$ file statdiv1.dat demo statdiva.v2001 $ file ha144hl converted from hess to lanczos nastran system(108)=65536 $ request old sort. should be built in later ID MSC, HA144H $ V69 KLK 9-SEP-1996 $ID MSC, HA144B $$$$$$$$ HANDBOOK FOR AEROELASTIC ANALYSIS EXAMPLE HA144B $$$$$$$$ $ $ $ MODEL DESCRIPTION BAH JET TRANSPORT WING EXAMPLE $ $ CANTILEVERED WING WITH TEN BEAM $ $ ELEMENTS AND DUMBBELL MASSES $ $ $ $ SOLUTION STATIC AEROELASTIC SOLUTION TO $ $ AN AILERON DEFLECTION USING DOUBLET $ $ LATTICE METHOD AERODYNAMICS AT MACH $ $ NO. 0.0 $ $ $ $ OUTPUT PLOTS OF THE STICK MODEL AND AERO $ $ GRID, LISTS OF RESTRAINED AND $ $ UNRESTRAINED ANTISYMMETRIC STATIC $ $ STABILITY DERIVATIVES PLUS THE $ $ STRESSES AND DEFLECTIONS FOR A $ $ TYPICAL DESIGN CONDITION $ $ $ $$$$$$$$ $$$$$$$$ TIME 5 $ CPU TIME IN MINUTES DIAG 8,12,64 $ SOL 144 $ STATIC AERO include 'statdiva.v2001' $ print and plot divergence eigenvectors CEND title = demo use of statdiva.v2001 alter statdiv1 $TITLE = EXAMPLE HA144B: BAH JET TRANSPORT WING DYNAMIC ANALYSIS HA144H SUBTI = divergence analysis ECHO = BOTH SPC = 13 $ MPC = 1 $ CONTROL SURFACE RELATIVE MOTION $OUTPUT SET 2 = 7 THRU 12 SET 3 = 11 $ DISP = 2 DISP = ALL $ GET ALL EIGENVECTOR DATA SPCF = 3 AEROF = ALL APRES = ALL $ diverg = 100 cmethod = 100 $ clan subcase 11 $ add subcase for each mach number. diverg=101 $ one vector per mach number subcase 12 diverg=102 BEGIN BULK param, post, 0 $ put on xdb for patran plots $*** * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * ***$ $ $ $ THE ANNOTATIONS IN THIS INPUT SECTION ARE INTENDED TO $ $ EXPLAIN THE DATA ON THE ENTRY IMAGES FOR THIS SPECIFIC $ $ EXAMPLE WITHOUT REFERENCE TO THE VARIOUS MANUALS WHERE $ $ MORE GENERAL DESCRIPTIONS WILL BE FOUND. $ $ $ $*** * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * ***$ $ THE GRID ENTRY DEFINES THE LOCATION OF A STRUCTURAL GRID $ $ POINT. LISTED ARE ITS COORDINATE SYSTEM ID, ITS LOCATION, $ $ THE ID OF THE COORDINATE SYSTEM IN WHICH ITS DISPLACEMENTS $ $ ARE DEFINED, ITS PERMANENT SINGLE-POINT CONSTRAINTS, AND $ $ ITS ASSOCIATED SUPERELEMENT ID. $ $ $ $ THE BAH JET TRANSPORT WING, AS SHOWN ON P.45 OF THE BOOK $ $ "AEROELASTICITY" BY BISPLINGHOFF, ASHLEY AND HALFMAN, IS $ $ ROTATED 180 DEG AROUND THE Y AXIS. THAT ORIENTATION IS $ $ RETAINED