脉冲等离子体推力器工作过程及羽流的数值仿真研究
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摘要
脉冲等离子体推力器(Pulsed Plasma Thruster,PPT)作为一种电磁推力器是最早进行空间运用的电推进形式,具有体积小、重量轻、结构紧凑、控制方便灵活、可靠性高等特点,能够广泛应用于微小卫星的姿轨控推进系统,是目前小卫星推进技术的重要发展方向。PPT的工作过程包含多种复杂的物理过程,涉及流体力学、电动力学、等离子体物理等多个学科;PPT的羽流成分复杂,其中包含了复杂的电离、化合以及碰撞过程,且PPT瞬态的工作特征使得对其特征参数的把握十分不易,因此对PPT开展全面深入的研究具有十分重要的意义。
本文采用理论分析和数值仿真的方法,针对局部热力学平衡的等离子体温度特性,建立了一维双温和三维MHD(磁流体力学,Magnetohydrodynamic)PPT工作过程模型,研究固体聚四氟乙烯推进剂平行板电极PPT工作过程和工作机理,探寻提高该PPT性能的途径和方法;改进了DSMC/PIC混合算法,对PPT的羽流进行数值仿真,掌握PPT羽流形成发展过程;通过对PPT羽流双温入口模型的建立,形成一套能够从PPT工作过程到羽流的全流场分析系统。
建立了基于磁流体力学方法的平行板电极脉冲等离子体推力器工作过程的一维双温模型,对不同初始电压、电容以及不同电极长度的PPT工作过程以及性能进行评估,为发动机性能评估提供基本手段。在一维模型的基础上,建立了基于磁流体力学方法的PPT工作过程三维MHD模型,在此基础上给出了全MHD方程组,对全MHD方程组的特征值系统进行了求解。通过三维模型对脉冲等离子体推力器推力室工作过程开展三维数值仿真,对不同参数下的多种电极构型的推力器工作过程进行了仿真研究,获得了关于PPT工作过程的三维变化特性。
对PPT的基本工作过程进行了研究,结果显示,脉冲时间内的放电电流的波形和大小影响着推力器中的流场变化,放电电流与感应磁场的相互作用影响着等离子体在各个方向的运动速度;推进剂表面温度具有与放电电流相似的波形变化规律,同时也影响着推力室中的等离子体的密度和速度分布;推力室的中心区域的温度较高,离子浓度较高,速度较高,而在推力室边缘地区,原子浓度相对较高,速度较低,低速度原子在一定程度上可能造成积碳问题。
对影响推力器性能的各种因素进行了研究,结果表明,脉冲初期的高速等离子体是推力器推力的主要来源,脉冲末期过高的推进剂表面温度造成的滞后烧蚀,是造成推力器效率低下的一个重要原因;周边温度高的推进剂表面温度分布会使大量等离子体产生在低速区域,不利于推力器性能提高;长电极有助于电磁加速,但带来的电流密度减小又制约着喷射速度;适当加高电极间距有助于加速以及推进剂在放电末期的冷却;窄电极下的高放电电流密度、脉冲初期的高推进剂表面温度和末期的快速冷却,有利于性能的提高;通过改变构型对PPT性能进行改善时,气动力的加速效果非常有限,需要考虑有利于洛伦兹力加速的流动状态;通过延长高放电电流持续的时间和等离子体的膨胀过程,提高推进剂的高喷射速度,有利于性能提高,在进行电流优化的过程中,需要针对具体的推力器构型以及该构型下的能量水平,尽量采用低的电流变化率,努力延长等离子体膨胀加速的时间。
建立了脉冲等离子体推力器羽流模型,实现了DSMC/PIC流体混合算法,对网格点统计权重因子求解进行了修正,并采用改进型极小残量剩余方法对电势场和温度场进行求解以提高运算效率,为获得与实际PPT工作过程相关的羽流场信息,建立了基于一维双温模型、三维双温模型的羽流入口模型,开展了对PPT羽流的数值仿真研究。
对脉冲等离子体推力器羽流场的特征规律进行研究,结果表明,在脉冲持续周期时间内,等离子体羽流团迅速扩散,离子的扩散范围较中性粒子更广;离子和中性粒子团均出现了不同程度的回流现象,带电粒子回流不论是在影响区域还是影响程度上都远远高于中性粒子回流,是回流污染的主要因素;电荷交换(CEX)碰撞延缓了羽流的轴向扩散速度,促进了羽流的径向扩散,是影响回流现象的一个主要因素;粒子回流和羽流中CEX离子的分布受到放电电流波形特征的影响;在各类不同的能量状态下,羽流成分以及其变化规律是相似的,在高能量状态下羽流的质量流率更高,影响域更广。
对运用几种不同的羽流入口模型的羽流结果进行比较后发现,推力器喷射产物决定着羽流分布和变化情况,要对这个过程进行正确的模拟需要借助建立在推力器工作过程模型基础上的入口边界模型;三维入口模型的入口边界较一维入口模型更能体现出脉冲初期高速离子流和脉冲末期低速中性粒子流的特征,且三维入口模型能够有效的反映入口速度的喷射角度对于回流的影响。
The Pulsed Plasma Thruster (PPT) is a pioneer electromagnetic thruster used in space at first, which has some advantages such as small bulk, light weight, compact framework, easy controllability and high reliability, etc. Thus, it can be widely applied in attitude or orbit control propulsion system of micro-satellites, and plays an important role in the propulsion system of micro and small satellites. The PPT operation process unites many complex interactions resulted from hydrodynamics, electromechanical, plasma-physics processes. The PPT plume contains complicated species, where ionization, combination and collision processes may occur. The pulse-typed operation mode makes it difficult to master characteristics of PPT operating physics. So it is very important to do theoretical research thoroughly on PPT.
