基于人因工程视角的民机驾驶舱告警系统研究综述

为研究现代民机驾驶舱告警系统的发展历程及应用现状,通过文献综述,以人因工程学为视角,结合事故调查分析、国内外民机驾驶舱告警系统应用进展,了解民机驾驶舱告警系统功能、告警方式和告警类别,总结国内外驾驶舱告警系统概况,分析民机驾驶舱告警系统现存问题。基于驾驶舱告警的适航管理规章要求和机组在飞行任务中的认知需求,探究驾驶舱告警系统的设计需求。结合人因工程领域的研究进展,提出驾驶舱告警系统的改进方向和发展趋势,即民机告警系统设计的及时性和可靠性还存在一定改进空间,驾驶舱告警系统整体结构的设计必须要突出重点,注重自主化及个性化设计,必要时考虑驾驶舱触觉感知的融合,旨在为后续告警系统的总体设计及优化提供参考。     

A door-opening system using a low-cost fingerprint scanner and a PC

Biometrics can offer improved security for access control. Several biometric devices can be adapted to our special requirements and some criterion is needed to choose the best solution for us. On the one hand, it is possible to use a standalone embedded system. On the other hand, a low-cost PC-based system can be better fitted to our special requirements, by means of special purpose software. With the actual reduction on the price of informatic components, it can be a good alternative. This describes one of these systems for door-opening with the user's fingerprint. Special emphasis is given on the design, advantages, and inconveniences with respect to embedded systems.     

High accuracy navigation and landing system using GPS/IMU systemintegration

In this paper, the accuracy, integrity and continuity of function requirements for automatic landing systems using satellite navigation systems are discussed. Such a landing system is the integrated navigation and landing system (INLS) developed by Deutsche Aerospace (DASA/Ulm, Germany). The system concepts of the INLS are presented. It is shown how an INLS, based on system integration of a satellite navigation system (e.g., GPS) in realtime differential mode with an inertial measurement unit (IMU) in the accuracy class of an attitude and heading reference system (AHRS), can meet the requirements: the results given are mainly devoted to the accuracy issues. Using Kalman filter techniques, an in-flight calibration of the IMU is performed. The advantage of system integration, especially in dynamic flight conditions and during phases of flight with satellite masking, is explained. The accuracy, integrity and continuity of function of the INLS were proven by means of flight tests in a commuter aircraft using a laser tracker as a reference. These flight tests have shown that the short-term accuracy (<60 seconds) of the AHRS used within the INLS has been improved from low cost sensor quality to the accuracy of a high quality laser inertial navigation system (LNIS). With the presented INLS, a landing at any airfield, not equipped with conventional Instrument Landing System (ILS) or Microwave Landing System (MLS), is possible by using a very cost effective system. The INLS is a high accuracy navigation and landing system designed to be used instead of conventional landing systems at small airfields and to fill operational gaps of conventional navigation and landing systems in cruise and approach on large airports     

复杂环境下翼伞系统的组合式航迹规划

传统翼伞系统的航迹规划主要考虑落点精度及逆风着陆等指标,而当空投区域环境较为复杂,在翼伞系统归航路径上存在障碍时,如何规避这些障碍也成为翼伞系统航迹规划所必须要考虑的因素。针对翼伞空投过程有可能遇到高山或者高大建筑物阻碍的问题,提出了一种复杂环境下翼伞系统的组合式航迹规划策略。该方法将翼伞空投的区域分为障碍区和着陆区,在障碍区中采用快速搜索随机树（RRT）算法进行可行路径搜索,考虑到RRT算法生成的轨迹包含棱角,导致路径不够平滑的问题,结合翼伞系统质点模型的运动特性,对其进行了适用性改进,以使规划的航迹满足实际翼伞空投需求。为了解决RRT算法搜索方向随机,难以满足逆风着陆的问题,当翼伞系统进入着陆区后采用分段归航的方式设计航迹,并借助遗传算法（GA）求解目标参数,实现翼伞系统能量控制及逆风着陆。提出的复杂环境下翼伞系统的组合式航迹规划策略求解速度较快,能够同时满足翼伞系统避障、能量控制及逆风着陆要求,得到的参考航迹较为平滑。     

