In-flight Performance Research Articles

PARASOL in-flight calibration and performance

Since 18 December 2004, the PARASOL satellite is a member of the so-called A-train atmospheric orbital observatory, flying together with Aqua, Aura, CALIPSO, CLOUDSAT, and OCO satellites. These satellites combine for the first time a full suite of instruments for observing aerosols and clouds, using passive radiometer complementarily with active lidar and radar sounders. The PARASOL payload is extensively derived from the instrument developed for the POLDER programs that performs measurements of bidirectionality and polarization for a very wide field-of-view and for a visible/near-infrared spectral range. An overview of the results obtained during the commissioning phase and the reevaluation after one year in orbit is presented. In-flight calibration methods are briefly described, and radiometric and geometric performances are both evaluated. All algorithms are based on a panel of methods using mainly natural targets previously developed for POLDER missions and adapted or redeveloped in the PARASOL context. Regarding performances, all mission requirements are met except for band 443 (not recommended for use). After one year in orbit, a perfect geometrical stability was found while a slight decrease of the radiometric sensitivity was observed and corrected through an innovative multitemporal algorithm based on observations of bright and scattered convective clouds. The scientific exploitation of PARASOL has now begun, particularly by coupling these specific observations with other A-train sensor measurements.

PAMELA: A payload for antimatter matter exploration and light nuclei astrophysics

PAMELA is a satellite-borne experiment designed to study the charged component of the cosmic radiation, with particular emphasis on antiparticles. PAMELA is mounted on the Resurs DK1 satellite that was launched on June 15th 2006 from the Baikonur cosmodrome and has a foreseen lifetime of at least 3 years. The PAMELA apparatus consists of a magnetic spectrometer, an electromagnetic calorimeter, a time-of-flight system, an anticoincidence system, a shower tail catcher scintillator and a neutron detector. The signal from all detectors allows a reliable identification of antiparticles in a large background of other charged particles. The first studies of the in-flight performance are presented in this article.

Archeops in-flight performance, data processing, and map making

Aims.Archeops is a balloon-borne experiment inspired by the Planck satellite and its high frequency instrument (HFI). It is designed to measure the cosmic microwave background (CMB) temperature anisotropies at high angular resolution (~12 arcmin) over a large fraction of the sky (around 30%) at 143, 217, 353, and 545 GHz. The Archeops 353 GHz channel consists of three pairs of polarized sensitive bolometers designed to detect the polarized diffuse emission of Galactic dust.

The Suzaku High Resolution X-Ray Spectrometer

Abstract The X-Ray Spectrometer (XRS) has been designed to provide the Suzaku Observatory with non-dispersive, high-resolution X-ray spectroscopy. As designed, the instrument covers the energy range 0.3 to 12 keV, which encompasses the most diagnostically rich part of the X-ray band. The sensor consists of a 32-channel array of X-ray microcalorimeters, each with an energy resolution of about 6 eV. The very low temperature required for operation of the array (60 mK) is provided by a four-stage cooling system containing a single-stage adiabatic demagnetization refrigerator, a superfluid-helium cryostat, a solid-neon dewar, and a single-stage, Stirling-cycle cooler. The Suzaku/XRS is the first orbiting X-ray microcalorimeter spectrometer and was designed to last more than three years in orbit. The early verification phase of the mission demonstrated that the instrument worked properly and that the cryogen consumption rate was low enough to ensure a mission lifetime exceeding 3 years. However, the liquid-He cryogen was completely vaporized two weeks after opening the dewar guard vacuum vent. The problem has been traced to inadequate venting of the dewar He and Ne gases out of the spacecraft and into space. In this paper we present the design and ground testing of the XRS instrument, and then describe the in-flight performance. An energy resolution of 6 eV was achieved during pre-launch tests and a resolution of 7 eV was obtained in orbit. The slight degradation is due to the effects of cosmic rays.

The X-Ray Telescope onboard Suzaku

Abstract We present the design parameters, production process, and in-flight performance of the X-ray telescope (XRT) onboard Suzaku. The imaging capability is significantly improved over the ASCA XRT, which had half-power diameters of ${3\rlap {.}{}^{\mathrm {\prime }}6}$, to ${1\rlap {.}{}^{\mathrm {\prime }}8}$–${2\rlap {.}{}^{\mathrm {\prime }}3}$ for all four XRT-I modules. The optical axes are found to be distributed within a radius of ${1\rlap {.}{}^{\mathrm {\prime }}3}$, which makes the observation efficiency of all the XRTs more than 97% at the XIS-default observing position. The vignetting over the XIS field of view predicted via ray-tracing coincides with that measured for observations of the Crab Nebula to within $\sim 10\%$. Contemporaneous fits of a power law to all of the XIS spectra of the Crab Nebula taken at the two standard observing positions (XIS/HXD-default positions) gives a flux consistent with that obtained by Toor and Seward (1974, AJ, 79, 995) to within $\sim 2\%$. The pre-collimator on the top of each XRT module successfully reduces the intensity of the stray light from the $20'$ and $50'$-off directions down to the level of pre-flight expectations.

