包含运动界面的爆炸流场数值模拟方法及其应用
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摘要
凝聚态炸药的爆炸流场广泛存在于国防和国民经济建设的许多领域,典型的爆炸流场中存在三种不同形式的运动界面:炸药/爆轰产物与空气的界面、空气与可动物体的界面、爆轰产物/空气与水的界面,本文采用数值方法对这三类运动界面问题进行研究。
本文首先发展了一套动态混合网格的多组分流动数值模拟算法及软件,并以此作为研究工作的基础。该软件在动态混合网格上求解任意拉格朗日-欧拉形式的积分型控制方程,空间离散采用AUSM+-up和HLLC格式以及Venkatakrishnan限制器,时间离散采用Runge-Kutta格式,具有时空二阶精度,可以处理一维/二维/三维及球、柱、轴对称问题。计算方法不涉及特征矩阵的分解,适于计算各种形式的单流体/混合流体状态方程。在动网格方面,采用弹簧近似和网格重构相结合的方法模拟运动边界,采用虚拟网格通气技术解决运动物体从接触到分离过程中网格拓扑变化的难题。
针对炸药/爆轰产物与空气的界面,采用流体混合型方法,提出了一种炸药/爆轰产物/空气的流体混合模型。该模型中炸药及爆轰产物采用JWL状态方程,空气采用完全气体模型,在固相(炸药)与气相(爆轰产物、空气)间采用等压假设,且体积可加;气相间满足等温假设及分压定理。该模型中混合流体的状态方程无需迭代求解,计算效率较高。将该模型与点火-生长反应模型结合,可以有效处理炸药/爆轰产物与空气间界面的复杂运动问题。数值模拟了空气中球形TNT装药的爆轰问题,计算得到了清晰的波系结构及流体界面,爆炸近区的峰值超压与实验符合较好。研究了驱动管中爆轰波的传播过程,得到了典型的有限直径药柱中的二维爆轰波结构,获得了管壁及管底的压力加载曲线,为驱动管设计提供了重要参考;分析了不同的驱动管排布方式以及延长段长度对激波管性能的影响。
针对流体与可动物体间的动边界绕流问题,本文采用动网格跟踪运动边界,推导了ALE形式的流体控制方程,研究了动网格的几何守恒律,分析了不满足几何守恒律导致计算误差的原因,并提出了一种新的体积修正方法,可以消除网格运动引起的计算误差。将多体动力学求解方法与流场计算相耦合,解决了存在相互作用力的多个刚体的绕流的非定常求解方法。综合采用网格变形、网格重构、多体动力学耦合求解、虚拟网格通气等技术,仿真了内嵌式助推器的分离过程,发现了进气道整流罩打开后,进气道和燃烧室内存在衰减较慢的大幅压力振荡;助推器头部通过前体飞行器的喉部时,助推器所受的法向力剧烈振荡,给分离安全性带来一定影响。模拟了爆炸波驱动下卡车的运动,验证了本文方法对于含有运动物体的爆炸问题的模拟能力。
针对水下爆炸中的水-气界面问题,本文采用ALE方法追踪流体界面,并将改进的虚拟流体方法应用于界面计算中。对气-气、气-水、爆轰产物-水等多个Riemann问题的模拟表明,相对于Euler型方法以及原始的ALE界面追踪方法,改进后的ALE方法具有更小的界面耗散以及更高的计算精度,界面压力无振荡。模拟了一维和二维水下爆炸问题,结果反映出了激波与水-气界面的相互作用,得到的气泡最大半径和首次脉动周期与实验值符合较好;二维水下爆炸中的气泡界面清晰,且不存在物理量的虚假振荡。
最终,通过本文的工作,形成了模拟空中爆炸和水下爆炸的数值计算软件,可用于计算炸药爆轰、爆炸近区流场、爆炸波与刚性物体的相互作用,可以处理气-气、气-固、气-液等多种流体界面。软件具有较高的精度和较好的鲁棒性、通用性,并在工程实际问题中得到了应用。
Explosion flow field of condensed explosives widely exists in the field of defense and economic contribution, there are three forms of moving interface in typical explosion flow field: interface between explosives/detonation products and air; moving boundary between air and movable objects; interface between detonation products/air and water. These three moving interface problems are numerically investigated in this thesis.
