航空电源机电一体化的发展

航空电源作为飞行器第二动力源是飞机重要功能系统,它一直为飞机设计师和使用部门所重视。近代飞机性能不断提高,装备了大量机载用电设备,包括电子、计算机等。因此,对飞机供电系统要求日益提高,飞机早期使用的低压直流电源及交直流混合电源已远远满足不了主机的需要。从70年代起我国重视引进西方先进航空电源技术,并对航空电源研制生产厂所给予了一定关注与必要的投入,研制水平取得了可喜的进步。     

机载大功率超导发电机发展现状与展望

新一代飞机对电力的需求越来越大,尤其是定向能武器的使用,将需要兆瓦(MW)级的电源系统。由于超导发电机发电功率大、结构简单、重量轻,是机载大功率用电设备的理想电源。本文综述了机载超导发电机的类型、研究进展和关键技术,分析指出了其未来的发展前景。     

基于机载静变器的三相交流地面电源车设计与应用

引言 针对机载电子设备的广泛应用和对供电品质的高要求，为满足某型号预警飞机“任务系统”用电设备的地面维护、供电需求。介绍一种基于机载静变电源的为机上或地面机载电子设备供电、调试和维护，提供三相交流电源的便携式三相交流多功能地面电源车的设计和应用。     

机载用电设备的供电适应性试验系列标准制定与实施

机载用电设备的供电适应性试验是对各类机载用电设备在各种供电状态下的性能以及用电设备工作对供电系统影响的验证，是保证用电设备（尤其是大功率电子设备）与飞机供电系统相兼容的重要措施和方法。本文阐明了我国机载用电设备的供电适应性试验系列标准的组成和相互关系，着重对供电适应性试验方法标准的定位、框架、结构要素的确定和主要内容进行了分析，并提出实施供电适应性方法标准的建议。     

对GJB181-8 6贯彻实施中一些问题的修订建议

扼要介绍了 GJB181—86《飞机供电特性及对用电设备的要求》在研制和定型的机载火控设备中的应用情况及在使用中出现的问题,并提出了一些修改建议。     

飞机电压尖峰要求和试验方法标准分析

对比分析了MIL-STD-704系列标准中关于电压尖峰的要求和RTCA DO-160、MIL-STD-461等标准中的试验方法,为开展飞机电气系统设计和机载用电设备电压尖峰试验提供指导。     

苏-27飞机电源系统

苏-27飞机电源系统的主要功用是向飞机上用电设备提供交、直流电能,保证机上交、直流用电设备能够正常工作。苏-27飞机电源系统主要包括:交流供电系统;直流供电系统;地面供电系统。     

机载用电设备谐波试验系统的研究与实现

现代飞机因机载任务系统多、用电设备负载特性复杂,易造成电网谐波偏高甚至超标的情况,因此,必须考核用电设备在供电谐波时的工作可靠性。飞机供电特性国军标未对此做出规定,参考HB 6167第18部分:电源输入试验航空标准设计了谐波试验系统。分析了谐波产生原理,设计了适应中频500VA供电系统的谐波产生电路,采用基于USB的数据采集系统对波形进行采样分析。测试结果表明,系统硬件选型正确,谐波畸变达到了设计要求,但HB 6167推荐方案存在操作不便、谐波可控性不佳的缺陷,针对以上不足,给出了改进意见。     

军用飞机机载用电设备供电兼容性验证要求分析

在综合分析机载用电设备GJB 181-1986和GJB 181A-2003符合性验证要求,以及MIL-STD-704F、DO-160G符合性验证要求的基础上,对国内军用飞机机载用电设备供电兼容性试验的开展现状和试验项目要求进行了分析,并对机载用电设备开展GJB 181B-2012标准符合性试验验证的要求提出了一些验证建议。     

试飞中分离相负载不平衡引起电压偏离量的方法

飞机上存在着许多单相用电设备,它们消耗功率不同、工作状态不同,致使机载电源系统处于不对称的运行状态。在这种状态下所测得的供电系统调压点的电压数据,实际上包合了系统配电不平衡引起的电压偏离量,不能直接用于评定新研制电源系统的调节水平。本文介绍了在电源系统试飞中分离相负载不平衡引起电压偏离量的方法。     

Compact equipment for on-board communications subsystem supervisoryand control system

Onboard equipment for the communications subsystem supervisory and control (CSC) system of a next-generation multibeam high-capacity communications satellite is discussed. In order to keep the equipment as compact, lightweight, and low in power consumption as possible, an onboard data bus system using four kinds of LSIs was developed. It will be carried on-board the Japanese Engineering Test Satellite VI for launch in 1993. Configuration and functions of the CSC equipment, design philosophy of the LSIs, and characteristics of the LSIs developed are discussed     

Aerospace High Voltage Development

High voltage has been used for electrical power system generation, transmission, and distribution for over 75 years and manufacturers have been designing x-rays, radios/television transmitters and receivers for many years with excellent success. High voltage usage in aerospace equipment initiated during World War II with the advent of high power communications and radar for airplanes. About 20 years ago the first high voltage components were built for spacecraft systems. This article is to provide some insight into the status of high voltage for aerospace equipment and the differences between terrestial and aerospace system functions and the attendant problems. What are the basic differences between terrestial/commercial and aerospace equipment? The aerospace environment is defined as that significantly above the Earth's surface: From 5000 feet altitude to deep space. The basic differences are the constraints placed on the user vehicle (airplane, missile, or spacecraft). Constraints include: Atmospheric pressure, temperature, lifting capability, electronic requirements, and volume. Early airplanes needed only radios and mechanical pressurization instruments. Today's sophisticted airplanes require transmitters, receivers, controls, displays, and in the military case, special electronics. The addition of electronic devices has increased the electrical power demand from a few watts (for early aircraft) to well over one megawatt for special applications. There is the need for compact packaging to reduce weight and volume. Spacecraft with booster limitations are ever more restrictive of weight and volume then airplanes while they must maintain complete electrical system integrity for mission durations of several months to years.     