The ADS40 Vaihingen/Enz geometric performance test

This paper presents the main results of a comprehensive ADS40 performance analysis conducted at the Vaihingen/Enz test field. As such it represents one example of an independent in-flight performance study for one of the new and commercially operational digital airborne camera systems. Based on a large number of well coordinated and defined object points, which served as independent check points, the absolute geometric accuracy of the ADS40 from true operational data has been verified. Empirical analysis of data from flying heights ranging from 1500 m to 4000 m proved the ADS40 geometric accuracy to be in the range of 1–2 μm at image scale for horizontal coordinates and 0.03–0.05‰ of the flying height for vertical components. This is fully within specification for airborne imaging.

OMEGA/Mars Express: Visual channel performances and data reduction techniques

In this paper we discuss the on-ground and in-flight performances of the visual channel of the OMEGA instrument on board the European mission Mars Express. OMEGA is a mapping spectrometer designed for mineralogical and atmospheric investigation of Mars. This work aims to be a guide to future users for the analysis of the OMEGA data. We give a detailed description of the instrumental characteristics of the OMEGA visual channel and systematic effects known so far, providing the guideline for the correct data processing.

ICE, the electric field experiment on DEMETER

The objective of the ICE (Instrument Champ Electrique) experiment on board DEMETER is to provide a nearly continuous survey of the electromagnetic and/or electrostatic waves that may arise from the coupling of seismic activity with the upper atmosphere and ionosphere. To this aim it makes use of 4 spherical electrodes with embedded preamplifiers that are deployed by stacer booms at approximately 4 m from the satellite. Measurements are made over a wide frequency range from DC to 3.175 MHz, subdivided in the signal processing unit in four frequency channels DC/ULF, ELF, VLF and HF. Three axis measurements are available in the DC/ULF range for all modes of operation of DEMETER and in the ELF range in the DEMETER Burst modes. In the VLF and HF ranges and in ELF during DEMETER Survey modes only one axis of measurement is available that can be selected by telecommand. We present in this paper a general description of the instrument and its modes of operation and in-flight performances. The sensitivity is ∼0.1–0.2 μV/m Hz 1/2 from ∼100 Hz through the HF range and the dynamical range is >80 dB in ELF and VLF and about 42 dB in HF. In order to illustrate the instrument capabilities, we briefly describe a number of observations from the first months of operation in various regions along the orbit from the equator to high latitudes.

The ISGRI CdTe gamma camera in-flight performance

The International Gamma-Ray Astrophysics Laboratory (INTEGRAL) soft gamma-ray imager (ISGRI) is the first large CdTe gamma camera ever built. It has provided faultless operations in space since the launch of INTEGRAL in October 2002. Here we give a general presentation of the system and pay particular attention to the noisy pixel handling. The observed effect of charged particles on the detectors and their integrated electronics is also presented. The in-flight detector evolution is detailed and the camera performance is reviewed

In-Flight status and performances of the detectors on board the INTEGRAL spacecraft

INTEGRAL is an observatory of the European Space Agency (ESA) dedicated to the study of the Gamma Ray sky. It features many different detector technologies: imaging micro-strip gas chambers, germanium crystals, cadmium telluride pixels, cesium iodide pixels, BGO crystals, silicon diodes, CCD optical camera. The measured stability and performances of those detectors have been for the moment according specifications. The noise level is slightly worse then expected. All the surrounding infrastructure of the detectors (orbit, satellite services, communications, ground segment) has exceeded specifications.

