A Method of Spacecraft Attitude Stability Control Through Internal Vibration Isolation Structure
A technology for stability control and spacecraft, applied in attitude control and other directions
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[0097] An internal vibration isolation structure of a control moment gyroscope, which is composed of a plurality of flexible support structures 1; the flexible support structure 1 is located between the rotor 2 and the frame 3 and between the frame 3 and the spacecraft; when the control moment gyroscope is working, the flexible support The structure 1 will then start to produce a vibration isolation effect, thereby suppressing the disturbance generated by the rotor 2.
[0098] The number of the plurality of flexible support structures 1 is at least four, two of which are fixedly connected between the rotor 2 and the frame 3, and the other two are fixedly connected between the frame 3 and the spacecraft;
[0099] The flexible support structure includes a rigid support part 4 and a flexible deformation part 5, and the rigid support part 4 and the flexible deformation part 5 are fixedly connected;
[0100] The rigid supporting part 4 is made of titanium alloy material; the flexib...
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