【摘要】：隨著航天技術(shù)的飛速發(fā)展,電推進(jìn)系統(tǒng)因其具有更高的工質(zhì)利用率和長(zhǎng)時(shí)間的在軌壽命等突出優(yōu)點(diǎn)得到了廣泛的研究和應(yīng)用。電推進(jìn)技術(shù)已經(jīng)成為通信衛(wèi)星工程應(yīng)用中必不可少的技術(shù)手段,對(duì)我國(guó)衛(wèi)星領(lǐng)域的能力提升具有重要研制意義。在國(guó)外,電推進(jìn)技術(shù)更加成熟,且已在主流大型衛(wèi)星平臺(tái)上應(yīng)用,有眾多值得借鑒之處。我國(guó)對(duì)電推進(jìn)技術(shù)的研究也一直在進(jìn)步,部分衛(wèi)星平臺(tái)上已經(jīng)得到應(yīng)用。但是由于電推進(jìn)器在工作時(shí),會(huì)向外噴射高溫、高能的羽流,羽流的復(fù)雜電磁環(huán)境會(huì)對(duì)航天系統(tǒng)產(chǎn)生多種危害,進(jìn)而造成巨大損失。所以必須要對(duì)電推進(jìn)羽流和整星的電磁兼容問題開展全面且深入的研究工作,將在軌情形可能遇到的所有未知電磁問題使用地面仿真測(cè)試手段進(jìn)行有效預(yù)估,以推動(dòng)電推進(jìn)技術(shù)在我國(guó)衛(wèi)星平臺(tái)上的成功應(yīng)用。電推進(jìn)羽流是一種復(fù)雜的非均勻等離子體,對(duì)等離子體的物理性質(zhì)描述一般包括等離子體頻率,碰撞頻率和入射電磁波頻率,這三者互相影響,存在著強(qiáng)烈的非線性作用,因此決定了等離子體和電磁波之間作用方式的復(fù)雜性與多樣性。在本文中,根據(jù)入射電磁波的頻段范圍不同,介紹了多種用于分析羽流電磁效應(yīng)的數(shù)值計(jì)算方法,及適用于不同方法的羽流電子濃度建模方式。主要包括近似算法:WKB近似方法和傳播矩陣法;高精度算法有:FDTD方法和射線跟蹤方法。重點(diǎn)仿真計(jì)算了羽流對(duì)通訊電磁波的能量、相位及輻射方向特性圖的影響和衛(wèi)星表面上任一點(diǎn)敏感元器件處的接受場(chǎng)值大小,并和無羽流情況作對(duì)比。測(cè)試結(jié)果表明了羽流的電磁影響,這為實(shí)際在軌情形中羽流與航天系統(tǒng)的電磁兼容性問題提供了一定的參考價(jià)值。
[Abstract]:With the rapid development of spaceflight technology, the electric propulsion system has been widely studied and applied because of its outstanding advantages such as higher working medium utilization rate and longer in-orbit life. The electric propulsion technology has become an indispensable technical means in the application of communication satellite engineering, and has important significance for the development of the capability improvement in the field of satellite in China. In foreign countries, the electric propulsion technology is more mature, and has been used in the mainstream large satellite platform, there are many worthy of reference. The research on electric propulsion technology in China has been progressing, and some satellite platforms have been applied. However, when the electric thruster is working, it will spray high temperature, high energy plume and complex electromagnetic environment of plume, which will cause many kinds of harm to the space system and cause great losses. Therefore, it is necessary to carry out a comprehensive and in-depth study on the electromagnetic compatibility between the electropropulsion plume and the whole satellite, and to effectively predict all the unknown electromagnetic problems that may be encountered in the orbit situation by means of ground simulation tests. In order to promote the successful application of the electric propulsion technology on the satellite platform of our country. The electropropulsion plume is a kind of complex inhomogeneous plasma. The physical properties of the plasma generally include the frequency of plasma, the frequency of collision and the frequency of incident electromagnetic wave. Therefore, the complexity and diversity of the interaction between plasma and electromagnetic wave are determined. In this paper, according to the different frequency range of the incident electromagnetic wave, several numerical methods for analyzing the plume electromagnetic effect are introduced, and the modeling methods of the plume electron concentration suitable for different methods are introduced. It mainly includes the approximate algorithm: WKB approximation method and propagation matrix method, and the high precision algorithm includes the: FDTD method and ray tracing method. The effects of plume on the energy, phase and radiation direction of the electromagnetic wave are simulated and calculated, and the value of the receiving field at any sensitive component on the satellite surface is calculated and compared with that in the case of no plume. The test results show that the electromagnetic effect of plume provides a certain reference value for the problem of electromagnetic compatibility between plume and space system in the actual orbital case.
【學(xué)位授予單位】：西安電子科技大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2015
【分類號(hào)】：O53;TN03

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本文編號(hào)：2178888