A Method for Optimizing Structural Parameters of Flute Tubes in Anti-icing System
A technology of structural parameters and anti-icing systems, applied in multi-objective optimization, design optimization/simulation, neural architecture, etc., can solve problems such as slow iteration speed, low efficiency, and high design experience requirements
Active Publication Date: 2022-06-03
LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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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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[0045] In order to make the objectives, technical solutions and advantages of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments.
[0046] like figure 1 As shown, this embodiment provides a method for optimizing structural parameters of a flute pipe of an anti-icing system, including the following steps:
[0047] S100: Determine several structural parameters of the flute tube and the hot gas mass flow, and simultaneously determine several structural parameters of the flute tube and the value range of the hot gas mass flow; the structural parameters of the flute tube include aperture, number of holes, hole spacing, impact Distance, etc., several structural parameters indicate that one or more structural parameters can be selected; of course, the specific structural parameters of the flute pipe include but are not limited to the above list.
[0048] S200: Sampling the structu...
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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. The goal is to minimize the mass flow rate of hot gas, and the surface of the anti-icing system is not icing as a constraint condition, combined with several structural parameters, the maximum thickness of icing, and the lowest temperature as the input layer of the neural network, and the mass flow rate of hot gas as the output layer of the neural network The agent model is obtained through neural network training, and the simulated annealing algorithm is used to optimize the design of the hot gas mass flow rate and structural parameters of the piccolo tube. The present invention reduces the number of numerical simulation sample points required for establishing a proxy model by sampling through the Latin hypercube method, realizes rapid hot gas mass flow rate acquisition by establishing a proxy model, and realizes global search for hot gas mass flow rate and structural parameters by using simulated annealing algorithm Excellent, the entire optimal design method has the advantages of fast and efficient.
Description
technical field [0001] The invention belongs to the technical field of anti-icing and deicing, in particular to a method for optimizing structural parameters of a flute pipe of an anti-icing system. Background technique [0002] When an aircraft passes through a cloud layer containing supercooled water droplets, ice accumulation will occur on its windward surface, and the occurrence of ice accumulation will cause great 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 and the lip of the engine air intake. [0003] Hot air anti-icing is one of the commonly used anti-icing methods for windward surfaces such as the leading edge of the wing and the engine. In this method, high-temperature and high-pressure gas is drawn from the high-pressure compressor of the engine, led to the position requiring protection through the hot gas pipeline, and heat...
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IPC IPC(8): G06F30/17G06F30/15G06F30/27G06N3/04G06F111/06G06F113/08G06F119/08
CPCY02T90/00
Inventor 陈宁立易贤王强柴得林
Owner LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT