Flush Air Data Sensing System Design and Test for Supersonic Vehicle

In view of the head shape of a typical supersonic vehicle, the array pressure data of the supersonic vehicle is calculated by computational fluid dynamics numerical simulation method. The real-time solution scheme for algorithm model of the flush air data sensing system based on BP neural network technique and FPGA + DSP architecture digital signal processing is designed, which flight Ma number range is from 2.0 to 4.5. The experiment of real-time calculation of the principled sample machine is done in 1.2 m × 1.2 m supersonic wind tunnel. Test results are in good agreement with the measurement results of the wind tunnel system. The system is working without any fatal error in the whole test, which can reflect the flow parameters changes, and has good robustness and agility. Static pressure measurement relative error is ≤6.9%, the Mach number measurement error <0.1, the angle of attack and side slip angle measurement error <1^o.