Changeset 145 in JEM-EUSO
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- May 13, 2013, 3:56:40 PM (11 years ago)
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ICRC2013/EusoBalloonDetector/trunk/icrc2013-EBDet-morettodagoret.tex
r141 r145 50 50 This telescope will be the payload of a stratospheric balloon operated by CNES, starting its flight campaign in 2014. 51 51 Current technical development for JEM-EUSO are a challenge for a space project, have been implemented in EUSO-Balloon. 52 In this poster, the complete design of this instrument will be presented. It consists of an advanced modular telescope structure including a set of three Fresnel lenses having an excellent focusing capability onto its pixelized focal surface of its UV Camera. This camera is very sensitive to single photons, with 6 orders of magnitude dynamic range thanks to an adaptive gain, and fast enough to observe speed-of-light phenomena. The camera is an array of multianodes photomultipliers, which dynodes are driven by Crockoft Walton HV generators capable of switching down the gain in few microseconds to protect the photodetectors against strongly luminous events.52 In this article, the complete design of this instrument will be presented. It consists of an advanced modular telescope structure including a set of three Fresnel lenses having an excellent focusing capability onto its pixelized focal surface of its UV Camera. This camera is very sensitive to single photons, with 6 orders of magnitude dynamic range thanks to an adaptive gain, and fast enough to observe speed-of-light phenomena. The camera is an array of multianodes photomultipliers, which dynodes are driven by Crockoft Walton HV generators capable of switching down the gain in few microseconds to protect the photodetectors against strongly luminous events. 53 53 The analog signals at anodes are digitised continuously each time window (2.5 microsecond) by an ASIC, performing two kinds of signal measurements and readout by a FPGA applying a first level trigger algorithm. 54 54 The Electronics is operated by a digital processing unit comprising a CPU associated to Clocks generators board and a GPS receiver, an event filtering board based on a FPGA and an House-Keeping unit for the instrument monitoring. The CPU controls both acquisition and the data storage. … … 66 66 67 67 \section{Introduction} 68 EUSO-Ballon is a telescope aiming at verifying the conceptual design as well as the technologies foreseen to be applied for the construction of the future space telescope JEM-EUSO mission~\cite{bib:EUSOperf}. Even if this instrument is a reduced version of JEM-EUSO, it however includes almost all the required components of the original space mission. The scientific and technical goals on its mission are reviewed in the reference~\cite{bib:EBpath}. This instrument will be the payload of a stratospheric balloon operated by CNES,69 to perform a series of night-flights at altitudes of 40 km, at various earth locations, lasting from a few hours to tens of hours. This program s require payload recovery after landing either in water or hard soil, and repairing after each mission.70 The special atmospheric environmental conditions and recovery requirements involved much precautions in the design and implied dedicated tests the realisation of prototypes. 71 First of all, the section~\ref{sec:OverviewInstrument} gives the overview of the instrument, including its particular mechanical design adapted to the balloon flights. Then the section~\ref{sec:Subsystems} provides details on the subsystems comprising the instrument highlighting the reasons for the chosen design. Afterward, the section~\ref{sec:AssemblyTest} deals with the series of preliminary measurements and tests which are mandatory before the commissioning of the instrument for exploration. And finally, in the section 5, the control and analysis tasks to be performed during the operation are mentioned. 