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xk6125 数控 铣床 总体 整体 横向 进给 传动 机构 设计 全套 cad 图纸

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下载后包含有 CAD 图纸和说明书,咨询 Q 197216396 或 11970985毕 业 设 计 (论 文 )XK6125 数控铣床总体及横向进给传动机构设计所 在 学 院专 业班 级姓 名学 号指 导 老 师年 月 日下载后包含有 CAD 图纸和说明书,咨询 Q 197216396 或 11970985I摘 要本论文是对 XK6125数控铣床总体及横向进给传动机构设计，其内容包括：进给伺服系统机械部分设计与计算、步进电动机的计算与选型、铣床改造的结构特点、安装调整中应注意的问题等。对普通铣床进行数控改造符合我国国情，即适合我国目前的经济水平、教育水平和生产水平，又是国内许多企业提高生产设备自动化水平和精密程度的主要途径，在我国有着广阔的市场。从另一个角度来说，该设计既有机床结构方面内容，又有机加工方面内容，还有数控技术方面的内容，有利于将大学所学的知识进行综合运用。虽然设计者未曾系统的学习过机床设计的课程，但通过该设计拓宽了知识面，增强了实践能力，对普通机床和数控机床都有了进一步的了解。关键词：横向进给系统，数控化改造，机床改造，铣床下载后包含有 CAD 图纸和说明书,咨询 Q 197216396 或 11970985IIAbstractThe present paper is to XK6125 for feed system of NC transformation, its contents include: feed servo system of mechanical part design and calculation, and the calculation of the stepper motor selection, Miller structure characteristics, installation and adjustment should pay attention to the problem. On the common milling machine numerical control transformation in line with Chinas national conditions, that is suitable for Chinas current economic level, educational level and the level of production, but also many domestic enterprises to improve the level of automated production equipment and precision degree of the main way, has the broad market in our country. From another perspective, the design is a machine tool structure in terms of content, but also organic processing aspects, CNC technical content, the university knowledge to make comprehensive use of. Although the designers have not studied the machine design course, but through the design to broaden the knowledge, enhances the ability of practice, the general machine tools and CNC machine tools have a further understanding.KeyWords: horizontal feed system, NC transformation, transformation of machine tools, milling machine下载后包含有 CAD 图纸和说明书,咨询 Q 197216396 或 11970985III目录摘 要 .IAbstract .II目录 .III第 1 章 数控机床发展概述.11.1 数控机床发展概述 .11.2 数控机床的组成及分类 .11.2.1 数控机床的组成 .11.2.2 数控机床的分类 .31.3 数控机床的特点及应用范围 .41.3.1 数控机床的特点 .41.3.2 数控机床的应用范围 .4第 2 章 数控机床总体方案的制订及比较.52.1 课题要求 .52.1.1 题目名称（包括主要技术参数）及技术要求 .52.1.2 课题内容及工作量 .52.2 设计原则 .52.3 总结构设计 .62.3.1 数控机床的机构设计要求 .62.3.2 提高机床的结构刚度 .62.3.3 提高进给运动的平稳性和精度 .7第 3 章 确定切削用量及选择刀具.83.1 刀具选择 .83.2 切削用量确定 .83.3 切削三要素 .93.4 加工精度和表面粗糙度 .93.5 刀具材料 .12第 4 章 传动系统图的设计计算.13IV4.1 传动系统设计 .134.1.1 参数的拟定 .134.1.2 传动结构或结构网的选择 .134.1.3 转速图拟定 .154.1.4 齿轮齿数的确定及传动系统图的绘制 .184.2 传动件的估算与验算 .224.2.1 传动轴的估算和验算 .224.2.2 齿轮模数的估算与验算 .244.3 展开图设计 .294.3.1 结构实际的内容及技术要求 .294.3.2 齿轮块的设计 .314.3.3 传动轴设计 .334.3.4 主轴组件设计 .364.4 制动器设计 .414.5 截面图设计 .424.5.1 轴的空间布置 .424.5.2 润滑 .434.5.3 箱体设计的有关问题 .44第 5 章 横向进给传动机构装配图零件图的设计计算.455.1 进给伺服系统的设计 .455.1.1 对进给伺服系统的基本要求 .455.1.2 进给伺服系统的设计要求 .455.1.3 进给伺服系统的动态响应特性及伺服性能分析 .465.2 横向进给滚珠丝杠副设计 .465.2.1 导程确定 .465.2.2 确定丝杆的等效转速 .465.2.3 估计工作台质量及负重 .475.2.4 确定丝杆的等效负载 .475.2.5 确定丝杆所受的最大动载荷 .47下载后包含有 CAD 图纸和说明书,咨询 Q 197216396 或 11970985V5.2.6 精度的选择 .485.2.7 选择滚珠丝杆型号 .495.3 校核 .495.3.1 临界压缩负荷验证 .495.3.2 临界转速验证 .505.3.3 丝杆拉压振动与扭转振动的固有频率 .515.4 电机的选择 .515.4.1 电机轴的转动惯量 .525.4.2 电机扭矩计算 .52总结与展望.54参考文献.55致 谢.56VI下载后包含有 CAD 图纸和说明书,咨询 Q 197216396 或 11970985VII11Optimal Design of Compliant Trailing Edge for Shape ChangingAbstract: Adaptive wings have long used smooth morphing technique of compliant leading an d trailing edge to improve their aerodynamic characteristicsThis paper introduces a systematic approach to design compliant structures to carry out required shape changes under distributed pressure loadsIn order to minimize the deviation of the deformed shape from the target shape，this method uses M ATLAB and ANSYS to optimize the distributed compliant mechanisms by way of the ground approach and genetic algorithm (GA)to remove the elements possessive of very low stressesIn the optimization process，man y factors should be considered such as air loads，input displacements，and geometric nonlinearities。Direct search method is used to locally optimize the dimension an d input displacement after the GA optimization。The resultant structure could make its shape change from 0 to 93degreesTheexperimental data of the model confirm s the feasibility of this approachKeywords： adaptive wing；compliant mechanism；genetic algorithm ；topology optimization；distributed pressure load；geometric nonlinearity1 Introduction：As conventional airfoil contours are usually designed with specific lift coefficients and M ach numbers，they could not change in accordance with the environment changingSiclari and Austin indicated that the variable camber trailing edge would produce the drag about sixty percent less than the conventional fixed camber airfoilThere are three methods used to design able camber wingsOf themone is conventional hinged mechanism，which，however, will create discontinuities over the wings surface leading to earlier airflow separation an d drag increase The others are smart material and the compliant mechanism，of which both could realize smooth shape changingNevertheless，compared to the compliant mechanism，the smartmaterialmade actuators have many disadvantages，such as deficient in energy ,slow in response，strong in hysteresis， limited by temperature，and difficult to control too many actuatorsMusolff from Industry University of Berlin 12used NiTi shapememoryalloy wire to make an adaptive variable camber wing，which could quickly change its shape，but could not perform highly frequent alteration because of its resilience depend en ton the heat exchange with the outside environment。