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
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