FMS巡航阶段的垂直轨迹预测算法及应用

飞机的飞行过程涉及多个垂直飞行阶段,巡航阶段占了绝大部分的飞行时间、飞行距离及燃油消耗,研究飞行管理系统（FMS）巡航阶段的垂直轨迹预测算法,对于提升飞行的经济性、舒适性、安全性是非常重要和必要的。为了满足不同类型飞机之间巡航阶段垂直轨迹预测算法的通用性,提高垂直轨迹预测的精确度和可信度,提出一种适用于巡航阶段的垂直轨迹预测算法。首先,通过计算巡航阶段的速度剖面,构建预测过程中更加符合实际的大气模型;然后基于第一性原理（第一法则）的飞机模型计算所需的巡航燃油流量数据,通过设计的巡航阶段垂直轨迹预测算法逻辑,给出巡航阶段预测的垂直轨迹;最后通过地面仿真试验和空中试飞验证算法的有效性与准确性。结果表明：本文提出的基于第一性原理飞机模型的FMS 巡航阶段垂直轨迹预测算法能够预测飞机的巡航轨迹,且预测精度误差低于1%。     

民用飞机飞行管理仿真系统设计与实现

主要讨论关于广义飞行管理系统的仿真实现,对水平和垂直剖面优化算法及其飞行控制算法方面进行了相关研究,并且在Visual C++平台上实现了飞行计划、导航、四维制导、控制显示单元、ARINC429总线通信、主飞行显示和航图显示等功能。仿真结果表明,此仿真系统的设计是成功的,开展飞行管理系统的仿真研究在整个飞机的研制中具有十分重要的意义。     

航空数据库适航审定政策研究

航空数据库（Aeronautical Database）作为实现航空器导航、避障和指引功能的重要部分，其数据结 构遵循特定格式的标准。航空数据库的质量将直接影响到航空器的运行安全。当前民航适航体系针对原始数据 及后续处理过程的质量体系的审定缺乏实际经验，给机载设备和飞机运行的适航性带了挑战。本文首先介绍当 前世界范围内航空数据库适航管理的办法及技术标准，再结合当前国内航空数据库的审定的现状，提出一种可 行的中国航空数据库适航审定的政策建议，供国内各类航空数据库的研制单位及审查方参考。     

Flight dynamics characteristics of canard rotor/wing aircraft in helicopter flight mode

The aerodynamic layout of the Canard Rotor/Wing(CRW) aircraft in helicopter flight mode differs significantly from that of conventional helicopters. In order to study the flight dynamics characteristics of CRW aircraft in helicopter mode, first, the aerodynamic model of the main rotor system is established based on the blade element theory and wind tunnel test results. The aerodynamic forces and moments of the canard wing, horizontal tail, vertical tail and fuselage are obtained via theoretical analysis and empirical formula. The flight dynamics model of the CRW aircraft in helicopter mode is developed and validated by flight test data. Next, a method of model trimming using an optimization algorithm is proposed. The flight dynamics characteristics of the CRW are investigated by the method of linearized small perturbations via Simulink. The trim results are consistent with the conventional helicopter characteristics, and the results show that with increasing forward flight speed, the canard wing and horizontal tail can provide considerable lift,which reflects the unique characteristics of the CRW aircraft. Finally, mode analysis is implemented for the linearized CRW in helicopter mode. The results demonstrate that the stability of majority modes increases with increasing flight speed. However, one mode that diverges monotonously,and the reason is that the CRW helicopter mode has a large vertical tail compared to the conventional helicopter. The results of the dynamic analysis provide optimization guidance and reference for the overall design of the CRW aircraft in helicopter mode, and the model developed can be used for control system design.     

New reference trajectory optimization algorithm for a flight management system inspired in beam search

With the objective of reducing the flight cost and the amount of polluting emissions released in the atmosphere, a new optimization algorithm considering the climb, cruise and descent phases is presented for the reference vertical flight trajectory. The selection of the reference vertical navigation speeds and altitudes was solved as a discrete combinatory problem by means of a graphtree passing through nodes using the beam search optimization technique. To achieve a compromise between the execution time and the algorithm's ability to find the global optimal solution, a heuristic methodology introducing a parameter called ‘‘optimism coefficient was used in order to estimate the trajectory's flight cost at every node. The optimal trajectory cost obtained with the developed algorithm was compared with the cost of the optimal trajectory provided by a commercial flight management system(FMS). The global optimal solution was validated against an exhaustive search algorithm(ESA), other than the proposed algorithm. The developed algorithm takes into account weather effects, step climbs during cruise and air traffic management constraints such as constant altitude segments, constant cruise Mach, and a pre-defined reference lateral navigation route. The aircraft fuel burn was computed using a numerical performance model which was created and validated using flight test experimental data.     

