08_Design Formula for Sierpinski Gasket
ART MX821八路混音器音频路由器操作手册说明书
ART – MX821Eight Channel Mic/Line Mixer with Tone ControlOPERATION MANUALINTRODUCTIONThe MX821 is a versatile rack mount mixer combining eight independent input channels into a single mono line level mixed output.Essential features include: XLR microphone and 1/4 inch line level inputs, Level and Tone controls, and switch-selectable +48 Volt phantom power on each channel. Main output is balanced low impedance. Additional Pre-Fade output and Aux Buss input jacks allow patching of multiple MX821’s when more channels are needed.Built in power supply and single high 19-inch rack mount format allows for easy installation and reliable long-term operation.FEATURES:•Eight Independent Input Channels•Level and Tone Controls on each Channel•Balanced XLR Microphone and 1/4-inch Unbalanced Line Inputs on each Channel•Full +48 Volt Phantom Power on XLR inputs with DIP Switch for each Channel•Balanced TRS 1/4-inch Main Output Jack with Master Level Control•RCA-type Pre-Fade Output Jack (Not Affected by the Master Level Control)•RCA-type Aux Buss Input Jack for Channel Expansion•Solid Single High Rack Mount Chassis w/ Built In Power SupplySPECIFICATIONS:•Input Connections: XLR-F balanced (8), 1/4-inch unbalanced (8), RCA (1)•Output Connections: 1/4-inch balanced TRS (1), RCA (1)•Input Impedance: 2K Ohms Mic, 20K Ohms Line, 10K Ohms Aux. Bus In•Output Impedance: 200 Ohms balanced Main Out, 100 Ohms Pre-Fade Out•Maximum Input Level: -6dBu Mic, +18dBu Line•Maximum Output Level: +27dBu balanced, +21dBu unbalanced•Phantom Power: +48 Volts DC (regulated/low noise)•Maximum Gain: 65dB/39dB mic/line•Signal to Noise Ratio: >90dB typical•THD: <0.01% typical•Equivalent Input Noise -108dBu typical•CMRR: >52dB typical•Phase Shift: <10 degrees, 20Hz - 20kHz•Power Requirements: 120VAC / 50-60Hz, or 230VAC / 50 Hz, 15VA•Dimensions: (HxWxD in) 1.75 x 19 x 6•Dimensions: (HxWxD mm) 44.5 x 483 x 152•Weight: 6.3 lbs. (2.9kg)OPERATIONa) Verify proper voltage selection on the IEC style power connector for your location. Connect the AC cord to a grounded AC outlet.b) Connect low-impedance microphones to the XLR sockets.c) Connect shielded unbalanced line inputs to the ¼” inch jacks.d) For microphone channels requiring phantom power (for condenser microphones) set the appropriate PHANTOM POWER DIP switches in the down position. Do not engage phantom power on a channel unless it is for a condenser microphone.e) Switch on the power and set the MASTER LEVEL to the ½ way setting, then adjust the channel LEVEL controls as required for the best mix and level. Adjust the channel TONE controls for the desired balance of lows and highs. Center setting is neutral.f) Re-adjust the MASTER LEVEL as required for best overall signal level.g) To patch two MX821’s for 16 channel input operation, run a shielded, unbalanced RCA type patch cable from the PREFADE OUT jack on mixer A to the AUX BUS INPUT jack on mixer B. Note that only the MASTER LEVEL on mixer B will now function.h) To convert the ¼” line input on any channel to a direct line output for that channel, unplug the MX821’s AC cord from the wall and remove the top cover. Inside you will see a row of jumpers. Move the jumper for the desired channel to the left, when viewed from the front. Now that channel’s line input is converted to a direct line output and may be connected to the input of another mixer. Any converted channel is still included in the main output mix as well. Do not connect the output of a mixer or any other signal source to the ¼” jack on this channel now or the channel may sustain damage. Be sure to replace the lid before plugging the unit back into the AC socket.WARNINGSAll operating instructions should be read before using this equipment.To prevent the risk of electrical shock, do not remove the cover.There are no user-serviceable parts inside. Please refer servicing to a qualified service technician.Do not expose this unit to rain or moisture or to heat sources such as radiators, stoves, or other items that generate excessive heat.This unit should be cleaned only with a damp cloth. Do not get moisture inside the unit.When moving this equipment, it should be placed in its original carton and packing, to reduce the risk of damage in transit.WARRANTY INFORMATIONLimited WarrantyApplied Research and Technology will provide warranty and service for this unit in accordance with the following warrants:Applied Research and Technology, (ART) warrants to the original purchaser that this product and the components thereof will be free from defects in workmanship and materials for a period of three years from the date of purchase. Applied Research and Technology will, without charge, repair or replace, at its option, defective product or component parts upon prepaid delivery to the factory service department or authorized service center, accompanied by proof of purchase date in the form of a valid sales receipt.Exclusions:This warranty does not apply in the event of misuse or abuse of the product or as a result of unauthorized alterations or repairs. This warranty is void if the serial number is altered, defaced, or removed.ART reserves the right to make changes in design or make additions to or improvements upon this product without any obligation to install the same on products previously manufactured.ART shall not be liable for any consequential damages, including without limitation damages resulting from loss of use. Some states do not allow limitations of incidental or consequential damages, so the above limitation or exclusion may not apply to you. This warranty gives you specific rights and you may have other rights, which vary from state to state.For units purchased outside the United States, an authorized distributor of Applied Research and Technology will provide service.SERVICEThe following information is provided in the unlikely event that your unit requires service.1) Be sure that the unit is the cause of the problem. Check to make sure the unit has power, all cables are connected correctly, and the cables themselves are in working condition. You may want to consult with your dealer for assistance in troubleshooting or testing your particular configuration.2) If you believe the ART unit is at fault, go to . You may contact Customer Service for more assistance, or directly request a Return Authorization for service in the “resources” area of the website.3) If you are returning the unit for service, pack the unit in its original carton or a reasonable substitute. The original packaging may not be suitable as a shipping carton, so consider putting the packaged unit in another box for shipping. Print the RA number clearly on the outside of the shipping box.4) Include, with your unit, a note with the RA number and your contact information including a daytime phone number, preferably attached to the top of the unit. Copyright 2010 Applied Research & Technology MX821。
Capsense 设计指南
赛普拉斯半导体 198 Champion Court San Jose, CA 95134-1709 电话(美国):880.858.1810 电话(国际):4 赛普拉斯半导体公司,2010-2012。此处所包含的信息可能会随时更改,恕不另行通知。除赛普拉斯产品的内嵌电路之外, 赛普拉斯半导体公司不对任何其他电路的使用承担任何责任。也不根据专利或其他权利以明示或暗示的方式授予任何许可。 除非与赛普拉斯签订明确的书面协议,否则赛普拉斯产品不保证能够用于或适用于医疗、生命支持、救生、关键控制或安全 应用领域。此外,对于可能发生运转异常和故障并对用户造成严重伤害的生命支持系统,赛普拉斯不授权将其产品用作此类 系统的关键组件。若将赛普拉斯产品用于生命支持系统中,则表示制造商将承担因此类使用而招致的所有风险,并确保赛普 拉斯免于因此而受到任何指控。 商标 PSoC Designer™、Programmable System-on-Chip™ 和 SmartSense™ 是赛普拉斯半导体公司的商标,PSoC® 和 CapSense® 是赛普拉斯半导体公司的注册商标。此处引用的所有其他商标或注册商标归其各自所有者所有。 源代码 所有源代码(软件和/或固件)均归赛普拉斯半导体公司(赛普拉斯)所有,并受全球专利法规(美国和美国以外的专利法 规)、美国版权法以及国际条约规定的保护和约束。赛普拉斯据此向获许可者授予适用于个人的、非独占性、不可转让的许 可,用以复制、使用、修改、创建赛普拉斯源代码的派生作品、编译赛普拉斯源代码和派生作品,并且其目的只能是创建自 定义软件和/或固件,以支持获许可者仅将其获得的产品依照适用协议规定的方式与赛普拉斯集成电路配合使用。除上述指定 的用途之外,未经赛普拉斯的明确书面许可,不得对此类源代码进行任何复制、修改、转换、编译或演示。 免责声明 赛普拉斯不针对此材料提供任何类型的明示或暗示保证,包括(但不仅限于)针对特定用途的适销性和适用性的暗示保证。 赛普拉斯保留在不做出通知的情况下对此处所述材料进行更改的权利。赛普拉斯不对此处所述之任何产品或电路的应用或使 用承担任何责任。对于可能发生运转异常和故障并对用户造成严重伤害的生命支持系统,赛普拉斯不授权将其产品用作此类 系统的关键组件。若将赛普拉斯产品用于生命支持系统中,则表示制造商将承担因此类使用而招致的所有风险,并确保赛普 拉斯免于因此而受到任何指控。 产品使用可能受适用的赛普拉斯软件许可协议限制。
布尔拉性能增强器-福特必angs GT X-管道安装说明书
NOTE: This X-Pipe is designed to replace the factory H-Pipe which may vary width dimension from center to center. You may need to loosen the (4)15mm flange nuts in front of each cat-pipe to adjust. (See Fig.4)
Borla Performance Industries assumes no responsibility for damages occurring from misuse, abuse, improper installation, improper operation, lack of responsible care, or all previously stated reasons resulting from incompatibility with other manufacturer’s products and/or systems.
