基于TTP协议的飞机配电系统通信仿真研究

针对飞机配电系统典型单元,建立基于时间触发的四节点控制与通信模型;实现系统典型节点的信号交互,并进行实时控制与仿真分析。以供电系统处理机(PSP)、发电机控制器和汇流条控制器的组合(GCUs+BPCU),某个负载管理中心(ELMC)、以及多个固态功率控制器(SSPCs)为四个典型节点,在研究模型节点内部控制与逻辑关系、建立消息时刻表的基础上,仿真了配电系统在双发、单发、应急情况下,汇流条和负载的自动管理。仿真结果表明,信号严格按照确定的消息时刻表传送,通信具有较高的实时性和可靠性。研究结果为时间触发协议在航空器领域的应用提供了参考。     

Design of Boeing 777 electric system

The electric power system for the Boeing 777 is comprised of two independent electrical systems, the main and the backup. The main electric system includes two engine-driven integrated drive generators, a generator driven by the auxiliary power unit, three generator control units, and a bus power control unit. The backup electric system includes two engine-drive generators and one integrated converter/control unit to provide the redundancy of electrical sources equivalent to a three-engine airplane. Automation of the system is achieved by the use of state-of-the-art, microprocessor-based control units that perform system control, protection, and built-in-test functions. Each control unit has redundant two-way communication through an ARINC 629 communication bus that requires significantly fewer discrete wires than similar systems, allowing considerable reduction of the interface circuits and reduction in weight     

飞机用开关磁阻起动/发电系统负载影响研究

组合起动/发电(IS/G)系统是多/全电飞机(M/A EA)的关键子系统,而开关磁阻电机(SRM)被认为是实现飞机IS/G系统的首选机型。研究了负载对开关磁阻起动/发电(SR S/G)系统电能质量及稳定性的影响。针对多电飞机电气系统的特点,所涉及的负载被划分为三类:传统负载、特殊负载和恒功率负载,给出了突加、突卸负载时SRM的输出电压和相电流曲线。同时,对恒功率负载下系统的稳定性进行了理论分析和仿真验证。     

Real-time expert systems for advanced power control (a statusupdate) [aerospace power system testbed]

The most recent developments in the Boeing Aerospace Autonomous Power System (APS) testbed are presented. The APS testbed is a 28-VDC system with 3-kW capability, assembled for use in developing improved control, techniques for aerospace electrical power systems. The main emphasis is on the development of a sophisticated programming environment to control concurrent execution of multiple autonomous algorithms coupled with a continuous input/output data flow. The integration of high-level control algorithms used for battery charge control into a real-time execution environment is discussed. This includes methods that allow several functions to respond to real-time input, affect/maintain expert system (shared) memory, and control the electrical power system configuration. Sophisticated schemes for scheduling these expert system control functions are required to allow real-time multitasking     

High-frequency AC power distribution in Space Station

A utility-type, 20-kHz, AC power distribution system for the space station employing resonant power-conversion techniques is presented. The system converts raw DC voltage from photovoltaic cells or three-phase, low-frequency AC voltage from a solar dynamic generator into a regulated, 20-G kHz AC voltage for distribution among various loads. Operations of the components of the system such as driver inverter, DC receiver, bidirectional receiver, and three-phase AC receiver are discussed. EASY5 computer modeling and simulations were performed to study the local and global performance of the system. Simulation results show that the system has fast response and good transient behavior. The AC bus voltage is effectively regulated using the phase-control scheme, which is demonstrated with both line and load variations. The feasibility of paralleling the outputs of driver modules is illustrated with the driver modules synchronized and sharing a common feedback loop. A high-frequency, sinusoidal AC voltage is generated in the three-phase, AC input case, when the driver modules are phased 120° away from one another and their outputs are connected in series     

基于GRNN算法的飞机用电设备非侵入式负荷监测方法

随着飞机的多电化和全电化,机上电气检测及其负荷管理至关重要,然而飞机上为诊断所设置的传感器数量要求越少越好,非侵入式负荷监测（NILM）方法无需分散进入负荷内部,仅检测汇流条级别电力参数可完成负荷识别。选择稳态电流谐波参数为负荷印记,采集某型飞机交流主汇流条上用电设备真实电流波形,提取1~19次谐波含量建立特征库,用广义回归神经网络（GRNN）算法辨识负荷类别,设置适当样本数和扩展速度以有效提高识别准确度。实验表明：GRNN算法较之BP神经网络算法和SVM算法识别准确度更高,计算速度更适于飞机电气系统负荷监测和管理。将非侵入式负荷监测方法引入飞机供电系统分析,将为飞机电气管理、故障诊断和预测等进一步研究提供有效参考。     

