REWARD

CAE SETS (Structure Engineering Turnkey System): True #1

TRUE NO. 1 in STRUCTURE ENGINEERING

REWARD: STAAD CAPABILITY and others:
In one single run, any one who solves the example problem below correctly:

1) Using any one of existing STAAD series Programs:

All four loading cases: US$2000.00 for the earliest TEN (10) entities.

Extra: Solve one loading case: US$50.00 for the earliest TEN(10) entities.

All four loading cases:
US$1000.00
for the earliest FIVE(5) entities.
- Extra: Solve one loading case: US$50.00 for the earliest FIVE(5) entities.

US$500.00 for using any other existing competitor's programs for the FIRST entity per each developer upto TEN(10) entities total.

3-1) All four loading cases.
- Extra: Solve one loading case with loading diagram in ISOMETRIC VIEWS that retain, for any one group of parallel lines, correct proportion in length vs true length to enable you to check visually the correctness of NODE COORDINATES:US$10.00 for the FIRST entity per each developer upto ONE Hundred(100) entities total.

3-2) All four loading cases with loading diagram in ISOMETRIC VIEWS that retain, for any one group of parallel lines, correct proportion in length vs true length to enable you to check visually the correctness of NODE COORDINATES.

HOW TO CLAIM:

Obtain your solution from your software if it can do for you.

log on to the COMPUTATION CENTER:

Go to Your Account Folder. See Home Page: Open a user account

Deposit your solution there, identify yourself, what year the software acquired,what version/release, what system used and other pertinent info.

People who claim less than US$50.00 can send to email: support@caesets.net

CAESETS solution is located at: NEXT FOLDER

$ POWERFUL EXAMPLE OF NON-LINEAR ANALYSYS:

$ ONE SET OF INPUT WITH ONE SET OF OUTPUT IN ONE RUN FOR FINAL RESULTS

$ TO OBTAIN UNLIMITED NUMBER OF LOAD CASES INCLUDING CORRECT NON-LINEAR

$ EFFECT OF LOAD COMBINATIONS. (Say; 1.4 DL + 1.7 LL + 1.33 WL)

$ OTHER COMPETITOR'S PROGRAM NEXT IN LINE IN CAPABILITY IS TO MANUALLY

$ INPUT, MANUALLY STUDY RESULTS IN SEQUENCES WITH 100 SETS OF INPUT AND

$ 100 SETS OF OUTPUTS OR MORE.

$ IT IS A SMALL JOB HERE FOR USP VS OTHERS, A BIG PROJECT BEYOND

$ ECONOMIC ALLOWABLE.

$ 3-D GABLE STRUCTURE WITH GEOMETRICAL AND LOADING SYMMETRY

$ THE OUTPUT IS CONSISTENT IN THE FORM OF 4 OF A KIND OR A PAIR

$ THUS IT CAN BE VISUALLY AND QUICKLY VERIFIED AS A ROUGH CHECK.

$ CAEINC. WARRANTS THAT PROGRAM SHALL PERFORM SUBTANTIALLY IN COMPLIANCE

$ WITH SPECIFICATIONS. HERE IS A SMALL TIP ON HOW YOU CAN VERIFY IT.

$ THOUGH, THE EXAMPLE CONTAINS POWERFUL NON-LINEAR THEORY, OBLIQUE COOR-

$ NATE AND SUPPORT MOVEMENTS.

$ MANUALLY, THE RESULT CAN BE CHECKED FOR STATIC EQUILIBRIUM AND

$ COMPATABILITY IN STRAIN VS STRESS RELATIONSHIP.

$ A SOPHOREMORE IN ENGINNERING WITH UNDERSTANDING OF STATICS AND

$ STRENGTH OF MATERIAL CAN CHECK IT.

$ COMPLETE INPUT AND OUTPUT ARE PROVIDED FOR YOUR CHECK.

$ A TEST POLIT, WHO DOES NOT HAVE TO POSSESS THE TECHNOLOGICAL

$ CAPABILITY OF THE PLANE MANUFACTURER AND WHO, IF SUPPLIED WITH A REAL

$ COMPLETE AIR PLANE CAN VERIFY THE PLANE'S CAPABILITY.

$ ASK OUR COMPETITOR TO SUPPLY YOU WITH COMPLETE INPUT AND OUTPUT.

$ DO NO ACCEPT IMCOMPLETE INPUT AND OUTPUT WITH " AS IS " WARRANTY.

