首页 | 本学科首页   官方微博 | 高级检索  
     检索      

新一代运载火箭的数据驱动快速测试技术
引用本文:宋征宇.新一代运载火箭的数据驱动快速测试技术[J].宇航学报,2015,36(12):1435-1443.
作者姓名:宋征宇
作者单位:北京航天自动控制研究所,北京 100854
摘    要:本文提出一种数据驱动的快速测试技术。数据由箭上系统通过自检测(BIT)采集,经箭地高速总线传送至地面;地面数据处理终端采用与箭上系统相同的模型和算法,复现箭上的处理过程,从而判断系统中是否存在故障,实现快速故障定位。本文全面介绍实现这一设计的关键技术,包括箭上信息监测点的选择、总线窃听技术、飞行软件中的数据管理任务等,并示例说明各类典型数据的分析以及故障诊断和定位等。所有分析工作均实时自动完成,并能随测试用例的调整自适应地计算出新的比对结果,为提高系统级测试的覆盖性创造条件;并大大节省地面专用测试设备和数据分析时间,减少技术保障人员。

关 键 词:运载火箭  测发控系统  快速测试技术  
收稿时间:2014-12-01

Data Driven Responsive Test Technique for New Generation Launch Vehicle
SONG Zheng yu.Data Driven Responsive Test Technique for New Generation Launch Vehicle[J].Journal of Astronautics,2015,36(12):1435-1443.
Authors:SONG Zheng yu
Institution:Beijing Aerospace Automatic Control Institute, Beijing 100854, China
Abstract:A kind of data-driven responsive test technique is presented in this paper. The data are sampled by using the on-board system based on built in test (BIT) technique, and sent to a ground system through high speed data bus; the evaluation procedure as the playback of the on-board processing is triggered by using these data with the same model and algorithm in the ground data processing terminal. The calculation results of the on-board system and the ground system are compared to detect and isolate failures quickly. Both background and necessity of the technique are reviewed, and a rather comprehensive introduction is provided for the implementation of each part of the design including selection of the monitoring spot, bus interception technique and data management task. Moreover, the principle of data evaluation for various representative signals and the means for fault detectectionand isolation are illustrated. The analysis is real-time, automatically, and can adapt the test cases adjustment, which is beneficial to system-level test coverage, thus decreasing test equipment, time for data analysis and engineers involved in technical support.
Keywords:Launch vehicle  Test and launch control system  Responsive test technique  
本文献已被 CNKI 等数据库收录!
点击此处可从《宇航学报》浏览原始摘要信息
点击此处可从《宇航学报》下载免费的PDF全文
设为首页 | 免责声明 | 关于勤云 | 加入收藏

Copyright©北京勤云科技发展有限公司  京ICP备09084417号