It is the responsibility of the purchaser to follow all installation instruction guidelines and safety procedures supplied with your Borla Performance X-Pipe
TITLE: Ford Mustang X-Pipe Installation Instructions
PART NO. A-35627
Rev. 1 Page 1 of 4
BORLA PERFORMANCE INDUSTRIES
关于Sierpinski垫片的Hausdorff测度的上限估值
I 引言 与 预备 知 识
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IBM Engineering Systems Design Rhapsody 工具包说明书
IBM Engineering Systems Design Rhapsody Kit for DO-178B/CPlease first read document"Rhapsody Kit for DO-178B-C Overview.pdf".It describes the content of the "IBM Engineering Systems Design Rhapsody Kit for DO-178B/C".Version 1.14License AgreementNo part of this publication may be reproduced, transmitted, stored in a retrieval system, nor translated into any human or computer language, in any form or by any means, electronic, mechanical, magnetic, optical, chemical, manual or otherwise, without the prior written permission of the copyright owner, BTC Embedded Systems AG.The information in this publication is subject to change without notice, and BTC Embedded Systems AG assumes no responsibility for any errors which may appear herein. No warranties, either expressed or implied, are made regarding Rhapsody software including documentation and its fitness for any particular purpose.TrademarksIBM® Engineering Systems Design Rhapsody®, IBM® Engineering Systems Design Rhapsody® ‐ Automatic Test Generation Add On, and IBM® Engineering Systems Design Rhapsody® ‐ TestConductor Add On are registered trademarks of IBM Corporation.All other product or company names mentioned herein may be trademarks or registered trademarks of their respective owners.© Copyright 2000-2020 BTC Embedded Systems AG. All rights reserved.。
芬特(Festo)MS9-SV-G-C-V24-S-VS软启动 快排气阀说明书
to EU directive for EMC to EU directive for machinery in accordance with EU RoHS directive To UK instructions for EMC To UK instructions for machines To UK RoHS instructions Line installation
Material housing Material seals Material Piston slide Material cover Material underneath cover
Value
with accessories Optional Any 3,200 g G1/8 G1/4 G1 1 NPT Plug pattern type A to EN 175301-803 Plug to EN 175301-803 Cubic design Aluminium die cast NBR Brass Wrought Aluminium alloy PA
08/11/2023 – Subject to change – Festo SE & Co. KG
1/2
Feature
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Pneumatic connecபைடு நூலகம்ion, port 3
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08/11/2023 – Subject to change – Festo SE & Co. KG
国内外石油化工行业“行业标准”对照表----中英文对照!
1)Please find attached the list of international codes and standards to be applied for the design and manufacturing of the whole supply (doc n。
0002-00-00-000-B—G-1-43-002)随函附上全部供应材料设计和制造中应用的国际规范和标准一览表(文件号0002-00—00-000-B-G-1—43—002).Please kindly confirm compliance;moreover,please confirm that it is already included in your quotation or update accordingly。
请确认符合情况,此外,请确认其已相应包含在贵方报价或更新文件中.2)ASTM / ASME standard Materials with proper certifications (refer to attached material certificate EN 102043.1 samples) shall be provided for the whole supply materials;equivalent Chinese standard material are not accepted by our Client (except the ones listed in the attached doc n. 0002-00-00-000—B—G-1—43-002 section 3).应为全部材料提供ASTM/ ASME标准材料和适当的认证(参考随附的材料证书EN 10204 3。
1),我们的客户不接受同等的中国标准材料(随附文件号0002-00-00-000-B-G-1—43—002第3节列出的材料除外)。
Elements of Electromagnetics
Elements of Electromagnetics, 3rd Ed., Matthew N.O. Sadiku solutions manual GetSolution team Source: /Archive/Sci/sci.stat.consult/2008−03/msg00019.html•From: getsolution2008@xxxxxxxxx•Date: Sun, 9 Mar 2008 13:46:47 −0700 (PDT)Hi!We organized group was founded in 2006 from the head of the filing toreduce the suffering students in the universities to find solutions totheir books.plaese see the list of solutions manual we have to get you solutions pleaseSend a mail from your email address to the following addresgetsolution@xxxxxxxxxxx getsolution(at)our new list:Mechanics of Fluids Solutions Manual by John Ward−Smith 8 edElements of Chemical Reaction Engineering By H Fogler, 3rd edAdvanced Engineering Mathematics by Erwin Kreyszig 8ed solutionsmanual"Analysis and Design of Analog Integrated Circuits (4th Edition) Gray,Hurst, Lewis and Meyer"Analytical Mechanics:1 Solutions Manual Grant R. 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Design of variable-stiffness composite panels for maximum buckling load
Design of variable-stiffness composite panelsfor maximum buckling loadShahriar Setoodeh,Mostafa M.Abdalla,Samuel T.IJsselmuiden,Zafer Gu ¨rdal *Faculty of Aerospace Engineering,Delft University of Technology,Kluyverweg 1,2629HS Delft,The NetherlandsAvailable online 26January 2008AbstractA generalized reciprocal approximation is presented for design of variable-stiffness laminated composite panels for maximum buck-ling load.The buckling load is expanded in terms of the inverse of the stiffness tensor.For discretized panels such an approximation hasthe important property of being separable,which allows the maximization to be carried out at each discrete node separate from the oth-ers.This makes the algorithm particularly suited to parallel computations.The sensitivity analysis is performed exactly using an adjoint method,requiring only one back substitution using the already factored inplane stiffness matrix with different right hand sides to com-pute the sensitivities for all design variables.A conforming CLPT finite element is used for the buckling analysis of rectangular plates and the proposed reciprocal approximation is used to update fiber orientation angles at each finite element node.Numerical results obtained for rectangular plates show that significant improvements can be gained in the buckling load by allowing the stiffness properties to vary spatially.The case of repeated eigenvalues is handled using a dual formulation.Ó2008Elsevier Ltd.All rights reserved.Keywords:Tow-placement;Variable-stiffness panels;Buckling design;Reciprocal approximation;Adjoint sensitivity analysis1.IntroductionBuckling design of laminated composite plates is well studied in the literature [8,9,27].Grenestedt [9]used lami-nation parameters with an approximate feasible domain definition to design panels against shear buckling.In his formulation,four design variables corresponding to the bending lamination parameters over the entire domain were used to design a panel.His work was later extended by Fukunaga [8]using exact definitions for the feasible combination of lamination parameters for panels with and without shear coupling,and with two and four design variables,respectively.Liu et al.[15]showed that the feasi-ble domain of the bending lamination parameters for lay-ups with only discrete 0 ;Æ45 ,and 90°layers assumes a hexagonal shape inside the Miki Parabola,and then used it to design panels for maximum buckling load.Although significant increase in the buckling load can beobtained through tailoring laminate stacking sequence of composite panels with traditional straight fibers,the poten-tial of fibrous composites is not fully exploited.An approach for the design of panels with cutouts was first introduced in the late eighties [12]in which curvilinear fibers were suggested to improve structural response instead of straight fiber paths.The approach has been gen-eralized later by Gu ¨rdal and Olmedo [10]by designing var-iable-stiffness laminates that use continuous curvilinear fiber paths.For such variable-stiffness panels,the stiffness properties are continuous functions of position.Ideally,by steering the fiber paths the fiber orientation angle can be varied,which in turn changes the stiffness properties at each point in the panel independently.The additional freedom in locally tailoring the stiffness properties means that the performance of variable-stiffness panels can be highly improved over constant-stiffness (straight fibers)panels.However,this additional freedom comes at the price of having significantly enlarged design space as well as the complexity of maintaining uniform fibre paths.0263-8223/$-see front matter Ó2008Elsevier Ltd.All rights reserved.doi:10.1016/pstruct.2008.01.008*Corresponding author.E-mail address:z.gurdal@tudelft.nl (Z.Gu ¨rdal)./locate/compstructAvailable online at Composite Structures 87(2009)109–117Research in variable-stiffness concept has been stimu-lated by recent developments of advanced tow-placement technology[5,26].Tow-placement machines are computer numerical controlled multi-axis machines that are capable of steering multiple tows(up to32with each tow having a width of about1/8inch)along prescribed paths.Each tow can be placed at a different rate allowing a radius of curvature as low as12inches[17].Moreover,tows can be independently stopped(cut)and started permittingflexible coverage patterns to build composite panels.The idea of curvedfibers orfiber orientation angle dis-tribution has been used earlier to design composite lami-nates for maximum buckling loads.Improvements in buckling resistance of composite plates with a circular cen-ter hole was studied by Hyer and Lee[13]using curvilinear fiber format.They usedfinite difference based sensitivity analysis tofind conditions that maximize buckling perfor-mance of a plate with a central circular hole.To reduce the problem size,they use a quarter model with selected regions of straightfiber orientations.Banichuk et al.