本文關(guān)鍵詞：柔性太陽翼桅桿材料屬性對(duì)熱誘發(fā)振動(dòng)影響分析　出處：《南京航空航天大學(xué)》2016年碩士論文　論文類型：學(xué)位論文

  更多相關(guān)文章： 柔性太陽翼 熱變形 熱激勵(lì) 熱誘發(fā)振動(dòng) 熱控涂層 材料屬性

【摘要】：柔性太陽翼多被用于大型空間站的供電系統(tǒng),工作期間由中央支撐桅桿展開�？臻g站在軌期間會(huì)進(jìn)出地球陰影區(qū),因此太陽翼系統(tǒng)受到周期性的熱輻射,使太陽翼各部件產(chǎn)生變化的溫度載荷,引起太陽翼的熱變形甚至振動(dòng)。在太陽翼系統(tǒng)各部件中,支撐桅桿的熱變形會(huì)帶動(dòng)柔性電池陣面發(fā)生振動(dòng),為保證柔性電池陣面的正常工作,支撐桅桿的熱變形需保持在安全范圍內(nèi)。本文以某空間站的大型柔性太陽翼為研究對(duì)象,從太陽翼中央支撐桅桿材料屬性入手,研究桅桿在不同的熱控涂層和不同的材料下,太陽翼柔性陣面的熱誘發(fā)振動(dòng)特性。柔性太陽翼熱誘發(fā)振動(dòng)結(jié)合了傳熱學(xué)、熱彈性力學(xué)、動(dòng)力學(xué)等基礎(chǔ)理論,使用熱-結(jié)構(gòu)非耦合的假設(shè),將太陽翼在軌受熱輻射的溫度載荷轉(zhuǎn)化為熱激勵(lì)來計(jì)算熱誘發(fā)振動(dòng)。根據(jù)此理論采用順序耦合的工程計(jì)算方法,將溫度載荷和熱誘發(fā)振動(dòng)分開計(jì)算,使用有限元軟件NX I-deas計(jì)算太陽翼在軌的溫度分布,然后使用有限元軟件ABAQUS將溫度結(jié)果作為振動(dòng)的激勵(lì)計(jì)算太陽翼的振動(dòng)響應(yīng)。為對(duì)比不同材料屬性對(duì)太陽翼熱誘發(fā)振動(dòng)的影響,將分熱控涂層和材料兩部分進(jìn)行對(duì)比。桅桿熱控材料選擇電鍍涂層和白漆涂層與未鍍層的桅桿進(jìn)行對(duì)比,分析不同涂層對(duì)太陽翼柔性陣面熱誘發(fā)振動(dòng)的影響。桅桿材料的改變需要對(duì)桅桿尺寸進(jìn)行優(yōu)化,使用modeFRONTIER優(yōu)化軟件結(jié)合ABAQUS軟件對(duì)鋁合金、鈦合金和不銹鋼三種材料的桅桿按相同的力學(xué)性能進(jìn)行優(yōu)化,然后對(duì)比計(jì)算。分析結(jié)果可作為太陽翼桅桿設(shè)計(jì)的依據(jù)和評(píng)估。
[Abstract]:The flexible solar wing is mostly used for the power supply system of large space stations and is carried out by the central support mast during the operation. During the orbit, the space station will enter the shadow area of the earth. Therefore, the solar wing system is subjected to periodic thermal radiation, so that the components of the solar wing will generate varying temperature loads, causing the thermal deformation and even vibration of the solar wings. In the components of the solar system, the thermal deformation of the supporting mast will drive the vibration of the flexible battery array. In order to ensure the normal operation of the flexible battery surface, the thermal deformation of the mast must be kept in a safe range. Taking the large flexible solar wing of a space station as the research object, starting from the material properties of the central support mast, the thermal induced vibration characteristics of mast under different thermal control coatings and different materials are studied. The thermal induced vibration of flexible solar wings is combined with the basic theories of heat transfer, thermoelasticity, dynamics and so on. Based on the assumption of thermal structure coupling, the thermal load of the solar radiation on the orbit is transformed into thermal excitation to calculate the thermally induced vibration. According to the calculation method of this theory by using sequential coupling engineering, temperature load and heat induced vibration are calculated separately, using the finite element software NX I-deas to calculate the temperature distribution of the solar wing vibration in orbit, and then use the finite element software ABAQUS the temperature as a result of vibration response calculation of the solar wing. In order to compare the effects of different material properties on the heat induced vibration of the solar wing, the two parts of the thermal control coating and the material are compared. The mast thermal control material is selected to compare the electroplating coating and white paint coating with the mast without coating. The influence of different coatings on the thermal induced vibration of the solar wing flexible array is analyzed. Mast material changes need to optimize the mast size. The modeFRONTIER optimization software combined with ABAQUS software is used to optimize the mechanical properties of three kinds of mast, aluminum alloy, titanium alloy and stainless steel, and then the comparative calculation is made. The analysis results can be used as the basis and evaluation of the design of the Sun Wing mast.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2016
【分類號(hào)】：V414

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