KEYWORDS: Sensors, Image quality, Signal detection, Signal to noise ratio, Modulation transfer functions, Point spread functions, Image sensors, Charge-coupled devices
The Institute of Optical Sensor Systems (OS) at the Robotics and Mechatronics Center of the German Aerospace Center (DLR) has more than 35 years of experience with high-resolution imaging and imaging technology. This paper shows the institute’s scientific results of a hardware driven method to validate the image quality and keep it constant over the whole mission life time. This technology is applicable for highest resolution systems as well as for systems which are foreseen to measure reproducible data series over years. The technology is applicable for panchromatic and multispectral instrument designs. The paper will first define image quality, which is described by modulation transfer function, signal to noise ratio, spatial and spectral resolution, linearity and other key parameters. They are shown the differences in the quality assessment compared to the classic image-based methods. Within an in-orbit initialization phase of the instrument, the full electrical channel is validated by generating a defined amount of electrons instead of electrons coming from the photodiode. The approach is based on charge injection with a reproducible number of electrons which is driving the complete vertical pixel chain. The basic idea is to generate a periodic signal in orbit which can be analyzed with respect to radiation influences. The control timing of the FPGA sensor controller can be operated from ground via commanding. This procedure includes also the initialization mode by controlling the phase adjustment of the CDS sampling. The possible image degradation as a result of typical radiation effects over the mission life time is described in the paper as well as how such effects can be avoided in future by implantation of the proposed method. This new approach enables e.g. linearity test, analysis and alignment and shows the relevance of such a validation technology for high-resolution optical space instruments.
Greenhouse gas emissions caused by human activities remain one of the most important subjects of international discussions. The routine gas flaring has been estimated to be responsible for as much as 1% of global carbon dioxide emission per year. Gas flaring analysis is one of the key-interest subjects in remote sensing community. Some of the existing publications use remote sensing techniques with satellite imagery to derive information about flame temperature and further about to estimate the volume of the flared gas. The often missing element is an in-situ measurement analysis of gas flames, combining signals recorded by a camera on-ground and data on flared gas volume, temperature and gas type. In order to address this problem, an experiment was conducted, in which the gas flame was recorded by thermal cameras on-ground, simultaneously to an aerial survey and the gas flow was measured at the same time on-ground. The measurement setup was designed in cooperation between Institute of Optical Sensor Systems of German Aerospace Center (DLR) and German Federal Institute for Materials Research and Testing (BAM). Cameras recording in thermal and mid-wave IR wavelengths were used to record the burning gas on-ground and from the aerial survey. All the measurements have been compared and statistically analysed with respect to the recorded temperature. The purpose of the examination was to describe the signal changes in thermal imagery with respect to changes in energy, emitted by the burning process. This approach will allow for later calculation of the amount of energy in form of thermal radiation sent from the flame to the satellite.
The Institute of Optical Sensor Systems (OS) at the Robotics and Mechatronics Center of the German Aerospace Center (DLR) has more than 35 years of experience with high-resolution imaging technology. This paper shows the institutes scientific results of the next generation of CMOS detector design in a TDI (Time Delay and Integration) architecture. This project includes the technological design of future high or multispectral resolution space-borne instruments and the possibility of higher integration. First results where published by Eckardt, et al. (1 ) 2013 and (2 ) 2014. DLR OS and the Fraunhofer Institute for Microelectronic Circuits and Systems in Duisburg were driving the technology of new detectors for future high resolution projects and hybridization capability in order to keep pace with the ambitious scientific and user requirements. In combination with the engineering research, the current generation of space borne sensor systems is focusing on VIS/NIR high spectral resolution to meet the requirements on earth and planetary observation systems. The combination of large swath and high-spectral resolution with intelligent synchronization control, fast-readout ADC chains and new focal-plane concepts open the door to new remote-sensing and smart deep-space instruments. The paper gives an overview over the DLR detector development and verification program on FPA level. New control possibilities for CMOS-TDI NGdetectors in synchronization control mode, and key parameters like linearity, PTC, cross talk and control effort will be discussed in detail.
