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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。
The study compared the missile’s motion characteristics and the effect of aircraft-to-air aerodynamic perturbation when the missile’s jet was considered in launching airborne missiles. The simulation of the missile’s motion is realized by the dynamic structure nested grid technique. The flow field information is obtained by solving the three-dimensional unsteady Euler equation combined with the six-degree-of-freedom kinematic equation of the rigid body. Missile thrust is calculated from the jet of the engine combustor; thrust is achieved by giving the unsteady force directly at the missile’s tail, irrespective of the jet effect. This method is used to simulate the launching process of a missile based on the Global Hawk UAV platform and obtain detailed flow field information including missile attitude, motion trajectory and machine-bomb interference characteristics. The analysis results show that during the launch, the missile jet flow greatly changes the flow field structure of the wing near the pylon, which has a significant impact on the missile movement characteristics and the mechanical-aero aerodynamic disturbance characteristics. The research results have reference value for airborne missile launch design.