Gyroscope Sensor for Measuring Angular Velocity Vector Projections 2

Purpose: Measurement of angular increments (rate integral) on sensitive axes of four measurement channels and transmission of that information to the object’s control system.
Year of release: 2016
Guaranteed service life (years): 15
Estimated production / delivery time (months): 18
Flight qualification of the product: Yes
Brief history of flight qualification: Use as a part of Onboard Control System of SC.
Possibility to adapt the product to customer requirements: Yes

Parameter	Value
Measured angular velocity range	1,6◦/s
Nominal certified value of scale factor (information impulse value)	(0,30-0,45) arc.sec
Random component of the deviation of the IR zero signal, independent of overload, in continuous start-up up to 24 hours	0,003 ◦/h
Weight	12,9 kg
Maximum value of the IR zero signal, independent of overload, per module	3,0 ◦/h
Noise component (1 RMS) of the IR output signal of the device on a stationary ground at the averaging time from 0.1 to 10 s	0,15 arc second
Energy consumption of the device in the steady-state thermal state of 4 IR at a temperature of heat-absorbing surface of the satellite from 5 to 30˚C	71 W
Power supply voltage	27,5 V
Precision readiness (from the thermal readiness state, from the moment of switching on the IR)	180 min

Redundant free form gyroscopic angular velocity vector meter for spacecraft orientation and stabilization control system.
Sealed monoblock device, including electronic and optoelectronic modules with a block of four sensitive elements of a fiber-optic gyroscope and four sensitive elements of pendulum quartz accelerometer, thermal control system and vibration protection system.

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