1. REINFORCED CONCRETE - TumCivil.com · 2010-03-25 · Load Combination List ACI 318-89 & AISC-ASD89 & AISI-CFSD86. 21.80. Structural Design Criteria. Combination (LCB) ACI 318-89

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1. REINFORCED CONCRETE

1.1 Code of Practices

1.1.1 American Concrete Institute, ACI 318-83

1.1.2 ACI Detailing Manual - 1980, Publication SP-66

1.1.3 Engineering Institute of Thailand, EIT 1001

1.1.4 Thailand Construction Code of Practice & Control Law BE.2522

1.2 Material Properties

1.2.1 Concrete fc' at 28 days (Cylinder) = 210 ksc.

fc = 0.45fc' = 95.00 ksc.

vc = 0.29 fc' = 4.21 ksc.

1.2.2 Reinforcement and R.C. Factor

SD-30 SD-30 SD-40

fy 3,000 3,000 4,000 ksc.

fs = 0.5fy 1500 1500 1700 ksc.

Es 2.04 x 106

2.04 x 106

2.04 x 106

ksc.

EC = 15,210 fc' 220,414 219,110 219,110 ksc.

k 0.370 0.371 0.342

j 0.877 0.876 0.886

n = 9.26 9.31

R = fc . J .k 15.391 14.401

Structural Design Criteria

ksc.

9.31

15.441

ES

EC

1

2

2. Structural Concrete Design. (Ultimate Strength Design, USD.)

Concrete fc' at 28 days (Cylinder) fc' = ksc.

Grade of Main Rebar (SD30) fy = ksc.

Grade of Sub-Rebar (SD24) fy = ksc.

For Flexure f = 0.90

For Axial Tension with Flexure. f = 0.90

For Axial Compression, and Axil Compression with Flexure

- Member with spiral Reinforcement f = 0.75

- Other Reinforcement Member f = 0.85

For Shear f = 0.85

3. Structural Steel Design. (American Institute of Steel Constuction, AISC.)

Grade :

Poisson's Ratio P =

Tensile Strength fu = ksc.

Yield Strength fy = ksc.

Yield Strength fy = ksc.

Modulus of Elasticity E = ksc.

4. Loading Condition.

DL. Of Roof Tile (กระเบ�องลกฟกลอนค) = 20 kg/m2

LL. Of Roof = 30 kg/m2

LL. กนสาด = 100 kg/m2

LL. หองน�า = 150 kg/m2

LL. หองเรยน = 300 kg/m2

LL. ทางเดน และบนได = 400 kg/m2

LL. ถงเกบน�า = 500 kg/m2

DL. อฐมอญ = 180 kg/m2

DL. อฐมอญเตมแผน = 360 kg/m2

DL. Of Concrete = 2,400 kg/m3

0.30

4,100

2,200

2.1 x 106

Stength Reduction Factors


American Concrete Institute ACI 318-89

AISC-ASD89 & AISI-CFSD86

210

3,000

2,400

Loading Condition.

SS400

2,400

5. Wind Load Design. UBC (1997)

Exposure Category : =

Basic Wind Speed : = mile/h

Importance Factor (I) : =

Mean Roof Height : = m.

6. Load Combination List

(LCB ) (LCB )1 1.4D + 1.7L 1 D + L

2 0.75(1.4D + 1.7L + 1.7Wx) 2 0.75(D + L + Wx)

3 0.75(1.4D + 1.7L + 1.7Wy) 3 0.75(D + L + Wy)

4 0.75(1.4D + 1.7L - 1.7Wx) 4 0.75(D + L - Wx)

5 0.75(1.4D + 1.7L - 1.7Wy) 5 0.75(D + L - Wy)

6 0.9D + 1.3Wx 6 0.75(D + Wx)

7 0.9D + 1.3Wy 7 0.75(D + Wy)

8 0.9D - 1.3Wx 8 0.75(D - Wx)

9 0.9D - 1.3Wy 9 0.75(D - Wy)

10 SERV :D + L

11 SERV :D + L + Wx

12 SERV :D + L + Wy

13 SERV :D + L - Wx

14 SERV :D + L - Wy

15 SERV :D + Wx

16 SERV :D + Wy

17 SERV :D - Wx

18 SERV :D - Wy

(LCB )19 Footing Strength Envelope

20 Footing Serviceability Envelope

7. Pile & Soil

P.C. Pile (Allowable Load per Pile > F.S. = 2.5 ) = 0.30 x 0.30 m. ( 50 Tons )

