B样条工线的小波光顺法

本文研究了Ｂ样条曲线的小波光顺法，首先介绍了利用准均匀Ｂ样条曲线逼近具有任意节点矢量的Ｂ样线的方法，从而将任意Ｂ样条曲线转化为多分辨率表示，进而提出了基于小波的曲线光顺误差控制算法。小波光顺法在光顺曲线的同时具有减少控制顶点的作用，兼具简单性和通用性的优点。     

基于半正交B样条小波的任意控制顶点数曲线光顺

目前,小波分析应用于逆向工程时,对控制顶点有特殊要求,只能处理2j r个控制顶点的图形,为此提出了一种可以光顺任意控制顶点B样条曲线的小波分析新方法。在介绍B样条定义的基础上,从小波分析的定义出发,用严格的数学证明推导了任意控制顶点曲线的小波分解与重构具体算法。最后,该算法成功应用于B样条曲线的小波光顺,实例表明,该算法准确、结果稳定,效率理想。     

基于小波的B样条曲线局部光顺算法

针对传统的小波光顺方法只能进行整体光顺,而不能进行局部光顺的问题,根据小波的时频局部特性,提出了一种基于小波的B样条曲线局部光顺算法。该方法在“滤波”时,只去除原曲线中对“坏点”有影响的高频成分,而不修改那些对关键特征点有影响的小波系数,使得光顺后的曲线,不仅具有较好的光顺性,而且整体形状变化较小。同时讨论了“坏点”的选取、误差的控制、边界约束的处理等相关问题。     

平面参数三次样条曲线的优化光顺算法

给出了基于Kjellander和离散曲率的平面参数三次样条曲线的一种优化光顺算法.首先介绍了离散曲率和Kjellander的光顺法,进而给出了一个带有修改因子λ的目标函数,并通过求解得到λ值和光顺后的型值点,最后得到光顺后的曲线.此法使曲线的曲率变化均匀,使光顺后的曲线与原曲线的偏差小,并且算法简单易行,计算量较小.     

参数三次B样条曲线的一种整体光顺方法

本文在能量法的基础上，提出了一种新的目标函数，给出了参数三次Ｂ样条曲线的一种新的整体光顺方法。利用这种方法得到的曲线不仅具有较小的应变能，而且曲率变化比较均匀，具有很好的光顺效果。该方法能推广到对曲面的光顺。     

有理Bézier光顺样条曲线

本文给出一种用低次有理Bézier样条曲线光顺逼近任意次Bézier曲线及其等距线的方法,本文还应用了非线性优化技术。     

一种参数三次样条曲线光顺优化算法

论文给出了一种基于修改因子和修改角度的平面参数三次样条曲线的优化光顺算法,该算法通过求解一个带有修改因子λ和修改角度θ的目标函数得到光顺后的型值点,插值光顺后的型值点得到光顺曲线。目的是使曲线的曲率变化均匀的同时,使光顺后的曲线与原曲线的偏差尽量小,此算法简单易行,计算量较小。     

B-样条曲线升阶的几何收敛性

B-样条曲线的升阶算法是CAD系统相互沟通必不可少的手段之一。B-样条曲线的控制多边形经过不断升阶以后,和Bézier曲线一样都会收敛到初始B-样条曲线。根据双次数B-样条的升阶算法,得到了B-样条曲线升阶的收敛性证明。与以往升阶算法不同的是,双次数B-样条的升阶算法具有割角的性质,这就使B-样条曲线升阶有了鲜明的几何意义。得到的结论可以使B-样条曲线像Bézier曲线一样,通过几何割角法生成。     

曲线曲面的B3样条拟合

本文介绍了一种新的曲线曲面的生成方法——B3样条拟合。给出了B3样条曲线(面)的概念、核函数及其数学表达式,并论述了两种B3样条曲线(面)的计算机生成方法——通常的矩阵计算法和特殊的查表法。分析了用B3样条进行曲线(面)形状控制时的几种情况。并指出B3样条不仅保留了B样条曲线C~2连续性,而且点点通过型值点,因而提供了一种直观形象的,有很多实际应用价值的曲线(面)设计方法。     

基于非线性规划解的双圆柱螺线样条的局部构造

给出基于非线性规划解的双圆柱螺线样条局部构造法,把平面几何样条－双圆弧样条推广到常曲率和常挠率的空间几何样条。一对G^1拼接的圆柱螺线段可插值空间两端点位矢和单位切矢,且可适应不同的设计要求,如逼近在双圆柱螺线段两端点处的主法矢,使曲线光顺等。本方法在数控加工和显示中有良好的应用前景。     

一种选点法和能量法相结合的曲线光顺方法

将选点修改法和能量法相结合，提出了一种新的曲线光顺方法。和传统的选点修改法以及能量法的区别是：选点修改法每次只修改一个坏点，能量法一次性地修改所有控制顶点，而本文的方法则是用能量法一次性地修改所有对坏点有影响的控制顶点。数值实例表明，这是一种有效的曲线光顺方法。     

Sensitivity Analysis Based Multiple Objective Preform Die Shape Optimal Design in Metal Forging

The multiple objective preform design optimization was put forward. The final forging＇s shape and deformation uniformity were considered in the multiple objective. The objective is to optimize the shape and the deformation uniformity of the final forging at the same time so that a more high integrate quality of the final forging can be obtained. The total objective was assembled by the shape and uniformity objective using the weight adding method. The preform die shape is presented by cubic B-spline curves. The control points of B-spline curves are used as the design variables. The forms of the total objective function, shape and uniformity sub-objective function are given. The sensitivities of the total objective function and the sub-objective functions with respect to the design variables are developed. Using this method, the preform die shape of an H-shaped forging process is optimally designed. The optimization results are very satisfactory.     

