Numerical Simulation Of Uav Airborne Missile Launching From Rail-catapult Integrated Launcher

As information weapon equipment, the UAV is playing a more and more important role in modern wars. One of the most important development directions of the UAV is setting reconnaissance, surveillance and attack capabilities in one. The only way to attack targets of UAVs is mounting precision guided weapons. Missiles launching from UAV belongs to one of the multi-body separation problems. At the initial stage of separation, there is significant aerodynamic interference between the missile and the UAV. The tail jet generated by the missile ignition has a very serious interference on the aerodynamic characteristics of the UAV, which affects the flight stability of the aircraft. Therefore, researching the machine mounted missile produced gas dynamic interference problem has an important significance to the UAV flight safety and missile safety separation.In this thesis, we focus on the influence of tail jet on the aerodynamic characteristics of the UAV when the missile launching from the rail-catapult integrated launcher.Based on computational fluid dynamics, CFD software Fluent as a platform, combined with two dimensional unstructured dynamic grid technologies, simulated the process of integrated launch of airborne missile.In this paper, CATIA is used to establish a simplified model, and the grid is divided into the unstructured grid generation technique.Considered the relative motion between the missile and the UAV, the dynamic mesh technology of Fluent is used to update the large deformation grid automatically.Considered the relative motion between the missile and the UAV, the dynamic mesh technology of Fluent is used to update the large deformation grid automatically. The grid fixed with the wing is at rest. The grid fixed with missile would move with it. Properties and boundary conditions of the flow field were defined in Fluent, and the change of the lift and drag coefficient of the wing was monitored.Through the simulation of the rail-catapult integrated launching process of the airborne missile, we can find that using rail-catapult integrated launcher will reduce the aerodynamic effect on the wing caused by the missile tail jet and the aerodynamic interference to the wing at different time after ejection were reduced to a certain extent.At the same time, the launching process of the missile was simulated under different flight speed. The influence of tail jet flow on the aerodynamic effect of the wing is different under different Maher number. The simulation results can provide some reference for the research of the integrated launching device of the unmanned aerial vehicle missile.