HERE. POINTS 1 THRU 10 ARE ALONG THE ONE- AND $ $ THREE-QUARTER CHORD LINES, POINT 11 IS AT THE ROOT OF THE $ $ ELASTIC AXIS (35% CHORD), AND POINT 12 IS AT THE INBOARD $ $ TRAILING EDGE OF THE AILERON. $ $ $ $INCLUDE 'TPLDIR:bahstru.dat' $*** * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * ***$ $ $ $ * * * STRUCTURAL DATA * * * $ $ $ $ (LB-IN-SEC SYSTEM) $ $ $ $ * * GRID GEOMETRY * * $ $ $ $ GRID 1 - 10 (T3) WING CONTROL POINTS $ $ GRID 11 (T3,R1,R2) BODY $ $ (R3) WING ROOT HINGE $ $ GRID 12 (T3) AILERON TRAILING EDGE CONTROL POINT $ $ (R2) AILERON RELATIVE ROTATION $ $ EPOINT 115 AILERON HINGE MOMENT $ $ $ $ $ $ THE GRID ENTRY DEFINES THE LOCATION OF A STRUCTURAL GRID $ $ POINT. LISTED ARE ITS COORDINATE SYSTEM ID, ITS LOCATION, $ $ THE ID OF THE COORDINATE SYSTEM IN WHICH ITS DISPLACEMENTS $ $ ARE DEFINED, ITS PERMANENT SINGLE-POINT CONSTRAINTS, AND $ $ ITS ASSOCIATED SUPERELEMENT ID. $ $ $ $ THE BAH JET TRANSPORT WING, AS SHOWN ON P.45 OF THE BOOK $ $ "AEROELASTICITY" BY BISPLINGHOFF, ASHLEY AND HALFMAN, IS $ $ ROTATED 180 DEG AROUND THE Y AXIS. THAT ORIENTATION IS $ $ RETAINED HERE. POINTS 1 THRU 10 ARE ALONG THE ONE- AND $ $ THREE-QUARTER CHORD LINES, POINT 11 IS AT THE ROOT OF THE $ $ ELASTIC AXIS (35% CHORD). $ $ $ $ ID CP X1 X2 X3 CD PS SEID 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. 126 $ use soft bars to draw outlines. Stiffness is defined on genel cbar, 13, 13, 1, 3, 0. 0. 1. =, 24, =, 2, 4, == =, 35 =, 3 5, == =, 46, =, 4, 6, == =, 57, =, 5, 7, == =, 68, =, 6, 8, == =, 79, =, 7, 9, == $ =, 810, =, 8, 10, == $1.e-6, , pbar, 13, 13, 1. $ axial only mat1, 13, 1.e-6, , .3 $ very soft, massless. for viewing only $ $ $ $ $ * * STRUCTURAL STIFFNESS PROPERTIES * * $ $ $ $ * FLEXIBILITY INFLUENCE COEFFICIENTS * $ $ $ $ THE GENEL ENTRY DEFINES A GENERAL ELEMENT IN TERMS OF ITS $ $ STRUCTURAL INFLUENCE COEFFICIENTS. IT LISTS THE ELEMENT $ $ ID NO. AND PAIRS OF GRID POINT NUMBERS PLUS THEIR UNCON- $ $ STRAINED DOFS. THIS IS FOLLOWED BY THE CORRESPONDING PAIRS $ $ THAT WERE CONSTRAINED TO OBTAIN THE INFLUENCE COEFFICIENTS. $ $ THIS IS FOLLOWED BY THE LOWER TRIANGULAR PART OF THE MATRIX $ $ OF INFLUENCE COEFFICIENTS. FINALLY, A MATRIX OF GEOMETRIC $ $ CONSTANTS IS LISTED. THESE CONSTANTS PRODUCE TOTAL FORCES $ $ AND MOMENTS DUE TO