A numerical simulation algorithm and software for multi-species flow using dynamic hybrid grids is developed, which is the basis of this thesis's research. Integral governing equations in arbitrary Lagrangian Eulerian(ALE) form are solved on dynamic hybrid grid in this software, in which AUSM+-up and HLLC schemes combined with Venkatakrishnan’s limiter are used in spatial discretization and multi-stage Runge-Kutta scheme in temporal discretization. The ultimate method has 2-order accuracy both in spatial and temporal direction, and it could hold one/two/three dimensional and spherical/cylindrical/axial symmetry problems. This algorithm is free of characteristic matrix decomposition, accordingly it's suitable for singe/multi-species flows with any form of state equations. The mesh movement strategy combined of deformation and remeshing is used, and a kind of "virtual mesh ventilation method" is used to resolve the problem when multi bodies move from contact to separation and the mesh topology changes.
Aimed at the interface between explosive/detonation product and air, a new mixed fluid model of explosive, detonation product and air is proposed within fluid-mixture type algorithm. In this model, JWL and perfect gas state equations are used for explosive/products and air separately, isobaric assumption is made between solid phase(explosives) and gas phase(detonation products and air), and iso-temperature assumption and partial pressure law is used within gas phases. The state equations of mixed fluid in this model can be solved without iteration, so a high computation efficiency is gained. Combined with growth and ignition reaction model, complex flow problems involving moving interface between explosive/detonation products and air can be effectively solved in this model. Detonation of spherical TNT explosives in air is simulated, fluid structure and interface are captured clearly, and the near-field peak overpressure accords well with experimental results. The spread of detonation wave in driven tube is researched, a typical two dimensional detonation wave structure in finite diameter explosives is achieved, and the time history of overpressure on the side and bottom of the driven tube is gained, which affords an important reference to the design of driven tube. Influence of different distribution forms of driven tubes and length of extended section to the performance of shock tube is also analyzed.
Aimed at the moving boundary problems between fluid and movable objects, dynamic grid method is used to track moving boundaries, the ALE form of governing equations is derived, and the geometrical conservation law(GCL) is studied. The reason of introducing computation errors when violating GCL is analyzed, and a new volume correction method is proposed, which could eliminate computation errors arised from moving grid. Coupled multi-body dynamics with fluid calculation, a unsteady computation method for the flow field of multi-body with interactional forces is established. Integrated with grid deforming, remeshing, multi-body dynamics and virtual mesh ventilation method, the embedded booster's separation process is simulated, and it's found that pressure oscillation will occur in the inlet and combustor after the open of inlet cover and it's hard to attenuate. When the booster's head passes through the forebody's throat, normal forces on the booster oscillate severely, which may influence the safety of separation. The movement of a truck driven by blast wave is simulated, which validates the simulation ability to the explosion problems involving moving objects.
Aimed at the gas-water interface problem in underwater explosion, ALE formulation is used to trace fluid interface, and the modified ghost fluid method is introduced to the interface computation. Through the calculation of several Riemann problems such as gas-gas, gas-water, detonation product-water Riemann problems, this modified ALE method is proved of smaller interface dissipation and higher computation accuracy than Euler and original ALE method. In the simulation of one and two dimensional underwater explosion, interactions between shock wave and gas-water interface is captured, and the maximum radius and first period of air bubble accord well with experimental results. The bubble's interface is clear, without nonphysical spurious oscillations.
