临近空间高超声速飞行器武器投放方案数值模拟  

Numerical simulation of weapon delivery schemes for hypersonic vehicles in near space

作　　者：孙佳濛 左光 徐艺哲 杜若凡 崔玉红[1] SUN Jiameng;ZUO Guang;XU Yizhe;DU Ruofan;CUI Yuhong(School of Mechanical Engineering,Tianjin University,Tianjin 300072,China;Land Space Technology Corporation Ltd,Beijing 100176,China;Qian Xuesen Laboratory of Space Technology,China Academy of Space Technology,Beijing 100094,China)

机构地区：[1]天津大学机械工程学院,天津300072 [2]蓝箭航天空间科技股份有限公司,北京100176 [3]中国空间技术研究院钱学森空间技术实验室,北京100094

出　　处：《航空学报》2023年第13期22-37,共16页Acta Aeronautica et Astronautica Sinica

基　　金：CAST创新基金(CAST-2020-02-04)。

摘　　要：针对马赫数4~10的临近空间高超声速飞行器武器投放方案开展数值研究,提出导弹内置投放、舱门开启导弹外挂投放、导弹直接外挂投放、导弹后置滑轨投放4种方案。研究采用基于密度的求解器,采用剪切应力输运(SST)k-ω湍流模型和二阶迎风的通量格式,同时采用非结构动网格技术,采用计算流体力学(CFD)耦合六自由度(DOF)方程的方法模拟导弹的投放过程。重点研究了4种投放方案的流场特征、马赫数对导弹投放姿态的影响,攻角对导弹投放姿态的影响,以及不同投放方案的对比。结果表明:舱门开启导弹外挂投放方案和导弹直接外挂投放方案在马赫数4~10时均能以很好的姿态进行投放;导弹内置投放方案在马赫数8、10的超高声速下无法正常投放;导弹后置滑轨投放方案在各马赫数下均不能正常投放;3°的飞行器初始攻角会有效改善导弹投放过程。导弹直接外挂投放方案成功率最高,并且气动干扰最小,是一种较为可行的临近空间高超声速武器投放方案。临近空间高超声速飞行器武器投放研究具有重要实用价值,计算方法和计算模型的尝试对后续开展临近空间的数值研究提供技术支持和参考。Numerical research was conducted on the near space hypersonic vehicle missile separation scheme with Mach number 4-10.We proposed four separation schemes including the missile built-in,the hatch opened with mis⁃sile plug-in,the direct missile plug-in model,and the missile placed behind model.The density-based solver,the Shear Stress Transport(SST)k-ωturbulence model,the second order upwind flux format,as well as the unstructured dynamic grid technology are adopted to simulate the missile launch process with the Computational Fluid Dynamics(CFD)coupled Six Degrees of Freedom(6DOF)equation method.The flow field characteristics of four separation schemes,the influence of the Mach number on the missile separation attitude,the effect of the angle of attack on the missile separation attitude,and comparison of different separation schemes are studied.The results show that both the hatch opened with missile plug-in model and the direct missile plug-in model can be launched with a reasonable at⁃titude in the range of Mach number 4-10,and the missile built-in model cannot be launched normally at high Mach numbers of 8 and 10,while at none of the Mach numbers can the missile placed behind model be launched normally.The initial attack angle of the aircraft of 3°will effectively improve the missile separation process.The direct missile plug-in model has the highest success rate and the least aerodynamic interference.It is therefore a relatively feasible near space hypersonic missile separation scheme.This research has an important practical value,and the attempt of the calculation method and calculation model provides technical support and reference for the subsequent numerical research on near space.

关 键 词：临近空间 高超声速 飞行器 武器投放 数值模拟 

分 类 号：V411[航空宇航科学与技术—航空宇航推进理论与工程]