DEFLECTIONS IN EACH MODE, IN THIS CASE $ $ LIFT, ROLLING MOMENT, PITCHING MOMENT AND WING ROOT BENDING $ $ MOMENT. $ $ $ $ EID UI1 CI1 UI2 CI2 UI3 CI3 GENEL 432 1 3 2 3 3 3 +01 $ UI4 CI4 UI5 CI5 UI6 CI6 UI7 CI7 +01 4 3 5 3 6 3 7 3 +02 $ UI8 CI8 UI9 CI9 UI10 CI10 +02 8 3 9 3 10 3 +03 $ "UD" UD1 CD1 UD2 CD2 UD3 CD3 +03 UD 11 3 11 4 11 5 +04 $ UD4 CD4 +04 11 6 +05 $ "K"|"Z" Z11 Z21 Z31 ETC (BY COLUMNS) +05 Z 8.7172-61.3361-61.2778-56.2720-61.6251-51.0492-52.0478-5+06 +06 1.5630-52.4285-52.0403-53.0861-56.2720-63.2297-51.0492-53.3529-5+07 +07 1.5630-53.5021-52.0257-53.5785-52.7732-51.5726-54.8255-53.7628-5+08 +08 7.3284-56.4338-59.5810-58.8378-56.3749-53.7628-58.0136-56.4338-5+09 +09 1.0012-48.8378-51.1811-41.2758-41.1344-41.9350-41.8160-42.5283-4+10 +10 2.4294-41.6999-41.8160-42.2920-42.4294-42.8249-43.6862-43.5052-4+11 +11 5.2675-45.1171-44.2292-45.1171-45.7187-48.4840-48.2340-49.2340-4+12 $ "S" S11 S12 S13 ETC (BY ROWS) +12 S 1.0 90.0 -20.25 45.0 1.0 90.0 81.0 +13 +13 45.0 1.0 186.0 -17.85 141.0 1.0 186.0 71.4 +14 +14 141.0 1.0 268.0 -15.80 223.0 1.0 268.0 63.2 +15 +15 223.0 1.0 368.0 -13.30 323.0 1.0 368.0 53.2 +16 +16 323.0 1.0 458.0 -11.05 413.0 1.0 458.0 44.2 +17 +17 413.0 $ $ $ $INCLUDE 'TPLDIR:bahmass.dat' $ $ $ * * MASS AND INERTIA PROPERTIES * * $ $ $ $ * WING MASSES * $ $ $ $ THE CMASS2 ENTRY DEFINES A SCALAR MASS ELEMENT WITHOUT $ $ REFERENCE TO A PROPERTY ENTRY. IT LISTS THE MASS, THE $ $ GRID NO. AND ITS DOF COMPONENTS. WHEN TWO GRID POINTS $ $ ARE LISTED THE MASS IS ADDED TO BOTH POINTS. $ $ $ $ EID M G1 C1 G2 C2 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 $ $ $ * FUSELAGE MASS AND INERTIA VALUES * $ $ $ $ THE CONM1 ENTRY DEFINES A 6 BY 6 SYMMETRIC INERTIA MATRIX $ $ FOR A GRID POINT. LISTED IS THE ID, THE GRID POINT NO., $ $ THE COORDINATE SYSTEM IN WHICH THE INERTIA MATRIX IS $ $ DEFINED AND THE LOWER LEFT TRIANGULAR PART OF THE MATRIX. $ $ $ $ EID G CID M11 M21 M22 M31 M32 CONM1 1 11 +51 $ M33 M41 M42 M43 M44 M51 M52 M53 +51 17400. 