$ FILE mm441.dat RUN MULTIPLE MASS CONFIGS ON ONE PASS $ MUST BE RUN SCR=NO. NOT YET TESTED FOR RESTART. $init master(s) $ do NOT do this. do NOT submit scr=yes $ FILE HA144A BORROWED FROM V69 TPL changes in lower case diag 8,15 $ SOL 144 $ STATIC AERO include 'mm44a.v2001' $ alter for multiple mass configs. in sol 144 CEND TITLE = EXAMPLE HA144A: 30 DEG FWD SWEPT WING WITH CANARD mm441 SUBTI = SYMMETRIC FLIGHT CONDITIONS, DOUBLET-LATTICE AERO LABEL = HALF-SPAN MODEL, STATIC SYMMETRIC LOADING, multiple mass configs ECHO = BOTH SPC = 1 $ SYMMETRIC CONSTRAINTS DISP = ALL $ PRINT ALL DISPLACEMENTS STRESS = ALL $ PRINT ALL STRESSES FORCE = ALL $ PRINT ALL FORCES AEROF = ALL $ PRINT ALL AERODYNAMIC FORCES APRES = ALL $ PRINT ALL AERODYNAMIC PRESSURES PARAM, WTMASS .031081 $ ABOVE SUBCASE LEVEL FOR ALL configs SUBCASE 1 TRIM = 1 $ 1 G LEVEL FLIGHT (LOW SPEED) M2PP = BASIC SUBCASE 2 TRIM = 2 $ 1 G LEVEL FLIGHT (HIGH SUBSONIC SPEED) M2PP = BASIC subcase 11 $ new subcases which call new incremental masses trim = 1 $ 1 g level flight (low speed) m2pp = config2 $ change in m2pp causes new loop subcase 21 trim = 1 $ m2pp = config4 BEGIN BULK $*** * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * ***$ $ $ $ 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. $ $ $ $*** * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * ***$ $ $ $ * * * STRUCTURAL DATA * * * $ $ $ $ (LB-FT-SEC SYSTEM) $ $ $ $ * * GRID GEOMETRY * * $ $ $ $ GRID 90 - 100 (T3) FUSELAGE POINTS $ $ GRID 110 - 122 (T3) WING POINTS $ $ $ $ * FUSELAGE GRID * $ $ $ $ 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. $ $ $ $ ID CP X1 X2 X3 CD PS SEID GRID 90 15. 0. 0. GRID 97 0. 0. 0. GRID 98 10. 0. 0. GRID 99 20. 0. 0. GRID 100 30. 0. 0. $ $ $ * WING GRID * $ $ $ $ ID CP X1 X2 X3 CD PS SEID GRID 111 24.61325 +5. 0. GRID 110 27.11325 +5. 0. GRID 112 29.61325 +5. 0. GRID 121 18.83975+15. 0. GRID 120 21.33975+15. 0. GRID 122 23.83975+15. 0. $ $ $ * * STRUCTURAL STIFFNESS PROPERTIES * * $ $ $ $ * FUSELAGE STRUCTURE * $ $ $ $ THE CBAR ENTRY DEFINES A SIMPLE BEAM ELEMENT. LISTED ARE $ $ ITS PROPERTY ENTRY ID, THE TWO GRID POINTS JOINED BY THE $ $ BEAM AND COMPONENTS OF A VECTOR FROM THE FIRST POINT. $ $ THIS VECTOR DEFINES THE DIRECTION OF THE STRUCTURAL DE- $ $ FLECTION OF THE POINT AND ITS POSITIVE SENSE. $ $ $ $ EID PID GA GB X1,GO X2 X3 CBAR 101 100 97 98 0. 0. 1. CBAR 102 100 98 90 0. 0. 1. CBAR 100 100 90 99 0. 0. 1. CBAR 103 100 99 100 0. 0. 