occur with higher wind speeds. A double layer of membranes is applied in the GREGOR construction whereas the DOT dome is equipped with a single layer. Simultaneous climate measurements inside and outside the dome have proven the thermal-insulation capability of this double-layer construction. The experiences with the GREGOR showed that the elongation by tensioning of the prestrained membrane material is much lower than originally expected. In the meantime, more strong and stiff membrane material is available and applied in the EST design. As a consequence, the clamps of the EST can have a relatively much shorter length and there is no need anymore for simultaneous operation of the clamps and the main actuators in low speed with help of a frequency inverter. The clamps can close after the main bow operation is finished, which simplifies the electrical control.

Modern astronomical instrumentation is often developed through non traditional congurations and free form optics. Recent technological development allows the manufacturing of exotic surfaces, sometimes very far away from rotationally symmetric geometries. We propose new developments of the solid telescope concept using multiple re ections between the faces of a single lens. Taking advantage of modern materials and manufacturing solutions, a compact, robust, and easily replicable optical subsystem could represent an optimal solution for small telescopes tailored to specic applications. In this paper we describe the solution for an instrument devoted to the fast transients detection and tracking.

The mirror segments for the E-ELT and TLT are nearly equal in size and shape (hexagonal, 1.2 m over flat sides). They are very thin (about 50 mm) compared to their size. Supporting these mirrors and obtaining high optical performance is a challenge from design and manufacturing point of view. TNO has designed and build (together with VDL-ETG) three identical prototypes for supporting the mirror segments of the E-ELT. These mirror segments vary in size. Hence the gravity induced deformation of the mirror segments will vary from mirror to mirror segment when no measures are taken. The paper will concentrate on the design and analysis of the design features within the support structure to minimize the mirror deformation due to gravity. These features concern passive and active means to influence the mirror segment shape and to compensate for deformation differences.

The stochastic parallel gradient descent algorithm based on the generalized phase diversity wavefront sensor is presented for co-phasing of segmented mirrors. Cost functions of the optimization algorithm were built up in different circular zones for intensity images of the sensor. In order to achieve high accuracy for co-phasing, four phase diversity functions with increasing amplitudes were applied to the sensor for improving the strength of output signal from the wavefront sensor during the aberrations of the segmented mirror decreasing with the co-phasing process. A simulated segmented mirror was used to test the feasibility of this method. The numerical experiments show that the co-phasing accuracy is very high for the aberrations of the segmented mirrors less than 1.5 wavelengths. And the algorithm is very robust and noise tolerant.

Detection and observation of gravitational waves requires extreme stability in the frequency range 3e-5 Hz to 1 Hz. NGO/LISA will attain this by creating a giant interferometer in space, based on free floating proof masses in three spacecrafts. To operate NGO/LISA, the following piezo mechanisms are developed: 1. A piezo stack mechanism (Point Angle Ahead Mechanism) Due to time delay in the interferometer arms, the beam angle needs to be corrected. A mechanism rotating a mirror with a piezo stack performs this task. The critical requirements are the contribution to the optical path difference (less than 1.4 pm/√Hz) and the angular jitter (less than 8 nrad/√Hz). 2. A piezo sliding mechanism (Fiber Switching Unit Actuator) To switch from primary to the redundant laser source, a Fiber Switching Unit Actuator (FSUA) is developed. The critical requirements are the coalignment of outgoing beams of <+/-1 micro radian and <+/-1 micro meter. A redundant piezo sliding mechanism rotates a wave plate over 45 degrees. 3. A piezo stepping mechanism (In Field Pointing Mechanism) Due to seasonal orbit evolution effects, beams have to be corrected over a stroke of +/-2.5 degrees. The critical requirements are the contribution to the optical path difference (less than 3.0 pm/√Hz) and the angular jitter (less than 1 nrad/√Hz). Due to the large stroke, a piezo stepping concept was selected. Dedicated control algorithms have been implemented to achieve these challenging requirements. This paper gives description of the designs and the ongoing process of qualifying the mechanisms for space applications.

The spectroscopy of the far UV emission lines of the solar spectrum combined with an imaging capability is essential to understand the physics of the outer solar atmosphere. An imaging Fourier transform spectrometer (IFTSUV) is an attractive instrumental solution to perform such far-UV solar observations. Working in the far UV involves high precision metrology to maintain the optical path difference (OPD) during the entire scanning process of the interferogram. It also involves a compact all-reflection design for UV applications. We present the specification of a servo-system that enables dynamic tip/tilt alignment compensation and OPD sampling measurement of the IFTSUV scanning mirror. We also discuss the first experimental results of a breadboard as well as the preliminary design of a space-based device.

This paper wants to illustrate possible applications of Shape Memory Alloy (SMA) as functional devices for space and ground based application in Instrumentations for Astronomy. Thermal activated Shape Memory Alloys are materials able to recover their original shape, after an external deformation, if heated above a characteristic temperature. If the recovery of the shape is completely or partially prevented by the presence of constraints, the material can generate recovery stress. Thanks to this feature, these materials can be positively exploited in Smart Structures if properly embedded into host materials. Some technological processes developed for an ecient use of SMA-based actuators embedded in smart structures tailored to astronomical instrumentation will be presented here. Some possible modeling approaches of the actuators behavior will be addressed taking into account trade- offs between detailed analysis and overall performance prediction as a function of the computational time. The Material characterization procedure adopted for the constitutive laws implementation will be described as well. Deformable composite mirrors,1 opto-mechanical mounting with superelastic kinematic behavior and damping of launch loads onto optical element2 are feasible applications that will be deeply investigated in this paper.

A liquid atmospheric dispersion corrector (LADC) is investigated to compensate atmospheric dispersion for modern extremely large telescopes (ELTs). The LADC uses a pair of immiscible liquids in a small glass container which can be placed very close to the telescope focal plane. A pair of liquid prisms is formed and the apex of the two prisms varies with telescope zenith because of gravity. The idea is that a large number of independent deployable units (e.g., AAO's 'Starbugs') would each carry its own LADC. Three pairs of liquids were identified that were found suitable for use in an LADC after thousands of chemicals were investigated. We have theoretically and experimentally verified that LADC can correct atmospheric dispersion adaptively. It is demonstrated that a LADC can correct a simulated atmospheric dispersion of 0.34° at a Zenith of 48°, over a wavelength range of 370nm to 655nm. The experimental results show very good agreement with the optical (Zemax) model.

Liquid lenses have been developed as a means for fast and reliable variable-focus optics by using an adjustable curvature in a liquid-liquid interface. The use of liquid lenses also provides the benefit of reducing the number of elements in a system, and providing a degree of freedom without any moving parts. Different methods for surface curvature actuation have been developed, including aperture adjustment, mechanical actuators, stimuli-responsive hydrogels, and mechanical-wetting. Current liquid lens designs are limited to small apertures (less than 4mm) and density-matching fluids to lessen the negative effects of gravity. By creating a lens intended for use in a microgravity environment, the aperture size can be increased by orders of magnitude, and optimal fluids can be used regardless of their density. Using a large-aperture (12mm) liquid lens, image and surface metrology was conducted using a fixed-focus configuration. The Software Configurable Optical Test System (SCOTS) method was utilized to test the effect of microgravity, standard gravity, and hypergravity on the liquid lens during parabolic flights. Under standard gravity, the RMS wavefront error (WFE) was 27 wavelengths, while microgravity conditions allowed an improvement to 17 wavelengths RMS WFE. Test performance can be improved by using lower viscosity fluids or longer duration microgravity flights. The experiment also served as an engineering demonstration for the SCOTS method in an environment where other methods of optical metrology would be impossible.

Small deformable mirrors (DMs) produced using microelectromechanical systems (MEMS) techniques have been used in thermally stable, bench-top laboratory environments. With advances in MEMS DM technology, a variety of field applications are becoming more common, such as the Gemini Planet Imager’s (GPI) adaptive optics system. Instruments at the Gemini Observatory operate in conditions where fluctuating ambient temperature, varying gravity orientations and humidity and dust can have a significant effect on DM performance. As such, it is crucial that the mechanical design of the MEMS DM mount be tailored to the environment. GPI’s approach has been to mount a 4096 actuator MEMS DM, developed by Boston Micromachines Corporation, using high performance optical mounting techniques rather than a typical laboratory set-up. Flexures are incorporated into the DM mount to reduce deformations on the optical surface due to thermal fluctuations. These flexures have also been sized to maintain alignment under varying gravity vector orientations. This paper is a follow-up to a previous paper which presented the preliminary design. The completed design of the opto-mechanical mounting scheme is discussed and results from finite element analysis are presented, including predicting the stability of the mirror surface in varying gravity vectors and thermal conditions.

In order to maintain image quality during Javalambre wide field telescope operations, deformations and rigid body motions must be actively controlled to minimize optical disturbances. For JST/T250 the aberrations of the telescope will be measured with four curvature sensors at the focal plane. To correct the measured distortions, the secondary mirror position (with a hexapod support) and the camera position can be modified in a control closed loop. Multiple software tools have been developed to accomplish this goal, constituting the "Observatorio Astrofísico de Javalambre" (OAJ) Active Optics Pipeline. We present a comprehensive analysis of the wave-front sensing system, including the availability of reference stars, pupil registration, wavefront estimators and the iteration matrix evaluation techniques. Some preliminary simulations have been made using a telescope model with a Optical Ray Tracing Software.

In this paper, we present two original concepts of deformable mirrors to compensate for first orders optical aberrations with a minimum number of actuators: one optical mode is generated with one actuator. The Variable O_-Axis parabola (VOALA) concept is a 3-actuators, 3-modes system able to generate independently Focus, Astigmatism3 and Coma3. The Correcting Optimized Mirror with a Single Actuator (COMSA) is a 1-actuator system able to generate a given combination of optical aberrations. The limited number of degrees of freedom of such systems makes them easy to set up and monitor, which is a significant advantage, notably for space use.

As the costs of space missions continue to rise, the demand for compact, low mass, low-cost technologies that maintain high reliability and facilitate high performance is increasing. One such technology is the stabilized dispersive focal plane system (SDFPS). This technology provides image stabilization while simultaneously delivering spectroscopic or direct imaging functionality using only a single optical path and detector. Typical systems require multiple expensive optical trains and/or detectors, sometimes at the expense of photon throughput. The SDFPS is ideal for performing wide-field low-resolution space-based spectroscopic and direct-imaging surveys. In preparation for a suborbital flight, we have built and ground tested a prototype SDFPS that will concurrently eliminate unwanted image blurring due to the lack of adequate platform stability, while producing images in both spectroscopic and direct-imaging modes. We present the overall design, testing results, and potential scientific applications.

