FIELD: measuring equipment.
SUBSTANCE: invention relates to methods of constructing measurement systems and control systems of gyroscopes intended for control of rockets at initial sections of their trajectories. Proposed method is intended for accelerated delivery of gyroscope with rotor coupled with engine shaft by spherical ball bearing. On the rotor there is an elastic plate with three or more lobes bent relative to the rotor rotation plane. At ends of lobes, remote from rotor rotation axis, inertial masses are located. Ends of lobes are in contact with disc installed on engine shaft, and axes of rotor and engine shaft are aligned. When the engine is switched on, the lobes are engaged with the disc so that the rotor rotation speed is increased to the preset value. When the engine is switched off and the projectile movement begins, in which the gyroscope is installed, the gyroscope is brought into a ready state, i.e. loss of contacts of petals of the plate of the rotating rotor with the disc and their removal from the disc at the required distances under the action of centrifugal forces of inertia.
EFFECT: simplified method of accelerated bringing of gyroscope into ready state.
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Authors
Dates
2020-01-31—Published
2019-06-10—Filed