68 EUSO-Ballon is a telescope aiming at verifying the conceptual design as well as the technologies foreseen to be applied for the construction of the future space telescope JEM-EUSO ~\cite{bib:EUSOperf}. Even if this instrument is a reduced version of JEM-EUSO, it however includes almost all the required components of the original space mission. The scientific and technical goals on its mission are reviewed in the reference~\cite{bib:EBpath}. This instrument will be the payload of a stratospheric balloon operated by CNES, 69 to perform a series of night-flights at altitudes of 40 km, at various earth locations, lasting from a few hours to tens of hours. This program requires payload recovery after landing either in water or hard soil, and repairing after each mission. The special atmospheric environmental conditions and recovery requirements involve much precautions in the design and imply dedicated tests for the realisation of prototypes. 70 71 This paper is organised as follows. First, section~\ref{sec:OverviewInstrument} gives the overview of the instrument, including its particular mechanical design adapted to the balloon flights. Section~\ref{sec:Subsystems} provides details on the subsystems and highlights reasons for the chosen design. Afterward, the section~\ref{sec:AssemblyTest} deals with the series of preliminary measurements and tests which are mandatory before the commissioning of the instrument for exploration. Finally, the control and analysis tasks to be performed during the operation are mentioned in section ~\ref{sec:Operation}. 72 72 73 73 … … 75 75 \label{sec:OverviewInstrument} 76 76 77 The EUSO-balloon instrument structure is shown in the figure~\ref{fig:globalview} and its main characteristics are given in the table~\ref{tab:properties}. Th is parallelepiped telescope78 presents a wide field of view of 12$^o \times $12$^o$ for a collecting surface of 1m$\times$1 m. It points to the nadir direction toward the atmosphere.77 The EUSO-balloon instrument structure is shown in the figure~\ref{fig:globalview} and its main characteristics are given in the table~\ref{tab:properties}. These parameters will be justified in the section~\ref{sec:Subsystems} devoted to the subsystems. This parallelepiped telescope 78 presents a wide field of view of 12$^o\times$12$^o$ for a collecting surface of 1.2 m$\times$1.2 m. It points to the nadir direction toward the earth. 79 79 It basically consists in an optical bench associated to an instrument booth placed at the focal position. 80 The optical bench comprises two lenses. The instrument booth includes the allelectronics inside a pressurised watertight box. One side of the instrument booth is provided by the third lens.80 The optical bench comprises two lenses. The instrument booth includes the whole electronics inside a pressurised watertight box. One side of the instrument booth is provided by the third lens. 81 81 \begin{figure} 82 82 \centering 83 \includegraphics[width=0.4\textwidth]{GlobalViewInstrument }83 \includegraphics[width=0.4\textwidth]{GlobalViewInstrument.jpg} 84 84 \caption{EUSO-Balloon Instrument Overview.} 85 85 \label{fig:globalview} 86 86 \end{figure} 87 The instrument includes an external roof-rack permitting the fixation of complementary instrument like an infra-red camera. 87 The instrument includes an external roof-rack permitting the fixation of complementary instrument like an infra-red camera for atmosphere monitoring. 88 88 89 89 90 \subsection{General characteristics and functions} 90 The main characteristics of the instrument are given in the table~\ref{tab:properties}. These parameters will be justified in the section~\ref{sec:Subsystems} devoted to the subsystems. 91 The optical subsystem includes the optical bench which have the purpose of focusing parallel light rays in a narrow focal point which is pixelized by 92 an array of photodetectors called MAPMTs (Multi-Anode Photomultiplier). The focal surface is instrumented by an electronics which has the properties of a very high sensitivity, in the UV range, fast measurement rate within the microsecond timescale, auto-triggering capability, event filtering and event recording. This electronics is capable to record on disk a burst of 128 consecutive sky pictures separated each-other by a time period of 2.5 $\mu$s called the GTU (Gate Time Unit, the basic time unit useful in cosmic rays detection in space). 