Abstract
In order to meet in many aspects contradictory requirements to gyroscopes used in space applications, this paper proposes to use the multimode Coriolis vibratory gyroscope, which operates in a new differential mode in addition to well-known rate and rate-integrating modes. The differential mode of operation can provide high resistance to external disturbances acting on the gyroscope under operating in launch, docking, and landing regimes of spacecraft. The differential mode of operation differs from the other two known modes by the presence of two, X and Y, measurement channels. Each of the channel measures angle rate with opposite sign. This mode of operation can be implemented by the disposition of standing wave pattern between the drive and sense electrodes. The paper presents promising capabilities of the differential mode of operation to self-compensate for external disturbances. The condition for the standing wave angle disposition that provides maximum compensation for the disturbances is proposed. Numerical and graphical test results on the determination of shock suppression coefficient, vibration sensitivity reduction coefficient, and also reduction of sensitivity to constant and variable magnetic fields are presented.
Highlights
Nowadays, gyroscopes including MEMS sensors are widely used in space applications, for example, as hardware of systems for small satellite launch
The standing wave has initially been installed at the angle θinitial = π/8 = 22 5° and standard scale factor SFx and SFy calibration procedures have been applied to the tested metallic resonator Coriolis vibratory gyroscope (CVG) described in detail in [7]
The differential CVG can be considered as the third mode of operation for vibratory gyroscopes along with two well-known modes such as rate and rate-integrating ones
Summary
Gyroscopes including MEMS sensors are widely used in space applications, for example, as hardware of systems for small satellite launch. Space applications are characterized in many respects by contradictory requirements to gyroscopes These requirements are resistance to vibrations, low sensitivity to linear acceleration during launch regime, resistance to shocks during landing and docking, and at the same time, small noise in the measurement of small angular rates at an orbit. Such contradictory requirements can be met using a multimode gyroscope with automatic switching from one mode to another. Under measuring of small angle rate, it is advisable to operate in the rate mode, since the measurement errors and sensitivity are mainly determined by the noise and bias drift which can be lower than that for rate-integrating mode of operation [1]. It complements the two first ones and provides accurate measurements, while gyros being subjected to external disturbances
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