A.

Presentation of main Optical MEMS

Optical MEMS could be useful for designing future generation of instruments. In addition to their compactness, scalability, and specific task customization, they could generate new functions not available with current technologies. These devices have been developed or successfully used in a wide range of ground-based commercial applications, from telecom to life science, and from imaging to spectroscopy. MOEMS are not yet widely used for space application, but this technology will most likely provide the key to new science and instrumentation. The first major application will be the microshutters array in NIR-Spec for JWST. We have developed a table gathering parameters and information on relevant components for this study. Some of the commercial components are of prime interest for Earth Observation instruments.

Texas Instruments’ Digital Micromirror Devices (DMD), [1], are the most popular MOEMS devices available on the market. If the prime use is for displaying images numerous applications may be thought: multi-object selection, spectral selection, hyperspectral imaging, confocal microscopy … However, the flexibility in terms of applications is balanced by the rigidity in terms of customization: TI (or related companies) proposes only a limited number of components (array format and size of the mirrors) and sometimes, three possible coatings on the protecting window (UV, visible, IR). In terms of space compatibility, a full campaign has been already conducted through an ESA contract and do not reveal any show-stopper concerning the ability of the DMD to meet environmental space requirements (vacuum, -40°C, mirror in tilted position during 1500s), [2].

Boston Micromachines Corporation (BMC) [3] produces the most advanced MEMS deformable mirrors. Their main parameters are approaching the requirements values, i.e. large number of actuators (up to 4096), large stroke (up to 5.5 μm), good surface quality, but they still need large voltages for their actuation (150 – 250 V). Space qualification is an issue and to our knowledge, tests have been conducted for that purpose. This year, NASA has selected BMC for two Phase 1 contracts, in order to develop devices and electronics suited for space applications (main goal: wave-front control in space-based high contrast imaging instruments).

Programmable Micro Diffraction Gratings (PMDG) are possible candidates for tailoring spectrum of any beam or could be integrated in compact spectrographs. Polychromix has developed in 2005 a complete NIR spectrometer with the grating organized into 100 groups of 12-element pixels, [4]. This device has also been fully space-qualified and used for the NASA L-CROSS (Lunar Crater Observation and Sensing Satellite) mission to look for water on the Moon. Silicon Light Machines (SLM) is another device supplier with more pixels (1086 pixels made of 6 ribbons) and FPGA-based electronics for loading the patterns, [5]. It has been purchased and used in an ESA study addressing new applications of this type of MEMS. No space qualification could be foreseen in a near future for this device.

Scanning mirrors are developed in many companies and laboratories for a wide range of commercial applications. Their potential space applications are in LIDARs, switches, target selection, pointing. These components are usually qualified for applications on ground and only few components have been tested in space environment under ESA and CNES studies (for example SERCALO switches, [6]).

B.

Earth observation instruments considered for market-pull analysis

All current and future ESA Earth Observation missions were analyzed in order to find MEMS based concepts, which can enhance performances of these instruments.

EarthCARE, [7],is a joint European-Japanese mission addressing the need for a better understanding of the interactions between cloud, radiative and aerosol processes that play a role in climate regulation. To realize the measurement goals and meet the scientific objectives, a single platform with a payload of two active sounders: Lidar (ATLID) and radar (CPR); and two complementary passive instruments: multispectral imager (MSI) and a broadband radiometer (BBR) will be launched into a polar Sun-synchronous afternoon orbit.

Sentinel-2 [8] polar-orbiting satellites will provide systematic global acquisitions of high-resolution multispectral imagery with a high revisit frequency. This mission is tailored towards the needs of operational land monitoring and emergency services. The Sentinel-2 mission is envisaged to fly as a pair of satellites with the first planned to launch in 2013. Sentinel 2 spacecrafts are designed to carry a single multi spectral instrument.

Sentinel-3 [9] instruments are the SLSTR (Sea and Land Surface Temperature Radiometer), the Ocean and Land Colour Instrument (OLCI), the SAR Radar Altimeter (SRA) for Sea Surface Topography and Wave Height, the dual frequency Microwave Radiometer (MWR) to provide wet tropospheric corrections for radar altimeter, and a package for the precise determination of orbit that comprises a GNSS receiver, a laser tracking mirror and a DORIS receiver. The Mission is in phase C and the launch of the first Sentinel 3 satellite is foreseen to be in 2013. Sentinel-3 is a low Earth orbit (800–830km altitude) operational mission is part of the GMES Program.

