Small fixed-wing aircraft stall control method based on nonlinear dimension reduction

Abstract

The invention relates to a small fixed-wing aircraft stall control method based on nonlinear dimensionality reduction, and belongs to the technical field of active flow control of small fixed-wing aircrafts. The attack angle of the wing is measured in real time, attack angle data are processed in real time through a nonlinear dimension reduction algorithm, whether the processed attack angle reaches a critical stall attack angle or not is judged, when the attack angle reaches the critical stall attack angle, the synthetic jet piezoelectric pump is controlled to work, low-momentum gas is sucked into a pump cavity from the tail edge of the wing through a flow guide pipeline, and the low-momentum gas is pumped into the pump cavity. And gas is sprayed to the surface of the wing through the flow guide pipeline to inhibit separation of a boundary layer on the surface of the wing, and when the attack angle is gradually reduced from the critical stall attack angle, the aerodynamic performance of the original wing section is kept. The method has the advantages that the measurement attack angle error is reduced, piezoelectric synthetic jet control has higher response speed so as to deal with the sudden stall condition of the aircraft in the air, speed compensation is carried out on the flight attitude under the stall attack angle, and stall of the aircraft is prevented.

Description

technical field [0001] The invention belongs to the technical field of active flow control of small fixed-wing aircraft, in particular to a synthetic jet stall control method for small fixed-wing aircraft based on a nonlinear dimensionality reduction algorithm, Background technique [0002] Generally speaking, the flight Reynolds number of a small fixed-wing aircraft is about 10,000-100,000, which makes the laminar flow dominate and the viscous force plays a significant role during flight. When the flight angle of attack increases, the pressure on the upper wing surface When the gradient reverses, the boundary layer separation is severe, causing the aircraft to stall. Therefore, in order to prevent the stall caused by the separation of the boundary layer of the upper airfoil, the speed of the upper airfoil needs to be increased to compensate for the speed loss caused by the reversal of the pressure gradient. [0003] Synthetic jet technology is an active control technology ...

AI Technical Summary

Problems solved by technology

[0005] The present invention provides a small fixed-wing aircraft stall control method based on nonlinear dimensionality reduction to solve the problem that small fixed-wing aircraft are prone to stall during low-speed and high-angle-of-attack flight

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