User:CsesLimadou/sandbox

CSES (China Seismo-Electromagnetic Satellite) is a multi-disciplinary scientific mission led by the Chinese and Italian Space Agency (ASI) and the China Earthquake Administration (CEA), and developed by a Chinese-Italian collaboration including the Italian National Institute for Nuclear Physics (INFN) and several Chinese and Italian Universities and research Institutes.

Italy participates to the CSES mission with the Limadou project, funded by the Italian Space Agency (ASI) and the National Institute for Nuclear Physics (INFN).

The LIMADOU Collaboration has designed, built and tested the High Energy Particle Detector (HEPD) and it has collaborated in developing and testing the Electronic Field Detector (EFD) in the INAF-IAPS plasma chamber in Rome, and participates in analyzing data of all payloads of the CSES mission.

The HEPD is a range-calorimeter designed to detect at LEO orbit electron fluxes (3-100 MeV), proton fluxes (30-300 MeV) and light nuclei. The instruments will allow to study short time scale variability and precipitation of inner Van Allen belt particles, the solar-terrestrial environment, Coronal Mass Ejections (CMEs), Solar Energetic Particle (SEP) events and low-energy cosmic rays.

The CSES satellite launch has been launched on February 2, 2018 from the Jiuquan Satellite Launch Center in the Gobi desert (Inner Mongolia).

HEPD Design
The detector, designed to detect electrons in the energy range between 3 and 100 MeV, protons between 30 and 200 MeV and light nuclei, is made up of several subdetectors:

- a silicon detector to provide the direction and the energy loss of the incident particle. It consists of two double-side silicon microstrip sensor planes, placed on the top of the HEPD, with total dimension of 213 x 213 x 0.3 mm3, distant z=10 mm and resolution of 50 micron. Each layer is made of 3 ladders, each one composed by 2 modules.

- a plane, placed 10 mm below the silicon detector, and made of plastic scintillators segmented into 6 paddles (200 x 30 x 5 mm3 each) along the y direction. Each paddle is read out by a photomultiplier tube (PMT) on each side;

- a range-calorimeter, divided into two sections. Its upper part is a tower made of plastic scintillator planes (150 x 150 x 10 mm3) read out by two PMTs, one for each side. The lower part of the calorimeter is made of a 3 x 3 inorganic scintillator (LYSO) matrix. Each LYSO crystal has dimensions 48 x 48 x 40 mm3, and is read out by a PMT located on the bottom face;

- a veto system, consisting of 5 plastic scintillator counters, four lateral and one at the bottom of the instrument.

The Electronics Subsystem consists of boards for trigger, data acquisition, CPU, Power Control and Low Voltage and High Voltage Power Supply.

HEPD Models
Following the standard space procedures, four HEPD models were produced and fully integrated.

- The Electrical Model (EM), developed to validate the payload functio-nal performance and verify the communications with the satellite.

- The Structural and Thermal Model (STM), produced to validate the structural and mechanical design and the satellite thermal control system.

- The Qualification Model (QM), used to qualify all the subsystems for spacecraft en-vironment, calibrate the instrument and assess the compliance with space requirements.

- The Flight Model (FM), built to be flown onboard the CSES satellite.