$ CHARGE THE SUPPLY WITH FRAUD AND DECEPTION IF YOU ARE CHEATED EVEN THE

$ SUPPLIER SAYS IT WILL NOT ACCEPT RESPONSIBILITY FOR MISREPRESENTATION

$ THAT IS LIKELY TO TURN OUT TO BE THE TIP OF ICEBURG OF ALL KINDS OF

$ MISREPRESENTATIONS.

- PrePre_1 makes this graph below -
Note: Loads also includes self-weight loads and temperature loads, which are not shown.

KEYUSP.DAT FILE

1 -5 0 1 36 20 220 110 25 1 5 0 0 2 150 0.04 0.04 0.2

KNODE1: 0, K_NODE IS THE K_NODE OF THE IMMEDIATE ELEMENT AHEAD.
(FOR 1ST ELEMENT: 1ST NODE OF NODE COORDINATE LIST USED)
In this example, KPT is K_NODE for all elements that need one.

$ MODEL.DAT FILE

$ MODEL.DATA

UNIT CONVERSION FACTOR 12.

$ NODE X-VALUE Y-VALUE Z-VALUE BOUND. CONDITION

$ ------ ------- ------- ------- ----------------

KPT S $ BLANK FOR DEFAULT 0. VALUE

L1 -15. 0. 0. -6 2 2 2 1 1 1 $ COMMENT AFTER $ SIGN

0.5 .86602 0. -.86602 .5 0. 0. 0. 1. $ LOCAL JOINT DIRECTIONS

0.25 -0.5 -0.75 $ JOINT DISPLACEMENTS

R1 15. 0. 0. -6 2 2 2 1 1 1

0.5 .86602 0. -.86602 .5 0. 0. 0. 1.

0.25 -0.5 -0.75

L2 -15. 10. $ BLANK IS FOR FREE JOINT

R2 15. 10.

TOP 0. 15.

N1 0. 0. -15. -6 2 2 2 1 1 1

0.5 .86602 0. -.86602 .5 0. 0. 0. 1.

0.25 -0.5 -0.75

S1 0. 0. 15. -6 2 2 2 1 1 1

0.5 .86602 0. -.86602 .5 0. 0. 0. 1.

0.25 -0.5 -0.75

N2 0. 10. -15.

S2 0. 10. 15.

$ TOP 0. 15. 0. 6 -3 -3 1 1 1 -3

$ TOP 0. 15. 0. 6 -3 -3 1 1 1 0

$ TOP 0. 15. 0. 0

$ TOP 0. 15. 0. 6 -3 -3 -3 -3 -3 0

$ CARRIAGE RETURN AS END DATA BELOW

$ CARRIAGE RETURN AS END DATA ABOVE

ELEMENT BEAM

L1 L2

R1 R2

L2 TOP

R2 TOP

N1 N2

S1 S2

N2 TOP

S2 TOP

END DATA

ELEMENT ONE-WAY

T CRI .787 L1 TOP 0.5

T T-C -2.927224 R1 TOP

T CRIT .787 N1 TOP

T T-C -2.927224 S1 TOP

$ CARRIAGE RETURN AS END DATA BELOW

$ CARRIAGE RETURN AS END DATA ABOVE

ELEMENT TRUSS

L1 R2 3 1.0 36. 1. 60.

R1 L2

N1 S2

S1 N2

DEACTIVATE

$ IF YOUR COMPUTER CAN NOT TAKE IT, USE 0. AS PLACE HOLDER

T S-LF 0.00 L1 R1 0. 0. 0. 0. 0. 1. 1.

DEAC $ REDUNDANT DEACtivate CAN BE PRESENT WITHOUT ANY EFFECT.

REACTIVATE

T S-LF -0.00 L1 R1 , , , , , , 1., 1.

T FS-L 0.005 N1 S1

L2 R2 , , , , , , -1., -1.

N2 S2

$ N2 S2 0. 0. 0. 0. 0. -1. -1.

$ CARRIAGE RETURN AS END DATA BELOW

$ CARRIAGE RETURN AS END DATA ABOVE

$ LOAD.DAT FILE

$ LOAD.DATA FILE

$ 4 LOADING CASES, 3 IDENTICAL CASE RESULTS AS A CHECK.

$ THIS FILE CONTAINS THREE LOADING CONDITONS IDENTICALLY TO SHOW

$ VARIOUS WAY OF INPUT LOADS.

$ EACH LOADING CONDITION SERVE AS A CHECK FOR THE OTHER TWO.

$ LOADING CONDITION CASE 4 TO SHOW

$ POWERFUL LOAD COMBINATION TO OBTAIN CORRECT NON-LINAR COMBINATION

$ UNMATCHED BY THOSE PROGRAMS THAT CAN ONLY DO LINEAR COMBINATION.