[3] used triangularfinite elements to search for optimal angles of orthotropy,which maximizes the critical buckling parameter.They performed exact sensitivity analysis for both simple and multiple eigenvalues.Their numerical results showed a significant increase in the critical buckling load just with reorientation of the orthotropic material in an optimal manner.Tatting and Gu¨rdal[25]used a two parameter based continuous curvilinearfiber path defini-tion,in whichfiber orientation angles vary linearly along the panel side,to design variable-stiffness panels with a cen-ter hole for maximum buckling load.Their study showed that up to60%improvement can be gained by optimal design of panels while complying with the existing manu-facturing techniques for curvilinearfibre paths.A so called discrete material optimization approach was used by Lund et al.[16]based on a semi-analytic sensitivity analysis to design rectangular plates for maximum buckling load.In the present study,the generalized reciprocal approx-imation approach introduced by Abdalla et al.[2]is extended to buckling design of variable-stiffness panels. In this formulation,the critical load is approximated using afirst order Taylor series expansion in terms of the point-wise compliance tensors.Such an approximation has the important property of being separable,which is highly suit-able for parallel computing.Therefore,the problem of maximizing the buckling load is reduced to a simple local optimization problem at any discretization point.For buckling analysis,a conforming bilinearfinite element is used while the sensitivity of the buckling load is performed analytically.Practical manufacturing constraint on smooth spatial variation of thefiber orientation angle has been addressed approximately by using an interpolation scheme.In the following sections,first thefinite element discret-ization of the buckling analysis is briefly discussed,then the generalized reciprocal approximation applied for maxi-mum buckling design of variable-stiffness panels is pre-sented followed by the sensitivity analysis.Stiffness smoothing(or rather compliance smoothing)scheme is introduced next,followed by design update rule for the buckling load maximization and the treatment of the mul-timodal design.Finally numerical results are provided to demonstrate the performance of the current formulation along with the potential gains in the buckling load using a variable-stiffness design compared to a constant-stiffness design.The effect of boundary conditions on the optimal buckling load are also investigated.2.Buckling analysisThe buckling loads are determined through the eigen-value problemðK bÀk K gÞÁa¼0;ð1Þwhere K b is the global bending stiffness matrix,K g is the global geometric stiffness matrix,a is the mode shape com-prising of deformation degrees of freedom,and k is load multiplier.The mode shapes are normalized such thata TÁK bÁa¼1:ð2ÞThe geometric stiffness matrix is constructed through an assembly of element geometric matrices.The stiffness matrix of each element takes the formK ge¼Àn x K xÀn y K yÀn xy K xy;ð3Þwhere n e¼ðn x;n y;n xyÞT is the vector of inplane stress resultants averaged over the element,and K x;K y and K xy are constant matrices that depend only on element geometry.The averaged inplane stress resultants can be expressed asn e¼A eÁe e;ð4Þwhere A is the inplane stiffness matrix and e is the average strain vector given bye e¼B eÁu e;ð5Þwhere u is the vector of inplane displacements,B is the average element strain displacement matrix(see Appendix for the definitions),and u e is the vector of the degrees of freedom associated with nodes connected to the e th ele-ment.The inplane displacements can be found from the solution of the inplane equilibrium equationsK mÁu¼f:ð6Þwhere f is the vector of inplane loads.3.The generalized reciprocal approximationIn the standard reciprocal approximation,a function is expanded in a Taylor series in terms of reciprocal variables [11].Reciprocal variables are traditionally defined as the reciprocals of the design variables.The reciprocal approx-imation is used extensively for truss design,in which the design variables are the cross sectional areas of the mem-110S.Setoodeh et al./Composite Structures87(2009)109–117bers.To generalize the reciprocal approximation,it is noted that the cross sectional area for trusses plays the role of the stiffness of the member.In composite panel buckling design this rule is played by the inplane and bending stiff-ness matrices A and D.The generalized reciprocal approx-imation is,therefore,obtained by expanding the objective function in a Taylor series in terms of the inverse tensor of the stiffness tensors,commonly known as the compli-ance tensors,which is denoted by R¼AÀ1and S¼DÀ1.The derivatives of the buckling load with respect to the components of the bending compliance tensor,S,for the element e can be written using the chain rule aso k o S e ¼o ko D eÁo D eo S e:ð7ÞNoting that the second term is simply the derivative of the stiffness tensor with respect to the compliance tensor,it can be shown thato k o S e ¼ÀD eÁo ko D eÁD e:ð8ÞThe same formulation applies to the derivative of the buck-ling with respect to the in-plane compliance tensoro k o R e ¼ÀA eÁo ko A eÁA e:ð9Þ4.Sensitivity analysisThe sensitivity of the critical eigenvalue k cr to a change in a design variable which is generically denoted by b is considered here.The variable b is assumed to affect only the local stiffness properties of a single element i.The expression of the sensitivity can be written as[11]d k d b ¼k a TÁd K bd bÀkd K gd bÁa:ð10ÞThe sensitivity value in(10)is composed of two terms.The first term depending on the derivative of the bending stiff-ness is local in the case when b is linked to the stiffness of a single element.By local it is meant that this term can be evaluated using information from a single element,viz.S b1 a TÁd K bd bÁa¼a TiÁd K bid bÁa i:ð11ÞThe second term in(10)is not necessarily local.This is due to the fact that even when the stiffness of a single element is altered,the distribution of the inplane loads is altered for all elements and thus the geometric matrices of all element would change.In the following,an efficient way for the evaluation of this term is described.Substituting from(3)into(10)and rearranging the terms S b2is defined asS b2 a TÁd K gd bÁa¼ÀXes TeÁd n ed b;ð12Þwhere the vector s e can be calculated locally ass e¼a Te ÁK xÁa e;a TeÁK yÁa e;a TeÁK xyÁa eÀÁT:ð13ÞThe derivative of the inplane stress resultants can be ob-tained by differentiation of(4)asd n ed b¼d A ed bÁe eþA eÁd e ed b:ð14ÞThus,the sum in(12)can be decomposed into two terms corresponding to the two terms in(14).Thefirst term can be evaluated locally since only the inplane stiffness ma-trix of the i th element depends on b.The second term in-volves the derivative of the average strain of an arbitrary element with respect to the change of stiffness of the i th ele-ment and is not localS b2¼Às TiÁd A id bÁe iÀXes TeÁA eÁd e ed b:ð15ÞTo evaluate the second term above,which is denoted by S b22in(15)term,(5)is differentiated with respect to b to obtaind e ed b¼B eÁd u ed b:ð16ÞThus the strain term S b22simplifies toS b22¼Àg TeÁd u ed b;ð17Þwhere the vector g is assembled from element contributionsge¼B TeÁA eÁs e:ð18ÞThe derivative of the inplane displacement vector is ob-tained by differentiation of(6)asK mÁd ud b¼Àd K md bÁu:ð19ÞDefining the adjoint displacement vector v as the solution of the problemK mÁv¼Àg:ð20ÞThe strain term can be simplified toS b22¼Àv TÁd K md bÁu e;ð21Þwhich can be also evaluated locally.Thus,all the calculations required to evaluate the sensi-tivity of the buckling load with respect to local change of stiffness of the i th element can be calculated using informa-tion at the element level.The global redistribution of loads is accounted for totally through the evaluation of the adjoint displacement vector v.Substituting the above sensi-tivity equations back to(10),d kd bcan be written asd kd b¼k a TiÁd K bid bÁa iþk2s TiÁd A id bÁe iþv TiÁd K mid bÁu i:ð22ÞRecalling Eqs.