离散型制造企业生产质量信息管理与集成

针对离散型制造企业的质量管理,就生产质量管理系统与企业其他应用系统的信息集成问题展开研究,分析了生产质量管理系统与企业其他应用系统的集成需求,提出了实现方法。     

Mission/flight systems integration study: a long-term electronicsplanning project

The objective of the Mission/Flight System Integration Study (M/FSIS) is to identify the requirements and development objectives for electronics systems technologies and conceptual architectures in future weapon system applications (in and around the year 2005), based on analyses of future missions, threats, scenarios, aerospace system concepts, and technology trends. The products are substantiated requirements for future electronics functions, systems, and architecture; technology development objectives and roadmaps; and conceptual electronics architectures and functional definitions. The study outputs will serve to guide laboratory technology development planning and programs; guide weapon system program office long-range electronics planning; illustrate user needs in terms of electronics requirements; and guide air logistics center weapon-system master planning     

面向风险均衡的AFDX虚拟链路路径寻优算法

为确保综合模块化航空电子系统的安全性需求能够在全双工交换式以太网中得到一致性保证,提出了一种面向风险均衡的路径规化（RBPP）算法,以满足各航电功能间的安全隔离要求,同时分散风险,避免局部物理链路的风险集中,提高系统安全性。以民机失效状态类别划分为基础,建立了航电功能、分区、端系统、虚拟链路（VL）风险模型;RBPP以均衡各物理链路风险为目标,同时综合考虑网络实时性、链路负载能力等因素,采用粒子群算法进行优化目标求解。利用仿真优化方法对RBPP算法进行了实现,在典型工业航空电子全双工交换式以太网（AFDX）网络架构及A380AFDX网络架构下进行仿真分析,结果显示多播VL的简化处理的会使网络风险增加;在1 000条VL配置下与负载均衡（LB）算法和最短路径（SP）算法进行了分析对比,结果显示RBPP算法在满足各航电功能间的隔离需求的同时,链路风险均衡能力在两种网络拓扑下分别比负载均衡算法提高了10.7%和23.4%,比最短路径算法分别提高了35.4%和47.9%。     

系统安全性评估中飞行机组人为因素的分析方法

随着飞机系统日益高度综合复杂和自动化水平逐渐提高,飞行员在应对失效或应急情况时往往准备不足,纠正动作可能是不正确、不及时或不完整的,因此系统安全性评估中迫切需要考虑飞行机组人为因素问题。通过分析CCAR25.1309（b）和（c）条款的要求和飞行机组对失效的处理过程,基于功能危险性评估中的失效状态,提出人为因素需求的捕获方法和人为因素分析方法;通过在型号中应用这些方法,从失效状态向告警和程序的角度实现安全性正向设计,建立安全性评估中飞行机组人为因素的完整适航符合性证据链。结果表明：本文提出的方法可有效表明对CCAR25.1309（b）和（c）条款中人为因素相关的适航符合性。     

基于MBSE的副翼及其操纵系统研发技术及应用

飞机的设计研发是一项涉及多学科领域、多目标、多约束的复杂系统工程过程,系统耦合紧密、参与人员众多、设计信息庞杂,以文档为中心的需求管理等传统研发方法突显出一定的困难,亟需探索新的飞机设计研发方法。以副翼及其操纵系统为研究对象,对基于模型的系统工程(Model Based System Engineering,以下简称MBSE)方法进行了探索研究:采用达索MBSE方法论-MMS(Modeling Methodology for Systems,以下简称MMS),从使命、服务、功能和组件不同视角对副翼及其操纵系统研发的各个方面进行解析,进而完整定义系统;利用达索3D Experience平台,通过RFLP系统工程架构,进行了副翼及其操纵系统的需求开发、功能分析及逻辑架构设计,完成了需求、功能、逻辑架构、系统仿真、物理设计等模型的关联追溯,实现了以达索MBSE方法论为核心的研发技术的有效应用。     

