Abstract
This article is devoted to the design of three-axis orientation and navigation systems of CubeSat small spacecraft. The article discusses the problems of controlling the movement of spacecraft along the X, Y and Z axes and designing navigation systems. The design methodology of the navigation control system is presented, which considers modern trends and ensures high quality of control and navigation. The hardware component of the control system included an Arduino Nano microcontroller, ADXL335 accelerometers, an NRF24 radio frequency module, and motor driver and electromechanical executive bodies. GPS data and a ground station were used to receive navigation and telemetry information. The CubeSat body and internal component layout was modeled in a SolidWorks environment, and a physical prototype was later prepared. During the experiment, a given angle for the X, Y and Z axes, the actual angle of the apparatus and the control signal of the actuator were recorded. The results obtained showed that the real angle converges toward the reference value due to the applied control action and allows the developed experimental system to implement the principle of stabilization along the three coordinate axes. The proposed experimental platform can be used to further study and improve the orientation algorithms of CubeSat-type apparatuses.