1. $ $ $ THE PBAR ENTRY DEFINES GEOMETRIC PROPERTIES OF THE BEAM. $ $ LISTED ARE ITS ASSOCIATED MATERIAL ENTRY ID, ITS CROSS SEC- $ $ TIONAL AREA, AREA MOMENTS OF INERTIA, TORSIONAL MOMENT $ $ OF INERTIA AND NON-STRUCTURAL MASS PER UNIT AREA. THE $ $ OPTIONAL CONTINUATION ENTRY CONTAINS STRESS RECOVERY $ $ COEFFICIENTS, I.E., Y,Z COORDINATES WHERE STRESSES ARE $ $ TO BE COMPUTED. K1 AND K2 ARE AREA FACTORS FOR SHEAR $ $ STIFFNESS (DEFAULT IS BLANK; THEN SHEAR STIFFNESS IS $ $ INFINITE, I.E., SHEAR FLEXIBILITY IS ZERO. I12 IS THE $ $ AREA PRODUCT OF INERTIA. $ $ $ $ PID MID A I1 I2 J NSM PBAR 100 1 2.0 .173611 0.15 0.5 +PB1 $ C1 C2 D1 D2 E1 E2 F1 F2 +PB1 1.0 1.0 1.0 -1.0 -1.0 1.0 -1.0 -1.0 +PB2 $ K1 K2 I12 +PB2 0.0 $ $ $ * WING STRUCTURE * $ $ $ $ EID PID GA GB X1,GO X2 X3 CBAR 110 101 100 110 0. 0. 1. CBAR 120 101 110 120 0. 0. 1. $ $ $ THE RBAR ENTRY DEFINES A RIGID BAR. LISTED ARE THE GRID $ $ POINTS AT EACH END AND THE DEPENDENT AND INDEPENDENT DOFS $ $ AT EACH END. THE NUMBER OF INDEPENDENT DOFS AT THE TWO $ $ ENDS MUST EQUAL SIX. BY DEFAULT THOSE NOT DECLARED INDE- $ $ PENDENT ARE MADE DEPENDENT. $ $ $ $ EID GA GB CNA CNB CMA CMB RBAR 111 110 111 123456 RBAR 112 110 112 123456 RBAR 121 120 121 123456 RBAR 122 120 122 123456 $ $ $ PID MID A I1 I2 J NSM PBAR 101 1 1.5 0.173611+2.0 0.462963 +PB3 $ C1 C2 D1 D2 E1 E2 F1 F2 +PB3 0.5 3.0 0.5 -3.0 -0.5 3.0 -0.5 -3.0 +PB4 $ K1 K2 I12 +PB4 0.0 $ $ $ THE MAT1 ENTRY DEFINES THE MATERIAL PROPERTIES. LISTED $ $ ARE ITS ID, ITS ELASTIC MODULUS, SHEAR MODULUS, POISSONS $ $ RATIO, MASS DENSITY, TEMPERATURE EXPANSION COEFFICIENT, $ $ REFERENCE TEMPERATURE AND A STRUCTURAL DAMPING COEFFICIENT. $ $ $ $ MID E G NU RHO A TREF GE MAT1 1 1.44+9 5.40+8 $ $ $ * * MASS AND INERTIA PROPERTIES * * $ $ $ $ * FUSELAGE MASSES * $ $ $ $ THE CONM2 ENTRY DEFINES A CONCENTRATED MASS. LISTED ARE $ $ ITS ID, GRID LOCATION, COORDINATE SYSTEM TO LOCATE THE $ $ CENTER OF GRAVITY, THE MASS VALUE AND THE LOCATION OF $ $ THE CENTER OF GRAVITY RELATIVE TO THE GRID LOCATION. $ $ $ $ EID G CID M X1 X2 X3 CONM2 97 97 0 1500.0 CONM2 98 98 0 1500.0 CONM2 99 99 0 1500.0 CONM2 100 100 0 1500.0 $ $ $ * WING MASSES * $ $ $ CONM2 111 111 0 600.0 CONM2 112 112 0 400.0 CONM2 121 121 0 600.0 CONM2 122 122 0 400.0 $ $ $ * * STRUCTURAL PARAMETERS * * $ $ $ $ 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 90 $ $ $ 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 .031081 $ change for mm alters. put above subcase level to demo this function $ $ 