Architecture choices impact planning and scheduling of activity sequences for two widely separated spacecraft envisioned to be part of an astrophysics mission to observe extra-solar-planets. The two spacecraft consist of a large space telescope and an external occulter, separated by tens of thousands of kilometres. The science need is to maintain alignment at the tens of milliarcseconds level (~ metres) or less on given target stars after moving one of the spacecraft tens of thousands of kilometres. Doing this efficiently presents operational and architectural design challenges that rely on appropriate choice of navigation, propulsion, and alignment technologies, vehicle configuration, and activity scheduling strategies—an extensive combination of which may potentially be chosen from for such a mission. Challenges inherent in the general system architecture are described with emphasis on potential problems and the need for sound and appropriate integration of architecture planning, subsystem choice, and activity scheduling.

The apodizing phase plate (APP) is a solid-state pupil optic that clears out a D-shaped area next to the core of the ensuing PSF. To make the APP more efficient for high-contrast imaging, its bandwidth should be as large as possible, and the location of the D-shaped area should be easily swapped to the other side of the PSF. We present the design of a broadband APP that yields two PSFs that have the opposite sides cleared out. Both properties are enabled by a half-wave liquid crystal layer, for which the local fast axis orientation over the pupil is forced to follow the required phase structure. For each of the two circular polarization states, the required phase apodization is thus obtained, and, moreover, the PSFs after a quarter-wave plate and a polarizing beam-splitter are complementary due to the antisymmetric nature of the phase apodization. The device can be achromatized in the same way as half-wave plates of the Pancharatnam type or by layering self-aligning twisted liquid crystals to form a monolithic film called a multi-twist retarder. As the VAPP introduces a known phase diversity between the two PSFs, they may be used directly for wavefront sensing. By applying an additional quarter-wave plate in front, the device also acts as a regular polarizing beam-splitter, which therefore furnishes high-contrast polarimetric imaging. If the PSF core is not saturated, the polarimetric dual-beam correction can also be applied to polarized circumstellar structure. The prototype results show the viability of the vector-APP concept.

Circular phase mask concepts represent promising options for high contrast imaging and spectroscopy of exo-planets. Depending on their design, they can either work as a diffraction suppression system or as a focal plane wavefront sensor. While the apodized Roddier coronagraph uses a π-phase mask to obtain complete suppression of the star image in monochromatic light, the Zernike sensor uses a π/2-phase mask to measure the residual aberrations in the focal plane by encoding them into intensity variations in the relayed pupil. Implementations of the Zernike sensor can be considered in exoplanet imagers such as VLT-SPHERE, Gemini planet imager, Palomar-P1640 or Subaru-SCExAO to enlarge their capabilities. However, such concepts have not been validated experimentally up to now. Our goal is to perform lab demonstration of this concept on our visible coronagraph testbed at LAM and to propose an upgrade design for SPHERE. In this communication, we report on results of lab measurements of the Zernike sensor and determine its sensitivity to small wavefront errors.

The K-Band Multi-Object Spectrometer Integral Field Unit (KMOS IFU) is a complex optical instrument with over a thousand diamond machined optical surfaces. Many of these surfaces are highly unorthodox and extremely difficult to characterise accurately. In this paper, we summarise the analysis of form and surface texture measurements made on these complex surfaces. In particular we focus on a general analysis of all the form measurement results. The measurement of such a large number of surfaces offers an unprecedented opportunity for the general analysis of form errors in complex diamond machined surfaces. The wealth of statistical information is of exceptional value in the refinement of the manufacturing process. In particular, we analyse in some detail the variation of form error contributions with spatial frequency. In general, there is a substantial reduction in form error contribution with spatial frequency. This form error variation with spatial frequency may also be modelled using Zernike polynomials. This approach is particularly suited to optical modelling of systems incorporating such perturbed components. As such, this knowledge can be applied directly to the modelling of form errors in new optical designs. Application to tolerance modelling of future instrument designs is discussed.

For the Euclid mission a Pre-Development phase is implemented to prove feasibility of individual components of the system [1]. The Near Infrared Spectrometer and Photometer (NISP) of EUCLID requires high precision large lens holders (Ø170 mm) at cryogenic temperatures (150K). The four lenses of the optical system are made of different materials: fused silica, CaF2, and LF5G15 that are mounted in a separate lens barrel design. Each lens has its separate mechanical interface to the lens barrel, the so called adaption ring. The performance of the lens holder design is verified by adapted test equipment and test facility including an optical metrology system. The characterization of the lens deformation and displacement (decenter, tilt) due to mechanical loads of the holder itself as well as thermally induced loads are driven by the required submicron precision range and the operational thermal condition. The surface deformation of the lens and its holder is verified by interferometric measurements, while tilt and position accuracy are measured by in-situ fibre based distance sensors. The selected distance measurement sensors have the capability to measure in a few mm range with submicron resolution in ultra high vacuum, in vibration environments and at liquid nitrogen temperatures and below. The calibration of the measurement system is of crucial importance: impacts such as temperature fluctuation, surface roughness, surface reflectivity, straylight effects, etc. on the measured distance are carefully calibrated. Inbuilt thermal expansion effects of the fibre sensors are characterized and proven with lens dummy with quasi zero CTE. The paper presents the test results and measured performance of the high precision large cryogenic lens holders attained by the metrology system. These results are presented on behalf of the EUCLID consortium.

Structural materials with extremely low coecient of thermal expansion (CTE) are crucial to enable ultimate accuracy in terrestrial as well as in space-based optical metrology due to minimized temperature dependency. Typical materials, in particular in the context of space-based instrumentation are carbon-ber reinforced plastics (CFRP), C/SiC, and glass ceramics, e.g. Zerodur, ULE or Clearceram. To determine the CTE of various samples with high accuracy we utilize a highly symmetric heterodyne interferometer with a noise level below 2 pm√Hz at frequencies above 0.1 Hz. A sample tube made out of the material under investigation is vertically mounted in an ultra-stable support made of Zerodur. Measurement and reference mirrors of the interferometer are supported inside the tube using thermally compensated mounts made of Invar36. For determination of the CTE, a sinusoidal temperature variation is radiatively applied to the tube. One of the essential systematic limitations is a tilt of the entire tube as a result of temperature variation. This tilt can simultaneously be measured by the DWS technique and can be used to correct the measurement. Using a Zerodur tube as a reference, it is shown that this eect can be reduced in post processing to achieve a minimum CTE measurement sensitivity <10 ppb/K.

The James Webb Space Telescope (JWST) Optical Telescope Element (OTE) consists of a 6.6 meter clear aperture, all-reflective, three-mirror anastigmat. The 18-segment primary mirror (PM) presents unique and challenging assembly, integration, alignment and testing requirements. A full aperture center of curvature optical test is performed in cryogenic vacuum conditions at the integrated observatory level to verify PM performance requirements. Two wavefront calibration tests are utilized to verify the low and mid/high spatial frequency performance of the test system. In this paper the methods and results of the wavefront calibration tests are presented.

Improving the precision of observational astronomy requires not only new telescopes and instrumentation, but also advances in observing protocols, calibrations and data analysis. The Laser Applications Group at the National Institute of Standards and Technology in Gaithersburg, Maryland has been applying advances in detector metrology and tunable laser calibrations to problems in astronomy since 2007. Using similar measurement techniques, we have addressed a number of seemingly disparate issues: precision flux calibration for broad-band imaging, precision wavelength calibration for high-resolution spectroscopy, and precision PSF mapping for fiber spectrographs of any resolution. In each case, we rely on robust, commercially-available laboratory technology that is readily adapted to use at an observatory. In this paper, we give an overview of these techniques.

The Atacama Large Millimeter Array (ALMA) consists of a large number of 12m-diameter antennas that will operate up to 950GHz. To guarantee the scientific requirement in terms of pointing stability and residual delay, a dynamic and thermal Metrology System has to be integrated in the antenna. As a matter of fact, the antennas have to work at full performances in free air, in the night and in the day. Consequently, the performances are affected by all the nonrepeatable error sources, such as temperature variations and wind, blowing from different directions. The antenna is a very light and stiff structure, the elevation structure is in carbon fibre with also a very low thermal expansion coefficient, but in order to meet the ALMA specifications, thermal and dynamic corrections have to be applied. The Thermal Metrology is composed by a number of thermal sensors distributed on the antenna that compensate the elevation axis deformation due to temperature variations. The dynamic Metrology is based on two high-accuracy inclinometers with a very short recovery time, opportunely placed on the main structure. This report shows the results of the tests performed on the AEM antennas with both systems. The good performance of the systems, allowing the antenna to meet the specification during all observation condition and mode, is thus evident.

An imaging displacement sensor (IDS) has been developed that can measure the displacement with an accuracy of 30 nm in 0.03 s with the precision improving to 1 nm for averaging times of 100 s. The IDS consists simply of a light emitting diode (LED) pinhole collimator and a charge-coupled device (CCD) camera chip. The position accuracy is better than 0.05% over the few mm CCD size with deviation from linearity <140 nm. All six degrees of freedom (DoF), three translations and three angles, can be measured with the same accuracy by combining multiple IDS with different collimator beam orientations and knowing the nominal separation between the collimators and CCDs.

The image moment-based wavefront sensing (IWFS) utilizes moments of focus-modulated focal plane images to determine modal wavefront aberrations. This permits fast, easy, and accurate measurement of wavefront error (WFE) on any available finite-sized isolated targets across the entire focal plane (FP) of an imaging system, thereby allowing not only in-situ full-field image quality assessment, but also deterministic fine alignment correction of the imaging system. We present an experimental demonstration where fine alignment correction of a fast camera system in a fiber-fed astronomical spectrograph, called VIRUS, is accomplished by using IWFS.

A software configurable optical test system (SCOTS) based on fringe reflection was implemented for measuring the primary mirror segments of the Giant Magellan Telescope (GMT). The system uses modulated fringe patterns on an LCD monitor as the source, and captures data with a CCD camera and calibrated imaging optics. The large dynamic range of SCOTS provides good measurement of regions with large slopes that cannot be captured reliably with interferometry. So the principal value of the SCOTS test for GMT is to provide accurate measurements that extend clear to the edge of the glass, even while the figure is in a rough state of figure, where the slopes are still high. Accurate calibration of the geometry and the mapping also enable the SCOTS test to achieve accuracy that is comparable measurement accuracy to the interferometric null test for the small- and middle- spatial scale errors in the GMT mirror.

Full aperture interferometric metrology has enabled fabrication and verification of large primary mirrors with nm precision. The measurement of mirrors that are several meters in diameter with flat or convex aspheric surfaces can be performed using interferometric measurements of overlapping subaperture regions, then stitching the date from these measurements together to provide a full map. This paper explores the application of this measurement technique for very large mirrors, and discusses issues for measuring large flat or convex mirrors.

