【作者】 黄超；

【导师】 张凤奎； 徐辉；

【作者基本信息】 哈尔滨工程大学 ， 航天工程（专业学位）， 2016， 硕士

【摘要】 时至今日,各国对空间的探测活动越来越多,航天事业真正进入了全新的发展时期,由其对月球、火星的无人探测以及将来要进行的载人探测,这些规划要求动力系统的有效载荷比较大、效率较高、寿命较长、成本较低。但是现存的电推进装置一般功率较低推力较小,而载人深空探测航天器重量大、任务周期又不能太长,所以只有大功率的电推力器才能满足任务要求,大功率推力器必定成为动力装置的主要研究方向。.本文研究的圆柱形霍尔推力器就是大功率电推进的一种,为了测量其性能,首先加工出了一台缩比样机。本文的工作就是围绕此缩比样机的电离特性进行实验测量和数值模拟研究。首先对此缩比样机的各参数进行了实验测量,得到了推力器的放电电流、推力、阳极比冲和阳极效率随着放电电压及阳极流量增大时的变化规律;还得到了不同阳极流量及放电电压下的离子电流密度径向分布,从而得到了工质利用率随着放电电压和阳极流量增大时的变化规律。因为实验手段很难得到推力器放电通道内某些参数的详细分布,为了从微观上研究推力器的电离特性,必须采用数值模拟方法。本文采取粒子模拟手段研究了推力器的电离特性,主要内容包括:磁场和阳极流量不变时,得到了推力器的电离特性随放电电压的变化规律;磁场和放电电压不变时,得到了推力器的电离特性随阳极流量的变化规律;磁场位形和阳极流量不变时,根据磁场强度与放电电压的关系匹配磁场强度,得到了磁场强度匹配后推力器的电离特性随放电电压的变化规律以及电离特性随磁场强度的变化规律;最后,模拟了推力器环形渐扩区不同高径比时对电离特性的影响,表明了其对优化推力器电离特性的有效性。更多还原

【Abstract】 In recent years, international spaceflight entered a new peak of development. Space exploration activities on the moon,Mars and other solar systems are emerging in an endless stream, these plans proposed higher requirement for propulsion system on the high payload ratio, high efficiency, long life and low cost, etc. Electric propulsion has a higher impulse,which makes it can save a lot of propellant. Compared with chemical propulsion,the electric propulsion has a great advantage. However, the existing electric propulsion system’s power is generally lower, thrust is smaller. And manned deep space detection spacecraft is much heavier and the task cycle can not be too long, so only the high power electric propulsion system can satisfy the demands of the task. In order to meet the demand of geosynchronous orbit satellites long-distance rail promotion, orbit transfer and get the goal of making electric propulsion as a main propulsion device of deep space exploration detector and interstellar navigation detector in the future, the development of high-power thruster is bound to become the main development trend of propulsion system. In this paper, the cylindrical Hall thruster studied is one of the high power electric propulsion. In order to verify the feasibility of the design, firstly, we processed a scaled prototype. The work of this paper is studying on the ionization characteristics of the prototype using experiment and numerical simulation method.First of all, the experiment of the scaled prototype was carried out. And we get the thruster discharge current, thrust, anode impulse and anode efficiency’s variation law with variation of the discharge voltage and anode flux. We also get the radial distribution of ion current density under different anode flux and discharge voltage, and hence getting the working medium utilization’s variation law with the variation of discharge voltage and anode flux.The experiment is very difficult to obtain the detail parameters distribution in the thruster channel. Therefore, in order to understand the micro ionization characteristics of the thruster,we could use the numerical simulation method. In this paper, we adopts PIC particle simulation method to study on the ionization characteristics of the cylindrical hall thruster,and the main contents includes: when the magnetic field and anode flux is constant, studying on ionization characteristics of the thruster changes with discharge voltage; When the magnetic field and discharge voltage is constant, studying on ionization characteristics of the thruster changes with anode flux; When the magnetic field configuration and anode flux is unchanged, according to the relation between magnetic field intensity and discharge voltage,enlarge magnetic field intensity with discharge voltage increasing, and then studying on ionization characteristics of the thruster changes with the discharge voltage, as well as the ionization characteristics changes with the magnetic field intensity; Finally, under different ratio of height to medium diameter, studying the annular diffuser area’s effect on ionization characteristics, and which has been proved to be effective in optimizing the ionization characteristics of the cylindrical hall thruster.更多还原