Study on Combustion Flame of CL-20 Propellant

摘要

Two groups of composite modify double-base (CMDB) propellant formulations containing different content of CL-20 or RDX were designed. The change of the combustion flame was studied in combination with the combustion performance with the increase of the CL-20 or RDX. It is showed that the CL-20-CMDB propellant flame area decrease with the increase of CL-20 at IMPa, while the RDX-CMDB propellant instead. The flame area of CL-20-CMDB propellant is greater than that of RDX-CMDB propellant above IMPa. The flame area is larger, the burning rate is higher. The combustion flame of both CL-20-CMDB and RDX-CMDB propellant are premixed flame, which is constituted by firstly flame, the dark zone and the secondary flame. The flame root of the secondary flame toward the dark area is corresponded to the firstly flame. The more firstly flame, the more flame root. This phenomenon indicates that the traditional lead, copper and carbon composite catalyst is still applicable to adjust the combustion performance of CL-20-CMDB propellant.