The principles for the realization of rewritable point-diffraction interferometers (PDIs) based on photochromic polyurethane films are described. Pinholes of variable sizes (diameter from 4 to 40 μm) have been optically written onto photochromic substrates converting locally the material from the colored to the uncolored form. The PDIs have been mounted in an interferometric setup and different reflective optics have been tested. By a controlled bleaching of the semi-transparent area around the pinhole, an optimal visibility in the interferograms is reached. Under this conditions several tests of reliability of the interferometer have been carried out.

We describe the optical test of a large flat based on a spherical mirror and a dedicated CGH. The spherical mirror, which can be accurately manufactured and tested in absolute way, allows to obtain a quasi collimated light beam, and the hologram performs the residual wavefront correction. Alignment tools for the spherical mirror and the hologram itself are encoded in the CGH. Sensitivity to fabrication errors and alignment has been evaluated. Tests to verify the effectiveness of our approach are now under execution.

We investigate the possibility to produce photochromic CGHs with maskless lithography methods. For this purpose, optical properties and requirements of photochromic materials will be shown. A diarylethene-based polyurethane is developed and characterized. The resolution limit and the in uence of the writing parameters on the produced patterns, namely speed rate and light power, have been determined. After the optimization of the writing process, gratings and Fresnel Zone Plates are produced on the photochromic layer and diraction eciencies are measured. Improvements and perspectives will be discussed.

Ground based near-infrared observations have long been plagued by poor sensitivity when compared to visible observations as a result of the bright narrow line emission from atmospheric OH molecules. The GNOSIS instrument recently commissioned at the Australian Astronomical Observatory uses Photonic Lanterns in combination with individually printed single mode fibre Bragg gratings to filter out the brightest OH-emission lines between 1.47 and 1.70μm. GNOSIS, reported in a separate paper in this conference, demonstrates excellent OH-suppression, providing very “clean” filtering of the lines. It represents a major step forward in the goal to improve the sensitivity of ground based near-infrared observation to that possible at visible wavelengths, however, the filter units are relatively bulky and costly to produce. The 2nd generation fibre OH-Suppression filters based on multicore fibres are currently under development. The development aims to produce high quality, cost effective, compact and robust OH-Suppression units in a single optical fibre with numerous isolated single mode cores that replicate the function and performance of the current generation of “conventional” photonic lantern based devices. In this paper we present the early results from the multicore fibre development and multicore fibre Bragg grating imprinting process.

For the PRV instrument using simultaneous calibration technique such as with sources like thorium lamps, Fabry Perot Etalons or laser comb, it is essential that the instrument stays stable between the wavelength calibration frame and the actual scientific measurement. These instruments are usually in pressure and temperature controlled environments for example under vacuum. However this is not sufficient to reach the instrumental stability required to get to precision level of the ms^-1 and below required to build the next generation PRV instruments. Another requirement is an as constant as possible illumination of the spectrograph to stabilize the line profile of the instrument. To achieve this, it is necessary to use a device that will scramble the light coming from the star to mitigate the effects of the atmosphere. In addition this device should not increase significantly the beam etendue, which is already a technological challenge for large telescopes. The common solution to this problem is to use optical fibers. Historically the solution has been to use circular fibers as they were the only one available. Recently for other purposes non-circular fibers have been developed and made available. They have been tested, and present an important improvement in the scrambling over the circular fibers. We will present in this paper the properties of the octagonal fibers used for the HARPS-N2 instrument and the achieved performance of its fiber train.

Optical fibres play more and more important roles in astronomy, for example, to transfer light from the focus point of telescopes to spectrometers. In this paper, a novel designed, a fibre-brush-shape converter was designed to transfer circle input of a fibre to a line-shape output. The brush-shape converter consists of several bare fibres at one end, one fibre at the other end and a taper between them. The light propagating from the bare fibres to the single fibre will be coupled. According to the theoretical and calculated results, the power of the light could be confined in the core of the fibre if the parameters of the taper are appropriate.

In this paper we present theoretical and laboratory results on integrated directly-written photonic lanterns with varying taper lengths. These lanterns convert seeing-limited light into multiple diffraction limited signals, in other words, a multimode signal into multiple single-mode signals. We investigated 19-channel structures which were written within a 30-mm-long glass block and designed to operate at 1550 nm. A single structure consisted of a multimode waveguide which transitioned into an array of single-mode waveguides and then back to a multimode waveguide utilizing cosine taper transitions. Based on simulations we found that transition lengths of 6 mm were sufficient to obtain throughput at a level of ~95%. Fabricated devices showed losses (coupling and transition losses) at the level of 30% for injection F/# < 5 and taper lengths < 5 mm. We believe that such devices show great promise for future use in astronomy.

The Prime Focus Spectrograph (PFS) is a fiber fed multi-object spectrometer for the Subaru Telescope that will conduct a variety of targeted surveys for studies of dark energy, galaxy evolution, and galactic archaeology. The key to the instrument is a high density array of fiber positioners placed at the prime focus of the Subaru Telescope. The system, nicknamed “Cobra”, will be capable of rapidly reconfiguring the array of 2394 optical fibers to the image positions of astronomical targets in the focal plane with high accuracy. The system uses 2394 individual “SCARA robot” mechanisms that are 7.7mm in diameter and use 2 piezo-electric rotary motors to individually position each of the optical fibers within its patrol region. Testing demonstrates that the Cobra positioner can be moved to within 5μm of an astronomical target in 6 move iterations with a success rate of 95%. The Cobra system is a key aspect of PFS that will enable its unprecedented combination of high-multiplex factor and observing efficiency on the Subaru telescope. The requirements, design, and prototyping efforts for the fiber positioner system for the PFS are described here as are the plans for modular construction, assembly, integration, functional testing, and performance validation.

Following the successful commissioning of SAMI (Sydney-AAO Multi-object IFU) the AAO has undertaken concept studies leading to a design of a new instrument for the AAT (Hector). It will use an automated robotic system for the deployment of fibre hexabundles to the focal plane. We have analysed several concepts, which could be applied in the design of new instruments or as a retrofit to existing positioning systems. We look at derivatives of Starbugs that could handle a large fibre bundle as well as modifications to pick and place robots like 2dF or OzPoz. One concept uses large magnetic buttons that adhere to a steel field plate with substantial force. To move them we replace the gripper with a pneumatic device, which engages with the button and injects it with compressed air, thus forming a magnet preloaded air bearing allowing virtually friction-less repositioning of the button by a gantry or an R-Theta robot. New fibre protection, guiding and retraction systems are also described. These developments could open a practical avenue for the upgrade to a number of instruments.

A multiple pick off mirror positioning sub-system has been developed as a solution for the deployment of mirrors within multi-object instrumentation such as the EAGLE instrument in the European Extremely Large Telescope (E-ELT). The positioning sub-system is a two wheeled differential steered friction drive robot with a footprint of approximately 20 x 20 mm. Controlled by RF communications there are two versions of the robot that exist. One is powered by a single cell lithium ion battery and the other utilises a power floor system. The robots use two brushless DC motors with 125:1 planetary gear heads for positioning in the coarse drive stages. A unique power floor allows the robots to be positioned at any location in any orientation on the focal plane. The design, linear repeatability tests, metrology and power continuity of the robot will be evaluated and presented in this paper. To gather photons from the objects of interest it is important to position POMs within a sphere of confusion of less than 10 μm, with an angular alignment better than 1 mrad. The robots potential of meeting these requirements will be described through the open-loop repeatability tests conducted with a Faro laser beam tracker. Tests have involved sending the robot step commands and automatically taking continuous measurements every three seconds. Currently the robot is capable of repeatedly travelling 233 mm within 0.307 mm at 5 mm/s. An analysis of the power floors reliability through the continuous monitoring of the voltage across the tracks with a Pico logger will also be presented.

Starbugs are miniature piezoelectric 'walking' robots with the ability to simultaneously position many optical fibres across a telescope's focal plane. Their simple design incorporates two piezoceramic tubes to form a pair of concentric 'legs' capable of taking individual steps of a few microns, yet with the capacity to move a payload several millimetres per second. The Australian Astronomical Observatory has developed this technology to enable fast and accurate field reconfigurations without the inherent limitations of more traditional positioning techniques, such as the 'pick and place' robotic arm. We report on our recent successes in demonstrating Starbug technology, driven principally by R&D efforts for the planned MANIFEST (many instrument fibre-system) facility for the Giant Magellan Telescope. Significant performance gains have resulted from improvements to the Starbug system, including i) the use of a vacuum to attach Starbugs to the underside of a transparent field plate, ii) optimisation of the control electronics, iii) a simplified mechanical design with high sensitivity piezo actuators, and iv) the construction of a dedicated laboratory 'test rig'. A method of reliably rotating Starbugs in steps of several arcminutes has also been devised, which integrates with the pre-existing x-y movement directions and offers greater flexibility while positioning. We present measured performance data from a prototype system of 10 Starbugs under full (closed-loop) control, at field plate angles of 0-90 degrees.

Many heating units exist on the fiber positioning device of LAMOST, and the heat has certain effect on the observation of telescope. Experimental and theoretical analysis methods are proposed in this paper to study the heat effect on the focal plane caused by heating units. In this paper, we mainly describe the experimental part. A temperature acquisition system is established on a simplified focal plane on which a group of fiber positioning units are installed. The thermal imager is used to determine the heating parts of the fiber positioning units. Thermocouples are bonded on the surface of heating parts and focal plane to sense the temperature change and the curve of the results are shown in LabVIEW. Temperature data obtained by the experiment is applied as initial conditions of theoretical analysis and a comparison with the analysis result. The thermal analysis software I-DEAS will be used to analyze the temperature field of the simplified focal plane, then a comparison will be made between experimental and theoretical analysis to confirm the rationality of simulation models for further research of LAMOST fiber positioning device. Based on the above research objectives, arrange the experiment. The research results have instructive significance for the LAMOST focal plane cooling solutions.

We present a new concept for a Doppler imaging remote sensing instrument to track moving objects within a wide field of view using a compact multi-object Dispersed Fixed-Delay Interferometer (DFDI). The instrument is a combination of a Michelson type interferometer with a fixed optical delay and a medium resolution spectrograph. This takes advantage of the strength of the DFDI approach over the traditional cross-dispersed echelle spectrograph approach for high radial velocity (RV) precision measurements: multi-object capability, high throughput and a compact design. The combination of a fiber integral field unit (IFU) with a DFDI instrument allows simultaneous sampling of all of the objects within the observing field of view (FOV) to provide differential RV measurements of moving objects over background objects. Due to the three dimensional nature of the IFU spectroscopy the object location and spectral features can be simultaneously acquired. With the addition of RV signals to the measurements, this approach allows precise extraction of trajectories and spectral properties of moving objects (such as space debris and near Earth Objects (NEOs)) through sequential monitoring of moving objects. Measurement results from moving objects in a lab as well as moving cars in a field using this innovative approach are reported.

