【摘要】：反對(duì)稱鋪設(shè)復(fù)合材料圓柱殼結(jié)構(gòu)具有兩種不同穩(wěn)定狀態(tài),可以通過(guò)機(jī)械載荷、智能材料或者溫度場(chǎng)等外在驅(qū)動(dòng)方式進(jìn)行穩(wěn)態(tài)之間的轉(zhuǎn)變,因此被稱為雙穩(wěn)態(tài)復(fù)合材料結(jié)構(gòu)(Bi-stable Composite Structure)。雙穩(wěn)態(tài)復(fù)合材料結(jié)構(gòu)具有輕質(zhì)、承載能力優(yōu)異以及可變形等特點(diǎn),在航空航天的可變形機(jī)構(gòu)和風(fēng)力發(fā)動(dòng)機(jī)葉片等諸多領(lǐng)域具有廣泛的應(yīng)用前景。當(dāng)雙穩(wěn)態(tài)復(fù)合材料結(jié)構(gòu)處于各種復(fù)雜的、極端的工作環(huán)境時(shí),溫度對(duì)結(jié)構(gòu)的雙穩(wěn)態(tài)特性影響較大。目前,對(duì)于溫度影響下反對(duì)稱鋪設(shè)圓柱殼結(jié)構(gòu)的研究較少,限制了其在實(shí)際應(yīng)用中的發(fā)展。本文采用理論推導(dǎo)、實(shí)驗(yàn)測(cè)試和有限元模擬等方法,研究了溫度對(duì)反對(duì)稱鋪設(shè)圓柱殼結(jié)構(gòu)的雙穩(wěn)態(tài)特性影響機(jī)理,得到了環(huán)境溫度(整體溫度場(chǎng))、局部溫度場(chǎng)以及溫度梯度影響下圓柱殼穩(wěn)態(tài)間相互轉(zhuǎn)變過(guò)程、突變載荷和變形情況,并利用溫度影響規(guī)律對(duì)結(jié)構(gòu)變形進(jìn)行了主動(dòng)調(diào)控。最后,從宏觀、微觀角度對(duì)熱暴露下雙穩(wěn)態(tài)結(jié)構(gòu)變形特性進(jìn)行了討論和解釋。主要研究?jī)?nèi)容和成果如下:1.在經(jīng)典層合板理論的基礎(chǔ)上,利用最小勢(shì)能原理推導(dǎo)了溫度影響下的反對(duì)稱鋪設(shè)圓柱殼結(jié)構(gòu)的雙穩(wěn)態(tài)理論模型。在理論上預(yù)測(cè)了包括整體溫度場(chǎng)和溫度梯度的變化對(duì)反對(duì)稱鋪設(shè)圓柱殼結(jié)構(gòu)的曲率的影響規(guī)律,并討論了影響扭曲率變化的因素。2.采用實(shí)驗(yàn)方法,利用經(jīng)改裝的帶有溫控箱的拉伸試驗(yàn)機(jī)測(cè)試平臺(tái)和自主研發(fā)的數(shù)字圖像處理技術(shù),得到溫度影響下的反對(duì)稱鋪設(shè)圓柱殼結(jié)構(gòu)的雙穩(wěn)態(tài)特性的變化規(guī)律。研究表明:整體溫度場(chǎng)溫度的增加會(huì)導(dǎo)致圓柱殼各個(gè)曲率都發(fā)生相應(yīng)的增加;第一穩(wěn)態(tài)轉(zhuǎn)變到第二穩(wěn)態(tài)的突變載荷不斷減小,第二穩(wěn)態(tài)回復(fù)到第一穩(wěn)態(tài)的突變載荷反而有所增加;當(dāng)在圓柱殼局部區(qū)域加熱時(shí),對(duì)結(jié)構(gòu)的穩(wěn)態(tài)轉(zhuǎn)變過(guò)程以及曲率產(chǎn)生影響。3.通過(guò)有限元軟件模擬了整體溫度場(chǎng)、局部溫度場(chǎng)以及溫度梯度影響下反對(duì)稱鋪設(shè)圓柱殼結(jié)構(gòu)的雙穩(wěn)態(tài)特性的變化情況,得到包括穩(wěn)態(tài)轉(zhuǎn)變過(guò)程的載荷—位移曲線以及兩個(gè)穩(wěn)態(tài)的曲率變化規(guī)律,計(jì)算結(jié)果與理論和實(shí)驗(yàn)結(jié)果較符合。溫度梯度影響下的圓柱殼曲率變化特性的模擬結(jié)果表明:可以通過(guò)在圓柱殼上施加負(fù)方向的溫度梯度來(lái)抑制由整體溫度場(chǎng)導(dǎo)致的圓柱殼扭轉(zhuǎn)變形的情況。4.利用恒溫箱和拉伸試驗(yàn)機(jī)等實(shí)驗(yàn)測(cè)試平臺(tái),獲得了不同溫度、不同暴露時(shí)間后反對(duì)稱鋪設(shè)圓柱殼結(jié)構(gòu)的雙穩(wěn)態(tài)特性的變化情況。通過(guò)熱暴露實(shí)驗(yàn),得到了宏觀尺度下穩(wěn)態(tài)轉(zhuǎn)變、曲率變化和微觀尺度下碳纖維、樹(shù)脂基底的變化情況。
[Abstract]:The antisymmetric composite cylindrical shell structure has two different stable states, which can be changed between steady state by mechanical load, intelligent material or temperature field, etc. So it's called bistable composite structure (Bi-stable Composite Structure). Bistable composite structures have many advantages such as light weight, excellent load-carrying capacity and deformability. They are widely used in many fields, such as deformable mechanism of aeronautics and astronautics and blade of wind turbine. When the bistable composite structures are in various complex and extreme working environments, the bistable properties of the structures are greatly affected by temperature. At present, there is little research on antisymmetric cylindrical shell structure under the influence of temperature, which limits its development in practical application. In this paper, the influence mechanism of temperature on bistable characteristics of antisymmetric cylindrical shell structure is studied by means of