Compliant mechanism is a kind of one-piece flexible structure，which can transfer motion and power through its own elastic deformationIt is not only flexible enough to deform，but also has enough stiffness to withstand external loadsThanks to its jointfree nature，it does not have the trouble some problems confronted by conventional mechanism such as friction，lubrication，noise and recoiling，thereby achieving smooth shape changing.In 1 994，Kota ，a professor from University of Michigan，firstly pointed out that compliant mechanism could be used to control static shape changing under the sponsorship of the Air Force Of ice of Scientific Research in USASaggere and Kotasuggested a new method to design compliant adaptive structures，which made the least square errors between the shapechanged curve and the target curve as the objective function for optimizationBased on their work，Lu put forward a load pathrepresentation methodHowever, her work was limited to only linear analysis under consideration of nodal loadsGood from Virginia Polytechnic Institute of State University used the compliant mechanism and the Moving Asymptotes method to design the fuselage tail within the allowable range of its tip maximal deflectionKota and He trick in2004 designed a compliant trailing edge on the baseof the F16s data，which can change from 0。to 15。and obtained a patentCampanile from German Aerospace Center presented a modal procedure to design synthetic flexible mechanisms for airfoil shape control，and pointed out that the future research should take into account the air load and the geometric nonlinearityBuhl from Riso National Laboratory of the Wind Energy Department in Denmark used the SIM P method and geometrically nonlinear finite element method to design compliant trailing edge flapsFlxSys Inc in 2006 produced an adaptive compliant wing，which stood the test on the White Knight airplaneThe results 13indicated that the compliant trailing edge could change+10 In China，the research of adaptive wing has been concentrated on smart material and conventional mechanismFew people，it seems，have worked on designing adaptive wings with the compliant mechanismYang is an exceptionHe analyzed the active aeroelastic wings based on the aeroservoelasticity technologyChen and Huang separately investigated the morphing of the compliant leading edge from the viewpoints of discreteness and continuity.This paper presents a method to design the shape changeable structure by MATLAB and ANSYS associated with distributed compliant mechanism on the base of the ground structure approach and genetic algorithm (GA)taking into account the external distributed loads and geometric nonlinearity.2 Optimization Process:21 Defining the trailing edge model and objective functionAs shown in Fig1，both curves represent two ideal shapes of the trailing edge in the different flying statesOne side point)of the structure is supposed to be fixed，and the other side point) to be sliding horizontally. Firstly, the design domain should be defined by the initial curve shapethe input location and the boundary conditionsThenit is divided with abeam element network simulating the birds feather as shown in Fig2This is termed the partial ground structure method.Fig1 Initial shape and target shape Fig2 Discretization of the design domain The simplest and most effective way to manufacture the planar compliant mechanism is to use wirecutting technologyIn the optimization program，all the elements are of rectangular beams with the same width equal to the thickness of the material，every beams height being a design variable14In order to make the structures deformation come close to the target shape curve， the least square error(LSE)between the deformed curve and the target curve is defined as the objective functionLSE is the sum of squares of position differences of various points along the curves Its expression is where I (=1， 2，P)is the number of the points along the curves ，P is the total number of points and are the coordinates of it h node on the target and deformed boundary curve respectivelyThe constraints are Where J (=1， 2， )is the