(8)and(9),the element sensitivities is decomposed into two separate bending and membrane parts as follows(see the Appendix for more details on the element matrices):S.Setoodeh et al./Composite Structures87(2009)109–117111/ðbÞab eÀo ko S eab¼k D br D qa a TeÁd K bed D qrÁa eð23Þand/ðmÞab eÀo ko R eab¼k2A br A qa s TeÁd A ed A qrÁe eþv TeÁd K med A qrÁu e:ð24Þ5.Reciprocal interpolationAn important requirement in the design optimization of variable-stiffness panels is to ensure the continuity of the distribution of thefiber orientation angles.Traditionally, design variables are linked to element properties.This is the intuitive approach suggested by the use of thefinite ele-ment method for analyzing the response of a structure. When independent design variables are linked to element properties to simulate the variable-stiffness concept,there is no guarantee that the distribution of the design variables is going to be smooth.This issue is well known and espe-cially severe in topology optimization,where it results in checkerboard patterns.To ensure the smoothness of the optimalfiber orienta-tion angles distribution,following the methodology intro-duced in[1,20,22]is proposed here,where the design variables are associated with nodes rather than elements. For the construction of element matrices,the variation of the stiffness properties over the element is required.The simplest rule is to use an average value over the element. The use of an average value simplifies the construction of element matrices.It also simplifies the calculation of sensi-tivities with respect to nodal variables.The key-point in introducing average element properties is that instead of defining the element stiffness tensor as the average of the stiffness tensor at the nodes,the element compliance tensor is calculated as the average of the com-pliance tensors at the nodes.This approach,first intro-duced in[1,22]was shown to be effective in producing smooth distribution of design variables for topology opti-mization problems.In this paper,the work of[1,22]is expanded to the case of composite stiffness properties design rather than density measure.The average element compliances are given byðR e;S eÞ¼Xc2I ew e;cðR c;S cÞ;ð25Þwhere superscript c denotes node numbers and I e is the set of nodes connected to element e.The sum is weighted by integration weighing coefficients w c such that for a smooth function f,Z X e f d X%ZX ed XXc2I ew e;c f c:ð26ÞThe effective element stiffness tensor is calculated as the in-verse of the average compliance tensor given by(25).6.Design update ruleThe reciprocal interpolation scheme introduced in Sec-tion5fits nicely with the generalized reciprocal approxima-tion introduced in Section3.In this section,an approximation of the eigenvalue of the panel is obtained in terms the nodal values of the compliance tensors R and S,and derive the corresponding optimality conditions.It is presumed here that an initial design R c and S c are known together with the corresponding mode shape a. The eigenvalue of the system is expanded in afirst order Taylor expansionk% kþo keabðR eabÀ R eabÞþo keabðS eabÀ S eabÞ;ð27ÞSubstituting the expressions for the eigenvalue sensitivity (23)and(24),and the interpolation formulas(25)into (27),the following compact form of the generalized reci-procal approximation in terms of nodal values is obtained:k%ð kþUðmÞcabR cabþUðbÞcabS cabÞÀUðmÞcabR cabÀUðbÞcabS cab;ð28Þwhereð/ðmÞc;/ðbÞcÞ¼Xe2I cw e;cð/ðmÞe;/ðbÞeÞ;ð29Þin which I c is the set of elements connected to node c.The generalized reciprocal approximation(28)has the important property of being a separable approximation [11].Each term in the summation depends only on the com-pliance tensor at one node,and hence only on thefiber ori-entation angles at this node.In order to update the design for the next iteration,the reciprocal approximation of the eigenvalue is maximized.Because of separability,the max-imization can be carried out at each node separate from the others.This makes the algorithm particularly suited to par-allel computations.The design update rule for the nodal values of thefiber orientation angles can thus be expressed asminh cðUðmÞcabR cabðh cÞþUðbÞcabS cabðh cÞÞ...no sum on c;ð30ÞIn numerical implementation of the update rule a move limit of2.5°is used to stabilize the iterative design process. Note that the design update involves a minimization prob-lem because of the minus sign in(28).If the optimization is carried out for a constant-stiffness panel,the compliance tensors of all nodes are identical,and the update rule is no longer dependent on the node num-ber.Thefiber orientation angles are thus updated asminh cXcðUðmÞcabR abðh cÞþUðbÞcabS abðh cÞÞ:ð31Þ7.Multimodal designThe multimodal case can be handled in a similar fashion to the method employed by Olhoff[19]where the problem is regularized by introducing an independent parameter b112S.Setoodeh et al./Composite Structures87(2009)109–117max bs :t :b 6a i k i ;ð32Þwhere a 1¼1,and a i 61;i ¼2;3;....The purpose of the a i coefficients is to be able to impose mode spacing constraints.This can be particularly useful when modal interaction leads to unstable post buckling behavior.The problem described by (32)can be solved using the dual method by Fleury [6].The Lagrangian is written as,L ¼X l i À1 b ÀX a i l i k i ;ð33Þwhere l i are Lagrange multipliers.The complementary Lagrangian is defined as the minimum over the design vari-ables of the Lagrangian.This leads to two conditions,L C ¼min ÀXa i l i k i ð34Þand Xl i ¼1:ð35ÞIt is noted that the auxiliary variable b is now eliminated from the formulation.The Lagrange multipliers are determined through the dual problem,max L C ;ð36Þsubject to (35),and non-negativity of the Lagrange multi-pliers l i .The gradient of the complementary Lagrangian with respect to the Lagrange multipliers is readily available aso L Co l i¼Àa i k i :ð37ÞThe Lagrange multipliers can now be solved for by using any gradient based optimization routine to solve the dual problem.1This can be efficiently accomplished since the number of the Lagrange multipliers is small (the number of considered modes).The evaluation of the complemen-tary Lagrangian requires the update of all design variables through the minimization problem (34).When the proce-dure is applied to the reciprocal approximation of the eigenvalues rather than the actual objective,the evaluation of the complementary Lagrangian is reduced to the solu-tion of a separable set of optimization problems similar to the uni-modal case.8.Numerical resultsBased on the design formulation presented,a Fortran code was implemented.The design and analysis cycle is repeated until the relative change in the buckling load is smaller than a given tolerance as mentioned earlier.In order to stabilize this iterative process,a move limit of 2.5°is used in design update rule.The mode spacing coef-ficients in Eq.(32)are set to a i ¼1:0;i ¼1;2;3;...with three modes considered in all of the examples.The buckling load P of a rectangular plate of dimensions a Âb is non-dimensionalized using the following relation N ¼12a 2p 2Q 22h P ;ð38Þwhere h is the total laminate thickness and Q 22is the re-duced stiffness transverse to the fiber.In the following examples,symmetric rectangular plates are considered with different boundary conditions and different loadings (see Fig.1).First design of single layer uni-directional constant-stiff-ness panels is considered based on the design update rule (31).Numerical results for design of panels with different aspect ratios against shear buckling ðN xx ¼N yy ¼0Þare given in Table 1.As this table shows,there is a good agr-ement between the present results and those reported by Grenestedt [9].The buckling loads for the Grenestedt results are computed using the present finite element code resulting in differences less than %0.15with the present optimal buckling loads.The difference in the optimal orien-tation angle is attributed to the fact that the buckling load1DNCONG of IMSL version 3.0is used in the present study.Table 1Design of constant-stiffness single layer plates with different aspect ratios for shear buckling ðN xx ¼N yy ¼0Þa =b Present Grenestedt [9]%Differenceh °N xy h °N xy 1.044.7104.6545.0104.6À0.011.249.089.4849.489.480.001.553.679.1354.479.130.001.756.075.9956.675.980.012.057.373.4358.073.420.012.557.169.8357.869.820.023.058.968.2159.868.180.054.059.566.5760.766.480.14S.Setoodeh et al./Composite Structures 87(2009)109–117113is ratherflat close to the optimal design[9]and differences in the analysis tools used in the two studies.To validated the formulation for multilayer symmetric composite panels for uni-axial and bi-axial loading the results are compared to those found by Narita and Turvey [18],who implemented an optimization routine using a lay-erwise approach.As can be seen from Table2,the results correlate exceptionally well,differing no more that0.5%.The results of the proposed approach are further com-pared to those of Erdal and Sonmez[4]who optimized a 64ply balanced symmetrical rectangular plate with simplesupports using simulated annealing.The optimal results found by the present formulation are compared to the best three designs found by Erdal and Sonmez in Table3.The difference in optimal buckling load of approximately3% can be attributed to the continuous nature of the presented formulation as opposed to the discrete set of ply angels used in Ref.