A concept of the passive thermal control of the small radiation monitor (RM) – High Energy Particle Spectrometer (HEPS) - was developed in the Bridge Phase of the ESA planned VIGIL mission. RM was required to dissipate its heat to the outer space while the thermal link with the S/C was designed to be weak. Technical challenges of heat dissipation were addressed and resolved using modelling based on the ANSYS software. To verify fulfilment of this requirement, a realistic thermal model was constructed and verified under representative conditions. Measurements obtained for various operation modes of the instrument validated the finite element calculations and confirmed the thermal model concept.
J. C. Sun, B. B. Wu, T. W. Bao, T. Batsch, T. Bernasconi, I. Britvitch, F. Cadoux, I. Cernuda, J. Y. Chai, Y. W. Dong, N. Gauvin, W. Hajdas, J. J. He, M. Kole, M. N. Kong, S. W. Kong, C. Lechanoine-Leluc, Lu Li, J. T. Liu, X. Liu, R. Marcinkowski, S. Orsi, M. Pohl, N. Produit, D. Rapin, A. Rutczynska, D. Rybka, H. L. Shi, L. M. Song, J. Szabelski, R. J. Wang, X. Wen, H. L. Xiao, S. L. Xiong, H. H. Xu, M. Xu, L. Zhang, L. Y. Zhang, S. N. Zhang, X. F. Zhang, Y. J. Zhang, A. Zwolinska
The Gamma-ray Burst Polarimeter-POLAR is a highly sensitive detector which is dedicated to the measurement of GRB’s polarization with a large effective detection area and a large field of view (FOV). The optimized performance of POLAR will contribute to the capture and measurement of the transient sources like GRBs and Solar Flares. The detection energy range of POLAR is 50 keV ~ 500 keV, and mainly dominated by the Compton scattering effect. POLAR consists of 25 detector modular units (DMUs), and each DMU is composed of low Z material Plastic Scintillators (PS), multi-anode photomultipliers (MAPMT) and multi-channel ASIC Front-end Electronics (FEE). POLAR experiment is an international collaboration project involving China, Switzerland and Poland, and is expected to be launched in September in 2016 onboard the Chinese space laboratory “Tiangong-2 (TG-2)”. With the efforts from the collaborations, POLAR has experienced the Demonstration Model (DM) phase, Engineering and Qualification Model (EQM) phase, Qualification Model (QM) phase, and now a full Flight Model (FM) of POLAR has been constructed. The FM of POLAR has passed the environmental acceptance tests (thermal cycling, vibration, shock and thermal vacuum tests) and experienced the calibration tests with both radioactive sources and 100% polarized Gamma-Ray beam at ESRF after its construction. The design of POLAR, Monte-Carlo simulation analysis, as well as the performance test results will all be introduced in this paper.
X. Wu, R. Walter, M. Su, G. Ambrosi, P. Azzarello, M. Böttcher, J. Chang, M. Chernyakova, Y. Fan, C. Farnier, F. Gargano, I. Grenier, W. Hajdas, M. Mazziotta, M. Pearce, M. Pohl, A. Zdziarski
PANGU (the PAir-productioN Gamma-ray Unit) is a gamma-ray telescope with a wide field of view optimized for spectro-imaging, timing and polarization studies. It will map the gamma-ray sky from 10 MeV to a few GeV with unprecedented spatial resolution. This window on the Universe is unique to detect photons produced directly by relativistic particles, via the decay of neutral pions, or the annihilation or decay light from anti-matter and the putative light dark matter candidates. A wealth of questions can be probed among the most important themes of modern physics and astrophysics. The PANGU instrument is a pair-conversion gamma-ray telescope based on an innovative design of a silicon strip tracker. It is light, compact and accurate. It consists of 100 layers of silicon micro-strip detector of 80 x 80 cm2 in area, stacked to height of about 90 cm, and covered by an anticoincidence detector. PANGU relies on multiple scattering effects for energy measurement, reaching an energy resolution between 30-50% for 10 MeV – 1 GeV. The novel tracker will allow the first polarization measurement and provide the best angular resolution ever obtained in the soft gamma ray and GeV band.
