摘要
对300余秒冲压发动机试验后的硅橡胶绝热层试验件残骸进行解剖分析,制样,测试了试验后烧蚀碳化层的密度、导热系数,并测量计算试验后发动机内部不同部位绝热层线烧蚀率。经与试验前实测数据进行对比,得出以下结论:硅橡胶绝热层在冲压发动机试验后,碳化层密度较原始材料增大,碳化层导热系数较原始材料降低;冲压发动机工作过程中绝热层的烧蚀是一个很复杂的过程,不同部位烧蚀情况差异较大,总的规律是头部较尾部烧蚀严重。并从理论上对此结论进行了解释。
The test piece wreckage of silicone rubber insulation layer after testing the ramjet motor for more than 300 s was anatomically analyzed, the sample was prepared. The density and thermal conductivity coefficient of ablated carbonization layer were determined after test. And the linear ablation rates of the insulation layer at different parts in the motor after test were tested and calculated. Through comparing with the actually measured data before test, the following conclusions were obtained： the density of carbonized layer is higher than that of the original material, and the conductivity coefficient of the carbonized layer is lower than that of the original material after the silicone rubber insulation layer ramjet motor test. The ablation of the insulating layer during the working process of ramjet motor is a quite complex process, the difference of ablation situation at different parts is larger. The general rule is that the ablation at head is more serious than that at tail. And the conclusions were theoretically explained.
出处
《化学推进剂与高分子材料》
CAS
2014年第1期49-51,56,共4页
Chemical Propellants & Polymeric Materials
关键词
冲压发动机
硅橡胶
绝热层
密度
烧蚀
导热系数
ramjet motor
silicone rubber
insulation layer
density
ablation
thermal conductivity coefficient
