SPEXone is a compact multi-angle spectropolarimeter that measures both spectral intensity and the state of linear polarization of light scattered by aerosols in the Earth’s atmosphere at five different viewing angles simultaneously. This enables a very accurate quantification and characterization of atmospheric aerosols, helping us to better understand their effects on global climate and air quality. Building upon the success of its predecessor SPEXone, which has been launched in 2024 as part of the NASA PACE observatory, a second and improved instrument, SPEXone Second Generation, has been built within the ESA PRODEX program. Most recently, the integrated instrument underwent full on-ground characterization and calibration in ambient conditions at SRON. This contribution gives an overview of the measurements and presents preliminary results from the characterization and calibration campaign, focusing on the instrument performance. A few key performance aspects such as straylight, spatial and spectral resolution are discussed, with data from SPEXone for PACE serving as a comparison. The result of the analysis shows excellent image quality and indicates an improvement in the amount of diffuse straylight.
The Copernicus missions Sentinel-4 (S4) and Sentinel-5 (S5) will carry out atmospheric composition observations on an operational long-term basis to serve the needs of the Copernicus Atmosphere Monitoring Service (CAMS) and the Copernicus Climate Change Service (C3S). Building on the heritage from instruments such as GOME, SCIAMACHY, GOME-2, OMI and S5P, S4 is an imaging spectrometer instruments covering wide spectral bands in the ultraviolet and visible wavelength range (305-500nm) and near infrared wavelength range (750-775 nm). S4 will observe key air quality parameters with a pronounced temporal variability by measuring NO2, O3, SO2, HCHO, CHOCHO, and aerosols over Europe with an hourly revisit time. A series of two S4 instruments will be embarked on the geostationary Meteosat Third Generation-Sounder (MTG-S) satellites. S4 establishes the European component of a constellation of geostationary instruments with a strong air quality focus, together with the NASA mission TEMPO (to be launched end 2022) [9] and the Korean mission GEMS (launched 19 February 2020) [8]. This paper addresses the result of the final and crucial phase for the end to end performance of the PFM instrument: the extensive on-ground Characterization and Calibration of the instrument that is happening during the summer/fall 2022. The paper presents an overview of the calibration campaign objectives, the main performance verification and calibration measurements and preliminary performances of the PFM as-built instrument.
We present the concept and detailed design of a Smart Slit Assembly for next generation spectrometers, and we experimentally demonstrate operation of an individual 221 μm × 111 μm smart slit channel employing a MEMS actuated shutter to continuously modulate the intensity of the optical input signal. The MEMS actuated shutter is fabricated in a 211 μm thick device layer of a Silicon-On-Insulator wafer by Deep Reactive Ion Etching. Electrostatic comb drive actuators allow an absolute displacement of 52 μm at 74 V, resulting in a continuously tunable shutter efficiency of up to 99.97% at an operating wavelength of 532 nm.
Sentinel-4 is an imaging UVN (UV-VIS-NIR) spectrometer, developed by Airbus Defence and Space as prime contractor under ESA contract in the frame of the joint EU/ESA COPERNICUS program. The mission objective is the operational monitoring of trace gas concentrations for atmospheric chemistry and climate applications. This paper gives an overview of the Sentinel-4 system architecture, its design & development status.
A spectrometer for combined Raman and Laser Induced Breakdown Spectroscopy (LIBS) is amongst the different instruments that have been pre-selected for the Pasteur payload of the ExoMars rover. It is regarded as a fundamental, next-generation instrument for organic, mineralogical and elemental characterisation of Martian soil, rock samples and organic molecules. Raman spectroscopy and LIBS will be integrated into a single instrument sharing many hardware commonalities [1]. The combined Raman / LIBS instrument has been recommended as the highest priority mineralogy instrument to be included in the rover’s analytical laboratory for the following tasks: Analyse surface and sub-surface soil and rocks on Mars, identify organics in the search for life and determine soil origin & toxicity.
The synergy of the system is evident: the Raman spectrometer is dedicated to molecular analysis of organics and minerals; the LIBS provides information on the sample’s elemental composition. An international team, under ESA contract and with the leadership of TNO Science and Industry, has built and tested an Elegant Bread Board (EBB) of the combined Raman / LIBS instrument. The EBB comprises a specifically designed, extremely compact, spectrometer with high resolution over a large wavelength range, suitable for both Raman spectroscopy and LIBS measurements. The EBB also includes lasers, illumination and imaging optics as well as fibre optics for light transfer.