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 .031081 $ $ $ * * STRUCTURAL CONSTRAINTS * * $ $ $ $ THE SPC1 ENTRY CONSTRAINS THE LISTED GRID POINTS IN THE $ $ SPECIFIED DOF COMPONENTS. $ $ $ $ SID C G1 G2 G3 G4 SPC1 1 1246 90 SPC1 1 246 97 98 99 100 $ $ $ 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. $ $ $ $ ID C SUPORT 90 35 $ $ $ THE OMIT1 ENTRY IDENTIFIES GRID POINT COMPONENTS TO BE $ $ OMITTED FROM THE REMAINDER OF THE ANALYSIS. $ $ $ $ ID G G OMIT1 4 110 120 $ $ $ * * * AERODYNAMIC DATA * * * $ $ $ $ (LB-FT-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. $ $ $ $ ACSID RCSID REFC REFB REFS SYMXZ SYMXY AEROS 1 100 10.0 40.0 200.0 1 $ $ $ THIS CORD2R ENTRY DEFINES THE AERO COORDINATE SYSTEM $ $ FLAGGED BY THE AEROS ENTRY. THE ORIGIN IS AT THE CANARD $ $ QUARTER CHORD. 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 12.5 0. 0. 12.5 0. 10. +CRD1 $ C1 C2 C3 +CRD1 20. 0. 0. $ $ $ THIS CORD2R ENTRY DEFINES THE NACA COORDINATE SYSTEM TO $ $ WHICH ALL THE STABILITY DERIVATIVES AND TRIM CONDITIONS $ $ WILL BE REFERENCED. $ $ $ $ CID RID A1 A2 A3 B1 B2 B3 CORD2R 100 0 15.0 0.0 0.0 15.0 0.0 -10.0 +CRD100 $ C1 C2 C3 +CRD100 0.0 0.0 0.0 $ $ $ * * 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. DTHX AND $ $ DTHY ARE ROTATIONAL ATTACHMENT FLEXIBILITIES (-1. SPECIFIES $ $ NO ATTACHMENT). $ $ $ $ EID CAERO ID1 ID2 SETG DZ DTOR CID SPLINE2 1601 1100 1100 1131 1100 0. 1. 2 +SPW $ DTHX DTHY +SPW -1. -1. $ $ $ 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 1100 1000 8 4 1 +CAW $ ( FWD LEFT POINT ) CHORD ( FWD RIGHT POINT ) CHORD $ X1 Y1 Z1 X12 X4 Y4 Z4 X14 +CAW 25. 0. 0. 10. 13.45299+20. 0. 10. $ $ $ 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 $ $ $ THE SET1 ENTRY DEFINES THE SETS OF STRUCTURAL GRID POINTS $ $ TO BE USED BY THE BEAM SPLINE FOR INTERPOLATION. $ $ $ $ SID G1 G2 G3 G4 SET1 1100 99 100 111 112 121 122 $ $ THE CORD2R ENTRY DEFINES THE COORDINATE SYSTEM IN WHICH THE $ $ BEAM SPLINE EXTENDS ALONG THE WING Y-AXIS. IT LISTS THE $ $ ORIGIN, A POINT ALONG THE Z-AXIS AND A POINT IN THE X-Z $ $ PLANE. $ $ $ $ CID CS A1 A2 A3 B1 B2 B3 CORD2R 2 0 30. 0. 0. 30. 0. 10. +CRD2 $ C1 C2 C3 +CRD2 38.66025+5.0 0. $ $ $ * 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 505 ELEV 1 1000 $ $ $ THE AELIST ENTRY LISTS AERODYNAMIC BOXES THAT LIE ON THE $ $ CONTROL SURFACE. $ $ $ $ SID E1 E2 E3 ETC AELIST 1000 1000 THRU 1007 $ $ $ * BEAM SPLINE FIT ON THE CANARD * $ $ $ $ AGRID PANEL (FIRST & LAST BOX)SGRID SPLCS SPLINE2 1501 1000 1000 1007 1000 0. 