KEYWORDS: Sensors, Calibration, Light emitting diodes, Camera shutters, Signal detection, Global Positioning System, Interference (communication), Temperature metrology, Spectroscopy, Space operations
The DLR Earth Sensing Imaging Spectrometer (DESIS) is a new space-based hyperspectral sensor developed and operated by a collaboration between the German Aerospace Center (DLR) and Teledyne Brown Engineering (TBE). DESIS will provide hyperspectral data in the visible to near-infrared range with high resolution and near-global coverage. TBE provides the platform and infrastructure for the operation on the International Space Station (ISS), DLR has developed the instrument. This paper gives an overview of the design of the DESIS instrument together with results from the optical on-ground calibration. In-flight calibration, stability of dark signal and rolling vs. global shutter analysis will be presented.
This paper focuses on the calibration and verification of the DESIS (DLR Earth Sensing Imaging Spectrometer) detector for the VIS/NIR (VNIR) spectral range. DESIS is a hyperspectral Instrument for the international space station, developed from the German Aerospace Center (DLR) and operate by Teledyne Brown Engineering (TBE). TBE provides the MUSES platform, on which the DESIS instrument will be mounted. The primary goal of DESIS is to measure and analyse quantitative diagnostic parameters describing key processes on the Earth surface. The main components of the sensor, the detector and the focal plane, were examined and verified. This allows predictions about the future data quality. The verification and validation of components and the entire system is an important and challenging task. The verification of the detectors is necessary to describe the characteristics of the detector according to predetermined specifications. The quantities to be examined are e.g. the quantum efficiency, the linearity of the detector, the pixel response non-uniformity (PRNU) and the dark current noise. For this purpose, specially calibrated integrated spheres are used that allow traceability of the measured data. With these information, the future performance of the sensor can be estimated using simulations.
Hyperspectral instruments are fundamental tools in remote sensing for environmental control and precision farming. For hyperspectral sensors often conventional optical designs based on grating or prism spectrometers are preferred. These instruments meet the system and mission requirements. From the provided data high quality information can be derived. However, more and more data is being offered by low-cost missions. This will establish new business models and data providers. This article is intended to provide an overview of current low cost sensors for hyperspectral applications.
The DLR Earth Sensing Imaging Spectrometer (DESIS) is a new space-based hyperspectral instrument developed by DLR and operated under collaboration between the German Aerospace Center (DLR) and Teledyne Brown Engineering (TBE). DESIS will be mounted on the International Space Station on the MUSES platform in 2018 and will provide hyperspectral Earth Observation in the wavelength range from visible to near-infrared with high resolution and near global coverage. TBE provides the platform and infrastructure on the ISS. DLR developed the instrument, while the optical system was fabricated and pre-aligned by the Fraunhofer Institut fur Angewandte Optik und Feinmechanik (IOF). This paper presents the on-ground adjustment, focusing and calibration approach for DESIS done at the optical lab of the Institut fur Optische Sensorsysteme (DLR). The optical lab set-up will be described in detail. Selected calibration results like detector Modulation Transfer Function (MTF) and linearity, optics MTF and wave front, focus position, smile and keystone measurement, instrument spatial and spectral MTF, and absolute radiometric calibration will be presented. The spectral and radiometric in- ight calibration approach of the DESIS calibration unit (CAL) based on stabilized Light Emitting Diode (LED) arrays will be demonstrated. In addition, the innovative pointing unit (POI) in front of the instrument and its pointing accuracy will be introduced. Finally imaging quality and accuracy of the sensor calibration will be evaluated with respect to foreseen applications.
The Sentinel-4 payload is a multi-spectral camera system, designed to monitor atmospheric conditions over Europe from a geostationary orbit. The German Aerospace Center, DLR Berlin, conducted the verification campaign of the Focal Plane Subsystem (FPS) during the second half of 2016. The FPS consists, of two Focal Plane Assemblies (FPAs), two Front End Electronics (FEEs), one Front End Support Electronic (FSE) and one Instrument Control Unit (ICU). The FPAs are designed for two spectral ranges: UV-VIS (305 nm - 500 nm) and NIR (750 nm - 775 nm). In this publication, we will present in detail the set-up of the verification campaign of the Sentinel-4 Qualification Model (QM). This set up will also be used for the upcoming Flight Model (FM) verification, planned for early 2018. The FPAs have to be operated at 215 K ± 5 K, making it necessary to exploit a thermal vacuum chamber (TVC) for the test accomplishment. The test campaign consists mainly of radiometric tests. This publication focuses on the challenge to remotely illuminate both Sentinel-4 detectors as well as a reference detector homogeneously over a distance of approximately 1 m from outside the TVC. Selected test analyses and results will be presented.