In the present thesis, by means of theoretical analysis and numerical simulation, for local temperature equilibrium, one-dimension two-temperature and three-dimension two-temperature MHD (Magneto-hydrodynamic) models were built, the basic physics research on Teflon propellant parallel-plate PPT has been carried out to investigate the method to enhance performance. With the improved DSMC (the Direct Simulation Monte Carlo) /PIC (Particle in Cell) fluid hybrid method, the PPT plume was simulated to understand the formation and development process of the plume. Through the two-temperature inlet model, an analytical system was built, which can simulate the whole flow field from the operation process to plume.
One-dimension time-dependent two-temperature parallel-plate PPT operation process model based on magneto-hydrodynamic was established. The operation process and performance of PPT were evaluated on different initial voltage, capacitance and electrode length. The model can provide an effective tool to evaluate the thruster performance. On the one-dimension basic model, three-dimension PPT operation process time-dependent two-temperature model based on magneto-hydrodynamic was built. The full MHD equations were proposed, and the eigenvalues system was solved. Using the three-dimension model, the processes of PPT at different parameters and geometries were simulated, the three-dimension characteristics of PPT operation process were obtained.
The basic operation process of PPT was studied, the results showed that in pulse the variation of discharge current affects the flow field in thruster, interaction on discharge current and inductive magnetic field influences on velocity of plasma; propellant surface temperature has the similar variation with the discharge current, which influences plasma density and velocity in chamber; there is plasma with high temperature, high ion density and high velocity in the central area of the chamber; and around the chamber, the plasma’s temperature and velocity are low, atom density is high, and atom with low velocity may bring the problem of charring.
The factors affecting the performance of PPT were investigated, the results showed that in the early pulse, high-velocity plasma is the main source of thrust, in the late pulse, the late-ablation aroused by high propellant surface temperature is an important reason for low efficiency of PPT; the high-temperature propellant around makes a great deal of plasma with low velocity, which is not good for performance; long electrode is favorable for magnetism acceleration, but the little current density is not good for spout velocity; proper long gap between electrodes is useful for acceleration of plasma and propellant cooling in late pulse; the high current density, high propellant surface temperature and quick cooling in late pulse at narrow electrode are beneficial for performance; to improve performance of PPT through geometry variation, the acceleration of gas dynamic force is limited, the flow situation suitable for Lorentz force should be considered; prolonging the time with high discharge current, expansion of plasma, advancing velocity of plasma is helpful for performance; in order to optimize current, it is necessary to choose low variation of current and prolong the time of expansion of plasma based on PPT geometry and energy.
The model of PPT plume was built, the DSMC/PIC fluid hybrid method is programmed, the appropriate conserving expression of shape factor for the sampling at node is corrected, potential field and electron temperature field are solved by improving GMRES algorithm to advance operation speed, for time-dependent PPT plume, one-dimension two-temperature inlet model and three-dimension two-temperature inlet model were built, the numerical researches of PPT plume were carried out.
The characteristics of PPT plume were studied, results showed, in pulse, plasma plume diffuses quickly, ion diffuses more widely than atom; there are back-flow of ion and atom, ion back-flow is stronger than atom, which is the main factor of back-flow pollution; charge exchange(CEX)collision delays the axial velocity of plume, accelerates the radial velocity, which is an important influence on back-flow; the distribution of back-flow and CEX ion in plume are affected by discharge current; variations of plume are similar with different energy, under higher energy the mass-flow-rate of plume is higher, and the area of plume is more extensive.
