天问一号探测器耐高温蜂窝夹层结构选材与性能研究  

Material Selection and Property Research of Honeycomb Sandwich Structure With High Temperature Resistance for Tianwen-1 Mars Probe

作　　者：杨强 杨昌昊[1] 李莺歌 王刚[1] 祁玉峰[1] YANG Qiang;YANG Changhao;LI Yingge;WANG Gang;QI Yufeng(Beijing Institute of Spacecraft System Engineering,Beijing 100094;Beijing Spacecrafts,Beijing 100094)

机构地区：[1]北京空间飞行器总体设计部,北京100094 [2]北京卫星制造厂有限公司,北京100094

出　　处：《宇航材料工艺》2021年第5期88-93,共6页Aerospace Materials & Technology

摘　　要：针对天问一号火星探测器耐高温大承载复合材料蜂窝夹层结构应用需求,基于材料匹配设计和工艺可行原则,提出了氰酸酯树脂体系的复合材料蜂窝夹层结构。通过比较不同后处理工艺下M40J/BS-4氰酸酯基复合材料高温层间剪切性能,发现BS-4氰酸酯基复合材料经200℃下3~5 h后处理可获得较佳的高温使用性能。经200℃下4 h后处理的M40J/BS-4氰酸酯基复合材料,在170℃下各项力学性能保持率均达到室温测试值的80%以上。板芯胶高温力学性能测试以及其对夹层结构高温承载性能的影响研究表明,氰酸酯体系的J-245C、J-389B两种板芯胶在温度不超过200℃时均具有足够协调板芯变形及传递板芯间载荷的能力,但高温下胶黏剂的性能退化会造成夹层结构刚度的退化。天问一号探测器蜂窝夹层结构典型单元在高温下的弯曲性能、侧向压缩性能测试结果表明,碳纤维氰酸酯基复合材料铝蜂窝夹层结构具备耐170℃高温下大承载的能力。Aiming at the application requirements of the composite honeycomb sandwich structure with high temperature resistance and large load bearing for Tianwen-1 Mars probe,a cyanate resin composite honeycomb sandwich structure was proposed based on material matching design and process feasibility.By comparing the high temperature interlaminate shear properties of M40J/BS-4 cyanate resin composites under different post-treatment processes,it was found that BS-4 cyanate resin composites can be obtained with better high temperature performance after 3 to 5 hours post-treatment at 200℃.For M40J/BS-4 cyanate resin composite material after 4 hours post treatment at 200℃,the retention coefficient of various mechanical properties at 170℃reached more than 80%of the room temperature test value.The high-temperature mechanical properties test of the adhesives and the study of the adhesives influence on the high-temperature load-bearing performance of the sandwich structure showed that the two adhesives of the cyanate ester,J-245C and J-389B,have sufficient ability to coordinate the deformation and transfer the load between skins and cores when the temperature does not exceed 200℃.The performance degradation of the adhesive at high temperatures will cause the rigidity degradation of the sandwich structure.The test results of bending performance and lateral compression performance of honeycomb sandwich structure of Tianwen-1 mars probe showed that the honeycomb sandwich structure of carbon fiber cyano matrix composite has the large bearing capacity under 170℃high temperature.

关 键 词：耐高温 复合材料 蜂窝夹层结构 材料选择 性能研究 

分 类 号：TB33[一般工业技术—材料科学与工程]