number of elements，miss the tota1 number of elements，h i the dimension variable，h min and hmax are the lower and upper bounds of the element beam height for all elements with the value dependent on manufacturing，h b the height of the boundary elements， the maximumnoda1 deformation of the nodes on the curve boundary when the input point is inactive，and should be smaller thandto ensure structure stiffness，d the allowable maximum displacement when the input point is inactive，Omax the maximum stress of al1 the elements which must be smaller than Tj to prevent yielding，T j the topology variable equal to 1，or else0 when the element is eliminated22 GA optimizationGA is an optimization method which simulates the heuristic selection rule in nature， where the fittest living things have the most chance to survive，but the inferior ones also have the opportunity to exist Different from the continuous optimization method，it does not require the gradient-based information of the objective function.15Every element could be expressed as a topology variable and a dimension variable Therefore，each individua1 could be coded as followswhere ，2 is the number of elements except the boundary onesWith the same heights，the boundary elements throughout the optimizing process arerepresented by only one variable，h b.The fitness is the criterion of the GA optimization It could be transformed from the objective function into where is a coefficient deciding the compulsive selection of the betterindividua1The smaller the value，the more different would be between the two individualsfitness thus increasing the compulsiveness of choosing the individual of higher fitnessThe selection of control parameters plays an important role in the convergence of the GAGenerally speakingthe cross probability ranges 040099；the mutation probability is 0000 01-001and the number of individuals 1 0200The variable would be updated through the crossover and mutation，so the possible design could generate in the GA process23 Finite element analysis(FEA)Because of the limited design variables and the target function，the optimization module of FEA software could not be used to design the compliant morphing mechanismTherefore ，this paper programmed the GA in MATLAB and the FEA in ANSYSIn the FEA，taking only account of geometric nonlinearities and the material being of linear elasticity, ANSYS could solve the node displacements and the element stressesThen by deleting the elements with low stress，the fitness could be calculatedFig3 shows the detailed process 16Fig3 Flowchart of the structural optimization program24 Second optimizationAlthough the GA could optimize the topology and dimension simultaneously in a large solution space，the dimension usually could not directly converge to the optimizationIn order to solve this problem，after the GA，the Direct Search methodshould be used to find the best values of the input displacement and the dimensions of the elements which remain in the results after the GAFor morphing of compliant mechanism，Fig3describes the whole optimization processIt mainly contains initialization of the design domain，FEA ，GA optimization and second optimization.3 Presentation of Results:Adopted from Ref，the sizes of the initial and the target trailing edge are reduced by sixty percent ，I1ab1e 1 lists the design parameters.Because the displacement is used as the input，the nonlinear analysis could hardly converge and the stress of the initia1 solutions is very largeWhich should be considered after thirtieth generation.17Table 1 Design parameters Fig4 and Fig5 illustrate the results from the GA optimization and the second optimization respectivelyFig4 Results after the GA optimization Fig5 Results after the second optimizationForm Table 2，it could be found that through the second optimization of the input displacement and the dimension，the LSE is reduced by 1352 8mmand improved by 313 The altered angle is increased by 1049 3Table 2 Results after the two optimization 18Fig6 Stability of final optimal structureFig6 shows the influences of the parameters when the outside distributed pressure load changes from 0 to 1 0 Nmm and the input displacement remains 1 1389 7 mm on the optimal structureIt could be seen that the optimal structure has a good stability if the load is kept in the range Of 05 NmmAs the external load exceeds 5 Nmm，the max stress is likely to exceed the yield stress19Because this optimization program is based on the M ATLAB and ANSYSin order to verify the results an attempt is made to introduce the analytical results of the optimized structure into ANSYS and PATRAN respectively, and then a comparison is made between themAs shown in Fig7 and Fig8，the two altered shapes are in good agreement：for in ANSYS the tip displacement is 5497mm and in PATRRAN 5450mmThe minor d