ComputerAided_Design_Engineering_amp_Manufactur.pdf

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SIG3= -1013.3 END J SDIR=0.00000E+00 SBZ= -1.7041 SBY= 382.49 SIG1= 384.19 SIG3= -384.19 STATIC FORCES ON NODE 1 0.000000E+00 12500.0 0.184741E-12 0.000000E+00 299991. 562500. 0.00000E+00 0.00000E+00 3-D BEAM 4 END I SDIR=0.00000E+00 SBZ= -1.7041 SBY= 382.49 SIG1= 384.19 SIG3= -384.19 END J SDIR=0.00000E+00 SBZ= -1.5837 SBY= -246.50 SIG1= 248.08 SIG3= -248.08 STATIC FORCES ON NODE 2 0.000000E+00 12500.0 -0.113687E-12 0.000000E+00 299991. 225000. STATIC FORCES ON NODE 3 0.000000E+00 -12500.0 -0.113687E-12 0.000000E+00 -299991. 112500. FIGURE 1.6 solving, which utilizes the expertise of different domain experts in the field of process planning. The domain experts use the geometrical and technological information of the raw stock and the workpiece, which is available from the solid-modeler-based CAD data model, in order to develop the process plan. The system allows for the process plan to be developed in a hierarchical fashion with control executed © 2001 by CRC Press LLC INTEGRATED CAD/FEM SYSTEM Models Graphics Layouts Options Help Command Logout Services content /bin/csh STATIC FORCES ON NODE 2 0.000000E+00 -12500.0 -0.184741E-12 0.000000E+00 -299991. -225000. ELEM 1 STRAIN ENERGY= 11.7829 EL= 2 NODES= 2 3 MAT= 2 TCENT,TTOPZ,TBOTY= 0.0 0.0 0.0 QZ,QY= ELEM 2 STRAIN ENERGY= 7.50061 EL= 3 NODES= 3 4 MAT= 2 TCENT,TTOPZ,TBOTY= 0.0 0.0 0.0 QZ,QY= 0.00000E+00 0.00000E+00 3-D BEAM 4 END I SDIR= 0.00000E+00 SBZ=0.40122E-01 SBY= -209.66 SIG1= 209.70 SIG3= -209.70 END J SDIR= 0.00000E+00 SBZ=0.26748E-01 SBY= -139.77 SIG1= 139.80 SIG3= -139.80 Redefining defrule: aero3 +j+j+j Redefining defrule: aero4 +j+j+j Redefining defrule: aero5 +j+j Redefining defrule: aero6 +j+j Redefining defrule: aero7 =j+j+j Redefining defrule: aero8 =j+j+j Redefining defrule: aero9 =j+j+j Redefining defrule: aero10 =j+j+j CLIPS> CLIPS> ******************************************************************* *****Change the location of the engine to the wing*** *****station at 60% of the chord length, ****** CLIPS> Concept Modeler AGM Cruise Altitude 50000 Mach Number 2, 5 Thrust Load 250 Select Aircraft Configuration High (1), Low(2), Mid(3), Joined(4), Wing 2 Select the Engine type: General Electric (1), Rolls-Royce(2), Pratt & Whitney(3) Number of Engines 0 Range 1500 Engine Weight 3000 Runway Length 700 Number of Separate fuel tanks 4 Fuel flow rate 34 CruiseSpeed 4500 EOS 1.25 Live Speed 1900 Root thickness 4 Tip Thickness Ratio 0.56 1/2 Chord sweep 0.5 Sea Level Pressure 90 Cast load factor 2.25 Endurance (days) 3 Taxi load factor 1.25 Thermal Environment (-50:60) Generation of suggestions for modification of initial wing configuration. Specific fuel Cons. Bypass ratio Approx Wing aspect ratio 0.134 User Ops #1 User Ops #2 User Ops #3 User Ops #4 Wing loading 103 Wing Area 1883 Wing Span 133 7 Mean chord 14.074 Root Chord NIL Aspect Ratio 9.5 Sweep (1/4 chord) 27 Taper 0.25 Sweep (1/2 chord) 21 Twist 4 Wing Incidence 5 Dihedral angle 5 Thickness ratio(normal/chord) 12% Thickness ratio(strearwise) 10.69% Manufg. Thickness Ratio(root)13.2% Thickness Ratio(tip) 2.7% Assembly 2 Maintainabili
FIGURE 1.7 through the control expert (blackboard architecture terminology) resident in the process planning system. The control expert incorporates the appropriate heuristics for reasoning about resources and constraints and allows for concurrent exploration of alternate plans. The blackboard-architecture-based process planner (BBPP) was implemented using the CLIPS expert system shell in a prototype expert system. © 2001 by CRC Press LLC Concept Modeller AGM Models Graphics Layouts Options Help Command Logout Services Cavalier View Z Y X (THE AIRCRAFT-WING AEROFOIL-SECTION-8 FRONT-SECTION ORIENTATION) It is an object of type AEROFOIL. Components of AIRCRAFT-WING AIRCRAFT-WING AEROFOIL-SECTION-20 AEROFOIL-SECTION-19 AEROFOIL-SECTION-18 AEROFOIL-SECTION-17 AEROFOIL-SECTION-16 AEROFOIL-SECTION-15 AEROFOIL-SECTION-14 AEROFOIL-SECTION-13 