$ ID PROP, TEST ID PROP, PROP2 $ $ test of generating QJH matrix with PROP alters in deck - no dmig $ $ $ SAMPLE AERO PROBLEM WITH PROP TERMS - BAH WING/NACELLE WITH 7 FT PROP $ TIME 100 diag 8 sol 145 $ $ include 'propa.v2001' $ CEND TITLE = PROP WHIRL SAMPLE - BAH WING/NACELLE WITH 7 FT 4-BLADE PROP2 SUBT = BAH WING WITH NACELLE AND PROP LABEL = PK-FLUTTER SOLUTION SEALL = ALL $ SOL 75 HAS SUPERELEMENT CAPABILITY ECHO = BOTH $ ANNOTATED AND SORTED INPUT DATA SPC = 1 $ CONSTRAINT AT FUSELAGE/WING-E.A. INTERSECTION MPC = 99 $ CONSTRAINTS FOR NACELLE ROTATIONS METHOD = 10 $ MODIFIED GIVENS FOR VIBES SVEC = ALL $ PRINT VIBRATION MODES DISP = ALL $ PRINT FLUTTER MODES $ SDAMP = 2000 $ INCLUDE 2% STRUCTURAL DAMPING ON ALL MODES SUBCASE 10 FMETHOD = 5 $ PK-FLUTTER METHOD - V = 2400 K2PP=AEROS101 B2PP=AEROB101 SUBCASE 14 FMETHOD = 10 $ PK-FLUTTER METHOD - V = 3600 K2PP=AEROS102 B2PP=AEROB102 SUBCASE 20 FMETHOD = 20 $ PK-FLUTTER METHOD - V = 4800 K2PP=AEROS103 B2PP=AEROB103 SUBCASE 30 FMETHOD = 30 $ PK-FLUTTER METHOD - V = 6000 K2PP=AEROS104 B2PP=AEROB104 SUBCASE 40 FMETHOD = 40 $ PK-FLUTTER METHOD - V = 7200 K2PP=AEROS105 B2PP=AEROB105 SUBCASE 50 FMETHOD = 50 $ PK-FLUTTER METHOD - V = 9600 K2PP=AEROS106 B2PP=AEROB106 SUBCASE 60 FMETHOD = 60 $ PK-FLUTTER METHOD - V = 12000 K2PP=AEROS107 B2PP=AEROB107 SUBCASE 70 FMETHOD = 70 $ PK-FLUTTER METHOD - V = 14400 K2PP=AEROS108 B2PP=AEROB108 SUBCASE 80 FMETHOD = 80 $ PK-FLUTTER METHOd - V = 16800 K2PP=AEROS109 B2PP=AEROB109 SUBCASE 90 FMETHOD = 90 $ PK-FLUTTER METHOD - V = 19200 K2PP=AEROS110 B2PP=AEROB110 SUBCASE 100 FMETHOD = 100 $ PK-FLUTTER METHOD - V = 21600 K2PP=AEROS111 B2PP=AEROB111 BEGIN BULK param,usetprt,2 $ $ add partn1 and 2 to partition qjh $ $ pick dof 29 = prop z int. element: select with PARTN1 $ dmi,partn1,0,2,1,0,,40,1 dmi,partn1,1,29,1. $ $ select interference elements with PARTN2: in this case dof 29 thru 34 $ dmi,partn2,0,2,1,0,,40,1 dmi,partn2,1,29,1.,thru,34 $ $ $ PROP HUB IS GRID 99 - ATTACHED TO SPOINTS VIA MPCS FOR FREQUENCIES $ GRID 99 137.48 186.0 0.0 15 14 $ RELATIVE PITCH ANGLE OF NACELLE SPOINT 100 $ RELATIVE YAW ANGLE OF NACELLE SPOINT 102 $ MPCS FOR NACELLE SPRINGS AND HUB DOFS $ SID G C A G C A ETC MPC 99 100 119.63 3 3 -2.34039 +MPC100 +MPC100 4 3 1.34039 99 3 1.0 MPC 99 99 5 89.25 3 3 1.0 +MPC101 +MPC101 4 3 -1.0 100 -89.25 MPC 99 102 119.63 99 2 -1.0 MPC 99 99 6 1.0 102 -1.0 $ $2345678123456781234567812345678123456781234567812345678123456781234567812345678 $ CONCENTRATED MASS FOR PROP $ EID G CID M X1 X2 X3 CONM2 99 99 400.0 +PROP $ I11 I21 I22 I31 I32 I33 +PROP 864000. 432000. 432000. $ $ CELAS4 SPRINGS FOR NACELLE ATTACHMENT $ $ PITCH SPRING $ EID K S1 S2 ETC CELAS4 1 19.2+6 100 $ YAW SPRING CELAS4 2 24.0+6 102 $ $BAH WING DATA FROM HA75B.DAT AERO 1 131.232 1.1468-71 $ INB0ARD WING AERO $ EID PID CP NSPAN NCHORD LSPAN LCHORD IGID +CONT CAERO1 1001 1001 0 4 77 1 +CA1 $ X1 Y1 Z1 X12 X4 Y4 Z4 X14 +CA1 78.75 0.0 0.0 225.0 35.0 500.0 0.0 100.0 AEFACT 77 .0 .09 .213 .336 $ OUTBOARD WING AERO CAERO1 1013 1001 0 4 78 1 +CA13 +CA13 78.75 0.0 0.0 225.0 35.0 500.0 0.0 100.0 AEFACT 78 .408 .556 .704 .852 1.0 $ PID B1 B2 B3 ETC PAERO1 1001 2001 $ INBOARD WING SPLINE SPLINE2 101 1001 1005 1012 14 0.0 1.0 0 +SP101 +SP101 -1.0 -1.0 SET1 14 1 THRU 11 $ OUTBOARD WING SPLINE SPLINE2 113 1013 1013 1028 15 0.0 1.0 0 +SP113 +SP113 -1.0 -1.0 SET1 15 1 THRU 11 $ENGINE NACELLE AERO VIA CAERO2 & PAERO2 AT W.S. 186.0 $ EID PID CP NSB NINT LSB LINT IGID +CONT CAERO2 2001 2001 0 2001 2001 1 +CA2 $ X1 Y1 Z1 X12 +CA2 162.48 186.0 0.0 278.5 AEFACT 2001 0.0 0.180 0.359 0.593 0.680 0.840 1.0 $ PID ORIENT WIDTH AR LRSB LRIB LTH1 LTH2 +CONT PAERO2 2001 Z 18.0 1.0 2010 2018 +PA2 $ THI1 THN1 THI2 THN2 +PA2 1 6 AEFACT 2010 0.0 13.5 18.0 18.0 18.0 18.0 18.0 AEFACT 2018 90.0 270.0 $ NACELLE SPLINE SPLINE2 201 2001 2001 2006 16 0.0 1.0 0 +SP201 +SP201 -1.0 SET1 16 3 4 99 CMASS2 121 5248.7 1 3 CMASS2 122 134.9 1 3 2 3 CMASS2 123 790.3 2 3 CMASS2 341 9727. 3 3 CMASS2 342 11005. 3 3 4 3 CMASS2 343 473. 4 3 CMASS2 561 3253.6 5 3 CMASS2 562 -139.7 5 3 6 3 CMASS2 563 946.3 6 3 CMASS2 781 2617.8 7 3 CMASS2 782 21. 7 3 8 3 CMASS2 783 782.3 8 3 CMASS2 9101 494.8 9 3 CMASS2 9102 -7.3 9 3 10 3 CMASS2 9103 185.2 10 3 CONM1 1 11 +51 +51 17400. 4.37+7 +52 +52 4.35+09 $ $ coordinate system for prop point $ CORD2R 15 0. 0. 0. 0. 0. 1. +cr15 +cr15 1. 0. 0. CORD2R 1 0. 0. 0. 0. 0. -1. +C1 +C1 -1. 0. 0. EIGR 10 MGIV 12 +EIGR +EIGR MAX FLFACT 1 1. DENSITY FLFACT 2 .0 MACH NO FLFACT 3 2400. VELOCITY FLFACT 4 3600. VELOCITY FLFACT 5 4800. VELOCITY FLFACT 6 6000. VELOCITY FLFACT 7 7200. VELOCITY FLFACT 8 9600. VELOCITY FLFACT 9 12000. VELOCITY FLFACT 10 14400. VELOCITY FLFACT 11 16800. VELOCITY FLFACT 12 19200. VELOCITY FLFACT 13 21600. VELOCITY FLUTTER 5 PK 1 2 3 L 5 FLUTTER 10 PK 1 2 4 L 5 FLUTTER 20 PK 1 2 5 L 5 FLUTTER 30 PK 1 2 6 L 5 FLUTTER 40 PK 1 2 7 L 5 FLUTTER 50 PK 1 2 8 L 5 FLUTTER 60 PK 1 2 9 L 5 FLUTTER 70 PK 1 2 10 L 5 FLUTTER 80 PK 1 2 11 L 5 FLUTTER 90 PK 1 2 12 L 5 FLUTTER 100 PK 1 2 13 L 5 GENEL 432 1 3 2 3 3 3 +01 +01 4 3 5 3 6 3 7 3 +02 +02 8 3 9 3 10 3 +03 +03 UD 11 3 11 5 +04 +04 Z 8.7172-61.3361-61.2778-56.2720-61.6251-51.0492-52.0478-5+05 +05 1.5630-52.4285-52.0403-53.0861-56.2720-63.2297-51.0492-53.3529-5+06 +06 1.5630-53.5021-52.0257-53.5785-52.7732-51.5726-54.8255-53.7628-5+07 +07 7.3284-56.4338-59.5810-58.8378-56.3749-53.7628-58.0136-56.4338-5+08 +08 1.0012-48.8378-51.1811-41.2758-41.1344-41.9350-41.8160-42.5283-4+09 +09 2.4294-41.6999-41.8160-42.2920-42.4294-42.8249-43.6862-43.5052-4+10 +10 5.2675-45.1171-44.2292-45.1171-45.7187-48.4840-48.2340-49.2340-4+11 +11 S 1.0 -20.25 1.0 81.0 1.0 -17.85 1.0 +12 +12 71.4 1.0 -15.8 1.0 63.2 1.0 -13.3 1.0 +13 +13 53.2 1.0 -11.05 1.0 44.2 GRID 1 20.25 90. 12456 GRID 2 -81. 90. 12456 GRID 3 17.85 186. 12456 GRID 4 -71.4 186. 12456 GRID 5 15.8 268. 12456 GRID 6 -63.2 268. 12456 GRID 7 13.3 368. 12456 GRID 8 -53.2 368. 12456 GRID 9 11.05 458. 12456 GRID 10 -44.2 458. 12456 GRID 11 0.0 0. 1246 MKAERO1 0. +MK +MK 0.001 0.05 0.10 0.20 0.50 1.0 PARAM GRDPNT 11 PARAM KDAMP -1 PARAM W4 57.554 PARAM LMODES 5 PARAM VREF 12.0 PARAM WTMASS .0025901 SPC1 1 35 11 $ $ ADD TABDMP1 FOR STRUCTURAL DAMPING $ TABDMP1 2000 +T2000 +T2000 0.0 0.00 10.0 0.00 ENDT ENDDATA