MODEL OF FLIGHT TECHNICAL ERROR IN SYMMETRICAL PLANE FOR PERFORMANCE BASED NAVIGATION  

性能基导航中对称面内飞行技术误差模型(英文)

作　　者：赵鸿盛[1] 徐肖豪[2] 张军[1] 朱衍波[1] 杨传森[3] 

机构地区：[1]北京航空航天大学电子信息工程学院 [2]中国民航大学空中交通管理学院 [3]南京航空航天大学民航学院

出　　处：《Transactions of Nanjing University of Aeronautics and Astronautics》2011年第3期246-254,共9页南京航空航天大学学报（英文版）

基　　金：Supported by the National Basic Research Program of China("973"Program)(2010CB731805);theFoundation for Innovative Research Groups of the National Natural Science Foundation of China(60921001);the National Key Technologies R&D Program of China(2011BAH24B02);the Basic Scientific Research Fundation of Central Institutions of Higher Education(ZXH2009D006)~~

摘　　要：In the performance based navigation（PBN）,the flight technical error（FTE）and the navigation system error（NSE）are two main parts of total system error（TSE）.The implementation of PBN requires pre-flight prediction and en-route short-term dynamical prediction of TSE.Once the sum of predicted FTE and NSE is greater than the specified PBN value,PBN cannot operate.Thus,it requires accurate modeling and thorough analysis of the two main contributors.Multiple-input multiple-output（MIMO）longitudinal flight control system of ARIC model is designed using the linear quadratic Gaussian and loop transfer recovery（LQG/LTR）method,and FTE in symmetrical plane of aircraft is analyzed during the turbulence disturbed approach.The error estimation mapping function of FTE in symmetrical plane and its bound estimation model are proposed based on the singular value theory.The model provides an approach based on the forming mechanism of FTE,rather than the costly flight test and the data fitting.Real-data based simulation validates the theoretical analysis of FTE in symmetrical plane.It also shows that FTE is partially caused by the turbulence fluctuation disturbance when the automatic flight control system（AFCS）is engaged and increases with escalating the environmental turbulence intensity.飞行技术误差(FTE)与导航系统误差(NSE)是性能基导航(PBN)中总系统误差(TSE)的主要组成部分。性能基导航的实施需要对总系统误差进行航前预测以及航行中的短期动态预测。当飞行技术误差预测值与导航系统误差预测值的和大于PBN导航的规定值时,将无法运行PBN导航。因此,对于总系统误差的两个主要误差分量需要精确建模和透彻分析。采用LQG/LTR方法针对ARIC模型设计了多输入多输出纵向飞行控制系统,分析了在湍流扰动下进近飞行器对称面内的飞行技术误差。基于奇异值理论提出了对称面内飞行技术误差的映射函数以及边界估计模型。模型是基于对对称面内飞行技术误差成型机理的分析提出的,提供了一种基于成型机理的分析和估计方法,从而避免了昂贵试飞和单纯的数据拟合。基于真实数据的仿真验证了对称面内飞行技术误差的理论分析。研究同时揭示了当自动飞行控制系统(AFCS)接通时性能基导航中对称面内飞行技术误差部分由湍流扰动引致,且随湍流强度的增强而增大。

关 键 词：flight technical error performance based navigation LQG/LTR air traffic management Kalman filter 

分 类 号：V355[航空宇航科学与技术—人机与环境工程]