In addition to their compactness, scalability and specific task customization, optical MEMS could generate new functions not available with current technologies and are thus candidates for the design of future space instruments. Most mature components for space applications are the Digital Mirror Device (DMD) from Texas Instruments (TI), the micro-deformable mirrors, the Programmable Micro Diffraction Grating and the tiltable micro-mirrors. Among 20-30 MEMS-based payloads concepts, two concepts are selected. The first concept is a programmable slit for straylight control for space spectro-imagers. This instrument is a push-broom spectro-imager for which some images cannot be exploited because of bright sources in the field-of-view. The proposed concept consists in replacing the current entrance spectrometer slit by an active row of micro-mirrors. The MEMS will permit to dynamically remove the bright sources and then to obtain a field-of-view with an optically enhanced signal-to-noise ratio. The second concept is a push-broom imager for which the acquired spectrum can be tuned by optical MEMS. This system is composed of two diffractive elements and a TI’s DMD component. The first diffractive element spreads the spectrum. A micro-mirror array is set at the location of the spectral focal plane. By putting the micro-mirrors ON or OFF, we can select parts of field-of-view or spectrum. The second diffractive element then recombines the light on a push-broom detector. Dichroics filters, strip filter, band-pass filter could be replaced by a unique instrument.

Multi-object spectroscopy (MOS) is a powerful tool for space and ground-based telescopes for the study of the formation and evolution of galaxies. This technique requires a programmable slit mask for astronomical object selection. We are engaged in a European development of micromirror arrays (MMA) for generating reflective slit masks in future MOS, called MIRA. The 100 x 200 μm² micromirrors are electrostatically tilted providing a precise angle. The main requirements are cryogenic environment capabilities, precise and uniform tilt angle over the whole device, uniformity of the mirror voltage-tilt hysteresis and a low mirror deformation. A first MMA with single-crystal silicon micromirrors was successfully designed, fabricated and tested. A new generation of micromirror arrays composed of 2048 micromirrors (32 x 64) and modelled for individual addressing were fabricated using fusion and eutectic wafer-level bonding. These micromirrors without coating show a peak-to-valley deformation less than 10 nm, a tilt angle of 24° for an actuation voltage of 130 V. Individual addressing capability of each mirror has been demonstrated using a line-column algorithm based on an optimized voltage-tilt hysteresis. Devices are currently packaged, wire-bonded and integrated to a dedicated electronics to demonstrate the individual actuation of all micromirrors on an array. An operational test of this large array with gold coated mirrors has been done at cryogenic temperature (162 K): the micromirrors were actuated successfully before, during and after the cryogenic experiment. The micromirror surface deformation was measured at cryo and is below 30 nm peak-to-valley.

The James Webb Space Telescope (JWST) relies on several innovations to complete its five year mission. One vital technology is microshutters, the programmable field selectors that enable the Near Infrared Spectrometer (NIRSpec) to perform multi-object spectroscopy. Mission success depends on acquiring spectra from large numbers of galaxies by positioning shutter slits over faint targets. Precise selection of faint targets requires field selectors that are both high in contrast and stable in position. We have developed test facilities to evaluate microshutter contrast and alignment stability at their 35K operating temperature. These facilities used a novel application of image registration algorithms to obtain non-contact, sub-micron measurements in cryogenic conditions. The cryogenic motion of the shutters was successfully characterized. Optical results also demonstrated that shutter contrast far exceeds the NIRSpec requirements. Our test program has concluded with the delivery of a flight-qualified field selection subsystem to the NIRSpec bench.

Laser frequency combs (LFC) provide a direct link between the radio frequency (RF) and the optical frequency regime. The comb-like spectrum of an LFC is formed by exact equidistant laser modes, whose absolute optical frequencies are controlled by RF-references such as atomic clocks or GPS receivers. While nowadays LFCs are routinely used in metrological and spectroscopic fields, their application in astronomy was delayed until recently when systems became available with a mode spacing and wavelength coverage suitable for calibration of astronomical spectrographs. We developed a LFC based calibration system for the high-resolution echelle spectrograph at the German Vacuum Tower Telescope (VTT), located at the Teide observatory, Tenerife, Canary Islands. To characterize the calibration performance of the instrument, we use an all-fiber setup where sunlight and calibration light are fed to the spectrograph by the same single-mode fiber, eliminating systematic effects related to variable grating illumination.

We here discuss recent progress on astronomical optical frequency comb generation at innoFSPEC-Potsdam. Two different platforms (and approaches) are numerically and experimentally investigated targeting medium and low resolution spectrographs at astronomical facilities in which innoFSPEC is currently involved. In the first approach, a frequency comb is generated by propagating two lasers through three nonlinear stages – the first two stages serve for the generation of low-noise ultra-short pulses, while the final stage is a low-dispersion highly-nonlinear fibre where the pulses undergo strong spectral broadening. In our approach, the wavelength of one of the lasers can be tuned allowing the comb line spacing being continuously varied during the calibration procedure – this tuning capability is expected to improve the calibration accuracy since the CCD detector response can be fully scanned. The input power, the dispersion, the nonlinear coefficient, and fibre lengths in the nonlinear stages are defined and optimized by solving the Generalized Nonlinear Schrodinger Equation. Experimentally, we generate the 250GHz line-spacing frequency comb using two narrow linewidth lasers that are adiabatically compressed in a standard fibre first and then in a double-clad Er/Yb doped fibre. The spectral broadening finally takes place in a highly nonlinear fibre resulting in an astro-comb with 250 calibration lines (covering a bandwidth of 500 nm) with good spectral equalization. In the second approach, we aim to generate optical frequency combs in dispersion-optimized silicon nitride ring resonators. A technique for lowering and flattening the chromatic dispersion in silicon nitride waveguides with silica cladding is proposed and demonstrated. By minimizing the waveguide dispersion in the resonator two goals are targeted: enhancing the phase matching for non-linear interactions and producing equally spaced resonances. For this purpose, instead of one cladding layer our design incorporates two layers with appropriate thicknesses. We demonstrate a nearly zero dispersion (with +/- 4 ps/nm-km variation) over the spectral region from 1.4 to 2.3 microns. The techniques reported here should open new avenues for the generation of compact astronomical frequency comb sources on a chip or in nonlinear fibres.

Radial velocity (RV) surveys supported by high precision wavelength references (notably ThAr lamps and I2 cells) have successfully identified hundreds of exoplanets; however, as the search for exoplanets moves to cooler, lower mass stars, the optimum wave band for observation for these objects moves into the near infrared (NIR) and new wavelength standards are required. To address this need we are following up our successful deployment of an H band(1.45-1.7μm) laser frequency comb based wavelength reference with a comb working in the Y and J bands (0.98-1.3μm). This comb will be optimized for use with a 50,000 resolution NIR spectrograph such as the Penn State Habitable Zone Planet Finder. We present design and performance details of the current Y+J band comb.

Ring resonators are a looped waveguide coupled to an input and an output waveguide. They can be used to filter, and drop, a series of wavelengths at the resonant frequencies of the ring. Both these properties are useful for astronomical applications. The dropped signal provides a frequency comb that can be used to provide accurate wavelength calibration. The free spectral range of such a device is larger than that from a laser comb, removing the requirement to perform subsequent filtering. The filtered signal could be used to suppress specific wavelengths, e.g. corresponding to atmospheric emission lines. We present the expected performance of devices designed for both applications and discuss their advantages and limitations.

We present a proof of concept compact diffraction limited high-resolution fiber-fed spectrograph by using a 2D multicore array input. This high resolution spectrograph is fed by a 2D pseudo-slit, the Photonic TIGER, a hexagonal array of near-diffraction limited single-mode cores. We study the feasibility of this new platform related to the core array separation and rotation with respect to the dispersion axis. A 7 core compact Photonic TIGER fiber-fed spectrograph with a resolving power of around R~31000 and 8 nm bandwidth in the IR centered on 1550 nm is demonstrated. We also describe possible architectures based on this concept for building small scale compact diffraction limited Integral Field Spectrographs (IFS).

We are developing an integral field unit (IFU) with an image slicer for the existing optical imaging spectrograph, Faint Object Camera And Spectrograph (FOCAS), on the Subaru Telescope. Basic optical design has already finished. The slice width is 0.4 arcsec, slice number is 24, and field of view is 13.5x 9.6 arcsec. Sky spectra separated by about 3 arcmin from an object field can be simultaneously obtained, which allows us precise background subtraction. The IFU will be installed as a mask plate and set by the mask exchanger mechanism of FOCAS. Slice mirrors, pupil mirrors and slit mirrors are all made of glass, and their mirror surfaces are fabricated by polishing. Multilayer dielectric reflective coating with high reflectivity (< 98%) is made on each mirror surface. Slicer IFU consists of many mirrors which need to be arraigned with high accuracy. For such alignment, we will make alignment jigs and mirror holders made with high accuracy. Some pupil mirrors need off-axis ellipsoidal surfaces to reduce aberration. We are conducting some prototyping works including slice mirrors, an off-axis ellipsoidal surface, alignment jigs and a mirror support. In this paper, we will introduce our project and show those prototyping works.

The Centre for Advanced Instrumentation (CfAI) of Durham University (UK) has recently successfully completed the development of 24 Integral Field Units (IFUs) for the K-band Multi-Object Spectrometer (KMOS). KMOS is a second generation instrument for ESO’s Very Large Telescope (VLT) which is due for delivery during the summer of 2012. The KMOS IFU is based on the Advanced Image Slicer Concept developed by the CfAI and previously successfully implemented on the Gemini Near-InfraRed Spectrograph and JWST NIRSpec. Each IFU contains 14 channels which have to be accurately aligned. In addition, all 24 IFUs have to be co-aligned requiring the accurate alignment of an unprecedented grand total of 1152 optical surfaces. In this paper we describe how this has been achieved through the use of complex monolithic multi-faceted metal mirror arrays, which were fabricated in-house by means of freeform diamond machining. We will summarise the results from the metrology performed on each of the optical components and describe how these were integrated and aligned into the system. We will also summarise the results from the system level acceptance tests, which demonstrate the excellent performance of the IFUs. Each of the 24 IFUs is essentially diffraction limited across the entire field (Strehl ratios ~ 0.8) with throughput predictions (based on measurements of the surface roughness) rising from 86% at a wavelength of 1 micron to 93% at 2.5 micron. We believe that this level of performance has not previously been achieved in any image slicing IFU and showcases the potential of the current state-of-the-art technology.

