FADS系统在尖楔前体高超声速飞行器中的应用

Abstract

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.