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NSGAII-based multi-objective optimization decision-making method for stratospheric aerostat

A technology of multi-objective optimization and decision-making method, which is applied in the field of multi-objective optimization and decision-making of stratospheric aerostats based on NSGA II, and can solve problems such as structural optimization of stratospheric aerostats

Active Publication Date: 2016-12-21
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
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Problems solved by technology

[0006] Purpose of the invention: In order to overcome the deficiencies in the prior art, the present invention provides a multi-objective optimization decision-making method for stratospheric aerostats based on NSGAⅡ, which intends to solve the structural optimization problem of stratospheric aerostats

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  • NSGAII-based multi-objective optimization decision-making method for stratospheric aerostat

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Embodiment

[0111] The beneficial effects of the inventive method can be verified by the following simulation experiments. Known conditions: Assume that the aerostat is flying at a fixed point at an altitude of 20km. Air density ρ at 20km a0 0.088035kg / m 3 , Density ρ of normal temperature air a 1.29kg / m 3 , helium density ρ He 0.169kg / m 3 , pressure coefficient C p =0.33; major axis L=a 1 +a 2 =170m; minor axis D=2b=60m; a 2 / a 1=2; set the film material density to 432g / m 3 ,, the Poisson's ratio of the membrane material is 0.33, assuming that the membrane material is an isotropic material, the elastic modulus E=1.055×10 9 N / m 2 .

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Abstract

The invention discloses an NSGAII-based multi-objective optimization decision-making method for a stratospheric aerostat. The method comprises the following steps of (1) building a stratospheric aerostat model, wherein the stratospheric aerostat model is a bielliptical geometric model composed of two semiellipsoids; (2) selecting skin volume, a resistance coefficient and a maximum loop stress of the aerostat as optimization objectives, and selecting skin thickness and a geometric slenderness ratio of the aerostat as optimization variables according to the built aerostat model; (3) performing optimization calculation on the aerostat model by using a multi-objective evolution algorithm, and performing continuous iteration to obtain a non-inferior solution of Pareto front; (4) performing decision-making analysis on an optimization result by adopting a fuzzy entropy weight-based TOPSIS (Technique for Order Preference by Similarity to Ideal Solution) method; and (5) determining an optimal scheme by adopting the TOPSIS method. According to the method, a relatively optimal scheme closest to a positive ideal solution and far away from a negative ideal solution is obtained through the fuzzy entropy weight-based TOPSIS multi-attribute decision-making method.

Description

technical field [0001] The invention belongs to the technical field of stratospheric aerostats, and in particular relates to a multi-objective optimization decision-making method for stratospheric aerostats based on NSGA II. Background technique [0002] The stratosphere refers to the atmosphere in the 20-50 km range of the atmosphere. The air flow in the stratosphere is stable, and it is suitable for deploying tasks such as air surveillance and early warning platforms, relay communications, and environmental monitoring. A stratospheric aerostat is an aircraft that works in the stratosphere and mainly uses gas lighter than air to generate net lift to overcome its own gravity. Due to its unique advantages such as low operating cost, long time in the air, strong load capacity, and good safety, it has a large development space and broad application fields. However, general stratospheric aerostats require a larger airbag volume to provide sufficient static lift to maintain flig...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/23Y02A90/10Y02T90/00
Inventor 陈川胡宇群陈佳慧刘伟毕苏艺
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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