基于内部1553B总线的航天器控制系统可测试性框架设计与验证

doi:10.3969/j.issn.1674-1579.2014.02.005

空间控制技术与应用 ›› 2014, Vol. 40 ›› Issue (2): 26-30.doi: 10.3969/j.issn.1674-1579.2014.02.005

基于内部1553B总线的航天器控制系统可测试性框架设计与验证

北京控制工程研究所,北京 100190

出版日期:2014-04-24 发布日期:2014-04-24

Frame Design and Verification of DFT Technique for Control System of Spacecraft Based on 1553B Bus Architecture

Beijing Institute of Control Engineering, Beijing 100190， China

Online:2014-04-24 Published:2014-04-24

摘要/Abstract

摘要： 可测试性设计是提升系统研制效率和测试品质的重要方法.给出基于内部1553B总线的航天器控制系统可测试性设计的分层递阶结构，建立可测试性设计的模型框架，并对基于1553B总线的航天器控制系统可测试性设计的技术实现进行了分析.最后利用TEAMS软件结合实例进行可测试性设计仿真评估，评估结果证明了这种可测试性设计方法的有效性.

关键词: 可测试性设计, 可测试性标准, 基于总线的体系结构, 航天器控制系统

Abstract: Design for testability (DFT) is an important approach to improve the manufacturing efficiency and test quality of a system. The hierarchical structure of DFT for AOCS of spacecraft based on 1553B bus architecture is given and the model frame of DFT is built. The technical realization of DFT is also analyzed. The software TEAMS(testability engineering and maintenance system) is used to simulate and evaluate the DFT via an example and the simulation result demonstrates the validity of this method.

Key words: DFT, testability standards, busbased configuration, control system of spacecraft

中图分类号:

王海博, 袁利. 基于内部1553B总线的航天器控制系统可测试性框架设计与验证[J]. 空间控制技术与应用, 2014, 40(2): 26-30.

WANG Hai-Bo, YUAN Li. Frame Design and Verification of DFT Technique for Control System of Spacecraft Based on 1553B Bus Architecture[J]. , 2014, 40(2): 26-30.

参考文献

［1］CHAMPLIN C. Iridium satellite: a large system application of design for testability\[C\]//IEEE International Test Conference. NJ， USA：IEEE service center, 1993:392-398. ［2］LARRY L, JHON A. Satellite hierarchical system test using IEEE 1149.1\[1\]Based COTS test tools a case history with results and lessons［C］//IEEE Systems Readiness Technology Conference. USA：IEEE service center, 1999:193-201. ［3］张强，李彬. 航天器控制系统可测试性设计现状与发展［C］//第二届国防科技工业试验与测试技术高层论坛论文集. 北京：中国计算机自动测量与控制技术学会， 2008：8387. ZHANG Q, LI B.Current status and development of test design for spacecraft\[C\]. The 2th High Level Forum of Experiment and Test Technique for Defence Technology and Industry. Beijing: China association of computor measurement and control technique, 2008:83-87. ［4］姚宁，朱琦，曹荣向，等. 基于内部总线的控制系统体系结构\[J\].空间控制技术与应用，2012,38(2);30-34. YAO N, ZHU Q, CAO R X，et al.Internal busbased AOCS configuration\[J\].Areospace Control and Application,2012, 38(2):30-34. ［5］田仲,石君友. 系统测试性设计分析与验证\[M\].北京：北京航空航天出版社，2003: 17-21. ［6］温熙森，胡政. 可测试性技术的现状与未来\[J\].测控技术， 2000, 19(1)： 9-12. WEN X S, HU Z.Current status and future of testability\[J\]. Measurement & Control Technology, 2000, 19(1)： 9-12. ［7］申宇皓，马春雷. 系统级可测试性设计\[J\].华北工学院学报，2004,25(5)：349-351. SHEN Y H,MA C L.Research on the system level design for measurability\[J\]. Journal of North China Institute of Technology,2004,25(5)：349-351. ［8］BHAVSAR D. An architecture for extending the IEEE standard 1149.1 test access port to system backplanes \[C\] //IEEE International Test Conference. NJ, USA:IEEE Service Conter, 1991:768-776. ［9］IEEE Std. 1149.5-1995 standard for module test and maintenace bus(MTMBus) ptotocol\[S\]. IEEE Standard Committee，1995.

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基于内部1553B总线的航天器控制系统可测试性框架设计与验证

Frame Design and Verification of DFT Technique for Control System of Spacecraft Based on 1553B Bus Architecture

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