在任何时间点，如果太阳仰角或是太阳方位角的错误或是动量向量的错误超过容忍度时，那么ACS将会为了修正此问题而回到适当的模式。
At any point, if the sun elevation or sun azimuth errors or the momentum vector error exceeds tolerances, the ACS will return to an appropriate mode in order to correct the problem.
在这个时机点，卫星已经进入最后的设定并且会透过修正方位角错误和仰角错误来达到最后的姿态。
At this point, the satellite is in its final configuration and it will reach its final attitude by correcting the azimuth error as well as the elevation error.
针对具有恒定俯仰角度载体的磁航向罗差标定和补偿问题，提出了一种用于磁罗差修正的偏差补偿算法(DCA)。
To calibrate and compensate the compass error of magnetic heading in a carrier with constant pitch Angle, the deviation compensation algorithm (DCA) for magnetic deviation compensation is put forward.
本文提出了一种用数值法修正雷达高仰角动态滞后误差的方法，并用任务实测数据进行了模型验证，结果显示这种方法能有效地降低动态滞后引起的误差。
This paper puts forward a new numeric model. Simulation with actual mission data shows that the new model significantly reduces lag error and improves the accuracy of data processing.
本文提出了一种用数值法修正雷达高仰角动态滞后误差的方法，并用任务实测数据进行了模型验证，结果显示这种方法能有效地降低动态滞后引起的误差。
This paper puts forward a new numeric model. Simulation with actual mission data shows that the new model significantly reduces lag error and improves the accuracy of data processing.
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