| 摘要 |
The orientation of flying objects, in particular satellites, must be stabilised in space. For that purpose, gyroscope devices are used with swivellable gyroscopes in a cardan frame or with gyroscopes fixed in three different directions with adjustable speeds of rotation. These constructions are costly, heavy and prone to failure in certain circumstances. The disclosed device requires only two gyroscopes (1, 2) which may be suspended with a limited cardan mobility, whose axes of rotation coincide in the initial stage and which rotate in opposite directions. By tilting at least one gyroscope and modifying the speed of rotation, any desired resulting torque-vector (Hg) and any desired rotation of the satellite may be achieved. |
