内埋弹舱舱门开启和武器分离过程数值模拟研究
发布时间：2018-07-22 10:06
【摘要】：武器内埋式装载是新一代战斗机实现超声速巡航和雷达隐身的重要技术,武器内埋技术涉及很多关键的气动性问题。在军事作战中,武器舱门需快速开启,导弹迅速地完成与弹舱的分离,强耦合流动会对外部流场产生强烈干扰,加剧舱内流场的非定常效应,出现一系列复杂的物理现象：如流动分离与再附着、旋涡的产生／发展／脱落、旋涡／剪切层相互干扰；特别在超声速条件下,还存在波系干扰、激波／剪切层及激波／边界层的相互作用。同时,强耦合流动会增加舱门及导弹表面的气动载荷,出现流致振动,引发结构疲劳及损伤,严重危及飞行安全。因此,有必要开展舱门开启和导弹分离所引发的耦合流场动态特性研究。 本研究采用数值计算的方法来模拟舱门开启和导弹分离的动态过程。通过有限体积法求解三维、非定常、可压缩N-S方程,运用非结构网格和基于局部重构的动态网格技术,分别对亚、跨、超声速下的舱门开启过程进行数值模拟研究。根据不同来流马赫数时的动态计算结果来分析流场中旋涡、剪切层、边界层、波系等物理现象的产生和发展机理,以及相互之间复杂干扰作用。并在此基础上进一步探究来流攻角和内埋导弹干扰分别对舱内／外流场非定常现象和舱门气动荷载产生的影响。 采用同样的数值方法,通过耦合求解控制方程和刚体六自由度(6DOF)方程,对超声速下(来流马赫数分别为1.5和2.0)的导弹分离动态过程进行数值模拟研究。依据瞬态流线图和流场云图,对超声速下的物理现象进行详细的分析；同时,对不同来流马赫数下舱底压力分布、导弹气动载荷作出对比分析,分别给出以上数据随导弹分离过程的变化趋势,揭示了飞行马赫数对流场动态特性及导弹姿态的影响。 模拟结果显示：舱门开启和导弹分离的动态过程,会引发舱内旋涡的非定常发展和旋涡／剪切层的相互干扰,在弹舱前缘、导弹上表面产生分离流动；跨、超声速流场中出现了激波相交、激波／膨胀波相交、激波／剪切层干扰和激波／边界层干扰等复杂物理现象；同时,舱门开启和导弹分离运动诱使舱内流动形态发生改变,引起舱底压力分布的变化,舱门和导弹的气动载荷也产生非定常效应。 本研究的数值模拟结果在一定程度上丰富了内埋武器技术的研究,为内埋武器舱的结构设计、导弹安全分离等工程实际问题提供了参考和依据。
[Abstract]:Weapon embedded loading is an important technology for the new generation fighter to realize supersonic cruise and radar stealth. The embedded weapon technology involves many key aerodynamic problems. In military operations, the weapon hatch needs to be opened quickly, and the missile is quickly separated from the projectile. The strong coupling flow will cause strong interference to the external flow field and aggravate the unsteady effect of the flow field in the cabin. A series of complex physical phenomena appear, such as separation and reattachment of flow, generation / development / shedding of vortex, interaction of vortex / shear layer, and interference of wave system, especially in supersonic condition. The interaction of shock wave / shear layer and shock wave / boundary layer. At the same time, the strong coupling flow will increase the aerodynamic load on the door and missile surface, cause fluid-induced vibration, cause structural fatigue and damage, and seriously endanger flight safety. Therefore, it is necessary to study the dynamic characteristics of coupled flow field caused by door opening and missile separation. In this study, a numerical method is used to simulate the dynamic process of door opening and missile separation. The three-dimensional, unsteady and compressible N-S equations are solved by finite volume method. The unstructured meshes and the dynamic meshes based on local reconstruction are used to simulate the opening process of the hatch at sub-, transonic and supersonic velocities, respectively. According to the dynamic calculation results of different incoming Mach numbers, the generation and development mechanism of vortex, shear layer, boundary layer and wave system in the flow field are analyzed, as well as the complex interaction between them. On this basis, the influences of angle of attack and missile interference on the unsteady phenomena and aerodynamic loads on the cabin / outflow field are further investigated. Using the same numerical method, the dynamic process of missile separation with supersonic velocity (Mach number 1.5 and Mach number 2.0) is numerically simulated by coupling solving control equation and 6-DOF equation of rigid body. According to the transient streamline diagram and the flow field cloud diagram, the physical phenomena under supersonic velocity are analyzed in detail, at the same time, the distribution of bilge pressure and the aerodynamic load of missile under different flow Mach numbers are compared and analyzed. The variation trend of the above data with the missile separation process is given, and the dynamic characteristics of the flight Mach number flow field and the influence of the missile attitude are revealed. The simulation results show that the dynamic process of hatch opening and missile separation will lead to unsteady development of vortex in cabin and mutual interference of vortex / shear layer, and separate flow on the upper surface of missile at the front edge of missile. Complex physical phenomena such as shock wave intersection, shock / expansion wave intersection, shock / shear layer interference and shock / boundary layer interference occur in supersonic flow field. The aerodynamic load of the hatch and missile also produces unsteady effect. The numerical simulation results of this study enrich the research of the embedded weapon technology to a certain extent and provide reference and basis for the structural design of the buried weapon cabin and the missile safety separation and other engineering practical problems.
