锻造LF6法兰阳极化后表面深灰色原因分析

锻造LF6材料法兰硫酸阳极化后表面产生深灰色物质,影响产品质量和性能。分析认为这种现象与材料、机械加工和表面腐蚀有关,为此设计了一系列工艺验证试验,探寻深灰色物质产生的原因。试验结果表明,锻造LF6材料自身所含有的金属元素、机械加工和生产周期过长是阳极化封闭后零件表面产生深灰色的主要原因。     

未知空间目标纹理缺失表面三维重建算法

针对传统三维重建方法难以对纹理缺失表面进行完整重建的问题,提出一种基于深度学习与截断符号距离函数(TSDF)融合的未知目标三维表面完整重建算法。首先设计一种基于深度学习的图像逐像素深度估计框架,通过在训练过程中引入多个复杂结构模型,提高该深度估计框架的泛化能力;其次,利用TSDF对各帧图像所估计的深度信息进行融合,实现对纹理缺失区域的空间目标完整三维重建。根据仿真校验,对于300 mm尺寸的卫星模型图像,像素深度估计平均误差约为13 mm,通过TSDF融合后尺寸精度误差小于5.10%。实验结果表明该算法可以对未知空间目标光学图像进行逐像素深度估计,并获得目标完整的三维结构与纹理信息,有效解决无纹理区域的重建结构缺失问题。     

内埋电阻丝阵列检测复合材料表面裂伤初探

探讨了用层间埋置Ｎｉ－Ｃｒ合金丝构成局部网络实现对复合材料表面损伤位置和损伤程度检测。对表面裂纹尖端附近的应力场分布进行了分析,并将试验结果与预测结果进行了比较。实验结果表明：Ｎｉ－Ｃｒ合金丝阵列可以在玻纤／环氧树脂复合材料中用作传感元件,合金丝阵列所反映的裂端附近应力场分布是合理的。     

Investigation on surface roughness,residual stress and fatigue property of milling in-situ TiB2/7050Al metal matrix composites

For higher efficiency and precision manufacturing, more and more attentions are focused on the surface roughness and residual stress of machined parts to obtain a good fatigue life. At present, the in-situ TiB₂/7050Al metal matrix composites are widely researched due to its attractive properties such as low density, good wear resistance and improved strength. It is of great significance to investigate the machined surface roughness, residual stress and fatigue life for higher efficiency and precision manufacturing of this new kind material. In this study, the surface roughness including two-dimensional and three-dimensional roughness, residual stress and fatigue life of milling in-situ TiB₂/7050Al metal matrix composites were analyzed. It was found from comparative investigation that the three-dimensional surface roughness would be more appropriate to represent the machined surface profile of milling particle reinforced metal matrix composites. The cutting temperature played a great role on the residual stress. However, the effect of increasing cutting force could slow down the transformation from compressive stress to tensile stress under 270 °C. An exponential relationship between three-dimensional roughness and fatigue life was established and the main fracture mechanism was brittle fracture with observation of obvious shellfish veins, river pattern veins and wave shaped veins in fracture surface.     

Evolution of periodic orbits near the Lagrangian point L2

A study of the evolution of the periodic and the quasi-periodic orbits near the Lagrangian point L₂, which is located to the right of the smaller primary on the line joining the primaries and whose distance from the more massive primary is greater than the distance between the primaries, in the framework of restricted three-body problem for the Sun–Jupiter, Earth–Moon (relatively large mass ratio) and Saturn–Titan (relatively small mass ratio) systems is made. Two families of periodic orbits around the smaller primary are identified using the Poincaré surface of section method – family I (initially elliptical, gradually becomes egg-shaped with the increase in the Jacobi constant C and elongated towards the more massive primary) and family II (initially egg-shaped orbits elongated towards L₂ and gradually becomes elliptical with the increase in C). The family I in the Sun–Jupiter and Saturn–Titan systems contains two separatrix caused by third-order and fourth-order resonances, while the Earth–Moon system has only one separatrix which is caused by third-order resonances. Also in the Sun–Jupiter and the Saturn–Titan systems, family I merge with family II, around Jacobian constant 3.0393 and 3.0163, respectively, while in the Earth–Moon system, family II evolves separately from two different branches. The two branches merge at C = 3.184515. In the Earth–Moon system, the family II contains a separatrix due to third-order resonances which is absent in the other two systems.     

Sliding mode control of reaction flywheel-based brushless DC motor with buck converter

Reaction flywheel is a significant actuator for satellites’ attitude control. To improve output torque and rotational speed accuracy for reaction flywheel, this paper reviews the modeling and control approaches of DC-DC converters and presents an application of the variable structure system theory with associated sliding regimes. Firstly, the topology of reaction flywheel is constructed. The small signal linearization process for a buck converter is illustrated. Then, based on the state averaging models and reaching qualification expressed by the Lee derivative, the general results of the sliding mode control (SMC) are analyzed. The analytical equivalent control laws for reaction flywheel are deduced detailedly by selecting various sliding surfaces at electromotion, energy consumption braking, reverse connection braking stages. Finally, numerical and experimental examples are presented for illustrative purposes. The results demonstrate that favorable agreement is established between the simulations and experiments. The proposed control strategy achieves preferable rotational speed regulation, strong rejection of modest disturbances, and high-precision output torque and rotational speed tracking abilities.     

提高飞行器升力的若干方法研究

本研究用数值模拟方法研究了四种增升方法。数据模拟的出发方程是可压流的Ｎ－Ｓ方程，格式为Ｂｅａｍ－Ｗａｒｍｉｎｇ格式的改进型。通过上述方法分别研究了：（１）动界效应对提高升力的作用；（２）涡的有利干扰对主升力面的影响；（３）吸气的驻涡增效应；（４）升力面下表面向下喷气的增升作用。研究结果表明，采用上述四种方法可有效地提高飞行器的升力，对改善飞行器的性能有着十分重要的意义。     

光学基片表面软质抛光胶体粒子的激光清洗

介绍了光学基片表面软质抛光胶体粒子激光清洗的基本方法、原理和实验装置,并通过对含有污染微粒的基片表面进行激光清洗,获得了高洁净表面的光学基片.     

不同型线结构船艏表面压力特性对比实验研究

为优选船艏结构型线方案,在风洞中针对三个在结构型线上仅有细微差别的船艏方案进行表面压力特性对比测试。实验获得了各型线方案模型表面压力空间分布特性和压力脉动特性,并通过表面压力特性的综合对比进行了结构型线评估,为船艏的结构型线设计提供直接的技术依据。     

Reconfigurable Flight Control Design for Combat Flying Wing with Multiple Control Surfaces

With control using redundant multiple control surface arrangement and large-deflection drag rudders,a combat flying wing has a higher probability for control surface failures.Therefore,its flight control system must be able to reconfigure after such failures.Considering three types of typical control surface failures(lock-in-place(LIP),loss-of-effectiveness(LOE) and float),flight control reconfiguration characteristic and capability of such aircraft types are analyzed.Because of the control surface redundancy,the aircraft using the dynamic inversion flight control law already has a control allocation block.In this paper,its flight control configuration during the above failures is achieved by modifying this block.It is shown that such a reconfigurable flight control design is valid,through numerical simulations of flight attitude control task.Results indicate that,in the circumstances of control surface failures with limited degree and the degradation of the flying quality level,a combat flying wing adopting this flight control reconfiguration approach based on control allocation could guarantee its flight safety and perform some flight combat missions.