基于管道-过滤器模式的机载导航数据库格式化技术研究

针对飞行管理系统机载导航数据库应用需求,以管道-过滤器模式的软件架构体系为基础,设计了机载导航数据库格式化软件,实现标准导航数据格式到机载导航数据库格式的转换,生成适用于飞行管理系统的机载导航数据库文件系统。在分析机载导航数据库格式化的需求上,采用一种改进的管道-过滤器模式,通过裁剪和筛选导航数据的方法,降低数据容量。利用Access数据库作为中间数据库,建立不同类别的数据表,实现数据的快速查询和对比。通过实际的验证和应用表明机载导航数据库格式化软件是可行的,生成的机载导航数据库文件系统符合飞行管理系统要求,格式化后的数据是正确的。     

压气机静子叶片转角主备控制器转换装置改进

为了确保某型航空发动机高压压气机可调静子叶片转角控制系统主备控制器转换的可靠性,对系统原有的控制器转换装置进行了改进,加入了新的转换机构.仿真计算结果表明,若数字电子控制器故障后,未按照预定要求输出0脉冲占空比,而输出了固定的非0脉冲占空比信号或随机的不可预测的脉冲占空比信号,原系统的正常工作将受到较严重的影响;而采用...     

Reliability Predictions and System Support Costs

A case study demonstrates that spares requirements based on operational reliability predictions result in the system being undersupported during its burn-in and useful-life phases by average factors of 42.2 and 4.22, respectively. However, systems spares requirements based on logistics estimates result in the system being oversupported during its burn-in phase by an average factor of 4.26 with this factor probably increasing as the system enters the useful-life phase of its life cycle. Adequate system support within predetermined cost estimates will be achieved only when reliability predictions are accurate and when systems spares requirements are computed separately for the equipment burn-in phase and useful-lfe phase.     

Large eddy simulation of turbulent combustion processes in propulsion and power systems

Progress toward application of the large eddy simulation (LES) technique to turbulent multiphase combustion processes is presented with emphasis placed on propulsion and power systems. The primary objective is to provide a systematic analysis of the current state-of-the-art and assist in the development of technical performance metrics for model development and validation. Research is currently required to provide both improved multiphase combustion models and improved datasets for validation. Requirements for further model development must be established through detailed analyses of the space–time characteristics of small-scale flame structures and turbulence–chemistry interactions. Concurrently, a refined set of implementation requirements must be established. Steps taken towards these goals are described by first providing a generalized formulation of the filtered conservation equations using an arbitrary filter function that operates on both spatial and temporal scales, with no a priori assumptions made regarding the character of the multiphase fluid elements present in the system. The distinct requirements for LES are listed with a discussion that highlights current progress and unresolved issues. Two case studies are then presented that demonstrate the predictive capabilities of LES when implemented with the appropriate numerics and grid resolution, under highly controlled conditions, and with well-defined boundary conditions. The paper is concluded by highlighting recent findings associated with the International Workshop on Measurement and Computation of Turbulent Nonpremixed Flames.     

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     

Modular Stores Management System

Advanced Military aircraft operational requirements demand an ever increasing variety and quantity of Stores, coupled with continuous improvement in mission success, safety of operation, aircrew and groundcrew workload, interoperability and ground support facilities. Until now these ever more demanding requirements have been met by costly customized stores management system designs. GEC Avionics has surveyed the potential SMS requirements of a comprehensive range of aircraft and weapon types, in order to define a universal SMS design concept based on system availability, integrity and reliability, operational functions, peripheral interfaces and maintenance/human factors. This advanced concept not only includes provision for all existing weapon types but also has growth potential for the evolving MIL-STD-1760 weapon interfaces. System interface requirements have been rationalized in order to achieve a Modular Stores Management System (MSMS) design based on major factors such as cost, mission requirements and customer specifications. The key work for a successful MSMS design is flexibility and GEC Avionics has evolved a set of standard modules which can be packaged to satisfy specific customer needs. Typically, the standard modules provide over 80% of the hardware in every Stores Management application. The MSM concept features much reduced development costs and timescales, commonality between aircraft types minimizing parts inventory, VLSI technology providing high reliability and a common product support and maintenance philosophy. The MSM design offers a highly cost effective low risk concept for meeting the needs of modernization and new aircraft programs.     

