摘要
遥感卫星分辨率日趋精细,相机口径不断增大,受限于运载器直径对刚性遮光罩系统尺寸约束,柔性展开遮光系统在遥感器上逐渐应用,空间柔性展开结构在轨工作状态对于主任务判定有重要作用。报道了一种展开状态红外感知系统,应用于我国高分七号相机遮光罩系统在轨展开状态监测。首先介绍了高分七号双线阵相机及其遮光罩系统设计,分析了展开状态红外感知功能的特殊要求和约束。提出了一种利用"豆荚杆"作为传输通道的基于红外光线传输阻隔特性的新型展开状态感知方法,系统包含了红外光线产生系统与接收系统,采用红外光线产生系统发射的890 nm波段光线作为信息载体,经空间柔性展开结构"豆荚杆"通道后由红外光线接收系统转换为电信号,通过对电信号处理得到柔性结构展开状态信息。系统具有无动作机构部件、无较大能量消耗及数据带宽要求小等优点,对原有展开过程基本不产生影响。通过理论分析证明了该方法的可行性,试验验证了该方法中红外光线产生系统光功率、红外光线接收系统光电晶体管阵列上拉电阻以及工作温度等参数对展开判定准确性的影响。通过试验得到,现有展开状态红外感知系统的红外光线产生系统光功率参数大于25 mA、红外光线接收系统上拉电阻特征参数大于15 kΩ是系统工作的理想包络。在温度交变环境下,当红外光线接收系统上拉电阻特征参数不大于50 kΩ时,展开状态红外感知系统在125℃以下温度环境中能够有效的判定遮光罩系统的状态参数。为同类型柔性遮光罩系统监测方案设计及在轨温度交变环境下应用策略提供了试验数据基础,具有广泛前景。
The resolution of space remote sensing satellites is getting finer and finer, and the aperture is getting large and large, which is restricted by the diameter of the carrier. So the baffle system of flexible, deployment has been applied to remote sensors gradually. The monitoring of the geometry state of the space flexible deployable structure in orbit plays an important role in the determination of the main mission. This paper introduces an infrared unfolding state sensing system which is applied to the in-orbit unfolding state monitoring of GF-7 camera baffle system. Firstly, this paper introduces the design of GF-7 camera baffle system and analyzes the special function of infrared sensingduring the unfolding state. A novel unfolded state perception method based on infrared ray transmission barrier characteristics by using lenticular boom as the transmission channel is proposed. The system includes the infrared ray generation system and receiving system, and the 890 nm wavelength light generated by the infrared ray generation system using as the data carrier. The data passing through the flexible deployable structure is converted into an electrical signal by the infrared ray receiving system and the flexible deployment unfolding state information is obtained. The system has the advantages of no moving parts, low power consumption and data bandwidth requirements, and has no mechanical impact on the deployment process. The feasibility of this method is proved through theoretical analysis, and an experiment is designed to verify the optical power of the infrared ray generation system in this method. According to the experiment, the optical power of the infrared system is greater than 25 mA, and the pull-up resistance of the extremely ray receiving system is greater than 15 kΩ, which is the ideal bound for the system. The infrared unfolding state sensing system can effectively determine the state under 125 ℃ when the pull-up resistance is no more than 50 kΩ. For the monitoring design and the application strategy in the environment of in-orbit of the same type of the flexible deployment baffle system, it provides the basis of test data and has a board application prospect.
作者
刘靖雷
冯昊
曹旭
江长虹
贾贺
张章
LIU Jing-lei;FENG Hao;CAO Xu;JIANG Chang-hong;JIA He;ZHANG Zhang(Beijing Institute of Space Mechanics&Electricity,Beijing 100191,China;Key Laboratory for Nondestructive Spacecraft Landing Technology of China Academy of Space Technology,Beijing 100191,China)
出处
《光谱学与光谱分析》
SCIE
EI
CAS
CSCD
北大核心
2020年第9期2676-2680,共5页
Spectroscopy and Spectral Analysis
基金
国家重大专项工程
国家自然科学基金项目(11602018)资助。
关键词
遮光罩
展开状态红外感知
近红外
光线阻隔
Camera baffle
Infrared unfolding state sensing
Near-infrared
Light barrier