The detectors of the Sentinel 4 multi spectral imager are operated in flight at 215K while the analog electronics is operated at ambient temperature. The detector is cooled by means of a radiator. For thermal reasons no active component has been allowed in the cooled area closest to the detector as the passive radiator is restricted in its size. For thermal decoupling of detector and electronics a long distance between detector and electronics is considered ideal as thermal conductivity decreases with the length of the connection. In contradiction a short connection between detector and electronics is ideal for the electronic signals. Only a short connection ensures the signal integrity of both the weak detector output signal but similarly also the clock signals for driving the detector. From a mechanical and thermal point of view the connection requires a certain minimum length. The selected solution serves all these needs but had to approach the limits of what is electrically, mechanically and thermally feasible. In addition, shielding from internal (self distortion) and external distorting signals has to be realized for the connection between FEE(Front End Electronics) and detectors. At the time of the design of the flex it was not defined whether the mechanical structure between FEE and FPA (Focal Plane Assembly) would act as a shielding structure. The physical separation between CCD detector and the Front-end Electronics, the adverse EMI environment in which the instrument will be operated in (the location of the instrument on the satellite is in vicinity to a down-link K-band communication antenna of the S/C) require at least the video output signals to be shielded. Both detectors (a NIR and a UVVIS detector) are sensitive to contamination and difficult to be cleaned in case of any contamination. This brings up extreme cleanliness requirements for the detector in manufacturing and assembly. Effectively the detector has to be kept in an ISO 5 environment and additionally humidity has to be avoided - which does not comply with the usual clean-room atmosphere. This paper describes how in Sentinel 4 the given challenges have been overcome, how the limited load drive capability of the detector component has been considered on a flex length of about 20 cm (7.87 in) and how EMC shielding of the highly sensitive analog signals of the detector has been realized. Also covered are design/manufacturing aspects and a glance on testing results is provided
The Sentinel-4 instrument is an imaging spectrometer, developed by Airbus under ESA contract in the frame of the joint European Union (EU)/ESA COPERNICUS program. SENTINEL-4 will provide accurate measurements of trace gases from geostationary orbit, including key atmospheric constituents such as ozone, nitrogen dioxide, sulfur dioxide, formaldehyde, as well as aerosol and cloud properties. Key to achieving these atmospheric measurements are the two CCD detectors, covering the wavelengths in the ranges 305 nm to 500 nm (UVVIS) and 750 to 775 nm (NIR) respectively. The paper describes the architecture, and operation of these two CCD detectors, which have an unusually high full-well capacity and a very specific architecture and read-out sequence to match the requirements of the Sentinel- 4 instrument. The key performance aspects and their verification through measurement are presented, with a focus on an unusual, bi-modal dark signal generation rate observed during test.
KEYWORDS: Sensors, Ultraviolet radiation, Charge-coupled devices, CCD image sensors, Signal detection, Spectroscopy, Near infrared, Detector development, Data acquisition, Data modeling
The future ESA Earth Observation Sentinel-4/UVN is a high resolution spectrometer intended to fly on board a Meteosat Third Generation Sounder (MTG-S) platform, placed in a geostationary orbit. The main objective of this optical mission is to continuously monitor the air quality over Europe in near-real time. The Sentinel-4/UVN instrument operates in three wavelength bands: Ultraviolet (UV: 305-400 nm), Visible (VIS: 400- 500 nm) and Near-infrared (NIR: 750-775 nm). Two dedicated CCD detector have been developed to be used in the Focal Plane Subsystems (FPS), one for the combined UV and VIS band, the other covering the NIR band. Being a high resolution spectrometer with challenging radiometric accuracy requirements, both on spectral and spatial dimensions, an effect such the Random Telegraph Signal (RTS) can represent a relevant contribution for the complete system accuracy. In this work we analyze the RTS effect on data acquired during the FPS testing campaign with qualification models for the Sentinel-4/UVN detectors. This test campaign has been performed in late 2016. The strategy for the impact assessment of RTS is to measure the effect at room temperature and then to extrapolate the results to the at instrument operational temperature. This way, very-long lasting data acquisitions could be avoided since the RTS frequency is much lower at cryogenic temperatures. A reliable technique for RTS effect detection has been developed in order to characterize the signal levels amplitude and occurrence frequencies (flipping rate). We demonstrate the residual impact of the RTS on the global In-Orbit Sentinel-4/UVN instrument performance and products accuracy.
