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| 3 3 2 1 CCHH | ||
| 1 1 3 | ||
| 3.296187218 0.03516905 -0.0000356 | ||
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| 3 12 2 1 SMGH | ||
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| 122.178832064517 0.01102442948831 | ||
| 1 0. 0. 0. 0. 0. 0. | ||
| 2 0. 0. 0. 0. +1. 0. |
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pyNastran/bdf/cards/aero/nlfltr/case2/buckled.f06
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pyNastran/bdf/cards/aero/nlfltr/case2/buckled.mgh
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pyNastran/bdf/cards/aero/nlfltr/case2/nominal.kgg
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| @@ -0,0 +1,245 @@ | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| $ $ | ||
| $ STRUTWNG.INP $ | ||
| $ $ | ||
| $ STRUT-BRACED WING SUBJECTED TO DISCRETE GUST AT 2.5G AND -1 G CONDITIONS. $ | ||
| $ $ | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| $ BUCKLED.F06 CONTAINS THE MSC/NASTRAN MODAL RESULTS OF THE STRUT-BUCKLED $ | ||
| $ STRUTURE. THE MODE SHAPES ARE USED AS THE GENERALIZED COORDINAES BECAUSE $ | ||
| $ THEY CAN BETTER REPRESENT DEFORMATIONS OF THE NOMINAL,STRUT & WING-BUCKLED $ | ||
| $ STRUCTURES. $ | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| ASSIGN FEM =buckled.f06,PRINT=0,FORM=MSC,BOUND=SYM,SUPORT=3 | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| $ BUCKLED.MGH CONTAINS THE [MGG][PHI] MATRIX USED TO COMPUTE THE GRAVITY LOADS$ | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| ASSIGN MATRIX =buckled.mgh,MNAME=SMGH,PRINT=0 | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| $ NOMINAL.KGG CONTAINS THE G-SET STIFFNESS MATRIX OF THE NOMINAL STRUCTIRE. $ | ||
| $ IT IS ALSO USED TO GENERATE THE [SKGH] MATRIX. $ | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| ASSIGN MATRIX =nominal.kgg,MNAME=NOMKGG,PRINT=0 | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| $ WBUCKLED.KGG CONTAINS THE G-SET STIFFNESS MATRIX OF THE WING-BUCKLED $ | ||
| $ STRUCTURE. $ | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| ASSIGN MATRIX =wbuckled.kgg,MNAME=WBUCKGG,PRINT=0 | ||
| GENGUST | ||
| $ | ||
| DOUBLE | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| $ SUBAC50 TO MOVE AERODYNAMIC CENTER ON EACH BOX FROM DEFAULT 25% CHORD $ | ||
| $ O 50% CHORD $ | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| SUBAC50 | ||
| $ | ||
| CEND | ||
| $Begin Case Control Section | ||
| TITLE= Non-Linear Flutter of the Wing + Strut Configuration | ||
| ECHO = SORT | ||
| SUBCASE = 1 | ||
| SUBTITLE= Trim at 2.5G, U=650 fps,M=0.53 | ||
| LABEL= 2 Nonlinear Parameters: Axial Forces along wing & strut | ||
| NLFLTR = 10 | ||
| SUBCASE = 2 | ||
| SUBTITLE= Trim at -1.G, U=650 fps,M=0.53 | ||
| LABEL= 2 Nonlinear Parameters: Axial Forces along wing & strut | ||
| NLFLTR = 20 | ||
| BEGIN BULK | ||
| $...1..|...2...|...3...|...4...|...5...|...6...|...7...|...8...|...9...|...10..| | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| $ DEFINES: [SKGH]=[NOMKGG][SPHI]. [SKGH] IS USED TO COMPUTE THE AXIAL FORCES $ | ||
| $ ALONG THE STRUT AND THE WING FOR DEFINING THE TWO NONLINEAR PARAMETERS $ | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| ALTER 1 FEM SKGH 1. NOMKGG * SPHI | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| $ DEFINES: LOCALLY LINEAR SYSTEM OF THE POST-WING-BUCKLED STRUCTURE. $ | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| NLSYSM 300 NO | ||
| NO YES 1. BASE 1. WBUCKGG | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| $ DEFINES: LOCALLY LINEAR SYSTEM OF THE NOMINAL STRUCTURE $ | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| NLSYSM 400 NO | ||
| NO YES 1. BASE 1. NOMKGG | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| $ DEFINES: LOCALLY LINEAR SYSTEM OF THE POST-STRUT-BUCKLED STRUCTURE. $ | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| NLSYSM 600 NO | ||
| NO NO 1. BASE 1. BASE | ||
| $...1..|...2...|...3...|...4...|...5...|...6...|...7...|...8...|...9...|...10..| | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| $ $ | ||
| $ SUBCASE 1 : TRIM AT 2.5 G $ | ||
| $ $ | ||
| $ FOR NONLINEAR PARAMETER A: FORCET1 AT GRID 1 $ | ||
| $ =WING AXIAL BUCKLING FORCE (2.1E+06 LBF) $ | ||
| $ FORCET1 AT GRID 1 < 2.1E+06 CORRESPONDS TO NOMINAL STRUCTURE $ | ||
| $ (NLSYSM ID= 400) $ | ||
| $ FORCET1 AT GRID 1 > 2.1E+06 CORRESPONDS TO POST-WING-BUCKLED STRUCTURE $ | ||
| $ (NLSYSM ID= 300) $ | ||
| $ $ | ||
| $ FOR NONLINEAR PARAMETER B: FORCET1 AT GRID 8001 $ | ||
| $ =STRUT AXIAL BUCKLING FORCE (1.26E+05 LBF) $ | ||
| $ FORCET1 AT GRID 8001<1.26+05 CORRESPONDS TO NOMINAL STRUCTURE $ | ||
| $ FORCET1 AT GRID 8001>1.26+05 CORRESPONDS TO POST-STRUT-BUCKLED STRUCTURE$ | ||
| $ (NLSYSM ID= 600) $ | ||
| $ $ | ||
| $ NOTE: FORCES ALONG T1 AT GRIDS 1 AND 8001 ARE COMPUTED USING [SKGH] MATRIX $ | ||
| $ $ | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| NLFLTR 10 0 101 1 10 33 1 1 | ||
| 4 FORCET1 1 1. | ||
| 4 FORCET1 8001 1. | ||
| LINEAR 0.+1.26+05+1.26+05+1.26+06 | ||
| 0. 400 400 600 600 | ||
| +2.10+06 400 400 600 600 | ||
| +2.10+06 300 300 600 600 | ||
| +2.10+07 300 300 600 600 | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| $ DEFINE ALPHA AND H TO BE THE TWO AIRFRAME STATES $ | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| MLDSTAT 10 10 | ||
| ALPHA 0. H 0. | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| $ DEFINE 2.5 G TRIM CONDITION. ALPHA=7.155 IS OBTAINED BY TRIM ANALYSIS $ | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| MLDTRIM 10 32.2 2.5 MODALG25 | ||
