FEATURES OF USING THE ELECTROMAGNETIC ANGULAR STABILIZATION SYSTEM OF SPACE VEHICLES

Abstract

Virtually all spacecraft (SCs) use an electromagnetic angular orientation and stabilization system (AOSS) in low orbits. Its widespread use is primarily due to the simplicity of practical implementation (relatively cheap magnetometers are used as sensors, and electromagnets as actuators), and secondly, for unloading flywheel engines. The purpose of the work is to conduct an analytical review of the features of using electromagnetic AOSS. The models and characteristics of the Earth's magnetic field and the nature of the interaction of the Earth's magnetic field with the magnetic field of the spacecraft are considered. In a first approximation, near the Earth's surface (up to three of its radii), the Earth's magnetic field is represented as a magnetic dipole, the axis of which is inclined to the Earth's axis of rotation. This tilt gradually changes, requiring the model to be corrected every 5 years. In reality, the Earth's magnetic field differs from the theoretical model due to the appearance of so-called magnetic anomalies. The characteristics of these anomalies and their impact on the spacecraft are considered. The characteristics of these anomalies and their impact on the spacecraft are considered. An analysis of the errors of the electromagnetic AOSS is carried out, including: the model of the Earth's magnetic field, relative to which the angular position of the spacecraft is determined according to magnetometer measurements, has deviations from the real magnetic field; when the axis of the spacecraft coincides with the magnetic field line, the rotation of the spacecraft around this axis becomes impossible; the determination of magnetometer measurements of the Earth's magnetic field vector projections is significantly affected by magnetic fields created by electromagnets (EMs) and spacecraft instruments; as the spacecraft moves in orbit, the Earth's magnetic field changes its position in space; the steering torque created by the EMs is small, which leads to a significant stabilization time. The main factors that affect the accuracy of angular stabilization of the spacecraft and methods that allow reducing their impact on both the accuracy of orientation (determination of the angular position of the spacecraft in space) and the accuracy of stabilization (maintaining the angular position of the spacecraft) are determined. Creating more effective electromagnetic algorithms AOSS can be achieved through the use of artificial intelligence (AI).