METHOD OF SPACESHIP ORIENTING AND DEVICE TO THIS END Russian patent published in 2014 - IPC B64G1/24 

FIELD: transport.

SUBSTANCE: invention relates to aerospace engineering, particularly, to spacecraft orientation. Proposed method comprises the steps that follow. Generation of angle estimate and spacecraft spin rate estimate signal are generated. Determination of difference in angle signal and angle estimate signal. Determination of difference in spin rate and spin rate estimate signal. Corrected angle estimate signal and corrected spin rate estimate signal are defined. Control signal is generated using said corrected angle estimate signal and corrected .spin rate estimate signal Proposed device comprises engine-flywheel model, four integrators, four adders, four normally closed switches and two normally-open switches. Output of 2^nd adder is connected via engine-flywheel model, 1^st integrator, 4^th adder, 2^nd integrator, 5^th adder, 6^th adder, 1^st switch and 3^rd integrator, all being connected in series, with 5^th adder 2^nd input. Output of the latter is connected via 1^st switch with 2^nd input of 1^st adder. Output of 4^th adder is connected via 7^th adder, 2^nd switch and 4^th integrator, all being connected in series, with 4^th adder 2^nd input. Output of the latter is connected via 2^nd switch with 3^rd input of 2^nd adder. Output of spin rate transducer is connected with 7^th adder 2^nd input and, via 3^rd switch, with 2^nd amplifier input.

EFFECT: higher accuracy and reliability.

2 cl, 1 dwg