Parameter Deviation Effect Study of the Power Generation Unit on a Doubly-Fed Induction Machine-based Shipboard Propulsion System

To lower the difficulty of fault protection,a doubly-fed induction machine based shipboard propulsion system(DFIM-SPS)that is partially power decoupled is presented.In such an intrinsically safe SPS architecture,a synchronous generator(SG)is employed for power generation,and the accuracy of the parameters of power generation unit(PGU)plays an important role in SPS stable operation.In this paper,the PGU parameter deviations are studied to evaluate the effects on system performance.The models of salient-pole SG,type DC1A excitation system(EXS)and DFIM are illustrated first.Besides,the corresponding control scheme is explained.For the 16 important parameters of PGU,up to 40%of parameter deviations are applied to implement parameter sensitivity analysis.Then,simulation studies are carried out to evaluate the parameter deviation effects on system performance in detail.By defining three parameter deviation effect indicators(PDEIs),the effects on the PGU output variables,which are the terminal voltage and output active power,are studied.Moreover,the increasing rates of PDEIs with different degrees of parameter deviations for the key parameters are analyzed.Furthermore,the overall system performance is investigated for the two most influential PGU parameters.This paper provides some vital clues on SG and EXS parameter identification for DFIM-SPS.

The Low-Frequency Oscillation Restrain Method Research of Converter-Fed Multi-Phase Induction Motor Propulsion system

The inverter-fed induction motor drive system may become unstable at low frequencies and light load, and phase current and speed of the induction motor may oscillate periodically, which will threaten safety and reliability of the system. This paper chooses nine-phase induction motor simulated propulsion system as the research object, small disturbance model of three-phase induction motor is built, and average equivalent model of the converter is built by introducing switch function. On the basis above, small disturbance mathematic model of the whole system is obtained. As for the limitation of parameters adjustment method of restrain low-frequency oscillation, the restrain method combining current close-loop with dead-time compensation is put forward. Finally, the proposed restrain method is verified respectively on the built simulation and experimental analogue platform. And the simulation and experimental results indicate that the proposed method can not only satisfy the requirement of low-frequency oscillation restraining, but also be expanded widely, and the stability of the system can get improved greatly.

A Study on an Airgap Control System in a Rotary-Small-Scaled Linear Induction Motor for Railway Vehicles

In general, it is important to operate the; airgap length uniformly for improving the system efficiency independent of the flatness of the reaction plate in a railway propulsion system by a linear induction motor （LIM）. And it is possible to operate the LIM propulsion system efficiently without a change of the LIM capacity through the airgap length control on the sloped rail. So, in this research, the authors introduce an airgap control system to control the airgap length which depends on the flatness of the secondary reaction plate when the LIM is operated, and design a rotary small-scaled LIM and its airgap control system before manufacturing the real system. Then, the authors analyze some characteristics of the LIM （thrust and normal force, input current, efficiency and power factor）, and through the LIM control modeling, the authors finally analyze an effect of the airgap-length control of the LIM by the airgap control system.

Optical detection method of discharge mode transition of inductively coupled plasma in an atmosphere-breathing electric propulsion system

Plasma discharge stability is an important problem in atmosphere-breathing electric propulsion system when maintaining long-term missions at ultra-low earth orbit.This paper designed an inductively coupled plasma source to imitate the ionization section.The effect of inflow rate and Radio Frequency(RF)power on the plasma discharge mode transition is experimentally studied.A discharge mode detection method is proposed,which determines the discharge mode by identifying the morphology of the plasma core.By using the method,the discharge mode transition is quantified and a control model based on the parameter sensitivity is constructed.To verify the method,the spectra are measured and the electron temperature spatial distribution is calculated.And the method has been proven effective.The results show that the inductively coupled discharge contains capacitive components affected by the mass flow rate and the radio frequency power.The plasma characteristics can be maintained stably by controlling the radio frequency power when the mass flow rate randomly changes in a certain range.It is demonstrated that the application of detection method effectively identifies the discharge mode,which is a promising active control method for the plasma discharge mode.

1A级射频感性耦合等离子体中和器电子引出特性研究

为解决低轨道吸气式离子电推力器的电中和问题,设计了一套抗氧化能力强、长寿命的1 A级氙工质感性耦合等离子体中和器,实验研究了发射孔径对其电子引出特性的影响。实验结果表明:发射孔径的变化,会对中和器电子引出电压、饱和电流和工质利用系数产生较大的影响,且在部分孔径下发现了电子束流随引出电压上升时出现二次跃变现象,根据工质利用系数和电子引出功耗比确定出中和器最优发射孔径为1.5 mm;电子束流引出为1 A时,工质利用系数达到27.7,电子引出功耗比为94.6 W/A。同时,测试了中和器温度对工作稳定性的影响,中和器热平衡状态下与点火初期相比中和器电子引出性能下降约10%。

An atmosphere-breathing propulsion system using inductively coupled plasma source

CubeSats have attracted more research interest recently due to their lower cost and shorter production time.A promising technology for CubeSat application is atmosphere-breathing electric propulsion,which can capture the atmospheric particles as propulsion propellant to maintain longterm mission at very low Earth orbit.This paper designs an atmosphere-breathing electric propulsion system for a 3 U CubeSat,which consists of an intake device and an electric thruster based on the inductively coupled plasma.The capture performance of intake device is optimized considering both particles capture efficiency and compression ratio.The plasma source is also analyzed by experiment and simulation.Then,the thrust performance is also estimated when taking into account the intake performance.The results show that it is feasible to use atmosphere-breathing electric propulsion technology for CubeSats to compensate for aerodynamic drag at lower Earth orbit.

