Is it possible to perform a harmonic piezoelectric analysis in English units?
|
Yes. The input below is a modification of VM231 using a consistent system based on feet, pounds, seconds and Coulomb. A unit conversion table is attached to this solution. The following link explains the difference between gravitational, engineering and absolute system of units. <a target=_blank href="http://en.wikipedia.org/wiki/Slug_%28mass%29">http://en.wikipedia.org/wiki/Slug_%28mass%29</a>http://en.wikipedia.org/wiki/Slug_%28mass%29 /COM,ANSYS MEDIA REL. 11.0 (10/27/2006) REF. VERIF. MANUAL: REL. 11.0 /SHOW,JPEG /TITLE, VM231, PIEZOCERAMIC RECTANGLE UNDER PURE BENDING LOAD /COM, REF: PARTON,V.Z., KUDRYAVTSEV, B.A. AND SENIK,N.A. (1989) /COM, "MECHANICS OF PIEZOELECTRIC MATERIALS" IN "APPLIED MECHANICS: /COM, SOVIET REVIEW.", Vol.2: ELECTROMAGNETOELASTICITY, /COM, G.K.MIKHAILOV AND V.Z.PARTON (EDS.), HEMISPHERE PUBL. CORP., P.28 /com, Conversion factors from SI to a consistent system of British Units mLen=3.28084 mPres=0.6719687 mVolt=23.73 mPer=0.01284 mE=0.0929 mD=0.1383 /NOPR /COM, /COM, GEOMETRY DATA /COM, L=1.E-3*mLen ! PLATE LENGTH,ft H=0.5E-3*mLen ! PLATE THICKNESS,ft /COM, /COM, LOAD DATA /COM, SIG1=-20E9*mPres/mLen ! PRESSURE SLOPE, lb/(s_ft^2) /PREP7 /COM, /COM, MATERTIAL PROPERTIES FORTHE FINITE ELEMENT SOLUTION: /COM, CONSTITUTIVE MATRICES FOR PZT-4 (POLAR AXIS ALONG Y) /COM, /COM, [c11 c13 c12 0 0 0 ] [ 0 e31 0 ] [ep11 0 0 ] /COM, [c13 c33 c13 0 0 0 ] [ 0 e33 0 ] [ 0 ep33 0 ] /COM, [c12 c13 c11 0 0 0 ] [ 0 e31 0 ] [ 0 0 ep11] /COM, [ 0 0 0 c44 0 0 ] [e15 0 0 ] /COM, [ 0 0 0 0 c44 0 ] [ 0 0 e15] /COM, [ 0 0 0 0 0 c66] [ 0 0 0 ] /COM, emunit,epzro,8.854e-12*mPer MP,PERX,1,728.5 ! PERMITTIVITY AT CONSTANT STRAIN MP,PERY,1,634.7 MP,PERZ,1,728.5 TB,ANEL,1 ! ANISOTROPIC ELASTIC STIFFNESS TBDA,1,13.9E10*mPres,7.43E10*mPres,7.78E10*mPres ! c11,c13,c12 TBDA,7,11.5E10*mPres,7.43E10*mPres ! c33,c13 TBDA,12,13.9E10*mPres ! c11 TBDA,16,2.56E10*mPres ! c44 TBDA,19,2.56E10*mPres ! c44 TBDA,21,3.06E10*mPres ! c66 TB,PIEZ,1 ! PIEZOELECTRIC STRESS COEFFICIENTS TBDA,2,-5.2*mE ! e31 TBDA,5,15.1*mE ! e33 TBDA,8,-5.2*mE ! e31 TBDA,10,12.7*mE ! e15 TBDA,15,12.7*mE ! e15 /COM, /COM, FINITE ELEMENT MODEL /COM, ANTYPE,STATIC ET,1,223,1001,0,0,0 ! PLANE223 (UX,UY,VOLT) PLANE STRESS N,1,0,0 N,2,L,0 N,3,L,H N,4,0,H E,1,2,3,4 emid,ad,all NSEL,S,LOC,X,0 ! DEFINE STRUCTURAL B.C. DSYM,SYMM,X NSEL,R,LOC,Y,0 D,ALL,UY,0 D,ALL,VOLT,0 NSEL,S,LOC,Y,0 DSYM,ASYMM,Y NSEL,ALL SFGRAD,PRES,0,Y,0,-SIG1 ! SPECIFY PRESSURE LOAD GRADIENT NSEL,S,LOC,X,L SF,ALL,PRES,0 ! APPLY PRESSURE LOAD NSEL,ALL FINISH /SOLVE OUTPR,,LAST SOLVE FINISH /post1 PRNSOL,S,COMP PRNSOL,EPEL,COMP PRNSOL,EF,COMP PRNSOL,D,COMP ! ! MATERTIAL PROPERTIES FOR THE ANALYTICAL SOLUTION ! S11=12.3093E-12/mPres ! ELASTIC COMPLIANCE COEFFICIENTS S13=-5.34878E-12/mPres D31=-1.23816E-10*mD ! PIEZOELECTRIC STRAIN COEFFICIENTS D33= 2.91296E-10*mD EP33=11.3063E-9*mPer ! PERMITTIVITY COEFFICIENT AT CONSTANT STRESS K31=D31*D31/(S11*EP33) ! ELECTROMECHANICAL COEFFICIENTS KS=D33*D31/(S13*EP33) ! ! ANALYTICAL SOLUTION AT NODE 3 ! UX3=S11*(1-K31)*SIG1*NX(3)*NY(3) UY3=S13*(1-KS)*SIG1*NY(3)**2/2 UY3=UY3-S11*(1-K31)*SIG1*NX(3)**2/2 VOLT3=D31*SIG1*NY(3)**2/(2*EP33) SX3=SIG1*NY(3) EFY3=-D31*SIG1*NY(3)/EP33 ! ! RESULT OUTPUT ! *GET,SX,NODE,3,S,X *GET,EFY,NODE,3,EF,Y *DIM,LABEL,CHAR,5,3 *DIM,VALUE,ARRAY,5,3 LABEL(1,1)='UX, ','UY, ','VOLT, ','SX, ','EFZ, ' LABEL(1,2)='(um) ','(um) ','(V) ','(N/mm^2)','(V/mm)' *VFILL,VALUE(1,1),DATA,UX3*1E6,UY3*1E6,VOLT3,SX3*1E-6,EFY3*1E-3 *VFILL,VALUE(1,2),DATA,UX(3)*1E6,UY(3)*1E6,VOLT(3),SX*1E-6,EFY*1E-3 *VFILL,VALUE(1,3),DATA,ABS(UX(3)/UX3),ABS(UY(3)/UY3),ABS(VOLT(3)/VOLT3) *VFILL,VALUE(4,3),DATA,ABS(SX/SX3),ABS(EFY/EFY3) /COM /COM /COM,---------------------- VM231 RESULTS COMPARISON ------------------ /COM, /COM, NODE 3 | TARGET | ANSYS | RATIO /COM, *VWRITE,LABEL(1,1),LABEL(1,2),VALUE(1,1),VALUE(1,2),VALUE(1,3) (1x,A8,A8,' ',F9.3,' ',F9.3,' ',F7.3) /COM,------------------------------------------------------------------ FINISH |
||
|