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。     

New Data Bus Interface Technique

Data bus systems as defined in MIL-STD-1553B are widely used in aerospace instrumentation systems for digital data transmissions between units on the bus. Although the bus is protected against a short circuit which may occur in the remote unit electronics or transformer, it has no protection against a cable termination failure. Open or short failure along main bus cable results in failure of the entire bus system. A new data bus interface technique is described which is insensitive to cable termination failure. The central feature of this new interface circuit is that communication between main unit and remote units is not affected by the cable termination failure. In applications such as multistage missiles, no provisions need be made for retermination in the cable characteristic impedance after stage separation. The key to this new technique is a directional coupling transformer which is only slightly more complicated than standard interface transformers. Design equations for directional coupling transformer and experimental results of new data bus systems are presented.     

270-VDC/hybrid 115-VAC electric power generating system technologydemonstrator

The approach, system architecture, instrumentation, and performance of a technology demonstrator system for the application of 270-VDC/hybrid 115-VAC electrical power generation and distribution to future military aircraft are examined. The design has focused on assembling a highly flexible test system. The loads are typical of those in a hybrid electrical system. The system consists of a single 3-phase, 115-VAC electrical generator whose output is rectified, filtered, and supplied through DC contactors to both a 270-VDC load bus and to the input of an inverter, which supplies a 400-Hz, 115-VAC load bus. A variable-frequency, 115-VAC bus is also available directly from the generator. A prototype variable-speed constant-frequency 120-kVA generator is used. The test facility is designed to provide loads to all power types capable of being produced by the system. The system has provided particularly good insight into various aspects of 270-VDC/115-VAC hybrid systems and their components     

新支线飞机供电系统航电接口仿真器设计

为了满足新支线飞机ARJ21供电系统地面独立试验的需要,设计了用于模拟航空电子系统、发动机系统等与电气系统之间相关接口功能的仿真器,为电气系统提供其它飞机系统的仿真信号并指示供电系统的运行状态.为验证供电系统的各项性能提供支持.实际运行结果表明在新支线飞机ARJ21供电系统的12种状态下仿真器对导光板和供电系统的控制逻辑正确,对电源系统简图页和EICAS信息指示合理,通过ARINC429总线与各发电机控制器的通信正常,各项功能与飞机系统设计一致,完全能够满足飞机供电系统综合试验的要求.     

基于不同拓扑结构的十二相同步发电机整流电压波形分析

传统中小功率十二相整流型同步发电机电压等级较低,整流装置通常采用4套不控整流单元并联结构。随着舰船中压直流综合电力技术的发展,整流发电系统的容量和电压等级大幅提升,十二相整流单元采用两并两串的拓扑结构可以适应发电机绕组较高的电压设计值,同时整流端中性线可引出用于电力推进调速装置的均压控制。分析了两并两串拓扑结构的不同联接组合型式,重点对两种可行的拓扑结构下的直流侧电压波形进行了解析计算,并通过仿真与试验验证了理论分析的正确性,证明了(Y1//Y3)+(Y2//Y4)拓扑结构为最优组合方式,具有最佳的直流电压品质。     

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。     

Dynamics of Wind Generators on Electric Utility Networks

Dynamic interaction of wind-turbine-driven generators on electric utility networks was studied by computer simulation. Nonlinear representations of wind-turbine and various drive train elements and Park equation representations of synchronous and induction generators were implemented. An infinite capacity network was assumed. Time history responses for various system configurations were computed using as the input function severe wind gust data added to cyclical torque variations occurring at turbine blade frequency. Results indicated that severe transient mechanical and electrical stresses can be induced for certain system configurations. Best results were obtained by interposing rate or damped compliant couplings between the wind turbine and a synchronous generator. The induction generator did not appear to require such means. Blade pitch control (or equivalent) was required to limit output above rated wind velocities for wind turbines configured to produce maximum mum specific power. The blade pitch control loop must exhibit high performance to limit transient overshoots. An aerodynamically limited turbine driving an induction generator exhibited good response without the need for blade pitch control, but at the cost of increased turbine rotor diameter. Further work is indicated, taking into account wind-turbine aeroelastic effects, finite capacity networks, and other factors.     

