Possibility of unification of requirements for radiation resistance for spacecraft with different operating conditions

During the period of active lifetime in different types of orbits, spacecraft are exposed to various factors of outer space. The main factor influencing the performance of electronic equipment is the ionizing radiation of outer space. The main effect associated with the impact of the ionizing radiation of outer space on the spacecraft (dose effects), in its physics, is determined by the radiation dose absorbed in the components of the electronic component base and construction materials during the entire lifetime. This effect explains the failures in the operation of radio-electronic equipment due to the degradation of the parameters used in the products of the electronic component base and materials. Calculation of levels of exposure to absorbed doses depending on various parameters of the orbit is a necessary and important task for ensuring the functioning of the spacecraft during a given lifetime, since calculations of radiation resistance are based on the levels of exposure in orbit. The key, from the point of view of minimizing mass protection and the scope of testing of critical electronic component base products, is to carry out calculations taking into account the design features of the spacecraft and on-board equipment. In addition to taking into account the design of the spacecraft and the spacecraft, an important aspect when calculating the radiation resistance is taking into account the relative position of the spacecraft in the spacecraft. This article considers the possibility of unifying the requirements for radiation resistance for spacecraft with different operating orbits and lifetime, as well as the possibility of carrying out a unified calculation without taking into account the design features of the spacecraft, spacecraft and relative position within the spacecraft.