| ALPHA 7.155 | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| $ MATRIX MODALG25 CONTAINS THE MODAL SOLUTION OF THE 2.5 G TRIM CONDITION $ | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| $...1..|...2...|...3...|...4...|...5...|...6...|...7...|...8...|...9...|...10..| | ||
| DMI MODALG250 2 2 DMIL 15 1 | ||
| DMIL MODALG25 1 1+0.000000000E+00+CONT | ||
| +CONT -5.789515686E+01-1.399510765E+01+6.287665367E+00+1.841790962E+01+CONT | ||
| +CONT +3.751965165E-01+9.434514642E-01+1.309653568E+01+9.744488001E-01+CONT | ||
| +CONT -1.976884723E+00-1.346108317E-01+3.507952988E-01+4.009834304E-02+CONT | ||
| +CONT +2.326263905E+00+2.984036505E-01 | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| $ * GUST LOAD * $ | ||
| $ 1-COS DISCRETE GUST WITH ONE SECOND DELAY. Wg=50Ft/S, Wg/(AIRSPEED)=0.07692 $ | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| DGUST 33 OMCOS 1.4444 +.07692 -650. 0. 0.01 | ||
| MLDTIME 1 0. 10. 0.001 5 -1 | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| $ OUTPUT TRANSIENT REPONSES ON FILE STRUTWNGG2.XLS FOR SUBCASE 1 $ | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| MLDPRNT 1 STRUTWNGG2.XLS TABLE TIME | ||
| FORCET1 1 FORCET1 8001 GRIDGT3 63 GRIDGT3 43 | ||
| GRIDXT1 8035 GRIDXT1 8041 | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| $ STORE ANIMATION OF THE STRUCTURAL DEFORMATION ON FILE STRUTWNGG2.PLT $ | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| PLTTIME 100 10 0. 10. 20 NORIGID TECPLOT | ||
| STRUTWNGG2.PLT | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| $ $ | ||
| $ SUBCASE 2 : TRIM AT -1.0 G $ | ||
| $ $ | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| NLFLTR 20 0 101 1 20 33 1 2 | ||
| 4 FORCET1 1 1. | ||
| 4 FORCET1 8001 1. | ||
| LINEAR 0.+1.26+05+1.26+05+1.26+06 | ||
| 0. 400 400 600 600 | ||
| +2.10+06 400 400 600 600 | ||
| +2.10+06 300 300 600 600 | ||
| +2.10+07 300 300 600 600 | ||
| $ DEFINE ALPHA AND H TO BE THE TWO AIRFRAME STATES | ||
| MLDSTAT 20 20 | ||
| ALPHA 0. H 0. | ||
| $ DEFINE -1.0G TRIM CONDITION. ALPHA=-2.86199 IS OBTAINED BY TRIM ANALYSIS | ||
| MLDTRIM 20 32.2 -1. MODALGN1 | ||
| ALPHA -2.86199 | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| $ MATRIX MODALGN1 CONTAINS THE MODAL SOLUTION OF THE -1.0 G TRIM CONDITION $ | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| $...1..|...2...|...3...|...4...|...5...|...6...|...7...|...8...|...9...|...10..| | ||
| DMI MODALGN10 2 2 DMIL 15 1 | ||
| DMIL MODALGN1 1 1+0.000000000E+00+CONT | ||
| +CONT +2.315807152E+01+5.598048210E+00-2.515070677E+00-7.367168903E+00+CONT | ||
| +CONT -1.500793993E-01-3.773847222E-01-5.238612175E+00-3.897801042E-01+CONT | ||
| +CONT +7.907548547E-01+5.384410545E-02-1.403182447E-01-1.603935659E-02+CONT | ||
| +CONT -9.305058122E-01-1.193614081E-01 | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| $ OUTPUT TRANSIENT REPONSES ON FILE STRUTWNGN1.XLS FOR SUBCASE 2 $ | ||
| $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ | ||
