基于CFD方法的前支杆试飞测量装置误差分析  

Error Analysis on Noseboom Flight Test Instrument Based on CFD Method

作　　者：马玉敏 汪发亮 徐倩 郭洁 MA Yu-min;WANG Fa-liang;XU Qian;GUO Jie(AVIC the First Aircraft Institute,Xi'an 710089,China;Xi'an Aircraft Certification Center,CAAC,Xi'an 710065,China;AVIC XAC Commercial Aircraft Co.,Ltd.,Xi'an 710089,China)

机构地区：[1]航空工业第一飞机设计研究院,陕西西安710089 [2]中国民用航空适航审定中心西安航空器审定中心,陕西西安710065 [3]中航西飞民用飞机有限责任公司,陕西西安710089

出　　处：《测控技术》2021年第8期76-80,共5页Measurement & Control Technology

摘　　要：准确可靠的大气数据信息对飞行器的安全至关重要。处于研制阶段的大气数据系统往往存在一定程度的误差,需要在试飞阶段予以校准。试验机上加装的试飞测量装置要求尽可能地接近未受扰动的气流,同时减少对飞机已有大气数据系统的影响。采用计算流体力学方法,对某型民机进行数值模拟,确定了前支杆试飞测量装置的安装位置和长度,获得了前支杆的位置误差并评估了对飞机已有大气数据系统的影响。研究表明,选定前支杆长度情况下,前支杆测量的静压测量误差引起的高度误差偏大,对现有大气数据系统静压亦有一定影响,对迎角影响较小。这一结果可作为某型民机确定空速校准方法的依据,亦可作为其他飞机在空速校准方案选用方面的参考。Accurate and reliable atmospheric data information is very important to the safety of aircraft.The air data system in the development stage often has some errors,which needs to be calibrated in the flight test stage.The flight test measurement device installed on the test aircraft should be close to the undisturbed air flow as far as possible,and reduce the impact on the existing air data system of the aircraft.By using computational fluid dynamics(CFD)method,a civil aircraft is simulated.The installation position and length of the noseboom flight test measurement device are determined.The position error of the noseboom is obtained and the influence on the existing air data system of the aircraft is evaluated.The results show that when the length of the front strut is selected,the height error caused by the static pressure measurement error of the noseboom is larger,which also has a certain impact on the static pressure of the existing air data system,and has a small impact on the angle of attack.This result can be used as the basis for determining the airspeed calibration method of a certain type of civil aircraft,and also as a reference for other aircraft in the selection of airspeed calibration scheme.

关 键 词：飞行试验 大气数据 计算流体力学 前支杆 民用运输机 

分 类 号：V217[航空宇航科学与技术—航空宇航推进理论与工程]