[4].The last row shows the optimal buckling load when designing the plate using the closed form solu-tion of simply supported plates and lamination parameters [14].The results are obtained using the reciprocal approx-imation following the formulation presentated in[14].It is to be seen that the values of the optimum lamination parameters are quite different from the corresponding val-ues at the continuous and discrete optima.On the other hand,the value of the optimum buckling load is fairly close.This can be explained by the relative insensitivity of the buckling load to changes in lamination parameters in certain directions[9].Now to demonstrate the performance of the proposed design methodology for design of variable-stiffness panels, design of a rectangular composite panel as depicted in Fig.1is considered with the following orthotropic material properties:E11E22¼25;G12E22¼0:5;m12¼0:25:Optimal buckling loads for single layer constant-stiffness and variable-stiffness designs are listed in Table4for sim-ply supported and clamped plates.The corresponding var-iable-stiffness designs are depicted in Fig.2a and b. Optimization process for these examples was started from a design with allfibers in the90°direction(direction of the loading).Similar designs were also reported in Lund et al.[16].For both boundary conditions considered sub-stantial improvement in the buckling load of the variable-stiffness panels with respect to their constant-stiffness coun-terparts were observed.Also note that in the case of simplyTable2Comparison of the critical buckling factor of an8-layer,symmetric constant-stiffness square panel(a/b=1)k h1h2h3h4Uni-axial,simply supportedPresent320.9744.96À44.93À44.93À44.93 Narita[18]321.0045.00À45.00À45.00À45.00 Uni-axial,clampedPresent687.56À0.01À0.01À0.01À0.01 Narita690.900.000.000.000.00 Bi-axial,simply supportedPresent160.4944.92À44.96À44.96À44.96 Narita160.5045.00À45.00À45.00À45.00 Bi-axial,clampedPresent347.29À0.0990.0090.00À90.00 Narita348.000.0090.0090.0090.00 Table3Comparison of critical buckling factor of a64-layer,simply supported symmetric constant-stiffness rectangular panel(a/b=2)k W1W3 Present4097.3À0.06690.0243 Erdal and Sonmez[4](1)½9010=Æ452=902=Æ453=902=Æ454 s3973.0À0.06190.0405(2)½908=Æ45=902=Æ45=902=Æ45=902=Æ456 s3973.0À0.06190.0405(3)½9010=Æ45=902=Æ457=902=Æ45s 3973.0À0.06190.0405Optimal lamination parameters(W1;W3)[14]4102.3À0.79480.2660Table4Design of single layer square panels for uni-axial buckling;cs:constant-stiffness;vs:variable-stiffness(a=b¼1,N xx¼N xy¼0:,30Â30nodes) Design N1N2N3%Improvements Simply supportedcs½h 28.5050.98102.75–vs½h 75.6876.6492.07165.58 Clampedcs½h 106.87140.32208.52–vs½h 136.46160.22203.7627.70114S.Setoodeh et al./Composite Structures87(2009)109–117。
卡梅伦液压数据手册(第 20 版)说明书
iv
⌂
CONTENTS OF SECTION 1
☰ Hydraulics
⌂ Cameron Hydraulic Data ☰
Introduction. . . . . . . . . . . . . ................................................................ 1-3 Liquids. . . . . . . . . . . . . . . . . . . ...................................... .......................... 1-3
4
Viscosity etc.
Steam data....................................................................................................................................................................................... 6
1 Liquid Flow.............................................................................. 1-4
Viscosity. . . . . . . . . . . . . . . . . ...................................... .......................... 1-5 Pumping. . . . . . . . . . . . . . . . . ...................................... .......................... 1-6 Volume-System Head Calculations-Suction Head. ........................... 1-6, 1-7 Suction Lift-Total Discharge Head-Velocity Head............................. 1-7, 1-8 Total Sys. Head-Pump Head-Pressure-Spec. Gravity. ...................... 1-9, 1-10 Net Positive Suction Head. .......................................................... 1-11 NPSH-Suction Head-Life; Examples:....................... ............... 1-11 to 1-16 NPSH-Hydrocarbon Corrections.................................................... 1-16 NPSH-Reciprocating Pumps. ....................................................... 1-17 Acceleration Head-Reciprocating Pumps. ........................................ 1-18 Entrance Losses-Specific Speed. .................................................. 1-19 Specific Speed-Impeller. .................................... ........................ 1-19 Specific Speed-Suction...................................... ................. 1-20, 1-21 Submergence.. . . . . . . . . ....................................... ................. 1-21, 1-22 Intake Design-Vertical Wet Pit Pumps....................................... 1-22, 1-27 Work Performed in Pumping. ............................... ........................ 1-27 Temperature Rise. . . . . . . ...................................... ........................ 1-28 Characteristic Curves. . ...................................... ........................ 1-29 Affinity Laws-Stepping Curves. ..................................................... 1-30 System Curves.. . . . . . . . ....................................... ........................ 1-31 Parallel and Series Operation. .............................. ................. 1-32, 1-33 Water Hammer. . . . . . . . . . ...................................... ........................ 1-34 Reciprocating Pumps-Performance. ............................................... 1-35 Recip. Pumps-Pulsation Analysis & System Piping...................... 1-36 to 1-45 Pump Drivers-Speed Torque Curves. ....................................... 1-45, 1-46 Engine Drivers-Impeller Profiles. ................................................... 1-47 Hydraulic Institute Charts.................................... ............... 1-48 to 1-52 Bibliography.. . . . . . . . . . . . ...................................... ........................ 1-53
ProSystem fx Engagement到Workpapers CS数据转换信息Kit说明书
Information Kit for Conversions from ProSystem fx Engagement to Workpapers CSThis document provides information about the data converted from ProSystem fx® Engagement to Workpapers CS™.ContentsWhat to expect from the data conversion (2)Conversion considerations and recommendations (2)Installing the conversion program (2)Converting the client data before import into Workpapers CS (2)Data transferred during conversion (4)Chart of Accounts and balances (4)Grouping schedules (5)Transactions (5)Engagement-related data transferred during conversion (6)Engagement information (6)Folder information (7)Workpaper information (7)ProSystem fx Engagement Excel and Word demographic formulas (7)ProSystem fx Engagement Excel and Word link formulas (8)Conversion notes and exceptions (8)Items not converted (8)Data Conversion Report (9)Getting help (9)Help & How-To Center (9)Product support (9)What to expect from the data conversionThe overall objective of the data conversion from ProSystem fx Engagement is to provide accurate, comprehensive Workpapers CS data to help you move forward with Workpapers CS.Important!Due to differences between applications, some data must be modified during the conversion process and some data cannot be converted. Additions and/or modifications may be required to exactly duplicate engagement and workpaper information in Workpapers CS after the conversion.Conversion considerations and recommendationsPlease review the following before beginning the conversion process.▪We recommend that you convert a smaller, easy-to-process client first. This will help you become familiar with the conversion options in Workpapers CS.▪Some data items from ProSystem fx Engagement are not converted because there is no exact equivalent in Workpapers CS.Installing the conversion programClick this link to download a ZIP file and install the ProSystem fx Engagement to Workpapers CS conversion utility.Converting the client data before import into Workpapers CS Important! When you convert large or complex sets of engagement files for a ProSystem fx Engagement client, you should allow a significant amount of time for the conversion and import. Please wait for the process to be completed before converting another client.After installing the ProSystem fx Engagement to Workpaper CS conversion program, use the following steps to create the converted data files for import into Workpaper CS.The conversion process does not modify existing client data in ProSystem fx Engagement. However, we strongly recommend that you create a backup of the original client before you process any clients.1. Verify that the ProSystem fx Engagement binder has been synchronized with the Local File Roomand that any instances of this binder or workpapers are closed on your workstation.2. To start the conversion program, right-click the CS Data Conversions icon on your desktop andchoose Run as Administrator. If you did not install the shortcut, click Start on the Windows taskbar and then choose All Programs > CS Professional Suite > CS Data Conversions.3. In the Select competitor field, select ProSystem fx from the drop-down list.4. In the Select the export location for the converted files field, click the Browse button to browse to thelocation where the import files should be placed until imported into WorkpaperCS.5. Click Start conversion.6. If prompted to close all open sessions of Word® and Excel®, close those sessions.7. If prompted to select your user, select the login for the Local File Room for which you want to convertdata. This dialog will open only if multiple logins exist on the workstation.8. In the Processing Type dialog, click either Single or Multiple. Single converts just one client at a timeand allows for greater customization. Multiple allows for multiple clients, but the application makes more assumptions about the clients during the conversion.9. In the Select a Client dialog or Select client(s) dialog, select the client(s) you want to convert, andclick Continue.Note: This dialog lists all available clients for conversion from ProSystem fx Engagement. Yourselection of Single or Multiple in step 8 determines whether you can select one or multiple clients. 