HARMONI, the High Angular Resolution Monolithic Optical & Near-infrared Integral field spectrograph is one of two first-light instruments for the European Extremely Large Telescope. Over a 256x128 pixel field-of-view HARMONI will simultaneously measure approximately 32,000 spectra. Each spectrum is about 4000 spectral pixels long, and covers a selectable part of the 0.47-2.45 μm wavelength range at resolving powers of either R≈4000, 10000, or 20000. All 32,000 spectra are imaged onto eight HAWAII4RG detectors using a multiplexing scheme that divides the input field into four sub-fields, each imaged onto one image slicer that in turn re-arranges a single sub-field into two long exit slits feeding one spectrograph each. In total we require eight spectrographs, each with one HAWAII4RG detector. A system of articulated and exchangeable fold-mirrors and VPH gratings allows one to select different spectral resolving powers and wavelength ranges of interest while keeping a fixed geometry between the spectrograph collimator and camera avoiding the need for an articulated grating and camera. In this paper we describe both the field splitting and image slicing optics as well as the optics that will be used to select both spectral resolving power and wavelength range.

We developed the technology of microslice integral field units some years ago as the next step in SAURON type microlens IFU design with typically 5 times more spatial elements (spaxels) for the same spectrograph and spectral length aiming at 1,000,000 spaxels IFUs. A full instrument for laboratory demonstration composed of the fore-optics, the IFU, the spectrograph and the detector has now been built and tested. It has about 10,000 spatial elements and spectra 150 pixel long. Our IFU has 5 cylindrical microlens arrays along the optical axis as opposed to one hexagonal array in the previous design. Instead of imaging pupils on the spectrograph input focal plane, our IFU images short slitlets 17 pixel long that keep the spatial information along the spatial direction then giving 17 spaxels per slitlet instead of one in pupil imaging. This removes most of the lost space between spectra leaving place for more and keeps the spatial information over the element size while pupil images lose it. The fore-optics re-images the field on the input of the IFU. They are made of cylindrical optics to get the desired different magnifications in both directions. All the optics and detector fit in a cylinder 35 mm in diameter and 280 mm long. With a different set of fore-optics on a 4-m telescope, a field of 43" x 6.7" with spatial elements of 0.14" x 0.22" could be observed so 12 of these mini-spectrographs would cover a field surface area of about 1 arcmin² and 120,000 spaxels.

Sodium laser guide stars (LGS) are used, or planned to be used, as single or multiple artificial beacons for Adaptive Optics in many present or future large and extremely large telescopes projects. In our opinion, several aspects of the LGS have not been studied systematically and thoroughly enough in the past to ensure optimal system designs. ESO has designed and built, with support from industry, an experimental transportable laser guide star unit, composed of a compact laser based on the ESO narrow-band Raman Fiber Amplifier patented technology, attached to a 30cm launch telescope. Besides field tests of the new laser technology, the purpose of the transportable unit is to conduct field experiments related to LGS and LGS-AO, useful for the optimization of future LGS-AO systems. Among the proposed ones are the validation of ESO LGS return flux simulations as a function of CW and pulsed laser properties, the feasibility of line-of-sight sodium profile measurements via partial CW laser modulation and tests of AO operation with elongated LGS in the EELT geometry configuration. After a description of the WLGSU and its main capabilities, results on the WLGSU commissioning and LGS return flux measurements are presented.

NIST-calibrated detectors will be used by the ground-based 100mm diameter Astronomical Extinction Spectrophotometer (AESoP) to calibrate the spectral energy distributions of bright stars to sub-1% per 1nm spectral resolution element accuracy. AESoP will produce about a hundred spectroradiometrically calibrated stars for use by ground- and space-based sensors. This will require accurate and near-continuous NIST calibration of AESoP, an equatorially mounted objective spectrophotometer operating over the wavelength range 350nm – 1050nm using a CCD detector. To provide continuous NIST calibration of AESoP in the field a near-identical, removable 100mm diameter transfer standard telescope (CAL) is mounted physically parallel to AESoP. The CAL transfer standard is calibrated by NIST end-to-end, wavelength-by-wavelength at ~ 1nm spectral resolution. In the field, CAL is used in a near-field configuration to calibrate AESoP. Between AESoP science observations, AESoP and CAL simultaneously observe clear sub-apertures of a 400mm diameter calibration collimator. Monochromatic light measured simultaneously by AESoP and CAL is dispersed by the objective grating onto the AESoP pixels measuring the same wavelength of starlight, thus calibrating both wavelength and instrumental throughput, and simultaneously onto a unique low-noise CAL detector providing the required throughput measurement. System sensitivity variations are measured by vertically translating the AESoP/CAL pair so that CAL can observe the AESoP sub-aperture. Details of this system fundamental to the calibration of the spectral energy distributions of stars are discussed and its operation is described. System performance will be demonstrated, and a plan of action to extend these techniques firstly into the near infrared, then to fainter stars will be described.

Astronomical instrumentation is most of the time faced with challenging requirements in terms of sensitivity, stability, complexity, etc., and therefore leads to high performance developments that at first sight appear to be suitable only for the specific design application at the telescope. However, their usefulness in other disciplines and for other applications is not excluded. The ERA2 facility is a lab demonstrator, based on a high-performance astronomical spectrograph, which is intended to explore the innovation potential of fiber-coupled multi-channel spectroscopy for spatially resolved spectroscopy in life science, material sciences, and other areas of research.

Currently, every single instrument using NIR detectors is cooled down to cryogenic temperatures to minimize the thermal flux emitted by a warm instrument. Cryogenization, meaning reaching very low operating temperatures, is a must when the K band is needed for the science case. This results in more complex and more expensive instruments. However, science cases that do not benefit from observing in the K band, like the detection of exoplanets around M dwarfs through the radial velocity technique, can make use of non-cryogenic instruments. The CARMENES instrument is implementing a cooling system which could allow such a solution. It is being built by a consortium of eleven Spanish and German institutions and will conduct an exoplanet survey around M dwarfs. Its concept includes two spectrographs, one equipped with a CCD for the range 550-950 nm, and one with HgCdTe detectors for the range from 950-1700 nm, covering therefore the YJH bands. In this contribution, different possibilities are studied to reach the final cooling solution to be used in CARMENES, all of them demonstrated to be feasible, within the requirements of the SNR requested by the science case.

Fibre Bragg grating (FBG) OH suppression is capable of greatly reducing the bright sky background seen by near infrared spectrographs. By filtering out the airglow emission lines at high resolution before the light enters the spectrograph this technique prevents scattering from the emission lines into interline regions, thereby reducing the background at all wavelengths. In order to take full advantage of this sky background reduction the spectrograph must have very low instrumental backgrounds so that it remains sky noise limited. Both simulations and real world experience with the prototype GNOSIS system show that existing spectrographs, designed for higher sky background levels, will be unable to fully exploit the sky background reduction. We therefore propose PRAXIS, a spectrograph optimised specifically for this purpose. The PRAXIS concept is a fibre fed, fully cryogenic, fixed format spectrograph for the J and H-bands. Dark current will be minimised by using the best of the latest generation of NIR detectors while thermal backgrounds will be reduced by the use of a cryogenic fibre slit. Optimised spectral formats and the use of high throughput volume phase holographic gratings will further enhance sensitivity. Our proposal is for a modular system, incorporating exchangeable fore-optics units, integral field units and OH suppression units, to allow PRAXIS to operate as a visitor instrument on any large telescope and enable new developments in FBG OH suppression to be incorporated as they become available. As a high performance fibre fed spectrograph PRAXIS could also serve as a testbed for other astrophotonic technologies.

The instrumentation of many space missions requires operation in cryogenic temperatures. In all the cases, the use of mechanisms in this environment is a matter of concern, especially when long lifetime is required. With the aim of removing lifetime concerns and to benefit from the cryogenic environment, a cryogenic contactless linear mechanism has been developed. It is based on the levitation of a permanent magnet over superconductor disks. The mechanism has been designed, built, and tested to assess the performances of such technology. The levitation system solves the mechanical contact problems due to cold-welding effects, material degradation by fatigue, wearing, backlash, lubrication...etc, at cryogenic temperatures. In fact, the lower is the temperature the better the superconductor levitation systems work. The mechanism provides a wide stroke (18mm) and high resolution motion (1μm), where position is controlled by changing the magnetic field of its environment using electric-magnets. During the motion, the moving part of the mechanism levitates supported by the magnetic interaction with the high temperature type II superconductors after reaching the superconductor state down to 90K. This paper describes the results of the complete levitation system development, including extensive cryogenic testing to measure optically the motion range, resolution, run-outs and rotations in order to characterize the levitation mechanism and to verify its performance in a cryogenic environment.

The high reliability of the mechanisms of any space instrument is one of the most critical and challenging requirements. This is even more pronounced in the case of cryogenic instruments, such as the Mid-Infrared Instrument (MIRI) to be flown on the James Webb Space Telescope (JWST) – which will be cooled down to below 7 K. MIRI hosts three wheel mechanisms for filter, grating and dichroic selection. All of them have an open loop torque drive and thus the precise characterisation of the mechanisms and their motors is fundamental to achieve minimum heat load and maximum reliability of the mechanism movements over the lifetime. In this paper we present the overview of the characterisation and verification of the MIRI wheel mechanisms. Our method is based on measuring back EMF voltages generated by the two phase cold redundant motors of the wheel mechanisms after they had been fully integrated into the MIRI optical module. We present the analysis of the data and the resulting performance increase. We discuss the optimisation of the open loop drive, as well as the verification of the measurement results and the physical model of the motors and mechanisms.

The Mid-infrared E-ELT Imager and Spectrograph, or METIS, is foreseen as the third instrument for the European Extremely Large Telescope (E-ELT). A key part of METIS is the Cold Chopper (MCC) which switches the optical beam between the target and a nearby reference sky during observation for elimination of the fluctuating IR background signal in post-processing. This paper discusses the development of the MCC demonstrator. The chopper mirror (Ø64mm) has to tip/tilt in 2D with a combined angle of up to 13.6mrad with 1.7μrad stability and repeatability within 5ms (95% duty cycle at 5Hz) at 80K. As these requirements cannot be met in the presence of friction or backlash, the mirror is guided by a monolithically integrated flexure mechanism. The angular position is actuated by three linear actuators and measured by three linear position sensors, resulting in a fast tip, tilt, and focus mirror. Using the third actuator to introduce symmetry, homogeneity in forces and heat flux is obtained. Both the actuators and the sensors are key components. A voice coil actuator had to be custom designed, to achieve the required acceleration force within the specified 1W heat load. The requirements for the displacement measurement can be met with a commercially available, fiber interferometry system. For integration of this system, stray light elimination is a critical design aspect and retro-reflectors have been used to reflect sufficient power into the fiber at large tip/tilt angles.

Polished 1.5m bare beryllium, off-axis aspheric mirror segments, constituting the cryogenic primary mirror of NASA's ambitious Flagship Mission, James Webb Space Telescope (JWST), have been successfully completed at L-3 Communications -Tinsley. Tinsley has finished the secondary, tertiary, fine steering and spare mirrors as well. We will describe both the end results, where it was demonstrated that visible quality mirror results can be achieved on large extremely lightweighted compliant off-axis mirrors, and the steps taken at Tinsley to achieve these results. Over 26 square-meters of bare beryllium were optically processed twice, first for room temperature figure, then for the cryo-null figure for the cryogenic differences.