一种近似解耦方法在飞控系统中的应用

应用输出及部分状态反馈、极点配置和奇异摄动法对某高性能飞机的多变量飞行控制系统进行了设计。基于Ｐｏｒｔｅｒ的研究,对其不足之处做了改进。设计中考虑了１／ｇ因子的项,并推导了相应的数学表达式。借助这些表达式可调整控制器的参数值以求减少系统中的耦合以及配置闭环系统的零、极点使其满足设计要求。基本实现了快速和解耦控制。     

A Digital Map Set for the Night Attack Aircraft

There has been much interest recently in applying cartographic digital data bases to advanced avionics systems as a solution to specific problems associated with night attack aircraft missions. The tremendous computer horsepower required to accomplish this task in real-time in an airborne environment is well documented. Hardware implementation of complex algorithms traditionally has produced custom devices which accomplish a specific function on a specific data structure. Historically, this has resulted in powerful but inflexible systems incapable of adapting to the changing requirements of military missions. In an age of evolving technology, these pitfalls must be avoided by incorporating expected changes into the design of digital map systems. If they are made to accommodate a variety of cartographic data bases and allow for programmable manipulation of those bases, this new class of digital map sets can be reconfigured at the software level to meet the changing requirements of aircraft missions. This paper addresses current design concepts for such a map system on a Night Attack aircraft. The focus is on issues concerning the development and handling of existing map data products to meet current system requirements. This system, called the Digital Map Set (DMS), is being designed to accomplish the classical manipulations of Defense Mapping Agency Digital Land Mass System data. Additionally, aeronautical charts, aerial reconnaissance photos, flight plan data, and other two-dimensional bit mapped graphics also are accommodated. Mission requirements relating to the cartographic data bases shall be discussed along with ground support station and airborne system design issues.     

商用涡扇发动机推力控制故障处置功能解析

针对运输类飞机对动力装置必须确认任何单一失效或故障及可能的失效组合都不会危及飞机安全飞行的适航要求,经工程研究和飞机运营经验证明,原有的通过安全性分析以及申请豁免来表明设计符合性的验证方法存在不足,为了保障飞机飞行的安全性,可增加推力控制故障处置(TCMA)系统。以B787飞机配装的GEnx发动机TCMA系统为研究对象,采用系统工程的方法研究和分析了该系统的安全性需求来源、符合性验证方法及其演进、TCM事件危害、TCMA系统架构和系统功能,其中包括事件侦测、处置逻辑、激活功能监控与内部自检BIT等功能。分析结果表明:TCMA系统是1个集成的智能控制系统,在TCM事件发生后无需飞机机组人员干预,能够自动处置并保障飞机的飞行安全。     

民用飞机内话系统接插件选型

飞机设计是复杂而庞大的系统工程,通常根据不同的系统,分包给不同的供应商,但供应商一般只提供子系统的初步架构及主要设备清单,主机方需要考虑各子系统的集成及供应商未提供的设备选型。内话系统本身依托于音频管理系统实现主要功能,主机方需要完成内话系统的集成工作,设备级工作就包括内话接插件的选型。内话接插件即内话插孔,选择时需要考虑各类插孔的适用机型、插孔的机械要求、温度要求和环境要求等,还需要考虑插孔的接线规则,使其能和终端话筒耳机相匹配。     

100N推力级微小型涡喷发动机数字式电子控制器研究

建立了100N推力级微小型涡喷发动机模型,应用鲁棒控制算法进行了控制器软、硬件系统开发设计;提出了全新的仿真方法,用该方法对控制器进行了仿真,取得了良好的效果。电子控制器不仅具备等转速调节功能,且有足够的逻辑、多种控制监测和保护功能,完全符合多功能FADEC控制的要求。