捕获、对准、跟踪系统是空间激光通信重要组成部分,是通信正常进行的前提与保障。针对捕获系统中的初始指向内容进行了详细研究,给出初始系统指向系统模型,应用坐标转换矩阵补偿由于位置不同、姿态变化、安装基准轴差异、初始零位不一致等对初始指向方位角和俯仰角的影响。提出初始指向系统视轴标校方法,根据误差分析方法确定了指向精度及捕获不确定区域大小。在飞机-飞机动态演示实验中,应用双天线全球定位系统/捷联导航系统(GPS/INS)组合器件实时得到位置、姿态等参数,实现初始指向系统性能测试。借助观靶相机实际测量本系统捕获不确定区域大小为10mrad,与理论分析结果基本一致。 Capture, alignment, tracking system is an important part of space laser communications, communication is the premise of normal conduct and protection. The initial orientation in the acquisition system is studied in detail. The initial system point system model is given. The initial orientation azimuth and pitch are compensated due to the difference of position, the change of attitude, the difference of the initial datum and the coordinate transformation matrix. The impact of horns. The method of calibrating the boresight of the system is proposed, and the accuracy of pointing and the size of the uncertain region are determined according to the error analysis method. In the aircraft-aircraft dynamic demonstration experiment, the dual-antenna GPS / INS combination device was used to obtain the position, attitude and other parameters in real time to achieve the initial pointing system performance test. With the help of the target camera, the size of the uncertainty area captured by the system was measured to be 10 mrad, which is basically consistent with the theoretical analysis.