| MLDPRNT 2 STRUTWNGN1.XLS TABLE TIME | ||
| FORCET1 1 FORCET1 8001 GRIDGT3 63 GRIDGT3 43 | ||
| GRIDXT1 8035 GRIDXT1 8041 | ||
| $ STORE ANIMATION OF THE STRUCTURAL DEFORMATION ON FILE STRUTWNGN1.PLT | ||
| PLTTIME 200 20 0. 10. 20 NORIGID TECPLOT | ||
| STRUTWNGN1.PLT | ||
| $...1..|...2...|...3...|...4...|...5...|...6...|...7...|...8...|...9...|...10..| | ||
| FLUTTER 101 SYM 22 15 | ||
| FIXMDEN 22 101 2.377E-3SLUG FT 1.68 | ||
| 650. | ||
| $ | ||
| $...1..|...2...|...3...|...4...|...5...|...6...|...7...|...8...|...9...|...10..| | ||
| $ | ||
| $ ROGER'S METHOD FOR RATIONAL AERODYNAMIC APPROXIMATION | ||
| $ | ||
| $...1..|...2...|...3...|...4...|...5...|...6...|...7...|...8...|...9...|...10..| | ||
| MINSTAT 1 122 30 | ||
| APCONST 30 1 -1 -1 1 1 1 1 | ||
| AEROLAG 122 8 | ||
| $ | ||
| $...1..|...2...|...3...|...4...|...5...|...6...|...7...|...8...|...9...|...10..| | ||
| $ | ||
| $ * AERO PARAMETERS / FLIGHT CONDITIONS * | ||
| $ | ||
| $...1..|...2...|...3...|...4...|...5...|...6...|...7...|...8...|...9...|...10..| | ||
| $ | ||
| AEROZ 0 YES NO SLUG FT 32.31 108.45 1. +A | ||
| +A 0. 0. 0. | ||
| MKAEROZ 101 0.53 | ||
| 0.02 0.5 1.0 1.5 2.0 2.5 3.0 3.5 | ||
| 4.0 4.5 5.0 | ||
| $ | ||
| $...1..|...2...|...3...|...4...|...5...|...6...|...7...|...8...|...9...|...10..| | ||
| $ | ||
| $ * AERODYNAMIC MODEL * | ||
| $ | ||
| $...1..|...2...|...3...|...4...|...5...|...6...|...7...|...8...|...9...|...10..| | ||
| $ | ||
| CAERO7 1000 WINGIB 17 15 +CA1 | ||
| +CA1 0. 0. 0. 32.31 0 0 +CA2 | ||
| +CA2 49.45145 74.4996 0. 14.7653 0 0 | ||
| SPLINE2 4501 4501 170 70 | ||
| SET1 170 1 THRU 50 | ||
| PANLST3 4501 WINGIB | ||
| CORD2R 70 13.9588 0. 0.0577 13.9588 0. 9.0577 +CRD1 | ||
| +CRD1 23.9588 -5.5983 0.0577 | ||
| $ $ | ||
| $ | ||
| CAERO7 1600 WINGOB 7 8 +CA1 | ||
| +CA1 49.45145 74.4996 0. 14.7653 0 0 +CA2 | ||
| +CA2 71.9871 108.45 0. 6.77 0 0 | ||
| SPLINE2 4502 4502 172 70 | ||
| SET1 172 40 THRU 63 | ||
| PANLST3 4502 WINGOB | ||
| $ $ | ||
| $...1..|...2...|...3...|...4...|...5...|...6...|...7...|...8...|...9...|...10..| | ||
| $ $ | ||
| CAERO7 2000 STRUT 16 4 +CA1 | ||
| +CA1 27.8889 0. -20.33 6.616 0 0 +CA2 | ||
| +CA2 53.5558 74.4996 -3.1678 6.616 0 0 | ||
| $ | ||
| SPLINE2 4506 4506 270 75 | ||
| SET1 270 8001 8005 8035 8041 8010 8020 8030 | ||
| PANLST3 4506 STRUT | ||
| CORD2R 75 30.2045 0.0000-20.33 29.4950 -2.05924 -10.33 +CRD1 | ||
| +CRD1 40.2045 -3.44524 -20.33 | ||
| $ | ||
| $...1..|...2...|...3...|...4...|...5...|...6...|...7...|...8...|...9...|...10..| | ||
| $ | ||
| CAERO7 3000 OFFSET 4 4 +CA1 | ||
| +CA1 53.5558 74.4996 0.0226 6.616 0 0 +CA2 | ||
| +CA2 53.5558 74.4996 -3.1678 6.616 0 0 | ||
| $ | ||
| SPLINE3 5501 5501 370 | ||
| SET1 370 8041 43 44 42 8035 | ||
| PANLST3 5501 OFFSET | ||
| ENDDATA |
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