METHOD FOR CONTROL DESIGN OF SPACECRAFT WITH POWER GYROSCOPES AND ROTARY SOLAR PANELS Russian patent published in 2017 - IPC B64G1/28 B64G1/36 B64G1/44 

FIELD: aviation.

SUBSTANCE: invention relates to the attitude motion control of the spacecraft (SC) with power gyroscopes (PG) and solar panels (SP) mounted at mutually opposite sides of the spacecraft. At the time of the SC turnmeter fault the spacecraft sum vector of kinetic moment is recorded and the angle rate of axially symmetrical spacecraft precession is determined. Then the kintetic moment of PG is controlled for generating lighting conditions of SP. At the same time SP are turned around their common axis of symmetry in opposite directions at certain angles, the currents from each of the SP and the SC orientation relative to the direction of the sun are determined. SC is taken off into an orbital angular stabilization mode, wherein the temperature of "northern" and "southern" spacecraft surfaces is measured for the damping of rotation about the roll axis.

EFFECT: preservation of the spacecraft functionality with the loss of its orientation to the sun due to the turnmeter fault.

4 dwg