AEROFOIL-SECTION-12 AEROFOIL-SECTION-11 AEROFOIL-SECTION-10 AEROFOIL-SECTION-9 AEROFOIL-SECTION-8 AEROFOIL-SECTION-7 AEROFOIL-SECTION-6 AEROFOIL-SECTION-5 AEROFOIL-SECTION-4 AEROFOIL-SECTION-3 AEROFOIL-SECTION-2 AEROFOIL-SECTION-1 The complete product model of the aircraft wing along with its wingbox. SKIN FRONT - SECTION WING - BOX MIDDLE - SECTION WING - BOX END - SECTION WING - BOX FRONT - SECTION WING - BOX MIDDLE - SECTION WING - BOX END - SECTION WING - BOX FRONT - SECTION WING - BOX MIDDLE - SECTION WING - BOX END - SECTION WING - BOX FRONT - SECTION WING - BOX MIDDLE - SECTION WING - BOX WING - BOX END - SECTION WING - BOX FRONT - SECTION WING - BOX MIDDLE - SECTION WING - BOX END - SECTION WING - BOX FRONT - SECTION WING - BOX MIDDLE - SECTION WING - BOX END - SECTION WING - BOX FRONT - SECTION WING - BOX MIDDLE - SECTION WING - BOX END - SECTION WING - BOX FRONT - SECTION WING - BOX MIDDLE - SECTION WING - BOX END - SECTION WING - BOX FRONT - SECTION WING - BOX MIDDLE - SECTION WING - BOX END - SECTION WING - BOX FRONT - SECTION WING - BOX MIDDLE - SECTION WING - BOX END - SECTION WING - BOX FRONT - SECTION WING - BOX MIDDLE - SECTION WING - BOX WING - BOX END - SECTION WING - BOX FRONT - SECTION WING - BOX MIDDLE - SECTION WING - BOX END - SECTION WING - BOX FRONT - SECTION WING - BOX MIDDLE - SECTION WING - BOX END - SECTION WING - BOX FRONT - SECTION WING - BOX MIDDLE - SECTION WING - BOX END - SECTION WING - BOX FRONT - SECTION WING - BOX MIDDLE - SECTION WING - BOX
Page 1 and 2: COMPUTER-AIDED DESIGN, ENGINEERING,
Page 3 and 4: Library of Congress Cataloging-in-P
Page 5 and 6: Editor Cornelius T. Leondes, B.S.,
Page 7 and 8: Chapter 1 Chapter 2 Chapter 3 Chapt
Page 9 and 10: the implementation of the IPD syste
Page 11 and 12: In our IPD system implementations,
Page 13 and 14: 2. Specification of analysis-specif
Page 15 and 16: FIGURE 1.2 base or the design insta
Page 17 and 18: FIGURE 1.4 System architecture of t
Page 19: of a beam is considered for FEA. Th
Page 23 and 24: 2. machining facility (e.g., gang m
Page 25 and 26: from the FBDS. The user also specif
Page 27 and 28: Depending on the type of feature to
Page 29 and 30: TABLE 1.6 Tolerance synthesis is de
Page 31 and 32: FIGURE 1.12 Display of the NC tool
Page 33 and 34: component geometric entities and va
Page 35 and 36: FIGURE 1.14 The system architecture
Page 37 and 38: TABLE 1.10 User Input for the Toler
Page 39 and 40: TABLE 1.11 Tolerance Specifications
Page 41 and 42: 7. Z. Young and I. R. Groose. A rul
Page 43 and 44: FIGURE 2.1 Tool paths generated for
Page 45 and 46: FIGURE 2.2 sented by instances of f
Page 47 and 48: TABLE 2.1 A CAD-Generated Hole Conf
Page 49 and 50: FIGURE 2.6 mounted on the rotary ta
Page 51 and 52: FIGURE 2.8 fixture for the machinin
Page 53 and 54: FIGURE 2.10 or best-fit, or the cur
Page 55 and 56: FIGURE 2.11 Linear approximation of
Page 57 and 58: FIGURE 2.13 Circular approximation
Page 59 and 60: FIGURE 2.14(b) Circular approximati
Page 61 and 62: FIGURE 2.16 Types of biarcs. FIGURE
Page 63 and 64: FIGURE 2.18 Approximation of scanne
Page 65 and 66: FIGURE 2.20 A touch trigger probe c
Page 67 and 68: TABLE 2.4 Substitute Elements in CM
Page 69 and 70: FIGURE 2.21 CMM planning requiremen
Page 71 and 72:
Product Model Representation for Co
Page 73 and 74:
© 2001 by CRC Press LLC TABLE 2.5
Page 75 and 76:
TABLE 2.7 Partial Listing of Dimens
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24. Makinouchi, S., Okamoto, M., an
Page 79 and 80:
Bijan Shirinzadeh Monash University
Page 81 and 82:
FIGURE 3.1 Trends in flexible manuf
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FIGURE 3.3 and constrain different
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Other Fixturing Techniques There ar
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FIGURE 3.6 contact point. The geome
Page 89 and 90:
FIGURE 3.8 The vertical support fix
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and moments about the contact point
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een identified, the normals are use
