波音777飞机高升力控制系统余度管理分析

飞行控制系统普遍采用余度技术来提高自身的任务可靠性。余度部件效能的发挥程度主要取决于余度管理策略和方法。根据波音777飞机高升力控制系统的基本构架,通过在线监控与信号表决相结合的方法对系统余度管理方法进行研究。在余度管理方法的设计过程中,充分考虑了布线技术、硬件设计技术及与软件相结合的方法,不但简化了襟缝翼控制器的硬件设计,同时也简化了控制器软件的设计难度,提高了系统可靠性,所用到的方法对同类系统设计有一定的参考价值。     

新概念机翼尾流特性实验

大型飞机常采用开启襟翼以增大机翼升力系数,实现较大迎角的起飞和降落,而机翼在大迎角状态下,翼尖会产生能量集中且自由消散时间长的飞机尾涡,严重影响后续起降飞机的安全。基于Rayleigh-Ludwieg不稳定性,提出一种新概念飞机襟翼布局,通过水槽实验发现:新概念布局的襟翼对翼尖涡的消散具有明显的促进作用,不同参数组合下襟翼涡对翼尖涡的运动特性和能量变化的影响均有不同。实验结果也为飞机尾流控制的研究提供了参考,在满足飞行力学设计的基础上,合理运用增升装置构建四涡系统可以有效促进飞机尾流的消散,提高机场飞机起降效率。     

基于低冗余度的传感器故障诊断研究

对于大型飞机来说,飞行控制系统各部件(包括传感器)多采用高余度的硬件配置来提高系统的任务可靠性,但对小型飞机来说,由于受重量、空间及费用等原因的影响,一些传感器不适合安装三余度或四余度传感器。对于二余度或单传感器来说,如何鉴别故障传感器或判断传感器是否发生故障较为困难。同样,传统的故障诊断与隔离方法并不能隔离三余度传感器系统中的多个故障。为了解决低冗余度传感器故障诊断问题,提出一种不依赖数学模型的奇偶方程方法与小波分析相结合的传感器故障诊断方法。     

Architecture Considerations for Digital Automatic Flight Control Systems

Functional partitioning, redundancy structure, internal communications, and software modularization define the architecture of a digital automatic flight control system (DAFCS). Selection of a suitable system architecture for commercial transports involves such factors as the functional scope, growth provision and flexibility requirements, sensor interfaces, the aircraft's actuator and control surface redundancy, and the dispatch reliability requirements. Trade-offs concerning these various factors are discussed, and it is shown that a very versatile and almost universal DAFCS can be configured to meet the general and peculiar needs associated with each aircraft application. Specific results associated with this system's recent demonstration flights in the DC-10 aircraft, as well as examples from several other transport aircraft applications of the same DAFCS architecture, are used to illustrate the design concepts.     

机载供电系统双余度控制器的容错控制

介绍双发（Twin-engines）系统的战斗机的机载供电系统控制器的设计和实现。机载供电系统控制器是管理飞机的供电系统的航空电子设备,是飞机供电系统的核心设备,肩负飞机安全的使命。为了提高控制器的可靠性和灵活性,放弃传统的模拟方法,使用先进的数字化技术实现对飞机供电、配电系统的管理。在设计中为了提高可靠性,使用主动复制的容错技术,设计了双余度控制器,在发生单通道错误的情况下,整个系统能够正确工作。对机载供电系统控制器容错技术进行了研究,包括双余度系统的管理策略、同步控制机制、余度管理和故障综合、信号比较监控和通道切换逻辑。     

Future architecture of flight control systems

The development of fault tolerant embedded control systems such as flight control systems (FCS) are currently highly specialized and time-consuming. We introduce a conceptual architecture for the next decade control system where all control and logic are distributed to a number of computer nodes locally linked to actuators and connected via a communication network. In this way, we substantially reduce the life-cycle cost of embedded systems and attain scalable fault tolerance. All fault tolerance is based on redundancy. Our philosophy is to cover permanent faults with hardware replication and handle all error processing caused by both permanent and transient faults with software techniques. With intelligent nodes and use of inherent redundancy we introduce a robust and simple fault tolerant system that utilizes minimum hardware and has bandwidth requirements of less than 300 kbits/s, which can be met with an electrical bus. The study is based on an FCS for JAS 39 Gripen, a multi-role combat aircraft that is statically unstable at subsonic speed.     