93 \begin{table} 91 The optical subsystem includes the optical bench which have the purpose of focusing parallel light rays in a narrow focal point on a pixelized surface, consisting in an array of photodetectors called MAPMTs (Multi-Anode Photomultipliers). This focal surface is instrumented by an electronics which has the properties of a very high sensitivity in the UV range, fast measurement rate within the microsecond timescale, auto-triggering capability, event filtering and event recording. This electronics is capable to record on disk a burst of 128 consecutive sky pictures separated each-other by a Gate Time Unit (GTU) of 2.5 $\mu$s. 92 93 \begin{table}[h!] 94 94 \begin{center} 95 95 %{\tiny 96 96 \begin{tabular}{|c|c|}\hline 97 {\tiny Parameter name} & {\tiny values} \\ \hline 98 \multicolumn{2}{|c|}{{\tiny 1:General parameters} } \\ \hline 99 {\tiny Field of View } & {\tiny 12$^o \times$ 12$^o $ } \\ 100 {\tiny Aperture} & {\tiny 1 m$^2 \times$ 1 m$^2$} \\ 97 \multicolumn{2}{|c|}{{\tiny General parameters} } \\ \hline 98 {\tiny Field of View } & {\tiny 12$^o \times $12$^o $ } \\ 99 {\tiny Aperture} & {\tiny 1.2 m $\times$ 1.2 m} \\ 101 100 {\tiny Height} & {\tiny 2.66 m} \\ 102 {\tiny Width} & {\tiny 1.2 1 m} \\101 {\tiny Width} & {\tiny 1.24 m (without crash pads)} \\ 103 102 {\tiny Weight }& {\tiny 300 kg }\\ \hline 104 \multicolumn{2}{|c|}{{\tiny 2:Optics} } \\ \hline103 \multicolumn{2}{|c|}{{\tiny Optics} } \\ \hline 105 104 {\tiny Focal Length } & {\tiny 1.62 m} \\ 106 105 {\tiny Focal Point Spread (RMS)} & {\tiny 2.6 mm} \\ \hline 107 \multicolumn{2}{|c|}{ {\tiny 3:Focal Surface} } \\ \hline106 \multicolumn{2}{|c|}{ {\tiny Focal Surface} } \\ \hline 108 107 {\tiny Curvature Radius} & {\tiny 2.5 m} \\ 109 108 {\tiny Number of Pixels} & {\tiny 2304} \\ 110 {\tiny Pixel FOV} & {\tiny 0.25$^o \times$ 0.25$^o$} \\111 {\tiny Pixel size} & {\tiny 2.88 mm $\times$2.88 mm} \\109 {\tiny Pixel FOV} & {\tiny 0.25$^o \times$ 0.25$^o$} \\ 110 {\tiny Pixel size} & {\tiny 2.88 mm $\times$ 2.88 mm} \\ 112 111 {\tiny BG3 UV Filter transmittance} & {\tiny 98 \%} \\ 113 112 {\tiny Wavelength range} & {\tiny 290 nm - 430 nm} \\ 114 {\tiny Number of MAPMTs} & {\tiny 6 $\times$ 6} \\ \hline115 \multicolumn{2}{|c|}{{\tiny 4:PhotonDetection (MAPMTs)}} \\ \hline113 {\tiny Number of MAPMTs} & {\tiny 6 $\times$ 6} \\ \hline 114 \multicolumn{2}{|c|}{{\tiny PhotonDetection (MAPMTs)}} \\ \hline 116 115 {\tiny Number of channels} & {\tiny 64} \\ 117 116 {\tiny Photon detection efficiency} & {\tiny 35 \%} \\ … … 121 120 {\tiny Dynamic Range} & {\tiny 1 - 100 photons} \\ 122 121 {\tiny Maximum tube current} & {\tiny 100 $\mu$A} \\ \hline 123 \multicolumn{2}{|c|}{{\tiny 4:Signal Measurement (ASIC)}} \\ \hline122 \multicolumn{2}{|c|}{{\tiny Signal Measurement (ASIC)}} \\ \hline 124 123 {\tiny Sampling period (GTU)} & {\tiny 2.5 $\mu$s} \\ 125 124 {\tiny Photon Counting (64 ch), photoelectrons} & {\tiny 0.3 pe (50 fC) - 30 pe (5 pC)} \\ 126 125 {\tiny Charge to Time Conv (8 ch)} & {\tiny 2 pC (10 pe) - 200 pC (100 pe)} \\ 127 126 {\tiny Readout Clock} & {\tiny 40 MHz} \\ \hline 128 \multicolumn{2}{|c|}{ {\tiny 6:Triggers (FPGA, Virtex 6(L1) and Virtex 4(L2))} }\\ \hline127 \multicolumn{2}{|c|}{ {\tiny Triggers (FPGA, Virtex 6(L1) and Virtex 4(L2))} }\\ \hline 129 128 {\tiny L1 rate} & {\tiny 7 Hz (1-100 Hz)} \\ 130 129 {\tiny L2 rate} & {\tiny Max 50 Hz} \\ \hline 131 \multicolumn{2}{|c|}{ {\tiny 7:Event readout and DAQ (CPU, Clocks, GPS)}} \\ \hline130 \multicolumn{2}{|c|}{ {\tiny Event readout and DAQ (CPU, Clocks, GPS)}} \\ \hline 132 131 {\tiny Event size} & {\tiny 330 kB} \\ 133 132 {\tiny Data flow} & {\tiny 3.24 Mb/s} \\ 134 133 {\tiny Readout Clock} & {\tiny 40 MHz} \\ 135 134 {\tiny Event dating} & {\tiny at $\mu$s level} \\ \hline 136 \multicolumn{2}{|c|}{ {\tiny 8:Instrument Monitoring (microcontroler)}} \\ \hline137 \multicolumn{2}{|c|}{ {\tiny 9:On/Off capability, alarms, temperature and voltage control }}\\ \hline138 \multicolumn{2}{|c|}{{\tiny 10:Power supply}} \\ \hline135 \multicolumn{2}{|c|}{ {\tiny Instrument Monitoring (microcontroler)}} \\ \hline 136 \multicolumn{2}{|c|}{ {\tiny On/Off capability, alarms, temperature and voltage control }}\\ \hline 137 \multicolumn{2}{|c|}{{\tiny Power supply}} \\ \hline 139 138 {\tiny 60 batteries cells} & {\tiny 225 W during 24 hours, V: 28 V} \\ \hline 140 139 \end{tabular} … … 143 142 %\par} 144 143 \end{center} 145 146 144 \end{table} 147 145 148 149 \subsection{Instrument mechanics} 150 The mechanics of the instrument is made of Fibrelam panels, arranged together through Fibreglass sections. 151 The instrument will be coated by an insulating cover to protect the instrument component from fast temperature changes during balloon ascent and descent. 152 Special valves inserted in the optical bench are used to enable pressure equilibrium between indoor and outdoor. Wherever the after-flight fall location occurs, the instrument must be recovered with the smallest induced damages. 153 The bottom part is equipped with crash-pad which absorb brutal acceleration (up to 15G) at landing on ground. A baffle with special holes in the optical bench are used as a piston-effect to damp the shock for a fall over water. 154 The instrument booth which is a totally watertight sealed box, consists of a central aluminium plate on which the various electronic boxes are fixed. One of its side is the third lens. The opposite side is an aluminium radiator used to dissipate the heat generated by electronics equipment by radiation. 146 \subsection{Instrument mechanics and architectrure} 147 The mechanics of the instrument is made of Fibrelam\textregistered panels, arranged together through fibreglass sections. 148 The instrument will be coated by an insulating cover to protect the instrument's component from fast temperature changes during balloon ascent and descent. 149 Special watertight valves inserted in the optical bench are used to enable pressure equilibrium with the atmosphere. Wherever the after-flight landing location occurs, the instrument must be recovered with the smallest damages. 150 The bottom part is equipped with crash-pads which absorb brutal deceleration (up to 15 G) when landing on ground. A baffle with special holes in the optical bench are used as a piston-effect to damp the shock for a fall over water. 151 The instrument booth which is a totally watertight sealed box, consists of a central aluminium plate on which the various electronic boxes are fixed. One of its side is the third lens. The opposite one is an aluminium radiator used to dissipate the heat generated by electronics equipment. 155 152 The instrument is surrounded by buoys to avoid sinking if sea landing and to raise straight up the instrument booth above the water level. 156 153 \section{The instrument Subsystems} 157 154 \label{sec:Subsystems} 158 The instrument is broken down into subsystems defined to be the Optics, the Focal Surface, the Photo-detection with the MAPMT, the Signal measurement with the ASICs, the trigger readout with the PDMB and the CCB, The Data Acquisition System (DAQ) and the utilities like the monitoring also called the House-Keepting and the Power Supplies. Those subsystems are all described succinctly below.155 The instrument is broken down into subsystems defined to be the optics, the Focal Surface (FS), the Photo-detector with the MAPMT, the signal measurement with the ASICs, the trigger readout with the Photo-Detector Module Board (PDMB) and the Cluster Control Board (CCB). The Data Acquisition System (DAQ) and the utilities like the monitoring also called the House-Keepting (HK) and the power supplies. Those subsystems are all described succinctly below. 159 156 \subsection{Optics subsystem} 160 The Optics subsystem involves the three lenses.157 The optics subsystem involves the three lenses. 