รบน�าหนกบรรทกปลอดภยไดไมนอยกวา 50 ตน

Pile & Soil

UBC (1997)B

70

1.00

1 + 2 + 3 + 4 + 5 + 6 + 7 + 8 + 9

10 + 11 + 12 + 13 + 14 + 15 + 16 + 17 + 18

(Steel Design) Description (Concrete Design) Description

Load Combination List ACI 318-89 & AISC-ASD89 & AISI-CFSD86

21.80


Combination (LCB) ACI 318-89

(Concrete Design) Description Combination (LCB)

MIDAS/Gen WIND LOAD CALC. PROJECT TITLE :

Company

Author

Client

File Name STA(Design).wpf

WIND LOADS BASED ON UBC1997(Normal Force Method) [UNIT: kgf, m] _________________________________________________________________________________

Design Wind Loads : F = p * Area Design Wind Pressure : p = Ce1*Cq1*qs*Iw-Ce2*Cq2*qs*Iw

Exposure Category : B Basic Wind Speed [mph] : V = 70.00 Importance Factor : Iw = 1.00 Windward Pressure Coefficient : Cq1 = 0.80 Leeward Pressure Coefficient : Cq2 = -0.50 Wind Stagnation Pressure [psf] : qs = 12.60

Scale Factor for X-directional Wind Loads : SFx = 1.00 Scale Factor for Y-directional Wind Loads : SFy = 0.00

----------------------------------------------------------------------------------------------- Wind force of the specific story is calculated as the sum of the forces of the following two parts. 1. Part I : Lower half part of the specific story 2. Part II : Upper half part of the just below story of the specific story

The reference height for the calculation of the wind pressure related factors are, therefore, considered separately for the above mentioned two parts as follows.

Reference height for the wind pressure related factors(except topographic related factors) 1. Part I : top level of the specific story 2. Part II : top level of the just below story of the specific story

-----------------------------------------------------------------------------------------------

** Combined Height, Exposure and Gust Factor Coefficients at Windward and Leeward Walls (Ce1, Ce2)

STORY Ce1 Ce2 NAME (Windward) (Leeward) ---------- ----------- ----------- Roof 1.002 1.002 12F 1.002 1.002 11F 0.977 1.002 10F 0.975 1.002 8F 0.918 1.002 6F 0.855 1.002 4F 0.769 1.002 2F 0.667 1.002 1F 0.620 1.002 ----------------------------------

** Story Force = Wind Force x Scale Factor + Added Force

** Story Torsion = Wind Torsion x Scale Factor + Added Torsion

W I N D L O A D G E N E R A T I O N D A T A X - D I R E C T I O N

STORY NAME PRESSURE ELEV. LOADED LOADED WIND ADDED STORY STORY OVERTURN`G HEIGHT BREADTH FORCE FORCE FORCE SHEAR MOMENT ---------- -------- ------- ------- ------- ---------- ---------- ---------- ---------- ---------- Roof 80.1235 21.8 0.825 0.0 694.06979 0.0 694.06979 0.0 0.0 12F 80.1235 20.15 0.9 10.5 756.2229 0.0 756.2229 694.06979 1145.2151 11F 78.92459 20.0 1.825 10.5 2241.4044 0.0 2241.4044 1450.2927 1362.759 10F 78.8156 16.5 3.5 15.8 2578.166 0.0 2578.166 3691.6971 14283.699 8F 75.98376 13.0 3.5 3.0 781.51102 0.0 781.51102 6269.8631 36228.22 6F 72.87548 9.5 3.5 3.0 743.16904 0.0 743.16904 7051.3742 60908.029 4F 68.68052 6.0 4.0 3.0 790.11735 0.0 790.11735 7794.5432 88188.931 2F 63.63624 1.5 3.0 3.0 1050.5155 0.0 1050.5155 8584.6605 126819.9 G.L. 61.33046 0.0 0.75 13.5 0.0 0.0 -- 9635.1761 141272.67--------------------------------------------------------------------------------------------------

W I N D L O A D G E N E R A T I O N D A T A Y - D I R E C T I O N

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Print Date/Time : 03/09/2010 21:08 Modeling, Integrated Design & Analysis Software http://www.MidasUser.com MIDAS/Gen V 7.2.5

