金属体积成形的无网格Galerkin模拟

为避免金属体积成形有限元法模拟中网格畸变造成网格重划和模拟精度降低,采用无网格法模拟金属体积成形.利用无网格法近似位移场,建立金属体积成形的无网格法连续性控制方程,采用罚函数法施加本征边界条件和体积不变条件,基于Markov变分原理推导了金属体积成形的无网格Galerkin求解列式.用数值计算法求解该列式,实现金属体积成形的无网格模拟.数值结果表明,无网格法能有效处理金属体积成形中出现的大变形,避免了网格畸变和重划,具有较高的模拟精度.     

线性装药聚能射流成型过程无网格MPM法数值模拟

线性装药聚能药柱起爆后能产生高速射流,为了研究线性装药聚能药柱的爆轰和射流的形成过程,该文应用无网格MPM法进行三维数值模拟,采用显式算法对爆轰产物和射流的速度、密度以及压力分布进行了数值计算。无网格MPM法与有限元和其他无网格法相比,能获得比较好的模拟结果,而且在数值计算效率方面具有优势。     

多层抗爆结构冲击响应无网格MPM法分析

在两层钢板中间夹衬泡沫铝等多孔材料构成多层复合结构被应用于抗爆、抗冲击的结构设计中,能够有效地降低冲击载荷对结构的破坏作用。为了研究多层复合结构的抗爆机理和变形破坏过程,使用材料非线性本构模型和无网格物质点法对在高速冲击载荷作用下各层材料的弹塑性大变形进行数值模拟。MPM法利用了欧拉法和拉格朗日法两者的优点,不仅与网格无关,也避免了有限元法中网格畸变,而且在对涉及多物质分界面的问题计算时,因MPM法的耦合条件自动满足,不需要考虑材料界面的变形和破坏,为计算多层抗爆结构的冲击响应建立了一个有效的无网格法数值模拟平台。     

现代数值模拟方法与工程实际应用

该文简要介绍现代数值模拟方法的发展状况和工程实际应用前景,从全局、多尺度、实时动态和强非线性等4个方面分析现代数值模拟方法的发展趋势和研发中存在的问题和难点。然后分别对基于网格法和无网格法的数值计算方法进行探讨,重点用有限元法、差分法和光滑粒子动力学方法对实际问题进行对比分析,探讨两种数值计算方法在工程应用中的进展和发展趋势。最终,评论目前数值模拟方法在工程实际问题中的推广应用意义和用户应用当中存在的共性问题。     

压电结构动力分析的无网格自然单元法

自然单元法是一种新兴的无网格数值计算方法,在本质边界条件的施加上较采用移动最小二乘法的无网格法具有明显的优势。将无网格自然单元法与精细积分法相结合,提出了压电结构动力响应分析的一条新途径。在空间域上采用自然单元法离散,并运用加权余量法推导了压电结构动力分析的离散控制方程。然后,采用精细积分法在时间域上进行求解。最后给出了数值算例,并验证了所提方法的有效性和正确性。     

圆柱形长杆超高速正碰撞薄板结构破碎效应

超高速碰撞多层板结构破碎效应研究对空间碎片防护及动能武器毁伤效应研究有着重要意义。采用ANSYS/AUTODYN程序的SPH方法,对超高速碰撞碎片云的形成过程进行了数值模拟,某典型时刻一次及二次碎片云形貌的数值模拟结果与实验结果吻合较好,验证了计算方法和模型参数的正确性。在此基础上采用数值模拟方法,对钨合金、轧制均质装甲(Rolled Homogeneous Armor,RHA)及LY12铝三种材料的圆柱形弹体超高速碰撞薄板的破碎规律进行了研究,基于量纲分析方法得出了弹体破碎长度随弹靶材料特性、弹靶尺寸及初始撞击速度变化的关系式。并研究了钨合金及RHA两种材料的长杆弹对八层RHA板结构的超高速碰撞效应。     

基于小波分析技术的高速撞击声发射源定位

针对在轨航天器遭受空间碎片撞击损伤的定位问题,利用二级轻气炮发射铝弹丸撞击铝板来模拟空间碎片对航天器结构的损伤;通过声发射传感器实时记录结构中的时域波形信号,结合板波的频散特性,分析了高速撞击穿孔损伤时波动在铝板中的传播模式.基于小波时频分析技术研究了高速撞击损伤的定位问题,分析了波速对定位精度的影响.结果表明,基于小波分析技术的高速撞击声发射源定位能够满足撞击损伤的定位要求,为解决航天器在轨遭受空间碎片撞击的损伤定位提供了一种新的方法.     