10. In the Engagement selection dialog, which lists all of the binders / engagements for the selectedclient(s), select an engagement type for each binder you want to convert, and then click Continue. 11. If you selected a single conversion, an optional Trial Balance selection dialog may open if multipleTrial Balances existed in ProSystem fx Engagement. Workpapers CS supports only one Trial Balance per engagement. Select the desired Trial Balance.If you selected multiple conversions, the last accessed Trial Balance will be used.12. Click Continue.13. In the Account classification selection dialog, select the ProSystem fx Engagement group thatcontains the account classification you want to use in Workpaper CS.Note: If you click Skip, the program will not convert any Account Classifications for the Trial Balance Accounts.14. In the Tax group selection dialog, select the set of tax codes to convert for your Trial Balance.If you selected multiple conversions, the last tax year will be used.15. Click Continue to begin the data conversion process, and then follow the prompts that appear on thescreen.16. At the prompt indicating the conversion process is complete, click OK to begin importing theconverted data into Workpapers CS.17. In Accounting CS, choose File > Import > ProSystem fx Engagement to open the ProSystem fxEngagement conversion wizard.18. Source Data: Select the location where your ProSystem fx Engagement export files are stored andclick Next.19. Source Data - Clients: Mark the checkbox next to the ProSystem fx Engagement client—or multipleclients—that you want to convert, and then click Next.20. Staff: Select the Accounting CS Workpapers staff member—or multiple staff members—to map to foreach corresponding ProSystem fx Engagement staff in the list.Note:If the appropriate staff member is not available from the drop-down list in the Accounting CS Staff column, exit the wizard and add that staff member in the Setup > Firm Information > Staffscreen, and then restart the conversion process.21. Click Finish to complete the conversion.Data transferred during conversionThe following tables detail the ProSystem fx Engagement data that converts to Workpapers CS.Chart of Accounts and balancesProSystem fx Engagement menu navigation andfield name Workpapers CS menunavigation and field nameComments and additionalinformationTrial Balance > Chart ofAccountsActions > Enter Trial BalanceAccount # Account numberDescription DescriptionReport ReportBudget BudgetProposed PotentialUNADJ Unadjusted Unadjusted balance is convertedonly for the current period.ADJ Adjusted Prior-year and prior-periodbalances only.FTAX Tax Prior-year and prior-periodbalances only.OBAL1 Other Prior-year and prior-periodbalances only.Trial Balance > AccountGroupings > Tax CodeAccount GroupingTax Code Tax Code Tax codes and tax codeassignments for clients with ayear end of 2012 or later.menu navigation andfield namenavigation and field name informationTrial Balance > AccountGroupings > Group AccountGrouping > AdvancedAccClass RatioClass Classification codeClassification subcodeIn ProSystem fx Engagement,classification and ratios are seton a group-by-group basis.During the conversion process,you will be asked from whichgroup we should pullclassification and ratios.Grouping schedulesProSystem fx Engagement menu navigation andfield name Workpapers CS menunavigation and field nameComments and additionalinformationTrial Balance > AccountGroupings > Group AccountGroupingEnter Trial Balance > Account Groupings Account group name GroupingCode CodeCode Description Code DescriptionSubcode SubcodeSubcode Description Subcode DescriptionTransactionsProSystem fx Engagement menu navigation andfield name Workpapers CS menunavigation and field nameComments and additionalinformationTrial Balance > Journal EntrySummaryActions > Enter Transactions JE# ReferenceDescription DescriptionAdditional Distributions (Account, Amount, Description) Distributions (Account, Account Description, Amount)menu navigation andfield namenavigation and field name information Reversing journal entry Auto-reverse next periodType:Adjusting Journal Entries Reclassifying Journal Entries Federal Tax Journal Entries Other Journal Entries1 Proposed Journal Entry Type:AdjustingReclassifyingTaxOtherPotentialJournal entries are posted to thespecific engagement for whichthe entries were intended.Engagement-related data transferred during conversionThe following information is provided to identify ProSystem fx Engagement items that are automatically converted to Workpapers CS items.Engagement informationProSystem fx Engagement menu navigation andfield name Workpapers CS menunavigation and field nameComments and additionalinformationBinder Properties Engagement PropertiesName Engagement binder name If you convert multiple binders fora single client, the binders musthave a unique name.Type Type You must select the newWorkpapers CS type during theconversion.Entity In the ProSystem fx Engagementconversion, Entity is determinedby the selection on the TaxGroup selection screen. Thisdata is mapped to the Client >Accounting information tab. Period sequence Period FrequencyBinder Index View Binder TreeEngagement tree structure Engagement tree structureFolder informationProSystem fx Engagement menu navigation andfield name Workpapers CS menunavigation and field nameComments and additionalinformationTab Properties Engagement tree structureIndex # Folder name Index # and Name are combinedto comprise the Workpapers CSfolder name.Name Folder nameWorkpaper informationProSystem fx Engagement menu navigation andfield name Workpapers CS menunavigation and field nameComments and additionalinformationWorkpaper Properties Workpaper PropertiesName NameIndex # ReferenceSign Off: Preparers Preparer You can rename Preparer,Reviewer, and Reviewer 2names in Workpapers CS, ifdesired.Sign Off: 1st Reviewers Reviewer You can rename Preparer,Reviewer, and Reviewer 2names in Workpapers CS, ifdesired.Sign Off: 2nd Reviewers This will depend on staff mappingand whether signoffs are set upin Workpapers CS beforehand. Sign Off Initials Sign Off Initials Initials and date will display underthe signed off heading inWorkpapers CS.ProSystem fx Engagement Excel and Word demographic formulasThe following table lists the applicable ProSystem fx Engagement formulas and the equivalent formula variables in Workpapers CS.ProSystem fx EngagementName FunctionsWorkpapers CS VariablesBinder Name Engagement NameBinder Due Date Completion DateBinder Type Engagement TypeProSystem fx EngagementWorkpapers CS VariablesName FunctionsBinder Report Release Date Report Release DateWorkpaper Name Workpaper NameWorkpaper Index Workpaper ReferenceCurrent Period End Current Period DateProSystem fx Engagement Excel and Word link formulasExcel® and Word® link formulas do not convert.Conversion notes and exceptionsThis section details conversion notes and exceptions.▪Engagement tree structure: The order and appearance of the engagement tree structure in Workpapers CS after the conversion may differ from the ProSystem fx Engagement binder. Please note all items are converted to the correct folder locations within the engagement. To providemaximum flexibility, Workpapers CS does not automatically sort folders and workpapers.▪Excel and Word workpaper add-ins, macros, and links: Excel workpapers are modified during the conversion process for removal of add-ins, macros, and/or links.▪Manual workpapers: Manual workpapers are converted as text documents.▪Tax Codes: If UltraTax CS® Tax Codes are desired during the conversion, a translation of ProSystem fx Engagement Tax Codes to UltraTax CS is available. Only one Tax Code Group will convert.