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| 1 | Uniform Coverage of Fibres over Open-contoured Freeform Structure Based on Arc-length Parameter显示文摘这篇文章使用弧长度参数路径计划在开轮廓的结构上执行机器的纤维放置(RFP ) 。这允许由更简单的算术用一个相同数学方程和计算代表起始的路径和偏移量点。在古典微分几何学的帮助下,放纤维的路径的计算可以在参量的域(参量地定义的模子表面) 或在 3D 空格(含蓄地定义的模子表面) 被归结为一阶的平常的微分方程的起始值的问题的答案,显著地从而在存在方法上改善。与常规方法相比,除它的计算简洁以外,建议方法在计算起始的路径和偏移量点有更好的错误控制机制。数字实验也被执行在合成形成的进程并且也表明新方法的可行性它在计算机的潜在的应用程序用机器制造的数字控制(计算机数值控制) ,表面修剪,和另外的工业惯例。 | Wang Xiaoping An Luling Zhang Liyan Zhou Laishui | 2008 | Chinese Journal of Aeronautics2008，21，6： | 7 |
| 2 | Two-stage open-loop velocity compensating method applied to multi-mass elastic transmission system显示文摘In this paper,a novel vibration-suppression open-loop control method for multi-mass system is proposed,which uses two-stage velocity compensating algorithm and fuzzy I + P controller. This compensating method is based on model-based control theory in order to provide a damping effect on the system mechanical part. The mathematical model of multi-mass system is built and reduced to estimate the velocities of masses. The velocity difference between adjacent masses is calculated dynamically. A 3-mass system is regarded as the composition of two 2-mass systems in order to realize the two-stage compensating algorithm. Instead of using a typical PI controller in the velocity compensating loop,a fuzzy I + P controller is designed and its input variables are decided according to their impact on the system,which is different from the conventional fuzzy PID controller designing rules. Simulations and experimental results show that the proposed velocity compensating method is effective in suppressing vibration on a 3-mass system and it has a better performance when the designed fuzzy I + P controller is utilized in the control system. | Zhang Deli Yang Haiqiang An Luling | 2014 | Chinese Journal of Aeronautics2014，27，1： | 3 |
| 3 | Constructing G^2 Continuous Curve on Freeform Surface with Normal Projection显示文摘This article presents a new method for G~2 continuous interpolation of an arbitrary sequence of points on an implicit or parametric surface with prescribed tangent direction and curvature vector,respectively,at every point.First,a G~2 continuous curve is constructed in three-dimensional space.Then the curve is projected normally onto the given surface.The desired interpolation curve is just the projection curve,which can be obtained by numerically solving the initialvalue problems for a system of first-order ordinary differential equations in the parametric domain for parametric case or in three-dimensional space for implicit case.Several shape parameters are introduced into the resulting curve,which can be used in subsequent interactive modification so that the shape of the resulting curve meets our demand.The presented method is independent of the geometry and parameterization of the base surface.Numerical experiments demonstrate that it is effective and potentially useful in numerical control (NC) machining,path planning for robotic fibre placement,patterns design on surface and other industrial and research fields. | Wang Xiaoping,An Luling,Zhou Laishui,Zhang Liyan Jiangsu Key Laboratory of Precision and Macro-manufacturing Technology,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China | 2010 | Chinese Journal of Aeronautics2010，23，1： | 3 |
| 4 | Erratum to 'Uniform Coverage of Fibres over Open-contoured Freeform Structure Based on Arc-length Parameter' [Chinese Journal of Aeronautics 21(2008)571-577]显示文摘It is regretted that the author corrections requested at the proof stage were not made accurately. There are some incorrect typings in two equations which will lead to inaccurate results if readers perform calculations directly | Wang Xiaoping An Luling Zhang Liyan Zhou Laishui | 2009 | Chinese Journal of Aeronautics2009，22，3： | 2 |
| 5 | Influence of Shim Layers on Progressive Failure of a Composite Componentin Composite-Aluminum Bolted Joint in Aerospace Structural Assembly显示文摘The influence of varying shim layers on the progressive damage/failure of a composite component in a bolted composite-aluminum aerospace structural assembly was investigated using a non-linear three-dimensional(3 D)structural solid elements assembled model of a carbon fiber-reinforced polymer(CFRP)-aluminum single-lap joint with a titanium(Ti-6 Al-4 V)fastener and a washer generated with the commercial finite element(FE)software package,ABAQUS/Standard.A progressive failure algorithm written in Fortran code with a set of appropriate degradation rules was incorporated as a user subroutine in ABAQUS to simulate the non-linear damage behavior of the composite component in the composite-aluminum bolted aerospace structure.The assembled 3 DFE model simulated,as well as the specimen for the experimental testing consisted of a carbon-epoxy IMS-977-2 substrate,aluminum alloy 7075-T651 substrate,liquid shim(Hysol EA 9394),solid peelable fiberglass shim,a titanium fastener,and a washer.In distinction to previous investigations,the influence of shim layers(liquid shim and solid peelable fiberglass shim)inserted in-between the faying surfaces(CFRP and aluminum alloy substrates)were investigated by both numerical simulations and experimental work.The simulated model and test specimens conformed to the standard test configurations for both civil and military standards.The numerical simulations correlated well with the experimental results and it has been found that:(1)The shimming procedure as agreed upon by the aerospace industry for the resolution of assembly gaps in bolted joints for composite materials is the same for a composite-aluminum structure;liquid shim series(0.3,0.5 and 0.7 mm thicknesses)prolonged the service life of the composite component whereas a solid peelable fiberglass shim most definitely had a better influence on the 0.9 assembly gap compared with the liquid shim;(2)The shim layers considerably influenced the structural strength of the composite component by delaying its ultimate failure thereby increasing its service life;and(3)Increasing the shim layer′s thickness led to a significant corresponding effect on the stiffness but with minimal effect on the ultimate load. | Cephas Yaw Attahu An Luling Li Zhaoqing Gao Guoqiang | 2018 | Transactions of Nanjing University of Aeronautics and Astronautics2018，35，1： | 2 |
| 6 | A syetem for supporting rapid assembly modeling of mechanical products via components with typical assembly features显示文摘 | Li Guidong Zhou Laishui An Luling | 2010 | International Journal of Advanced Manufacturing Technology2010，46，： | 1 |
| 7 | A system for supporting rapid assembly modeling of mechanical products via components with typical assembly features显示文摘 | Li Guidong Zhou Laishui An Luling | | 0，，5： | 1 |
| 8 | A System for Supporting Rapid Assembly Modeling of Mechanical Products Via Components with Typical Assembly Features 显示文摘 | Li Guidong Zhou Laishui An Luling | 2010 | The International Journal of Advanced Manufacturing Technology2010，46，5678： | 1 |
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