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one of choosing the variables: such
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Fixture Module Location An importan
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FIGURE 3.15 Illustration of functio
Page 101 and 102:
FIGURE 3.18 Minimum separation test
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direction) the face, respectively.
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FIGURE 3.21 Software structure for
Page 107 and 108:
3.8 Conclusion A reconfigurable fix
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Heui Jae Pahk Seoul National Univer
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FIGURE 4.1(b) Conceptual framework
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4.3 Measurement Points Sampling and
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Surface S2 Measurement Path FIGURE
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FIGURE 4.4 Rough phase alignment ba
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deviation between the nominal CAD d
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FIGURE 4.6(a) Sum of squares distan
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FIGURE 4.7(c) Trailing edge. (c) th
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FIGURE 4.8(a) Profile tolerance of
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The calculated minimum form error i
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FIGURE 4.11(a) A typical mold havin
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FIGURE 4.11(d) Inspection results f
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FIGURE 4.12(c) Maximum deviation (p
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5.1 Introduction Developments in th
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process plan for a part (Figure 5.3
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FIGURE 5.5 leading to the developme
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the previously stored process plan
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FIGURE 5.7 Techniques of defining a
Page 145 and 146:
Feature Recognition and Extraction
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in relation to another feature (e.g
Page 149 and 150:
FIGURE 5.9 Framework for building a
Page 151 and 152:
FIGURE 5.10 Process plan content.
Page 153 and 154:
FIGURE 5.12 Schematic sketch of the
Page 155 and 156:
Several techniques of defining a fe
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TABLE 5.1 Data Structure for Repres
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FIGURE 5.16 Classification of the t
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system to ensure that the part bein
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FIGURE 5.19 Graphical model of the
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TABLE 5.4 Data Structure for Repres
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FIGURE 5.20 Mapping between machini
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algorithms. (Some details of the pr
Page 171 and 172:
FIGURE 5.24 An example rotational p
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FIGURE 5.26 Down_face-turn-up_face
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FIGURE 5.27 Procedure for machine t
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FIGURE 5.28 Determining the number
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DL is needed to be set only if the
Page 181 and 182:
FIGURE 5.31 Operation sequencing co
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Cutting Tool Selection Selection of
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1. A tool is searched for in the da
Page 187 and 188:
FIGURE 5.32 Inputs to optimization
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When these values are substituted,
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Usually, maximum and minimum speed
Page 193 and 194:
FIGURE 5.33 Solution methodology.
