摘要
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 aerodynamic model for flush air data sensing system （FADS） is built based on the surface pressure distribution obtained through the pressure orifices laid on specific positions of the surface, and the flight parameters, such as angle of attack, angle of side-slip, Math number, free-stream static pressure and dynamic pressure are inferred from the aerodynamic model. The relationship between the surface pressure and flight parameters through three-dimensional theory is built. The results show that the error for Mach number is about 5% through FADS system.
出处
《战术导弹技术》
2013年第1期28-31,共4页
Tactical Missile Technology