ZERODUR^® is a well-established material in astronomy and all fields of applications where temperature gradients might limit extreme precision and stability. Together with its rich heritage come a series of recent developments, which reveal the potential of the material for broader and more demanding applications. The outstanding degree of light-weighting achieved with progress in CNC grinding in the last two years shows its high suitability for space telescope mirrors. This is supported by new data on strength enabling higher mechanical loads. Also ground based telescopes benefit from the improved light-weight processing such as solar telescopes and downstream mirrors of extremely large telescopes. More and better data have been collected demonstrating the unique CTE homogeneity of ZERODUR^® and its very high reproducibility a necessary precondition for large series mirror production. Deliveries of more than 250 ZERODUR mirrors of 1.5 m in diameter prove the availability of robust industrial serial production capability inevitable for ELT mirror segment production.

Sagem – Reosc has been awarded by ESO a contract for the manufacturing and testing of seven prototype segments of the E-ELT primary mirror in 2008. The purpose of this contract was to demonstrate the ability to produce aspherical off-axis hexagonal segments with very little edge effect and very high quality wavefront error and plan the production of the 931 segments needed for the primary mirror and spares. The manufacturing of the prototype segments is now completed. They have been delivered. Sagem has achieved for the best segment integrated on its support an overall surface error of 23 nm RMS and 6 nm RMS after removal of the allowed amount of Focus, Astigmatism and Trefoil. This article will present the process developped by Sagem and its performance. Sagem has also assessed the performances of an alternate manufacturing process based on the polishing of the segments under stress conditions (Stress Mirror Polishing). The results obtained by this process will also be presented.

Latest progress on Tinsley methods are described for faster stress mirror polishing (SMP) of the Thirty Meter Telescope (TMT) primary mirror segments as well as the European Extremely Large Telescope (EELT). Most recent data is shown which illustrates that the SMP process is capable of producing very smooth surfaces to 1um PV, independent of the segment type being produced.

Mankind loves space and is drawn to explore its vastness. Existing space telescopes routinely encounter data losses and delayed data collections during the constantly changing temperature and load disruptions of space missions. The harsh environment of space thermal cycles and spacecraft motion loads create unwanted activity such as spacecraft slew, acquisition slew, and temperature induced blur. In order to compensate for the low performance of the materials currently used for telescope optics, engineers and designers are using costly on-board coolers, mechanical actuators, and deformed mirrors, for example, with limited success. However, Zero-defect Single Crystal Silicon (SCSi) can perform in space environments without coolers, actuators, and other such devices because SCSi is not ductile and is homogeneous and therefore is not subject to creep, and will not jitter, or blur during operations. To take advantage of the unique advantages of Zero-defect SCSi, we are developing and fabricating a Cryostable All-Silicon Imaging Telescope (CAIT). In this paper, we will discuss the basis for selecting SCSi for our space telescope design, the status of the CAIT design and fabrication progress, and compare SCSi thermal and strength properties with other typical space optical materials.

Through the years many stable optical mounts have been designed, analyzed and tested at TNO. This paper gives an overview of the design principles used. Various examples are presented together with verification test results. The use of adhesives in combination with an iso-static mount design allows mounting of optical components in a limited volume with limited deformation of the optical surfaces due to thermal and mechanical loads. Relatively large differences in thermal expansion over large temperature ranges can be overcome using a simple and predictable design at reasonable costs. Despite adhesives have limited dimensional stability and loadability, stable optical mounts can be realized when proper design principles are used.

The Near Infrared Spectrometer and Photometer (NISP) of EUCLID requires high precision large lens holders (Ø170 mm) at cryogenic temperatures (150 K). The lenses of the optical system are glued into separate lens holders, the so called adaption rings. For the selection and verification of a suitable adhesive extensive glue selection tests are performed and results presented in this paper. With potential glue candidates, handling, single lap shear, connection tension and shear tests are carried out at room temperature (RT) and 150 K (OPS). For the NISP optical system DP490 is selected as the most suitable adhesive. The test results have shown that an even distribution of the glue in the glue gap is of crucial importance for the functioning and performance of the bonded lens system. The different coefficients of thermal expansion (CTE) between lens and lens holder produce large local mechanical stress and might cause lens breakage or failure of bonding. The design of the injection channel and the gluing procedure are developed to meet the lens performance requirements. An example is shown that after thermal cycling the remaining 0.5 mm – 1 mm thick adhesive in the injection channel results in large local mechanical stresses, and hence, damage of the lens. For a successful performance of the glue interface not only an optimum glue gap of 80 – 150 μm is important, also micro-cracks of the glass at the gluing area have to be avoided. The performed glue tests with DP490 for 3 different lens/ring material combinations show sufficient mechanical tension and shear strength for bonding of the lens system. Titanium/LF5G15 and Invar/Fused Silica combinations have reached the strength of 30 MPa at RT and 50 GPa at 150 K. These results are presented on behalf of the EUCLID consortium.

Throughout the history of telescopes and astronomical instrumentation, new ways were found to open up unexplored possibilities in fundamental astronomical research by increasing the telescope size and instrumentation complexity. The ever demanding requirements on instrument performance pushes instrument complexity to the edge. In order to take the next leap forward in instrument development the optical design freedom needs to be increased drastically. The use of more complex and more accurate optics allows for shorter optical trains with smaller sizes, smaller number of components and reduced fabrication and alignment verification time and costs. Current optics fabrication is limited in surface form complexity and/or accuracy. Traditional active and adaptive optics lack the needed intrinsic long term stability and simplicity in design, manufacturing, verification and control. This paper explains how and why active arrays literally provide a flexible but stable basis for the next generation optical instruments. Combing active arrays with optically high quality face sheets more complex and accurate optical surface forms can be provided including extreme a-spherical (freeform) surfaces and thus allow for optical train optimization and even instrument reconfiguration. A zero based design strategy is adopted for the development of the active arrays addressing fundamental issues in opto-mechanical engineering. The various choices are investigated by prototypes and Finite Element Analysis. Finally an engineering concept will be presented following a highly stable adjustment strategy allowing simple verification and control. The Optimization metrology is described in an additional paper for this conference by T. Agócs et al.

This paper addresses two challenges in establishing a new process chain for polishing hexagonal segments for extremely large telescopes:- i) control of edge and corner profiles in small-tool polishing of hexagons, and ii) achieving the required smoothness of the bulk aspheric form. We briefly describe the performance of a CNC-grinding process used to create the off-axis asphere, which established the input-quality for subsequent processing. We then summarize processes for smoothing ground mid-spatials and pre- and corrective polishing using Zeeko CNC machines. The impact of two cases is considered; i) all processing stages are performed after the segment is cut hexagonal, and ii) final rectification of a hexagon after cutting from an aspherised roundel, as an alternative to ionfiguring. We then report on experimental results on witness samples demonstrating edges and corners close to the EELT segment specification, and results on a full-aperture spherical segment showing excellent surface smoothness.

The Thirty Meter Telescope (TMT) is a next-generation optical/infrared telescope to be constructed on Mauna Kea, Hawaii toward the end of this decade, as an international project. Its 30 m primary mirror consists of 492 off-axis aspheric segmented mirrors. This paper describes the progress of the test fabrication of an outermost mirror segment for the TMT as a joint R&D program between National Astronomical Observatory and Canon. A zero-expansion glass CLEARCERAM™ blank was polished by a computer-controlled small-tool polishing machine (CSSP, Canon) and its surface shape was measured by a touch-probe measuring machine(A-Ruler, Canon). Residuals of lower Zernike terms of the surface shape were 11 nmRMS, clearing the original specifications based on the structure function. There remains, however, a need to fulfill latest revised specifications. Possible solutions to improve and achieve the new specifications and a plan for revising the process for mass production are also described.

Production of segments for the Giant Magellan Telescope is well underway at the Steward Observatory Mirror Lab. We report on the completion of the first 8.4 m off-axis segment, the casting of the second segment, and preparations for manufacture of the remaining segments. The complete set of infrastructure for serial production is in place, including the casting furnace, two 8.4 m capacity grinding and polishing machines, and a 28 m test tower that incorporates four independent measurement systems. The first segment, with 14 mm p-v aspheric departure, is by some measures the most challenging astronomical mirror ever made. Its manufacture took longer than expected, but the result is an excellent figure and demonstration of valuable new systems that will support both fabrication and measurement of the remaining segments. Polishing was done with a 1.2 m stressed lap for smoothing and large-scale figuring, and a series of smaller passive rigid-conformal laps for deterministic figuring on smaller scales. The interferometric measurement produces a null wavefront with a 3-element asymmetric null corrector including a 3.8 m spherical mirror and a computer-generated hologram. In addition to this test, we relied heavily on the new SCOTS slope test with its high accuracy and dynamic range. Evaluation of the measured figure includes simulated active correction using both the 160-actuator mirror support and the alignment degrees of freedom for the off-axis segment.

One of the most challenging tasks for future X-ray observatories is the enhancement of collecting area combined with very good angular resolution. Light-weight mirror materials, such as thin glass sheets, are needed to achieve this aims within the mass limits. We are developing a technology based on indirect hot slumping of thin glass segments. This technique enables us to produce the parabolic and hyperbolic part of the Wolter type I mirrors in one piece. Currently we focus on a combination of a ceramic slumping mould and glass type D263. The experimental set-up in our laboratories as well as the slumping process are described in detail; furthermore we report on the metrology methods used for measuring the glass sheets and moulds. Finally the results of the X-ray tests of several integrated glass sheets are presented.

Mid-infrared, 25 - 45 microns, is a very important wavelength region to investigate the physics of lower temperature environments in the universe. There are few transparent materials in the range of mid-infrared except silicon. However, the reflection on a silicon surface reaches 30 % because of its high refractive index (~3.4). To apply silicon to mid-infrared astronomical instruments, we need a way of antireflection and have adopted a moth-eye structure. This structure keeps durable under cryogenic environments, which is advantageous to mid-infrared instruments. We have fabricated three samples of the moth-eye structure on plane silicon surfaces by electron-beam photo-lithograph and reactive ion etching. The structures consist of many cones standing on silicon surfaces. We have substantiated the transmittance of 96 % or higher in the wide range of 20 - 50 microns and higher than 98 % at the maximum. The transmittance of moth-eye surfaces, however, is theoretically expected as 100 %. We have examined the discrepancy between the transmittance of the theory and fabrications with electromagnetic simulations. It has been revealed that shapes of the cones and gaps at the bottom of the cones seriously affect the transmittance. We have estimated a few tolerances for manufacturing the moth-eye structures achieving sufficient transmittance of nearly 100 %.

