| 摘要 |
The method involves pointing a terminal embedded in a satellite (S1) towards a remote terminal of a satellite (S2) by rotation of a main platform (100) of the satellite (S1), during optical transmission between the terminals. The embedded terminal has a thin pointing device and a transmission field oriented in a fixed manner with respect to the platform that is oriented using a gyroscopic actuator to point the embedded terminal. An independent claim is also included for a spacecraft having a main platform and optical transmission terminal. |