实验室聚能高速碎片生成装置设计与研究

地面超高速模拟实验是研究微小空间碎片撞击效应最经济和最有效的手段。目前的空间碎片生成装置安全性较低,无法在实验室内使用。为了在实验室模拟空间超高速碎片,研究设计了带防护壳体的占据式聚能装药空间碎片生成装置。根据数值模拟结果,加工制作了实验装置,通过试验测得截取的射流头部速度为10．52km／s、10．62km／s,与利用AUTODYN软件模拟得到的射流头部速度11．385km／8基本吻合。装置的保护外壳较为完整,实现了在实验室中模拟空间超高速碎片。     

扩展有限元法及与其它数值方法的联系

对扩展有限元方法(XFEM)的发展及其与其他数值方法的联系进行了综述。该文主要包括以下内容:首先对无网格法的发展背景和历程进行了介绍,并从近似位移场构造的角度对众多的无网格法进行了比较分析;从单位分解理论的形式出发,阐述了XFEM的特点及其与传统有限元法、无网格方法的联系;归纳了关于XFEM的应用研究及其自身理论发展的主要研究方向,并对XFEM的发展进行了展望。     

代数多重网格法在岩体力学有限元分析中的应用

代数多重网格法具有存贮量小、收敛精度高和计算时间少等优点,将代数多重网格方法引入到岩体力学有限元计算领域,论述了基于单元聚集和能量极小意义下适于岩体力学有限元求解的代数多重网格粗化策略与插值算子,并详细描述了相应的代数多重网格算法。数值试验表明:在岩体力学与工程问题的有限元数值计算中,代数多重网格求解法是高效的、适用的,较直接法和其他常用迭代方法具有明显的优越性。     

A single energy-based parameter to assess protection capability of debris shields

Protecting spacecraft structures against hypervelocity impacts (HVIs) of space debris, which may cause fatal damage to the spacecraft structures, has received wide attention. In this paper, the numerical simulation of hypervelocity solid–solid impacts is conducted and an energy-based parameter to assess protection capability of debris shields is proposed. To numerically simulate the hypervelocity impact phenomena, a two-dimensional improved smoothed particle hydrodynamics (SPH) method with new particle generation and particle merger techniques is used. The spatial and temporal distributions of the kinetic energy flux density of a debris cloud at the position of the upper surface of a pressure wall are calculated, and the correlation between the kinetic energy of the debris cloud and the deformation and fracture behavior of the pressure wall is discussed. Finally, based on the maximum value of the total kinetic energy of debris cloud per unit area at the position of the upper surface of a pressure wall, an energy-based parameter to assess protection capability of debris shields is proposed.     

椭球弹丸超高速撞击防护屏碎片云数值模拟

低地球轨道的各类航天器易受到微流星体及空间碎片的超高速撞击.本文采用AUTODYN软件进行了椭球弹丸超高速正撞击及斜撞击防护屏碎片云的数值模拟.给出了三维模拟的结果.研究了在相同质量的条件下,不同长径比椭球弹丸以不同速度和入射角撞击防护屏所产生碎片云的特性,并与球形弹丸撞击所应产生的碎片云特性进行了比较.结果表明:在相同的速度下,不同长径比椭球弹丸撞击的碎片云形状、质量分布和破碎程度是不同的,随撞击入射角的增加弹丸的破碎程度增大,滑弹碎片云的数量增加;随撞击速度的增加,弹丸的破碎程度也增加.     