We report on the on-going effort at University of California Observatories Astronomical Coatings Lab to develop robust protected-silver coatings suitable for telescope mirrors. We have identified a very promising recipe based on YF₃ that produces excellent reflectivity at wavelengths of 340 nm and greater, has ~1.5% emissivity in the thermal IR, and does not contain problematic materials for the Mid-IR, such as SiO₂ and Al₂O₃. The recipe holds up extremely well to aggressive environmental testing (80C and 80% RH; high-H₂S atmosphere), and currently is being evaluated under real observatory conditions. This coating may satisfy the need for telescope mirror coatings that are long-lasting (~5 years or more) and have good reflectivity into the UV. We also evaluate and compare some other silver-based coatings developed elsewhere that should be useful in the same role. In addition, we describe recent upgrades to our coating facilities allowing us to deposit ion-assisted e-beam coatings on optics up to ~1m. This novel arrangement places the e-gun and ion source on a pivoting "swing-arm", allowing the position to move radially without changing the e-gun/ion source/ substrate geometry. Large substrates can be coated with good uniformity using single-axis rotation only. This technique is scalable to arbitrarily large substrate sizes.

Astronomical observations in the far--ultraviolet (FUV) spectral region are some of the more challenging due to the very distant and faint objects that are typically searched for in cosmic origin studies such as origin of large scale structure, the formation, evolution, and age of galaxies and the origin of stellar and planetary systems. The problem is compounded by the very limited option of reflecting coatings to use at FUV wavelengths and the modest reflectivity offered by those coatings such as Al+MgF₂ [typically 82 % at Lyman-alpha, 1216 Α) that are used on reflecting surfaces of FUV instrumentation. Improved reflective coatings for optics, particularly in the ultraviolet part of the spectrum, could yield dramatically more sensitive instruments and permit more instrument design freedom. This paper will present recent advances in reflectance performance for Al+MgF₂ mirrors optimized for Lymanalpha wavelength by comparing an ambient or ”cold” deposition with another where the deposition temperature for the MgF₂ layer is done at elevated temperatures. We will also consider this improved procedure for the deposition of LiF over-coated Al mirrors in order to realize similar reflectivity gains at even shorter wavelengths.

The optimization of the uniformity of high precision optical filters is often a critical and time consuming procedure. The goal of the present paper is to evaluate critical factors that influence the thickness distribution on substrates during a magnetron sputter process. A new developed sputter coater “EOSS” was used to deposit SiO₂ and Nb₂O₅ single films and optical filters. It is based on dynamic deposition using a rotating turntable. Two sets of cylindrical double magnetrons are used for the low and the high index layers, respectively. In contrast to common planar magnetrons, the use of cylindrical magnetrons should yield a more stable distribution during the lifetime of the target. The thickness distribution on the substrates was measured by optical methods. Homogenization is carried out by shaping apertures. The distribution of the particle flow from the cylindrical magnetron was simulated using particle-in-cell Monte Carlo plasma simulation developed at Fraunhofer IST. Thickness profiles of the low index and the high index layers are calculated by numerical simulation and will be compared with the experimental data. Experimental factors such as wobbling of the magnetron during rotation, geometrical changes of critical components of the coater such as uniformity shapers as well as gas flow variations will be evaluated and discussed.

Optical coatings are an integral part of superior optical components. Astronomical applications (ground- and space-based) place especially high demands on these coatings, not only with regard to their optical performance but also to their mechanical and environmental stability, their thermal properties, and their radiation resistance. This article presents a short overview of several coating solutions developed in recent years at Fraunhofer IOF in order to meet the challenging demands of astronomical applications. The focus is placed on high reflective coatings for different wavelength regions including coatings for the VUV range below 100nm, coatings for the DUV wavelength range above 100nm and VIS/NIR/IR coatings. Further, amorphous silicon layers will be introduced which can be polished to very low roughness values and therefore can act as polishing layer for the manufacture of ultraprecise optical components from metal substrates.

There is a description of Astrositall^® properties including CTE distribution and CTE homogeneity distribution, examples of this material usage in production of astronomical and space optics. There are also results of long term testing of Astrositall^® material.

For years now conventional aluminium 6061 T6 has widely been used for mirrors in astronomical instruments, being diamond turned or since a few years also being optically polished. This allows the development of optical systems that can be tested and operated at any temperature, without being affected by CTE effects. Using traditional aluminium the manufacturing methods could in some cases not deliver the required surface shape, accuracy and roughness due to the increasing demands from optical systems. Over the last few years RSP Technology developed a new series of aluminium alloys for several applications, produced with a Rapid Solidification Process. Both on a macroscopic and microscopic level these new aluminium alloys have different material characteristics compared to the traditional aluminium alloys. TNO and NOVA-ASTRON have performed diamond turning and polishing tests on these new aluminium alloys. This paper presents results of several diamond turning and polishing tests obtained over the last year and show the potential of these new alloys with surface roughness values of 1 nm on RSA 6061 and RSA 708 acquired with both diamond turning and polishing.

Placed on the Sun-Earth L2 Lagrange point, SPICA will operate in the 5 to 210 μm wavelength range. Astrium has been contracted by ESA/ JAXA to update the study of the SPICA telescope from a 3.5 m design (compatible to the Japanese HIIB launcher) to a 3.2 m design (compatible to the HII-A with the short 5S fairing): despite a similar fairing diameter, the shorter length of the fairing envelope results in a reduction of the M1-M2 distance and an associated diameter reduction of M1. Maximization of the M1-M2 distance within the constraints is important to maintain a reasonable polishing criteria of the main reflector. Therefore the M2 assembly sizing and the back focal length become main parameters for the telescope optical design. The main constraints are driven by the telescope requirements such as focal length, maximizing the diameter of M1 (3.2 m) and, M1 f-number (critical for the manufacturing aspects). The WFE must be below 350 nm rms, and operational temperature below 6K. . The main issues addressed in this paper are: - an improved telescope design based on the Astrium background in Silicon Carbide technology which has been tried-an-tested for mirrors and structural parts on several space projects, including HERSCHEL and Gaia (brazing, polishing, assembling, iso-static mountings). - performances which are taking advantage of the SiC properties ,such as homogeneity of the single-phase material inside the structure, and structural stability from ambient to the operational temperature range. Our study shows that the SiC telescope design can fulfil all the mechanical and optical requirements for SPICA. - the verification and optical tests definition which will be key elements in the qualification of the telescope to be incorporated in the logic of the satellite verification activity to be conducted in Japan.

Aspherical and freeform optical elements have a large potential in reducing optical aberrations and to reduce the number of elements in complex high performance optical systems. However, manufacturing a single piece or a small series of aspherical and freeform optics has for long been limited by the lack of flexible metrology tools. With the cooperative development of the NANOMEFOS metrology tool by TNO, TU/e and VSL, we are able to measure the form of aspheres and freeforms up to 500 mm in diameter with an accuracy better than 10 nm rms. This development opened the possibility to exploit a number of iterative, corrective manufacturing chains in which manufacturing technologies such as Single Point Diamond Turning, freeform grinding, deterministic polishing and classical polishing are combined in an iterative loop with metrology tools to measure form deviation (like CMM, LVDT contact measurement, interferometry and NANOMEFOS). This paper discusses the potentials, limitations and differences of iterative manufacturing chains used by TNO in the manufacturing of high performance optics for astronomical purposes such as the anufacturing of the L2 of the Optical Tube Assembly of the four laser-guide star facility of the ESO VLT, Manufacturing of Aluminium freeforms mirrors for the SCUBA-2 instrument. Based on these results we will give an outlook into the new challenges and solutions in manufacturing high-precision optics.

Ultra-lightweight and high-accuracy CFRP (carbon fiber reinforced plastics) mirrors for space telescopes were fabricated and their feasibility for low temperature applications was demonstrated. The CFRP mirrors were composed of sandwich panels with CFRP skins and CFRP honeycomb cores. Surface was deposited with epoxy thin layers by using a replica technique. The surface accuracy of the demonstrate mirrors of 150 mm in diameter was 0.8 μm RMS and the surface smoothness was improved to 5 nm RMS. Surface accuracy degradation was 0.6μm RMS (root mean square) from ambient temperature to liquid nitrogen. Surface asperity was classified with respect of their wave intervals and measurement areas. Surface accuracy and dimensional stability were strictly affected by raw materials and manufacturing conditions. Surface accuracy was measured at each process on the way of mirror forming. Manufacturing conditions to depress asperity were discussed.

Silicon immersion gratings offer size and cost savings for high-resolution near-infrared spectrographs. The IGRINS instrument at McDonald Observatory will employ a high-performance silicon immersion echelle grating to achieve spectral resolution R = λ/Δλ40,000 simultaneously over H and K near-infrared band atmospheric windows (1.5-2.5 μm). We chronicle the metrology of an R3 silicon immersion echelle grating for IGRINS. The grating is 30x80 mm, etched into a monolithic silicon prism. Optical interferometry of the grating surface in reflection indicates high phase coherence (<λ/6 peak to valley surface error over a 25 mm beam at λ= 632 nm). Optical interferometry shows small periodic position errors of the grating grooves. These periodic errors manifest as spectroscopic ghosts. High dynamic range monochromatic spectral purity measurements reveal ghost levels relative to the main diffraction peak at 1.6x10^-3 at λ = 632 nm in reflection, consistent with the interferometric results Improved grating surfaces demonstrate reflection-measured ghosts at negligible levels of 10^-4 of the main diffraction peak. Relative on-blaze efficiency is ~75%. We investigate the immersion grating blaze efficiency performance over the entire operational bandwidth 1500 <λ(nm) < 2500 at room temperature. The projected performance at operational cryogenic temperatures meets the design specifications.

We have developed the technology to manufacture an immersed grating in silicon for the Mid-infrared E-ELT Imager and Spectrograph, METIS. We show that we can meet the required diffraction-limited performance at a resolution of 100000 for the L and M spectral bands. Compared to a conventional grating, the immersed grating drastically reduces the beam diameter and thereby the size of the spectrometer optics. As diffraction takes place inside the high-index medium, the optical path difference and angular dispersion are boosted proportionally, thereby allowing a smaller grating area and a smaller spectrometer size. The METIS immersed grating is produced on a 150 mm industry standard for wafers and replaces a classical 400 mm echelle. Our approach provides both a feasible path for the production of a grating with high efficiency and low stray light and improves the feasibility of the surrounding spectrometer optics. In this contribution we describe and compare the classical-grating solution for the spectrometer with our novel immersed-grating based design. Furthermore, we discuss the production route for the immersed grating that is based on our long-standing experience for space-based immersed gratings. We use standard techniques from the semiconductor industry to define grating grooves with nanometer accuracy and sub-nanometer roughness. We then use optical manufacturing techniques to combine the wafer and a prism into the final immersed grating. Results of development of the critical technology steps will be discussed.

