太阳敏感器和红外地球敏感器是卫星姿态控制的重要部件，在卫星升空前必须对其进行地面实验。设计了一套由4条光缝组成的太阳模拟光源和针对地球同步轨道高度15.6°张角的南北红外地球模拟光源。详细介绍了地面姿态模拟光源系统的组成及总体结构，采用红外光学技术，设计了地球模拟光源的锗准直透镜，同时为了保证各模拟光源对真实卫星的安全对接试验，确认各光源对星上产品的激励作用满足要求，设计了地面姿态模拟光源安装支架。地球模拟光源能够模拟地球弦宽15.6°及卫星10~120 rpm的自旋转速，通过实验对地球模拟光源弦宽及转速进行了测试，结果表明模拟地球弦宽误差不大于0.04°，转速锁相误差不大于±1 ms。

The solar sensor and the infrared earth sensor are important equipments for controlling the satellite′s attitude; they must be tested in the ground before the satellite launch. The system includes one solar simulating light which′s made up of four slits and two earth simulating lights which is simulated for an earth angle of 15.6° of earth synchronous orbit height. In this paper, the overall structure and the components of the ground attitude simulation lights were described. To design the system, infrared optical technique was used and the germanium collimating lens was designed, meanwhile the installation institutions of the ground attitude simulation light source was designed in order to connect the simulation light source to the real satellite safely for ensuring the requirements of the star products. The earth simulation light can simulate the earth chord width of 15.6° and the speed of the satellite is 10-120 rpm. The earth chord width and speed were tested through experiment, which show that the earth angle error is less than 0. 04° and speed phase-locked error is no more than 1 ms.