钝前缘楔形翼颤振特性分析  

Analysis of Flutter Characteristics of Blunt Leading Edge Wedge-Shaped Wing

作　　者：蒋雯霄 JIANG Wenxiao(Beijing Institute of Space Long March Vehicle,Beijing 100076,China)

机构地区：[1]北京航天长征飞行器研究所,北京100076

出　　处：《强度与环境》2024年第2期20-26,共7页Structure & Environment Engineering

摘　　要：为了研究飞行器翼的颤振特性,基于钝前缘楔形三角翼模型,采用ZONA 7和ZONA 7U两种升力面方法计算翼的颤振边界,并与试验结果对比,可知ZONA7方法计算得到的颤振边界高于试验值,存在设计安全隐患;ZONA 7U方法可对颤振边界进行保守预测,提高设计可靠性。建立四种不同前缘半径楔形三角翼模型,采用ZONA7U方法分析前缘半径对翼颤振特性的影响,分析表明,增加前缘半径,颤振速度随之增加,颤振频率先增后降。在此基础上分析不同马赫数下颤振特性变化规律。结果表明,颤振速度随马赫数增加而增加,颤振频率受马赫数影响产生的变化较小。To study flutter characteristics of aircraft wings,ZONA 7 and ZONA 7U lifting surface methods were used to calculate flutter boundaries based on the blunt leading edge wedge-shaped delta wing model,and compared with the test results,the flutter boundaries calculated by ZONA 7 method are higher than the test value,which has hidden dangers in design.The ZONA 7U method can conservatively predict the flutter boundary and improve the design reliability.The ZONA 7U method is used to analyze the influence of leading-edge radius on flutter characteristics.The analysis shows that the flutter speed increases with the increase of the leading-edge radius,and the flutter frequency increases first and then decreases.The results show that the flutter velocity increases with the increase of Mach number,and the flutter frequency changes little with the increase of Mach number.

关 键 词：钝前缘 楔形翼 颤振特性 ZONA7U方法 前缘半径 

分 类 号：V414.33[航空宇航科学与技术—航空宇航推进理论与工程]