Fusing method of atmospheric attack angle and inertia attack angle in transonic flight stage

Abstract

The invention discloses a fusing method of an atmospheric attack angle and an inertia attack angle in transonic flight stage. The fusing method comprises the following steps of: firstly, data acquisition; secondly, transonic flight stage judgment; thirdly, inertia attack angle solution; fourthly, complementary filtering fusing; and fifthly, BP neural network correction. Through a complementary filter, the method inhibits impact wave interference fluctuation of the atmospheric attack angle, and enables complementary fused attack angles to eliminate fierce fluctuation and become stable. Further, by utilizing a favorable learning ability and a non-linear approximation property of the neural network, the method ensures a better anastomosis degree between a real attack angle and a final fused modified attack angle which is treated by the neural network, and enables whole precision and reliability of the attack angle to be improved further. By replacing a primary atmospheric attack angle in the transonic flight stage with the fused modified attack angle, the invention can effectively improve whole precision of the attack angle during flight, and provides a beneficial foundation of accurate navigation and flight control.

Description

technical field [0001] The invention relates to an angle of attack information fusion method of an atmospheric and inertial navigation system, and belongs to the technical field of flight angle of attack information fusion and correction methods. Background technique [0002] During the flight, the flight angle of attack is an important parameter affecting the lift and drag of the aircraft. It is a necessary parameter for the flight control and navigation system. It is also the key data required for the aircraft out of control or stall alarm. Safety. [0003] Transonic refers to a transition process between subsonic and supersonic speeds. As aviation continued to grow, the term "transonic" did not come into common use until the mid-1940s. When the aircraft is flying at transonic speed, due to the impact of shock waves and other factors, the performance and indicators of the aircraft will be seriously reduced, and the error will increase, which will bring inconvenience to t...

AI Technical Summary

Problems solved by technology

[0009] The purpose of the present invention is to provide a method to solve the problem that the flight angle of attack measured by the aircraft under the condition of transonic speed is seriously affected by the shock wave interference in order to obtain relatively stable, reliable and high-precision measurements under the condition of transonic flight. Flight angle of attack information, that is, the fusion method of atmospheric angle of attack and inertial angle of attack during transonic flight

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