POLAR is a joint European-Chinese experiment aimed at a precise measurement of hard X-ray polarization (50-500 keV) of the prompt emission of Gamma-Ray Bursts. The main aim is a better understanding of the geometry of astrophysical sources and of the X-ray emission mechanisms. POLAR is a compact Compton polarimeter characterized by a large modulation factor, effective area, and field of view. It consists of 1600 low-Z plastic scintillator bars read out by 25 at-panel multi-anode photomultipliers. The incoming X-rays undergo Compton scattering in the bars and produce a modulation pattern; experiments with polarized synchrotron radiation and GEANT4 Monte Carlo simulations have shown that the polarization degree and angle can be retrieved from this pattern with the accuracy necessary for identifying the GRB mechanism. The flight model of POLAR is currently under construction in Geneva. The POLAR instrument will be placed onboard the Chinese spacelab TG-2, scheduled for launch in low Earth orbit in 2015. The main milestones of the space qualification campaign will be described in the paper.
T. Bao, T. Batsch, I. Britvitch, F. Cadoux, J. Chai, Y. Dong, N. Gauvin, W. Hajdas, M. Kong, C. Lechanoine-Leluc, Lu Li, J. Liu, X. Liu, R. Marcinkowski, S. Orsi, M. Pohl, N. Produit, D. Rapin, A. Rutczynska, D. Rybka, H. Shi, J. Sun, J. Szabelski, R. Wang, X. Wen, B. Wu, H. Xiao, H. Xu, Li Zhang, L. Zhang, S. Zhang, Y. Zhang, A. Zwolinska
KEYWORDS: Polarization, Scintillators, Gamma radiation, Photons, Sensors, Polarimetry, Monte Carlo methods, Field programmable gate arrays, Synchrotron radiation, Space operations
POLAR is a Gamma-Ray Burst (GRB) polarization experiment in the energy range 50-500 keV. Detection
principle of the gamma-ray polarization is based on the anisotropy of the Compton scattering. POLAR consists
of 1600 low-Z plastic scintillator bars, read out by 25 flat-panel multianode photomultipliers. Simulations and
experiments have shown that the polarization degree and angle can be retrieved from the modulation curves
with the required accuracy. POLAR can reach a minimum detectable polarization of about 10%(3-sigma level)
for several strongest GRB detections per year. Construction and assembly of the Qualification Model (QM) are
ongoing, in view of a flight onboard of the Chinese Spacelab TG-2 scheduled for 2014.
The EURECA (EURopean-JapanEse Calorimeter Array) project aims to demonstrate the science performance and
technological readiness of an imaging X-ray spectrometer based on a micro-calorimeter array for application in future
X-ray astronomy missions, like Constellation-X and XEUS. The prototype instrument consists of a 5 × 5 pixel array of
TES-based micro-calorimeters read out by by two SQUID-amplifier channels using frequency-domain-multiplexing
(FDM). The SQUID-amplifiers are linearized by digital base-band feedback. The detector array is cooled in a cryogenfree
cryostat consisting of a pulse tube cooler and a two stage ADR. A European-Japanese consortium designs,
fabricates, and tests this prototype instrument. This paper describes the instrument concept, and shows the design and
status of the various sub-units, like the TES detector array, LC-filters, SQUID-amplifiers, AC-bias sources, digital
electronics, etc.
Initial tests of the system at the PTB beam line of the BESSY synchrotron showed stable performance and an X-ray
energy resolution of 1.58 eV at 250 eV and 2.5 eV @ 5.9 keV for the read-out of one TES-pixel only. Next step is
deployment of FDM to read-out the full array. Full performance demonstration is expected mid 2009.
W. Hajdas, N. Produit, E. Suarez-Garcia, F. Barao, C. Casella, K. Deiters, S. Deluit, C. Leluc, A. Mchedlishvilli, M. Pohl, D. Rapin, Ch. Tao, J.-P. Vialle, R. Walter, C. Wigger, A. Zehnder
The polarization data in hard X-ray and gamma-ray energy regimes remain until now very scarce. Having in mind very
large importance of the polarization information provided by astrophysical objects we propose a novel compact
polarimeter POLAR. It utilizes Compton scattering process and is based on the detector array made of low-Z, fast
scintillators. As the instrument with its relatively small dimensions and mass will be a non-intrusive one, it can be
installed on any typical satellite platform. It has a sensitivity peak in the energy range from tens to several hundreds keV
and a wide viewing angle covering almost a third of the sky. The main objects to be observed by POLAR will be
Gamma Ray Bursts and X-Ray Flashes but also X-ray pulsars (Crab). The instrument response and measurement
accuracy were intensively modeled and optimized in series of Monte Carlo simulations. It resulted in laboratory design
that consists of 2304 plastic scintillator bars with dimension 6x6x200 mm3. The scintillator light is converted by an
array of multi-anode photomultipliers. This arrangement assures both a large effective area for Compton scattering as
well as a big polarization modulation factor. Moreover, both quantities keep large values also for gammas coming off
the detector axis. Currently, a sequence of laboratory tests is performed using polarized photon sources of different
energies and various experimental setups. The first experiment consists of small (8x8) array of nominal scintillators
while the other one will utilize a large array (1536) of smaller bars (4x4x20 mm3) from the existing high energy project. The goal of these two measurements is to optimize the design, validate simulation results and test the prototype.
