Spatial Orbital Gyrocompass. Questions of Theory and Application

Abstract

The developed spatial (3D) orbital gyrocompass allows performing all the necessary functions of angular orientation of a spacecraft relative to the orbital coordinate system. In this regard, it is no different from the astronavigation system (ANS), except for the use of different types of external information sensors. In the first case, it is the Earth orientation device; in the second case, it is the star sensor. Each system has its advantages and disadvantages. The advantage of the ANS is higher orientation accuracy. The undeniable advantage of the 3D gyrocompass is the ability to control the orientation of the spacecraft for an extended period without using ballistic data. The sufficiently high functionality of the 3D gyrocompass makes the orientation system built on its basis quite competitive with astronavigation-based orientation systems. Thus, the task of studying the properties and improving the accuracy characteristics of the device becomes relevant.