Silicon immersion gratings (SIGs) offer several advantages over the commercial echelle gratings for high resolution infrared (IR) spectroscopy: 3.4 times the gain in dispersion or ~10 times the reduction in the instrument volume, a multiplex gain for a large continuous wavelength coverage and low cost. We present results from lab characterization of a large format SIG of astronomical observation quality. This SIG, with a 54.74 degree blaze angle (R1.4), 16.1 l/mm groove density, and 50x86 mm² grating area, was developed for high resolution IR spectroscopy (R~70,000) in the near IR (1.1-2.5 μm). Its entrance surface was coated with a single layer of silicon nitride antireflection (AR) coating and its grating surface was coated with a thin layer of gold to increase its throughput at 1.1-2.5 m. The lab measurements have shown that the SIG delivered a spectral resolution of R=114,000 at 1.55 m with a lab testing spectrograph with a 20 mm diameter pupil. The measured peak grating efficiency is 72% at 1.55 m, which is consistent with the measurements in the optical wavelengths from the grating surface at the air side. This SIG is being implemented in a new generation cryogenic IR spectrograph, called the Florida IR Silicon immersion grating spectrometer (FIRST), to offer broad-band high resolution IR spectroscopy with R=72,000 at 1.4-1.8 um under a typical seeing condition in a single exposure with a 2kx2k H2RG IR array at the robotically controlled Tennessee State University 2-meter Automatic Spectroscopic Telescope (AST) at Fairborn Observatory in Arizona. FIRST is designed to provide high precision Doppler measurements (~4 m/s) for the identification and characterization of extrasolar planets, especially rocky planets in habitable zones, orbiting low mass M dwarf stars. It will also be used for other high resolution IR spectroscopic observations of such as young stars, brown dwarfs, magnetic fields, star formation and interstellar mediums. An optimally designed SIG of the similar size can be used in the Silicon Immersion Grating Spectrometer (SIGS) to fill the need for high resolution spectroscopy at mid IR to far IR (~25-300 μm) for the NASA SOFIA airborne mission in the future.

Canon is developing wide variety of gratings that can be effective solutions for high precision spectroscopy for the next-generation ground-based and space telescopes. In this paper, we focus on our development of infrared immersion grating, which is one of the most demanding devices among various gratings. We use CdZnTe for mid-infrared (MIR) application and KRS5 for near-infrared (NIR) to MIR application. In particular, CdZnTe immersion grating is the key-device for the MIR high-resolution spectrograph for the space infrared telescope SPICA. Using our diamond cutting (planing) technique, grooves are shaped on the hypotenuse area (30 mm x 10 mm) of a CdZnTe prism with the spacing accuracy of < 5 nm (rms) and the surface roughness of < 5 nm (rms). We also performed cutting of KRS5 disk and confirmed that excellent grooves can be shaped on this material.

Volume Phase Holographic Gratings are interesting dispersing elements for astronomical instrumentation. An important point, in the realization of the grating, is the choice of the holographic material. Dichromated Gelatines (DCGs) are the best candidate, but they show some drawback especially regarding their water sensitivity and the complex developing process required to enhance their performances. New holographic materials are becoming interesting, such as photopolymers and photochromic materials. An exhaustive review of these classes of materials will be reported and their performances compared to those of DCGs, focusing mainly to the astronomical instrumentation field.

Ultrafast laser inscription (ULI) is a rapidly maturing technique which uses focused ultrashort laser pulses to locally modify the refractive index of dielectric materials in three-dimensions (3D). Recently, ULI has been applied to the fabrication of astrophotonic devices such as integrated beam combiners, 3D integrated waveguide fan-outs and multimode-to-single mode convertors (photonic lanterns). Here, we outline our work on applying ULI to the fabrication of volume phase gratings (VPGs) in fused silica and gallium lanthanum sulphide (GLS) glasses. The VPGs we fabricated had a spatial frequency of 333 lines/mm. The optimum fused silica grating was found to exhibit a first order diffraction efficiency of 40 % at 633 nm, but exhibited approximately 40 % integrated scattered light. The optimum GLS grating was found to exhibit a first order diffraction efficiency of 71 % at 633 nm and less than 5 % integrated scattered light. Importantly for future astronomy applications, both gratings survived cooling to 20 K. This paper summarises the grating design and ULI manufacturing process, and provides details of the diffraction efficiency performance and blaze curves for the VPGs. In contrast to conventional fabrication technologies, ULI can be used to fabricate VPGs in almost any dielectric material, including mid-IR transmitting materials such as the GLS glass used here. Furthermore, ULI potentially provides the freedom to produce complex groove patterns or blazed gratings. For these reasons, we believe that ULI opens the way towards the development of novel VPGs for future astronomy related applications.

A volume phase holographic grating (VPHG) achieves very high diffraction efficiency up to 100% for S or P polarized light at the first diffraction order. However, diffraction efficiency of the VPHG for non-polarized light becomes low according as Bragg angle becomes large, and bandwidth of diffraction efficiency becomes narrow according as refractive index modulation of grating lattice becomes small. A volume binary grating with rectangular lattice, consists of high and low refractive index media with large or small duty ratio, is able to achieve very high efficiency nearly 100% and a wide band width for both S and P polarization light. We have successfully fabricated germanium immersion gratings of step groove shape with resolving power of 45,000 at 10 micron by using a nano-precision 3D grinding machine and ELID (ELectrolytic In-process Dressing) method. However, the method requires a large amount of machine times and efforts. We had proposed a novel immersion grating with slot shape lattice of total reflection mirrors, which achieves high performance and lower fabrication cost. We describe the photolithography and the latest plasma nano-technologies for fabrications of the novel diffraction gratings in our presentation. We also introduce birefringence volume gratings in this article.

Modern electron beam lithography is a suitable technology for the fabrication of high performance gratings for spectroscopic applications. Due to a significant improved accuracy of the lithographic exposure the resulting gratings do show a very high wave-front quality, low stray-light, and grating ghosts. The high resolution accessible with e-beam writing can be used for sub-period engineering of the grating pattern in order to optimize the efficiency performance of the devices. This is demonstrated by different examples of pure dielectric reflection and transmission gratings developed for space missions. One is the Sentinel-4 earth observation mission; the second is the astrometry satellite GAIA of the ESA.

Advances in astronomy are often enabled by adoption of new technology. In some instances this is where the technology has been invented specifically for astronomy, but more usually it is adopted from another scientific or industrial area of application. The adoption of new technology typically occurs via one of two processes. The more usual is incremental progress by a series of small improvements, but occasionally this process is disruptive, where a new technology completely replaces an older one. One of the activities of the OPTICON Key Technology Network over the past few years has been a technology forecasting exercise. Here we report on a recent event which focused on the more radical, potentially disruptive technologies for ground-based, optical and infrared astronomy.

The next generation of focal-plane astronomical instruments requires technological breakthroughs to reduce their system complexity while increasing their scientific performances. Applied to the optical systems, recent studies show that the use of freeform reflective optics allows competitive compact systems with less optical components. In this context, our challenge is to supply an active freeform mirror system, using a combination of different active optics techniques. The optical shape will be provided during the fabrication using the mechanical property of metals to plasticize and will be coupled with a specific actuator system to compensate for the residual form errors, during the instrument operation phase. We present in this article the development of an innovative manufacturing process based on cold hydro-forming method, with the aim to adapt it for VIS/NIR requirements in terms of optical surface quality. It can operate on thin and flat polished initial substrates. The realization of a first prototype for a 100 mm optical diameter mirror is in progress, to compare the mechanical behaviours obtained by tests and by Finite Element Analysis (FEA), for different materials. Then, the formed samples will be characterized optically. The opto-mechanical results will allow a fine tuning of FEA parameters to optimize the residual form errors obtained through this process. It concerns the microstructure considerations, the springback effects and the work hardening evolutions of the samples, depending on the initial substrate properties and the boundary conditions applied. Modeling and tests have started with axi-symmetric spherical and aspherical shapes and will continue with highly aspherics and freeforms.

The next generation of ground-based astronomical observatories will require fabrication and maintenance of extremely large segmented mirrors tens of meters in diameter. At present, the large production of segments required by projects like E-ELT and TMT poses time frames and costs feasibility questions. This is principally due to a bottleneck stage in the optical fabrication chain: the final figuring step. State-of-the-art figure correction techniques, so far, have failed to meet the needs of the astronomical community for mass production of large, ultra-precise optical surfaces. In this context, Reactive Atom Plasma (RAP) is proposed as a candidate figuring process that combines nanometer level accuracy with high material removal rates. RAP is a form of plasma enhanced chemical etching at atmospheric pressure based on Inductively Coupled Plasma technology. The rapid figuring capability of the RAP process has already been proven on medium sized optical surfaces made of silicon based materials. In this paper, the figure correction of a 3 meters radius of curvature, 400 mm diameter spherical ULE^® mirror is presented. This work demonstrates the large scale figuring capability of the Reactive Atom Plasma process. The figuring is carried out by applying an in-house developed procedure that promotes rapid convergence. A 2.3 μm p-v initial figure error is removed within three iterations, for a total processing time of 2.5 hours. The same surface is then re-polished and the residual error corrected again down to λ/20 nm rms. These results highlight the possibility of figuring a metre-class mirror in about ten hours.

Recent advances in detection and characterization of exo-planets have led to increasing standards for repeatability of spectral-line detection of novel high-resolution spectrographs. This is important for exo-planet research but also has its impact on astroseismology and the study of variable stars. For these purposes optical fibres bear a huge advantage due to their improved scrambling ability - but this is subject to fundamental limits. This investigation gives experimental support for the theoretical proposals made in a companion paper which uses a ray-tracing approach. We will concentrate on the mechanisms that cause incomplete scrambling in order to gain insight in the true nature of scrambling, unlike previous mainly phenomenological studies. We describe the experimental setup that will be used to determine the fibre response to input beam parameters like focal ratio, tilt and offset. Preliminary experimental results are consistent with the theoretical predictions made and thus motivating a further exploration of these phenomena.

We describe the fiber optics systems for use in BigBOSS, a proposed massively parallel multi-object spectrograph for the Kitt Peak Mayall 4-m telescope that will measure baryon acoustic oscillations to explore dark energy. BigBOSS will include 5,000 optical fibers each precisely actuator-positioned to collect an astronomical target’s flux at the telescope prime-focus. The fibers are to be routed 40m through the telescope facility to feed ten visible-band imaging spectrographs. We report on our fiber component development and performance measurement program. Results include the numerical modeling of focal ratio degradation (FRD), observations of actual fibers’ collimated and converging beam FRD, and observations of FRD from different types of fiber terminations, mechanical connectors, and fusion-splice connections.