基于复杂动力学仿真的结冰情形下飞行安全窗构建方法

doi:10.7527/S1000-6893.2016.0274

飞机结冰致灾与防护专栏

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基于复杂动力学仿真的结冰情形下飞行安全窗构建方法

裴彬彬¹, 徐浩军¹, 薛源¹, 李哲¹, 刘东亮²

1. 空军工程大学航空航天工程学院, 西安 710038;
2. 北京航空工程技术研究中心, 北京 100076

收稿日期:2016-08-23 修回日期:2016-10-25 出版日期:2017-02-15 发布日期:2016-11-03
通讯作者: 薛源,E-mail:szxy1986@163.com E-mail:szxy1986@163.com
基金资助:
国家“973”计划（2015CB755800）；国家自然科学基金（61374145，U1333131）

Development of flight safety window in icing conditions based on complex dynamics simulation

PEI Binbin¹, XU Haojun¹, XUE Yuan¹, LI Zhe¹, LIU Dongliang²

1. Aeronautics and Astronautics Engineering College, Air Force Engineering University, Xi'an 710038, China;
2. Beijing Aeronautical Engineering Technology Research Center, Beijing 100076, China

Received:2016-08-23 Revised:2016-10-25 Online:2017-02-15 Published:2016-11-03
Supported by:
National Basic Research Program of China (2015CB755800); National Natural Science Foundation of China (61374145, U1333131)

摘要/Abstract

摘要：

目前针对结冰情形下增强驾驶员情景感知的研究比较有限，现有的手段一般为通过评估部分飞行安全关键参数是否超出其极限值来对风险事件是否发生进行预测。建立了驾驶员操纵-飞机本体-积冰影响的动力学模型，通过对单个飞行情形预测时间段内飞行参数风险度的叠加得到该情形下的飞行安全谱，并在此基础上得到该情形下的风险值。基于建立的并行飞行仿真平台，获取飞机在整个操纵范围内的风险拓扑图，即安全窗。分析了飞机在对称结冰情形和非对称结冰情形下飞行安全窗的变化，并对结冰的致灾机理进行了分析。仿真结果表明结冰导致安全飞行范围缩减，对于非对称结冰还会出现安全窗不对称的现象。安全谱的提出可以为事故的演化分析提供一种全面直观的分析方法，安全窗的构建可为飞机遭遇各种不利情形下的驾驶员操纵提供指示，也可为飞机设计人员优化飞机性能提供一定的参考。

关键词: 飞机结冰, 情景感知, 计算飞行动力学, 非对称结冰, 并行飞行仿真, 安全窗

Abstract:

Studies on enhancing situational awareness of pilots in icing conditions are relatively rare. Current methods normally predict occurrence of accidents by estimating whether the safety related parameters exceed their limitations. Complex dynamics of the pilot-vehicle-icing effect model is established. Safety spectrum of a single flight condition is obtained by comparing the risk degree of the flight data through the predict time interval, and the colored risk value for the flight condition is further acquired. Safety window for flight safety in the whole manipulation can be calculated using parallel flight simulation platform. The safety windows of symmetric and asymmetric icing conditions are researched, and the disaster-causing mechanism is analyzed. Simulation results show that ice will lead to shrink of the safety flight scope, and the asymmetrical ice will lead to the uneven safety window. The proposed method can provide theoretical support for enhancement of situational awareness in different adverse events, and engineering tool for optimizing the aircraft performance for aircraft designers.

Key words: aircraft icing, situational awareness, computational flight dynamics, asymmetric icing, parallel flight simulation, safety window

中图分类号:

V212

裴彬彬, 徐浩军, 薛源, 李哲, 刘东亮. 基于复杂动力学仿真的结冰情形下飞行安全窗构建方法[J]. 航空学报, 2017, 38(2): 520695-520708.

PEI Binbin, XU Haojun, XUE Yuan, LI Zhe, LIU Dongliang. Development of flight safety window in icing conditions based on complex dynamics simulation[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(2): 520695-520708.

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

基于复杂动力学仿真的结冰情形下飞行安全窗构建方法

Development of flight safety window in icing conditions based on complex dynamics simulation

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