Investigations for missile launching in an improved concentric canister launcher

Experimental and numerical investigations are carried out for missile launching in an improved concentric canister launcher (CCL). It can be seen that the missile can be protected effectively from high-temperature ablation by discharging exhaust gases from a fan-shaped tube, changing the flow direction with a guide plate and adding an inner block pressure loads that correspond to the impact force on the launcher vibrate with the influence of shock cells of supersonic jet flow and jet impinging distance; and the gun effect, which is typically dominated by pressure losses and choking states of tube flows, can produce momentum argumentation for missile launching in the improved CCL. The result shows that the section converging near the inlet of the flabellate tube compresses exhaust gases, and leads to flow choking in this area, where the maximum flow Mach number equals 1. Moreover, near the outlet of the tube, another flowchoking appears as a result of friction tube flow, which typically depends on both equivalent diameter and length of the tube.