飞机尾翼压力中心位置的计算  

The Calculation on Tail Pressure Center of Aircraft

作　　者：郭天天 孟新意 刘伟 杨全 GUO Tiantian;MENG Xinyi;LIU Wei;YANG Quan(Xi’an Aircraft Industry Group Company,Ltd.,Xi’an 710089,China)

机构地区：[1]西安飞机工业集团股份有限公司,陕西西安710089

出　　处：《飞机设计》2021年第3期20-22,29,共4页Aircraft Design

摘　　要：目前,我国飞机尾翼压力中心计算所参考的规范和方法主要有FQG(S)《飞机强度设计规范》(1975年版)和《尾翼强度设计指南》,选取不同的规范和方法计算得到的尾翼压力中心位置不同,所得到的尾翼载荷大小也有所区别。为了和飞机设计规范中的估算方法进行对比分析和讨论,介绍了一种基于全机压力分布数值计算(以下简称CFD计算)的飞机尾翼压力中心位置的计算方法。本方法关于飞机尾翼压力中心位置的计算讨论,对尾翼气动力设计优化有重要的反馈评估作用。Introduces a calculation method of the pressure center position of the tail wing based on the calculation of the pressure distribution of the whole aircraft(referred to as CFD calculation),The purpose of the design is to compare and discuss with the estimation methods in the aircraft design specifications.At present,the main specifications for the calculation of the pressure centre of aircraft tail in China are as follows:FQG(S)《Code for design of Aircraft Strength》and《Tail Strength Design Guideline》.Different codes and methods are used to calculate the pressure centre position of the tail,and the tail load obtained is also different.This method is about the calculation and discussion of the pressure centre position of the aircraft tail,it plays an important role in feedback evaluation of aerodynamic design optimization of tail.

关 键 词：压力中心 载荷分布 飞机强度设计规范 尾翼强度设计指南 CFD计算 

分 类 号：V211.8[航空宇航科学与技术—航空宇航推进理论与工程]