Nanosatellite control system for its spatial orientation

Abstract

This utility model relates to spacecraft, specifically to the attitude control of CubeSat-type nanosatellites, and can be used for spatial orientation of nanosatellites in space. Currently, numerous nanosatellite attitude control systems exist that address the problem of nanosatellite positioning in space. The use of various optical systems, stabilization and control systems based on electronic components, and various gyroscopes is very popular; however, these methods have a number of disadvantages, the main one being the technical complexity of installation and the high cost of components. In order to achieve the technical result of the nanosatellite control system for its orientation in space, including a magnetometer, a microcontroller, a communication interface, according to the utility model, an astroorientation module is installed, containing a commercially available industrial-grade digital camera (COTS camera), an optical filter unit installed in the optical path of the camera and designed with the ability to reduce background illumination, a lens hood and an image pre-processing unit, wherein the image pre-processing unit is configured to isolate stellar objects and determine their coordinates, and the microcontroller is configured to jointly process data from the magnetometer and the astroorientation module to determine the orientation of the nanosatellite relative to the inertial coordinate system.