1. 1 +SPC +SPC 1. -1. $ $ $ PANEL PID CS NSPAN NCHORD IGP CAERO1 1000 1000 2 4 1 +CAC $ (FWD LEFT POINT ) CHORD (FWD RIGHT POINT ) CHORD +CAC 10. 0. 0. 10. 10. 5. 0. 10. $ $ $ SGRID GRID POINTS SET1 1000 98 99 $ $ $ $ $ * * * AERODYNAMIC DATA * * * $ $ $ $ * * USER SUPPLIED INPUT DATA * * $ $ $ $ THE DMI ENTRY ACCOMMODATES DIRECT INPUT OF USER SUPPLIED $ $ MATRICES OF DATA. LISTED ARE THE NAME OF THE MATRIX, THE $ $ FORM OF MATRIX (IN THIS CASE DIAGONAL), THE TYPE OF DATA $ $ (IN THIS CASE REAL SINGLE PRECISION), BEING INPUT AND THE $ $ TYPE EXPECTED AT OUTPUT (IN THIS CASE TO BE DETERMINED $ $ INTERNALLY). M IS THE NUMBER OF ROWS AND N IS THE NUMBER $ $ OF COLUMNS. THE DATA IS EXPECTED BY COLUMNS. THE CONTIN- $ $ UATION ENTRY LISTS THE COLUMN NO., THE ROW NO. OF THE FIRST $ $ NON-ZERO ELEMENT AND THE FOLLOWING ELEMENTS IN THAT COLUMN. $ $ $ $ * PRESSURE MODIFIERS (WEIGHTING MATRIX) * $ $ $ $ NAME "0" FORM TIN TOUT M N DMI WKK 0 3 1 0 80 1 $ NAME J I1 A(I1,J) A(I1+1,J) . . . DMI WKK 1 1 1.0 THRU 80 $ $ $ * INITIAL DOWNWASHES (E.G., DUE TO INCIDENCE,TWIST OR CAMBER) * $ $ $ DMI W2GJ 0 2 1 0 40 3 DMI W2GJ 1 9 .0017453THRU 40 DMI W2GJ 2 9 .0017453THRU 40 DMI W2GJ 3 9 .0017453THRU 40 $ $ $ * PRESSURES (E.G., AT ZERO ANGLE OF ATTACK) * $ $ $ DMI FA2J 0 2 1 0 40 3 DMI FA2J 1 1 0.0 THRU 40 DMI FA2J 2 1 0.0 THRU 40 DMI FA2J 3 1 0.0 THRU 40 $ $ $ $ $ * * * 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. $ $ $ $ ID LABEL AESTAT 501 ANGLEA AESTAT 502 PITCH AESTAT 503 URDD3 AESTAT 504 URDD5 $ $ $ * * 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: 1 G LEVEL FLIGHT AT LOW SPEED $ $ $ $ ID MACH Q LABEL1 UX1 LABEL2 UX2 +TRM TRIM 1 0.9 40.0 PITCH 0.0 URDD3 -1.0 +TR1 $ LABEL3 UX3 +TR1 URDD5 0.0 $ * * * $ $ TRIM CONDITION 2: 1 G LEVEL FLIGHT AT HIGH SUBSONIC SPEED $ $ $ TRIM 2 0.9 1200.0 PITCH 0.0 URDD3 -1.0 +TR2 +TR2 URDD5 0.0 $ * * * $ $ TRIM CONDITION 3: 1 G LEVEL FLIGHT AT LOW SUPERSONIC SPEED $ $ $ TRIM 3 1.3 1151.0 PITCH 0.0 URDD3 -1.0 +TR3 +TR3 URDD5 0.0 $INCLUDE 'ha144a.blk' $ file from tpl test problem of same name $ 2 3 4 5 6 7 8 9 10 $DTI MASSCF 1 MNAME S1 M1 SI MI ETC dti, masscf, 1, basic $ no incremental masses dti, masscf, 2, config2 1.0, 2 $ full tip store dti, masscf, 4, config4,0.2, 2 $ 0.2 factor * 0.5 store =.1 store begin auxmodel=2 $CONM2 122 122 0 400.0 conm2, 122 122 0 100.0 $PARAM WTMASS .031081 $ is set above case control level begin auxmodel = 4 conm2, 122 122 0 50.0 $ one half tip store enddata $