The Sentinel 4 instrument is an imaging spectrometer, developed by Airbus under ESA contract in the frame of the joint European Union (EU)/ESA COPERNICUS program with the objective of monitoring trace gas concentrations. Sentinel 4 will provide accurate measurements of key atmospheric constituents such as ozone, nitrogen dioxide, sulfur dioxide, formaldehyde, as well as aerosol and cloud properties. Sentinel 4 is unique in being the first geostationary UVN mission. The SENTINEL 4 space segment will be integrated on EUMETSAT's Meteosat Third Generation Sounder satellite (MTG-S). Sentinel 4 will provide coverage of Europe and adjacent regions. The Sentinel 4 instrument comprises as a major element two Focal Plane Subsystems (FPS) covering the wavelength ranges 305 nm to 500 nm (UVVIS) and 750 nm to 775 nm (NIR) respectively. The paper describes the Focal Plane Subsystems, comprising the detectors, the optical bench and the control electronics. Further the design and development approach will be presented as well as first measurement results of FPS Qualification Model.
We expect commercial high resolution imaging systems, which are able to provide data with 25cm ground sample distance (GSD) or better in the near future. For selling the data, it is necessary to re-sample it to 30cm. The situation is similar when swinging out the satellite perpendicular to his ight direction. The GSD is then variable with the angle to Nadir direction. In this paper a method is proposed that the resolution adjusts adaptively according to the requirements.
Photogrammetry and remote sensing (RS) provide procedures for deriving geometric, radiometric and thematic
information from image data. A variety of aircraft and space-borne sensors are available to capture image data.
Different standards and specifications of quality assessment for optical remote sensing data are available. Due to
the possibilities of absolute geometric and radiometric calibration digital sensors provide new promising opportunities
to create value added products like digital elevation models, land-use maps etc. Such cameras combine the
high geometric quality with the radiometric standards of earth observation systems. The determination of image
quality of remote sensing data can be distinguished in (spectral) radiometric and geometric aspects. Standards
contains different metrics for accuracy issues (spectral, radiometric and geometric accuracy) and for performance
parameters like SNR, MTF. Image artefacts (caused e.g. by compression) are an additional important topic.
The paper gives an overview of the current debate and the possibility of standardization.
The Institute of Optical Sensor Systems (OS) at the Robotics and Mechatronics Center of the German Aerospace Center
(DLR) has more than 30 years of experience with high-resolution imaging technology. This paper shows the institute’s
scientific results of the leading-edge detector design CMOS in a TDI (Time Delay and Integration) architecture. This
project includes the technological design of future high or multi-spectral resolution spaceborne instruments and the
possibility of higher integration. DLR OS and the Fraunhofer Institute for Microelectronic Circuits and Systems (IMS) in
Duisburg were driving the technology of new detectors and the FPA design for future projects, new manufacturing
accuracy and on-chip processing capability in order to keep pace with the ambitious scientific and user requirements. In
combination with the engineering research, the current generation of space borne sensor systems is focusing on VIS/NIR
high spectral resolution to meet the requirements on earth and planetary observation systems. The combination of large-swath
and high-spectral resolution with intelligent synchronization control, fast-readout ADC (analog digital converter)
chains and new focal-plane concepts opens the door to new remote-sensing and smart deep-space instruments. The paper
gives an overview of the detector development status and verification program at DLR, as well as of new control
possibilities for CMOS-TDI detectors in synchronization control mode.