4.37+7 +52 $ M54 M55 M61 M62 M63 M64 M65 M66 +52 4.35+09 $ $ $ * * STRUCTURAL PARAMETERS * * $ $ $ $ THE PARAM,WTMASS,GINV CAUSES ALL THE STRUCTURAL MASSES AND $ $ MASS DENSITIES TO BE MULTIPLIED BY GINV (I.E., BY ONE OVER $ $ THE ACCELERATION OF GRAVITY). THE DYNAMIC PRESSURE SUPPLIED $ $ FOR AERODYNAMIC FORCE CALCULATIONS WILL NOT BE MULTIPLIED $ $ BY GINV. $ $ $ PARAM WTMASS .0025907 $ $ $ THE PARAM,GRDPNT,XX ENTRY CAUSES THE GRID POINT WEIGHT $ $ GENERATOR TO BE EXECUTED USING GRID POINT XX AS THE REF- $ $ ERENCE POINT. THEN THE INERTIA MATRIX, THE TRANSFER MATRIX $ $ FROM BASIC TO PRINCIPAL AXES AND OTHER PERTINENT INERTIA $ $ DATA ARE PRINTED. $ $ $ PARAM GRDPNT 11 $ $ $ $INCLUDE 'TPLDIR:bahaile.dat' $ DEC/CMS REPLACEMENT HISTORY, Element BAHAILE.DAT $ *1 5-JUL-1994 16:44:58 A_BOYADJIAN "68 PLUS/G/ NEW FOR V68 AERO_SS BOOK" $ DEC/CMS REPLACEMENT HISTORY, Element BAHAILE.DAT $ GRID 12 IS INBOARD OF THE AILERON AND ON THE TRAILING EDGE; $ IT IS ALIGNED STREAMWISE BEHIND GRIDS 7 AND 8 AND PROVIDES $ THE MEANS TO INCLUDE THE AILERON IN THE ANALYSIS. $ $ ID CP X1 X2 X3 CD PS SEID GRID 12 -86.45 368. 1246 $ $ $ THE CELAS2 ENTRY DEFINES A SCALAR SPRING ELEMENT WITHOUT $ $ REFERENCE TO A PROPERTY ENTRY, IN THIS CASE AN AILERON $ $ HINGE SPRING STIFFNESS. IT LISTS THE ID, THE STIFFNESS, $ $ THE CONNECTION POINT AND DOF COMPONENT. $ $ $ $ EID K G1 C1 CELAS2 3 5142661.12 5 $ $ $ * * AILERON INERTIAL PROPERTIES * * $ $ CONM1 2 12 +AIL1 +AIL1 0.0 0.0 +AIL2 +AIL2 13970.5 $ $ THE MPC ENTRY DEFINES A MULTIPOINT CONSTRAINT IN THE FORM $ $ OF A LINEAR EQUATION. IT LISTS A SET OF TRIPLES CONSISTING $ $ OF THE GRID NO., THE CONSTRAINED DOF COMPONENTS AND THE $ $ LINEAR COEFFICIENT. $ $ $ $ THIS ONE SPECIFIES THAT THE Z DISPLACEMENT AT THE TRAILING $ $ EDGE OF THE AILERON IS A LINEAR EXTRAPOLATION FROM POINTS $ $ 7 AND 8 PLUS THE DISTANCE FROM THE HINGE-LINE TO THE $ $ TRAILING EDGE TIMES A UNIT (SMALL), ANGULAR ROTATION OF THE $ $ AILERON. SEE P.3.5-9 OF THE "HANDBOOK FOR DYNAMIC ANALYSIS" $ $ FOR A DISCUSSION OF THE LAGRANGE MULTIPLIER METHOD WHICH $ $ IS USED HERE TO INTRODUCE THE AILERON ROTATION DOF. $ $ $ $ SID G C A G C A MPC 1 12 3 -1.0 8 3 1.5 +MPC1 $ G C A G C A +MPC1 7 3 -0.5 12 5 33.25 $ $ $ $ * * STRUCTURAL CONSTRAINTS * * $ $ $ $ THE SPC ENTRY DEFINES SETS OF SINGLE-POINT CONSTRAINTS $ $ AND ENFORCED DISPLACEMENTS. IT LISTS THE ID, GRID POINT $ $ NO., CONSTRAINED DOFS AND VALUE OF AN ENFORCED DISPLACE- $ $ MENT. $ $ $ $ SID G C D SPC 13 11 345 $ $ $ THE SUPORT ENTRY IDENTIFIES A GRID POINT OR A SCALAR POINT $ $ AND SPECIFIES THE DOF COMPONENTS IN WHICH