飞机滚转运动的控制余度与重构效能

论证了独立操纵的左右平尾使飞机滚动运动具有较大的控制余度,它增加了飞机正常飞行时的滚转力矩,在飞行中副翼出故障时可进行补偿重构,从而提高了滚动通道的余度等级和飞行的安全性,为减少滚转通道的余度配置提供了依据,通过针对操纵面失效和卡死两类故障的重构设计和仿真也证实了上述结论,同时,初步比较说明了自修复飞控系统在上述故障下的任务可靠性和基本可靠性均高于传统控制系统。     

DDV作动器余度数字伺服系统工程设计与实现

 介绍一种直接驱动阀（DDV）式作动器的余度数字式伺服系统设计与实现,描述了系统的余度配置、设计思想及组成,建立了DDV作动器的结构参数化模型及数字伺服回路的模型,并进行了仿真,分析了作动器动静态特性、采样频率及监控器的设计性能。最后,采用快速原型实时仿真,对余度数字式伺服系统完成了的性能试验验证,结果表明系统性能令人满意。     

飞行力学和飞行控制试飞技术

为了适应高增益,全权限数字电传操纵系统飞行试验的需要,利用已研制成功的多台地面飞行模拟器和ＢＷ－１纵向,ＩＦＳＴＡ三自由度空中飞行模拟试验机,模型自由飞研究以及具有现代先进水平的机载数据采集记录和地面实时监控系统等设备和技术手段,进行了电传飞机的飞行品质和飞控稳定性等问题的研究,包括试飞输入设计,电传飞机飞行品质,电传飞控系统稳定裕度等。最后,提出了对下一代飞机飞行力学和飞行控制方面需要研究的试飞     

大型客机先进翼尖装置综合特性研究

 翼尖装置由于其良好的气动特性在航空界得到了广泛应用,然而它也使飞机的颤振及结构重量特性发生了变化。为了探求翼尖装置的综合特性,利用数值模拟方法对大型客机上最先进的3种翼尖装置(融合式、鲨鱼鳍式和阶梯式)进行了气动、颤振及重量3个方面的综合研究。3种翼尖装置减阻效果明显,但同时结构重量亦增加。翼尖装置均降低了机翼颤振速度。研究结果表明:加装翼尖装置后机翼颤振形态取决于翼尖装置的形式。相对于机翼颤振速度,翼尖装置形式对机翼颤振速度的影响是小量(1%~7%),且翼尖装置减阻和机翼压心外移的综合重量增益,为机翼结构设计提供了一定的设计空间。     

一种支持双余度CAN总线接口的A/D采集单元设计

模拟量输入通道是无人机飞行控制系统自动检测计算机的关键部件之一.设计了某自动检测计算机内部一种基于余度CAN总线的A/D采集单元.根据总体技术指标要求,从器件选型到系统软硬件设计采用了先进性与实用性兼顾的设计思想.实际测试结果表明该接口单元工作稳定,性能良好,满足检测无人机飞行控制系统各性能指标的要求.     

MD-11 automatic flight system

The overall architecture and redundancy of the highly integrated MD-11 automatic flight system for commercial aircraft are summarized, and the application of the flight control computer capabilities to each of the system functions is detailed. The automatic flight system interface with other primary systems and subsystems is described     

数字式飞机起落架转弯控制器设计

针对某型飞机起落架转弯控制系统,本文设计了一种以DSP和双口RAM为核心的双余度数字式控制器.控制器采用硬件冗余的方法搭建双通道热备份系统,制定了余度管理策略.借助自检测和比较监控技术实现一次故障工作、两次故障安全的目标.运用马尔可夫过程建立了系统的可靠度模型,利用MATLAB求解可靠度模型的微分方程组,并对系统的可靠度进行了仿真分析.     

