本論文主要探討的是利用角速率迴授對太陽同步軌道衛星在分離階段進行控制。由於衛星與載具在分離階段時，會使衛星產生角速度而造成滾轉，使得衛星無法確定太陽、地球或其他星體的位置，而且在此階段中有能量上的限制，無法使用太複雜的控制法或較耗能的感測器。因此在本論文中選擇較直接的方式對角速度進行控制，因此利用角速率迴授控制，在研究中發現出這種控制方式能有效地降低角速度，對於衛星在任何方向的角速度與姿態都能保持穩定，由於應用於太陽同步軌道中，因此只要能夠穩定衛星，即可利用太陽同步軌道的特性找到太陽的指向。在研究的方式，首先利用Matlab/Simulink建立衛星的動態模型，並模擬出衛星的初始軌道，在角速率回授控制作為控制器加入模型中，並完成整個模擬模型。利用太空中心(NSPO)所提供的資料與模擬結果進行比較，確定此方法的可靠性。 This thesis initital acquisition of sun-synchronous satellites using angular rate feedback in the separation stage control.Because the satellite and vehicles in the separation stage, the satellite will produce angular velocity caused by rolling, making the satellite can not determine the Sun, the Earth or other celestial body position, and at this stage there are restrictions on the energy, you can not use too complex control relatively energy-intensive method or sensors.
Therefore, in this thesis, choose a more direct way to control the angular velocity, thus using the angular rate feedback control, the study found that this control method can effectively reduce the angular velocity, the angular velocity of the satellite in any direction and attitude can be maintained stable, sun-synchronous orbit as used, so long as they can stabilized satellite, you can take advantage of the characteristics of a sun-synchronous orbit point to find the sun. In the study method, the first to use Matlab / Simulink establish satellite dynamic model and simulate the initial orbit of the satellite, the angular rate feedback control as a controller to the model and complete the simulation model. Use NSPO''s data with the simulation results are compared to determine the reliability of this method.
