PoS(ICRC2019)135 http://pos.sissa.it/ † ∗ [email protected] Speaker. for collaboration list see PoS(ICRC2019)1177 In this paper we willveloped present for a the China description Seismo of ElectromagneticCSES the Satellite is High (CSES) a Energy project. Particle scientific Detector missionturbations (HEPD-02) dedicated of de- to atmosphere monitoring and electromagnetic,and inner plasma to and Van the Allen particles study belts per- of caused the30 by low - energy 200 solar component MeV and of for terrestrial the protons). The cosmic phenomena, first rays satellite, (3 launched - in 100 2018,the MeV hosted Italian for several "Limadou" electrons instruments collaboration, and onboard. is Theas the HEPD-01, instrument well built devoted by as to separate lightof electrons nuclei double-sided and in protons, silicon the microstripsegmented detectors MeV plastic which energy scintillator give for window. trigger the and direction The aThe of calorimeter. CSES-02 detector satellite the is is incident planned composed particle, toforesees of be a improvements launched two both by planes the on end the ofnew tracker 2021. system and with The the crossed next calorimeter. layers generation of HEPD Todesigned. 2 improve mm A trigger new thick efficiency tracker segmented study a counters is read ongoing:ALICE by 3 experiment light-guides planes at has of LHC. been ALPIDE CMOS pixel chips, developed for † ∗ Copyright owned by the author(s) under the terms of the Creative Commons c Attribution-NonCommercial-NoDerivatives 4.0 International License (CC BY-NC-ND 4.0). 36th International Cosmic Ray Conference -ICRC2019- July 24th - August 1st, 2019 Madison, WI, U.S.A. Giuseppe Osteria Istituto Nazionale di Fisica Nucleare - Sezione di Napoli,for Italy the CSES-Limadou Collaboration Valentina Scotti Università degli Studi di Napoli FedericoNazionale II, di Dipartimento Fisica di Nucleare Fisica, - Napoli, Sezione ItalyE-mail: di and Napoli, Istituto Italy The High Energy Particle Detector onboardsatellite CSES-02 PoS(ICRC2019)135 Valentina Scotti . ◦ with respect to the first satellite, in 65 ◦ ± 1 shows the simulated tracking of the orbit of the two satellites. 1 inclination and 500 km altitude. In order to perform a comprehensive study of ionospheric ◦ All the instruments onboard CSES-02 will work along the whole orbit. Every payload will The High Energy Particle Detector will study low energy Cosmic Rays in the energy range 3 - CSES (China Seismo-Electromagnetic Satellite) is a scientific mission dedicated to monitoring The CSES mission is part of a collaboration program between the China National Space Ad- CSES program aims at building a space monitoring system to investigate the topside iono- CSES program foresees the realization of a constellation of satellites. The first satellite of the One of the instruments on-board is the High Energy Particle Detector (HEPD-01), built by The CSES-02 satellite is planned to be launched by the end of 2021. It will be placed on collect data in two operating modes:when "burst the mode" satellite and "survey passes mode". over the Theactivities burst whole in mode China is territory the activated and world, thegeneration while regions HEPD, with over the built all strongest upon seismic the theof other experience the areas, of system, HEPD-01, the with foresees surveyfollowing. substantial improvements mode changes to will on some part be parts of used. the apparatus, The which next will be2. described HEPD-02 in the 300 MeV. For each particle, the HEPD instrumentsmeasure can the identify the energy type and (proton, the electron,from nucleus), pitch the angle. Van Allen HEPD-02 belts canThe and therefore determine detect high-inclination the flows orbit of magnetospheric allows particles regionrevolution: the coming of galactic origin HEPD-02 cosmic with to rays, great detect particles accuracy. trapped particles in of the different magnetosphere, nature and during also solar its energetic electromagnetic, plasma and particles perturbations ofand the atmosphere, Van ionosphere, Allen magnetosphere belts inducedcorrelations with by the natural occurrence of sources seismic and events. anthropocentric emitters andministration to (CNSA) and study the Italian their Space Agencyquake (ASI). The Administration project (CEA) is developed and by Italian Chinawith Earth- National several Chinese Institute and for Italian Universities Nuclear and Physics research (INFN), Institutes. together sphere with the most advancedwide techniques data and of equipment, the and near-Earth designed electromagneticvations in environment. sharing order The service to observations for gather will international provide world- cooperation