多个裁剪参数曲面的有限元混合网格剖分法

根据冲压模具形状特点,对由CAD/CAM系统建立的冲压模具的多裁剪参数曲面数学模型,提出了一种符合冲压成形有限元分析需要的三角形和四边形混合网格剖分算法.按几何离散控制参数即最长边、最短边、距离误差和角度误差,将多裁剪参数曲面离散为多边形集.利用曲面曲线查找裁剪参数曲面相邻关系,建立B-Rep表示的曲面几何模型,并更新多边形集.然后由多边形集得到三角形和四边形混合网格,结果网格单元是相容的,在相邻裁剪参数曲面边界处无裂缝和覆盖.      

低RCS齿形挂架参数选择研究

常规飞机的机翼与外挂架构成90°的二面角,成为飞机侧向的重要散射源.为求在不改变机体结构的前提下减缩飞机侧向RCS,采用齿形方案改变了挂架外形,消除了直角二面角结构,削弱了耦合效应.计算结果显示,改形的国产某型战斗机的机翼-外挂架结构的RCS在侧向重点姿态角内降低了9~13dBsm,证明了齿形改形方案能明显改善飞机侧向的耦合散射效应.在计算过程中使用了射线追踪法.      

预期违约制度之比较剖析--兼论《合同法》第94条第2款和第108条之规定

预期违约在现代民法中占有重要地位。本文通过对预期违约制度的历史沿革及其比较法考察，将预期违约制度与不安抗辩权进行比较，进而对预期违约制度的构成要件和补救措施等作了系统分析和探讨，旨在对我国合同立法有所启示。     

Finite Element Modelling of Failure of a Multi-Material Target due to High Velocity Space Debris Impacts

Lagrangian finite element methods have been used extensively in the past to study the non-linear transient behaviour of materials, ranging from crash tests of cars to simulating bird strikes on planes. However, as this type of space discretisation does not allow for motion of the material through the mesh when modelling extremely large deformations, the mesh becomes highly distorted. This paper describes some limitations and applicability of this type of analysis for high velocity impacts. A method for dealing with this problem by the erosion of elements is proposed, where the main driver is the definition of element failure strains. Results were compared with empirical perforation results and were found to be in good agreement. The results were then used to simulate high velocity impacts upon a multi-layered aluminium target in order to predict a ballistic limit curve. LS-DYNA3D was used as the FE solver for all simulations. Meshes were generated using Truegrid.     

万能工具显微镜智能化改造

以国产新添数显万能工具显微镜为例，介绍了万能工具显微镜智能化改造的基本原理，两维测量软件的主要功能以及通用几何元素及其形位误差的数学算法，探讨了保证检测揩度的若干措施，并给出了U1、U2校准比对结果。     

清镇陨石（EH3）中陨硫钙石的REE微量元素及成因意义

本文运用INAA分析了14个清镇陨石中陨硫钙石单矿物颗粒的难熔元素(La、Ce、Sm、Eu、Yb、Lu、Ca、Sc、Hf和Th),挥发性元素(Na、Cr、Zn、Se、Br等)和亲铁元素(Fe、Ni、Co、Ir、Au、As)含量。结果表明陨硫钙石高度富集难熔亲石元素,是顽火辉石陨石中REE的主要载体,携带了约80％的全岩REE总量。相对于HREE,LREE有更大的富集程度,而且早期凝聚的颗粒较晚期凝聚的颗粒更富集REE,同时陨硫钙石富集挥发性元素Se、Br等。清镇陨硫钙石的微量元素特征揭示了它来自于太阳星云的高温凝聚特征和成因。     

Precise output loads control of load-diffusion components with topology optimization

The purpose of this paper is to present a novel topology optimization approach to control precisely the output loads under static loads and harmonic excitations. We introduce the Artificial Bar Element (ABE) at the designated output positions, where the output loads are equivalently measured and constrained with the nodal displacements of ABE. Optimization model is then formulated considering the output load constraints as well as the minimization of strain energy and dynamic displacement responses respectively under the static and dynamic conditions. The influences of the ABEs stiffness, different material usages of the design domain, widths of the output loads constraint intervals and variation ratios of output loads are discussed in detail. The proposed method is verified with several numerical examples with clear and reasonable load transfer paths.     

Exploration life support technology challenges for the Crew Exploration Vehicle and future human missions

As NASA implements the U.S. Space Exploration Policy, life support systems must be provided for an expanding sequence of exploration missions. NASA has implemented effective life support for Apollo, the Space Shuttle, and the International Space Station (ISS) and continues to develop advanced systems. This paper provides an overview of life support requirements, previously implemented systems, and new technologies being developed by the Exploration Life Support Project for the Orion Crew Exploration Vehicle (CEV) and Lunar Outpost and future Mars missions. The two contrasting practical approaches to providing space life support are (1) open loop direct supply of atmosphere, water, and food, and (2) physicochemical regeneration of air and water with direct supply of food. Open loop direct supply of air and water is cost effective for short missions, but recycling oxygen and water saves costly launch mass on longer missions. Because of the short CEV mission durations, the CEV life support system will be open loop as in Apollo and Space Shuttle. New life support technologies for CEV that address identified shortcomings of existing systems are discussed. Because both ISS and Lunar Outpost have a planned 10-year operational life, the Lunar Outpost life support system should be regenerative like that for ISS and it could utilize technologies similar to ISS. The Lunar Outpost life support system, however, should be extensively redesigned to reduce mass, power, and volume, to improve reliability and incorporate lessons learned, and to take advantage of technology advances over the last 20 years. The Lunar Outpost design could also take advantage of partial gravity and lunar resources.     

旋翼/机身干扰非定常流场数值模拟(英文)

基于非结构动态嵌套网格方法对直升机旋翼/机身干扰非定常流场进行了三维Euler方程数值模拟。嵌套网格系统由包含旋翼的运动区网格和包含机身的静止区网格组成,两区网格均来自于同一套初始的整体非结构网格,人工边界以及初始的插值贡献单元对应关系在网格分区时同时确定。在非定常计算中两区网格始终存在一定的重叠区域,无需重新建立人工边界。高效的贡献单元搜索算法可以根据初始的插值贡献单元对应关系很快更新每一个真实时间步上的贡献单元对应关系。为了准确计入旋翼桨叶的挥舞和变距变形,在运动区网格中引入线性弹簧方法。采用非定常Euler方程和双时间推进方法模拟了美国佐治亚理工学院旋翼/机身干扰实验外形非定常流场,计算结果与实验值以及文献的计算值相吻合。