The Meteosat Third-Generation (MTG) system [10] is being established through cooperation between EUMETSAT and the ESA. The MTG series will comprise six satellites, with the first spacecraft likely to be ready for launch from 2017. The in-orbit configuration will consist of two parallel positioned satellites, the MTG-I (imager) and the MTG-S (sounder) platforms. MTG-I satellites will fly the Flexible Combined Imager (FCI) and an imaging lightning detection instrument the Lightning Imager (LI). The MTG-S will include an interferometer the InfraRed Sounder (IRS) with hyper-spectral resolution in the thermal spectral domain, and the Sentinel-4 instrument, the high resolution Ultraviolet Visible Nearinfrared (UVN) spectrometer.

Activities are on going for the definition of the follow-on EUMETSAT Polar System (Post EPS, [11]), to replace the current satellite system in the 2020 timeframe and contribute to the Joint Polar System to be set up with NOAA. Through consultation with users and application experts, requirements have been defined for a range of candidate missions mainly in support of operational meteorology and climate monitoring. A number of on-board instruments, satellite platforms and ground support infrastructure are under study in coordination with ESA, NOAA, DLR and CNES. Feasibility studies are planned until 2011 with the main objective to define the baseline configuration for subsequent detailed design, development and operation programmes to be proposed and coordinated within the involved organizations.

Different High-resolution imagery programmes were analyzed, in Low Earth Orbit: Pléiades HR and in Geostationary Earth Orbit: Geo-Oculus and Optical Aperture Synthesis telescope.

C.

Estimation criteria of payloads improvements

A list of the criteria proposed to assess the improvement provided by MEMS technology to the Earth Observation missions is proposed. As the criteria are changing from instrument to instrument, a full ranking/selection of the solutions with such a number of criteria is something very heavy and subject to discussion. We propose to work with 3 meta-criteria with almost equal weights: Performance, System, and Programmatic.

TABLE I.

EVALUATION CRITERIA FOR PAYLOAD / INSTRUMENT IMPROVEMENT.

D.

Optical MEMS-based Earth observation instruments

A first selection of market-pull and techno-push concepts is done. In addition, some concepts are coming from outside Earth Observation. All these twelve concepts are relevant. Finally, after an objective trade-off based on criteria presented before, two concepts are selected for a preliminary study. Considering the meta-criteria cited above, a trade-off exercise is performed within the twelve concepts.

Two concepts are therefore selected and are addressed in the next section: Digital Mirror Array for cloud discarding; and Digital Micromirror Device for spectral selection with field-of-view.?

A.

Instrument level

This instrument is made of a ground imager and a spectrometer. The ground imager images the earth on the entrance slit of the spectrometer. This spectrometer disperses the light and forms a dispersed image of the entrance slit onto the focal plane array. The ground imager collects the light through the calibration mechanism Earth aperture and the scrambling window, and forms an image of the Earth in the plane of the spectrometer entrance slit. The focal length of the ground imager is 67,3 mm, so that it images a 272 m ground pixel onto a 22.5 micron spectrometer entrance slit width, from a nominal altitude of 815 km. Then the spectrometer disperses the light and forms a dispersed image of the slit on a CCD array. The resulting image of the slit is bi-dimensional: one dimension corresponds to the spatial extension of the slit, and the other one corresponds to the decomposition of light into all its spectral components from the visible to near infrared (390 - 1040 nm).

The goal of the sub-system presented in this paragraph is to cope with high flux coming clouds or sun glint. The TABLE II. summarizes the consequences of the observation of clouds and sun-glint. As far as the MEMS is able to filter light coming from clouds, we should couple it with a detection set-up and process. Three set-ups are proposed. Passenger small camera looking in advance, in the slit plane, we could place a detector or pick-up mirror + detector parallel to the spectrometer slit with spatial shift related to temporal advance (shift divided by EFL multiplied by H and divided by v) We can also use the light reflected by the MEMS is the OFF position and send it to an additional detector. As clouds are large and bright with a very high contrast with the intended signal, their detection could be based on a simple process based on analogue threshold could be performed onboard.

TABLE II.

SIGNAL POLLUTION BY EXTRAORDINARY STRAYLIGHT

According to, for one hand, the luminance of clouds and sun-glints, and for the other hand, the straylight level in the instrument; the sub-system proposed here is to replace the current slit by an active row of MEMS. Considering the ratio between the sun-glint flux and the reference flux, the sub-system does not seem to be able to afford such a difference. However as the detector is no longer saturated, recovering the full capacities of the instrument should be faster.

B.

Optical MEMS: MIRA

LAM and EPFL are engaged in a European development of micromirror arrays, called MIRA, for generating reflective slit masks in future Multi-Object Spectrographs, [12], [13]. This program includes devices realization and characterization setups developments [14], [15]. A first generation of up to 64×32 micro-mirrors fulfilled the requirements presented in the introduction paragraph and was fabricated.