an and obser- the scientific community. constellation, CSES-01, was launched inwith 2018, 98 and inserted into a circular Sun-syncronous orbit The HEPD onboard CSES-02 1. Introduction phenomena, the mission takes advantage ofAll a the multi-instrument payloads payload are comprising working nine at detectors. latitude comprised between the Italian "Limadou" Collaboration. Theelectrons main in task the of energy this rangewell high-precision between as instrument 3 light is and nuclei to in 100 the detect MeV, and MeV energy protons window. between 30 andthe 200 same MeV, orbital as plane of CSES-01, with a phase shift of 180 order to optimize the timingresolution. between two Fig. passages over the same site, and to reduce the temporal PoS(ICRC2019)135 phase ◦ Valentina Scotti 3 MeV 5 MeV > > ◦ with E +35 ◦ ◦ 45 W 45 kg ). A tracker is located on the top of the 6 years 2 10% with E 10 < < 100 Gb/day > < < < Protons: 30-200 MeV 2 HEPD-02 main technical characteristics. Mass Pointing Zenith Table 1: Life cycle Parameter Value Data budget Energy Range Electrons: 3-100 MeV Energy resolution Electrons: Angular resolution Electrons: Power Consumption Operative temperature -10 Simulation of the orbital tracking of CSES-01 and CSES-02. The figure shows the 180 The HEPD is composed of several detectors (see Fig. . instrument in order to limit the effectJust of Coulomb below, a multiple plane scattering on made the of direction two measurement. crossed layers of plastic scintillators gives the trigger; this plane is 1 Figure 1: shift between the two orbits. particles associated with transient phenomena suchachieve the as best Solar result Flares it or is Coronaland necessary Mass power to budgets Ejections. maximize constraints. To the Some geometrical of acceptance the main according parameters to of weight HEPD-02 are summarized in table The HEPD onboard CSES-02 PoS(ICRC2019)135 ), 3 3 matrix × , see Fig. 3 Valentina Scotti 12 mm ]. Respect to HEPD- × 4 38 × m. The control and read-out of the sensor is based 3 µ The architecture of the HEPD-02 onboard CSES-02 satellite. 512 square pixels of 28 × m) flexible printed circuits on which the sensors are glued and electrically µ Figure 2: the high trigger rate atpre-scaling; polar regions requires an improved trigger logic and thethe necessity larger of amount of acquired data requires an increased databoth budget; those conditions demand for improved operating modes. As was previously mentioned, the HEPD-02 onboard CSES-02 will be operational along all The design of the HEPD-02 will have a numberThe of development of improvements the with tracker minor of HEPD-02 changes is with ongoing, the new solution is based on 3 planes The tracker is composed of five independent tracking modules (225 • • • on ultra-thin (170 consisting each of three sensitive planes. Theeach sensitive containing area 1024 of every layer is made up of 10 sensors, the orbit, this situation sets additional and more stringent demands on the design: 3. The instrument respect to the first design (identical box dimensions, mechanical interfaces and budgets). of ALPIDE CMOS pixel chips, developed for ALICE experiment at LHC [ followed by a calorimeter, constituted byof a an tower inorganic of scintillator plastic LYSO. The scintillators, calorimeter followedplanes. volume by is a surrounded 3 by plastic scintillator veto 01, this technology reduces systematic uncertainties on6 tracking times giving better a and single-hit do resolution not up suffer to from multi-hit degeneracy. The HEPD onboard CSES-02 PoS(ICRC2019)135 Valentina Scotti 3 blocks; each ). Each plane is × 4 each excluding mechanics). Each counter 3 and consists of a matrix of 3 3 4 3 mm 3 matrix of inorganic LYSO crystals on the bot- × × 30 40 mm × × The layout of the trigger plane. 150 × Figure 4: The layout of the tracking module of the tracker of HEPD-02. (excluding mechanics). It is read out by two PMTs (Hamamatsu R9880-210) 3 Figure 3: 10 mm × 150 The calorimeter measures the energy of the incoming particles which are contained in it. It The LYSO plane measures 150 To cope with the increased fluxes rates of polar orbits, a trigger system with two crossed layers × block is covered by reflective coating and read out by PMT (Hamamatsu R9880-210) located on consists of 12 scintillator planes and of a 3 located on opposite corners. tom of the tower.150 Each plastic scintillator plane is covered with reflective coating and measures segmented in 5 counters (dimensions 200 of 3 mm thick scintillator planes read by light-guides has been designed (see Fig. connected. The modules are mechanicallyexternal supported frame. by a layer of reinforced carbon-fiber and an The HEPD onboard