本文選題：電推進(jìn)　切入點(diǎn)：螺旋波等離子體推力器　出處：《大連理工大學(xué)》2016年碩士論文　論文類型：學(xué)位論文

【摘要】：螺旋波等離子體是一種高密度的低溫、低氣壓磁化等離子體,電磁波通常以哨聲波模式在與靜態(tài)外加磁場(chǎng)平行的等離子體柱中傳播,采用環(huán)繞于石英管外壁的特定射頻天線激發(fā)引起右旋極化波共振,在10-1Pa的低氣壓條件下,理想情況的等離子體密度可達(dá)1017～1019m-3量級(jí),中心區(qū)電離效率可接近100%,其雙層加速效應(yīng)可加速離子噴出而產(chǎn)生推力。作為一種新型的電磁式推力器,螺旋波等離子體推力器工作原理研究至關(guān)重要,本文根據(jù)國(guó)內(nèi)外已有研究成果及電推進(jìn)相關(guān)理論,分析總結(jié)了離子加速方式,并對(duì)雙層的形成進(jìn)行了仿真,開(kāi)展了放電室等離子體特性參數(shù)規(guī)律的模擬工作,搭建了電推進(jìn)真空實(shí)驗(yàn)平臺(tái),設(shè)計(jì)出螺旋波等離子體推力器原理樣機(jī),最后觀察了其放電現(xiàn)象。本文具體研究?jī)?nèi)容如下：從傳統(tǒng)化學(xué)推進(jìn)的局限性出發(fā),闡述了先進(jìn)航天推進(jìn)技術(shù)的優(yōu)點(diǎn)并概述了幾種先進(jìn)航天推進(jìn)技術(shù)各自的特點(diǎn),重點(diǎn)說(shuō)明了電推進(jìn)與其他推進(jìn)技術(shù)相比所具有的突出優(yōu)勢(shì)和發(fā)展?jié)摿?進(jìn)而引出螺旋波等離子體推力器的特點(diǎn)及在電推進(jìn)領(lǐng)域中的應(yīng)用前景。論述了三種射頻等離子體源各自結(jié)構(gòu)與放電特點(diǎn),針對(duì)螺旋波等離子體推力器工作原理,概括了朗道阻尼作用與雙層加速效應(yīng)是等離子體獲得能量的途徑,總結(jié)了離子加速方式,并對(duì)其提出了優(yōu)化設(shè)計(jì)思路。在對(duì)螺旋波等離子體推力器工作原理的研究中,使用一維PIC/MCC方法,建立不同長(zhǎng)度電離區(qū)與擴(kuò)散區(qū)仿真模型并進(jìn)行計(jì)算,得到了可以產(chǎn)生高密度等離子體及形成穩(wěn)定電勢(shì)差的壓強(qiáng)區(qū)間與損失系數(shù)范圍,從而不僅證明了雙層加速效應(yīng)存在的合理性,也明確了其影響因素,為螺旋波等離子體推力器的深入研究提供理論支持。采用COMSOL多物理場(chǎng)耦合有限元仿真軟件,建立了放電室的基本模型并設(shè)定相應(yīng)參數(shù),模擬了真實(shí)的工作狀態(tài),計(jì)算得到了放電室內(nèi)部電子數(shù)密度、電子溫度與碰撞功率損耗的空間分布情況。根據(jù)實(shí)驗(yàn)室現(xiàn)有條件,分別采用四種自主設(shè)計(jì)的天線進(jìn)行了放電實(shí)驗(yàn),觀察并對(duì)比實(shí)驗(yàn)現(xiàn)象,得出了初步的結(jié)論。
[Abstract]:Helical wave plasma is a kind of high-density low-temperature, low-pressure magnetized plasma. The electromagnetic wave usually propagates in a plasma column parallel to the static applied magnetic field in the whistler mode. A special RF antenna surrounding the outer wall of a quartz tube is used to excite the dextral polarization wave resonance. Under the low pressure of 10 ~ (-1) Pa, the plasma density can reach 1017 ~ 1019 m ~ (-3). As a new type of electromagnetic thruster, it is very important to study the working principle of helical wave plasma thruster. In this paper, according to the existing research results at home and abroad and the related theory of electropropulsion, the ion acceleration mode is analyzed and summarized, and the formation of the double layer is simulated, and the simulation work on the characteristic parameters of plasma in the discharge chamber is carried out. A vacuum experimental platform for electric propulsion is built, a prototype of helical wave plasma thruster is designed, and its discharge phenomenon is observed. The main contents of this paper are as follows: based on the limitation of traditional chemical propulsion, This paper expounds the advantages of advanced space propulsion technology, summarizes the respective characteristics of several advanced space propulsion technologies, and emphasizes on the outstanding advantages and development potential of electric propulsion compared with other propulsion technologies. The characteristics of helical wave plasma thruster and its application prospect in the field of electric propulsion are introduced. The structure and discharge characteristics of three kinds of RF plasma sources are discussed, and the working principle of the spiral wave plasma thruster is discussed. In this paper, the Langdo damping and double acceleration are summarized as the ways for plasma to obtain energy, and the ion acceleration mode is summarized, and the optimized design method is proposed. In the study of the working principle of helical wave plasma thruster, By using one-dimensional PIC/MCC method, the simulation models of ionization and diffusion regions with different lengths are established and calculated. The pressure range and the range of loss coefficient are obtained, which can produce high density plasma and form stable potential difference. It not only proves the rationality of the two-layer acceleration effect, but also clarifies the influencing factors, which provides theoretical support for the further study of helical wave plasma thruster. COMSOL multi-physical field coupled finite element simulation software is used. The basic model of the discharge chamber is established and the corresponding parameters are set up, the real working state is simulated, and the spatial distribution of electron number density, electron temperature and collision power loss in the discharge chamber is calculated. The discharge experiments were carried out with four kinds of independently designed antennas. The experimental phenomena were observed and compared, and a preliminary conclusion was drawn.
【學(xué)位授予單位】：大連理工大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2016
【分類號(hào)】：V439.2

【參考文獻(xiàn)】

相關(guān)期刊論文 前7條

1 李波;王一白;張普卓;王守國(guó);;VASIMR中螺旋波等離子體源設(shè)計(jì)[J];北京航空航天大學(xué)學(xué)報(bào);2012年06期

2 夏廣慶;王冬雪;薛偉華;張家良;;螺旋波等離子體推進(jìn)研究進(jìn)展[J];推進(jìn)技術(shù);2011年06期

3 吳漢基;蔣遠(yuǎn)大;張寶明;張志遠(yuǎn);;電火箭推進(jìn)的空間探測(cè)器[J];中國(guó)航天;2006年04期

4 周新紅;航天推進(jìn)新技術(shù)開(kāi)拓太空探索新時(shí)代[J];中國(guó)航天;2005年09期

5 張郁;電推進(jìn)技術(shù)的研究應(yīng)用現(xiàn)狀及其發(fā)展趨勢(shì)[J];火箭推進(jìn);2005年02期

6 毛根旺,韓先偉,楊涓,何洪慶;電推進(jìn)研究的技術(shù)狀態(tài)和發(fā)展前景[J];推進(jìn)技術(shù);2000年05期

7 劉國(guó)球,胡平信;液體火箭發(fā)動(dòng)機(jī)技術(shù)的回顧與展望[J];推進(jìn)技術(shù);1998年04期

，

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