This paper presents a new concept of frequency comb LIDAR instrument for atmospheric CO2 mapping. The French space agency (CNES) has initiated the development of an airborne proof of concept. The main originality of this instrument lies in the use of two probe combs crossing the same atmospheric path and used for self-phase correction. This technique, named Double Heterodyne Detection (DHD), allows us to coherently average interferograms beyond the coherence time of the laser source. The LIDAR airborne instrument is designed for real-conditions atmospheric CO2 measurements at 1.572 μm and mainly relies on commercial telecom components. We present experimental results on a breadboard laboratory version of the instrument and our data processing method. Then, we extend the study to a space instrument and provide a first estimation of radiometric performances.
Able to monitor very precisely CO2 gases concentration in the atmosphere (better than 1 ppm), MicroCarb is a CNES mission which instrument is a passive Short Wave InfraRed spectrometer that will help scientists to better understand the planet’s major ecosystems and gain a clearer picture of its carbon budget at regional scales. Reaching such a monitoring precision means that the instrument has very stringent requirements especially in terms of radiometry, spectral filtering, spectral bands co-registration and polarization sensitivity. The MicroCarb instrument is currently under integration at Airbus Defence and Space facilities in Toulouse (France). It is based on an innovative concept permitting the acquisition of the spectral bands using a single split-pupil telescope, spectrometer and detector. Spectral bands multiplexing is obtained by the grating, each band corresponding to a different diffraction order, between 15 and 40. The split-pupil concept is characterized by 3 sets of 4 to 5 assembled prisms at entrance telescope pupil, spectrometer slit and in front of the detector, all participating to the complex spectral filtering. All the components considered as critical for the performances of the instrument have been manufactured and are under integration: the echelle grating replicated in a SiC substrate, the assembled optical elements with narrow spectral filtering coatings and the Dual Babinet polarization scrambler. In this paper we will focus on these optical components, detailing for each one how the stringent requirements of the instrument have been transposed to their specification, close to the limits of manufacturability. We will be able to present their development and achievement with respect to these specifications and how they impact the global performances of the instrument.
MicroCarb is a space program which uses a passive Short Wave InfraRed (SWIR) spectrometer instrument. MicroCarb will provide measurements of the atmospheric concentration of the carbon dioxide at global level with a precision sufficient in order to permit to the scientific community to improve the model of the carbon cycle by understanding the mechanisms governing the exchanges of CO2 between the sources and the sinks.
The MicroCarb Instrument is currently under development at Airbus Defense & Space (ADS). Among the spectral requirements that it must meet, some concern the Instrumental Spectral Response Function (ISRF), which is a key quantity of spectrometers, needed for spectral instrument calibration and atmospheric inversion calculations.
During the development of the Instrument, ADS proposed a method based on several Fourier Transforms to compute the ISRF, based on the one developed by R. Berlich for the FLORIS Instrument [1], in order to have an accurate model of its spectral performances.
In this paper, we will explain the simulation method, which allows to take into account diffraction at the system entrance pupil, the spectrometer slit and the dispersion grating, and also the theoretical optical quality of the Instrument. We will describe the preliminary experiments ADS performed to validate this approach. We will then present the work done at ADS and CNES for validating and cross-checking the results of our computations, that required the use of advanced light propagation modules of CODE V.
Once validated, this tool allows to accurately compute the theoretical performances of a given working point, such as the Full-Width at Half Maximum (FWHM) of the ISRF, the resolution of the spectrometer and the likeness of the ISRF to a gaussian function. It is also a powerful tool to quickly compute many ISRFs and thus carry out trade-offs on several parameters of the instrument.
Finally, by including this static computation into a loop and by varying the radiance inside the slit, it is possible to obtain dynamic ISRFs of complex scenes on the ground, and thus have a complete and validated model of the spectral performances of the MicroCarb instrument.
Monitoring the concentration of greenhouse gases from space is an important need. It can be achieved via a precise analysis of the chemical gaseous species (CO2, CH4, CO, etc.) signature in the spectrum of the reflected sunlight. The MICROCARB project aims to reach a very high quality measurement from on board a small volume Microsat platform, in 4 different spectral bands (O2 spectral band, 2 CO2 spectral bands and a CH4 spectral band), in order to locate and characterize the CO2 sinks and sources and to have a better understanding of the carbon cycle. But this is a very tricky measurement especially for the CO2 monitoring as its concentration in the atmosphere is about 380ppm and we need to measure it with accuracy better than +/− 1ppm. Another presentation is fully dedicated to the MICROCARB instrument design (see [1]).