161 158 Its goal is to provide the best focalisation for the smallest focal distance. The focalisation requirement is constrained by the pixel size of the photo detection system. 162 Due to the wide angular field of view, it is necessary to combine 3 flat lenses of which the two external are of focusing Fresnel type for one of their side and the middle lens is purely dispersive to correct forchromatic aberrations. These lenses are manufactured in PMMA material~\cite{bib:Optics}. The ray tracing calculations including the temperature profile expected for flights in cold and warm cases provide a focal length of 1.62 m and a focal point spread width of the order of 2.6 mm, smaller than the pixel size.159 Due to the wide angular field of view, it is necessary to combine 3 flat lenses. External ones are focusing Fresnel type on a side and the middle lens is purely dispersive to correct chromatic aberrations. These lenses are manufactured in PMMA material~\cite{bib:Optics}. The ray tracing calculations including the temperature profile expected for flights in cold and warm cases provide a focal length of 1.62 m and a focal point spread width of the order of 2.6 mm, smaller than the pixel size. 163 160 164 161 \subsection{Front-End Electronics} 165 The Focal Surface is constituted by an array of photodetectors called the MAPMTs (Multi-Anode Photomultipliers), which anode signals are measured and digitised by ASICs, themselves are readout by FPGA to run the trigger algorithm. This Focal Surface is arranged into a so-called Photo-Detector module (PDM) which design and effective realisation is described in details in~\cite{bib:FrontEndEl}. We review here the main properties of this electronics~: 166 \paragraph{Focal Surface} The focal Surface is a slightly curved surface, similarly to that of the JEM-EUSO central PDM, being an array of 48$\times 48$ pixels of 2.88mm$\times$2.88mm size exceeding slightly the focal point spread. This granularity fits perfectly the accuracy requirements to make the image the longitudinal profile of Air-shower above $10^{18}$eV. Practically, the Focal Surface of the PDM is broken up into 9 sets of identical Elementary cells (EC), which are matrixes of 2$\times$2 MAPMTs. Inside the PDM structure, the 9 EC are disposed and tilted according the appropriate shape required for the Focal Surface.167 \paragraph{MAPMTs} They are photon detectors consisting of a matrix of 8$\times 8$ pixels. Each pixel is associated to an output channel generating a charge or a current called an anode. Their sensitivity is as low as a few tens of photoelectrons and their dynamic range can extend up to few 100 photoelectrons per $\mu$s when working at high gain $10^6$.168 This high gain is achieved through 14 dynodes polarised by High Voltage Power Supplies (HVPS) for which the photocathode is set at -900 V. Limited power consumption is obtained with a Crockoft-Walton (CW) high voltages supplier. Dynamic range can be extended up to 10$^6$ photonsif the gain is reduced automatically gradually from 10$^6$ to 10$^4$, 10$^2$ or 30 by fast switches (SW) reacting to the micro-second timescale in case of large current flow is detected in the anodes. In the PDM, there is 9 independent HVPS controlling the 9 ECs.162 MAPMTs constituting the FS, provide anode signals measured and digitised by ASICs, themselves readout by FPGA to run the trigger algorithm. The FS is arranged into a so-called Photo-Detector Module (PDM) whose design and effective realisation is described in details in~\cite{bib:FrontEndEl}. We review in the following the main properties of this electronics. 