Using Sun Glint to Check the Relative Calibration of Reflected Spectral Radiances

Abstract Observations of sunlight reflected from regions of sun glint are used to check the relative calibration of spectral radiances obtained with imaging radiometers. Reflectances at different wavelengths for sun-glint regions are linearly related. Provided that the atmosphere is reasonably transparent at the wavelengths, the aerosol burden is reasonably light, 0.64-μm optical depth less than 0.2; the particles constituting the aerosol are reasonably large, as is the case for marine aerosols; and the solar zenith angle is less than about 35°, the linear relationships between reflectances at different wavelengths are rather insensitive to the factors that govern the reflectances themselves. The relationships are remarkably insensitive to atmospheric composition, surface wind speed and direction, illumination, and viewing geometry. The slopes and offsets of the linear relationships are used to assess the relative accuracies of the calibrations of the different channels. Such assessments would appear to be attractive for checks on the in-flight performance of aircraft-borne imaging radiometers. Here, observations of reflectances at 0.64, 0.84, 1.6, and 2.1 μm for regions of sun glint obtained with the Terra and Aqua Moderate Resolution Imaging Spectroradiometer (MODIS) instruments are shown to be consistent with each other. Observations of the 0.64- and 1.6-μm reflectances for the Tropical Rainfall Measuring Mission (TRMM) Visible and Infrared Scanner (VIRS) instrument are shown to be inconsistent with the MODIS observations, the VIRS 1.6-μm gain appearing to be too low by 9%. The 0.64-, 0.84-, and 1.6-μm reflectances obtained with the NOAA-16 and NOAA-17 Advanced Very High Resolution Radiometers (AVHRRs) for December 2002 are shown to be inconsistent with each other and inconsistent with the MODIS observations. Based on observations of the extensive ice sheets of Antarctica, the NOAA-16 0.64-μm gain is found to be too low by 5% and that for the 0.84-μm reflectance is too low by 12%; the NOAA-17 0.64-μm gain is found to be accurate (within 2%), but the 0.84-μm gain is too low by 15%. With the gains adjusted, the 0.64- and 0.84-μm reflectances obtained for regions of sun glint with the AVHRRs are consistent with each other and consistent with the Terra and Aqua MODIS observations. These results suggest that the gain for the NOAA-16 AVHRR 1.6-μm reflectance is accurate (within 1%) and that for the NOAA-17 AVHRR is too low by 5%. All of the observations were made with the AVHRR in the low-reflectance (high gain) mode. The accuracy of these assessments is expected to be about 5%.

The TopHat Experiment: A Balloon‐borne Instrument for Mapping Millimeter and Submillimeter Emission

The TopHat experiment was designed to measure the anisotropy in the cosmic microwave background radiation on angular scales from 03 to 30° and the thermal emission from both Galactic and extragalactic dust. The balloon-borne instrument had five spectral bands spanning frequencies from 175 to 630 GHz. The telescope was a compact, 1 m, on-axis Cassegrain telescope designed to scan the sky at a fixed elevation of 78°. The radiometer used cryogenic bolometers coupled to a single feed horn via a dichroic filter system. The observing strategy was intended to efficiently cover a region 48° in diameter centered on the south polar cap with a highly cross-linked and redundant pattern with nearly uniform sky coverage. The Long Duration Balloon flight over Antarctica in 2001 January surveyed about 6% of the sky. Here we describe the design of the instrument and the achieved in-flight performance and provide a brief discussion of the data analysis.

JASON 1: lessons learned from the development and 1 year in orbit

The JASON-1 small satellite was launched in December 2001 and has performed successfully since then, with in-flight performances exceeding expectations. The JASON-1 mission is dedicated to ocean and climate forecasting, in continuation with the successful TOPEX-POSEIDON satellite, launched in 1992. This project is in cooperation between NASA and CNES. JASON-1 is the first satellite based on the small PROTEUS bus, a cooperative partnership between CNES and ALCATEL Space Industries. This project was initiated in 1993 and in 1996 entered its developmental phase. At that time, the Faster, Better, Cheaper guidelines were driving the decisions and thus strong budgetary and schedule constraints were placed on the project while keeping ambitious technical performances. After more than 1 year of Jason operations in orbit, this paper gives a synthetic view of the major project achievement with respect to the initial requirements with a focus on advantages and drawbacks of a fast-paced development and qualification.

Spacecraft Disposal on a Graveyard Orbit: The In-Flight AOCS Performance for Eurostar 2000 and SPOT 1 during End-of-Life Operations

In agreement with the Inter-Agency Space Debris Coordination Committee recommendations, some EADS-Astrium spacecraft have been recently disposed of on a graveyard orbit at the end of their operational life. This disposal poses new challenges to the AOCS (Attitude and Orbit Control System) design. Two recent examples of such operations are described in this paper, based on in-orbit data: the Eurostar 2000 geostationary satellite and the SPOT 1 Low Earth Orbit satellite.