Finally, a numerical computation software of simulating air blast and underwater explosion is established in this thesis, it could be used to compute detonation of condensed explosives, near-field blast, interaction of blast wave and rigid body and handle multi-fluid interface including gas-gas, gas-solid, gas-liquid interfaces. This software is accuracy, robust and universal, it has been applied in practical engineering problems.
本文首先发展了一套动态混合网格的多组分流动数值模拟算法及软件,并以此作为研究工作的基础。该软件在动态混合网格上求解任意拉格朗日-欧拉形式的积分型控制方程,空间离散采用AUSM+-up和HLLC格式以及Venkatakrishnan限制器,时间离散采用Runge-Kutta格式,具有时空二阶精度,可以处理一维/二维/三维及球、柱、轴对称问题。计算方法不涉及特征矩阵的分解,适于计算各种形式的单流体/混合流体状态方程。在动网格方面,采用弹簧近似和网格重构相结合的方法模拟运动边界,采用虚拟网格通气技术解决运动物体从接触到分离过程中网格拓扑变化的难题。
针对炸药/爆轰产物与空气的界面,采用流体混合型方法,提出了一种炸药/爆轰产物/空气的流体混合模型。该模型中炸药及爆轰产物采用JWL状态方程,空气采用完全气体模型,在固相(炸药)与气相(爆轰产物、空气)间采用等压假设,且体积可加;气相间满足等温假设及分压定理。该模型中混合流体的状态方程无需迭代求解,计算效率较高。将该模型与点火-生长反应模型结合,可以有效处理炸药/爆轰产物与空气间界面的复杂运动问题。数值模拟了空气中球形TNT装药的爆轰问题,计算得到了清晰的波系结构及流体界面,爆炸近区的峰值超压与实验符合较好。研究了驱动管中爆轰波的传播过程,得到了典型的有限直径药柱中的二维爆轰波结构,获得了管壁及管底的压力加载曲线,为驱动管设计提供了重要参考;分析了不同的驱动管排布方式以及延长段长度对激波管性能的影响。
针对流体与可动物体间的动边界绕流问题,本文采用动网格跟踪运动边界,推导了ALE形式的流体控制方程,研究了动网格的几何守恒律,分析了不满足几何守恒律导致计算误差的原因,并提出了一种新的体积修正方法,可以消除网格运动引起的计算误差。将多体动力学求解方法与流场计算相耦合,解决了存在相互作用力的多个刚体的绕流的非定常求解方法。综合采用网格变形、网格重构、多体动力学耦合求解、虚拟网格通气等技术,仿真了内嵌式助推器的分离过程,发现了进气道整流罩打开后,进气道和燃烧室内存在衰减较慢的大幅压力振荡;助推器头部通过前体飞行器的喉部时,助推器所受的法向力剧烈振荡,给分离安全性带来一定影响。模拟了爆炸波驱动下卡车的运动,验证了本文方法对于含有运动物体的爆炸问题的模拟能力。
针对水下爆炸中的水-气界面问题,本文采用ALE方法追踪流体界面,并将改进的虚拟流体方法应用于界面计算中。对气-气、气-水、爆轰产物-水等多个Riemann问题的模拟表明,相对于Euler型方法以及原始的ALE界面追踪方法,改进后的ALE方法具有更小的界面耗散以及更高的计算精度,界面压力无振荡。模拟了一维和二维水下爆炸问题,结果反映出了激波与水-气界面的相互作用,得到的气泡最大半径和首次脉动周期与实验值符合较好;二维水下爆炸中的气泡界面清晰,且不存在物理量的虚假振荡。
最终,通过本文的工作,形成了模拟空中爆炸和水下爆炸的数值计算软件,可用于计算炸药爆轰、爆炸近区流场、爆炸波与刚性物体的相互作用,可以处理气-气、气-固、气-液等多种流体界面。软件具有较高的精度和较好的鲁棒性、通用性,并在工程实际问题中得到了应用。
Explosion flow field of condensed explosives widely exists in the field of defense and economic contribution, there are three forms of moving interface in typical explosion flow field: interface between explosives/detonation products and air; moving boundary between air and movable objects; interface between detonation products/air and water. These three moving interface problems are numerically investigated in this thesis.
