摘要
面向直升机尾传动轴抗弹击设计,开展了不同因素影响下尾传动轴弹击损伤规律数值模拟研究。基于有限元仿真软件建立了尾传动轴弹击损伤数值仿真模型,并通过弹击试验验证模型的可靠性。进而基于经验证的数值仿真模型,分析了偏移量和入射角两个典型参数对尾传动轴弹击损伤的影响规律。分析结果表明:尾传动轴弹击损伤程度随着子弹偏移量及入射角的增大,呈现先增大后减小的趋势,在切边位置、入射角为75°工况下尾传动轴弹击损伤最为严重。在此基础上,进一步研究了摩擦因数、子弹入射速度、尾传动轴转速、子弹偏航角四个弹靶参数对尾传动轴弹击损伤的影响规律。研究结果表明:摩擦因数对尾传动轴弹击损伤影响较小,尾传动轴转速、子弹入射速度和子弹偏航角均对尾传动轴弹击损伤有较大影响。
Here,aiming at anti-projectile impact design of helicopter tail drive shaft,numerical simulation was performed for projectile impact damage law of helicopter tail drive shaft under different affecting factors.The numerical simulation model for projectile impact damage of helicopter tail drive shaft was established based on finite element simulation software,and the reliability of the model was verified with impact tests.Then,based on the verified numerical simulation model,effects of 2 typical parameters of offset and incident angle on projectile impact damage of tail drive shaft were analyzed.The analysis results showed that damage degree of tail drive shaft caused by projectile impact increases firstly and then decreases with increase in bullet offset and incidence angle;the most severe impact damage occurs under the condition of trimming position and incidence angle of 75°.Furthermore,effects of 4 target parameters of friction coefficient,bullet incidence velocity,tail drive shaft rotating speed and bullet yaw angle on projectile impact damage of tail drive shaft were further studied.The study results showed that friction coefficient has a smaller impact on projectile impact damage of tail drive shaft,while tail drive shaft rotating speed,bullet incident velocity and bullet yaw angle all have larger impacts on projectile impact damage of tail drive shaft.
作者
未雷
林瑶洁
吴汪箭
陈蔚芳
王希
朱如鹏
王旦
WEI Lei;LIN Yaojie;WU Wangjian;CHEN Weifang;WANG Xi;ZHU Rupeng;WANG Dan(National Key Lab of Science and Technology on Helicopter Transmission Technology,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;National Key Lab of Science and Technology on Helicopter Transmission Technology,Hunan Aviation Powerplant Research Institute,AECC,Zhuzhou 412002,China)
出处
《振动与冲击》
EI
CSCD
北大核心
2024年第13期324-332,340,共10页
Journal of Vibration and Shock
基金
国家自然科学基金(52005253)
江苏省自然科学基金(BK20200426)
直升机传动技术国家级重点实验室开放基金(HTL-A-21G07,HTL-A-22K01)
江苏省精密与微细制造技术重点实验室自主科研项目。
关键词
直升机
尾传动轴
弹击损伤
数值模拟
helicopter
tail drive shaft
projectile impact damage
numerical simulation