EURECA (EURopean-JapanEse Calorimeter Array) comprises a 5 x 5 pixel imaging TES-based micro-calorimeter
array read-out by SQUID-based frequency-domain-multiplexed electronics and cooled down by an adiabatic
demagnetization refrigerator. A European-Japanese consortium designs, fabricates, and tests this prototype instrument
with the aim to show within about 2 years technology readiness of a TES-based X-ray imaging micro-calorimeter array
in anticipation of future X-ray astronomy missions, like XEUS (ESA), Constellation-X (NASA), NEXT (JAXA), DIOS
(JAXA), ESTREMO (ASI), and NEW (Dutch-multinational). This paper describes the instrument concept, and shows
the design of the various sub-units, like the TES detector array, LC-filters, SQUID-amplifiers, flux-locked-loop
electronics, AC-bias sources, etc.
The Reuven Ramaty High Energy Solar Spectroscopic Imager (RHESSI) is a
NASA Small Explorer satellite designed to study hard x-ray and
gamma-ray emission from solar flares. In addition, its
high-resolution array of germanium detectors can see photons
from high-energy sources throughout the Universe. Here we discuss
the various algorithms necessary to extract spectra, lightcurves,
and other information about cosmic gamma-ray bursts, pulsars,
and other astrophysical phenomena using an unpointed, spinning
array of detectors. We show some preliminary results and discuss
our plans for future analyses. All RHESSI data are public, and
scientists interested in participating should contact the
principal author.
A Bismuth Germanate (BGO) 'veto' shield surrounds on five faces the detector planes of the IBIS instrument on-board the satellite INTEGRAL (INTErnational Gamma-Ray Astrophysics Laboratory). The Veto System provides anti-coincidence signals to the two imager layers covering the energy range from 20 keV to 10 MeV. The area to be shielded is about 8000 cm2, and with a shield thickness of 20 mm, this leads to a total BGO crystal weight of about 115 kg. This paper describes the shield design, and how some scientific and engineering requirements are implemented. Also results from tests with the Engineering Model are presented. Particular emphasis is given to the electronic signal chain, and its response to overload particles, mainly high energy protons, expected in the INTEGRAL orbit (Elliptic Earth Orbit with 72 h period). The overload response has been studied in detail both with a built-in Light Emitting Diode (LED) in the laboratory, and at a proton beam facility. Based on the lab measurements the expected blinding of the shield in-orbit is around 1%. This is obtained with a simple, but optimized chain, consisting of a front-end amplifier and a bi-polar shaper, that provides input to the trigger generator. Results from beam tests with proton energies from 60 to 300 MeV are reported, and it is demonstrated that the proton pulses in terms of amplitude, shape and duration are very similar to the simulated ones, and thus confirm the expected system response.
KEYWORDS: Imaging systems, Imaging spectroscopy, Calibration, Solar energy, Solar processes, Modulation, Space operations, Spectroscopy, Spatial resolution, Hard x-rays
The primary object of HESSI is to study the explosive energy release in solar flares. HESSI will image flares with spatial resolution ranging between 2 and 35 arcseconds over the energy range 3 keV to 20 MeV. The system is based on Fourier-transform imaging in connection with high-resolution Ge-detectors. HESSI uses 9 Rotating Modulation Collimators, each consisting of a pair of widely separated (1.55 m) grids mounted on the rotating spacecraft. The grid pitches range from 34 micron to 2.75 mm in steps of sqrt(3). This gives angular resolutions that are spaced logarithmically from 2.3 arcseconds to 3 arcmin, allowing sources to be imaged over a wide range of angular scales. In our design the most critical performance parameter, the relative twist between the two grids of each pair--can be very precisely monitored on ground (on a level of several arcseconds) by a special Twist Monitoring System (TMS). Extensive measurements and cross-calibrations between the TMS and several coordinate measuring machines before and after the environmental tests demonstrated the precision and stability of the alignment to be on the order of 5 arcseconds.
