运输类飞机弹性体和刚体离散突风动载荷比较分析  

Comparative Analysis of Flexible and Rigid Body Dynamic Discrete Gust Loads of Transport Aircraft

作　　者：谢卫杰 孙小平 童亚斌 XIE Weijie;SUN Xiaoping;TONG Yabin(Institute of Aircraft Design,Xi’an Aircraft Industry(Group)Co.,Ltd.,Xi’an 710089,China;Military Representatives Agency of Xi’an Office,Air Force Equipment Department,Xi’an 710089,China;Engineer Technology Center,XAC Commercial Aircraft Co.,Ltd.,Xi’an 710089,China)

机构地区：[1]西安飞机(集团)股份有限公司西飞设计院,陕西西安710089 [2]空装西安局军事代表室,陕西西安710089 [3]西飞民用飞机有限责任公司工程技术中心,陕西西安710089

出　　处：《飞机设计》2021年第2期22-27,共6页Aircraft Design

摘　　要：各类适航规范都要求在突风动响应载荷计算中考虑飞机弹性模态的影响,而弹性体和相应的刚体飞机的突风动响应载荷计算之间存在着紧密的联系。为了研究这2种计算方法间的区别和联系,首先对突风载荷计算理论基础进行了分析,然后结合某型常规布局飞机载荷计算数据在数值结果方面进行了进一步的比较分析。分析结果表明,对此常规布局飞机而言,弹性体飞机突风动响应载荷主要表现为刚体模态响应载荷和弹性体模态响应载荷的线性叠加,广义气动力矩阵中刚体模态和弹性模态耦合的存在不会引起太大的畸变;弹性模态对惯性载荷影响较大,而对总气动力载荷的影响则较小。All kinds of airworthiness regulations require that the elastic modes of the airplane must be taking into account in the dynamic gust load calculation.Besides,there is an inextricable connection between the dynamic gust load calculation of flexible airplane and its rigid counterpart.To study the differences and relationships of these two kinds of approaches,the basic theory of gust load calculation is analyzed at first.Then,comparative analysis is carried out on the numeric results according to the data calculated for the dynamic gust load of one regular overall arrangement airplane.According to the analysis and research,it is found that for the regular overall arrangement airplane,the dynamic load of the flexible airplane could be represented as the linear superposition of load of rigid mode responses and flexible mode responses,and the existence of non-diagonal partial matrices of the generalized aerodynamic matrix which represent coupling between rigid mode freedoms and flexible mode freedoms would not produce notable distortion.It is also found that flexible modes have significant influence on inertial load,but little influence on aerodynamic load.

关 键 词：动响应载荷 突风载荷 弹性体飞机载荷 刚体飞机载荷 动态载荷放大 

分 类 号：V214.1[航空宇航科学与技术—航空宇航推进理论与工程]