飞机空速校准用静压测量装置轮廓结构绕流影响分析  

Analysis of Impact of Flow Around Caused by Profile of Static Pressure Measurement Device for Aircraft Airspeed Calibration

作　　者：刘笃喜[1] 王新刚[1] 朱云龙[1] 张森[1] 

机构地区：[1]西北工业大学空天微纳系统教育部重点实验室,西安710072

出　　处：《计算机测量与控制》2014年第6期1887-1889,1911,共4页Computer Measurement &Control

基　　金：航空科学基金项目(2011ZD53044)

摘　　要：介绍了针对一种面向飞机空速校准的外置式静压测量方法,为了减小测量装置轮廓结构绕流对静压测量的影响,从而提高静压测量精度,应用FLUENT对装置轮廓结构进行绕流影响分析,得到绕流影响最小的轮廓结构类型,并采用正交试验方法对收缩角度β、过渡长度L、最大直径ΦD、最小直径Φd共4个参数进行优化;仿真结果表明,测量装置轮廓采用圆弧型收缩过渡结构绕流影响最小,轮廓最大直径和过渡长度对静压测量绕流影响较为显著;最优参数组合为:β=33°,L=40mm,ΦD=50mm,Φd=22mm,优化后的结构对静压管的绕流影响减小了37.5%,提高了静压测量精度。Outboard static pressure measurement method was proposed for aircraft airspeed calibration. In order to reduce the impact of flow around caused by profile of the measurement device and to improve static pressure measurement accuracy, we analyze the impact of flow with commercial software package, FLUENT. From our analysis, the types of transitional structures with the minimum flow range are ob- tained. Then the structural geometric include contraction angle 13, transition length L, maximum diameter ФD, minimum diameter Фd are op- timized based on the orthogonal test design method. It shows that the optimum structure shape is arc transitions the maximum diameter and transition length of the profile produce significant impact on air flows the optimal combination of parameters isβ= 33°, L= 40mm, ФD= 50mm, Фd=22mm. And by optimization, the structure has reduced the impact of flow around by 37.5% for the static pressure tube and greatly improved static pressure measurement accuracy.

关 键 词：静压测量装置 绕流 轮廓结构 正交试验 

分 类 号：V248.1[航空宇航科学与技术—飞行器设计]