飞机结构强度试验系统PID控制参数自整定技术  

PID Control Parameter Self-Tuning Technology for Aircraft Structural Strength Test System

作　　者：王刚[1] 谢文娇 尹伟[1] 赵洪伟[1,3] 米征 宋鹏飞[1] 张革命[1] WANG Gang;XIE Wenjiao;YIN Wei;ZHAO Hongwei;MI Zheng;SONG Pengfei;ZHANG Geming(National Key Laboratory of Strength and Structural Integrity,Aircraft Strength Research Institute of China,Xi′an 710065,Shaanxi,China;Aviation Industry Corporation of China,Beijing 100000,China;Xi′an Jaotong University,Xi′an 710000,Shaanxi,China)

机构地区：[1]中国飞机强度研究所,强度与结构完整性全国重点实验室,陕西西安710065 [2]中国航空工业集团有限公司,北京100000 [3]西安交通大学机械工程学院,陕西西安710000

出　　处：《工程与试验》2025年第1期13-16,63,共5页Engineering and Test

摘　　要：飞机结构试验是新机研制的主要环节之一。PID控制参数主要是通过人工经验试凑获得,参数整定效率偏低。在低载下进行整定,获得的PID参数不适合中高载荷情况,影响试验运行。针对此问题,本文以试验系统为研究对象,开发算法辨识了系统模型,并建立试验系统模型,通过仿真验证了辨识模型的合理性。基于辨识理论,通过Zeigler-Nichols方法,利用试验控制系统输入输出数据拟合控制传递函数,自动整定PID参数,为结构强度试验PID整定提供了理论指导。Aircraft structure test play a key role in the development of new aircraft.The PID control parameters are mainly obtained by manual experience,and the parameter tuning efficiency is low.The PID parameters obtained by tuning under low load are not suitable for medium and high load conditions,which affects the test operation.To solve the problem,the test system is taken as the research object,and an algorithm is developed to identify the system model.The test system model is established,and the rationality of the identification model is verified through simulation.Based on the identification theory,the Zeigler-Nichols method is used to fit the control transfer function with the input and output data of the test control system,and the PID parameters are automatically tuned,which provides theoretical guidance for the PID tuning of structural strength test.

关 键 词：试验系统 力加载 PID自整定 控制参数 

分 类 号：V216.1[航空宇航科学与技术—航空宇航推进理论与工程]