FADS系统在尖楔前体高超声速飞行器中的应用

对于具有尖楔前体的高超声速飞行器，特别是某些验证超燃发动机项目的飞行器，仅仅依靠惯性导航系统（Inertial Navigation System，INS）得到的攻角不能满足其精度要求．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）．对于FADS／INS组合系统，本文首次提出了采用切楔斜激波理论建立其气动理论模型，攻角经过校准后精度较高（误差小于0．1°）；对于FADS系统，运用二维区及三维区理论建立其气动理论模型，马赫数误差在5％左右．验证结果表明FADS系统在具有尖楔前体的高超声速飞行器上应用前景广阔．

Application of FADS system in hypersonic flight vehicles with sharp wedged fore-bodies

For some hypersonic flight vehicles with sharp wedged fore-bodies, especially for those which are used to verify supersonic combustion ramjet technology, the precision of angle of attack will not be achieved only through Inertial Navigation System （INS）. 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, Mach number, free-stream static pressure and dynamic pressure are inferred from the aerodynamic model. For FADS/INS integrated system, angle of attack can be determined through aerodynamic model we have firstly built based on oblique shock wave theory, and the error for angle of attack is accurate enough （〈0.1 °）. For FADS system alone, the flight parameters can be determined through aerodynamic model based on two and three dimensional flow theory, and the error for Mach number is about 5%. The results show that FADS system can be applied widely in hypersonic flight vehicles with sharp wedged fore-bodies.