THE USER DESIRES $ $ REACTIONS TO BE APPLIED TO PREVENT RIGID BODY MOTION. IT $ $ THUS INVOKES THE SOLUTION OF THE BALANCE EQUATIONS TO DETER- $ $ MINE THE REACTIONS. IN THE STATIC AEROELASTIC SOLUTION $ $ THE DOF COMPONENTS MUST BE CONSISTENT WITH THE UNDEFINED $ $ VARIABLES ON THE TRIM ENTRIES. $ $ $ $SUPORT 11 4 $ $ $ $ $ * * * AERODYNAMIC DATA * * * $ $ $ $ (LB-IN-SEC SYSTEM) $ $ $ $ * * ELEMENT GEOMETRY * * $ $ $ $ THE AEROS ENTRY IS UNIQUE TO THE STATIC AEROELASTICITY $ $ SOLUTION, SOL21. ACSID IDENTIFIES THE AERO COORDINATE $ $ SYSTEM. RCSID IDENTIFIES THE REFERENCE COORDINATE SYS- $ $ TEM FOR RIGID BODY MOTION. REFC IS THE REFERENCE CHORD. $ $ REFB IS THE REFERENCE SPAN. REFS IS THE REFERENCE WING $ $ AREA. SYMXZ AND SYMXY ARE SYMMETRY KEYS. $ $ $ $ ACS RCID CHORD SPAN AREA SYMYZ SYMXY AEROS 1 1 162.5 1000.0 81250.0 1 $ $ $ $ $ * CONTROL SURFACE DEFINITION * $ $ $ $ THE AESURF ENTRY DEFINES AN AERODYNAMIC CONTROL SURFACE. $ $ LISTED ARE THE ALPHANUMERIC NAME OF THE SURFACE, THE ID $ $ OF A COORDINATE SYSTEM THAT DEFINES THE HINGE LINE AND $ $ THE ID OF AN AELIST ENTRY. $ $ $ $ ID LABEL CID1 ALID1 CID2 ALID2 AESURF 503 AILE 10 2005 $ $ $ THE CORD2R ENTRY DEFINES THE COORDINATE SYSTEM IN WHICH THE $ $ HINGE-LINE IS DEFINED. IT LISTS THE ORIGIN, A POINT ALONG $ $ THE Z-AXIS AND A POINT IN THE X-Z PLANE. $ $ $ $ CID RID A1 A2 A3 B1 B2 B3 CORD2R 10 -90.0 0. 0. -90.0 0. 1. +CR10 $ C1 C2 C3 +CR10 410.0 -50.0 0.0 $ $ $INCLUDE 'TPLDIR:aero58.dat' $ DEC/CMS REPLACEMENT HISTORY, Element AERO58.DAT $ *1 5-JUL-1994 16:44:37 A_BOYADJIAN "68 PLUS/G/ NEW FOR V68 AERO_SS BOOK" $ DEC/CMS REPLACEMENT HISTORY, Element AERO58.DAT $ THIS CORD2R ENTRY DEFINES THE AERO COORDINATE SYSTEM $ $ FLAGGED BY THE AEROS ENTRY. THE ORIGIN IS AT THE ROOT $ $ OF THE ELASTIC AXIS. LISTED ARE THE ORIGIN, A POINT $ $ ALONG THE Z AXIS AND A POINT IN THE X-Z PLANE, ALL IN $ $ THE RID COORDINATE SYSTEM. $ $ $ $ CID RID A1 A2 A3 B1 B2 B3 CORD2R 1 0. 0. 0. 0. 0. -1. +C1 $ C1 C2 C3 +C1 -1. 0. 