Simple and efficient hypersonic flight vehicle FADS system pressure measuring hole layout method

Abstract

The invention discloses a simple and efficient hypersonic flight vehicle FADS system pressure measuring hole layout method. The method comprises the following steps of: defining the initial position of a pressure measuring hole according to an initial conjecture value; calculating the pressure distribution of the head of the aircraft by using CFD; resolving atmospheric data based on the aerodynamic model of the FADS system, repeatedly averaging for multiple times, and comparing with reference data to obtain an error; and calculating a value function, and realizing minimization of a target function through a differential genetic algorithm. The differential genetic algorithm adopted by the invention has the capability of jumping out of the local optimal solution, so that the quality of the obtained optimal solution is more reliable, and global optimization is facilitated; and based on the characteristics, the method can determine the optimal pressure measuring hole position of the hypersonic flight vehicle, so that the measurement precision and the anti-interference capability of the FADS system are improved.

Description

technical field [0001] The invention relates to a method for determining detection points of an embedded air data sensing (Flush Airdata Sensing, FADS) system, in particular to a simple and efficient method for layout of pressure measuring holes of a hypersonic aircraft FADS system. Background technique [0002] The air-breathing hypersonic vehicle powered by the scramjet, due to the integrated fuselage / propulsion system design, the scramjet is extremely sensitive to the angle of attack and requires accurate measurement. The high thermal environment of hypersonic flight limits the application of traditional air data systems based on pitot tubes and windvane angle-of-attack sensors. The FADS system measures parameters such as angle of attack, sideslip angle, dynamic pressure, static pressure, and Mach number through a pressure sensor array installed at the front end of the aircraft head or the leading edge of the wing. Usually, at least four air pressure sensors are arranged...

AI Technical Summary

Problems solved by technology

On the one hand, this method can only optimize the cross-sectional position of the pressure measuring hole (ie figure 2 x-coordinate in ), but the position of the pressure measuring hole on the same section has not been optimized; How to choose the position of the pressure measuring hole

In addition, this method has limitations such as not giving an optimization criterion for the number of pressure measuring holes, and the complexity of the real number product operator increases rapidly with the increase of stations.

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