惯性导航系统仿真试验研究

惯性导航系统是通过测量加速度自动推算飞机速度和位置数据的自主式导航设备,其作用是保证飞机按预定的航线飞行,准确地抵达目的地。在航空电子设备试验中,采用惯导仿真器可以减少测试的复杂性,而且还能获得更好的动态效果。本文介绍了惯导系统功能控制逻辑和显示画面的验证方法,同时还介绍了仿真器的软件编制技术。     

GPS/INS integration on the Standoff Land Attack Missile (SLAM)

The Standoff Land Attack Missile (SLAM) is a worldwide, all-weather, precision-strike weapon system deployed from carrier-based aircraft. In the primary mode of operation, target location and other mission data are generated from intelligence sources available on the aircraft carrier and loaded into the missile prior to aircraft takeoff. After missile launch, the SLAM inertial navigation system (INS) guides the missile along the planned trajectory. Updating the missile INS from the Global Positioning System (GPS) during flight provides precise midcourse navigation and enhances target acquisition by accurate, on-target pointing of the SLAM Maverick seeker. The GPS/INS avionics and software integration used for SLAM are described in detail, along with some of the design tradeoffs that led to the approach. The avionics configuration integrates the Harpoon midcourse guidance unit, which includes a strapdown inertial sensor package and digital processor, with a Rockwell-Collins single-channel, sequential GPS receiver processor unit (RPU), a derivative of the GPS phase-III user equipment. In addition to the GPS receiver elements the RPU contains the navigation processor, which executes the SLAM navigation, Kalman filter algorithms, and other guidance algorithms including seeker pointing. Flight-test results of the SLAM GPS-aided INS are also included     

基于Stateflow的自动飞行模式转换逻辑研究

现代民用飞机的自动飞行模式有很多种,且各模式间相互关联和影响,容易造成模式转换的混乱。为解决模式转换的混乱问题,对自动飞行模式转换逻辑进行了研究,分别梳理了飞行指引、自动驾驶仪以及横向和纵向模式转换关系。利用Stateflow搭建了自动飞行各功能的模式转换模型,同时利用Matlab的GUI搭建仿真的飞行控制板和自动飞行模式显示界面,模拟仿真飞机的自动飞行模式转换功能。最后通过预期的模式转换矩阵的方式验证平台中模式转换的正确性。     

基于WPF技术的试飞数据实时监控系统设计研究

立足于当前大型民用飞机试飞模式,集合数据处理及实时监控特点,在Visual Studio环境下,利用WPF软件编程技术,构建了基于数据层、业务逻辑层、表示层的试飞数据实时监控系统。系统利用多种显式控件,充分模拟了试飞数据监控状态,通过WPF数据驱动模型及合理的线程资源调配,实现了对不同类型数据的实时监控、分析、存储和回放,为后续民机试飞测试技术的创新提供了参考依据。     

Navigation system of pilotless aircraft via GPS

The pilotless aircraft has wide applications in measuring earth, surveying mineral sources, fireproofing in the forest, observing floods and so on. In this paper, after briefly introducing positioning and navigation technologies for pilotless aircraft-a new kind of navigation system for pilotless aircraft using GPS (Global Positioning System) is presented. An overall plan of the navigation system is discussed, and its technology cruxes are analysed. Its hardware and software are designed and implemented, and experimental results are given. The navigation system not only has autonomous navigation capability, but can also achieve navigation aided by telecontrol system. It can supervise flying by telemetering system and displaying predetermined air line and flight path maps on the computer monitor. It can run in simple GPS receiver mode or in the differential GPS mode by means of available telecontrol channel. These are, no doubt, of great value for the navigation of pilotless aircraft     

基于模型检查的民用飞机飞控系统安全性评估

在以大型民机为代表的安全关键系统研制中,系统复杂度的提升极大地降低了依赖设计人员经验的传统安全性评估手段的效率与有效性,并带来了反复迭代困难等问题,基于模型的安全性评估方法(MBSA)能够显著降低研制过程的分析复杂度,提高安全性评估的工作效率。民机系统安全性评估指南ARP 4761A中也增加了MBSA相关的安全性评估工作。阐述了利用有限状态机与时态逻辑构建形式化安全性模型,开展安全性评估的基本原理,详细的分析过程及定义安全属性的方法,并以某民用飞机为对象,建立飞控系统副翼控制功能的SMV形式化模型,定义了副翼控制功能的形式化安全性需求,给出了基于形式模型的安全性属性验证评估案例,证明了基于形式化方法的安全性评估在民机系统安全性工作中的可行性。     