Comparing the results of different inlet models, results showed that the distribution and variation of plume were determined by thruster spout, and the correct simulation needs the inlet model based on PPT operation process model; high-velocity ion in early pulse and low-velocity neutral in late pulse can be acquired through three-dimension inlet model, which is better than one-dimension inlet model, and through which the influence of the spout angle of inlet velocity on back-flow could be effectively simulated.
本文采用理论分析和数值仿真的方法,针对局部热力学平衡的等离子体温度特性,建立了一维双温和三维MHD(磁流体力学,Magnetohydrodynamic)PPT工作过程模型,研究固体聚四氟乙烯推进剂平行板电极PPT工作过程和工作机理,探寻提高该PPT性能的途径和方法;改进了DSMC/PIC混合算法,对PPT的羽流进行数值仿真,掌握PPT羽流形成发展过程;通过对PPT羽流双温入口模型的建立,形成一套能够从PPT工作过程到羽流的全流场分析系统。
建立了基于磁流体力学方法的平行板电极脉冲等离子体推力器工作过程的一维双温模型,对不同初始电压、电容以及不同电极长度的PPT工作过程以及性能进行评估,为发动机性能评估提供基本手段。在一维模型的基础上,建立了基于磁流体力学方法的PPT工作过程三维MHD模型,在此基础上给出了全MHD方程组,对全MHD方程组的特征值系统进行了求解。通过三维模型对脉冲等离子体推力器推力室工作过程开展三维数值仿真,对不同参数下的多种电极构型的推力器工作过程进行了仿真研究,获得了关于PPT工作过程的三维变化特性。
对PPT的基本工作过程进行了研究,结果显示,脉冲时间内的放电电流的波形和大小影响着推力器中的流场变化,放电电流与感应磁场的相互作用影响着等离子体在各个方向的运动速度;推进剂表面温度具有与放电电流相似的波形变化规律,同时也影响着推力室中的等离子体的密度和速度分布;推力室的中心区域的温度较高,离子浓度较高,速度较高,而在推力室边缘地区,原子浓度相对较高,速度较低,低速度原子在一定程度上可能造成积碳问题。
对影响推力器性能的各种因素进行了研究,结果表明,脉冲初期的高速等离子体是推力器推力的主要来源,脉冲末期过高的推进剂表面温度造成的滞后烧蚀,是造成推力器效率低下的一个重要原因;周边温度高的推进剂表面温度分布会使大量等离子体产生在低速区域,不利于推力器性能提高;长电极有助于电磁加速,但带来的电流密度减小又制约着喷射速度;适当加高电极间距有助于加速以及推进剂在放电末期的冷却;窄电极下的高放电电流密度、脉冲初期的高推进剂表面温度和末期的快速冷却,有利于性能的提高;通过改变构型对PPT性能进行改善时,气动力的加速效果非常有限,需要考虑有利于洛伦兹力加速的流动状态;通过延长高放电电流持续的时间和等离子体的膨胀过程,提高推进剂的高喷射速度,有利于性能提高,在进行电流优化的过程中,需要针对具体的推力器构型以及该构型下的能量水平,尽量采用低的电流变化率,努力延长等离子体膨胀加速的时间。
建立了脉冲等离子体推力器羽流模型,实现了DSMC/PIC流体混合算法,对网格点统计权重因子求解进行了修正,并采用改进型极小残量剩余方法对电势场和温度场进行求解以提高运算效率,为获得与实际PPT工作过程相关的羽流场信息,建立了基于一维双温模型、三维双温模型的羽流入口模型,开展了对PPT羽流的数值仿真研究。
对脉冲等离子体推力器羽流场的特征规律进行研究,结果表明,在脉冲持续周期时间内,等离子体羽流团迅速扩散,离子的扩散范围较中性粒子更广;离子和中性粒子团均出现了不同程度的回流现象,带电粒子回流不论是在影响区域还是影响程度上都远远高于中性粒子回流,是回流污染的主要因素;电荷交换(CEX)碰撞延缓了羽流的轴向扩散速度,促进了羽流的径向扩散,是影响回流现象的一个主要因素;粒子回流和羽流中CEX离子的分布受到放电电流波形特征的影响;在各类不同的能量状态下,羽流成分以及其变化规律是相似的,在高能量状态下羽流的质量流率更高,影响域更广。
对运用几种不同的羽流入口模型的羽流结果进行比较后发现,推力器喷射产物决定着羽流分布和变化情况,要对这个过程进行正确的模拟需要借助建立在推力器工作过程模型基础上的入口边界模型;三维入口模型的入口边界较一维入口模型更能体现出脉冲初期高速离子流和脉冲末期低速中性粒子流的特征,且三维入口模型能够有效的反映入口速度的喷射角度对于回流的影响。
The Pulsed Plasma Thruster (PPT) is a pioneer electromagnetic thruster used in space at first, which has some advantages such as small bulk, light weight, compact framework, easy controllability and high reliability, etc. Thus, it can be widely applied in attitude or orbit control propulsion system of micro-satellites, and plays an important role in the propulsion system of micro and small satellites. The PPT operation process unites many complex interactions resulted from hydrodynamics, electromechanical, plasma-physics processes. The PPT plume contains complicated species, where ionization, combination and collision processes may occur. The pulse-typed operation mode makes it difficult to master characteristics of PPT operating physics. So it is very important to do theoretical research thoroughly on PPT.
