Impact modeling of composite aircraft structures

这是一个在CRIAQ行业主导项目计划下进行的研究和开发项目。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。重点是为复合材料和金属飞机开发增强的耐撞性仿真工具和实用的故障建模和验证。这是加拿大航空业迫切需要的，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、机舱、螺旋桨和航空发动机导管和风扇叶片。这些部件容易受到鸟撞和异物的高速撞击，或者受到不同表面上可幸存的坠毁着陆的冲击，这可能会对飞机安全构成严重威胁。该项目联合体由机身制造商、研究机构和软件专家组成。大体上，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，并对复合材料的应力应变和破坏行为进行建模。这项工作将为改进以前开发的率相关损伤模型提供基础，该模型将由软件专家实施到商业有限元程序包中。这项工作的结束将通过验证数字模型与受冲击和碰撞载荷的选定工业演示部件以及改进的计算机分析和验证遭受鸟或异物损坏(FOD)打击的飞机部件的方法。

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.