民用飞机开环和闭环情况突风载荷对比研究  

COMPARATIVE STUDY OF GUST LOAD ON CIVIL AIRCRAFT IN OPEN LOOP AND CLOSED LOOP CONDITIONS

作　　者：刘晓晨 杜云龙 LIU Xiaochen;DU Yunlong(Shanghai Aircraft Design and Research Institute,Shanghai 201210,China)

机构地区：[1]上海飞机设计研究院,上海201210

出　　处：《力学与实践》2024年第2期273-279,共7页Mechanics in Engineering

摘　　要：以某民用飞机为研究对象,建立了飞机的突风计算模型,并搭建引入了相应的控制律模型,分别对开环和闭环情况下的离散突风载荷进行了计算对比,同时研究了不同计算输入下主要升力面突风增量载荷的差异和原因。研究表明,载荷设计中考虑控制律之后会对飞机不同部件的突风载荷产生一定的影响,具体计算结果与控制律设计逻辑相关。同时,不同计算输入情况下的计算结果差异较大且存在一定规律,通过及早进行变参数分析可以很好地提升突风载荷设计和评估效率。In this paper,we take a civil aircraft as the research object,establish a gust calculation model for the aircraft,and introduce corresponding control law models to calculate and compare discrete gust loads under open loop and closed loop conditions.At the same time,the differences and reasons for the gust incremental loads on the main lift surface under different calculation inputs are studied.Research has shown that considering control laws in load design can have a certain impact on the gust loads of different components of the aircraft,and the specific calculation results are related to the logic of control law design.At the same time,there are significant differences and certain patterns in the calculation results under different calculation inputs.Early variable parameter analysis can effectively improve the efficiency of gust load design and evaluation.

关 键 词：民用飞机 突风载荷 控制律 突风梯度 

分 类 号：V211.47[航空宇航科学与技术—航空宇航推进理论与工程]