$ LOADING CONDITION 1

$ BIGD 2

JOINT LOAD

TOP Y -10000.

END DATA

$ POWERFUL LOAD GENERATION CAPABILITY

$ DIRECTION MULTIPLICATION FACTOR

SELF LOAD Y -3.

END DATA

SELF LOAD Y -7.

$ TO GENRATE LOAD FOR EVERY MEMBER IN -Y DIR. AT 10 TIMES OF ITS WEIGHT.

$ ALSO ITS OWN DEAD LOAD

END DATA

GEN TEMP X 20.

END DATA

GEN TEMP X 40.

$ TO GENERATE LOAD DUE TO TEMP. INCREASE BY 60 DEGREE FOR EVERY MEMBER.

END DATA

$ END DATA

$ LOADING CONDITION 2

$ AN IDENTICAL LOADING SITIATION AS LOADING CONDITION 1 BUT IN DIFFERENT

$ FORM AS A CHECK

$ JOIt LOAd

$TOP Y -10000.

$END DATA

$ TO VERIFY IT WITH INDIVIDUAL MEMBER LOAD AS A CHECK

MEMBER LOAD

L1 L2 KPT

UNIform Y $ use UNI command

$ AREA X WT/UNIT VOLUME X CONVERSION FACTOR = WT/UNIT LENGTH

$ 67.6 X 0.000283566 X 12 = 0.230028739

$ UNIFORM FULL SPAN LOAD

$ WT/UNIT LENGTH X MULTIPLICATION FACTOR = INPUT LOAD /UNIT LENGTH

$ 0.230028739 X 10 = 2.30028739

$ UNIFORM FULL SPAN LOAD

U-F -2.30028739

$ NO 4th LINE IS USED

TEM X

U-F 60

END DATA

R1 R2 KPT

UNIform Y

F-U -2.30028739

$ NO 4th LINE IS USED

TEM X

U-F 60

END DATA

L2 TOP KPT

UNIform Y $ use UNI command

-2.30028739

FR 0.0 1.0 $ use FRactional distance

TEM X

U-F 60

END DATA

R2 TOP KPT

UNIform Y $ use UNI command

-2.30028739

FR 0.0 1.0 $ use FRactional distance

$ AC 0.0 15.8113883 $ use ACtual distance

TEM X

U-F 60

END DATA

N1 N2 KPT

DIStributed Y $ use DIS command

-2.30028739 -2.30028739

FR 0.0 1.0 $ use FRactional distance

TEM X

U-F 60

END DATA

S1 S2 KPT

DIStributed Y $ use DIS command

-2.30028739 -2.30028739

$ AC 0.0 10. $ use ACtual distance

FR 0.0 1.0 $ use FRactional distance

TEM X

U-F 60

END DATA

N2 TOP KPT

$ ACCUMULATIVE WITH LOAD INPUT MORE THAN ONCE BELOW

DIStributed Y $ use DIS command

-1.0 -1.0

FR 0.0 1.0 $ use FRactional distance

DIStributed Y $ use DIS command

-1.30028739 -1.30028739

FR 0.0 1.0 $ use FRactional distance

$ ACCUMULATIVE WITH LOAD INPUT MORE THAN ONCE ABOVE

TEM X

U-F 60

END DATA

S2 TOP KPT

DIStributed Y $ use DIS command

-2.30028739 -2.30028739

$ AC 0.0 15.8113883 $ use ACtual distance

FR 0.0 1.0 $ use FRactional distance

TEM X

U-F 60

END DATA

L1 TOP

TEM X

U-F 60

END DATA

R1 TOP

TEM X

U-F 60

END DATA

N1 TOP

TEM X

U-F 60

END DATA

S1 TOP

TEM X

U-F 60

END DATA

L1 R2

UNIform Y

U-F -0.962115628

TEM X

U-F 60

END DATA

R1 L2

UNIform Y

U-F -0.962115628

TEM X

U-F 60

END DATA

N1 S2

UNIform Y

U-F -0.962115628

TEM X

U-F 60

END DATA

S1 N2

UNIform Y

U-F -0.962115628

TEM X

U-F 60

END DATA

L1 R1

UNIform Y

U-F -0.962115628

TEM X

U-F 60

END DATA

N1 S1

UNIform Y

U-F -0.962115628

TEM X

U-F 60

END DATA

L2 R2

UNIform Y

U-F -0.962115628

TEM X

U-F 60

END DATA

N2 S2

UNIform Y

U-F -0.962115628

TEM X

U-F 60

END DATA

JOIt LOAd

TOP Y -10000.

