民用飞机静压孔气动布局设计

Design of civil aircraft's static source aerodynamic layout

民用飞机根据静压、总压等基本测量参数,通过大气数据计算机解算得到飞机飞行的高度、速度等,因此静压测量的精确度对飞机安全性至关重要,而静压孔的气动布局直接关系到静压测量精度。对于亚声速民机,机身表面静压孔测量静压主要受飞机马赫数、迎角和构型的影响。根据CFD计算结果,采用均方差方法,确定飞机机身表面静压随马赫数和迎角变化不敏感的区域,结合飞机实际机体结构或其他设备布置的限制,确定了静压孔布局位置。采用风洞试验方法,验证静压孔测量特性,试验测量襟缝翼、扰流板、起落架以及地面效应对静压孔测量的影响量,为飞机静压修正提供重要输入。

Civil aircraft obtains the flight height, speed, etc. by the air data computer with the measured static pressure, total pressure and other basic parameters as input. Therefore, the flight safety strongly depends on the accuracy of the static pressure measurement which is related to the aerodynamic layout of the static ports. For subsonic civil aircrafts, the pressures measured by static ports are mainly affected by the Mach number, angle of attack（AOA） and the configuration of the aircraft. Based on CFD results, the positions of static ports are determined by the mean square deviation method. The measurement characteristics of static ports and the disturbances on measurement due to the flap/slat, spoiler, landing gear and ground effect which are essential inputs for the static source error correction （SSEC） were obtained by wind tunnel tests.