CAN总线在飞机交流电源功率控制器中的应用

交流电源功率控制器(APCU)是实现飞机电气负载控制与电源自动化管理的重要组成部分。系统采用CAN总线设计实现了APCU与供电系统处理机和机电综合管理系统的通信。利用流和管道技术编写了基于DSP/BIOS的CAN总线的设备驱动程序。为了满足通信需求,本论文中共设计了2个CAN接口,一个为F2812内置的CAN接口模块,另一个为通过SJA1000的扩展CAN接口模块以备用。通过实际的通信试验,结果表明系统通信运行可靠,数据传输准确,符合预期的设计目标。     

小型无人机发电系统的研制

本文介绍了一种适用于无人机的专用电源系统的设计方案,该方案由永磁同步发电机和宽电压输入范围的电源变换/调节装置组成.该方案具有系统结构简单、可靠性高、电源品质高和转速范围宽的优点,并对电源系统进行了实验验证,实验结果和理论分析一致.     

燃料电池无人机动力系统方案设计与试验

针对燃料电池为主能源的无人机（UAV）动力系统,设计了纯燃料电池动力系统、燃料电池/蓄电池（简称燃蓄）被/主动混合动力系统3种拓扑结构方案。以空冷质子交换膜燃料电池为例,搭建了燃料电池动力系统方案一体化试验平台。考虑阶梯型和阶跃型2种加载形式,试验研究了燃料电池自身的动态特性和启动特性。以阶梯型功率剖面的加载形式,试验研究了纯燃料电池动力系统放电特性;以无人机典型任务剖面作为加载形式,开展燃蓄被/主动混合动力系统对比试验研究。试验结果表明：纯燃料电池动力方案适用于低机动小型无人机,燃蓄被动混合方案可满足小型无人机大机动飞行,燃蓄主动混合方案系统可适应中大型无人机更长航时飞行。     

基于变频供电系统试验的模拟负载及控制的设计与研究

在民用飞机变频供电系统的设计和适航符合性验证试验中,负载特性的模拟是一项关键技术,为适应变频供电系统负载特性的综合测试和验证对负载模拟的符合性需求,论述了一种适应变频供电环境下的变频模拟负载作为模拟飞机115/200V、(360～800Hz)三相四线制变频供电系统负载的综合电气特性,并为之设计智能控制系统。通过在线优化阻抗参数,提高负载的闭环特性和自适应能力,确保变频供电系统负载电气特性参数测试的准确性。     

多电飞机混合储能系统的设计与仿真

多电飞机直流配电系统是电功率传输的核心,由于涡轮电机的单向性,系统并不完全可逆。为了维持直流汇流条的稳定、提高能源效率,需建立相应的存储和消耗系统。研究了一种带有超级电容器的多电飞机储能系统,分析了该系统中超级电容器的作用及其控制策略,根据超级电容器本身的特性利用Matlab/Simulink软件建立相应仿真模型,并针对于飞机电网突加和突卸负载时电压不同状态设计了相应控制策略,通过仿真实验验证了带有超级电容器的混合储能系统的有效性。     

Starter/generator employing resonant-converter-fed induction machine. II. Hardware prototype

The feasibility of operation of a new procedure to start a jet engine (JE) and to generate power by means of a single induction machine (IM) directly coupled to the turbine has been shown by means of a hardware prototype. An introduction, background, operation principle of this type of a system and software simulation portion was presented in Part I. Both in software simulation and in the experimental phase of the studies the JE is replaced by a DC machine. The DC machine is brought to an initial speed by the motoring operation of the IM. Later, the IM is taken into generating mode and the DC machine is into motoring mode of operation. This mode would correspond to the turbine catch-up initiation phase and initiate driving phase of the induction generator in the actual world. The generated power is then converted to a three-phase, 400 Hz (in software), 60 Hz (in hardware), 115 V voltage-regulated bus via a double stage power conversion utilizing a 20 kHz parallel resonant high frequency AC link and pulse density modulated converter technology. Independent of the coupled machine speed, a constant amplitude and constant frequency three-phase voltage-regulated AC bus is formed and maintained by the proper control of the power converters.     

Prognostic Health Management of Aircraft Power Generators

In this paper, prognostic tools are developed to detect the onset of electrical failures in an aircraft power generator, and to predict the generator's remaining useful life (RUL). Focus is on the rotor circuit since failure mode, effects, and criticality analysis (FMECA) studies indicate that it is a high priority candidate for condition monitoring. A signature feature is developed and tested by seeded fault experiments to verify that the initial stages of rotor faults are observable under diverse generator load conditions. A tracking filter is used to assess the damage state and predict generator RUL. This information helps to avoid unexpected failures while reducing the overall life-cycle cost of the system.     

