Method of spaceship orienting and device to this end

FIELD: aircraft engineering. SUBSTANCE: proposed method comprises generation of signals for estimation of: spacecraft orientation angle, spacecraft sing angle and control. Signal difference of said parameters and their estimates are defined. Several formulas are used to calculate the correction signals of setting and estimation of external interference. Said corrections are allowed for at correction of orienting angle estimate signals and angular velocity signal. The latter are applied in spacecraft orientation control circuit. Proposed device comprises the following extra units: memory, adders, amplifiers, integrators interconnected and connected with other elements via system of switches. Proposed device incorporates models of the spacecraft orientation main circuit and flywheel engine. EFFECT: higher accuracy and reliability of spacecraft orientation at faults of appropriate hardware. 2 cl, 1 dwg