基于可重构技术的上面级航天器综合电子系统

孙兆伟; 邢雷; 徐国栋; 叶东

doi:10.3788/OPE.20122002.0296

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基于可重构技术的上面级航天器综合电子系统

微纳技术与精密机械 | 更新时间：2020-08-12

- 基于可重构技术的上面级航天器综合电子系统
- Integrated electronic system of upper-stage spacecraft based on reconfigurable technology
- 光学精密工程 2012年20卷第2期页码：296-304
- 作者机构：
  
  哈尔滨工业大学卫星技术研究所,黑龙江哈尔滨,150001
- 作者简介：
- 基金信息：
  
  国家863高技术研究发展计划资助项目(No.2009AA7020101)()
- DOI：10.3788/OPE.20122002.0296
  中图分类号： V442;TP391.4
- 收稿日期：2011-07-18，
  
  修回日期：2011-09-28，
  
  网络出版日期：2012-02-25，
  
  纸质出版日期：2012-02-25
- 稿件说明：
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孙兆伟, 邢雷, 徐国栋, 叶东. 基于可重构技术的上面级航天器综合电子系统[J]. 光学精密工程, 2012,20(2): 296-304

SUN Zhao-wei, XING Lei, XU Guo-dong, YE Dong. Integrated electronic system of upper-stage spacecraft based on reconfigurable technology[J]. Editorial Office of Optics and Precision Engineering, 2012,20(2): 296-304
孙兆伟, 邢雷, 徐国栋, 叶东. 基于可重构技术的上面级航天器综合电子系统[J]. 光学精密工程, 2012,20(2): 296-304 DOI： 10.3788/OPE.20122002.0296.

SUN Zhao-wei, XING Lei, XU Guo-dong, YE Dong. Integrated electronic system of upper-stage spacecraft based on reconfigurable technology[J]. Editorial Office of Optics and Precision Engineering, 2012,20(2): 296-304 DOI： 10.3788/OPE.20122002.0296.

摘要

为实现卫星工程的整体优化

本文打破传统卫星与运载器独立各自设计的界限

将小卫星和小运载器上面级有机融合构成一类上面级航天器

并给出了适用于上面级航天器的可重构综合电子系统方案。该电子系统以Microblaze软核处理器为核心处理单元

采用基于CAN总线的分布式网络结构提高系统的可扩展性

并利用可重构技术实现电子系统核心处理单元的分时复用

以满足运载段和在轨段对电子系统的不同需求。实现了姿态轨道控制算法硬件化

减轻处理单元的负担

提升了系统的计算和处理能力。设计并建立了半物理实验系统

对飞行全过程、全模式进行了仿真验证。结果表明:运载段控制周期达到10 ms

姿态轨道算法硬件化后运行时间约为7.5 ms;相机工作期间姿态指向精度达0.035

稳定度达0.000 68()/s。所设计的可重构综合电子系统完成了上面级航天器的全模式飞行任务

满足运载段强实时性、在轨段高可靠性以及高精度控制等要求。

Abstract

To implement the integral optimization of satellite engineering

a upper-stage spacecraft is proposed based on the combination of a small satellite and a small launcher

and a reconfigurable integrated electronic system for the upper-stage spacecraft is designed to achieve the high function density development of aerospace electronic systems. By taking the Microblaze as a soft-core processor

the electronic system improves its expandability based on a distributed network structure with CAN bus. It realizes the time sharing of a central computer in the core of electronic system and satisfies different requirements of the launching phase and on-orbit phase. Furthermore

the control algorithm has implemented by hardware

which reduces the calculation of processor and improves the computing and processing capabilities of the system. A semi-physical system is built and the full-mode simulation is carried out to verify effectiveness of the designed system. The experiment results show that the control period in the launching phase is 10 ms

the running time of control algorithm is about 7.5 ms

and the attitude orientation accuracy and the stability are 0.035and 0.000 68()/s

respectively. The reconfigurable integrated electronic system can achieve the full-mode flight mission of upper-stage spacecrafts

satisfy the requirements of strong real time in the launching phase

high stability in the on-orbit phase and can offer higher control accuracy.

关键词

Keywords

references

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