变体翼梢小翼的减阻机理数值模拟

总结了对翼梢小翼减阻效果影响最大的几何参数,在此基础上采用数值模拟方法研究了这些几何参数的最佳变化范围,为变体翼梢小翼设计提供理论依据.并从气动性能、气动载荷分布和翼尖涡的角度探讨了变体翼梢小翼相对传统翼梢小翼的优缺点.结果表明:在飞机的起飞阶段,变体翼梢小翼的减阻效率比传统翼梢小翼高2.2%,同时将翼尖涡强度降低了15%,有利于提高飞机的燃油效率和机场空域安全;但也会增大机翼的翼根弯矩,因此必须权衡变体翼梢小翼带来的气动收益与结构强度不利因素.     

Distributed flight control system using fiber distributed datainterface (FDDI)

The design of fault-tolerant distributed control systems is discussed. The application described is a generic flight control system (FCS) for a fighter aircraft. The system is designed for high redundancy and expandability to meet various requirements. The communication network is based on the fiber distributed data interface (FDDI), which provides a high level of electromagnetic interference resistance and reliability. The choice of fiber optic media also provides an extremely high bandwidth and tremendous growth capability for future communications needs. This study is not specific to FDDI or flight control systems. The methods and configurations presented should be applicable to many real-time control implementations     

Data communications concept for a SATS scenario

The small aircraft transportation system (SATS) concept envisions doorstop to destination transportation in a safe and timely manner. Data communications are a key component in achieving the aviation-related operational performance improvements that are sought. However, data communication doesn't start when you get into the aircraft; it starts back at the location where the flight is planned. In fact, data communications support the pilot in all phases of the flight: flight planning, pre-flight, departure, en route, transition, approach, landing, and rollout as well as for a missed approach. The Internet is being used to perform flight planning activities, and the mobile communications available today support Internet access en route to the departure airfield. On-board the aircraft, data communications provide surveillance and air traffic control (ATC) support to the pilot. The location of other aircraft is available to the pilot and ATC system through automatic dependent surveillance-broadcast (ADS-B) and traffic information service-broadcast (TIS-B) applications that transmit the location of other aircraft in the vicinity. Other aircraft locations are used to forecast potential conflicts and, thus, enhance flight safety. As the aircraft nears a SATS-equipped airfield, the pilot uses data link messages to request a landing sequence. The airport management module (AMM) provides a landing sequence assignment to the aircraft. As the pilot maneuvers the aircraft for a landing, he/she is using data-linked surveillance data to determine the location of other aircraft and maintain a safe separation distance between aircraft even in a low visibility environment.     

非相似余度飞控计算机

从容错的角度介绍了Boeing777和A320的数字飞行控制计算机系统。Boeing777和A320的飞控计算机都采用了非相似的余度技术,能容忍软件和硬件的共态故障,但在每个计算机的功能分配和整个飞控计算机系统的余度结构编排等方面体现了各自的特点。用广义随机Petri网描述了Boeing777余度结构和容错动态过程,并进行了系统的可靠性计算和容错度分析。针对中国"大型飞机"容错飞控系统的设计作了分析和建议。     

无尾飞机翼尖失速问题研究

首先分析了无尾飞机翼尖失速的特点，包括与其他布局形式共有的和自身特有的特点，重点是翼尖失速对无尾飞机飞行品质的影响。讨论了后掠角和尖削比这两个机翼外形参数对翼尖失速特性的影响。从空气动力学角度出发，根据2种不同的思路，综述了5种解决翼尖失速的方法，分析它们各自的作用原理。最后提出改善无尾飞机翼尖失速特性的若干建议。