▪Workpaper references: Workpapers CS requires that workpapers have reference values.Workpapers without an index value are assigned a reference value during the conversion. You may rename the workpaper reference, if desired. If a duplicate reference exists in a folder, the duplicate references will be renamed.▪Finalized Binders: Finalized binders will be converted as Active unfinalized binders. We recommend that you convert only active / unfinalized binders.Items not convertedThis section details items not converted.▪Workpapers not in a standard binder folder: This includes workpapers within the Unfiled Workpapers, Conflicts, Incompatible Workpapers, Published Workpapers, and Trash folders. To convert these workpapers, you must move the workpapers into a standard binder folder before the conversion process.▪Trial Balance: Consolidated trial balances.▪Firm information▪Client Information▪Engagement and workpaper password information▪Engagement and workpaper history▪Workpaper notes and templates▪Staff▪M3 Tax CodesData Conversion ReportThe data conversion from ProSystem fx Engagement to Workpapers CS creates a report for each engagement converted. The Data Conversion report lists certain modifications made during the conversion process, such as truncations, abbreviations, and so on. Most items in the report are informational and do not require immediate attention.To access the report, locate and open YYYYYY.html, where YYYYYY is the binder name. The report is placed in the user’s Documents folder.Getting helpHelp & How-To CenterFor answers to questions on using Workpapers CS, access the Help & How-To Center by clicking the Help link on the toolbar. For more information, including sample searches, see Finding answers in the Help & How-To Center.Product supportFrom the Support Contact Information page on our website, you can complete a form to send a question to our Support team. For additional product support, visit the Support section of our website. You can also access our Support website from Workpapers CS by choosing Help > Additional Resources > General Support Information.。
核电厂TES水泥固化线控制策略研究与应用
核电厂TES水泥固化线控制策略研究与应用Research and Application of the Control Strategyfor TES Cement Solidification Line in Nuclear Power Plant壤蕊杰1林#2糾錦潯1i M1 (深圳中广核工程设计有限公司1,广东深圳518172;深圳行健自动化股份有限公司2,广东深圳518000)摘要:在对ISA - S88标准和核电厂固体废物处理系统进行简述的基础上,对固体废物处理工艺——水泥固化线的控制策略进行了 详细研究,并对其应用S88标准技术的合理性及适用性进行了分析。
最后通过这套典型的机-电-仪综合自动化控制系统在核电厂 的成功实施,论证了该控制策略的实际应用效果,并形成一定的标准化设计方法,对其他类似系统具有指导意义。
关键词:I S A-S88批量控制顺序控制核电厂C P R1000数字化仪控系统控制策略中图分类号:TH -3 ;TP273 文献标志码: A D O I:10.16086/j. cnki. issnlOOO -0380.201511008A bstract:Based on the brief descriptions of ISA -S88 standard and the solid waste treatment system of nuclear power plant, the control strategy of solid waste technological process, i. e. , the cement solidification line is researched in detail; and the rationality and applicability of applying S88 standard are analyzed. Through successfully implementing this machine-electricity-instrument integrated automation control system in nuclear power plant, the practical application effects of this control strategy is proved; and certain standardized design method is form ed; it possesses guiding significance to other similar systems.Keywords :ISA - S88 Batch control Sequential control Nuclear power plant CPR1000 Digital I&C system Control strategy〇引言水泥固化线作为一种核电厂运行期间产生的固体 废物的处理工艺,长期以来被国外供货商垄断,但近一 两年来,具有自主知识产权的固体废物处理系统自主 化设计方案相继在国内多个CPR1000项目上成功实 施,彻底打破了国外供货商的垄断局面。
Optimization of the cyclone separator geometry for minimum pressure drop
a b s t r a c t
The response surface methodology has been performed based on the Muschelknautz method of modeling (MM) to optimize the cyclone geometrical ratios. Four geometrical factors have significant effects on the cyclone performance viz., the vortex finder diameter, the inlet width and inlet height, and the cyclone total height. There are strong interactions between the effect of inlet dimensions and vortex finder diameter on the cyclone performance. CFD simulations based on Reynolds stress model are also used in the investigation. A new set of geometrical ratios (design) has been obtained (optimized) to achieve minimum pressure drop. A comparison of numerical simulation of the new design and the Stairmand design confirms the superior performance of the new design compared to the Stairmand design. & 2010 Elsevier Ltd. All rights reserved.
冷弯薄壁型钢结构入门指南说明书
A Beginner’s Guide to Cold-FormedSteel FramingCold-Formed Steel Framing Resource Center for Building ProfessionalsINTRODUCTIONWhat is Cold-Formed Steel Framing and How Can I Use It?The 6 Most Critical Design Steps to Take Before Starting Your Next Cold-Formed Steel Framed ProjectNeed to Order Cold-Formed Steel Framing? Start With ThisSimple GuideQuick Guide: Training forCold-Formed Steel Framers1 2 4 6 10ContentsIf you’re unfamiliar with cold-formed steel (CFS) framing or simply haven’t used it in a while, you may have several questions: What is it? How can I use it? Why should I use it?CFS certainly isn’t a new building material. It actually has been used in North America for over 100 years. Because of its light weight and durability, it can be used in a range of applications — from interior, non-loadbearing partition walls to structural members in mid-rise and multi-family buildings.Whatever your current level of knowledge, consider this eBook a primer on all things CFS framing. In it, you’ll learn whatCFS is, how it can benefit a construction project, the basicsof designing with and ordering CFS, and training options for expanding your CFS knowledge.Tip: Before you get started, familiarize yourself with industry and technical terms related to cold-formed steel framing by accessing theWhat is Cold-Formed Steel FramingCFS as a construction material has many advantages. For example, CFS doesn’t shrink or split, won’t absorb moisture, and resists warping, termites, and fire.The 6 Most Critical Design Steps to Take Before Starting Your Next Cold-Formed Steel Framed ProjectDo you need to order cold-formed steel framing (CFS) for your next project — but aren’t sure where to start?When ordering CFS, you must first be aware of the different types of products and how they’re designated by manufacturers and distributors.Since a wide variety of CFS member profiles, depths, widths, and material thicknesses exist, the steel framingmanufacturing industry developed a standard designator system that all CFS manufacturers and suppliers use. It is important to note that this universal designator system is used in identifying cold-formed steel framing in building codes as well. Understanding the designator system makes it easy to specify the right CFS components — and once you do that, you can then move on to finding the CFS distributor for your project.The system is alpha-numeric. For example, a CFS member might have the designation 350S162-43. Without knowledge of the designation system, you can’t tell much from that number. Is it a stud? Track? U-channel? What about its thickness and other material dimensions? Once you understand the system, you can identify the member at a glance.6Need to Order Cold-Formed Steel Framing? Start With This Simple GuideDESIGNATOR LETTERS CONVEY THE TYPE OF CFS FRAMING MEMBERThere are five CFS profiles. To remember them, think of the acronym STUFL: stud, track, U-channel, furring channel, and L-headers.I m a g e s C o u r t e s y o f C l a r k D i e t r i c h7indicate the member’s web depth, flange width, and material thickness.FINDING A CFS DISTRIBUTORCFS framing is typically supplied by a regional distributor. Distributors include traditional lumberyards and gypsum board supply warehouses. Larger contractors may be able to purchase directly from manufacturers To locate distributors, check with a CFS manufacturer. Many link to distributors on their websites. Some manufacturers supply framing packages and uncommon CFS shapes and sizes.Of course, this is just the beginning when it comes to ordering CFS materials. Some CFS members have different coating options, come in varying stock lengths, and can be ordered in a variety of packaging bundles. The quantities of your order will depend on the specific assembly designs, which will determine their spans and spacing and, therefore, the lengths and quantities you’ll need.And, don’t forget that if you’re working on a green building project, you’ll want help choosing a nearby supplier, so you can qualify for all allowable green building points.9Quick Guide:HIGH SCHOOLS AND VOCATIONAL SCHOOLS SKILLSUSANATIONAL CENTER FORCONSTRUCTION EDUCATION AND RESEARCHNational Center for Construction Education and Research (NCCER) provides open-shop craft professionals with training at more than 4,000NCCER-accredited locations across the United States. The NCCER Registry System is an online database that allows participants to provide easy verification of their training to employers. 