Changing law of launching pitching angular velocity of rotating missile

In order to provide accurate launching pitching angular velocity（LPAV） for the exterior trajectory optimization design, multi-flexible body dynamics（MFBD） technology is presented to study the changing law of LPAV of the rotating missile based on spiral guideway. An MFBD virtual prototype model of the rotating missile launching system is built using multi-body dynamics modeling technology based on the built flexible body models of key components and the special force model.The built model is verified with the frequency spectrum analysis. With the flexible body contact theory and nonlinear theory of MFBD technology, the research is conducted on the influence of a series of factors on LPAV, such as launching angle change, clearance between launching canister and missile,thrust change, thrust eccentricity and mass eccentricity, etc. Through this research, some useful values of the key design parameters which are difficult to be measured in physical tests are obtained. Finally,a simplified mathematical model of the changing law of LPAV is presented through fitting virtual test results using the linear regression method and verified by physical flight tests. The research results have important significance for the exterior trajectory optimization design.     

Damage characteristics and constitutive modeling of the 2D C/Si C composite: Part I – Experiment and analysis

This paper reports an experimental investigation on the macroscopic mechanical behaviors and damage mechanisms of the plain-woven(2D) C/Si C composite under in-plane on- and offaxis loading conditions. Specimens with 15, 30, and 45 off-axis angles were prepared and tested under monotonic and incremental cyclic tension and compression loads. The obtained results were compared with those of uniaxial tension, compression, and shear specimens. The relationships between the damage modes and the stress state were analyzed based on scanning electronic microscopy(SEM) observations and acoustic emission(AE) data. The test results reveal the remarkable axial anisotropy and unilateral behavior of the material. The off-axis tension test results show that the material is fiber-dominant and the evolution rate of damage and inelastic strain is accelerated under the corresponding combined biaxial tension and shear loads. Due to the damage impediment effect of compression stress, compression specimens show higher mechanical properties and lower damage evolution rates than tension specimens with the same off-axis angle. Under cyclic tension–compression loadings, both on-axis and off-axis specimens exhibit progressive damage deactivation behaviors in the compression range, but with different deactivation rates.     

空间环境研究的现状与展望

空间环境研究的内容包括空间环境模式研究、空间环境效应研究和空间环境实验研究。当前国外空间环境研究注重对大型软件组织多学科、多单位长期合作研究;模式研究与实验研究紧密结合;注意开发对工程适用的模式;工作重点是太阳帆板带电和低轨卫星表面带电。建议我国在今后的空间环境研究中加强联合,集中攻克急需的大型软件;加强对材料特性的实验研究;着手发射环境效应卫星;开拓空间环境研究的新领域;在空间环境效应研究中加强卫星研制单位、卫星操作部门与环境效应研究单位的合作。     

短裂纹疲劳扩展的试验方法

近十年来,人们发现短裂纹具有一系列不同于普通长裂纹的特异扩展规律,它对耐久性损伤容限分析具有重要的意义。短裂纹扩展率试验是短裂纹研究中一项迫切而重要的,同时也是较为困难的工作。     

复合材料波纹腹板梁坠撞试验与数值模拟

为了探究复合材料波纹腹板梁在坠撞过程中的吸能性能,对复合材料波纹腹板梁试验件进行了动态冲击压溃试验研究,得到了试验件的损伤破坏形貌以及载荷和能量的历程曲线。基于ABAQUS/Explicit平台二次开发得到了模拟复合材料波纹腹板梁冲击压溃过程的仿真分析模型,模型采用了改进的Hashin损伤判定准则和Choi-Chang准则综合判断单元失效,并结合Cohesive界面单元,可较为真实地反映所研究复合材料层合结构的各向异性和渐进损伤特性。通过数值模拟得到了能量评估参数比吸能（Specific energy absorption, SEA）和平均压溃载荷,与试验结果进行了对比分析。基于仿真分析模型,本文进一步研究了不同波数的复合材料波纹腹板梁的吸能能力。数值模拟结果表明：波纹腹板梁在冲击载荷作用下发生了渐进压溃失效;平均压溃载荷的相对误差较小,验证了模型的有效性;在腹板单波长度不变的情况下,波纹腹板梁的长度对抗冲击吸能的影响较大。当波纹腹板梁长度较小时,结构容易失稳,无法有效地吸收能量。     

受剪紧固件DFR_τ的确定方法

本文介绍DFR_τ和其他疲劳参数之间的关系以及利用受拉光滑试件疲劳试验数据、根据强度理论并考虑擦伤影响来确定DFR_τ的方法。     

再入飞行器复合材料舱段极限应力强度分析

由于缺少可靠实用的极限强度分析方法,复合材料结构的设计长久依赖于试验验证手段确保设计可靠度,产品研制难度大。该文发展此前研究提出的通用强度失效准则和算法,开展再入飞行器复合材料舱段的应力强度分析方法应用研究,对设计重点关注的典型蒙皮与端框结构,建立有限元模型,预示其极限承载能力并与实测数据对比,结果表明:复合材料舱段极限强度的预示与实测结果吻合良好,对端框复杂结构预示精度能够达到-14.2%量值水平,复合材料舱段的结构强度可靠度有条件通过设计计算来保证。     

弹道导弹惯性测量系统精度指标自适应分配方法

对弹道导弹惯性测量系统进行误差分析和精度指标分配是保证导航精度和武器作战性能的一项重要任务.针对目前惯性导航系统误差分析不全面、精度评估准则单一以及精度指标分配方法不准确的不足,提出了一种弹道导弹惯性测量系统精度指标自适应分配方法,能够按照误差项对精度的影响合理化分配精度指标.该方法首先分析了影响导航精度的所有误差项,...     

Damage characteristics and constitutive modeling of the 2D C/SiC composite: Part Ⅱ–Material model and numerical implementation

In this work, a macroscopic non-linear constitutive model accounting for damage, inelastic strain and unilateral behavior is proposed for the 2D plain-woven C/Si C composite. A set of scalar damage variables and a new thermodynamic potential expression are introduced in the framework of continuum damage mechanics. In the deduced constitutive equations, the material's progressive damage deactivation behavior during the compression loading is described by a continuous function, and different deactivation rates under uniaxial and biaxial compression loadings are also considered. In damage evolution laws, the coupling effect among the damage modes and impediment effect of compression stress on the development of shear damage in different plane stress states are taken into account. Besides, the general plasticity theory is applied to describing the evolution of inelastic strain in tension and/or shear stress state. The Tsai–Wu failure criterion is adopted for strength analysis. Additionally, the material model is implemented as a user-defined material subroutine(UMAT) and linked to the ABAQUS finite element software, and its performance is demonstrated through several numerical examples.     

旋转槽道湍流的格子Boltzmann方法模拟

基于多松弛格子Boltzmann方法的大涡模拟对雷诺数为194,旋转数从0~5.0的旋转槽道湍流进行数值模拟.采用动态亚格子应力模型模化滤波后的不封闭项,修正二阶矩作用力模型计算压力梯度、哥氏力.对平均速度、均方根脉动速度、雷诺应力以及湍流结构进行了计算.结果显示哥氏力使流场平均速度呈现不对称性:在压力面,随着旋转数的增加,湍流度增强;而在吸力面湍流脉动减弱,具有层流化的趋势.将格子Boltzmann模型与直接数值模拟求解进行对比,结果验证了格子Boltzmann方法在旋转湍流模拟中的可行性.