RDX-CMDB推进剂燃速温度敏感系数的实验研究

为了揭示RDX-CMDB推进剂中各常见组分对其燃速温度敏感系数的影响规律,制备了一系列含RDX、铝粉及燃烧催化剂的CMDB推进剂样品。采用氮气靶线法测得其在2~14MPa下的燃速温度敏感系数(σp)。讨论了RDX含量、铝粉、燃烧催化剂对RDX-CMDB推进剂燃速温度敏感系数的影响。结果表明,提高工作压强、增加RDX含量、添加燃烧催化剂均有助于降低RDX-CMDB推进剂在一定初始条件下的燃速温度敏感系数。配方中引入铝粉后可降低中低压下RDX-CMDB推进剂的燃速温度敏感系数,且燃速温度敏感系数几乎不随压强变化而变化。选用含邻苯二甲酸铅和没食子酸铋锆作燃烧催化剂,均可在2~10MPa下降低RDX-CMDB推进剂的燃速压强指数,同时降低燃速温度敏感系数。

Experimental Research on Temperature Sensitivity Coefficient of Burning Rate for RDX-CMDB Propellant

In order to reveal the effects of the commonly used component on temperature sensitivity coefficient of burning rate for RDX‐CMDB propellant ,a series of propellant samples containing RDX ,aluminium powder and combustion catalyst were prepared .Their temperature sensitivity coefficients of burning rate σP were determined at the pressure of 2MPa to 14MPa by using nitrogen strand burner method .The influences of RDX content ,aluminium powder and combustion cata‐lysts on the temperature sensitivity coefficient of burning rate were discussed .The results show that the increase of working pressure and RDX content and the addition of combustion catalyst are healpful to reduce the temperature sensitivity coeffi‐cient of burning rate of RDX‐CMDB propellant under certain initial conditions .After introducing aluminium powder into the formulation ,the temperature sensitivity coefficient of burning rate of RDX‐CMDB propellant at middle and low pressures can be reduced and is almost not changed with the pressure .Using lead phthalate and bismuth/zirconium gallate as combus‐tion catalyst may reduce pressure exponent of burning rate at the pressure of 2M Pa to 10M Pa and reduce the temperature sensitivity coefficient of burning rate .