| 汪芊芊,苏晗,林臻,王海涛,蓝鲲.运载火箭电子设备测试性验证方法研究[J].电子测量与仪器学报,2024,38(2):241-248 |
| 运载火箭电子设备测试性验证方法研究 |
| Research on testability verification of launch vehicle electronic equipment |
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| DOI： |
| 中文关键词: 测试性验证 冗余降级FMEA分析 故障覆盖率 |
| 英文关键词:testability verification redundancy function degradation FMEA analysis voverage rate of fault modes |
| 基金项目: |
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| Author | Institution |
| Wang Qianqian | Beijing Institute of Astronautical Systems Engineering, Beijing 100076, China |
| Su Han | Beijing Institute of Astronautical Systems Engineering, Beijing 100076, China |
| Lin Zhen | Beijing Institute of Astronautical Systems Engineering, Beijing 100076, China |
| Wang Haitao | Beijing Institute of Astronautical Systems Engineering, Beijing 100076, China |
| Lan Kun | Beijing Institute of Astronautical Systems Engineering, Beijing 100076, China |
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| 摘要点击次数: 249 |
| 全文下载次数: 572 |
| 中文摘要: |
| 装备测试性验证及FMEA分析传统按照单故障模式考虑，并采用抽样方法确定故障样本，并未考虑冗余模块的不同失效模式以及对故障模式的覆盖程度。针对运载火箭电子设备冗余功能验证需求、测试覆盖性需求等测试性验证需求和难点，在装备通用测试性验证方法基础上，提出冗余降级FMEA分析及故障覆盖率指标评估方法，形成了适用于运载火箭电子设备的测试性验证及评估方法，最后以某箭上电子设备为例进行了验证。结果证明，本文提出的冗余降级FMEA分析方法有效识别了运载火箭电子设备冗余模块的冗余性能降低和整体失效故障模式，并将冗余模块的故障模式纳入测试性指标评估，实现了测试性验证对于运载火箭电子设备冗余功能的考核；所提出的故障覆盖率指标评估方法及样本量补充方法有效提升了测试性验证对运载火箭故障模式的覆盖程度。本文方法适用于运载火箭电子设备的测试性验证及指标评估，并可推广至全箭电气系统。 |
| 英文摘要: |
| Testability verification and FMEA analysis of equipment consider single faults and use sampling methods to determine fault samples traditionally, without considering the different failure modes of redundant modules and the coverage rate of faults. Aiming at the requirements and difficulties of testability verification for launch vehicle electronic equipment, including redundant function verification requirements and testing coverage requirement etc., the functional degradation FMEA analysis method and evaluation method of coverage rate of fault modes was proposed on the basis of the general testability verification method of equipment, and a testability verification and evaluation method suitable for the launch vehicle electronic equipment was formed. An electronic equipment on the launch vehicle was taken as an example for modeling. The results proved that the method proposed in this paper effectively identified the redundant faults, and incorporate the fault modes of redundant modules into the evaluation of testability indicators. The faults of redundant modules were considered in the evaluation of testability indicators, and the verification of redundant functions of launch vehicle electronic equipment was assessed. The proposed fault coverage evaluation method and sample size supplement method effectively improve the coverage of testability verification for fault modes. It is suitable for testability verification and evaluation of launch vehicle electronic equipment, and can be extended to the electrical system of launch vehicle. |
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