基于CEL的某型飞机撞水数值仿真

飞机水上迫降已成为适航取证不可缺少的一部分.飞机撞水过程属于复杂的流固耦合模型,从发生在2014年震惊全球的马航MH370航班失事重大事故的背景出发,依据流固耦合理论为基础,对失事客机波音B777-20ER进行非计划的水上迫降冲击动力学分析研究.利用有限元仿真软件ABAQUS采用耦合欧拉-拉格朗日算法(CEL)模拟失事飞机在无计划情况下撞水过程.根据马航MH370官方发布的事故搜救信息和安全调查讨论,建立合理的飞机撞水有限元模型,对不同工况下进行数值模拟,着重讨论飞机偏转角和飞机翼尖压强变化趋势,验证采用CEL法研究飞机水上迫降性能的可行性,也为研究水上迫降和航空失事飞机搜救调查提供参数指导和技术参考.     

基于多元极值Copula的尾流飞行风险概率评估

在尾流问题日益突出的背景之下,结合人-机-环复杂系统建模与多元极值理论,评估遭遇近距近地尾流情形下的飞行风险概率。基于蒙特卡罗法提取尾流极值参数,验证了一维极值参数符合广义极值（GEV）分布;在此基础上提出了二维极值参数的双参数变权重（DPAVW） Copula模型,利用自适应区间粒子群优化（ARPSO）算法对目标函数中的未知参数进行了辨识,拟合优度检验的结果表明DPAVW Copula模型具有比其他Copula模型更高的精度;在利用Copula模型对尾流三维空间中所有二维极值参数进行描述的基础上,求出了每个网格节点上对应的飞行风险概率值,构建了尾流场内二维及三维可视化风险概率图。所提方法是对飞机系统安全性评估理论与方法的有效补充,对于尾流场内的导航控制与风险规避、机场起降的尾流安全间隔改进、环境风险可视化等研究方向有一定的参考价值;同时也适用于不同状况下飞行风险概率的横向对比分析。     

鸭式旋翼/机翼飞机悬停状态飞行动力学特性

针对鸭式旋翼/机翼(Canard Rotor/Wing,CRW)飞机独特的气动布局,常规的分析方法及经验公式很难准确地对CRW飞机进行飞行动力学研究,通过飞行辨识对CRW飞机悬停状态特性进行了研究。首先,设计了飞行试验并获得了高质量的飞行数据,基于频率响应对CRW飞机的状态空间模型进行了简化。然后,在频域内对飞机的动力学参数进行了拟合优化,获得了CRW飞机悬停状态的动力学模型,并用飞行数据对所建模型进行了验证。最后,用辨识所得参数与常规直升机悬停状态时的参数进行了对比。结果显示悬停时CRW飞机的操纵导数和阻尼导数均比常规直升机小,经分析,操纵导数的减小主要是CRW飞机独特的旋翼设计所致,阻尼导数减小的原因主要是旋翼气动影响以及鸭翼、平尾、垂尾的结构影响。动力学特性分析结果为CRW飞机旋翼模式总体设计的进一步优化提供了指引和参考,所建立的模型可用于控制系统设计。     

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。     

Aiding vertical guidance understanding

A study was conducted to evaluate training and displays for the vertical guidance system of a modern glass cockpit airliner. The experiment consisted of a complete flight performed in a fixed-base simulator with airline pilots. Three groups were used to evaluate a new flight mode annunciator display and vertical navigation training. Results showed improved pilot performance with training and significant improvements with the training and the Guidance-Flight Mode Annunciator. Using actual behavior of the avionics to design pilot training and FMA is feasible and yields better pilot performance.     

XDF-196电子飞行仪表系统

电子飞行仪表系统是K8飞机的主导航设备,它将来自机载传感器的各种信息综合处理,进行导航计算,并产生各种导航方式下的显示画面和字符,在多功能显示器上进行显示,完成导航训练所有飞行科目。     

飞行管理系统导航功能分析

本文研究了飞行管理系统(FMS)导航功能的要求,分析了导航滤波方法、结构和导航方式及FMS自动导航管理等问题。     

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.     

基于多轨迹预测的飞机近地防撞技术研究

针对飞机近地飞行安全问题,提出了一种基于多轨迹预测的飞机近地防撞技术实现方法。建立了飞机近地防撞功能触发的架构逻辑和评价标准,设计了一套六自由度多轨迹实时预测的轨迹预估算法和防撞控制算法,将近地防撞模型与飞机模型结合起来,在数字仿真环境中验证整套算法的合理性。结果表明,基于多轨迹预测的飞机近地防撞算法实时性好,飞行轨迹预测准确性高,逻辑架构鲁棒性强,易于成果转化,具有很高的工程应用价值。