含HNIW的NEPE推进剂的热分解特性研究  

Thermal Decomposition of NEPE Propellant Containing HNIW

作　　者：李杰[1] 张维[1] 罗运军[1] 赵辉[1] 马俪芳[1] 谭惠民[1] 

机构地区：[1]北京理工大学材料科学与工程学院,北京100081

出　　处：《含能材料》2006年第2期92-94,共3页Chinese Journal of Energetic Materials

基　　金：兵器预研基金资助(404060305022)

摘　　要：利用TG和DSC研究了古六硝基六氮杂异伍兹烷（HNIW）的NEPE推进剂的热分解特性。结果表明，用HNIW取代推进剂中RDX的50％，使硝酸酯在80—145℃的挥发失重比例减小；同时，在145～240℃时RDX和HNIW相互作用，同时发生分解反应，表现出大量的放热。当HNIW完全取代RDX后，分解反应在145—240℃分为两个阶段，即硝酸酯分解失重和部分HNIW分解失重，说明HNIW受硝酸酯放热分解的影响，其分解温度提前。Thermal decomposition of NEPE propellant containing hexanitrohexaazisowurtzita （HNIW） was investigated by thermogravimetry （TG） and differential scanning calorimetry （DSC）. The results show that when RDX was replaced by HNIW by half in the propellant, the mass loss of nitric esters mainly took place from 80 ℃ to 145 ℃. Furthermore, when the temperature went up to 145 ℃ , RDX and HNIW influenced each other for their thermal decomposition with a major exothermic peak appearing in DSC curve. When RDX was replaced by HNIW totally in the propellant, the mass loss between 145 ℃ and 240 ℃ was split in two steps, i.c. decomposition nitric esters and partial decomposition of HNIW. This phenomenon fully shows that the incorporation of nitric esters greatly affects thermal decomposition of HNIW.

关 键 词：物理化学 六硝基六氮杂异伍兹烷(HNIW) NEPE推进剂 热分解 TG DSC 

分 类 号：V512[航空宇航科学与技术—航空宇航推进理论与工程]