The basic concept is shown in Figure 1. A single cell of the device consists of a silicon mirror suspended by poly-silicon beams. The beams are fixed on a frame, which maintains the mirrors together. The frame lies on a spacer that provides a precise distance between the mirror and the electrode. A system of landing beam and stopper beams on the mirror and on the frame was developed to assure a precise and constant tilt angle. When a DC voltage is applied on the electrode an electrostatic force appears between the electrode and the mirror and the micro-mirror begins to turn until the landing beam touches the landing pad. The mirror starts to turn in the opposite direction until it hits the stopper beams attached on the frame and remained electrostatically fixed in this position.

Figure 1.

Micro-mirror for multi-object spectroscopy: (Up) (a) Concept of the micro-mirror device. (b-d) A system of landing beam and stopper beams was introduced that provides uniform tilt-angle over the whole micro mirror array. (Down) Frontside of the mirror chip with micro-mirrors of size 100x200 μm². One row is actuated, implementing the long slit mode.

Replacing a slit by a MEMS involves contrast issues. Indeed the previous slit is made by chromium deposition and etching on a silica substrate. Contrast obtained is around one thousand near the slit (membrane porosity) and around one million a bit further. We should get a similar contrast between ON and OFF micro-mirrors states. Different factors are assessed during the MEMS device development such as rugosity (BRDF), diffraction by gaps, light reflected by substrate behind the micro-mirrors.

C.

Optical design

The optical design is based on conventional space spectro-imagers. The main modification is that the usual slit is in transmission. In the new design the optical MEMS is a micromirror, the spectrometer has been turned. All the previous elements are kept such as the scrambling window unit, the catadiotric objective, the concave grating and the focal plane as we can see in the Figure 4.

Figure 2.

Across-track transition scene

Figure 3.

Stray light ratio without the cloud removal

Figure 4.

Global overview of the MEMS-based instrument.

D.

Straylight analysis

The results of end-to-end straylight simulations have been post-processed. These simulations are performed with ASAP with all the different realistic coatings and flux. This straylight analysis is spit in four parts: Ground imager scattering, Ground imager ghost, Spectrometer scattering, and Spectrometer ghosts.

The scenes are contrasted scenes Lmax/Lref whom separation is across-track.

E.

Mechanical designs

As presented in the previous paragraph, the main modifications between a conventional spectro-imager and the new instruments are: a spectrometer reversal, the introduction of a MEMS and its board, and the use of additional slit. The optical design is superimposed to the CAD view in the Figure 6. The blue box is the MIRA board, which dimensions are 10 x 10.5 x 2.5 cm³. The area of mechanical conflict is shown. The MIRA board is above the focal plane array. Of course, the MIRA board can be redesigned but we must pay attention to this zone, which is quite dense.

Figure 5.

Stray light ratio in presence of the cloud removal

Figure 6.

Superimposition of the optical design and of the CAD view

F.

First experimental demonstration at LAM

Experimental demonstration of this concept has been conducted on a dedicated bench. A scene with a contiguous bright area (factor 10²) has been focused on a micro-mirror array and imaged on a CCD detector. The micro-mirror array is a DMD device from Texas Instrument made of 13.5μm mirrors. After the programmable slit, the straylight issued from the bright zone is set to the right level, i.e. equal to the scene signal level and pollutes the scene.

The resulting signal with the clouds and the polluted signal is recorded on a CCD camera. In order to restore the signal, the micro-mirrors located on the bright area are switched off, removing almost completely the straylight in the instrument.

In Figure 7. a), the profile of the FOV including the scene (left part) and the clouds area (right part) is shown: the green curve represents the FOV when the programmable slit is all ON, and the blue curve, the FOV when the micro-mirrors located in the bright area (clouds) are switched OFF.

Figure 7.

Cloud removal experiment; a) profile of the FOV including the scene (left part) and the clouds (right part) when the programmable slit is all ON (green curve) and when the micro-mirrors located on the bright area are switched OFF (blue curve); b) Close-up view of the transition area; the light blue curve represents the perfect scene, without clouds.

A close-up view (Figure 7. b) permits to see the benefit of removing optically the polluting source, where the straylight produced by the bright area is nearly completely removed; the light blue curve represents the perfect scene, without clouds.

This successful demonstration shows the high potential of this new concept in future spectro-imager for Earth Observation.

A.