Image quality specifications should aimed to fulfil high resolution mission requirements of remote sensing satellites with a minimum cost. The most important trade-off to be taken into account is between Modulation Transfer Function, radiometric noise and sampling scheme. This compromise is the main driver during design optimisation and requirement definition in order to achieve good performances and to minimise the mission cost.
For the SPOT 5 satellite, a new compromise had been chosen. The supermode principle of imagery (sampling at 2.5 meter with a pixel size of 5 meter) imp roves the resolution by a factor of four compared with the SPOT 4 satellite (10 meter resolution).
This paper presents the image quality specifications of the HRG-SPOT 5 instrument. We introduce all the efforts made on the instrument to achieve good image quality and low radiometric noise, then we compare the results with the SPOT 4 instrument’s performances to highlight the improvements achieved. Then, the in-orbit performance will be described. Finally, we will present the new goals of image quality specifications for the new Pleiades-HR satellite for earth observation (0.7 meter resolution) and the instrument concept.
Measuring the concentration of greenhouse gases from space is a current challenge. This measurement is achieved via a precise analysis of the signature of chemical gaseous species (CO2, CH4, CO, etc.) in the spectrum of the reflected sunlight. First at all, two families of spectrometers have been studied for the MicroCarb mission. The first family is based on the phenomena of interference between two radiation waves (Michelson Interferometer). The second family is based on the use of dispersive optical components. The second family has been selected for the forthcoming studies in the MicroCarb project. These instruments must have high radiometric and spectral resolutions, in narrow spectral bands, in order to discriminate between absorption lines from various atmospheric chemical species, and to quantify their concentration. This is the case, for example, for the instrument onboard the OCO-2 satellite (NASA/JPL).
Our analysis has led us to define a new instrumental concept, based on a dispersive grating spectrometer, with the aim of providing the same accuracy level as the OCO-2, but with a more compact design for accommodation on the Myriade Evolution microsatellite class. This compact design approach will allow us to offer a moderate-cost solution to fulfil mission objectives. Two other studies based on dispersive grating are in progress by CNES prime contractors (ASTRIUM and THALES ALENIA SPACE).
A summary of the main specifications of this design will be described, in particular the approach with the so-called “merit function”. After a description of such a space instrument, which uses a specific grating component, a preliminary assessment of performances will be presented, including the theoretical calculations and formula. A breadboard implementation of this specific grating has allowed us to show the practicality of this concept and its capabilities. Some results of this breadboard will be described. In addition, an instrument simulator is being developed to validate the performances of this concept. A grating component prototype has been built, and the specifications, together with the expected performances, will be described, in particular the polarisation ratio. Some elements about detectors will be also given regarding their suitability for the mission. This preliminary design is encouraging and shows that such a spectrometer may be compatible with a microsatellite platform (low mass, low power and compact design). Some prospects of improvements will also be considered.
The MicroCarb mission objective is to better understand the carbon cycle and predict its evolution. For that purpose MicroCarb is designed to measure the carbon dioxide (CO2) mixing ratio column within 1 ppm (a measurement precision of ~0.3%) from a space observatory in low Earth orbit (LEO) so as to locate and characterise the CO2 sinks and sources.
Measuring the concentration of greenhouse gases from space is a topical challenge. They are measured via a precise
analysis of the signature of chemical gaseous species (CO2, CH4, CO, etc.) in the spectrum of the Earth's atmosphere.
Two types of spectrometer are commonly used. The first is based on the interference between two radiation waves. The
Infrared Atmospheric Sounding Interferometer (IASI) aboard the METOP satellite is a good example of a fullyoperational
instrument of this kind. The second is based on the use of dispersive optical components. These instruments
must have high radiometric and spectral resolutions in narrow spectral bands to be able to discriminate absorption lines
from various atmospheric chemical species and to quantify their concentration. This is the case, for example, of the
instrument aboard NASA's Orbiting Carbon Observatory (OCO).
Our analysis led us to define a new instrument concept, based on a dispersive grating spectrometer, offering similar
performance in a more compact and therefore less expensive instrument.
After describing this instrument, which uses a specific grating component, a preliminary assessment of performances
will be presented, including the theoretical calculations and formulae. A mock-up version of this specific grating
demonstrated the feasibility of this concept and its capabilities. This preliminary design is encouraging and shows that
such a spectrometer may be compatible with a microsatellite bus. Some prospects for improvement are also considered.
