Method for optimizing structural parameters of flute-shaped pipe of anti-icing system

Abstract

The invention belongs to the technical field of anti-icing and deicing, and particularly relates to a flute-shaped pipe structure parameter optimization method of an anti-icing system. Neural network training is carried out by taking the minimum hot gas mass flow as a target, taking the condition that the surface of an anti-icing system is not iced as a limiting condition, taking a plurality of structure parameters, the iced maximum thickness and the lowest temperature as an input layer of a neural network, and taking the hot gas mass flow as an output layer of the neural network to obtain a proxy model type; and a simulated annealing algorithm is adopted to carry out optimization design on hot gas mass flow and structural parameters of the flute-shaped pipe. According to the method, the number of numerical simulation sample points needed for establishing the proxy model is reduced through sampling of the Latin hypercube method, the hot gas mass flow is rapidly obtained by establishing the proxy model, and global optimization of the hot gas mass flow and structural parameters is achieved by adopting the simulated annealing algorithm; the whole optimization design method has the advantages of rapidness and high efficiency.

Description

technical field [0001] The invention belongs to the technical field of anti-icing and in particular relates to a method for optimizing structural parameters of a flute-shaped pipe of an anti-icing system. Background technique [0002] When an aircraft passes through a cloud layer containing supercooled water droplets, icing will occur on its windward surface, and the occurrence of icing will cause serious harm to the safety of the aircraft. Therefore, it is necessary to design a corresponding anti-icing system on the windward surface of the aircraft, such as the leading edge of the wing, the lip of the engine inlet, and the like. [0003] Hot gas anti-icing is one of the commonly used anti-icing methods for the leading edge of the wing and the windward surface such as the engine. This method leads high-temperature and high-pressure gas from the high-pressure compressor of the engine, leads it to the position that needs to be protected through the hot gas pipeline, and heats...

AI Technical Summary

Problems solved by technology

The final result obtained by this method is only a local optimal solution, which is not the global optimal solution, and the design experience of the designer is relatively high. At the same time, this method needs to carry out a large number of numerical simulation calculations, and the iteration speed is slow and the efficiency is low.

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