A summary of the functional and environmental requirements together with a description of the optical design and its expected performance are described in [2]. The EBB was developed and constructed to verify the instruments’ end-to-end functional performance with natural samples. The combined Raman / LIBS EBB realisation and test results of natural samples will be presented.
For the Flight Model (FM) instrument, currently in the design phase, the Netherlands will be responsible for the design, development and verification of the spectrometer unit, while the UK provides the detector. The differences between the EBB and the FM will be demonstrated.
Fibre Bragg Grating (FBG) sensor systems based on optical fibres are gaining interest in space applications. Studies on Structural Health Monitoring (SHM) of the reusable launchers using FBG sensors have been carried out in the Future European Space Transportation Investigations Programme (FESTIP). Increasing investment in the development on FBG sensor applications is foreseen for the Future Launchers Preparatory Programme (FLPP). TNO has performed different SHM measurements with FBGs including on the VEGA interstage [1, 2] in 2006.
Within the current project, a multi-parameter FBG sensor array demonstrator system for temperature and strain measurements is designed, fabricated and tested under ambient as well as Thermal Vacuum (TV) conditions in a TV chamber of the European Space Agency (ESA), ESTEC site. The aim is the development of a multi-parameters measuring system based on FBG technology for space applications. During the TV tests of a Space Craft (S/C) or its subsystems, thermal measurements, as well as strain measurements are needed by the engineers in order to verify their prediction and to validate their models. Because of the dimensions of the test specimen and the accuracy requested to the measurement, a large number of observation/measuring points are needed. Conventional sensor systems require a complex routing of the cables connecting the sensors to their acquisition unit. This will add extra weight to the construction under test. FBG sensors are potentially light-weight and can easily be multiplexed in an array configuration.
The different tasks comply of a demonstrator system design; its component selection, procurement, manufacturing and finally its assembly. The temperature FBG sensor is calibrated in a dedicated laboratory setup down to liquid nitrogen (LN2) temperature at TNO. A temperature-wavelength calibration curve is generated. After a test programme definition a setup in thermal vacuum is realised at ESA premises including a mechanical strain transducer to generate strain via a dedicated feed through in the chamber. Thermocouples are used to log the temperature for comparison to the temperature FBG sensor. Extreme temperature ranges from -150°C and +70°C at a pressure down to 10-4 Pa (10-6 mbar) are covered as well as testing under ambient conditions. In total five thermal cycles during a week test are performed. The FBG temperature sensor test results performed in the ESA/ESTEC TV chamber reveal high reproducibility (within 1 °C) within the test temperature range without any evidence of hysteresis. Differences are detected to the previous calibration curve. Investigation is performed to find the cause of the discrepancy. Differences between the test set-ups are identified. Equipment of the TNO test is checked and excluded to be the cause. Additional experiments are performed.
The discrepancy is most likely caused by a ’thermal shock’ due to rapid cooling down to LN2 temperature, which results in a wavelength shift. Test data of the FBG strain sensor is analysed. The read-out of the FBG strain sensor varies with the temperature during the test. This can be caused by temperature induced changes in the mechanical setup (fastening of the mechanical parts) or impact of temperature to the mechanical strain transfer to the FBG. Improvements are identified and recommendations given for future activities.
Amongst the different instruments that have been preselected to be on-board the Pasteur payload on ExoMars is the Raman/ Laser Induced Breakdown Spectroscopy (LIBS) instrument. Raman spectroscopy and LIBS will be integrated into a single instrument sharing many hardware commonalities.
An international team under the lead of TNO has been gathered to produce a design concept for a combined Raman Spectrometer/ LIBS Elegant Bread-Board (EBB). The instrument is based on a specifically designed extremely compact spectrometer with high resolution over a large wavelength range, suitable for both Raman spectroscopy and LIBS measurements. Low mass, size and resources are the main drivers of the instrument’s design concept. The proposed design concept, realization and testing programme for the combined Raman/ LIBS EBB is presented as well as background information on Raman and LIBS.
