基于SOPC的陀螺星敏感器姿态确定系统(英文)  

Attitude Determination System of Gyros and Star Sensors Based on SOPC

作　　者：白博[1] 周军[1] 于晓洲[1] 

机构地区：[1]西北工业大学精确制导与控制研究所,西安710072

出　　处：《火力与指挥控制》2011年第2期33-38,共6页Fire Control & Command Control

基　　金：教育部博士点基金资助项目(20070699004)

摘　　要：为了提高姿态确定算法的计算速度,通过对陀螺星敏感器姿态确定算法的详细分析,设计出了基于SOPC(System On a Programmable Chip)系统的卡尔曼滤波处理器。在该处理器中,对算法进行了软硬件代码划分。软件部分采用Nios Ⅱ IDE编程环境进行编写和编译,硬件部分采用硬件描述语言进行构造。通过SOPC系统,将两者集成于单一的FPGA(Field Programmable Gate Array)芯片中。最后,对于相同条件,在实际芯片与Matlab上分别对算法进行了仿真。两者的仿真结果表明,基于SOPC系统的姿态确定算法能够在一定精度范围内正确并快速地确定航天器的姿态。In order to improve the calculating speed of attitude determination algorithm, the Kalman filter processor, which is based on SOPC （System On a Programmable Chip）, is designed on the careful analysis of the algorithm with gyros and star sensors. In this processor, the hardware-software partition is made for the algorithm. The software is edited and compiled in the programming environment of Nios Ⅱ IDE, and the hardware is constructed with Hardware Description Language. By the SOPC system, the software and hardware are integrated in one FPGA（Field Programmable Gate Array） chip. Finally, the algorithm is simulated in the actual chip and Matlab under the same condition, respectively. The two simulation results show that, the attitude determination algorithm based on SOPC system can determine the spacecraft ~s attitude in a certain precision range correctly and quickly.

关 键 词：SOPC 陀螺 星敏感器 姿态确定 

分 类 号：V448.21[航空宇航科学与技术—飞行器设计]