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Company

Author

Client



W I N D L O A D G E N E R A T I O N D A T A RZ - D I R E C T I O N

STORY NAME TORSIONAL ELEV. LOADED LOADED WIND ADDED STORY ACCUMULATED PRESSURE HEIGHT BREADTH TORSION TORSION TORSION TORSION ---------- --------- ------- ------- ------- ---------- ---------- ---------- ----------- Roof 0.0 21.8 0.825 0.0 0.0 0.0 0.0 0.0 12F 0.0 20.15 0.9 10.5 0.0 0.0 0.0 0.0 11F 0.0 20.0 1.825 10.5 0.0 0.0 0.0 0.0 10F 0.0 16.5 3.5 15.8 0.0 0.0 0.0 0.0 8F 0.0 13.0 3.5 3.0 0.0 0.0 0.0 0.0 6F 0.0 9.5 3.5 3.0 0.0 0.0 0.0 0.0 4F 0.0 6.0 4.0 3.0 0.0 0.0 0.0 0.0 2F 0.0 1.5 3.0 3.0 0.0 0.0 0.0 0.0 G.L. 0.0 0.0 0.75 13.5 0.0 0.0 -- 0.0-----------------------------------------------------------------------------------------

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Company

Author

Client


WIND LOADS BASED ON UBC1997(Normal Force Method) [UNIT: kgf, m] _________________________________________________________________________________

Design Wind Loads : F = p * Area Design Wind Pressure : p = Ce1*Cq1*qs*Iw-Ce2*Cq2*qs*Iw

Exposure Category : B Basic Wind Speed [mph] : V = 70.00 Importance Factor : Iw = 1.00 Windward Pressure Coefficient : Cq1 = 0.80 Leeward Pressure Coefficient : Cq2 = -0.50 Wind Stagnation Pressure [psf] : qs = 12.60

Scale Factor for X-directional Wind Loads : SFx = 0.00 Scale Factor for Y-directional Wind Loads : SFy = 1.00

----------------------------------------------------------------------------------------------- Wind force of the specific story is calculated as the sum of the forces of the following two parts. 1. Part I : Lower half part of the specific story 2. Part II : Upper half part of the just below story of the specific story

The reference height for the calculation of the wind pressure related factors are, therefore, considered separately for the above mentioned two parts as follows.

Reference height for the wind pressure related factors(except topographic related factors) 1. Part I : top level of the specific story 2. Part II : top level of the just below story of the specific story

-----------------------------------------------------------------------------------------------

** Combined Height, Exposure and Gust Factor Coefficients at Windward and Leeward Walls (Ce1, Ce2)

STORY Ce1 Ce2 NAME (Windward) (Leeward) ---------- ----------- ----------- Roof 1.002 1.002 12F 1.002 1.002 11F 0.977 1.002 10F 0.975 1.002 8F 0.918 1.002 6F 0.855 1.002 4F 0.769 1.002 2F 0.667 1.002 1F 0.620 1.002 ----------------------------------

** Story Force = Wind Force x Scale Factor + Added Force

** Story Torsion = Wind Torsion x Scale Factor + Added Torsion

W I N D L O A D G E N E R A T I O N D A T A X - D I R E C T I O N


W I N D L O A D G E N E R A T I O N D A T A Y - D I R E C T I O N

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Company

Author

Client



W I N D L O A D G E N E R A T I O N D A T A RZ - D I R E C T I O N

STORY NAME TORSIONAL ELEV. LOADED LOADED WIND ADDED STORY ACCUMULATED PRESSURE HEIGHT BREADTH TORSION TORSION TORSION TORSION ---------- --------- ------- ------- ------- ---------- ---------- ---------- ----------- Roof 0.0 21.8 0.825 0.0 0.0 0.0 0.0 0.0 12F 0.0 20.15 0.9 10.5 0.0 0.0 0.0 0.0 11F 0.0 20.0 1.825 10.5 0.0 0.0 0.0 0.0 10F 0.0 16.5 3.5 15.8 0.0 0.0 0.0 0.0 8F 0.0 13.0 3.5 3.0 0.0 0.0 0.0 0.0 6F 0.0 9.5 3.5 3.0 0.0 0.0 0.0 0.0 4F 0.0 6.0 4.0 3.0 0.0 0.0 0.0 0.0 2F 0.0 1.5 3.0 3.0 0.0 0.0 0.0 0.0 G.L. 0.0 0.0 0.75 13.5 0.0 0.0 -- 0.0-----------------------------------------------------------------------------------------

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Ec = 219,110 ksc. fc = 94.5 ksc. R = 15.316 ksc.

n = 9.31 fc' = 210 ksc. j = 0.877

k = 0.370 fs = 1500 ksc. L = 5.50 m.ลกนอน = 0.250 m. 16 mm.ลกตง = 0.1703 m. 9 mm.

ความกวางบนได = 1.200 m. 0.030 m.

กาหนดความหนา = 0.20 m. 0.2 m.

นาหนกบรรทกคงท = = 665.79 kg/m2.= ( WDL ) = 798.94 kg/m.

นาหนกบรรทกจร = WLL = 400 kg/m2.= ( WLL ) = 480 kg/m.

นาหนกทงหมด = ( WDL + WLL ) = 1278.94 kg/m.

