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嵌入式大气数据传感系统(Flush Air Data Sensing System,FADS)通过在飞行器表面特定区域布置测压孔测量来流压力,根据建立的气动模型反推得到飞行参数(攻角、侧滑角、马赫数、静压及动压等)。利用在尖楔前体表面三维区中分布测压孔的方法,根据三维区中的流动特征和压力分布规律,建立压力分布与飞行参数之间的关系。试验结果表明,基于三维区理论的FADS系统得到的马赫数误差在5%左右,精度较高。
The Flush Air Data Sensing System (FADS) measures the flow pressure by arranging pressure-measuring holes in a specific area of the aircraft surface. The flight parameters (angle of attack, side slip angle, Mach Number, static pressure and dynamic pressure, etc.). Based on the flow characteristics and pressure distribution in the three-dimensional area, the relationship between pressure distribution and flight parameters is established by means of distributing pressure-measuring holes in the three-dimensional area of the tip wedge surface. The experimental results show that the Mach number error obtained by the FADS system based on the three-dimensional region theory is about 5% and the accuracy is high.