| 摘要 |
A gyro system for control of the angular state of spaceship contains on each is orthogonal coordinate system, associated with the housing, a three-stage power gyroscope of variable structure, which allows to transform it into the two-step power gyroscope, arresting device on the external frame of gyroscope, sensor of moment and damping device on axle suspension of internal frame. For exclusion from the control process of gas-dynamic jet engines on each axis of orthogonal coordinate system, associated with the housing, the analogous three-stage power gyroscope of variable structure with arresting device on the external frame and sensor of moment and damping device on axle of suspension of internal frame are mounted. The axles of suspension of external frames of both power gyroscopes are collinear to each other. On the axles of suspension of internal frames of both power gyroscopes the sensors of angle of rotation of frames are located, while on the axles of the suspension of external frames - flywheel motors, which stators are rigidly connected with the axles of suspension of the external frames of power gyroscopes.
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