| 飞机操纵系统载荷机构原位测试仪的设计 |
| Design of In Situ Testing Instrument for Load Feeling Mechanism in Operating System of Aircrafts |
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| 中文摘要: |
| 针对目前飞机操纵系统载荷机构离位性能检测带来的工作量大、周期长的问题，基于现代测控理论与技术，综合运用传感器、PLC和便携式计算机，设计了“飞机操纵系统载荷机构原位测试仪”，根据检测到的驾驶杆纵向、横向杆力-杆位移信号，通过软件实时生成驾驶杆实际的操纵特性曲线，在此基础上与标准特性曲线对比进行性能评判。试用表明：该设备检测准确、使用方便，实现了载荷机构的原位、自动性能测试，能够满足机务人员的使用需求。 |
| 英文摘要: |
| Against heavy workload and long periodicity caused by dislocation performance testing of load feeling mechanism in operating system in aircrafts, based on modern measuring and controlling theory and technology, “in situ testing instrument for load feeling mechanism in operating system of aircrafts” is designed, which applies sensors, PLC and portable computer. The instrument can generate actual operating characteristic curve in real time with software through detected lengthwise direction and cross direction force and displacement of steering column, then compared with standard operating characteristic curve, performance of load feeling mechanism is evaluated. The tryout of the instrument shows that it can meet the needs of aircrafts maintaining crew because of its accurate detecting, convenient using, in situ and auto testing. |
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| 中文关键词: 飞机 操纵系统载荷机构 性能检测 原位测试仪 |
| 英文关键词:aircrafts load feeling mechanism in operating system performance testing in situ testing instrument |
| 基金项目: |
| DOI：10.11823/j.issn.1674-5795.2017.03.07 |
| 引用本文：唐元恒,张玎,刘振岗,邹刚.飞机操纵系统载荷机构原位测试仪的设计[J].计测技术,2017,37(3):39~41. |
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