FIELD: astronautics.SUBSTANCE: invention relates to systems for stabilizing and controlling the orientation of spacecraft and can be applied for controlling the angular motion of a small spacecraft. Device is a combined control system consisting of a self-extracting gravity rod with an end load and a two-stage gyro with a torque sensor on the suspension axis performing the function of this load. To control the spacecraft on-course, the specified gyro is used as a gyrodyne, and for controlling the roll and pitch angles – as an electromechanical actuator (flywheel).EFFECT: technical result of the invention is expansion of the system functionality and the increase in the accuracy of the spacecraft orientation.1 cl, 3 dwg
КОМБИНИРОВАННАЯ ГРАВИТАЦИОННАЯ СИСТЕМА ОРИЕНТАЦИИ МАЛОГО КОСМИЧЕСКОГО АППАРАТА
2017-10-19
Patent
Electronic Resource
Russian
IPC: | B64G Raumfahrt , COSMONAUTICS |
СПОСОБ ОРИЕНТАЦИИ КОСМИЧЕСКОГО АППАРАТА В СОЛНЕЧНО-ЗЕМНОЙ СИСТЕМЕ КООРДИНАТ
European Patent Office | 2017
European Patent Office | 2018
ТЕРМОРЕГУЛИРУЮЩАЯ ЛЕНТА, СИСТЕМА И СПОСОБ ДЛЯ КОНСТРУКЦИИ КОСМИЧЕСКОГО АППАРАТА
European Patent Office | 2020
УСТРОЙСТВО АЭРОДИНАМИЧЕСКОГО ТОРМОЖЕНИЯ КОСМИЧЕСКОГО АППАРАТА
European Patent Office | 2018