太空中的PM2.5——太阳系尘埃动力学研究进展

对太阳系尘埃动力学所涉及到的基本内容进行概述，包括尘埃的种类、成分、尺寸、密度、形状和生命周期。介绍了近年来在尘埃的来源与生成机制方面的力学过程、主要理论、模型与方法，包括冲击溅射、表面喷射、风化、滑坡、质量脱落、旋转断裂等，阐述了尘埃的充电过程与磁场环境，简要概述了航天任务的尘埃探测结果，介绍了尘埃受力模型、单个尘埃颗粒的运动以及大量尘埃的分布特征、动力学现象及内在规律方面的最新研究结论。最后对太阳系尘埃动力学领域的未来发展趋势进行了展望。     

混合小推力航天器轨道保持高性能滑模控制

针对采用太阳帆、太阳电混合小推力推进的航天器，研究了其在日心悬浮轨道的保持控制问题。为解决已有控制方法中未综合考虑内部未建模动态和外部未知扰动的问题，以及进一步提高系统控制性能，设计了一种高性能滑模控制策略。首先，考虑模型不确定性，建立了混合小推力航天器在日心悬浮轨道柱面坐标系的动力学方程；其次，基于改进型条件积分滑模面和径向基（RBF）神经网络设计了控制律，结合自适应方法在线估计不确定参数；接着，将求取的虚拟控制量在推进剂最优条件下转换成实际控制量，即太阳帆姿态角和太阳电推进力；最后，数值仿真验证了上述设计方法提高了系统鲁棒性，减小了轨道位置超调，并且混合推进相比于单一太阳帆推进，在更短收敛时间内控制精度提高了4个数量级，相比于单一太阳电推进，一年可以节省约89.6%的推进剂。     

Grindability and Surface Integrity of Cast Nickel-based Superalloy in Creep Feed Grinding with Brazed CBN Abrasive Wheels

The technique of creep feed grinding is most suitable for geometrical shaping, and therefore has been expected to improve effectively material removal rate and surface quality of components with complex profile. This article studies experimentally the effects of process parameters (i.e. wheel speed, workpiece speed and depth of cut) on the grindability and surface integrity of cast nickel-based superalloys, i.e. K424, during creep feed grinding with brazed cubic boron nitride (CBN) abrasive wheels. Some important factors, such as grinding force and temperature, specific grinding energy, size stability, surface topography, microhardness and microstructure alteration of the sub-surface, residual stresses, are investigated in detail. The results show that during creep feed grinding with brazed CBN wheels, low grinding temperature at about 100 °C is obtained though the specific grinding energy of nickel-based superalloys is high up to 200-300 J/mm³. A combination of wheel speed 22.5 m/s, workpiece speed 0.1 m/min, depth of cut 0.2 mm accomplishes the straight grooves with the expected dimensional accuracy. Moreover, the compressive residual stresses are formed in the burn-free and crack-free ground surface.     

Tool Life and Surface Integrity in High-speed Milling of Titanium Alloy TA15 with PCD/PCBN Tools

Titanium alloys are widely used in aeronautics that demand a good combination of high strength, good corrosion resistance and low mass. The mechanical properties lead to challenges in machining operations such as high process temperature as well as rapidly increasing tool wear. The conventional tool materials are not able to maintain their hardness and other mechanical properties at higher cutting temperatures encountered in high speed machining. In this work, the new material tools, which are polycrystalline diamond (PCD) and polycrystalline cubic boron nitride (PCBN) tools, are used in high-speed milling of Ti-6.5Al-2Zr-1Mo-1V (TA15) alloy. The performance and wear mechanism of the tools are investigated. Compared to PCBN tool, PCD tool has a much longer tool life, especially at higher cutting speeds. Analyses based on the SEM and EDX suggest that attrition, adhesion and diffusion are the main wear mechanisms of PCD and PCBN tools in high-speed milling of TA15. Oxidation wear is also observed at PCBN tool/workpiece interface. Roughness, defects, micro-hardness and microstructure of the machined surface are investigated. The recorded surface roughness values with PCD/PCBN tools are bellow 0.3 μm at initial and steady cutting stage. Micro-hardness analysis shows that the machined surface hardening depth with PCD and PCBN tools is small. There is no evidence of sub-surface defects with PCD and PCBN tools. It is concluded that for TA15 alloy, high-speed milling can be carried out with PCD/PCBN tools.     

小展弦比飞翼布局作战飞机可控性设计方法

 飞翼布局飞机取消了常规布局飞机采用的安定面和操纵面,由此引起其可控性设计的诸多新问题。以某小展弦比飞翼布局作战飞机为例,利用风洞试验结果研究了几种典型新型操纵面的操纵新机理及不同飞行条件下的操纵效能等。基于可控性设计的要求,估算了该飞翼构型作战使用所需的三轴最大控制力矩系数。通过引进舵容量的概念提出了新型操纵面的参数化设计方法,最后对这一新布局方案进行了可控性评估,为飞翼布局飞机概念设计阶段的新型操纵面布置和设计提供了一种实用的方法。     

结构可靠度逐步逼近径向基神经网络响应面法

提出了逐步逼近径向基神经网络响应面法计算结构可靠度,这种数值方法较好地解决了结构功能函数非线性及结构随机变量非正态分布时采用结构可靠度指标度量结构可靠度存在误差的问题.经过多个数值试验表明,该算法迭代收敛迅速、计算准确性较高、应用过程简单.利用这种方法对含有多个随机变量的结构进行可靠性分析和设计,特别是当结构功能函数具有较强的非线性或结构随机变量分布具有较大的偏斜度时,具有一定的应用价值.      

长边条翼身融合过渡曲面的构造方法

 针对飞航导弹长边条翼身融合过渡曲面的构造展开研究,为满足融合过渡曲面过渡线能够由设计人员确定和长边条面必须是等截面的直纹面等要求,综合应用基于局部重新参数化构造过渡曲面和基于物理的能量曲面造型构造过渡曲面方法,并结合导弹弹身曲面是等截面直纹面的特点,通过构造翼身融合面、长边条面和头锥面3张曲面拼接来构造G-1连续的长边条翼身融合过渡曲面。提出了预先构造中间辅助面和辅助基曲面的方法,通过辅助基曲面和弹翼面上重新参数化局部基曲面间线性组合来构造翼身融合面。通过使中间辅助过渡面的边界切矢与弹身的纵向切矢一致,来保证长边条面与翼身融合面间的G-1连续性。最后利用基于物理的能量曲面造型方法构造与弹身和长边条面G-1连续的头锥过渡面。     

一种trimmed曲面的半自适应离散方法

提出了一种 trimmed曲面的半自适应离散算法。该算法通过对曲面的参数域进行预剖分,以及引进参数曲面上一点处的“最大法曲率”的概念,采用分区域处理的方法分片对 trimmed曲面的有效参数域进行三角形网格剖分。该方法计算速度快,能根据曲面的法曲率变化来控制 trimmed曲面三角化剖分的密度,并可有效地避免在三维空间产生奇异三角形与“裂缝”。     

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.      

人工神经网络技术在光电检测中的应用

人工神经网络不仅被广泛用于人工智能、自动控制、机械人、统计学等领域的信息处理中,还越来越多地被应用于光电检测.综述了人工神经网络技术在光电检测中的最新应用进展,重点讨论了人工神经网络技术在谷物蛋白质含量近红外在线监测、结构光三维视觉检测、焊缝缺陷射线实时成像识别、表面粗糙度及球半径精密测量应用中的优点和局限性,以期进一步推动本领域的研究和发展.