研究比较了机载导弹发射时是否考虑导弹尾喷流情况下导弹运动特性及机-弹气动干扰影响。通过动态结构嵌套网格技术实现了导弹运动的模拟,结合刚体六自由度运动方程求解三维非定常Euler方程得到流场信息。导弹推力由发动机燃烧室喷流计算得到;当不考虑喷流效应时,推力通过直接在导弹尾部给定非定常作用力实现。应用此方法模拟了基于类"全球鹰"无人机(UAV)平台的导弹发射过程,获得了详细的包括导弹运动姿态、运动轨迹和机-弹干扰特性等在内的流场信息。分析结果表明,在投放过程中,导弹尾喷流极大地改变了挂架附近机翼的流场结构,对导弹运动特性和机-弹气动干扰特性影响显著。该研究结果对机载导弹发射设计具有参考价值。
This paper simulates a missile launch process by the computational fluid dynamics (CFD) method, through which the aerodynamic interference and rules of missile movement with and without consideration of the plume field are studied. 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 capture the time-dependent interference between the stationary and moving boundaries. Two thruster models are developed to account for the influence of thruster rockets on the flowfield. One model applies an equivalent massflux at the rocket nozzle exit in order to simulate the rocket plume effects. For the second model, the thrust vector exerted by the rockets is attached to the missile body for the duration of the run. And the paper presents the results obtained for a time-accurate missile launching from the quasi-"Global Hawk" unmanned aerial vehicle (UAV) by the developed numerical methods. All major trends of the trajectory are captured, including the displacements, angular orientations, pressure coefficient distribution on the plane in the captive position, and force coefficients histories during separation, which are then used for comparison. The results show that the effect of the plume field is significant on the missile dynamic characteristics and aerodynamic interference. The simulations may provide a tool for design verification and risk mitigation for the missile launch procedure.
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