基于ISIGHT的复合材料机身优化设计研究  

ISIGHT-based composite fuselage structure design

作　　者：李占科[1] 徐合良[1] 李志超[1] 

机构地区：[1]西北工业大学航空学院,陕西西安710072

出　　处：《西北大学学报（自然科学版）》2015年第2期242-246,共5页Journal of Northwest University（Natural Science Edition）

基　　金：国家自然科学基金资助项目(1110216)

摘　　要：对机身等直段受气密载荷作用时蒙皮铺层的优化设计进行初步研究。将有限元软件NASTRAN求解器与遗传算法相结合,通过ISIGHT软件实现具体流程,并通过C++编程弥补ISIGHT的不足。分析得出了在气密载荷作用下,最优的机身等直段蒙皮的铺层顺序、铺层角度和层数。将优化前后复合材料机身对比,机身等值段减轻了16.2%的机身结构重量;与A320-200金属机身对比,相应机身段减轻了26.5%,提高了结构效率。该方法可实现读取初值、计算和读取结果整个过程的自动化,减少了大量计算时间。done when A preliminary study of optimizing the skin lamination on the straight section of the fuselage has be only the airtight loads is considered. Combined the finite element software NASTRAN solver and the genetic algorithm to achieve the specific process by ISIGHT software, and to make up for deficiencies by ISIGHT C ＋ ＋ programming. Under airtight loading , analysis obtained the best lamination sequence, ply angles and layers of the fuselage skin. Contrast the before and after the optimization of composite fuselage, the equivalent section of the fuselage to reduce the 16.2% of the body weight of the structure; contrast to the metal air-frame of A320-200, corresponding fuselage sections reduced 26.5%, improving the structural efficiency. The calculation method can be automated to improve the computational efficiency. This method can achieve the initial read, automated calculations and read the results of the whole process, and reduces the amount of computation time.

关 键 词：复合材料 遗传算法 ISIGHT 气密载荷 铺层方式 

分 类 号：V214.8[航空宇航科学与技术—航空宇航推进理论与工程]