Martin Fivian, Jacek Bialkowski, W. Hajdas, Reinhold Henneck, A. Mchedlishvili, P. Ming, Knud Thomsen, Alex Zehnder, Gordon Hurford, David Curtis, David Pankow, Brian Dennis
HESSI will image Solar flares with spatial resolution ranging from 2 and 190 arcsec over the energy range from 3 keV to approximately equals 100 keV and as low as 35 arcsec for energies up to 20 MeV, respectively. The system is based on Fourier- transform imaging in connection with high-resolution Ge- detectors. In order to achieve arcsec-quality images with an instrument having only arcmin alignment requirements one needs in addition two precise aspect systems: (1) The Solar Aspect System (SAS) will provide Sun aspect data with high precision (< 0.2 arcsec relative and 1 arcsec absolute) and at high frequency (100 Hz). It consists of three identical lens/filter assemblies with focus Sun images on three 2048 X (13 micrometers )2 linear CCDS at 1.55 m focal distance. Simultaneous exposures of three chords of the focused solar images are made and the pixels spanning each solar limb are recorded. (2) The Roll Angle System (RAS) will provide precise (arcmin) information on the roll angle of the rotating spacecraft. The RAS is a star scanner which points out radially and observes stars at 75 degrees from the Sun direction using a commercial lens and a fast CCD. The passage of a star image over the CCD will induce a signal in one or several pixels and the timing of this signal defines the roll angle, once the star has been identified by comparing its pixel position and amplitude with a star map. With a limiting magnitude of mv equals 3 we expect to observe at least 1 star per revolution (during direct Sun view) over 1 year; on the average we will detect about 10 stars/revolution. We report on the design, construction and calibration measurements of the SAS and RAS flight-model instruments.
Reinhold Henneck, Jacek Bialkowski, F. Burri, Martin Fivian, W. Hajdas, A. Mchedlishvili, P. Ming, Knud Thomsen, J. Welte, Alex Zehnder, M. Dettwyler, F. Buerki, Gordon Hurford, David Curtis, David Pankow
The purpose of the HESSI RAS is to provide information on the roll angle of the rotation spacecraft. Precise knowledge of the roll angle is a necessary ingredient for image reconstruction. The RAS is a continuously operating star scanner that points out radially and observes stars at 75 degrees from the Sun direction using a commercial lens and a fast CCD. The passage of a star image over the CCD charges one or several pixels above threshold and the timing of this signal defines the roll angle, once the star has been identified by comparing its pixel position and amplitude with a star map. Roll angles at intermediate times are inferred by assuming uniform rotation. With a limiting star magnitude of mv equals 3 we expect to observe at least 1 star per revolution over 1 year; on the average we will detect about 10 stars/revolution.
Reinhold Henneck, Jacek Bialkowski, F. Burri, Martin Fivian, W. Hajdas, A. Mchedlishvili, P. Ming, Knud Thomsen, J. Welte, Alex Zehnder, Brian Dennis, Gordon Hurford, David Curtis, David Pankow
KEYWORDS: Charge-coupled devices, Sun, Imaging systems, Space operations, Solar energy, Fermium, Frequency modulation, Data processing, Light emitting diodes, Imaging spectroscopy
The HESSI SAS is a set of three Sun sensors, which shall provide high bandwidth information on the solar pointing of the rotating spacecraft. The precision of <EQ 0.4 arcsec relative is necessary in order to obtain the HESSI imaging resolution of 2 arcsec; the absolute accuracy of 1 arcsec is required for comparison with other measurements. Each SAS is based on focusing the Sun through a narrow bandwidth filter on to a 2048-element x (13(mu) )2 linear CCD. A digital threshold algorithm is used to select N pixels that span each solar limb for inclusion in the telemetry. Determination of the 6 limb crossing locations provided by the 3 subsystems defines the position offset of the Sun in the rotating frame. In this paper we describe the mechanical and electronic configuration of the SAS FM and the results of the first test measurements.
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