theoretical derivation, experimental test and finite element simulation, and the ambient temperature (integral temperature field) is obtained. Under the influence of local temperature field and temperature gradient, the steady state transformation process, sudden load and deformation of cylindrical shell are studied. Finally, the deformation characteristics of bistable structures under thermal exposure are discussed and explained from macroscopic and microscopic perspectives. The main contents and results are as follows: 1. Based on the classical laminated plate theory, the bistable theoretical model of antisymmetric cylindrical shell structure under the influence of temperature is derived by using the principle of minimum potential energy. The influence of temperature field and temperature gradient on the curvature of antisymmetric cylindrical shell is predicted theoretically, and the factors influencing the distortion rate are discussed. 2. By means of the experimental method, the bistable characteristics of the antisymmetric cylindrical shell structure under the influence of temperature are obtained by using the test platform of the modified tensile testing machine with the temperature control box and the digital image processing technology developed by ourselves. The results show that the increase of the temperature of the whole temperature field will result in the corresponding increase of the curvature of the cylindrical shell. The sudden load from the first steady state to the second steady state decreases, while the second steady state returning to the first steady state increases. When heated in the local region of the cylindrical shell, the steady state transformation process and curvature of the structure are affected. 3. 3. The change of bistable characteristics of antisymmetric cylindrical shell structure under the influence of temperature gradient and the whole temperature field, local temperature field and temperature gradient are simulated by finite element software. The load-displacement curves including the steady state transition process and the curvature variation laws of the two steady states are obtained. The calculated results are in good agreement with the theoretical and experimental results. The simulation results show that the torsional deformation of cylindrical shell caused by the whole temperature field can be restrained by applying negative temperature gradient to the cylindrical shell under the influence of temperature gradient. The change of bistable characteristics of antisymmetric cylindrical shell structure with different temperature and different exposure time was obtained by means of an experimental test platform such as a constant temperature box and a tensile testing machine. The steady state transition, curvature change and carbon fiber and resin substrate change at macro scale and micro scale were obtained by thermal exposure experiment.
【學(xué)位授予單位】：浙江工業(yè)大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2015
【分類號(hào)】：TB33

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