某型飞机阵风载荷分析与载荷减缓设计
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- 英文论文题名：The Gust Load Analysis and Alleviation Design For a Certain Aircraft
- 论文作者：宗宁
- 英文论文作者：Zong Ning ; AVIC Shenyang Aircraft Design & Research Institute
- 年：2016
- 作者机构：中航工业沈阳飞机设计研究所;
- 论文关键词：飞行载荷 ; 阵风减缓 ; 主动控制 ; 风洞试验
- 英文论文关键词：flight load ; gust alleviation ; active control ; wind tunnel experiment
- 会议召开时间：2016-11-25
- 会议录名称：2016年航空科学与技术全国博士生学术论坛摘要集
- 语种：中文
- 分类号：V221
- 学会代码：XBHH
- 会议名称：2016年航空科学与技术全国博士生学术论坛
- 会议地点：中国陕西西安
- 主办单位：西北工业大学研究生院、中国高校航空学院院长联席会
- 学会名称：西北工业大学航空学院
- 页数：1
- 文件大小：564k
- 原文格式：D
- 会议级别：全国
摘要
对于大展弦比飞机,具有结构轻、翼载小、柔性大特点,阵风产生的附加过载非常严重,因此必须考虑阵风载荷减缓设计问题。本文针对某型大展弦比飞机,制定了阵风载荷减缓主动控制方案,针对刚性飞机进行了无控和有控情况的离散阵风载荷分析,即以飞机质心过载为反馈信号、前翼+升降舵+内侧副翼为控制组合舵面。在这种控制面组合情况下,结果表明将质心过载限定在2.9g是可以实现的。同时,开展了阵风载荷减缓风洞验证性试验,明确了阵风载荷减缓试验的方案设计的有效性。理论仿真分析结果与试验数据反映的趋势一致,验证了理论分析方法是有效的。
For the aircraft with large aspect ratio,the main features include light weight, low load of the wing and large flexibility. The added overload induced by the gust is very serious, so the design of the gust load alleviation is a question that should be considered. The analysis of discrete gust load for rigid aircraft under the condition with and without contral is carried out. Combined with the layout of the aircraft's control surface, the scheme design of gust load alleviation is also carried out. The scheme of gust load alleviation where the overload of centroid seems as the feedback signal is effective. The overload of centroid can be limited to 2.9g by this combination of control surface. Meanwhile, the wind tunnel experiment of gust load alleviation is carried out. Through the validating experiment of gust load alleviation, the effectiveness of the scheme design of wind tunnel experiment of gust load alleviation is validated clearly. The theoretical simulation results are consistent with the experiment data, which proves that the theoretical analysis method is effective.
For the aircraft with large aspect ratio,the main features include light weight, low load of the wing and large flexibility. The added overload induced by the gust is very serious, so the design of the gust load alleviation is a question that should be considered. The analysis of discrete gust load for rigid aircraft under the condition with and without contral is carried out. Combined with the layout of the aircraft's control surface, the scheme design of gust load alleviation is also carried out. The scheme of gust load alleviation where the overload of centroid seems as the feedback signal is effective. The overload of centroid can be limited to 2.9g by this combination of control surface. Meanwhile, the wind tunnel experiment of gust load alleviation is carried out. Through the validating experiment of gust load alleviation, the effectiveness of the scheme design of wind tunnel experiment of gust load alleviation is validated clearly. The theoretical simulation results are consistent with the experiment data, which proves that the theoretical analysis method is effective.
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