Pleiades is the highest resolution civilian earth observing system ever developed in Europe. This imagery programme is conducted by the French National Space Agency, CNES. It will operate in 2008-2009 two agile satellites designed to provide optical images to civilian and defence users. Images will be simultaneously acquired in Panchromatic (PA) and multispectral (XS) mode, which allows, in Nadir acquisition condition, to deliver 20 km wide, false or natural colored scenes with a 70 cm ground sampling distance after PA+XS fusion. Imaging capabilities have been highly optimized in order to acquire along-track mosaics, stereo pairs and triplets, and multi-targets. To fulfill the operational requirements and ensure quick access to information, ground processing has to automatically perform the radiometrical and geometrical corrections. Since ground processing capabilities have been taken into account very early in the programme development, it has been possible to relax some costly on-board components requirements, in order to achieve a cost effective on-board/ground compromise. Starting from an overview of the system characteristics, this paper deals with the image products definition (raw level, perfect sensor, orthoimage and along-track orthomosaics), and the main processing steps. It shows how each system performance is a result of the satellite performance followed by an appropriate ground processing. Finally, it focuses on the radiometrical performances of final products which are intimately linked to the following processing steps : radiometrical corrections, PA restoration, image resampling and PAN-sharpening.
Optical remote sensing images are usually acquired according to the classical pushbroom principle. A linear array of CCD detectors, placed in the focal plane of the telescope, acquires a scanline over an integration time. The satellite's motion along its orbit, which is perpendicular to the linear array, ensures acquisition of successive lines. Because of inter-detector sensitivity differences, the image of a uniform landscape is striped vertically. Detector normalization aims at correcting these relative sensitivities and delivering uniform images of uniform areas. Determination of inter-detector coefficients requires observation of one uniform landscape, provided that each detector behaves linearly.
High resolution optical satellites like the future French PLEIADES-HR have to face a lack of signal, which moves the useful signal range towards the non-linear part of the detector response. For such designs, normalization has to be run with a non-linear model : this is a cost-effective way to improve image quality at low radiances and relax detector sorting. Regarding in-flight operations, non-linear parameters identification requires observation of several uniform landscapes and may be actually very difficult to run, because of the uniformity constraint.
An efficient way to bypass the quest of uniformity is to use the satellite agility in order to align the ground projection of the scanline on the ground velocity. This weird viewing principle allows all the detectors to view the same landscape. Thus, non-linear normalization coefficients can be computed by a histogram matching method.
The goal of this paper is to present the Pleiades-HR non-linear normalization model, the suited steered mode and the method to compute the coefficients within Pleiades-HR context.
Since SPOT1 launch in February 1986 and until SPOT5 launch in May 2002, the methods and means to insure the best quality of the images delivered to SPOT IMAGE customers have been continuously improved and updated. The quality of the corrected images is quantified through several figures of merit, including, for radiometric quality, the Signal-to-Noise Ratio (SNR).
Radiometric noise is due to two separate phenomena:
-column-wise noise: it represents on-board image chain performances.
-line-wise noise: normalization defects (radiometric model deviations) may lead to visible “columns” on a uniform landscape.
For each image, these two noises are combined in an “image noise” that quantifies the variations of the digital numbers on a uniform landscape.
Different techniques can be used to assess these different noises in-flight. For SPOT1 to SPOT4, the on-board lamp is used for both normalization and SNR assessment. For SPOT5, without lamp unit, we use images acquired over the quasi-uniform landscapes of Antarctic and Greenland for normalization. However, uniformity of these landscapes is not sufficient to accurately measure the SNR. So, a new method experimented during SPOT3 in-flight commissioning phase and operational for SPOT5 is applied. It consists in using two images of the same landscape acquired simultaneously to eliminate the landscape contribution.
This paper focuses on the presentation of this new method and compares its accuracy to the other methods. Finally, a comparison between flight measurements and ground measurements before launch is given.
The SPOT5 remote sensing satellite was launched in May 2002. It provides SPOT service continuity above and beyond SPOT4 operation but the SPOT5 system also significantly improves the SPOT service with the new characteristics of its two HRG (High Resolution Geometry) cameras and its HRS (High Resolution Stereo) camera. SPOT5's first two months of life in orbit were dedicated to instrument calibration and the assessment of image quality performances. During this period, the CNES team used specific target programming to compute image correction parameters and estimate the performance of the image processing chain, at system level. This paper focuses on the relative radiometric performances of the different spectral bands for the three instruments, deduced from in-flight measurements. For each spectral band, a radiometric model gives the ratio between detector response and input radiance. This model takes the architecture of the onboard image chain into account. Calibration provides the normalisation parameters (dark currents and relative inter-detector sensitivities) used to correct the images. The quality of the corrected images is quantified through several signal-to-noise ratio measurements based on different techniques. These methods are presented and their accuracy is discussed. Finally, a comparison is given between flight measurements and ground measurements.
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