ARINC429总线接口设计与实现

ARINC429总线在航空电子系统领域被广泛的应用。本文分析了ARINC429总线的工作原理,根据其数据格式、接口电平要求,给出了由FPGA设计实现ARINC429总线的基本原理,并通过VHDL语言编程,实现了ARINC429总线协议部分,实现了接收和发送功能。采用FPGA器件设计集成ARINC429总线协议的通信芯片,可以有效地提高数据通信模块的处理能力和集成度。通过实际与通用型ARINC429总线芯片的通讯,验证了方案的正确性。     

某型民机电源系统发电机控制器一体化测试系统研制

随着多电飞机、全电飞机高速发展,对民机电源系统各控制部件,尤其对发电机控制器（GCU）提出更高的质量要求和测试系统建设需要。为降低测试系统技术输入难度和后续能力扩展费用,提升我国民机系统核心部件的部件级测试水平,首先比对了国内外民机主制造商在部件级测试领域的能力现状,然后详细分析了某型民机电源系统发电机控制器的结构功能、技术指标,最后从该发电机控制器的测试需求出发,提出一种通用化、标准化、模块化的一体化测试系统,通过建立电源系统核心部件功能、性能验证及排故、维修能力,力求覆盖入厂接收检验严格管控、总装地面功能试验高效排故、外场运营维护快速响应多应用场景测试要求,最终实现我国民机测试保障体系的建设目标。     

基于模型的多电飞机能源优化特性仿真分析

多电飞机是一种用电能部分取代原来的液压能和气压能的飞机,其二次能源系统以电能为主。为实现多电飞机能源系统的优化设计,将飞机的发电、配电和用电集成在一个统一的系统内,实行发电、配电和用电的统一规划、统一管理和集中控制。为快速有效地分析多电飞机能源系统优化特性,本文采用基于模型的系统工程方法论,针对多电飞机能源优化仿真分析平台开展研究,提出了一种面向电气设备的多物理域模型建模方法,以实现机载系统的大规模集成仿真。并以飞控系统为对象,建立了多电飞机飞控系统和传统飞机飞控系统的能量利用、能量传送、能量变换设备等仿真模型,仿真分析了两种飞控系统的能源应用特性,为多电飞机能源系统的优化设计提供了有效支撑。     

基于佘度和容错技术的高可靠机载智能配电系统设计

针对大型无人机(UAV)用常规配电系统占用航空总线资源多和可靠性低的问题,通过研究多电/全电飞机技术发展趋势和大型无人机供电系统技术特点,提出一种适用于大型无人机体系结构和指标要求的机载智能配电系统;建立系统的马尔可夫模型,计算和分析不同余度结构的供电处理机(PSP)和电气负载管理中心(ELMC)对系统可靠性的影响,进...     

变循环发动机完全分布式控制

采用分布式控制架构可以降低变循环发动机控制系统的重量并有利于系统的开发和扩展。提出了一种完全分布式控制架构,控制算法的计算完全分布到智能执行机构中,计算所需的参数值由智能传感器通过串行数据总线发送到智能执行机构。变循环发动机完全分布式控制系统研发的主要工作是设计分散控制算法和总线通信方案。将控制回路的耦合当作总扰动的一部分,使用线性自抗扰控制器(ADRC)观测并在控制信号中消除总扰动,实现了分散控制。在CAN总线硬件的基础上,使用CANaerospace高层协议设计了时间触发的总线通信方案。从而实现了变循环发动机完全分布式控制。在MATLAB/Simulink环境下使用TrueTime工具箱搭建了仿真系统。使用TrueTime Kernel模块仿真智能执行机构与智能传感器的计算单元,使用TrueTime Network模块仿真CAN总线,并且将线性ADRC和CANaerospace协议写入到计算单元中。仿真结果表明:所建立的变循环发动机完全分布式控制系统能够适应发动机进气状况和健康状况的大范围变化,具有较好的鲁棒性。     

Modeling of brushless DC generating systems using diakoptics

The mathematical modeling of a brushless DC generator is described, as an illustration of the application of diakoptic techniques to the analysis of small-scale electrical power supply systems. Modeling of the generator and its output rectifier is accomplished using an established matrix technique that accounts for the continuously changing conduction pattern of the diode bridge network. The advantages of using diakoptics are discussed together with the main generator linked to its exciter and to the automatic voltage regulator and permanent magnet generator which are often included in a complete unit. A solution algorithm is presented for this overall arrangement and a comparison is made between theoretical and practical results for a typical 3-stage, 4000-rev/min, 10.3-kW, 28-V unit     

