摘要
为验证某大型无人机主结构的疲劳寿命是否满足设计指标要求,探寻主结构的疲劳薄弱部位,为结构设计改进及制造工艺改进提供试验依据,进行全尺寸主结构耐久性试验。针对该型号无人机先进布局设计及结构设计所带来的试验机约束、载荷优化、载荷谱编制、精确加载等试验加载方面的难点,进行相关试验加载技术的对比与分析以及新技术的系列验证,由此提出大型无人机主结构耐久性试验的多功能支持夹具设计、无人机机体结构载荷优化、综合载荷与扣重的载荷谱协调编制、新型拉压垫弹性体应用、作动筒专用扣重装置设计等新的技术。经过该试验机半倍疲劳寿命的阶段性试验验证,可以表明各项技术合理可行,稳定可靠,确保了试验正常运行。
In order to verify the fatigue life of the main structure for a large Unmanned Aerial Vehicle(UAV)under the designed load spectrum and expose the weak part of the structure,improve structural detail design and test reference of manufacturing technology for full-scale main structure durability test,some new technologies were proposed,such as the design of the multifunctional support fixture,the optimization of the UAV structure load,the coordinated compilation of the comprehensive load and deduction load spectrum,the application of new tension and compression pad elastomer,and the design of special deduction device for the actuator,etc.Aiming at such difficulties like aircraft constraints,load optimization,load spectrum compilation,precise loading and other test loading difficulties were brought by the advanced layout design of this model of UAV and the structure design,comparison and analysis of related test loading technologies and series verification of new technologies were performed.Based on the phased test verification of the half-life fatigue of the aircraft,these technologies are reasonable,feasible,stable,and reliable and proved to be able to ensure the normal operation of the test.
作者
崔明
冯建民
米征
郭俊毫
CUI Ming;FENG Jianmin;MI Zheng;GUO Junhao(Aviation Technology Key Laboratory of Full Scale Aircraft Structure Static and Fatigue Test,Aircraft Strength Research Institute of China,Xi'an 710065,China)
出处
《航空学报》
EI
CAS
CSCD
北大核心
2022年第6期390-399,共10页
Acta Aeronautica et Astronautica Sinica
关键词
大型无人机
耐久性试验
试验机约束
载荷优化
载荷谱编制
加载装置
large UAV
durability test
testing aircraft constraints
load optimization
load spectrum complication
loading device
