摘要
为了满足未来高速高加速战术导弹对壳体承载能力和防热功能的要求,采用干法缠绕工艺制备结构/防热一体化?480 mm复合材料壳体,其中结构层采用T700碳纤维/氰酸酯复合材料,防热层采用复合防热结构,进行壳体内压检验、声发射和水压爆破实验,研究内压作用下壳体的应变变化规律,判断复合材料损伤类型,预测壳体破坏位置,评价外防热材料的结构完整性,考核壳体承受内压载荷的能力。结果表明:结构/防热一体化?480 mm壳体应变与压强呈线性关系,随压强的升高而增大;?480 mm壳体在内压作用下出现树脂开裂、单丝断裂、纤维束断裂和分层等声发射信号,分布在前后封头区域,二次加载后费利西蒂(Felicity)比为0.96;壳体的爆破压强为18.6MPa,容器特性系数达到42.1 km,后封头区域出现宏观纤维断裂现象;防热层材料表面出现少量纤维起毛、断丝和发白现象,未出现分层和脱落,保持较好的结构完整性。
In order to meet the high requirements of future high-speed and high acceleration tactical missiles for shell bearing capacity and heat protection function,the integrated structure-heat protection Φ480 mm composite shell was prepared by dry winding process,in which the structure layer adopted T700 carbon fiber/cyanate ester composite,and the heat protection layer adopted composite heat protection structure.The internal pressure,acoustic emission and hydraulic burst tests had been done for integrated structure-heat protection Φ480 mm shell.The strain variation law,the damage type and damage location of Φ480 mm composite shell were researched.The structural integrity of external heat protection materials was evaluated.The capacity of bearing internal pressure load was also assessed for the integrated structure-heat protection Φ480 mm composite shell.The results show that the strain of Φ480 mm composite shell is linear with the pressure and increased with the raising pressure.The acoustic emission signals,such as resin cracking,monofilament fracture,fiber bundle fracture and delamination are distributed in the dome areas under the internal pressure.The Felicity ratio of Φ480 mm composite shell is 0.96 after secondary loading.The bursting pressure of Φ480 mm composite shell is 18.6 MPa,and the vessel characteristic coefficient reaches 42.1 km.The fiber fracture occurs in the dome areas.A small amount of fiber fuzzing,broken wire and whitening appear on the surface of the heat resistant layer material,and no delamination and shedding occur,maintaining good structural integrity.
作者
惠雪梅
张岗
侯晓
崔红
张承双
包艳玲
HUI Xuemei;ZHANG Gang;HOU Xiao;CUI Hong;ZHANG Chengshuang;BAO Yanling(Xi’an Aerospace Composites Research Institute,Xi’an 710025,China;Shaanxi Key Laboratory of Aerospace Composites,Xi’an 710025,China;Academy of Aerospace Solid Propulsion Technology,Xi’an 710025,China;China Aerospace Scienceand Technology Corporation,Beijing 100048,China)
出处
《航空材料学报》
CAS
CSCD
北大核心
2022年第3期97-103,共7页
Journal of Aeronautical Materials
基金
国家自然科学联合基金资助项目(U1837601)。
关键词
结构/防热一体化
氰酸酯树脂
爆破压强
声发射
费利西蒂比
structure and heat protection integration
cyanate ester
burst pressure
acoustic emission
Felicity ratio