基于ANSYS ACP的固体火箭发动机复合材料壳体强度分析  

Strength analysis of SRM composite case based on ANSYS ACP

作　　者：李靖 马虎[1] 周长省[1] 夏镇娟 LI Jing;MA Hu;ZHOU Changsheng;XIA Zhenjuan(School of Mechanical Engineering,Nanjing University of Science and Technology,Nanjing 210094,China)

机构地区：[1]南京理工大学机械工程学院,南京210094

出　　处：《固体火箭技术》2023年第3期383-391,共9页Journal of Solid Rocket Technology

基　　金：国家自然科学基金(12072163,52106161);中国博士后科学基金(2020M681616)。

摘　　要：为了较为准确地预测封头的纤维厚度以提高封头建模的准确性,并研究载荷边界条件对1/8固体火箭发动机复合材料壳体应力求解结果的影响,提供了一种基于ANSYS ACP的纤维缠绕发动机复合材料壳体铺层设计的分析方法,并采用有限元数值模拟对一定内压下的发动机复合材料壳体进行强度研究。基于网格理论,结合三次样条函数法预测发动机复合材料壳体的封头厚度,并采用ANSYS ACP中的插值表功能模拟封头段连续变化的缠绕厚度和缠绕角度,通过在ANSYS Workbench中对1/8发动机复合材料壳体有限元模型施加一定载荷及边界条件,对壳体的应力、应变进行了求解和分析。结果表明,采用位移对称边界会在约束处造成局部区域的应力分布不均,所设计的发动机壳体基本满足在12 MPa内压下的强度要求,在18 MPa最小设计爆破压强下,过渡段是壳体的应力薄弱区域。文中所采用的分析方法可以为在ANSYS Workbench中对固体火箭发动机复合材料壳体的设计和强度研究提供借鉴。In order to predict the fiber thickness of the dome more accurately to improve the dome modeling accuracy,and to research on the influence of load boundary conditions on stress solution results of the 1/8 solid rocket motor(SRM)composite case,an analysis method was provided for layup design of the fiber-wound SRM composite case based on ANSYS ACP,and finite element numerical simulation was used to research on the strength of the SRM composite case under a certain internal pressure.Based on the mesh theory,the dome thickness of SRM composite case was predicted by combining the cubic spline function method,and the Look-up Table function in ANSYS ACP was used to simulate continuous change of winding thickness and angle of the dome.By applying certain load and boundary conditions to the finite element model of 1/8 SRM composite case in ANSYS Workbench,the stress and strain of the case were solved and analyzed.The results show that the use of displacement symmetric boundary will form an uneven stress distribution in the local area at the constraint,the designed motor case basically meets the strength requirements under 12 MPa internal pressure.Under the minimum design burst pressure of 18 MPa,the transition section is the weak region of the case.The analysis method used in this paper can provide reference for design and strength study of SRM composite case in ANSYS Workbench.

关 键 词：固体火箭发动机 复合材料壳体 ANSYS ACP 强度分析 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]