Approximation of planar offset curves with globally bounded error for B-spline NC tool paths

The topic of representing the offset of a 2D B-spline curve in the same form has been a topic of research for a long time, and it has many industrial applications, especially in NC tool path generation for pocketing. For B-spline tool paths, it is often required that the tool paths have fewer control points, lower base function degree, and the approximation error is guaranteed within a given tolerance over the entire curve. However, the existing methods utilising global error control approximate the offsets of 2D free-form curves with high function degree and many control points. Although these offsets are useful in computer-aided design, they are inappropriate for the use of CNC machining. To address the problems in order to generate high quality B-spline tool paths, this original work formulates an error function of the offset approximation and then constructs a NURBS curve to globally bound the errors. By checking the maximum coefficient of the bounding curve, the upper bound of all the approximated offset errors is found and the errors can be reduced by segmenting the curve at appropriate knot values. The proposed new approach is more efficient, and the resulting offset approximations are more accurate, with fewer control points and lower function degree. It is useful to generate B-spline tool paths for CNC pocketing, which have the potential for other applications in industry.     

用摄动—加权残数法分析复合材料层合薄板的大挠度问题

本文将摄动法与加权残数法联合应用于解复合材料层合薄板的大挠度问题,对摄动后得到的各线线性微分方程组,全部采用统一试函数形式的最小二乘配点法求解,方法简捷,程序通用。     

曲面光顺的分片能量法

能量法是一种目前被广泛采用的光顺方法,但当数据点较多时,能量法的存储量和计算量都很大。本文研究Ｂ样条曲面光顺的分片能量法。应用该法可以在保持光顺效果的能量法基本一致的前提下,大大地减少了存储量和计算量。实例表明,这是一种行之有效的曲面光顺方法。     

B-spline approximation in boundary face method for three-dimensional linear elasticity

In this paper, basis functions generated from B-spline or Non-Uniform Rational B-spline (NURBS), are used for approximating the boundary variables to solve the 3D linear elasticity Boundary Integral Equations (BIEs). The implementation is based on the BFM framework in which both boundary integration and variable approximation are performed in the parametric spaces of the boundary surfaces to keep the exact geometric information in the BIEs. In order to reduce the influence of tensor product of B-spline and make the discretization of a body surface easier, the basis functions defined in global intervals are translated into local form. B-spline fitting function built with the local basis functions is converted into an interpolation type of function in which the nodal values of the boundary variables are used for control points. Numerical tests for 3D linear elasticity problems show that the BFM with B-spline basis functions outperforms that with the well-known Moving Least Square (MLS) approximation.     

航天器发射阶段声振环境载荷控制技术研究进展

航天器在发射阶段承受各种恶劣而复杂的声振环境载荷,严重影响着航天器的可靠性。目前,关于改善发射阶段航天器所承受的力学环境、切断振动噪声传播路径的相关研究已得到世界各国航天技术研究机构的重视。其中,各种声振环境载荷以透射声或结构声辐射的形式传递到整流罩内部后,将会在整流罩内形成恶劣声学环境——高声压级的噪声环境。本文主要对整流罩内噪声的主、被动控制技术的国外研究进展进行系统地综述和分析,以期对我国相关领域的技术研究及应用有所启示。     

Design and testing of the Minotaur advanced grid-stiffened fairing

A composite grid-stiffened structure concept was selected for the payload fairing of the Minotaur launch vehicle. Compared to sandwich structures, this concept has an advantage of smaller manufacturing costs and lighter weight. To reduce weight the skin pockets are allowed to buckle visibly up to about 0.5 cm peak displacement.

Various failure modes were examined for the composite grid-stiffened structure. The controlling criterion for this design was a joint failure in tension between the ribs and skin of the structure. The identification of this failure mechanism and the assessment of bounding strains required to control it required extensive test and analysis effort. Increasing skin thickness to control skin buckling resulted in reduced strains between the skin and ribs.

Following the identification of the relevant failure criteria, a final design for the fairing was generated. The resulting 6 m tall fairing was constructed of a tow-placed carbon fiber composite grid structure that was over-wrapped to create a laminated skin. Upon completion of curing and machining, the fairing was cut in half to create the classic “clam-shell” fairing. Static qualification testing demonstrated the structural integrity of the fairing, thereby proving the design and manufacturing process. Loads were applied incrementally in a static loading scenario. The applied load envelope exceeded worst-case dynamic flight conditions with an added safety factor of 25%. At peak load the fairing maintained structural integrity while remaining within the required displacement envelope for payload safety.

Data were collected during the test from a variety of sensors including traditional displacement transducers and strain gages. In addition, full field displacement was monitored at critically loaded fairing sections by means of digital photogrammetry. This paper summarizes the test results, presents the overall performance of the fairing under the test loads, correlates test response and analysis, and identifies lessons learned.

Work continues at the Air Force Research Laboratory (AFRL) and Boeing to identify means of further controlling tensile failure of the un-reinforced polymer bonded joint between the ribs and skin. Stiffening of skin adjacent to the joints and introduction of lightweight foam jackets at the interior of the fairing both show promise of delaying joint failure to higher loads.     

基于PC／104总线的飞机整流锥襟翼自动检查仪设计

为实时测量整流锥锥位和襟翼的收放角度,设计了基于PC/104总线的飞机整流锥襟翼自动检查仪;给出了硬件系统构成和各组成模块的功能,设计了信号调理、转换电路;利用Turbo C2.0构建的软件系统在DOS操作系统下实现整流锥和机动襟翼的自动检查以及检查数据的处理和显示;针对襟翼系统检查量大且复杂的特点,说明了襟翼自动检查的过程.使用结果表明,该检查仪满足根据大气参数自动检查整流锥和襟翼系统的需求,提高了检查效率与准确性.