弹性飞机跨声速机动载荷计算方法

doi:10.7527/S1000-6893.2016.0070

流体力学与飞行力学

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弹性飞机跨声速机动载荷计算方法

张辉, 李杰

西北工业大学航空学院, 西安 710072

收稿日期:2015-12-28 修回日期:2016-03-08 出版日期:2016-11-15 发布日期:2016-03-17
通讯作者: 李杰,男,博士,教授,博士生导师。主要研究方向:理论与计算流体力学,设计空气动力学。Tel.:13679258367,E-mail:lijieruihao@163.com E-mail:lijieruihao@163.com
作者简介:张辉,男,博士研究生。主要研究方向:理论与计算流体力学,气动弹性力学。Tel.:13991164363,E-mail:zhanghui_0104@126.com;李杰,男,博士,教授,博士生导师。主要研究方向:理论与计算流体力学,设计空气动力学。Tel.:13679258367,E-mail:lijieruihao@163.com
基金资助:
国家自然科学基金（11172240）；航空科学基金（2014ZA53002）；国家“973”计划（2015CB755800）

Maneuver load analysis for flexible aircraft in transonic flow

ZHANG Hui, LI Jie

School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China

Received:2015-12-28 Revised:2016-03-08 Online:2016-11-15 Published:2016-03-17
Supported by:
National Natural Science Foundation of China (11172240); Aeronautical Science Foundation of China (2014ZA53002); National Basic Research Program of China (2015CB755800)

摘要/Abstract

摘要：

基于跨声速非定常气动力求解的重叠场源法，开展了弹性飞机跨声速机动载荷计算方法研究，为现代飞机结构强度设计提供更加可靠和精确的临界载荷计算方法。首先通过采用重叠场源法求解关于62%根弦俯仰振荡的LANN机翼在马赫数为0.822的非定常气动力并与实验结果进行对比，验证了重叠场源法对跨声速激波效应预测和非定常气动力计算的能力；其次应用频域气动力有理近似技术拟合场源法计算得到的广义气动力系数矩阵，建立了机动载荷分析的状态空间模型；然后完成了某型民用飞机俯仰机动载荷分析，研究了俯仰机动飞行情况下飞机机体状态量及飞机部件载荷响应规律。计算结果表明：考虑机体弹性变形后，机翼和平尾气动载荷响应最大值分别减小了5.1%和10.6%，升降舵气动载荷响应最大值增大了16.2%，在飞机结构强度设计中必须考虑机体弹性效应对飞机部件载荷的影响。

关键词: 机动载荷, 非定常气动力, 气动力影响系数矩阵, 跨声速, 重叠场源法

Abstract:

Based on the overset field-panel method for computing unsteady aerodynamics in transonic flows, the calculation approach of maneuver load for flexible aircraft in transonic flows is developed, for the purpose of providing expedient and accurate critical loads for the design in structural strength of modern aircraft. The LANN wing in pitch mode about 62% root chord at Mach number 0.822 is solved to validate the unsteady pressure coefficient with the experimental data, and excellent agreement shows the capability of the overset field-panel method in predicting the shock location and strength. State space model for analyzing maneuver loads is generated through rational aerodynamic approximations, then the transient load analysis of a transport aircraft in pitching is conducted to investigate the response of the airframe states and loads acting on the components of the aircraft. The results indicate that the peak loads acting on the wing and horizontal tail decrease by 5.1% and 10.6% respectively, while one on the elevator increases by 16.2%, due to the structural deformation. Therefore, the effect of structural deformation on loads must be considered in the design concerning structural strength of modern aircraft.

Key words: maneuver load, unsteady aerodynamics, aerodynamic influence coefficient matrix, transonic, oveset field-panel method

中图分类号:

V211.47

张辉, 李杰. 弹性飞机跨声速机动载荷计算方法[J]. 航空学报, 2016, 37(11): 3236-3248.

ZHANG Hui, LI Jie. Maneuver load analysis for flexible aircraft in transonic flow[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(11): 3236-3248.

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E-mail：hkxb@buaa.edu.cn

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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

弹性飞机跨声速机动载荷计算方法

Maneuver load analysis for flexible aircraft in transonic flow

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