Leoda uzay aracı için uzay radyasyon monitörünün tasarımı ve ilk Türk sonda roketinde bir prototip uçuşunun sonuçları

Radiation damage to spacecraft is a major reason for malfunctions in electronic components. Monitoring real-time radiation that the spacecraft is exposed to is of utmost importance for subsequent investigation of faults and their correlation to radiation doses. Components which have completed mission lifetime successfully in space and therefore have gained heritage can be certified to a certain level of radiation tolerance for future missions. The design and optimization of a space radiation monitor was carried out as part of the IMECE project. The monitor consists of a proton radiation detector with heavy ion measurement capabilities, in a kinetic energy range of 2 MeV to 200 MeV, in addition to an electron radiation monitor with a kinetic energy range from 100 keV to 7 MeV. Both are optimized to record hits in 8 energy bins and the electron one to record fluxes higher than those of protons by a factor of 10^3 for LEO flights. Utilization of degraders and silicon detectors in sandwich form is essential to the working principal of the designed proton detector. Suitable readout electronics for these fluxes and flight qualification tests were chosen. This multipurpose radiation monitor will be manufactured and tested at the METU-DBL facility upon its completion. A protype for this radiation monitor was produced and flown to an altitude of 136 km twice on top the SR0.1 rocket launched by Roketsan on the 26th -29th of October 2020. Dose rates were measured at the Pfotzer-Regener maximum as well as all through the flight path and are presented in this thesis.