适应高压强的HTPB推进剂的燃烧性能

The Combustion Properties of HTPB Propellants under High Pressures

为改善高压强下HTPB推进剂的燃烧特性,研究了碳酸盐复合调节剂、二茂铁衍生物G、高氮化合物M、纳米铝粉和纳米金属氧化物对HTPB推进剂燃烧性能的影响。结果表明,碳酸盐复合调节剂能够降低推进剂的燃速和压强指数;二茂铁衍生物G能够提高推进剂的燃速,同时将推进剂在8.60~17.12M Pa下的压强指数降至0.27;高氮化合物也可降低推进剂的燃速和压强指数;将高氮化合物M与二茂铁衍生物G配合使用可将推进剂在8.63~16.48M Pa下的压强指数降至0.24;纳米铝粉和包覆的纳米金属氧化物可明显降低推进剂的燃速压强指数。

In order to improve the combustion properties of HTPB propellants, the effect of carbonate composites, ferrocene derivative G, high nitrogen energetic material M, nanometer metal oxide particles and nano-aluminum on combustion characteristics of HTPB propellants was studied. The results show. that carbonate composites decreased the burning rate and pressure exponent of HTPB propellants. The ferrocene derivative G decreased the pressure exponent of HTPB propellants to 0. 27 in the pressure range of 8. 60-17. 12MPa,and increased their burning rate. High-nitrogen energetic material M decreased both the burning rate and the pressure exponent of HTPB propellants. Modifier M and G decreased the pressure exponent of HTPB propellants to 0. 24 in the pressure range of 8. 63- 16. 48MPa. Nano aluminum and nano-metal oxide obviously decreased the pressure exponent of HTPB propellants.