11ASSOCIATION OF THE WALL AND CEILING INDUSTRY (AWCI)More than 10 years ago, SFA co-developed a CFS training program with AWCI called Steel—Doing It Right®. The two-day seminar is aimed at framers,foremen, superintendents, architects, and others who work with steel in design and construction. The event presents the construction methods associated with CFS load-bearing wall assemblies, interior wall systems framing, roof systems floor assemblies, and more.DECADES OF CFS TRAININGIn addition to the programs mentioned, SFA has conducted STUD University, Steel University forvocational building trades instructors, and countless other seminars. STUD University is a two-day session that provides technology transfer via discussion, demonstration, and hands-on experience on a mini-cold-formed steel framing project using state-of-the-art industry tools. It is specifically designed for architects, builders, contractors, engineers, building inspectors, and building trades instructors.With a foundational knowledge of the benefits, training options, and ordering process for cold-formed steel (CFS) framing, you are now well prepared to move forward with your next CFS-framed project.But if you still have questions, we can help. Whether you’re stuck in the design or planning process, or would like ideas for how to reduce costs or speed up your construction timeline, the BuildSteel team of experts can address your concerns. We offer complimentary project assistance for new or existing cold-formed steel framed projects. Request assistance now.。
Sierpinski垫片的Hausdorff测度上估算法的Java实现
Sierpinski垫片的Hausdorff测度上估算法的Java实现郭美美【摘要】测度与维数的估计和计算对于分形而言,既是十分重要,也是十分困难。
作为三大经典自相似集之一的Sierpinski垫片,尽管维数容易,但测度的计算仍是非常困难。
Sierpinski垫片的Hausdorff测度的计算结果更难且少。
经过部分学者的研究,对Sierpinski垫片的Hausdorff测度通过不同的计算方法,均未达到理想的准确值,但得到比较接近的上界估算值。
引用文献[1]的Sierpinski垫片的Hausdorff测度上估算法,用Java实现窗口对话,并计算出其算法的结果,同时存于Excel文档中。
%It is very important and difficult for the measure and the calculation of measure and dimension of the fractal. As one of the three classical self similar sets, Sierpinski Gasket is difficult to measure, although it is easy to dimension. The calculation of the Hausdorff measure of Sierpinski gasket is more difficult and less. The Hausdorff measure ofthe Sierpinski gasket by different calculation methods does not reach the accurate value of the ideal, but being relatively close to the upper bound estimates. Refers to the Hausdorff measure of the the Sierpinski gasket estimation method, which is in the paper [1]. Uses Java to achieve dialog window, it calculates the results of the algorithm, and to remain in the Excel document.【期刊名称】《现代计算机(专业版)》【年(卷),期】2015(000)012【总页数】4页(P51-54)【关键词】Sierpinski垫片;Hausdorff测度;Java实现;Excel【作者】郭美美【作者单位】韩山师范学院陶瓷职业技术学校,潮州 521031【正文语种】中文作为非线性科学的一个理论课题——分形集的Hausdorff测度,关于Sierpinski 垫片等,至今的结果还不多,一部分学者对于Sierpinski垫片的Hausdorff测度的研究均未过到理想的结果,只是通过不同的方法得到比较接近的上界估算值(文献[1])。
咖啡壶设计指引
TOLERANCES公差规定:Unless shown otherwise on the drawing or sketch, Strix uses a tolerance convention based on thenumber of decimal places shown in a dimension: 除非在图纸上另外指定,思瑞克斯基于尺寸所显示出的小数点的位数来确定公差精度。
Linear 线性公差 X ±0,5mmX,X ±0,2mmX,XX ±0,1mmAngular 角度公差±1°DXF versions of the drawings referred to in these pages are available on request via your localStrix contact.需要参考这个标准的DXF版本图纸可通过联系当地的思瑞克斯代表获得。
STEP and other format 3D CAD data are also available on request.STEP和其他的3D格式图档公差也可应要求获得。
IMPORTANT NOTICE: Approvals and Certification重要的提示: 批准和证明The submission for approval of each appliance into which Strix products are incorporatedis the responsibility of the OEM.所提交的每一个包含思瑞克斯产品的电器认证的责任是OEM厂商的。
Strix Products are developed and tested to the most stringent of appropriate international standards and are approved by applicable international approvals organisations. Strix can provide advice and assistance in the incorporation of Strix products into appliances, but the ultimate responsibility for appliance design, function and compliance with the appropriate safety standards must rest with the appliance designer and OEM.思瑞克斯的产品的研发与测试采用最严酷的国际标准并且被适用的国际机构批准。
ETAG 001-AnnexC amendment 06-11-24
5.2.3.1 Required proofs
5.2.3.2 Steel failure
5.2.3.3 Concrete pryout failure
5.2.3.4 Concrete edge failure
5.2.4 Resistance to combined tension and shear loads
EOTA© Avenue des Arts 40 Kunstlaan
1040 Brussels
TABLE OF CONTENTS
-2-
Introduction
ANNEX C Design methods for anchorages
1
Scope
1.1 Type of anchors, anchor groups and number of anchors
7.1 General
7.2 Shear resistance of concrete member
7.3 Resistance to splitting forces
-3-
Introduction
The design methods for anchorages are intended to be used for the design of anchorages under due consideration of the safety and design concept within the scope of the European Technical Approvals (ETA) of anchors.
4.2 Loads acting on anchors
4.2.1 Tension loads
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104
2. Resonant Frequency of Sierpinski Gasket Monopole Antenna 2.1 Modification of Existing Relation
Figure 1 shows the antenna geometry of a Sierpinski gasket planar monopole. Typically, such antennas exhibit a log-periodic spacing of the resonant frequencies, as well as an increase in the impedance bandwidth at higher bands [3]. It is interesting to note that the band number, n, and the iteration, k, are interchangeable. In other words, band zero and the 0th iteration correspond to the fundamental resonance of the antenna. The first band and the first fractal iteration correspond to the first log-periodic resonant frequency. Therefore, after the first fractal iteration, two resonant frequencies are available: the fundamental and the first log-periodic frequency. This is valid for other higher fractal iterations. In general, the antenna radiates in two distinct bands for a single fractal iteration, three bands for a double fractal iteration, and so on. Puente et al. proposed the following formula [3] for the resonant frequency corresponding to an operating band:
Design Formula for Sierpinski Gasket Pre-Fractal Planar-Monopole Antennas
1 R. K. Mishra , R. Ghatak1 , D. R. Poddar3
'Department of Electronic Science, Berhampur University Bhanja Bihar, Berhampur 760007, Orissa, India E-mail: prof.r. k.mishra@
T
removed or altered without significantly altering the multi-band behavior of a Sierpinski monopole antenna, as mentioned in [5]. Therefore, from an engineering prospective, it is important to determine the resonant frequencies in different Sierpinski modes when other parameters are available. Also, it is equally important to find the side length of the generating triangle when all other parameters are available. We propose an improved closed-form expression for the resonant frequencies, and then use it for finding a closed-form expression for the side length of the generating triangle. fEEE Antennas and Propagation Magazine, Vol. 50, No. 3, June 2008
2Department
of Physics, The University of Burdwan Burdwan, India
3Department
of Electronics and Telecommunication Engineering, Jadavpur University Kolkata, India
fr
In Equation (4), p =- - 0.230735, and x is one, as explained earlier. The frequencies predicted by this formulation are tabulated in Table 1. However, this will be valid for a Sierpinski gasket under the assumption of perfect magnetic wall boundaries. The following can be noted for the resonant frequency in the of imperfect magnetic walls, which is more realistic: case 1. An equilateral triangle is a zeroth-iteration antenna. For such an antenna, Helszajn and James suggested [6] accounting for an effective value of the side length.
Abstract
An improved formula for determination of resonant frequencies in different Sierpinski modes is developed from other existing formulas, using physical and analytical reasoning. The superiority of the proposed formula over other existing formulas is verified by comparing the results with those from experiments and simulations. A design formula for the side length of the generating Sierpinski triangle is also proposed by algebraic rearrangement of the formula for the resonant frequency. Keywords: Planar antennas; fractal antennas; monopole antennas
Because Equation (1) has a coefficient of 0.26 as compared to 0.245 in Equation (3), the results from these expressions will slightly differ. It is to be noted that in Equation (1), the scale factor is raised to the power of the band number, but in Equation (3), it is raised to the iteration of the Sierpinski gasket geometry. This similarity in form between the expressions of Equations (1) and (3), and the validity of Equations (2) and (1) for the lower and upper bands, implies that a judicious use of Equations (1) and (2) can approximately predict the resonant frequency. Since the conversion of the formn of Equation (2) into Equation (1) occurs in the second band, i.e., for n =I1, it will be appropriate to Ž1 use Equation (1) for n-: and Equation (2) for n = 0. Accordingly, we can use the following expression for the prediction of the resonant frequency:
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Tom Milligan Assoc. Editor, Antenna Designer's Notebook 8204 WNest Polk Place Littleton, CO 80123 USA Tel: +1 (303) 977 7268 Fax: +1(303) 977 8853 E-mail: TMilligan@