0. $ $ $ $ $ THE CAERO1 ENTRY IS USED FOR DOUBLET-LATTICE AERODYNAMICS. $ $ LISTED ARE ITS PAERO ENTRY ID AND THE COORDINATE SYSTEM $ $ FOR LOCATING THE INBOARD AND OUTBOARD LEADING EDGE POINTS $ $ (1 AND 4). NSPAN AND NCHORD, OR LSPAN AND LCHORD, ARE $ $ USED TO PARTITION THE WING INTO AERODYNAMIC PANELS, $ $ THE FORMER FOR UNIFORMLY SPACED PANELS AND THE LATTER $ $ FOR NON-UNIFORMLY SPACED PANELS. IGID IS THE ID OF ITS $ $ ASSOCIATED INTERFERENCE GROUP. THE CONTINUATION ENTRY $ $ DEFINES POINTS 1 AND 4, THE ROOT CHORD AND TIP CHORD. $ $ THE BOXES FORMED BY THE GRID LINES WILL BE NUMBERED $ $ BEGINNING WITH EID SO CHOOSE A NUMBER THAT IS UNIQUE, $ $ AND IS GREATER THAN ALL STRUCTURAL GRID, SCALAR AND $ $ EXTRA POINT IDS. $ $ $ $ EID PID CP NSPAN NCHORD LSPAN LCHORD IGID CAERO1 1001 1000 0 5 1 1 +CA1 $ ( FWD LEFT POINT ) ROOTCHORD ( FWD RIGHT POINT ) TIP CHORD +CA1 78.75 0. 0. 225. 35. 500. 0. 100. $ CAERO1 2001 1000 0 2 4 1 +CA2 +CA2 78.75 0. 0. 225. 35. 500. 0. 100. $ CAERO1 3001 1000 0 5 3 1 +CA3 +CA3 78.75 0. 0. 225. 35. 500. 0. 100. $ $ $ THE AEFACT ENTRY IS A UTILITY ENTRY USED TO SPECIFY LISTS OF $ $ NUMBERS. IN THIS EXAMLPLE THEY ARE IDENTIFIED BY THE ABOVE $ $ CAERO1 ENTRIES. THE FIRST ENTRY DEFINES THE SPANWISE DIVI- $ $ SIONS INBOARD OF THE AILERON. $ $ $ $ THE SECOND ONE DEFINES THE SPANWISE DIVISIONS ACROSS THE $ $ AILERON. $ $ $ $ THE THIRD ONE DEFINES THE SPANWISE DIVISIONS OF THE TIP $ $ FAIRING. $ $ $ $ THE FOURTH ONE DEFINES THE CHORDWISE DIVISIONS OF THE $ $ AILERON. THE AILERON HINGE-LINE IS AT THE THREE-QUARTER $ $ CHORD LINE SO THERE ARE TWO CHORDWISE BOXES ON THE $ $ AILERON. $ $ $ $ SID D1 D2 D3 D4 D5 D6 D7 AEFACT 1 0. .09 .21 .33 .45 .56 .66 +AE1 $ D8 +AE1 .74 $ $ AEFACT 2 .74 .82 .90 .974 $ $ AEFACT 3 .974 1.00 $ $ AEFACT 4 0. .1875 .375 .625 .750 .875 1.00 $ $ $ $ $ THE PAERO1 ENTRY IS REQUIRED EVEN THOUGH IT IS NON-FUNCTIONAL $ $ (BECAUSE THERE ARE NO ASSOCIATED BODIES IN THIS EXAMPLE). $ $ $ $ PID B1 B2 B3 B4 B5 B6 PAERO1 1000 $ $ $ * * SPLINE FIT ON THE LIFTING SURFACES * * $ $ $ $ * BEAM SPLINE FIT ON THE WING * $ $ $ $ THE SPLINE2 ENTRY SPECIFIES A BEAM SPLINE FOR INTERPOLAT- $ $ ION OVER THE REGION OF THE CAERO ENTRY (ID1 AND ID2 ARE $ $ THE FIRST AND LAST BOXES IN THIS REGION). SETG REFERS $ $ TO A SET1 ENTRY WHERE THE STRUCTURAL GRID POINTS ARE $ $ DEFINED. DZ AND DTOR ARE SMOOTHING CONSTANTS FOR LINEAR $ $ ATTACHMENT AND TORSIONAL FLEXIBILITIES. CID IDENTIFIES $ $ THE CORD2R ENTRY THAT DEFINES THE SPLINE AXIS. DHTX AND $ $ DTHY ARE ROTATIONAL ATTACHMENT FLEXIBILITIES (-1.0 SPECI- $ $ FIES NO ATTACHMENTS). $ $ $ $ EID CAERO ID1 ID2 SETG DZ DTOR CID SPLINE2 101 1001 1001 1035 14 0. 