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为准确建立载机复杂尾流场影响下火箭的气动模型,综合运用空气动力学和计算流体力学的基本理论,提出了一种基于动力学仿真和数值仿真的方法,通过建立载机和火箭的全尺寸实体模型,并根据混合网格和拼接网格的基本原理提出了一种针对复杂尾流场影响下火箭计算模型生成的新方法,并利用计算流体力学进行仿真计算,最终得到复杂尾流场中火箭的气动特性。针对无载机尾流扰动的情况进行对比分析,结果表明改进方法较为准确的建立了复杂尾流场影响下火箭的气动模型,从而为精确仿真内装式空射火箭的分离过程提供了重要的数据支撑。
In order to accurately establish the aerodynamic model of a rocket under the complex wake flow field of a carrier, a dynamic simulation and numerical simulation method based on the basic theories of aerodynamics and computational fluid dynamics are put forward. Through the establishment of aero-engine and rocket Full-scale solid model. According to the basic principle of hybrid mesh and splicing mesh, a new method for generating rocket calculation model under the influence of complex wake flow field is proposed. The computational fluid dynamics is used to simulate and calculate complex wakes Aerodynamic characteristics of the rocket in the field. The results show that the improved method can accurately establish the aerodynamic model of the rocket under complex wake flow field and provide important data for the accurate simulation of the separation process of the built-in air-launched rocket support.