| 摘要 |
The method involves determining a piloting control law by modeling based on interpretation of gyroscopic actuators as function of speed of rotation of an astronautics satellite (1) for change of attitude control, with reversal of function of translating kinetic moment according to the principle of conservation of an amount of motion of the satellite during change of attitude. The law is defined to include maximum attainable rotation speed of the satellite around a rotation axis, defined by calculating values of two-dimensional tabulated function. Independent claims are also included for the following: (1) an electronic system for controlling gyroscopic actuators of an astronautics satellite (2) a satellite.
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