A heat exchange model between the combustion-gas flow and the launching tube was constructed for shipborne missile concentric canister launcher(CCL).

In order to study the influence of combustion-gas flow of some new antiaircraft rocket system to fire accuracy.

With some grown-up theories of launch combustion-gas dynamics, the study shows that the combustion-gas flow field structure of the subscale model test is similar to that of prototype test and keeps of linear geometric similarity, while the combustion-flow parameters is same as that of prototype test at the corresponding spot and the load o.

Numerical simulation on coupling heat-transfer of low oxygen gas flowing through PMMA tube;

From the study result, we can make conclusions as following: Appropriate clearance between inside and outside canisters is the crux of jet flow discharge.

The thesis simulates the missile launch p ro cess by the method of the computational fluid dynamics and the technology of dyn amic mesh, in order to study the jet flow during the missile launch and the rule s of missile movement.

The necessity of reasonable exhaust of combustible airflow is explained.

The mathematicalmodel used for describing the effect of sedimentary deposit on gas flowwas derived,and the effect of sedimentary deposit on gaseousflame height was investigated.