The facility Optical Information Systems (OS) at the Robotics and Mechatronics Center of the German Aerospace Center (DLR) has more than 30 years of experience with high-resolution imaging technology. This paper shows the scientific results of the institute of leading edge instruments and focal plane designs for EnMAP VIS/NIR spectrograph. EnMAP (Environmental Mapping and Analysis Program) is one of the selected proposals for the national German Space Program. The EnMAP project includes the technological design of the hyper spectral space borne instrument and the algorithms development of the classification. The EnMAP project is a joint response of German Earth observation research institutions, value-added resellers and the German space industry like Kayser-Threde GmbH (KT) and others to the increasing demand on information about the status of our environment. The Geo Forschungs Zentrum (GFZ) Potsdam is the Principal Investigator of EnMAP. DLR OS and KT were driving the technology of new detectors and the FPA design for this project, new manufacturing accuracy and on-chip processing capability in order to keep pace with the ambitious scientific and user requirements. In combination with the engineering research, the current generations of space borne sensor systems are focusing on VIS/NIR high spectral resolution to meet the requirements on earth and planetary observation systems. The combination of large swath and high spectral resolution with intelligent synchronization control, fast-readout ADC chains and new focal-plane concepts open the door to new remote-sensing and smart deep space instruments. The paper gives an overview over the detector verification program at DLR on FPA level, new control possibilities for sCMOS detectors in global shutter mode and key parameters like PRNU, DSNU, MTF, SNR, Linearity, Spectral Response, Quantum Efficiency, Flatness and Radiation Tolerance will be discussed in detail.
Technology changes in detector development and the significant improvement of manufacturing accuracy in combination
with the permanent engineering research influences the spaceborne sensor systems, which are focused on Earth
observation and remote sensing. Developments in focal plane technology, e.g. the combination of large TDI lines,
intelligent synchronisation control, fast readable sensors and new focal plane and telescope concepts are the key
developments for new remote sensing instruments. This class of instruments disposes of high spatial and radiometric
resolution for the generation of data products for mapping and 3D GIS VR applications. Systemic approaches are
essential for the design of complex sensor systems based on dedicated tasks. The system-theoretical description of the
instrument inside and a simulated environment is the basic approach for the optimisation process of the optical,
mechanical and electrical designs and assembly. Single modules and the entire system have to be calibrated and verified.
The traceability of the performance-related parameters from the single sensor up to the flight readiness of the instrument
forms the main focus inside such complex systems. In the future it will also be possible to prove the sensor performance
on wafer level before assembly. This paper gives an overview about current technologies for performance measurements
on sensor, focal plane assembly (FPA) and instrument level without the optical performance of the telescope. The paper
proposes also a technology, which can be used for sensor performance measurements on wafer level.
The high-resolution imaging system ADS40 is a development to fulfill both photogrammetric and remote sensing requirements. The new sensor was introduced in mid 2000 and will close the digital chain for airborne photogrammetric data processing.
12 During the past two years the company LH Systems and the German Aerospace Center (DLR) have developed the commercial airborne digital sensor ADS40 based on the three-line principle. By assembling additional CCD lines into the same focal plane, the sensor is capable of generating a number of color images. In the first part, the sensor system itself is introduced shortly. The main concept and the key features are described and an overview of the data processing scheme is given. After that, we will focus on the results of test flights. The emphasis is placed on the properties of the overall system including the sensor itself, platform, airplane, and inertial measurement unit. The effect of using staggered CCD lines is discussed. Flights over well known test areas are used to prove the accuracy of derived data products, DEMs, color images, and ortho-images. Differences in data processing methods are pointed out in comparison to sensor systems based on CCD matrices or film.
The consistent simulation of airborne and spaceborne hyperspectral data is an important task and sometimes the only way for the adaptation and optimization of a sensor and its observing conditions, the choice and test of algorithms for data processing, error estimations and the evaluation of the capabilities of the whole sensor system. The integration of three approaches is suggested for the data simulation of APEX (Airborne Prism Experiment): (1) a spectrally consistent approach (e.g. using AVIRIS data), (2) a geometrically consistent approach (e.g. using CASI data), and (3) an end-to- end simulation of the sensor system. In this paper, the last approach is discussed in detail. Such a technique should be used if there is no simple deterministic relation between input and output parameters. The simulation environment SENSOR (Software Environment for the Simulation of Optical Remote Sensing Systems) presented here includes a full model of the sensor system, the observed object and the atmosphere. The simulator consists of three parts. The first part describes the geometrical relations between object, sun, and sensor using a ray tracing algorithm. The second part of the simulation environment considers the radiometry. It calculates the at-sensor-radiance using a pre-calculated multidimensional lookup-table for the atmospheric boundary conditions and bi- directional reflectances. Part three consists of an optical and an electronic sensor model for the generation of digital images. Application-specific algorithms for data processing must be considered additionally. The benefit of using an end- to-end simulation approach is demonstrated, an example of a simulated APEX data cube is given, and preliminary steps of evaluation of SENSOR are carried out.
