MODEL OF AN OPTICAL-ELECTRONIC SYSTEM FOR ORIENTIATION SMALL SATELLITES TO THE EARTH AND ENERGY CALCULATION OF ITS PHOTO RECEIVER

Abstract

The presented article analyzes the functionality of optical-electronic orientation and stabilization systems, examines the schemes for using these systems on satellites, and also develops a model of an optical-electronic system that ensures the orientation of small satellites to the Earth. The functional limitations inherent in existing orientation and stabilization systems are analyzed, and
various characteristics of optical-electronic orientation, stabilization and navigation devices used in spacecraft (SC) are considered. At the same time, it was shown that the complexity and design features of astronomical positioning systems significantly complicate their use on small satellites. As a result of studies and reports, it has been established that the use of microbolometer matrices (MBMs) developed in recent years and photodetectors created on their basis that do not require cooling make it possible to develop a new type of optical-electronic systems. As a result, of the research, a structural model of a compact, autonomous and high-precision optical-electronic alignment system has been proposed, which can be applied to small satellites based on an uncooled MBM photodetector that provides orientation to the Earth.