Impact modeling of composite aircraft structures

复合材料飞机结构的冲击建模

• 批准号: 429270-2011
• 负责人: Gakwaya, Augustin
• 金额: $ 2.38万
• 依托单位: Université Laval
• 依托单位国家: 加拿大
• 项目类别: Collaborative Research and Development Grants
• 财政年份: 2017
• 资助国家: 加拿大
• 起止时间: 2017-01-01 至 2018-12-31
• 项目状态: 已结题
• 来源: https://www.nserc-crsng.gc.ca/ase-oro/Details-Detailles_eng.asp?id=618375
• 关键词: Impact; modeling; composite; aircraft; structures

This is a research and development project run under the CRIAQ industry driven project scheme. Its aim is to develop design methodologies and predictive numerical simulation methods for the high velocity impact response of composite aircraft structures. The focus is on developping enhanced crashworthiness simulation tools and practical failure modeling and validation for composites and metallic aircraft . It is urgently required by the Canadian aircraft industry since fibre reinforced composite materials are increasingly being used in primary aircraft structures such as fuselage section, wing leading edges, nacelles, propellers and aeroengine ducts and fan blades. These parts are susceptible to high velocity impacts either from bird strike and foreign objects or from shock of survivable crash landings on different surfaces that can pose a serious risk to aircraft safety. The project consortium consists of airframe manufacturers, research establishments and software specialists. Broadly, the industrial partners will specify metallic and/or composite materials systems, define structures and perform impact tests. High rate materials testing, and modeling of composites stress-strain and failure behaviour will be carried out by the research institutes and university partners. This work will provide a basis for improvement of previously developed rate dependent damage models which will be implemented into commercial Finite Element packages by the software specialist. The work will be concluded by validating the numerical models against selected industrial demonstrator parts subjected to impact and crash loads and an improved methodology for computer analysis and certification of aircraft parts subjected to bird or foreign object damage (FOD) strike.

这是一个在CRIAQ行业驱动项目计划下运行的研发项目。其目的是发展复合材料飞机结构高速冲击响应的设计方法和预测数值模拟方法。重点是开发增强的耐撞性仿真工具和复合材料和金属飞机的实际故障建模和验证。加拿大飞机工业迫切需要这种材料，因为纤维增强复合材料越来越多地用于飞机的主要结构，如机身部分、机翼前缘、短舱、螺旋桨和航空发动机管道和风扇叶片。这些部件容易受到来自鸟撞和异物的高速冲击，或者来自在不同表面上的可存活的坠毁着陆的冲击，这可能对飞机安全构成严重风险。该项目联合体由机身制造商、研究机构和软件专家组成。从广义上讲，工业合作伙伴将指定金属和/或复合材料系统，定义结构并进行冲击测试。研究机构和大学合作伙伴将进行高速率材料测试，以及复合材料应力应变和失效行为的建模。这项工作将提供一个基础，为改进以前开发的率相关的损伤模型，将实施到商业有限元软件包的软件专家。这项工作的最后将通过验证数字模型对选定的工业验证机零件受到冲击和坠毁载荷和改进的方法，计算机分析和认证的飞机零件受到鸟或异物损坏（FOD）的打击。