Aerodynamic Studies And Simulation Of Missiles Internal

Modern fighter planes must have a supersonic cruise and stealth performance. It is because of these characteristics determine the fighter carries missiles way to change from traditional outside hanging for internal buried type and it will be a new trend in weapons development flight.There are key aerodynamic problems of the missiles inside. Especially the cavity flow structure and characteristics is very complicated and it will affect missiles posture and separation track. Internal missile launch system must solve the problem is how to achieve a successful missile separation from the cavity.Therefore,to research geometrical parameters design and the missile safety separation is significant and important very much for the advanced aircrafts.Based on the numerical simulation method, the paper analyzes and simulates the cavity flow structure and characteristics, the aerodynamic characteristics of missile separation with the FLUENT software. The main contents are as follows:1. According to the reference data to determine the flow field computation model of internal missiles'cavity.2. Analysis the cavity flow characteristics and the main factors of affecting flow. The main research parameters is pressure coefficients cavity floor and analyzes the effect of geometrical parameters and flow parameters on cavity flow characteristics.3. Using a programme to solve the 6 degree-of-freedom dynamics equation and the kinematics equation of the missile was made and complied based on the flight dynamics theory. To use this code in the FLUENT and obtains the aerodynamic data.4. The dynamic mesh technique was used to obtain the parameters of the 6 DOF movement .Compared the separation trajectory and missile posture change at subsonic speed and supersonic speed. Finally, got missile safe separation conditions.