Moving towards a more electric aircraft

The latest advances in electric and electronic aircraft technologies from the point of view of an "all-electric" aircraft are presented herein. Specifically, we describe the concept of a "more electric aircraft" (MEA), which involves removing the need for on-engine hydraulic power generation and bleed air off-takes, and the increasing use of power electronics in the starter/generation system of the main engine. Removal of the engine hydraulic pumps requires fully-operative electrical power actuators and mastery of the flight control architecture. The paper presents a general overview of the electrical power generation system and electric drives for the MEA, with special regard to the flight controls. Some discussion regarding the interconnection of nodes and safety of buses and protocols in distributed systems is also presented     

1553B总线在现代飞机自动配电系统中的应用

对1553B总线通讯技术进行了系统的研究。设计了采用80C196KB作为主处理机的1553B通讯接口板，设计并调试成功了1553B的通讯软件，并在双发电通道飞机自动配电系统地面模拟系统中进行了实验。系统模拟实验表明，与通用串行总线(如RS-485总线)相比，军用数据总线1553B有高传输率、高可靠性等特点，为飞机自动配电系统的应用奠定了坚实的基础。     

分级式航空电子综合化仿真系统研究

介绍一个分级式航空电子综合化仿真系统。该系统以航空电子综合化工程中一个分系统为仿真目标,由两层双余度1553B总线和MBI(multiplex bus interface)将AVS(Avionics simulator)、SSCU(subsystem control unit)、若干个EQS(equipment simulator)以及部分真实设备连成的三级分布式计算机系统。一个面向实时控制的分布式操作系统和相应的仿真软件分布在三级仿真器中;其中,分布式操作系统实现两级总线的衔接、通信控制、并行多任务管理、错误检测、故障处理和实时内存数据库管理,仿真软件模拟航空电子上层环境、操作员控制与显示、分系统各设备数据产生与接收数据处理以及信息处理应用任务。系统研制成功为工程化实现打下了技术基础并提供了一个实验环境。     

Direct drive options for electric propulsion systems

Power processing units (PPUs) in an electric propulsion system provide many challenging integration issues. The PPU must provide power to the electric thruster while maintaining compatibility with all of the spacecraft power and data systems. Inefficiencies in the power processor produce heat, which must be radiated to the environment in order to ensure reliable operation. Although PPU efficiencies are generally greater than 0.9, heat loads are often substantial. This heat must be rejected by thermal control systems which generally have specific masses of 15-30 kg/kW. PPUs also represent a large fraction of the electric propulsion system dry mass. Simplification or elimination of power processing in a propulsion system would reduce the electric propulsion system specific mass and improve the overall reliability and performance. A direct drive system would eliminate all or some of the power supplies required to operate a thruster by directly connecting the various thruster loads to the solar array. The development of concentrator solar arrays has enabled power bus voltages in excess of 300 V which is high enough for direct drive applications for Hall thrusters such as the Stationary Plasma Thruster (SPT). The option of solar array direct drive for SPTs is explored to provide a comparison between conventional and direct drive system mass     

基于第二动力技术的TBCC综合能源展望

飞行器电能、液压能和气压能的功率需求由第二动力系统单独做功或提取发动机主轴功率供应。TBCC发动机模态转换后,第二动力系统无法从发动机主轴提取功率。因此,需要解决空天飞行器第二动力系统长时间大功率能量输出的问题。分析航空蓄电池、起动发电机、APU、GTS、ATS和RAT的技术特点、发展现状以及第二动力的发展趋势,结合高超声速飞行器的发展趋势,提出ATS/RAT组合和多电超导发动机/大比能的储能装置技术组合是实现空天高超声速飞行器综合能源的技术路线。     

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     

基于CAN总线电源控制系统设计

利用CAN总线良好的适用性,设计了基于CAN总线的电源控制系统;采用集成CAN控制器的C8051F040作为主控芯片,很好地实现了通信和控制功能。