Europe is developing a new generation launcher, called Vega, a small launcher with a capacity to place satellites into polar and low-Earth orbits, which are used for many scientific and Earth observation missions. Its first launch is scheduled for early 2008. Dutch Space is responsible for the development, qualification and manufacturing of the Vega Interstage 1/2. This all-aluminium conically shaped section is designed as a monocoque structure. This subsystem of Vega has undergone its first qualification tests of force loading combined with an extensive programme of measurements (forces, displacements and strains), at TNO in Delft. In parallel to conventional strain gauges Fibre Optic Sensors (FOS) in the form of Fibre Bragg Grating (FBG) sensor arrays, consisting of five strain sensors and one temperature sensor, have been installed on different locations of the interstage. Direct comparisons of the results with conventional sensors during load tests up to several hundred tons are therefore possible. A self-evident benefit of FBG sensors in an array application is that each sensing FBG can have a different Bragg wavelength to reflect. Thus, Wavelength Division Multiplexing (WDM) can conveniently be used to distinguish the different sensing FBG’s at the receiving side. First test results from load measurements performed on the Qualification Model (QM) of the Vega Interstage 1/2 are presented in this paper as well as an outlook to future integration of the FBG in this field.
Moon4You is a project led by the Dutch Organisation for Applied Scientific Research TNO, with partners from industry
and universities in the Netherlands that aims to provide a combined Raman / LIBS instrument as scientific payload for
lunar exploration missions. It is the first time that Raman spectroscopy and LIBS (Laser Induced Breakdown
Spectroscopy) are combined into one miniaturised instrument with minimum mass, volume and use of resources and can
deliver data-products almost instantly. These characteristics make it the next-generation instrument for mineralogical and
elemental (atomic) characterisation of lunar soil and rock samples, as well as for a host of other planetary exploration
and terrestrial applications.
Among the different instruments that have been selected for the Pasteur payload on ExoMars is the Raman–laser-induced-breakdown-spectroscopy (LIBS) instrument. The novel, and technologically challenging, feature of this instrument is the integration of both Raman spectroscopy and LIBS techniques in the same hardware. An international team under the lead of TNO has been gathered together to produce a combined Raman-spectrometer–LIBS elegant breadboard. The instrument has been designed around an extremely compact spectrometer with a high resolution over a large wavelength range, which is suitable for both Raman spectroscopy and LIBS measurements. Low mass, size, and power consumption are the main drivers of the instrument design concept. A summary of the functional and environmental requirements together with a description of the optical design and its performance are included.
Darwin is a space based interferometry mission1 of the European Space Agency (ESA) with the aim to detect and characterise earth-like planets outside our solar system. The current Darwin baseline consists of four spacecrafts (3 telescopes). Destructive interference of the starlight is required to allow detection of much fainter planet signals. The nulling ratio required is 105.
For Darwin high requirements are set upon the wavefront quality of the beams. In order to be able to have destructive interference with a contrast factor of 105, a wavefront quality of λ/1400 (λ=6 micrometer) is needed. With current and/or foreseen technology, it is not possible to produce the optical elements with sufficient quality to meet this requirement. This means it is vital to develop wavefront filter devices for Darwin.
Most promising for this purpose are single mode fibres. For visible and near-infrared light commercially available single mode fibres are available, however they do not extend yet to wavelengths above 4 micrometer. To overcome this shortcoming new single mode fibres are developed (i.e. by Astrium and TNO/ University of Rennes) for the Darwin wavelength range (6-20 μm). To characterize and test these fibres a system is designed allowing to determine the possible star light suppression with the fibre. This system is called "Darwin Infrared Nulling Interferometer Demonstrator" (DINID).
The system is designed using the in-house knowledge from previous nulling set-ups in the visible and near-infrared wavelength range. It will permit to test fibres around 4 and 9 micrometer and includes an optical path difference control in order to compensate drifts.
This paper describes the basis on which the set-up is designed.
Spectral oscillation features originating from the on-board diffuser in the spectra of the SCIAMACHY instrument on ENVISAT have been observed in instrument data. These spectral diffuser surface interference features are observed in the daily sun-over-diffuser calibration measurements (solar irradiance). The effect may hamper the analysis of atmospheric trace gases. Diffuser spectral features were already known from the on-ground calibration phase, which led to the implementation of a second diffuser in SCIAMACHY to reduce the features magnitude. Spectral features like these have already been observed at TNO TPD during the on-ground calibration for instruments that utilise on-board diffusers (i.e. GOME-2, OMI). Analysis of the characteristics of the features indicates different types, where at least one type shows a pattern typical for speckles. In addition a separation method of the different features present in the spectrum will be described.
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