设计了一种基于光纤导入的太阳敏感器，其包括三个部分：光学头部、光电传感器和太阳偏移角度的算法。光学头部采用两对对称光纤和一根中心光纤，通过计算每对光纤导入光能的差分值，获得太阳与航天器自身坐标系统的相对角度关系。该光学结构兼顾了大、小视场，提高了太阳敏感器定位精度。采用光纤作为太阳光的导入器，将光能导入置于航天器内部的光电敏感元件，以防止宇宙中高能粒子直接轰击传感器而造成损坏。简要介绍了电路的构成和信号的处理。分析了测量误差并提出补偿措施。初步试验表明，系统精度可达到±0.15°。本设计将适用于航天飞行器定位和一些地面太阳跟踪系统。

Based on the technology of optical fiber, an analog sun sensor was designed. It consists of three parts: the optical head, optic-electronic sensor and the measurement and calculation of sun angle. The optical design of the sun sensor adopts two pairs of optical fiber and a central optical fiber, and then obtains the relative angular relationship between the sun and the spacecraft's own coordinate system by calculating the difference value of importing light of each pair of optical fiber. The optical structure can suit multi-fields of view, including both small and large. It can increase the accuracy of the positioning system. Optical fiber was used as a leader, which connected the optic-electronic sensor inside the spacecraft. Keeping the sensor deep inside the spacecraft will protect the sensor from being damaged by high-energy particle in space. Circuit and signal processing were briefly described, and compensation of the error was analyzed. Preliminary test has shown that the system accuracy can reach ±0.15 degrees. This sun sensor is particularly applicable to attitude control system of spacecraft and solar tracking system on ground.