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机翼前缘结冰对大飞机纵向模态特性的影响
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作者:
作者单位:

1.空军工程大学航空工程学院，西安 710038;2.航空工业第一飞机设计研究院，西安 710089

通讯作者:

裴彬彬，男，讲师， E-mail：1940bin@163.com。

中图分类号:

V 212

基金项目:

国家自然科学基金（62103440）。


Influence of Wing Leading Edge Icing on Longitudinal Modal Characteristics of Large Aircraft
Author:
Affiliation:

1.Aeronautics Engineering College, Air Force Engineering University, Xi’an 710038, China;2.AVIC The First Aircraft Institute, Xi’an 710089, China

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    摘要:

    结冰导致飞机气动特性恶化，进而影响飞行品质。针对机翼前缘结冰条件下飞机全包线范围飞行品质评估问题，提出了基于自适应拟配初值的等效系统拟配方法，构建了机翼前缘结冰构型，并通过数值模拟得到背景飞机机翼前缘结冰气动数据。建立了飞机系统模型，进行升降舵倍脉冲操纵，进而得到飞机的响应数据。分析数据特征计算了自适应拟配初值，在飞机全包线范围内干净构型及不同结冰严重程度条件下进行了等效系统拟配，获得了纵向短周期飞行模态特性参数，进而得出相应的飞行品质等级。仿真结果表明：结冰会对飞机模态特性造成影响，使得飞行品质降低，严重时可能导致飞行品质发生降级。

    Abstract:

    Icing leads to the deterioration of aircraft aerodynamic characteristics， which affects the flight quality. Aiming at the problem of aircraft flight quality evaluation in the full envelope range under the condition of wing leading edge icing， an equivalent system fitting method based on adaptive fitting initial value is proposed. The icing configuration of the wing leading edge is constructed， and the aerodynamic data of the background aircraft are obtained through numerical simulation. The aircraft system model is established and the elevator pulse doubling operation is conducted to obtain the response data of the aircraft. The data characteristics are analyzed to calculate the initial value of adaptive fitting. The equivalent system fitting is carried out under the conditions of clean configuration and different icing severity within the full envelope of the aircraft. The modal characteristic parameters of longitudinal short period flight are obtained， and the corresponding flight quality level is obtained. The simulation results show that icing will affect the modal characteristics and reduce the flight quality of the aircraft， and may lead to the degradation of flight quality in serious cases.

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伍强,孔满昭,徐浩军,裴彬彬,周景锋.机翼前缘结冰对大飞机纵向模态特性的影响[J].南京航空航天大学学报,2023,55(2):241-248

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  • 收稿日期:2022-04-26
  • 最后修改日期:2022-06-20
  • 在线发布日期: 2023-04-05
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