CSES-02 is covered with reflective coatingR9880-210), one and on each read side. out The signals bywith coming one light-guides from or the more connected segmented signal trigger to coming layer, from in PMTssignal. different coincidence planes (Hamamatsu of The the calorimeter, new provides trigger thetrigger HEPD will to trigger the allow whole a instrument, the fine-tuning triggerparticle, of layer improving measures the the electron-proton the discrimination. trigger loss of The efficiency. energy x-ytracking per segmentation of Besides also unit the complements length providing the incoming of the each particles and helps validating the tracking from the ALPIDE modules. PoS(ICRC2019)135 Valentina Scotti C). The trigger rate and the data ◦ C to +85 ◦ 5 tracker detector; scintillator detectors (trigger, energy and veto detectors); global control and data managing. With regard to front-end electronics, the handling of the signals coming from the PMTs has The global control and data managing system has been updated: the previous architecture, The HEPD-02 onboard CSES-02 satellite has been designed to improveA the new performances trigger system of has been designed, along with a calorimeter and veto shielding upgrade. The veto consists of five plastic scintillator planes (four lateral and one at the bottom of the The HEPD-02 is contained in an aluminum box with a base plate linked to the satellite cabin Most of the improvements of HEPD-02 compared to HEPD-01 concern electronics. All the The electronics system can be schematized into three blocks: • • • been optimized. In addition, theger, board as responsible well for as generating for and PMTin distributing signals order the processing to system and improve acquisition, trig- the has management beenASIC of redesigned. has PMT been In signals substituted the and with new the board, the generation CITIROC of chip, triggers, both the by EASIROC Weeroc. based on an ADSP2189 andXilinx an SoC. ACTEL The FPGA design Flashpro3, of will theimproved. be two replaced high with and a low board voltage based power supply on has also been reviewed4. and Conclusions the detector which is onboard the first satellite. In addition, a new tracking system basedALICE on experiment 3 at planes LHC, of will ALPIDE be CMOS used pixel for chips, the developed for first time in space. Each module has its own dedicated mechanicsheat that allows dissipation. anchoring Each to detector the HEPD-02 block base includestion plate power processing and chain chain. for The bias main distribution powerand and supply a provides the data the high acquisi- low voltages bias tocarried the voltages out detector for by electronics means PMTs. of the SPACEWIRE The LITE protocol. communications between the various subsystems is instrument), each covered with reflective coating210) and located read on out opposite by corners. twocontained The PMTs in veto (Hamamatsu the system detector. R9880- The allows selection to can select be particles applied whose both signal during isspace the acquisition fully which and allows offline. to dissipatequalification heat and flight by model. contact. Two models of the3.1 instrument The will electronics be realized: electronics of the HEPD-02 is designed withnents embedded will "Hot/Cold" be redundancy selected and capable all the the compo- industrial range (-40 The HEPD onboard CSES-02 the bottom face. stored have to be compliant with theper maximum day. data transfer rate from the satellite, which is 50 GB PoS(ICRC2019)135 Valentina Scotti 6 The CSES-02 satellite is planned to be launched in less than 3 years and all the instruments on This work was supported by the Italian Space Agency in the framework of the “Accordo At- on the ALPIDE sensor", ICRC2019 experiment", Nuclear and Particle Physics Proceedings,https://doi.org/10.1016/j.nuclphysbps.2017.06.024 291-293: 118-121 Energy Particle Detector on board the CSES satellite", ApJ Supplement, vol. 243, 2019 seismo-associated perturbations of the Van Allen643–652, belts", May, Sci. 2018, China DOI: Technol. https://doi.org/10.1007/s11431-018-9234-9 Sci., vol. 61, no. 5, pp. [4] R. Iuppa, "First use of CMOS Monolithic Active Pixel Sensors in space: the tracker of HEPD-02 based [3] V. Scotti, G. Osteria, for the CSES-Limadou Collaboration, "The electronics of the HEPD of the CSES [2] P. Picozza et al., (CSES-Limadou collaboration), "Scientific goals and in-orbit performance of the High board will be full time operational. Acknowledgment tuativo n. 2016-16-H0 Progetto Limadou Fase E/Scienza” (CUP F12F1600011005). References [1] G. Ambrosi et al., "The HEPD particle detector of the CSES satellite mission forinvestig ating The HEPD onboard CSES-02