同步感应式电磁线圈推射系统设计研究

电磁推射采用脉冲电流推进,无需化学燃料,对平台无影响,可重复使用,是一种新型推进装置,其中感应型电磁线圈推射是一种重要方式,其通过驱动线圈产生的磁场加速抛体,且抛体与发射管无接触,避免了烧蚀问题,具有较长的使用寿命。文章结合同步感应式电磁线圈推射系统技术特点,针对6kg模拟载荷推射需求,通过ANSYS仿真设计,验证了该系统用于电磁推射的可行性。研究结果表明:(1)9级线圈加速过程中,电枢和载荷受到的最大推力为16.91kN,受到的最大过载为198.87g,满足不超过200g的推射设计需求,载荷以最大速度36.58m/s出膛,满足不低于35m/s的推射初速要求;(2)载荷分离后,电枢受到线圈反向力的作用,在32.2ms后减速到0m/s,开始反向运动,实现电枢回收至发射筒内,便于下次试验重复利用。全系统发射效率13.61%,有效载荷发射效率9.39%。以上研究为6kg模拟载荷低成本高效投送及快速批量部署提供了技术支撑。

射频电子源数值仿真及实验研究

射频电子源以其结构简单、不易受污染、寿命长、瞬时启动等优点,可以作为离子和霍尔电推进的中和器,显著提升其寿命和性能。为了研究射频电子源的优化设计方法,基于放电室等离子体整体模型和非双极流动模型开展了射频电子源性能的仿真评估,并对研制的1A级电子源样机开展了实验测试。研究结果显示:仿真与实验结果一致性较好,引出电子电流与收集电压、小孔直径、工质流率、射频功率相关,各参数相互耦合且存在最优组合,样机额定工作点下,电子源放电损耗为99W/A,工质利用率系数为11。

不同磁感应强度下的磁流体加速实验研究

利用基于激波风洞的磁流体动力技术实验系统,设计了超声速喷管和分段法拉第型试验段,选用合理的电场及磁场方案,开展了不同磁感应强度下的磁流体加速实验研究。当激波管高压段压力1.2MPa、低压段压力500Pa,电容充电电压为400V时,得到的主要实验结论如下:随着磁感应强度增大,加速通道电极间电压增加,电流降低,单个电极的输入功率降低,负载系数略有降低,电效率略有升高;当磁感应强度分别为0.5T、1T、1.5T时,#10电极处超声速气流的电导率分别约为181S/m、81S/m和50S/m,利用#20电极开路电压的方法评估出口速度增量分别约为16.1%、14.7%、14.3%。电导率对输入功率的影响较大,提高加速效果需要同时提高气流的电导率和通道的电效率。

射频离子推力器热特性仿真分析

为了分析射频离子推力器热特性,建立了射频离子推力器整体热模型,基于二维流体模型,对11cm射频离子推力器开展了放电室等离子体仿真,获得了电子温度、电势分布等关键参数;以等离子体仿真结果和实测束电流为输入,获得了各热源的热通量;通过有限元计算获得了关键部组件的温度分布,与实验结果进行了对比分析。研究结果显示:放电室内电子温度约为3.6eV^3.9eV,等离子体电势最高20V,发热损耗主要来自带电粒子轰击放电室壁面和栅极造成的能量沉积、激发原子的热辐射以及射频线圈自身的发热损耗,温度仿真与实测结果一致性良好,最大误差7%,仿真得到的温度分布可以作为输入参数进一步研究栅极受热形变及对束流的影响。

感应式脉冲等离子体推力器技术综述

综合文献及作者研究实践,介绍了感应式脉冲等离子体推力器的原理和特点.从国外研究机构与项目、推力器组件和系统集成实验、工作机理数值仿真等方面,总结和评述了达到的技术状态与认识.最后梳理了面临的技术挑战,提出了可能的解决途径.

