可重构技术的航天应用与星载计算机设计  

Aerospace application of reconfigurable computing technique and design of on-board computer

作　　者：赵丹[1] 徐国栋[1] 刘源[1] 

机构地区：[1]哈尔滨工业大学卫星技术研究所,黑龙江哈尔滨150080

出　　处：《哈尔滨工程大学学报》2009年第5期486-490,共5页Journal of Harbin Engineering University

基　　金：国家高科技研究发展计划资助项目(2006AA702106)

摘　　要：针对微小型航天器星载计算机设计中存在的功能、性能与可靠性之间的矛盾,提出将可重构计算技术应用于航天领域,进行可重构星载计算机的设计.通过对可重构计算技术航天应用现状分析,从体系结构、功能、可靠性等方面进行微小卫星可重构星载计算机的研究与设计,并分析采用硬件编程实现重构配置算法的系统性能.构建基于可重构星载计算机和dSPACE仿真计算机的闭合回路仿真平台,进行上述设计的验证工作.实验表明,可重构星载计算机能够完成正常控制工作,在500 m s的控制周期下,稳态下姿态角速度的精度可达0.05°/s,通过实现对日定向与对地定向2种模式之间的切换,得到切换时间为520±40 m s,能够满足卫星对星载计算机的切换要求.To address functional, performance, and reliability issues with on-board computer （OBC）, reconfigu- rable computing technique was applied to aerospace. Based on reconfigurable computing technique, a reconfigurable OBC for micro-satellite was designed, including its architecture, functions, and reliability. System perform- ance of the OBC designed by hardware programming was analyzed and proved to be much better than that by soft- ware programming. To verify the reconfiguration function of the OBC, a closed loop simulation platform was estab- lished with a prototype of the reeonfigurable OBC and dSPACE. The results of the experiment, in which the OBC ran in Sun pointing control mode and then Earth pointing control mode, showed that the reeonfigurable OBC could control the satellite with a 500 ms control cycle, and the precision of attitude angular velocity could reach 0.05 deg/s under a steady-state condition. Reconfiguring time, when switching from Sun pointing control mode to Earth pointing control mode, was in the range of 520±40 ms and so successfully meets switching requirements.

关 键 词：可重构计算 星载计算机 FPGA 硬件编程 

分 类 号：V443[航空宇航科学与技术—飞行器设计]