交直流共用主电路及其控制方法在双输出航空静变电源中的应用

详细介绍一种通过交直流变换共用主电路实现同一电源双路分时输出的方法,给出了交直流共用主电路的拓扑结构及其工作原理,分析了交流变换五电平载波移相及直流变换级联移相控制策略。为了在三相交流变换电路的基础上实现大功率直流输出,并兼顾各相功率均衡,提出了一种相位角同步的均流控制策略。最后通过试验实现了同一电源分时输出交流115 V/400 Hz/100 kVA和直流270 V/80 kW,验证了所述拓扑结构和控制策略的合理性与可行性。     

Implementation of a single-phase AC/AC converter based on neutral-point-clamped topology

A single-phase ac/ac converter based on neutral-point-clamped scheme is proposed to perform unity input power factor and to provide a stable ac voltage to the critical loads. The ac/dc rectifier part is controlled to generate a unipolar pulsewidth modulation (PWM) waveform on the ac terminal by using four power switches with voltage stress of half the dc-link voltage. The carrier-based current control scheme is employed in the inner control loop to track the line current command. To regulate the dc bus voltage, a proportional-integral (PI) control is adopted in the outer control loop. The dc/ac inverter part of the system with four power switches is employed to generate a stable and clean sinusoidal output voltage to the critical load. The instantaneous current control scheme is used to track the output voltage command. To verify the effectiveness of the proposed control algorithm, the simulation and experimental results based on a laboratory prototype were implemented and discussed.     

现代飞机交流电源系统的不中断供电技术

现代飞机上安装了大量的微处理机、计算机。由于电源之间正常转换而出现的电源短暂中断现象会对微处理机、计算机的工作产生干扰。研制不中断供电的电源系统已是刻不容缓的任务。本文讨论了电源正常转换时电源中断现象及原因。以现代大型飞机上的电源系统不中断供电技术为例,阐述消除电源中断的技术方案以及汇流条保护控制组件(BPCU),发电机控制组件(GCU)内有关不中断电源转换的逻辑。     

Power management and distribution system for a more-electricaircraft (MADMEL)

A five-phase Power Management and Distribution System for a More-Electric Aircraft (MADMEL) program was awarded by the Air Force to Northrop/Grumman Military Aircraft Division in September 1991. The objective of the program is to design, develop, and demonstrate an advanced electrical power generation and distribution system for a More-Electric Aircraft (MEA). The MEA emphasizes the use of electrical power in place of hydraulics, pneumatic, and mechanical power to optimize the performance and life cycle cost of the aircraft. This paper presents an overview of the MADMEL program and a top-level summary of the program results, development and test of major components to date. In Phase I and Phase II studies, the electrical load requirements were established and the electrical power system architecture was defined for both near-term (NT-year 1996) and far-term (FT-year 2003) MEA application. The detailed design and specification for the Electrical Power System (EPS), its interface with the Vehicle Management System, and the test set-up were developed under Phase III. Phase IV, fabrication and testing of the subsystem level hardware, has been completed. Overall system level integration and testing, Phase V, is scheduled to be completed by September 1999     

用于航空高压直流电源系统的笼型异步发电机控制策略的研究

 现代电力电子技术的发展使得笼型异步发电机能够适用于航空高压直流系统中。着重对笼型异步电机与电力电子变换器结合构成的发电系统进行了研究,说明了采用直接转矩控制策略可使这种发电系统具有很好的动态特性。介绍了异步发电机直接转矩控制的原理与实现方法,并给出了仿真与实验结果。     

并联混合动力齿轮传动涡扇发动机建模与性能分析

为对比探究未来大推力航空混合动力系统与传统航空发动机的优劣,本文依托某概念型齿轮传动涡扇(Geared turbofan,GTF)发动机,设计了一个并联航空油-电混合动力系统(hybrid GTF,hGTF),在Matlab /Simulink数字仿真软件中建立相匹配的电动力模型以及氮氧化物NOx排放和噪声预测等性能参数计算模型,并在稳态和飞行任务剖面下初步分析了电动力系统的引入对原基线GTF发动机的性能改变状况。稳态仿真结果表明,大推力等级的并联油-电混合动力系统中,至少需要兆瓦级的电动力系统进行匹配;当电动力系统处于电动模式时,可能会带来低压压气机喘振的隐患;当电动力系统处于再生模式时,电能源相当于经过了电能到机械能再到电能的二次效率损失,不建议采用。飞行任务剖面动态仿真结果表明,相比于传统GTF发动机,hGTF推进系统的燃油消耗率最高下降15%,总燃油消耗节省8.3%, NOx总排放量减少18.8%,各部件起飞噪声总声压级减少1.5~3.3dB。分析结果表明采用并联混合动力系统具有显著提升省油、减排效果的能力,同时也具有一定的降噪潜力。