1. 0 +SP1 $ DTHX DTHY +SP1 -1.0 -1.0 $ SPLINE2 102 2001 2001 2016 14 0. 1. 0 +SP2 +SP2 -1.0 -1.0 $ SPLINE2 103 3001 3001 3005 14 0. 1. 0 +SP3 +SP3 -1.0 -1.0 $ $ $ $ $ THE SET1 ENTRY DEFINES THE SETS OF POINTS TO BE USED BY $ $ THE SURFACE SPLINE FOR INTERPOLATION. $ $ $ $ SID G1 G2 G3 G4 G5 G6 SET1 14 1 THRU 11 $ $ $ $ $ THE AELIST ENTRY LISTS AERODYNAMIC BOXES THAT LIE ON THE $ $ CONTROL SURFACE. $ $ $ $ SID E1 E2 E3 ETC AELIST 2005 2005 2006 2011 2012 2017 2018 $ $ $ * BEAM SPLINE FIT ON THE AILERON * $ $ $ $ THE SPLINE1 ENTRY DEFINES A SURFACE SPLINE FOR INTERPO- $ $ LATING OUT-OF-PLANE DISPLACEMENTS FROM THE STRUCTURAL $ $ GRID POINTS ON THE SETG ENTRY TO THE SUB-REGION DEFINED $ $ BY AERODYNAMIC BOXES 2005 THRU 2018 OF THE REGION ON THE $ $ CAERO1 ENTRY. DZ=0 SPECIFIES THAT NO SMOOTHING OF THE $ $ SPLINE IS TO BE IMPOSED. $ $ $ $ EID CAERO BOX1 BOX2 SETG DZ SPLINE1 104 2001 2005 2018 15 $ $ $ THE SET1 ENTRY DEFINES THE SETS OF POINTS TO BE USED BY $ $ THE SURFACE SPLINE FOR INTERPOLATION. $ $ $ $ SID G1 G2 G3 G4 G5 G6 SET1 15 8 10 12 $ $ $ $ $ * * * SOLUTION SPECIFICATIONS * * * $ $ $ $ * * AERODYNAMIC DOFS * * $ $ $ $ THE AESTAT ENTRY LISTS TRIM VARIABLES USED TO SPECIFY $ $ RIGID BODY MOTIONS. THESE AND THE CONTROL SURFACE $ $ ROTATIONS MAKE UP THE VARIABLES IN THE EQUATIONS OF $ $ MOTION. $ $ $ AESTAT 501 ROLL AESTAT 502 URDD4 $ $ $ * * TRIM CONDITIONS * * $ $ $ $ THE TRIM ENTRY SPECIFIES CONSTRAINTS FOR THE TRIM VARIABLES $ $ LISTED ON THE AESTAT AND AESURF ENTRIES. LISTED ARE ITS ID, $ $ THE MACH NUMBER, DYNAMIC PRESSURE AND PAIRS OF TRIM VARI- $ $ ABLES AND THEIR CONSTRAINED VALUES. THOSE THAT ARE NOT $ $ HELD FIXED MUST BE CONSTRAINED BY REACTION FORCES STIPU- $ $ LATED ON THE SUPORT ENTRY. SEE SECTION 3.5.3 OF THE THEO- $ $ RETICAL MANUAL FOR MORE DETAILS. $ $ $ $ TRIM CONDITION 1: STEADY ROLL $ $ $ $ ID MACH Q LABEL1 UX1 LABEL2 UX2 $ TRIM 1 0.0 4.0075 URDD4 0.0 AILE 1.0 $ $ $ THE PARAM,AUNITS,GINV PERMITS THE ACCELERATIONS ON THE TRIM $ ENTRY TO BE SPECIFIED IN UNITS OF LOAD FACTOR (I.E., IN G'S) $ PARAM AUNITS .0025907 $diverg 100 5 0.0 $ NROOT MACH NUMBER ONLY ONE OF EACH ALLOWED PER DEIVERGE ENTRY diverg, 101, 1, 0.0 $ diverg, 102, 1, 0.1 EIGC 100 CLAN MAX 5 $ ENDDATA