Patent RU-2495379-C2 (RU)
Inventor: SYROV ANATOLIJ SERGEEVICH
IPC: G01C21/24
Filed: 2011-12-28
Granted: 2013-10-10
Abstract: FIELD: measurement equipment. 
     SUBSTANCE: according to the proposed method, five threshold signals, signals of norms of gyroquaternions, signals of norms of bases, and a signal of norm of astroquaternion; speeds of change of output signals of each gyroscope are determined, and when they exceed the first threshold signal, the second failure signal is shaped; signals of differences of signals of gyroquaternions of bases are determined, and when they exceed the second threshold signal, the third failure signal is shaped. After at least one failure signal is received, difference signal is determined between signal of norm of gyroquaternion of working basis and signal of norm of astroquaternion, and when it exceeds the third threshold signal, L fourth failure signal is shaped; occasionally, at the time interval equal to five minutes there determined are difference signals of signals of gyroquaternions of signals and bases and signal of astroquaternion, and when it exceeds the fourth threshold signal, the fifth failure signal is shaped; occasionally, within four seconds, after the third failure signal is received, a control loop of a space vehicle is opened, a test signal is supplied to the actuating device input, output signals of gyroscopes are measured, and when they exceed the fifth threshold signal, the sixth failure signal is shaped. In addition, a device for the method's implementation includes three OR circuits, fourteen non-linear units, six adders, four shapers of signal of norm of gyroquaternion and a shaper of signal of norm of astroquaternion; output of astrodetector is connected through the shaper of astroquaternion norm signal to the first inputs of the fifth, the sixth, the seventh and the eighth adders; output of the shape of norm signal of astroquaternion is connected through the ninth adder to input of the fifth non-linear unit; output of the first shaper of basis is connected through in-series connected first shaper of norm signal of gyroquaternion, the fifth adder and the sixth non-linear unit to the first input of the first OR circuit, output of the second shaper of basis is connected through in-series connected second shaper of norm signal of gyroquaternion, the sixth adder and the seventh non-linear unit to the second input of the first OR circuit; output of the third shaper of basis is connected to the third input of the first OR circuit through in-series connected third shaper of norm signal of gyroquaternion, the seventh adder and the eighth non-linear unit, output of the fourth shaper of basis is connected to the fourth input of the first OR circuit through in-series connected fourth shaper of norm signal of gyroquaternion - the eighth adder and the ninth non-linear unit, output of the third shaper of norm signal of gyroquaternion is connected through the tenth adder to input of the tenth non-linear unit, output of the fourth shaper of norm signal of gyroquaternion is connected to the second input of the tenth adder, output of the first gyroscope is connected through the eleventh non-linear unit to the first input of the second OR circuit and through in-series connected first differentiating device and the twelfth non-linear unit to the first input of the third OR circuit, output of the second gyroscope is connected through the thirteenth non-linear unit to the second input of the second OR circuit, and through in-series connected second differentiating device and the fourteenth non-linear unit to the second input of the third OR circuit, output of the third gyroscope is connected through the fifteenth non-linear unit to the third input of the second OR circuit, and through in-series connected third differentiating link and the sixteenth non-linear unit to the third input of the third OR circuit, output of the fourth gyroscope is connected through the seventeenth non-linear unit to the fourth input of the second OR circuit, and through in-series connected fourth differentiating device and the eighteenth non-linear unit to the fourth input; the third OR circuit, outputs of the third OR circuit, the tenth non-linear unit, the fifth non-linear unit, the first OR circuit, the second OR circuit are the second, the fourth, the fifth and the sixth outputs of the device respectively. 
     EFFECT: improving reliability and accuracy of a monitoring method of failure of a gyroscopic measuring device, and a device for the method's implementation. 
     2 cl, 5 dwg