摘要
全尺寸飞机疲劳试验中,机翼加载部位常因为瞬时流量不足或加载点间耦合等因素,出现反馈滞后指令过多而导致加载精度及运行速度降低的情况,传统PID控制器此时已无法满足试验需求。通过对全尺寸飞机疲劳试验飞行谱编制形式以及微分前馈PID控制器的工作原理进行分析,并通过搭建验证试验,验证微分前馈PID控制器在疲劳试验中的应用。结果表明,微分前馈参数能够降低加载及采集过程中的误差,提高试验加载精度及运行速度,但当参数过大时,会对采集过程前及采集过程中加载精度产生严重影响。
In the Full-scale aircraft fatigue test,large deformations loading parts such as wing usually due to insufficient instantaneous or load point coupling,excessive feedback lagging instruction can result in reduction of load accuracy and speed,traditional PID controller cannot be able to meet test requirements.Through analysis the compilation of profile and working principle of differential feedforward PID controller,test is built to verify the impact on fatigue test.The results show differential feedforward parameter can reduce errors during loading and acquisition,improve test loading accuracy and running speed,but when the parameter is too large,it will have a serious impact on the loading accuracy before and during the acquisition process.
作者
牧彬
米征
Mu Bin;Mi Zheng(Aircraft Strength Research Institute Aircraft Strength Research Institute of AVIC Full Scale Aircraft Structural Static/Fatigue Lab,Xi’an Shaanxi 710065,China)
出处
《工程与试验》
2019年第4期113-115,共3页
Engineering and Test
关键词
疲劳试验
微分前馈
飞行谱编制
fatigue test
differential feedforward
profile compilation
作者简介
牧彬(1989-),男,陕西渭南人,工学硕士,工程师,主要研究方向为全尺寸飞机静力/疲劳试验控制技术与仿真。