民用飞机辅助发电机多功能试验装置的设计与实现

根据民用飞机辅助发电机(APU GEN)试验需求,设计并实现了专用于APU GEN试验的APU GEN多功能试验装置,该装置可远程操控,不仅具有冷却功能和加热保温功能,而且还具有润滑油流量连续可调节功能、联锁控制以及保护功能,能较好地满足APU GEN的试验需求。该装置的成功实现,不仅保障了民用飞机电源系统设计验证工作,而且还积累了我国民用飞机电源系统试验配套设施研制经验,对我国民用飞机电源系统试验具有重要的指导意义。     

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。     

Adaptive path planning for VTOL-UAVs

This describes the development of path planning algorithms of a small unmanned four-rotor helicopter. A powerful simulation environment of the whole UAV system - including the characteristics of the important ranging sensors for collision avoidance was developed. This is essential for developing, testing, and verifying of the algorithms. Different collision avoidance strategies for VTOL-UAVs are presented. Enhancements and miniaturization will offer more powerful sensor technologies regarding size, range, and power in the future. Very promising are improvements of sensor modules and new technologies like three-dimensional LASER range-finder, PMD sensors, RADAR range-rmnder, and stereo camera tracking system. Because of the general high level simulation tool introduced herein they can he easily validated and tested without the need and effort of a real hardware implementation. The results showed that adaptive path planning, including collision avoidance, is already applicable on-board small UAV vehicles. With the mentioned new sensor technologies and more calculation power, further improvements like advanced collision notice and global path planning on-board small UAVs are attainable.     

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。     

Recent active thermal management technologies for the development of energy-optimized aerospace vehicles in China

Recently, the development of modern vehicles has brought about aggressive integration and miniaturization of on-board electrical and electronic devices. It will lead to exponential growth in both the overall waste heat and heat flux to be dissipated to maintain the devices within a safe temperature range. However, both the total heat sinks aboard and the cooling capacity of currently utilized thermal control strategy are severely limited, which threatens the lifetime of the on-board equipment and even the entire flight system and shrink the vehicle’s flight time and range. Facing these thermal challenges, the USA proposed the program of “INVENT” to maximize utilities of the available heat sinks and enhance the cooling ability of thermal control strategies. Following the efforts done by the USA researchers, scientists in China fought their ways to develop thermal management technologies for Chinese advanced energy-optimized airplanes and spacecraft. This paper elaborates the available on-board heat sinks and aerospace thermal management systems using both active and passive technologies not confined to the technology in China. Subsequently, active thermal management technologies in China including fuel thermal management system, environment control system, non-fuel liquid cooling strategy are reviewed. At last, space thermal control technologies used in Chinese Space Station and Chang’e-3 and to be used in Chang’e-5 are introduced. Key issues to be solved are also identified, which could facilitate the development of aerospace thermal control techniques across the world.     

THE DIGITAL WAVE-PROCESSING EXPERIMENT ON CLUSTER

The wide variety of geophysical plasmas that will be investigated by the Cluster mission contain waves with a frequency range from DC to over 100 kHz with both magnetic and electric components. The characteristic duration of these waves extends from a few milliseconds to minutes and a dynamic range of over 90 dB is desired. All of these factors make it essential that the on-board control system for the Wave-Experiment Consortium (WEC) instruments be flexible so as to make effective use of the limited spacecraft resources of power and telemetry-information bandwidth. The Digital Wave Processing Experiment, (DWP), will be flown on Cluster satellites as a component of the WEC. DWP will coordinate WEC measurements as well as perform particle correlations in order to permit the direct study of wave/particle interactions. The DWP instrument employs a novel architecture based on the use of transputers with parallel processing and re-allocatable tasks to provide a high-reliability system. Members of the DWP team are also providing sophisticated electrical ground support equipment, for use during development and testing by the WEC. This is described further in Pedersen et al. (this issue).     

A PC based test system for an on-board computer

This paper presents a robust method of testing a processor based on-board computer used in the Indian remote sensing satellite (IRS-1C). The novelty of this scheme lies in a judicious mix of software and hardware approaches adopted to realise this PC-based system. All the electrical interfaces (like telemetry, Telecommand, timer and star sensor) are simulated. They are fabricated as add-on cards to PC-AT (ISAbus). The on-board computer controls two star sensors apart from handling three telemetry streams and accepting more than one hundred Telecommands     

某火力电厂机组控制系统的设计与实现

以某火力发电厂的建设为整体背景,结合电厂设计过程中实际出现的问题,以及以往的设计经验,利用MaxDNA控制系统,展开对于整体火力机组控制系统中的软硬件的设计。通过某火力发电厂实地进行联调联试,确保相应的设备能够正常的工作,以保证机组的正常运行。系统运行情况良好,基本实现工艺设备的控制要求,获得了用户的认可,降低了相关工作的工作强度,取得很好的经济效益。