A multisensor airborne campaign is carried out in Switzerland in summer 1997. The campaign did not only involve a suite of different sensors but also extensive ground supporting measurements. Amongst the sensor that acquired data over a predefined set of three standard test sites were the hyperspectral imagers DAIS 7915 and CASI, a wide angle airborne camera (WAAC) and a SAR (E-SAR) system as well as an imaging laserscanner. On the ground, geolocation is performed with differential GPS systems and a number of georeferenced ground control points. An active navigation system for the aircraft is used for accurate flight path determination in order to support single- and multi-pass interferometric flights. The thermal ground references consist of a number of targets in the field to verify the thermal performance of the DAIS. Radiometric validation on the ground involves spectroradiometric measurements of a number of selected reference targets, measurements of global flux and radiant temperature, as well as sunphotometer measurements. Conventional field mapping completes the full documentation of the three test sites. The generation of digital surface models using the stereo approach of the WAAC camera and the laserscanner is a goal to support the georeferencing of the different acquired image data. Finally all data are projected onto a common reference system and can be used for further analysis.
A simulation system allows analyses of specific sensor configurations. Application areas for such an approach are: (1) design and optimization of optical sensors for specific (well known) applications, (2) sensitivity of different data products to position and calibration errors, (3) test of retrieval algorithms, and (4) mission support. The simulation system consists of mathematical and physical models to simulate the passage of electromagnetic radiation from the source of the emission to the sensor. The key part of this simulation system is a ray tracer interacting with a digital terrain model around an ellipsoid, it also includes sensor opto- electronics and spacecraft orbit calculation. Other parts are the simulation of the planetary atmosphere and the hardware of the sensor with additional retrieving algorithms. The usefulness of the simulation system for the optimization has been shown with a three-line CD sensor for the determination of cloud position and speed. For the simulation system clouds are assumed as a partly transparent, uniformly moving body, modeled by a digital terrain model over the surface. Furthermore a simple radiometric model was implemented: A cloud has a constant transmission, the ground surface and the clouds have constant albedos. The simulation shows that some conditions are mandatory for the determination of cloud speed and height, especially the movement of the sensor has to be an accelerated one. This will be reached though a highly elliptical orbit of the satellite. However, the determination will not be possible near pericentre.
Images are degraded by both blur according to a deterministic spread function and by additive noise. The removal of blur is an ill-posed inverse problem. Therefore prior knowledge about the original scene and point spread function as well as noise information about the image forming system are necessary. In the past a lot of different algorithms have been proposed. In this paper an approach for comparison is presented and demonstrated on different example algorithms.
A simulation system has been developed that allows computer experiments with specific sensor configurations. Application areas for such an approach are: (1) design and optimization of optical sensors for specific (well known) applications; (2) sensitivity of different data products to position and calibration errors; (3) test of retrieval algorithms; and (4) mission support. The simulation system consists of mathematical and physical models to simulate the passage of electro-magnetic radiation from the source of the emission to the sensor. The key part of this simulation system is a ray tracer interacting with a digital terrain model around an ellipsoid. The simulator consists of three parts for the following tasks: (1) With a ray-tracing procedure in a digital terrain model (DTM) a reflection image is generated. The reflection model is Lambertian. The sensor geometry can be a CCD line or a matrix camera. (2) The calculation of the radiation intensity in front of the CCD. The transmission and scattering in the atmosphere, the reflection properties of the surface, spectral filters and angular dependences of the optics have been considered. (3) The evaluation of the analog part of the camera. A statistical noise is added to each pixel. The approach is outlined with some examples.
The paper describes a simulation system which allows numerical experiments with specific sensor configurations. The system consists of mathematical and physical models to simulate the passage of electro-magnetic radiation from the emitting source to the sensor. The simulation is focused on WAOSS (wide angle optoelectronic stereo scanner). WAOSS is a part of the Mars '94/96 project and shall orbit that planet on a platform together with other optical sensors. The crucial feature of this camera is the in-track stereo capability. A serious problem is the test of a simulator for the Mars application. A thorough investigation has two parts: The accuracy of the radiometric values and the geometric image given by the digital terrain model (DTM). Such tests are possible only on Earth, with the airplane camera of WAOSS in a well known reference area with an independently measured DTM. Measured and simulated data are compared and show a good correlation.
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