163 \paragraph{Focal Surface} The focal Surface is a slightly curved surface, similarly to that of the JEM-EUSO central PDM, being an array of 48$\times$48 pixels of 2.88 mm $\times$ 2.88 mm size exceeding slightly the focal point spread. This granularity fits perfectly the accuracy requirements to make the longitudinal profile image of Air-showers above $10^{18}$ eV. Practically, the focal surface of the PDM is broken up into a set of 9 identical Elementary Cells (ECs), which are matrixes of 2$\times$2 MAPMTs. Inside the PDM structure, the 9 ECs are disposed and tilted according to the appropriate shape required for the FS. 164 \paragraph{MAPMTs} They are photon detectors consisting of a matrix of 8$\times$8 pixels. Each pixel is associated to an anode generating a charge or a current in output. Their sensitivity is as low as a few tens of photoelectrons and their dynamic range can extend up to few 100 photoelectrons per $\mu$s when working at high gain ($10^6$). 165 \textbf{This high gain is achieved through 14 dynodes (not 12??) polarised by High Voltage Power Supplies (HVPS) for which the photocathode is set at -900 V. Limited power consumption is obtained with a Crockoft-Walton (CW) high voltages supplier. Dynamic range can be extended up to 10$^6$ photons (??) if the gain is reduced automatically gradually from 10$^6$ to 10$^4$, 10$^2$ or 30 by fast switches (SW) reacting to the micro-second timescale in case of large current flow is detected in the anodes. In the PDM, there is 9 independent HVPS controlling the 9 ECs. 169 166 Because a large photon flux generating anode current above 100$\mu$A would destroy the tube, an automatic control system reducing the gain or switching off the MAPMT is mandatory to guaranty the tube survival. 170 Practically this switching decision logic is implemented in a FPGA reading out the ASICs. 171 \paragraph{ASICs} 36 ASICs of the type SPACIROC~\cite{bib:ASIC}are used to perform the anode signals measurement and digitisation of the 36 MAPMTs. These ASICs have 64 channels. Their analog inputs are DC-coupled to the MAPMT anodes. They process the 64 analog signals in parallel in two modes : 1) in photoelectron counting mode, in a range from 1/3 of photoelectrons up to 100 photoelectrons, by discriminating over a programmed threshold each of the channels, 2) by estimating the charge from 20~pC to 200~pC, by time over threshold determination for exclusive groups of 8 anodes current sums. The 64 analog channels are balanced each-other relatively by gain matching over 8-bits.167 Practically this switching decision logic is implemented in a FPGA reading out the ASICs.} 168 \paragraph{ASICs} 36 SPACIROC~\cite{bib:ASIC} type ASICs are used to perform the anode signals measurement and digitisation of the 36 MAPMTs. These ASICs have 64 channels. Their analog inputs are DC-coupled to the MAPMT anodes. They process the 64 analog signals in parallel in two modes : 1) in photoelectron counting mode, in a range from 1/3 of photoelectrons up to 100 photoelectrons, by discriminating over a programmed threshold each of the channels, 2) by estimating the charge from 20~pC to 200~pC, by time over threshold determination for exclusive groups of 8 anodes current sums. The 64 analog channels are balanced each-other relatively by gain matching over 8-bits. 172 169 The discrimination voltage level used in the photo-counting is provided by a 10-bit DAC (Digital to Amplitude converter). 173 In both cases the digitisation is performed by 8-bits counters every GTU. There is no data buffering on the ASIC. The data are transferred to the later stage, aFPGA each GTU under the sequencing of a 40MHz clock.174 \paragraph{Trigger} The Instrument includes two trigger stages. The level 1 trigger (L1) implemented in the FPGA of a PDM-Board (PDMB), belonging to the Front-End Electronics. The PDMB readouts the data from the 36 ASICs from a PDM each GTU to compute the trigger L1. It principle consists in searching an excess of signals over background in groups of 3$\times$3 pixels, with enough time-persistence, which signal sum over time exceed a preset value. The background rate seen by pixel is monitored continuously to adjust in real-time the trigger threshold which are adjusted such the L1 rate is kept a a fixed level of a few Hz compatible with the DAQ readout rate. The trigger is evaluated each GTU. Because Air-Showermay extend over 100 GTU, this trigger has the buffering capability of 128 consecutive GTU.170 In both cases the digitisation is performed by 8-bits counters every GTU. There is no data buffering on the ASIC. The data are transferred to the FPGA each GTU under the sequencing of a 40MHz clock. 