三相切向结构永磁电动机电感参数解析计算

提出一种基于基本气隙磁场计算凸极同步电动机电感参数的解析计算法,该方法比使用传统气隙磁导法更方便。在介绍凸极同步电机基本气隙磁场概念及基本气隙磁密的求取的基础上,以一台三相7.5 kW切向式永磁推进电动机为算例,给出了基于基本气隙磁场的永磁电动机电感参数解析计算步骤,推导了电感参数解析计算公式。利用解析计算的参数进行性能仿真与试验所测的结果较好吻合,验证了该方法的有效性和准确性。

均衡电抗器及变压器漏感在12脉波整流系统中的影响分析

以船用推进为背景,对一种带直流均衡电抗器的12脉波整流系统网侧谐波电流表达式进行了推导及简化。综合考虑了变压器交流输入端漏感、整流输出端均衡电抗器、变频器直流输入电压等因素,对其与电网电流总谐波畸变及输入功率因数的关系进行了分析和仿真,仿真与试验表明:计算与实际情况具有较高的吻合度。该方法尤其适用于对系统参数匹配性敏感的特殊船舶应用领域。

混合动力汽车电驱动系统性能比较分析

介绍了混合动力汽车(HEV)驱动系统的结构和工作原理,对混合动力汽车中采用的直流电动机、感应电动机、永磁无刷电动机和开关磁阻电动机等电驱动系统的特点和主要性能作了详细比较和分析,由此得出感应电动机和永磁无刷电动机更能满足要求。

现代船用推进电机技术研究

本文论述了现代船用推进电机技术的发展现状,具体分析了舰船推进发展所需考虑的几项主要性能指标,并对不同类型的推进电机的关键技术指标进行了对比论证。最后,介绍了国外针对几项关键技术指标的发展趋势和采取的一些改进措施。

基于感应滤波的电力推进船舶电网谐波抑制

为研究谐波抑制方法在电力推进船舶电网中的应用,提出了一种基于感应滤波方式,同时具有自耦补偿和谐波抑制作用的新型推进变压器结构。该变压器二次侧采用延边三角形接线,它将传统滤波和无功补偿装置移至绕组内部且公共绕组的等效短路漏电感为零设计,使船舶大功率变流设备在电能变换过程中产生的谐波源无法进入交流网侧,有效地抑制了谐波对船舶电网的污染。对比船舶电网传统滤波方法,对新型推进变压器的结构设计,滤波原理进行了介绍,并分别对基于新型和传统推进变压器的6相交直交推进方式船舶电力系统进行了SIMU-LINK仿真,仿真结果的电流波形和电流频谱验证了方案的正确性和可行性。

一种船用多相电机驱动系统的仿真与实验研究

介绍一种基于dSPACE半实物仿真技术的舰船电力推进多相感应电机控制系统。本系统在MATLAB/SIMULINK环境中建立数据采集、驱动、保护等硬件系统的仿真模型和矢量变换、同步PI电流调节等相关控制算法,利用dSPACE快速控制原型方法对多相感应电机及其逆变器进行控制。15kW样机实验研究表明,所建立的半实物仿真控制系统稳定、可靠,实时性好,且便于在线修改控制结构和相关参数,为舰船电力推进变频调速系统提供一种可行方案,同时也较好地解决了大型舰船综合电力推进系统的试验室闭环测试问题。

磁控等离子体对收敛喷管性能的影响

采用诱导磁场方程,Mixture混合两相流和磁场修正的湍流两方程模型,研究施加不同强度磁场时,收敛喷管内等离子体的流动和传热特性以及等离子体对尾喷流的包裹情况.结果表明,随着气流在收敛喷管内加速,等离子体被掺混的程度增加.增强磁场可提高近壁面处等离子体体积分数,抑制其湍流度,降低高温气体向喷管壁面的传热.当By=1.3 T时,磁控等离子体可降低54.4%的壁面温升,增加0.74%的喷管推力系数,在出口4倍当量直径处对尾气仍有一定的包裹.

船舶电力推进六相感应电机控制系统设计

船舶电力推进是一种先进的推进方式,近几十年达到了空前繁荣。推进电动机及其控制技术是船舶电力推进的关键技术之一,本文介绍的主要是六相感应电机矢量控制系统。通过六相感应电机在d-q坐标系的数学模型,给出了基于TMS320F2812DSP的六相感应电机矢量控制系统的实现,并通过实验验证了本文所提的控制策略。本研究成果有望应用于大功率船用驱动电机。

射频离子推力器束流特性数值模拟

为了分析射频离子推力器束流特性,基于二维流体模型对自研的11 cm射频离子推力器开展放电室等离子体数值模拟,获得给定电气参数下离子密度、电子温度等关键参数的分布特性;研究了等离子体参数和束流大小与射频功率间的函数关系;以等离子体参数和栅极参数为输入,基于离子光学系统模型获得不同工况下的单孔离子引出轨迹。研究结果显示:离子密度和电子温度分别沿放电室径向逐渐减小和增大,有利于获得更好的束流均匀性及更大的束流;束流大小与射频功率呈线性正相关关系,有利于实现束流连续精确可调;屏栅上游鞘层的形成与离子密度、离子种类、栅极电压组合相关,综合考虑以上因素获得最佳束流聚焦和引出特性。