Effect of Al–Li Alloy on the Combustion Performance of AP/RDX/Al/HTPB Propellant

Aluminium–lithium alloy (Al–Li alloy) powder has excellent ignition and combustion performance. The product of Al–Li combined with ammonium perchlorate is gaseous at the working temperature solid rocket motors, which greatly reduces loss two-phase flow. Experimental investigations were thoroughly conducted to determine effect Al–2.5Li (2.5 wt% lithium) content on propellant agglomeration based thermogravimetry-differential scanning calorimetry, heat combustion, laser ignition, diagnosis, a simulated 75 mm motor condensed products (CCPs) collection device. results show that exothermic weight gain upon thermal oxidation obviously higher than those Al powder. Compared reference propellant’s formulation, leads an increase in burning rate decrease size propellants. As gradually increases from 0 19 wt%, 5.391 ± 0.021 mm/s 7.244 0.052 7 MPa pressure; meanwhile, pressure exponent law changed 0.326 0.047 0.483 0.045, d43 residue reduced 165.31 36.18 μm 12.95 4.00 μm. efficiency HTPB increased by about 4.4% when 19%. Therefore, promising fuel for