【学位授予单位】：北京交通大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V271.4
[Abstract]:Weapon embedded loading is an important technology for the new generation fighter to realize supersonic cruise and radar stealth. The embedded weapon technology involves many key aerodynamic problems. In military operations, the weapon hatch needs to be opened quickly, and the missile is quickly separated from the projectile. The strong coupling flow will cause strong interference to the external flow field and aggravate the unsteady effect of the flow field in the cabin. A series of complex physical phenomena appear, such as separation and reattachment of flow, generation / development / shedding of vortex, interaction of vortex / shear layer, and interference of wave system, especially in supersonic condition. The interaction of shock wave / shear layer and shock wave / boundary layer. At the same time, the strong coupling flow will increase the aerodynamic load on the door and missile surface, cause fluid-induced vibration, cause structural fatigue and damage, and seriously endanger flight safety. Therefore, it is necessary to study the dynamic characteristics of coupled flow field caused by door opening and missile separation. In this study, a numerical method is used to simulate the dynamic process of door opening and missile separation. The three-dimensional, unsteady and compressible N-S equations are solved by finite volume method. The unstructured meshes and the dynamic meshes based on local reconstruction are used to simulate the opening process of the hatch at sub-, transonic and supersonic velocities, respectively. According to the dynamic calculation results of different incoming Mach numbers, the generation and development mechanism of vortex, shear layer, boundary layer and wave system in the flow field are analyzed, as well as the complex interaction between them. On this basis, the influences of angle of attack and missile interference on the unsteady phenomena and aerodynamic loads on the cabin / outflow field are further investigated. Using the same numerical method, the dynamic process of missile separation with supersonic velocity (Mach number 1.5 and Mach number 2.0) is numerically simulated by coupling solving control equation and 6-DOF equation of rigid body. According to the transient streamline diagram and the flow field cloud diagram, the physical phenomena under supersonic velocity are analyzed in detail, at the same time, the distribution of bilge pressure and the aerodynamic load of missile under different flow Mach numbers are compared and analyzed. The variation trend of the above data with the missile separation process is given, and the dynamic characteristics of the flight Mach number flow field and the influence of the missile attitude are revealed. The simulation results show that the dynamic process of hatch opening and missile separation will lead to unsteady development of vortex in cabin and mutual interference of vortex / shear layer, and separate flow on the upper surface of missile at the front edge of missile. Complex physical phenomena such as shock wave intersection, shock / expansion wave intersection, shock / shear layer interference and shock / boundary layer interference occur in supersonic flow field. The aerodynamic load of the hatch and missile also produces unsteady effect. The numerical simulation results of this study enrich the research of the embedded weapon technology to a certain extent and provide reference and basis for the structural design of the buried weapon cabin and the missile safety separation and other engineering practical problems.
【学位授予单位】：北京交通大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V271.4
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