171 \paragraph{Trigger} The Instrument includes two trigger stages. The level 1 trigger (L1) implemented in the FPGA of a PDM-Board (PDMB), belonging to the Front-End Electronics. The PDMB readouts the data from the 36 ASICs from a PDM each GTU to compute the trigger L1. Its principle consists in counting an excess of signals over background in groups of 3$\times$3 pixels over a preseted time value. The background rate seen by pixel is monitored continuously to adjust in real-time the trigger threshold which is adjusted such as the L1 rate is kept at a fixed level of a few Hz compatible with the DAQ readout rate. The trigger is evaluated each GTU. Because Air-Showers may extend over 100 GTU, this trigger has the buffering capability of 128 consecutive GTU. 175 172 To reduced the dead-time induced by event readout, the event buffer is doubled. 176 173 \subsection{Data acquisition} 177 174 The data acquisition system is part of the computing system DP (Data Processing). 178 It comprises the CCB designed to produce the second level trigger L2, which is described in~\cite{bib:CCB}. For each generated L1 trigger, the CCB read the data corresponding to the 128 consecutive GTU from the PDMB buffer. In JEM-EUSO, the CCB is devoted to the combination of 9-PDMB triggers and to reduce the resulting combined trigger rate to about a few Hz or less compatible with the data storage capabilities of the DAQ. The triggering role of the CCB in EUSO-Balloon is marginal as there is only one PDM. However it has the task to read the whole event from the Front-End and to pass it to the CPU. The L2 decision is propagated to the Clock-Board (CLK-B, based on a Xilinks Virtex5 FPGA) generating all the clocks used by the electronics, itself associated with a GPS-Board (GPSB) to provide the event time tagging data with an accuracy of a few microseconds.175 It comprises the CCB designed to produce the second level trigger L2, which is described in~\cite{bib:CCB}. For each generated L1 trigger, the CCB reads the data corresponding to the 128 consecutive GTU from the PDMB buffer. In JEM-EUSO, the CCB is devoted to the combination of 9-PDMB triggers and to reduce the resulting combined trigger rate to about a few Hz or less compatible with the data storage capabilities of the DAQ. The triggering role of the CCB in EUSO-Balloon is marginal as there is only one PDM. However it has the task to read the whole event from the Front-End and to pass it to the CPU. The L2 decision is propagated to the Clock-Board (CLK-B, based on a Xilinks Virtex5 FPGA) generating all the clocks used by the electronics, itself associated with a GPS-Board (GPSB) to provide the event time tagging data with an accuracy of a few microseconds. 179 176 The CPU (Motherboard iTX-i2705 model, processor Atom N270 1.6 GHz) merges the event data with the time tagging data to build an event of a size of 330 kB, leading to a data flow of 3MB/s for a 10 Hz L1-L2 trigger. The CPU write all the data on disks (1 TB CZ Octane SATA II 2.5Ó SSD) and may also send to telemetry a subset of flagged events by CCB for event monitoring. 180 177 \subsection{Monitoring} … … 187 184 After fabrication, the subsystems directly related to the physics measurements need to be calibrated in an absolute way. 188 185 The goal of the absolute calibration is to relate a measured digitised signal into the true number of photons impinging on the Focal Surface or on the first lens. 189 Thus the Optics and the photo-detection done by the MAPMTs arewill be calibrated.186 Thus the Optics and the photo-detection done by the MAPMTs will be calibrated. 190 187 Other subsystems like the trigger has to be tested once the instrument is close to final assembly. 