END DATA

$ LOAD CASE 3

$ POWERFUL LOAD COMBINATION TO OBTAIN CORRECT NON-LINAR COMBINATION

$ UNMATCHED BY THOSE PROGRAMS THAT CAN ONLY DO LINEAR COMBINATION.

LOAd COMbination

$ LOAD COMBINATION LOAD COMBINATION

$ CASE FACTOR CASE FACTOR

$ ---- -------- ---- --------

1 0.4 2 0.6

END DATA

$ LOAD CASE 4

$ POWERFUL LOAD COMBINATION TO OBTAIN CORRECT NON-LINAR COMBINATION

$ UNMATCHED BY THOSE PROGRAMS THAT CAN ONLY DO LINEAR COMBINATION.

LOAd COMbination

$ LOAD COMBINATION LOAD COMBINATION

$ CASE FACTOR CASE FACTOR

$ ---- -------- ---- --------

1 1.4 2 1.6

END DATA

$ SECT.DAT FILE

$ SECT.DATA FILE

$ SECTION PROPERTIES OF MEMBERS

$ 1 2 3 4 5 6 7

$ --------- --------- --------- --------- --------- ------- -------

$ I D NAME AREA IY IZ J DY DZ

STELW36X230 67.6 940. 15000. 28.6 35.9 16.47

REPEat 7

MAT2PIPE2 1.07 .666 .666 1.332 2. 2.

REPEat 3

STELPIPE6 28.2744

REPEat 7

END DATA

$ --- All DATA BEYOND 2 end data lines is for human references only.

DITTO

STELPIPE2 1.07 .666 .666 1.332 2. 2.

DITTO

END DATA

TESTNONL 1.07 .666 .666 1.332 2. 2.

ROPE2 3.1416

PIPE2 1.07 .666 .666 1.332 2. 2.

$ MAT.DAT FILE
$ MAT.DATA FILE

$ I D NAME E G ALPHA RHO

$ ---------- ------- ------- --------- -----------

CNC1COLUMN 3300. 1240. 0.0000055 0.000086806

CNC2GIRDER 3300. 1240. 0.0000055 0.000434030

STEL 29000. 11200. 0.0000065 0.000283565

MAT2 29000. 11200. 0.0000065 0.000000000

$ THIS PORTION UP IS GOOD

$ END DATA

$ STELPIPE6 29000. 11200. 0.0000065 0.000000000

STELW24X076 29000. 11200. 0.0000065 0.000283565

STELWT9X38 29000. 11200. 0.0000065 0.000283565

STELPIPE2 29000. 11200. 0.0000065 0.000000000

STELPIPE6 29000. 11200. 0.0000065 0.000283565

ALUMBEAM 10000. 3750. 0.0000128 0.000095486

CONCCOLUMN 3300. 1240. 0.0000055 0.000086806

END DATA

$ FOR PLOT NO NON-LINEAR ALLOW BELOW FOR USP O K

NLINMATERAIL 10000. 3750. 0.0000128 0.0000

NONLCONTINUE 0.01 100. 0.02 100. 0.03 100.

NONLCONTINUE 0.06 100. 0.2 100.

$ FOR PLOT NO NON-LINEAR ALLOW ABOVE FOR USP O K

END DATA

STELW24X076 29000. 11200. 0.0000065 0.000283565

STELWT9X38 29000. 11200. 0.0000065 0.000283565

STELPIPE2 29000. 11200. 0.0000065 0.000000000

STELPIPE6 29000. 11200. 0.0000065 0.000283565

NONL 0.01 100. 0.02 130. 0.03 150.

NONL 0.06 160. 0.2 160.5

CAE SETS (Structure Engineering Turnkey System): True #1

- PrePre_1 makes this graph below - Note: Loads also includes self-weight loads and temperature loads, which are not shown.

KEYUSP.DAT FILE

$ MODEL.DAT FILE

$ LOAD.DAT FILE

$ SECT.DAT FILE

$ MAT.DAT FILE $ MAT.DATA FILE

Back to the CAE Home Page This page was last updated on Oct./15/2003 and Oct. 19, 2023 .

- PrePre_1 makes this graph below -
Note: Loads also includes self-weight loads and temperature loads, which are not shown.

$ MAT.DAT FILE
$ MAT.DATA FILE

Back to the CAE Home Page

This page was last updated on Oct./15/2003 and Oct. 19, 2023 .