Calibration and in-flight performance of the Compton telescope prototype LXeGRIT

The Liquid Xenon Gamma-Ray Imaging Telescope (LXeGRIT) is the first balloon-borne instrument developed to validate the concept of a monolithic detector with 3D imaging capability as a Compton telescope for MeV astrophysics. The geometrical area is about 350 cm 2, an order of magnitude smaller than that of COMPTEL and the thickness of sensitive LXe is 7 cm, of equivalent stopping power as COMPTEL D2 detector. The spectroscopic and imaging response of LXeGRIT has been fully characterized in calibration experiments on the ground and during balloon flight experiments. During its most successful flight campaign of 27 h from Ft Sumner, in Fall 2000, the LXeTPC was operated without any external shield. The γ-ray background, measured at float altitude in the 0.5–10 MeV energy band, is well explained by the known atmospheric γ-ray flux. Results on the LXeGRIT in-flight performance, effective area, minimum flux sensitivity and background level are presented in this paper.

SPI/INTEGRAL in-flight performance

The SPI instrument has been launched on-board the INTEGRAL observatory on October 17, 2002. SPI is a spectrometer devoted to the sky observation in the 20 keV-8 MeV energy range using 19 germanium detectors. The performance of the cryogenic system is nominal and allows to cool the 19 kg of germanium down to 85 K with a comfortable margin. The energy resolution of the whole camera is 2.5 keV at 1.1 MeV. This resolution degrades with time due to particle irradiation in space. We show that the annealing process allows the recovery of the initial performance. The anticoincidence shield works as expected, with a low threshold at 75 keV, reducing the GeD background by a factor of 20. The digital front-end electronics system allows the perfect alignement in time of all the signals as well as the optimisation of the dead time (12%). We demonstrate that SPI is able to map regions as complex as the galactic plane. The obtained spectrum of the Crab nebula validates the present version of our response matrix. The 3 $\sigma$ sensitivity of the instrument at 1 MeV is 8 10$^{-7}$ph$\cdot$cm$^{-2}\cdot$s$^{-1}\cdot$keV$^{-1}$ for the continuum and 3 10$^{-5}$ph$\cdot$cm$^{-2}\cdot$s$^{-1}$ for narrow lines.

JEM–X inflight performance

We summarize the inflight performance of JEM–X, the X–ray monitor on the INTEGRAL mission during the initial ten months of operations. The JEM–X instruments have now been tuned to stable operational conditions. The performance is found to be close to the pre-launch expectations. The ground calibrations and the inflight calibration data permit to determine the instruments characteristics to fully support the scientific data analysis.

IBIS/PICsIT in-flight performances

PICsIT (Pixellated Imaging CaeSium Iodide Telescope) is the high energy detector of the IBIS telescope on-board the INTEGRAL satellite. PICsIT operates in the gamma-ray energy range between 175 keV and 10 MeV, with a typical energy resolution of 10% at 1 MeV, and an angular resolution of 12 arcmin within a \~100 square degree field of view, with the possibility to locate intense point sources in the MeV region at the few arcmin level. PICsIT is based upon a modular array of 4096 independent CsI(Tl) pixels, ~0.70 cm^2 in cross-section and 3 cm thick. In this work, the PICsIT on-board data handling and science operative modes are described. This work presents the in-flight performances in terms of background count spectra, sensitivity limit, and imaging capabilities.

SPI/INTEGRAL observation of the Cygnus region

We present the analysis of the first observations of the Cygnus region by the SPI spectrometer onboard the Integral Gamma Ray Observatory, encompassing similar to600 ks of data. Three sources namely Cyg X-1, Cyg X-3 and EXO 2030+375 were clearly detected. Our data illustrate the temporal variability of Cyg X-1 in the energy range from 20 keV to 300 keV. The spectral analysis shows a remarkable stability of the Cyg X-1 spectra when averaged over one day timescale. The other goal of these observations is SPI inflight calibration and performance verification. The latest objective has been achieved as demonstrated by the results presented in this paper.

First results from the IBIS/ISGRI data obtained during the Galactic Plane Scan

We report on INTEGRAL/IBIS observations of the Vela region during a Galactic Plane Scan (hereafter GPS) presenting the IBIS in-flight performances during these operations. Among all the known sources in the field of view we clearly detect 4U 0836-429, Vela X-1, Cen X-3, GX 301-2, 1E 1145.1-6141, and H0918-549 in the 20-40 keV energy range. Only Vela X-1 and GX 301-2 are detected in the 40-80 keV energy range, and no sources are visible above. We present the results of each individual observation (~2200 s exposure), as well as those from the mosaic of these scans.