A numerical simulation algorithm and software for multi-species flow using dynamic hybrid grids is developed, which is the basis of this thesis's research. Integral governing equations in arbitrary Lagrangian Eulerian(ALE) form are solved on dynamic hybrid grid in this software, in which AUSM+-up and HLLC schemes combined with Venkatakrishnan’s limiter are used in spatial discretization and multi-stage Runge-Kutta scheme in temporal discretization. The ultimate method has 2-order accuracy both in spatial and temporal direction, and it could hold one/two/three dimensional and spherical/cylindrical/axial symmetry problems. This algorithm is free of characteristic matrix decomposition, accordingly it's suitable for singe/multi-species flows with any form of state equations. The mesh movement strategy combined of deformation and remeshing is used, and a kind of "virtual mesh ventilation method" is used to resolve the problem when multi bodies move from contact to separation and the mesh topology changes.
Aimed at the interface between explosive/detonation product and air, a new mixed fluid model of explosive, detonation product and air is proposed within fluid-mixture type algorithm. In this model, JWL and perfect gas state equations are used for explosive/products and air separately, isobaric assumption is made between solid phase(explosives) and gas phase(detonation products and air), and iso-temperature assumption and partial pressure law is used within gas phases. The state equations of mixed fluid in this model can be solved without iteration, so a high computation efficiency is gained. Combined with growth and ignition reaction model, complex flow problems involving moving interface between explosive/detonation products and air can be effectively solved in this model. Detonation of spherical TNT explosives in air is simulated, fluid structure and interface are captured clearly, and the near-field peak overpressure accords well with experimental results. The spread of detonation wave in driven tube is researched, a typical two dimensional detonation wave structure in finite diameter explosives is achieved, and the time history of overpressure on the side and bottom of the driven tube is gained, which affords an important reference to the design of driven tube. Influence of different distribution forms of driven tubes and length of extended section to the performance of shock tube is also analyzed.
Aimed at the moving boundary problems between fluid and movable objects, dynamic grid method is used to track moving boundaries, the ALE form of governing equations is derived, and the geometrical conservation law(GCL) is studied. The reason of introducing computation errors when violating GCL is analyzed, and a new volume correction method is proposed, which could eliminate computation errors arised from moving grid. Coupled multi-body dynamics with fluid calculation, a unsteady computation method for the flow field of multi-body with interactional forces is established. Integrated with grid deforming, remeshing, multi-body dynamics and virtual mesh ventilation method, the embedded booster's separation process is simulated, and it's found that pressure oscillation will occur in the inlet and combustor after the open of inlet cover and it's hard to attenuate. When the booster's head passes through the forebody's throat, normal forces on the booster oscillate severely, which may influence the safety of separation. The movement of a truck driven by blast wave is simulated, which validates the simulation ability to the explosion problems involving moving objects.
Aimed at the gas-water interface problem in underwater explosion, ALE formulation is used to trace fluid interface, and the modified ghost fluid method is introduced to the interface computation. Through the calculation of several Riemann problems such as gas-gas, gas-water, detonation product-water Riemann problems, this modified ALE method is proved of smaller interface dissipation and higher computation accuracy than Euler and original ALE method. In the simulation of one and two dimensional underwater explosion, interactions between shock wave and gas-water interface is captured, and the maximum radius and first period of air bubble accord well with experimental results. The bubble's interface is clear, without nonphysical spurious oscillations.
Finally, a numerical computation software of simulating air blast and underwater explosion is established in this thesis, it could be used to compute detonation of condensed explosives, near-field blast, interaction of blast wave and rigid body and handle multi-fluid interface including gas-gas, gas-solid, gas-liquid interfaces. This software is accuracy, robust and universal, it has been applied in practical engineering problems.
引文
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