Instrument design parameters

This instrument aims at Earth observation in different spectral channels. The satellite works in push-broom acquisition (linear field-of-view at 700 km altitude with a 7 km/s speed. This stating point is in close relation with the applications. The target should have a large field-of-view (swath higher than 10 km) with a medium spatial resolution, [17] Ground Sampling Distance (GSD) around 5 m. It should be noticed that the goal of this instrument is not to extract some lines in the spectrum but more using a linear combination of lines to discriminate some scientific signatures. In this way we don’t need a high SNR for one line.

Instead of a linear detector, we could envisage a matrix with 2000 columns for 5 to 20 lines. This detector should have two addressable modes. The first one is “Time Delay Integration”, as the scene moves on the detector because of the satellite speed; charges are transferred line after line in phase with the scene. The consequence is that the integration time can be increased by a factor 5 to 20 without changing the attitude of the spacecraft and loosing part of the Earth tracks.

By implementing optical MEMS it could be possible to perform the multi filtering function without any strip filters (cf. Figure 10.). In this solution, the focal plane is constituted for instance by 4 (or more) adjacent detector lines, and all these lines are taken simultaneously with the same waveband color selected by the optical MEMS device. Thanks to its very fast response, it is possible to change the waveband color just after the needed integration time. By this way, the 4 following lines will be taken in an other color with only one line of spatial (or temporal) separation. After a period of 4 integration times, the same on ground scene will be observed sequentially in the 4 color channels.

Figure 8.

Synthesis of mission user’s needs, [17]]

Figure 9.

Texas Instruments’ DMD: Principle and SEM photograph, courtesy Texas Instrument

Figure 10.

Possible solution using DMD. The filtering is obtained sequentially thanks to the very fast response of this MOEMS component. In this case, DMD could require improvements in term of dimension depending on the mission FOV

B.

Optical MEMS: DMD

The DMD concept is detailed in Figure 9. DMDs are component comprising hundreds of thousands micro-mirrors which are individually tiltable. Each micro-mirror measures a few microns. Thus, the incident beam can be redirected in many micro-beams oriented in two determined directions. Two electrodes control the position of each mirror via the electrostatic force. The reflected intensity in one direction can be modulated by periodically tilting the micro-mirrors during a fraction of the time.

In the first generation, the mirror width is 16μm, [1]. It can be tilted by 10° around its flexure arm in a binary way. A Scanning Electron Microscope (SEM) photograph (Figure 5-14) shows in false colors the different elements of an individual matrix mirror. The flexure arm width (in pink) is two microns and its thickness a few hundreds nanometers.

More recent DMD chips feature 2048 x 1080 mirrors, a 13.68μm pixel pitch, and a tilt angle of ±12°.

ESA has engaged with Visitech and LAM in a technical assessment of a DMD chip for space application, [2]. These results do not reveal any showstopper concerning the ability of the DMD to meet environmental space requirements. Insertion of such devices into final flight hardware would however still require additional efforts such as development of space compatible electronics, and original opto-mechanical design of the instrument.

C.

Optical design

As we perform a symmetric action on the light, part of the design could be used twice. For doing that, a grating is placed in the pupil in a collimating beam. DMD is placed at focus, the pupil image being at infinity (telecentric system). In this case, light is perfectly backtracking. However, entrance beam and exit beam cannot be separated, that’s the raison why two grating are used finally. The major problem is that the MEMS need to be tilted for 12° according to the (X+Y) diagonal direction.

Five meters is a quite small ground sampling distance (medium resolution). Diffraction and radiometry lead to the quite large entrance pupil diameter (>200mm). In consequence, a telescope is placed as fore optics. Considering the F/# and the field-of-view, a Ritchey-Chrétien design seems to be sufficient. But a TMA of a Korsch design could be envisaged in needed?

The Ritchey-Chrétien telescope is gathered with the spectrometer. Collimating lens after the slit and the focusing lens after the grating 2 are cemented achromatic doublets. This choice avoids multi-reflection and leaves some space to bend the instrument. Moreover, these lenses are more adapted to the aperture and field-of-view considered with respect to a single aspheric mirror.

D.

Mechanical designs

In Figure 12. a general view of the nominal instrument is shown. It is based on a flat angle bracket. One part is supporting the telescope; the other is supporting the instrument. The instrument is baffled with the yellow cover to prevent from straylight.

Figure 11.

Optical MEMS based spectrometer

Figure 12.

General view of this instrument

Figure 13.

Optical layout of the assembled instrument

As this instrument should work in NIR and SWIR (from 0.4 to 2.4 microns), the focal plane is put in a canister with coolers. Blue box represents the DMD board, which dimensions are 15x15x5 (thickness) cm³.