本文選題：蜂窩芯結(jié)構(gòu) + 穩(wěn)定性分析　； 參考：《中國科學(xué)技術(shù)大學(xué)》2015年碩士論文

【摘要】：在當(dāng)今航空、航天領(lǐng)域研究中,飛行器的智能變體技術(shù)是研究熱點(diǎn),同時因其結(jié)構(gòu)特性以及適應(yīng)飛行環(huán)境的苛刻需求,也使得智能變體技術(shù)的研究成為技術(shù)難點(diǎn)。從早期的“類魚鱗狀疊片式”傳統(tǒng)剛性蒙皮到現(xiàn)今的復(fù)合材料蒙皮結(jié)構(gòu),蒙皮的變形技術(shù)正在向應(yīng)用智能復(fù)合材料結(jié)構(gòu)的方向演進(jìn)。隨著蜂窩復(fù)合夾層結(jié)構(gòu)材料在生產(chǎn)和生活中的廣泛應(yīng)用,其結(jié)構(gòu)自身的優(yōu)良特性表現(xiàn)的越來越突出。在上述的大背景下,本實(shí)驗課題組將蜂窩夾層結(jié)構(gòu)引入到變體飛行器的蒙皮結(jié)構(gòu)設(shè)計,同時引入柔性機(jī)構(gòu)的理念。通過分析蜂窩夾芯結(jié)構(gòu)的拓?fù)錁?gòu)型和尺寸參數(shù)對自身結(jié)構(gòu)性能的影響規(guī)律,以期得到其應(yīng)用于超彈性蒙皮結(jié)構(gòu)變形時,其對蒙皮氣動性能的影響規(guī)律。本文系統(tǒng)地分析了蜂窩夾芯板結(jié)構(gòu)的國內(nèi)外研究現(xiàn)狀和發(fā)展趨勢,對蜂窩夾芯板結(jié)構(gòu)的力學(xué)性能及穩(wěn)定性進(jìn)行初步研究。以應(yīng)用于變體飛行器蒙皮結(jié)構(gòu)設(shè)計中的蜂窩芯結(jié)構(gòu)為研究對象,在經(jīng)典的Gibson公式和Euler梁理論的基礎(chǔ)上,在滿足機(jī)翼實(shí)現(xiàn)連續(xù)變體所需的低共面模量和高異面剛度的基礎(chǔ)上,建立柔性蜂窩芯結(jié)構(gòu)的參數(shù)優(yōu)化模型。借助智能算法對特定蜂窩芯單元選型參數(shù)進(jìn)行多目標(biāo)優(yōu)化設(shè)計,得到了不同蜂窩芯結(jié)構(gòu)的選型參數(shù)對各自面內(nèi)變形能力的影響規(guī)律,進(jìn)行蒙皮蜂窩芯結(jié)構(gòu)的選型分析,并開展了蜂窩芯板結(jié)構(gòu)的變形驅(qū)動方案設(shè)計。 本文的主要內(nèi)容如下： 1.對自適應(yīng)機(jī)翼技術(shù)、蜂窩復(fù)合材料的國內(nèi)外研究現(xiàn)狀進(jìn)行了介紹和總結(jié),闡述了論文的來源及研究意義。 2.對蜂窩夾層結(jié)構(gòu)的自由振動及穩(wěn)定性進(jìn)行了分析,得出了芯板結(jié)構(gòu)的彎曲平衡方程和屈曲基本方程。 3.在滿足機(jī)翼實(shí)現(xiàn)連續(xù)變體所需的低共面模量和高異面剛度的基礎(chǔ)上,確定柔性蜂窩芯結(jié)構(gòu)的參數(shù)優(yōu)化模型的邊界條件及其相應(yīng)目標(biāo)函數(shù),得到蜂窩芯結(jié)構(gòu)參數(shù)優(yōu)化數(shù)學(xué)模型。 4.借助遺傳算法對特定蜂窩芯單元選型參數(shù)進(jìn)行多目標(biāo)優(yōu)化設(shè)計,得到了不同蜂窩芯結(jié)構(gòu)的選型參數(shù)對面內(nèi)變形能力的影響規(guī)律,并進(jìn)行蒙皮蜂窩芯結(jié)構(gòu)的選型分析。 5.基于理論和優(yōu)化仿真研究,開展了對柔性蜂窩芯彈性蒙皮的結(jié)構(gòu)設(shè)計,提出了基于正、負(fù)泊松比蜂窩芯板組合的機(jī)翼蒙皮結(jié)構(gòu)驅(qū)動設(shè)計方案。
[Abstract]:In the field of aeronautics and spaceflight, the intelligent variant technology of aircraft is a hot research topic. At the same time, due to its structural characteristics and harsh requirements to adapt to the flight environment, the research of intelligent variant technology has become a technical difficulty. From the early "fish-like laminated" traditional rigid skin to the present composite skin structure, the deformation technology of the skin is evolving towards the application of intelligent composite structure. With the wide application of honeycomb sandwich materials in production and daily life, the excellent properties of honeycomb sandwich structures are becoming more and more outstanding. Under the above background, the honeycomb sandwich structure is introduced into the design of the skin structure of the variant aircraft, and the concept of flexible mechanism is introduced at the same time. By analyzing the influence of the structure parameters and topological configuration of honeycomb sandwich structure on the structural properties of honeycomb sandwich structure, the effect of the structure on the aerodynamic performance of the skin is obtained when it is applied to the deformation of the superelastic skin structure. In this paper, the present situation and development trend of honeycomb sandwich panel structure at home and abroad are systematically analyzed, and the mechanical properties and stability of honeycomb sandwich panel structure are studied preliminarily. Based on the classical Gibson formula and the Euler beam theory, the honeycomb core structure used in the design of the skin structure of the variant aircraft is studied. On the basis of satisfying the low coplanar modulus and the high cross-plane stiffness required for the wing to realize the continuous variant, the honeycomb core structure is studied. The parameter optimization model of flexible honeycomb core structure is established. With the help of intelligent algorithm, the multi-objective optimization design of the selection parameters of specific honeycomb core units is carried out, and the influence of the selection parameters of different honeycomb core structures on their in-plane deformation capacity is obtained, and the selection and analysis of the skin honeycomb core structures are carried out. The deformation-driven scheme of honeycomb core board structure is designed. The main contents of this paper are as follows: 1. The research status of adaptive wing technology and honeycomb composite materials at home and abroad are introduced and summarized. The origin and significance of this paper are described. 2. The free vibration and stability of honeycomb sandwich structure are analyzed. The bending equilibrium equation and buckling basic equation of core plate structure are obtained. 3. On the basis of satisfying the low coplanar modulus and high cross-plane stiffness of the wing to realize the continuous variation, the boundary conditions and the corresponding objective functions of the parameter optimization model of the flexible honeycomb core structure are determined, and the mathematical model of the parameter optimization of the honeycomb core structure is obtained. 4. By means of genetic algorithm, the multi-objective optimization design of specific honeycomb core unit selection parameters is carried out, and the influence law of different honeycomb core selection parameters is obtained, and the selection analysis of skin honeycomb core structure is carried out. 5. Based on the theory and optimization simulation, the structure design of flexible honeycomb core elastic skin was carried out, and the drive scheme of wing skin structure based on the combination of positive and negative Poisson's ratio honeycomb core was proposed.
【學(xué)位授予單位】：中國科學(xué)技術(shù)大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2015
【分類號】：TB383.4

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