基于察/打一体无人机平台的导弹发射模拟

Numerical Simulation of Missile Launching from the R/S UAV

为研究机载导弹发射过程中载机、导弹之间存在的气动干扰特性和导弹运动规律,采用计算流体力学方法对导弹发射过程进行了数值模拟。结合刚体六自由度运动方程,将运动嵌套网格技术应用于机载导弹发射问题中,通过求解三维非定常Euler方程得到流场信息。应用此方法成功模拟了基于察/打一体无人机平台的导弹发射过程,获得了详细的导弹运动速度、运动轨迹和受力情况等丰富的流场信息。算例表明:运动嵌套网格技术处理具有复杂外形、较大相对位移运动问题的能力,发动机推力的影响,载机、导弹之间的气动干扰影响较小。采用计算流体力学方法和运动嵌套网格技术可为研究导弹发射过程提供参考和依据。

The thesis simulates the missile launch process by the method of the computational fluid dynamics （CFD） , in order to study the aerodynamic interference and the rules of missile movement. A moving chimera grid approach is used coupled with an unsteady Euler flow solver, and a 6 - DOF model is fully integrated into the CFD solution procedure to determine the body dynamics. And the paper presents the results obtained for a time - accurate missile launching from the Pt/S UAV by the developed numerical methods. Major trends of the separation are captured. As a result, the application shows the validity of moving chimera grid method, the use of the method of the CFD and the technology of moving chimera grid give a reference and gist to the study of the process of missile launch. The computation result shows that the effect of aerodynamic interference due to the thrust is negligible.