Page 195 and 196:
TABLE 5.6 Process Plan Internal Rep
Page 197 and 198:
In a strict theoretical perspective
Page 199 and 200:
18. Domazet, D. S. and Lu, S. C. Y,
Page 201 and 202:
63. Prasad, A. V. S. R. K., Rao, P.
Page 203 and 204:
CAD systems. The sample consists of
Page 205 and 206:
learn to master the new system. An
Page 207 and 208:
Although researchers appear to agre
Page 209 and 210:
Link and Zmud28 found that organic
Page 211 and 212:
Informal Training Informal CAD trai
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informal training programs, felt th
Page 215 and 216:
6. C. A. Beatty, Tall Tales and Rea
Page 217 and 218:
A.Y.C. Nee National University of S
Page 219 and 220:
FIGURE 7.1 Planning, design, and ma
Page 221 and 222:
A metal stamping can have the follo
Page 223 and 224:
FIGURE 7.3 Strips used to notch out
Page 225 and 226:
A Skeletal Approach for the Recogni
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These findings can be used to devel
Page 229 and 230:
Semi-Direct Piloting In cases where
Page 231 and 232:
a larger value, the die operations
Page 233 and 234:
FIGURE 7.9 Symbolic relationship be
Page 235 and 236:
FIGURE 7.11 The shape of the envelo
Page 237 and 238:
TABLE 7.1 Schema for the Generation
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strong reasons to support a move to
Page 241 and 242:
FIGURE 7.16 3-D CAD model of a part
Page 243 and 244:
References Cheok, B.T. et al. (1994
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include the once forbidden generati
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A temporal matrix (T-Matrix) is pro
Page 249 and 250:
FIGURE 8.1 A basic process. (From R
Page 251 and 252:
FIGURE 8.4(a) Generate a new IG usi
Page 253 and 254:
Note if the pair of nodes are both
Page 255 and 256:
TABLE 8.1 Summary of the Rules Cond
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The correctness of these rules is e
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needs to show that after each full
Page 261 and 262:
ule is violated, a warning should b
Page 263 and 264:
Π1 Π3 Π4 FIGURE 8.8(a) After add
Page 265 and 266:
1 2 3 4 5 6 7 8 9 10 11 12 13 14 15
Page 267 and 268:
A ik � ‘U’ and is in a cycle
Page 269 and 270:
FIGURE 8.12(a) Add [p2 t7 p7 t8 p4]
Page 271 and 272:
FIGURE 8.12(c) Add a token to p8 vi
Page 273 and 274:
FIGURE 8.12(e) Add [p8 t9 p14 t10 p
Page 275 and 276:
FIGURE 8.13 An example of rule TT.0
Page 277 and 278:
FIGURE 8.14 A GPN model of a machin
Page 279 and 280:
FIGURE 8.15(b) The first exclusive
Page 281 and 282:
FIGURE 8.15(d) The last exclusive T
Page 283 and 284:
FIGURE 8.15(f) After entering the a
Page 285 and 286:
FIGURE 8.15(h) Completion of Compon
Page 287 and 288:
FIGURE 8.15(j) Two PP-generations:
Page 289 and 290:
FIGURE 8.15(l) The last exclusive T
Page 291 and 292:
t1 t5 p1 p5 t6 (a) t2 t3 t4 2 2 p2
Page 293 and 294:
FIGURE 8.17 An example of partial f
Page 295 and 296:
Theorem 10: If pi → pk in a synth
Page 297 and 298:
Note that control transitions are o
Page 299 and 300:
t j than the lower at , it indicate
Page 301 and 302:
• Programming logic and VLSI arra
Page 303 and 304:
7. Chao, D. Y. and D. T. Wang, Appl
Page 305 and 306:
53. Villaroel, J. L., J. Martinez,
Page 307 and 308:
q u : the numerator of the least ra
Page 309 and 310:
geometric modeling, engineering ana
Page 311 and 312:
In dimension driven or parametric d
Page 313 and 314:
FIGURE 9.3 configuration of bodies
Page 315 and 316:
FIGURE 9.6 FIGURE 9.7 Geometric Int
Page 317 and 318:
FIGURE 9.8 Intersection of degrees
Page 319 and 320:
will introduce a way to propagate p
Page 321 and 322:
Completeness of Dimensions Complete
Page 323 and 324:
FIGURE 9.12 3-D constraints. © 200
Page 325 and 326:
The distance constraint from pt �
Page 327 and 328:
therefore: Now merge the lists and
Page 329 and 330:
Quantity analysis methods have the
Page 331 and 332:
y a revolute joint. By selecting al
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