Design Of High-energy Particle Detector Data Acquisition And Control System

Earth electromagnetic anomaly and the coupling mechanism research of the earth space radiation has begun at the early century of twentieth, the first earth electromagnetic satellite in the world, DEMETER, which mounted a high-energy particle detector that can detect the charge particle energy range from 0.8Me V to2.5Me V. It captured lots of abnormal phenomena of ionosphere high-energy charge particles that lined with artificial source of VLF, extreme disasters weather and other factors. The high-energy payload of high energy particle detector onboard the China Seismic Electromagnetic Satellite(CSES), expand to the range of charge particle energy measurement, add to the identification of particle species and the angle measurement of the incident particle. The high energy electron measurable energy range extended to 0.1Me V to 50 Me V, and the high energy proton can be measured in the range of 2Me V to 200 Me V as well. It has great significance for further exploration the correlation between near-Earth space electromagnetic anomalies and the burst of energetic particles.The research of the thesis is about the detector's data acquisition control system based on high-energy payload of the high energy particle detector, which contains the design of the high energy particle detector system solution, the signal measurement technology of the detector, the design of data acquisition control system and also the software system, the system test and beam experiments.Firstly, this paper describes the background and significance of the subject and introduce the actuality of domestic and oversea research, figures out the association between earthquake and spatial particle flux changes. Based on my space program experience in the Institute of High Energy Physics internship stage, a brief introduction to the subject of high-energy particle detector data acquisition control system is made, and the main content and basic framework of this paper are summarized as well.Secondly, the high energy particle detector particle identification, angle measurement, energy measurement is discussed in detail, the existing types of detectors are compared too, and the high-energy particle detector unit design principles and CSES payload composition are come up, as well as high-energy particle detector technical indicators. In addition, the internal structure of the composition and the readout electronics system of the detector, and the basic principle for high energy particle detector, and the principle for energy regions division are introduced in detail.Then, this thesis analyze the unit circuit design of high energy particle detector,which contains the design of front-end electronics circuit and data acquisition control unit circuit of the detector. Then we expand the software design of data acquisition control system, introduced the software module design which based on FPGA and MCU respectively. Considering the particularity software environment on satellite, the corresponding software reliability design has to be taken into account.Finally, the basic performance of the high-energy data acquisition control system is tested, and the beam experiment has been conducted on payload systems. The data acquisition control system achieve all the technical requirements, such as species identification of charged particles, angle reconstruction and energy measurement of the incident particle. It has been proved to work effectively and reasonably by experiment. Besides, power consumption has been tested, system function has been verified too, and the detection performance and detection efficiency has been summarized at last.whole thesis point out that high-energy payload of high energy particle detector achieve all the technical indicators with expectations, and focus on the insufficient at the original stage, follow the aerospace reliability design requirements, make prospect of developing on flight model phase stage.* Note: particle energy Me V energy in Joules Me V and the SI System(J) conversion relationship is 1 Me V = 1.602176565(35) × 10-16 J.