Problems of development motion control algorithms for a small spacecraft for technological purpose taking into account temperature deformations of solar panels

Abstract

Abstract The paper considers the development of an algorithm for controlling the orbital motion of a small spacecraft using a control system that has flywheel engines and an electrothermal micromotor for unloading flywheels as executive bodies. It is assumed that a small spacecraft periodically falls into the shadow of the Earth. The temperature deformations of solar panels that affect the dynamics of evolution around the center of mass are taken into account. The restrictions on the internal environment micro-accelerations of a small spacecraft are taken into account when choosing the main parameters of the executive bodies. These restrictions are imposed when gravitationally sensitive technological processes are carried on board it. The aim is to reduce the level of micro-accelerations in the zone of technological equipment as possible while developing control algorithms.