Concentric Canister Launcher Gas Flow Field Numerical Simulation And Pilot Structure Design Improvements

The concentric canister launcher (CCL) is a new vertical launch system. The CCL is very popular with some country’s navy force as it has some advantages, which other system can’t reach such as easy to be miniaturization and lightweighting. The ability of gas exhaust is a very important rule, which because the gas always impinging the CCL when launching missile. Investigation object of this dissertation is concentric canister launcher. A series of research and exploration including the flow field characteristics of complex gas jet and the parameters of the missile body, jet-guide cone, the bottom and exit of CCL are carried out respectively. Three factors that influent the gas exhaust are analyzed.Taking the multicomponent transport equations and unsteady Euler equations as foundation. Using the Roe format finite volume method to carry on numerical simulation. The classic and representative problem forward-facing step and a supersonic jet impinging plate flow field test example are calculated, the result indicate that the methods is effective. The block structure mesh of the irregula computational area is established. Dynamic simulation of jet flow field is performed by using dynamic grid meshing technology. In order to cut the time exhaust of simulation, first carrying on simulation and comparison under two dimensional. The better program is chosen by comparing the temperature of missile body and flow rate. On this base, the three dimensional grid and flux model of better program is established. The features of the flux are analyzed after simulation. The changes of major parts’parameters with the time are gain. At the same time, this investigation offer an effective means for the analyzation of the complex flux in CCL.The computed results can be used to corrosion protection and noise reduction. It also can be used to intensity and rigidity design and check of this launch set and the model machine making.