Aero-servo-elastic design of a morphing wing trailing edge system for enhanced cruise performance 机翻标题: 暂无翻译,请尝试点击翻译按钮。

来源
Aerospace science and technology
年/卷/期
2019 / 86 / Mar.
页码
215-235
ISSN号
1270-9638
作者单位
Univ Naples Federico II, Dept Ind Engn, Aerosp Sect, Via Claudio 21, I-80125 Naples, NA, Italy;CIRA Italian Aerosp Res Ctr, Via Maiorise, I-84081 Capua, CE, Italy;Univ Naples Federico II, Dept Ind Engn, Aerosp Sect, Via Claudio 21, I-80125 Naples, NA, Italy;
作者
Arena, Maurizio;Concilio, Antonio;Pecora, Rosario;
摘要
The Adaptive Trailing Edge Device (ATED) was a sub -project inside SARISTU (Smart Intelligent Aircraft Structures, 2011-2015), an L2 level project of the 7th EU Framework programme coordinated by Airbus, aimed at developing technologies for realizing a morphing wing for the improvement of general aircraft performance. That study, divided into design, manufacturing and testing phases, involved universities, research centers and leading industries of the European consortium. The aim of the present work is to predict the aero-servo-elastic impact of a full-scale morphing wing trailing edge on a CS-25 category aircraft. Within SARISTU, many FE models were realized, taking into account the complete and complex adaptive wing structure behavior. Those numerical representations referred to the 5.5 m wing section that was then employed for wind tunnel tests; such segment included the winglet and was representative of the outer wing segment (namely, the so-called "aileron region"). Those models were taken as reference to develop numerical representation of the considered wing that better suited the complete wing segment, from the fuselage attachment to the end of the flap region. Therefore, a scaling process was necessary, aimed at translating the former architectures to the new geometries. This kind of extrapolation had the advantage to take into account larger rooms to host the complex actuator system with all its components. MSC Nastran FE models were elaborated to estimate stiffness and inertial distributions that allowed constructing the stick-beam mock-up of the complete structure. Several cases of flutter analysis were investigated by an in-house code, SANDY 3.0, to verify the safety requirements imposed by the applicable aviation regulations (paragraph 25.629, parts a and b-1). Moreover, dynamic stability assessment was performed with respect to single and combined failures of the actuation line and kinematic chain enabling morphing in order to support FHA (Fault and Hazard Analysis). (C) 2019 Elsevier Masson SAS. All rights reserved.
机翻摘要
暂无翻译结果,您可以尝试点击头部的翻译按钮。
关键词/主题词
Adaptive trailing edge device;Aeroelastic stability;Airworthiness;Failure;FEM morphing;
若您需要申请原文,请登录。

最新评论

暂无评论。

登录后可以发表评论

意见反馈
返回顶部