飞机操纵系统载荷机构原位测试仪的设计  

Design of an In-Situ Testing Instrument for Load Feeling Mechanism in Operating System of Aircrafts

作　　者：唐元恒[1] 张玎[1] 刘振岗[1] 邹刚[1] 

机构地区：[1]海军航空工程学院青岛校区航空机械系,山东青岛266041

出　　处：《计测技术》2017年第3期39-41,共3页Metrology & Measurement Technology

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。Based on modern measuring and controlling theory and technology,an＂in-situ testing instrument for load feeling mechanism in operating system of aircrafts＂is designed against heavy workload and long periodicity caused by dislocation performance testing of load feeling mechanism in operating system in aircrafts. It applies sensors,PLC and a 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 the curve is compared with standard operating characteristic curve,and the 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,and in-situ and auto testing.

关 键 词：飞机 操纵系统载荷机构 性能检测 原位测试仪 

分 类 号：TP23[自动化与计算机技术—检测技术与自动化装置] V267[自动化与计算机技术—控制科学与工程]