191 188 Each of the subsystems of the instrument are calibrated if necessary and tested before the full integration. Then the assembled instrument is then tested entirely. … … 195 192 196 193 \subsection{Measuring the MAPMT performances} 197 Each channel of the MAPMT is characterised by its photodetection efficiency (product of the photocathode quantum efficiency and the collection efficiency) and by the gain of the phototubes. This measurement is firstly done before their mounting inside EC-Units (see~\cite{bib: PMT}) and also after the EC-Units assembly.198 This measur ement is done by illuminating by a LED (controlled by a NIST) the photocathode in single photoelectron mode~\cite{bib:Calib} to measure the single photoelectron spectrum for each of the 2304 pixels of the instrument camera.199 This procedure allows to determine the exact high voltage to apply to each of the MAPMT photocathodes for each EC-Units.194 Each channel of the MAPMT is characterised by its photodetection efficiency (product of the photocathode quantum efficiency and the collection efficiency) and by the gain of the phototubes. This efficiency is firstly measured before the mounting of MAPMTs inside EC-Units (see~\cite{bib: PMT}) and also after the EC-Units assembly. \textbf{to be reformulated} 195 This measurment is done by illuminating by a LED (controlled by a NIST) the photocathode in single photoelectron mode~\cite{bib:Calib} to measure the single photoelectron spectrum for each of the 2304 pixels of the instrument camera. 196 This procedure allows to determine the exact high voltage to apply to each MAPMTs photocathodes. 200 197 \subsection{The ASIC settings} 201 The ASICs measure the single photoelectron spectr umsat nominal high voltage for each of the channels by performing S-curve (by performing series of runs by ramping the discriminator voltage).198 The ASICs measure the single photoelectron spectra at nominal high voltage for each of the channels by performing S-curve (by performing series of runs by ramping the discriminator voltage). 202 199 Because the relative gain of the channels inside an EC-Unit differs slightly from one-another, the ASICs allow balancing the discrepancies between the channels. This done once the PDM is mounted and each MAPMT is associated to an ASIC. Then the nominal discriminator threshold at 1/3 of a photoelectron to apply to each ASIC is established. 203 200 … … 212 209 \section{Operation and Analysis} 213 210 \label{sec:Operation} 214 During the balloon flight operation, the instrument will be controlled from ground by an operator using a control program~\cite{bib:OffOnLineAna} interfaced to the TC/TM system (Telecom and and Telemetry) NOSYCA of CNES.211 During the balloon flight operation, the instrument will be controlled from ground by an operator using a control program~\cite{bib:OffOnLineAna} interfaced to the TC/TM system (Telecommand and Telemetry) NOSYCA of CNES. 215 212 At a given altitude reached by the ballon, a command will be issued to turn on the instrument. The HK system will turn on one by one each of the subsystems while the monitoring parameter will be downloaded at ground. 216 When every parameters looks perfect, the Balloon operator can launch the DAQ program running on the CPU. He will control basic run parameters, namely the background rate calculated by the PDMB. Conventionally the thresholds auto-adapt to the required L1-L2 rates unless the operator forces another mode of trigger settings. At any moment, the operator can shut down the instrument. This will be done when the balloon descent will be activated.213 When every parameters looks perfect, the balloon operator can launch the DAQ program running on the CPU. He will control basic run parameters, namely the background rate calculated by the PDMB. Conventionally the thresholds auto-adapt to the required L1-L2 rates unless the operator forces another mode of trigger settings. At any moment, the operator can shut down the instrument. This will be done when the balloon descent will be activated. 217 214 218 215
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