基于干涉接触的前缘缝翼尾缘结构设计与分析  

Structural design and analysis of leading edge slat interference trailing edge

作　　者：冯蕴雯[1] 张家乐 薛小锋[1] 毛艺皓 袁坚锋 FENG Yunwen;ZHANG Jiale;XUE Xiaofeng;MAO Yihao;YUAN Jianfeng(School of Aeronautics,Northwestern Polytechnical University,Xi’an 710072,China;Shanghai Aircraft Design and Research Institute,Commercial Aircraft Corporation of China,Ltd.,Shanghai 201210,China)

机构地区：[1]西北工业大学航空学院,西安710072 [2]中国商用飞机有限责任公司上海飞机设计研究院,上海201210

出　　处：《北京航空航天大学学报》2023年第4期761-767,共7页Journal of Beijing University of Aeronautics and Astronautics

基　　金：国家自然科学基金(51875465)。

摘　　要：前缘缝翼是大型飞机起飞与降落阶段重要的增升装置,但受自身结构刚度及其支持刚度影响,承受气动载荷时缝翼易发生翘曲变形,与翼盒产生缝隙,影响到机翼的气动效率。为消除巡航状态缝翼的变形,提高机翼气动效率,提出前缘缝翼干涉尾缘结构设计技术。对影响前缘缝翼结构法向和弦向变形的主要因素进行理论分析。以国内某大型飞机前缘缝翼为研究对象,针对蒙皮等各结构尺寸对前缘缝翼本体刚度的影响,从质量和变形两方面进行详细论述。在保持原有前缘缝翼结构尺寸、质量的前提下,进行前缘缝翼干涉尾缘结构的设计。结果表明:所提的前缘缝翼干涉尾缘结构在巡航工况气动载荷下,可以保持与机翼不分离的状态,提高气动性能,且有效避免了质量的增加。The leading edge slat is an important lift increasing device in the take-off and landing stages of large aircraft.But affected by its own body stiffness and support stiffness,the slat is prone to warpage and deformation under aerodynamic load,resulting in gaps with the wing box,which affects the aerodynamic efficiency of the wing.To eliminate the deformation of slat in cruise and improve the aerodynamic efficiency of the wing,the leading edge slat interference trailing edge structural design technology is proposed in this paper.Firstly,the main factors affecting the normal and chord deformation of slat structure are theoretically analyzed.Then,taking the leading edge slat of a large domestic aircraft as the research object,the influence of skin and other structural dimensions on the stiffness of slat body is discussed in detail from two aspects of weight and deformation.Finally,on the premise of maintaining the size and weight of the original slat structure,the leading edge slat interference trailing edge structure is designed.The results show that the proposed interference trailing edge structure can maintain the state of non separation from the wing under the aerodynamic load of cruise condition,improve the aerodynamic performance,and effectively avoid the increase of weight.

关 键 词：干涉尾缘 前缘缝翼 变形因素 本体刚度 结构设计 

分 类 号：V222[航空宇航科学与技术—飞行器设计]