FIELD: astronautics.
SUBSTANCE: invention relates to controlling the relative motion of a spacecraft. Unloading of control reaction wheels (RW) in the selected orientation channel is carried out by a two-circuit scheme. First circuit realizes the necessary orientation of the spacecraft and accumulates the momentum of the external disturbing torque (DT), and a second circuit forms the unloading moment (UM). UM is opposite in sign to the total kinetic moment of the aircraft system - the control RW. At each control cycle, a pulse of UM is formed with the help of reaction engines (RE), equal in value to the momentum of DT and opposite to DT in sign. Turn-on time of RE on the control cycle is calculated in proportion to the difference between the current and set values of the total kinetic moment of the spacecraft system - the control RW.
EFFECT: technical result of the invention consists in reducing the orientation error of the spacecraft on a set reference point during the unloading of the RW with an increase in the permissible disturbing torque.
1 cl, 4 dwg