In the present thesis, by means of theoretical analysis and numerical simulation, for local temperature equilibrium, one-dimension two-temperature and three-dimension two-temperature MHD (Magneto-hydrodynamic) models were built, the basic physics research on Teflon propellant parallel-plate PPT has been carried out to investigate the method to enhance performance. With the improved DSMC (the Direct Simulation Monte Carlo) /PIC (Particle in Cell) fluid hybrid method, the PPT plume was simulated to understand the formation and development process of the plume. Through the two-temperature inlet model, an analytical system was built, which can simulate the whole flow field from the operation process to plume.
One-dimension time-dependent two-temperature parallel-plate PPT operation process model based on magneto-hydrodynamic was established. The operation process and performance of PPT were evaluated on different initial voltage, capacitance and electrode length. The model can provide an effective tool to evaluate the thruster performance. On the one-dimension basic model, three-dimension PPT operation process time-dependent two-temperature model based on magneto-hydrodynamic was built. The full MHD equations were proposed, and the eigenvalues system was solved. Using the three-dimension model, the processes of PPT at different parameters and geometries were simulated, the three-dimension characteristics of PPT operation process were obtained.
The basic operation process of PPT was studied, the results showed that in pulse the variation of discharge current affects the flow field in thruster, interaction on discharge current and inductive magnetic field influences on velocity of plasma; propellant surface temperature has the similar variation with the discharge current, which influences plasma density and velocity in chamber; there is plasma with high temperature, high ion density and high velocity in the central area of the chamber; and around the chamber, the plasma’s temperature and velocity are low, atom density is high, and atom with low velocity may bring the problem of charring.
The factors affecting the performance of PPT were investigated, the results showed that in the early pulse, high-velocity plasma is the main source of thrust, in the late pulse, the late-ablation aroused by high propellant surface temperature is an important reason for low efficiency of PPT; the high-temperature propellant around makes a great deal of plasma with low velocity, which is not good for performance; long electrode is favorable for magnetism acceleration, but the little current density is not good for spout velocity; proper long gap between electrodes is useful for acceleration of plasma and propellant cooling in late pulse; the high current density, high propellant surface temperature and quick cooling in late pulse at narrow electrode are beneficial for performance; to improve performance of PPT through geometry variation, the acceleration of gas dynamic force is limited, the flow situation suitable for Lorentz force should be considered; prolonging the time with high discharge current, expansion of plasma, advancing velocity of plasma is helpful for performance; in order to optimize current, it is necessary to choose low variation of current and prolong the time of expansion of plasma based on PPT geometry and energy.
The model of PPT plume was built, the DSMC/PIC fluid hybrid method is programmed, the appropriate conserving expression of shape factor for the sampling at node is corrected, potential field and electron temperature field are solved by improving GMRES algorithm to advance operation speed, for time-dependent PPT plume, one-dimension two-temperature inlet model and three-dimension two-temperature inlet model were built, the numerical researches of PPT plume were carried out.
The characteristics of PPT plume were studied, results showed, in pulse, plasma plume diffuses quickly, ion diffuses more widely than atom; there are back-flow of ion and atom, ion back-flow is stronger than atom, which is the main factor of back-flow pollution; charge exchange(CEX)collision delays the axial velocity of plume, accelerates the radial velocity, which is an important influence on back-flow; the distribution of back-flow and CEX ion in plume are affected by discharge current; variations of plume are similar with different energy, under higher energy the mass-flow-rate of plume is higher, and the area of plume is more extensive.
Comparing the results of different inlet models, results showed that the distribution and variation of plume were determined by thruster spout, and the correct simulation needs the inlet model based on PPT operation process model; high-velocity ion in early pulse and low-velocity neutral in late pulse can be acquired through three-dimension inlet model, which is better than one-dimension inlet model, and through which the influence of the spout angle of inlet velocity on back-flow could be effectively simulated.
引文
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