Comparison study of MPM and SPH in modeling hypervelocity impact problems

Due to the high nonlinearities and extreme large deformation, the hypervelocity impact simulation is a challenging task for numerical methods. Meshfree particle methods, such as the smoothed particle hydrodynamics (SPH) and material point method (MPM), are promising for the simulation of hypervelocity impact problems. In this paper, the material point method is applied to the simulation of hypervelocity impact problems, and a three-dimensional MPM computer code, MPM3D, is developed. The Johnson–Cook material model and Mie–Grüneisen equation of state are implemented. Furthermore, the basic formulations of MPM are compared with SPH, and their performances are compared numerically by using MPM3D and LS-DYNA SPH module.     

Laboratory simulation of hypervelocity debris

A series of hypervelocity damage experiments were performed on spacecraft materials in order to simulate micro-size space debris traveling at 3 to 8 km/s. Two types of impact simulations were investigated: high-power pulsed laser and laser-launched micro-flyer plate. In the first case a laser was used to generate a high-pressure shock wave which propagated into the target by means of rapid ablation of the target surface. The second case used the same laser to accelerate micro-flyer plates at a target. The laser-ablation technique and the apparatus used to propel the micro-flyer plates were compatible with a space environmental chamber equipped with instrumentation capable of analyzing the vapor ejected from the sample. Data obtained from two separate damage effects were of interest in this study: the vapor blow-off produced by the impact and the mechanical damage to the target. The value of the data obtained from both simulation methods was evaluated in terms of likeness to actual space debris damage.

Data for this work were obtained from polysulfone resin and a graphite polysulfone composite. Polysulfone was selected because it was flown on the Long Duration Exposure Facility (LDEF) satellite which spent several years in low earth orbit and experienced many space debris impacts.

The chemistry of the vapor produced by the two simulation techniques was analyzed with a time of flight mass spectrometer (TOFMS) which measured changes in the vapor chemistry as a function of time after impact, obtained a velocity measurement of the vapor, and estimated surface temperature immediately after impact using dynamic gas equations. Samples of the vapor plume were also captured and examined by transmission electron microscopy (TEM).

The mechanical damage effects caused by the simulation methods on a graphit polysulfone composite and a polysulfone resin were studied. Impact craters were examined under optical and scanning electron microscopes (SEM). Based on the two damage effect criteria the micro-flyer method proved to be a useful way to simulate hypervelocity impact of space debris. The laser-ablation method however, had shortcomings and required drastic compromises in the set criteria.     

5A06铝合金单层板超高速撞击弹道极限分析

日益增长的空间碎片对在轨航天器的安全运行构成了严重威胁,毫米级空间碎片的防护已成为航天器结构设计必须考虑的问题之一.航天器的蒙皮是抵御空间碎片超高速撞击的最基本防护结构.采用数值仿真并结合试验验证的方法,对5 mm厚5A06铝合金单层板承受2A12铝合金球形弹丸正撞击下的弹道极限进行了研究.研究表明,在验证实验速度范围内,数值仿真结果与实验结果吻合良好;使用数值仿真对实验速度以上的区间进行拓展研究,获得了其弹道极限曲线和弹道极限方程;数值仿真和实验结果与已有经验方程对比表明,经验方程与具体材料的弹道极限有较大偏差,因此,应具体问题具体分析.     

弹丸超高速撞击半无限厚铝板数值模拟

微流星体及空间碎片的超高速撞击威胁着长寿命、大尺寸航天器的安全运行,导致其严重的损伤和灾难性的失效.撞击损伤特性研究是航天器防护设计的一个重要问题.本文采用AUTODYN软件的Lagrange法对半无限铝板的超高速斜撞击和与其具有相同法向速度的正撞击进行了模拟,给出了不同撞击角和不同法向速度下半无限厚铝板弹坑深度、宽度、长度的变化规律及多弹坑的形成过程,并与经验方程进行了比较分析.结果发现:随撞击角的增加,弹坑的深度和宽度减小,而弹坑的长度增加;随撞击速度的增加弹坑的直径和深度增加;在撞击角大于70度时出现多弹坑.     

A Lagrangian model for debris cloud dynamics simulation

A new modeling approach has been developed for computer simulation of hypervelocity impacts on multi-plate orbital debris shields. This approach links an Eulerian finite difference code for shield perforation calculations to a Lagrangian finite element code for debris cloud evolution simulations. Mixture theory is used to account for the presence of void space in the debris cloud.