摘要
X型复合材料杆承受拉伸载荷的能力突出,可消除端部接头先于杆主体破坏的薄弱环节。新型火箭的大型结构需求高性能杆系,因此首先成功研制1∶2尺寸缩比的杆单元,通过研究得出适用实尺寸设计的四方面共性技术,即设计优化、与相邻段的端部连接设计、中空夹层杆的制造工艺技术和试验方法。对杆单元做特征化处理来建立两种有限元模型。在简化模型上,采用实验设计(Design of Experiments,DOE)手段筛选设计变量,工程方法缩减数量,再利用全局响应面法寻优;借助真实模型校核强度。连接接头尺寸、螺栓的余量设计兼顾所属部段的尺寸限制和承载需求。经有限元分析和试验验证,优化后杆单元实现同比减重约26%。
X-shaped composite bar’s ability of bearing tensile load is outstanding, by which the weak link between end joint and rod body can be eliminated. The joint often breaks up earlier than the rod body does. The heavy lift launch vehicles of large size demand light efficient truss,so first 0.5 size shrinkage ratio bar is successfully developed and is the generic technique summed up, which also apply to real size bar. Four items of the generic technique are design optimization, the adjacent end joint design, the manufacturing technology of the hollow bar and test method. Two kinds of finite element models are established by characterizing the bar. By using the simplified model, computer design of experiments(DOE) is carried to screen out variables, engineering approach is used to reduce the number, and then the global response surface method is used to evaluate the optimum;real model is utilized to verified the intensity. The size of joint and the allowance of bolt are designed to meet the size limitation and bearing requirements. Verified by finite element analysis and experiments, optimized X-shaped bar is reduced by 26% in the case of ensuring the use of strength requirements.
作者
李倩云
王会平
刘观日
张薇
刘利明
Li Qian-yun;Wang Hui-ping;Liu Guan-ri;Zhang Wei;Liu Li-ming(Beijing Institute of Astronautical Systems Engineering,Beijing,100076)
出处
《导弹与航天运载技术》
CSCD
北大核心
2020年第4期24-29,共6页
Missiles and Space Vehicles
关键词
X型
杆
设计
实现
X-shape
bar
design
implementation
