传感器飞机机翼结构优化与性能分析  

Structural Optimization and Property Analysis of a Sensorcraft Wing

作　　者：张平[1] 吴文志[1] 吴斌[1] 

机构地区：[1]中国电子科技集团公司第三十八研究所,安徽合肥230088

出　　处：《电子机械工程》2015年第4期28-31,45,共5页Electro-Mechanical Engineering

摘　　要：传感器飞机是一种集情报、监视和侦察功能于一体的未来先进无人机。一体化机翼作为传感器飞机飞行和探测的关键结构,其主要功能是作为雷达天线和为飞行器提供升力及操纵能力。文中初步设计了一种双梁式后掠一体化机翼构型,蒙皮分区域采用玻璃纤维和碳纤维面板蜂窝夹层结构,主承力骨架采用铝合金材料。对初始机翼构型的力学性能分析表明,其静强度和稳定性不能满足最大设计载荷下的使用要求。因此对机翼结构进行了局部尺寸缩放、纤维铺层调整以及骨架传力路径改善等优化设计,分别量化给出了各优化途径对机翼性能提升的效果。综合3种优化途径得到改进设计的一体化机翼,在结构重量增加很小的情况下,强度和稳定性得到了明显提高,满足设计要求。该设计和分析结果可供其他传感器飞机一体化机翼设计参考。The sensorcraft is a kind of advanced unmanned aerial vehicle in the future which integrates the functions of intelligence,surveillance and reconnaissance（ISR）.The integrated wing,as the key part of the sensorcraft,not only provides lift and control forces during flight,but also acts as the radar antenna during detection.In this paper a two-spar sweep integrated wing configuration is preliminarily designed,of which the skin uses honeycomb sandwich structure of glass and carbon fiber panel in different areas and the bearing frame uses aluminum alloy material.The mechanical analysis of the initial wing configuration shows that the static strength and stability do not meet the requirements under the maximum design load.Then optimal design is conducted to the wing by local size scaling,layer orientation adjustment and loading path improvement.And the quantitative effects are given for each approach on the wing property enhancement.The final wing optimal configuration is obtained by integrating the three improvement approaches.Mechanical analysis of the new wing model shows that with only little weight increase,the strength and stability have been improved obviously and meet the design requirements.This design and analysis results can be used as a reference for other sensorcraft wing design.

关 键 词：传感器飞机 平台载荷一体化 共形天线 复合材料 优化设计 

分 类 号：V224[航空宇航科学与技术—飞行器设计]