飞机载荷校准试验主动约束技术
Active constraint technology on aircraft load calibration test
李文龙 1吴波 1何乐儒 1张海涛1
作者信息
- 1. 中国飞行试验研究院,西安 710089
- 折叠
摘要
在研究以往飞机载荷校准试验支持和约束方式的基础上,结合某型飞机结构特点,提出一种载荷校准主动约束方法.对主动约束方法和传统的起落架方法飞机载荷校准进行受力分析,建立了 2 种约束方法的理论模型;设计2 种约束方法的机翼载荷校准对比试验,并提出主动约束载荷校准试验实施流程;结合某型飞机机翼载荷校准试验和飞行试验对主动约束方法进行了验证.结果表明:与传统的起落架约束方法相比,主动约束方法能有效解决有起落架布置的翼身整体结构机翼根部载荷测量难题,并将机翼载荷校准试验量级提高41%,机翼载荷模型误差可控制在3%以内.
Abstract
Based on the previous research of aircraft load calibration tests with support and constraint methods,and considering the structural characteristics of an aircraft,an active constraint method for load calibration was proposed.Firstly,force analysis of aircraft load calibration was conducted on the active constraint method and traditional landing gear constraint method,and theoretical models of the two constraint methods were established.Secondly,two constraint methods for wing load calibration comparison tests were designed,and an implementation process for active constraint load calibration test was proposed.Finally,the active constraint method was validated effectively by combining wing load calibration test and flight test of an aircraft.Compared with traditional landing gear constraint method,the result showed that the active constraint method solved the problem of measuring the wing root section load on wing-body integrated structure with landing gear layout.And the magnitude of the wing load calibration test was increased by 41%,and the error of the wing load model can be controlled within 3%.
关键词
飞机载荷校准试验/主动约束/载荷量级/载荷模型精度/飞行试验Key words
aircraft load calibration test/active constraint/load magnitude/load model accuracy/flight test引用本文复制引用
出版年
2024
NETL
NSTL
万方数据