DL LL

Vmax = = 3517 kg 2,197 1,320d = 0.2 - 0.03 - 0.008 = 0.162 m. 0.04

Mr = R x b x d2= 4019.470 3,224.00 OK.

vc = 0.29 fc' = 4.202 kg/cm.

Vc = vc x b x d = 6808.049 3,517.09 OK.

AS = = 15.132 cm2

Asmin = 0.0025 x 100 x 20 = 5.00 cm2

>

>DB-16 mm. @ 0.13 m.

RB-9 mm. @ 0.13 m.

Stair (ST1)

= = 3224.003 kg-m.

เหลกแกน =เหลกกนราว =

Corvering =

Mmax

บนไดทมจดรองรบเปน Fix Support

W x L2

0.5 x (W x L )

M

DB-16 mm. @ 0.1 m.

RB-9 mm. @ 0.15 m.

RB-6 mm. @0.2 m.

DB-16 mm. @ 0.1 m.

RB-6mm.

0.2 m.

5.5 m.

12

8 9 12

DB-16 mm. @ 0.1 m.

ST1

RB-9 mm. @ 0.15 m.

2,400 12 ( b + 0.025 ) h + t b + h 2 2

b + h 2 2

VisStructure 03 One-way Slab

( สงวนลขสทธ ) ชอโครงการ : โรงเรยนเทศบาล

วศวกร : สมบรณ แซลม ชอแผนพน : S1

Input Data

คอนกรตหมเหลก ................ = 3.00 ซม. นาหนกบรรทก = 100 กก./ตร.ม.

fc ..................................... = 95 กก./ตร.ซม. ความยาวชวง = 1.50 ม.

fc' .................................... = 210 กก./ตร.ซม. ความหนาของแผนพน = 10.00 ซม.

fs (ขนาด 6 มม. และ 9 มม.) = 1,200 กก./ตร.ซม. สมประสทธโมเมนต = 1/24 ทางซาย

fy (ขนาด 6 มม. และ 9 มม.) = 2,400 กก./ตร.ซม. สมประสทธโมเมนต = 1/9 ทางขวา

fs (ขนาดตงแต 12 มม.ขนไป) = 1,500 กก./ตร.ซม. สมประสทธโมเมนต = 1/14 กลางชวง

fy (ขนาดตงแต 12 มม.ขนไป) = 3,000 กก./ตร.ซม.

Result

ระยะโกงทนทเมอถอดแบบหลอ = 0.0050 ซม. นาหนกทถายเขาคาน = 255 กก./ม.

ระยะโกงประสทธผล = 0.0128 ซม. เหลกเสรมตานการยดหด = 2.50 ตร.ซม./ม.

ระยะโกงประสทธผลทยอมให = 0.6250 ซม.

M Mc R j d As

(กก.-ม./ม.) (กก.-ม./ม.) (ซม.) (ตร.ซม./ม.)

ทางซาย -31.88 736.67 17.17 0.859 6.55 0.47

ทางขวา -85.00 736.67 17.17 0.859 6.55 1.26

กลางชวง +54.64 736.67 17.17 0.859 6.55 0.81

. . . . . .0.10

RB 9มม @ 0.25

RB 9มม @ 0.25

RB 9มม @ 0.25

RB 9มม @ 0.25

0.38 0.38

1.50

S1

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VisStructure 03 Two-way Slab



Input Data

คอนกรตหมเหลก ................. = 3.00 ซม.

fc ..................................... = 95 กก./ตร.ซม.

fc' .................................... = 210 กก./ตร.ซม.

fs ( ขนาด 6 มม. และ 9 มม. ) = 1,200 กก./ตร.ซม.

fy ( ขนาด 6 มม. และ 9 มม. ) = 2,400 กก./ตร.ซม.

fs ( ขนาดตงแต 12 มม.ขนไป ) = 1,500 กก./ตร.ซม.

fy ( ขนาดตงแต 12 มม.ขนไป ) = 3,000 กก./ตร.ซม.

นาหนกบรรทก...................... = 500 กก./ตร.ม.

ความยาวชวง, Lx .................. = 3.00 ม.

ความยาวชวง, Ly .................. = 4.00 ม.

ความหนาแผนพน ................. = 10.00 ซม.

Result

นาหนกทถายจากแผนพนไปยงคานดานสน = 740 กก./ม. ( เพอการคานวนหาโมเมนตดดของคาน )

นาหนกทถายจากแผนพนไปยงคานดานยาว = 902 กก./ม. ( เพอการคานวนหาโมเมนตดดของคาน )

นาหนกทถายจากแผนพนไปยงคานดานสน = 555 กก./ม. ( เพอการคานวนหานาหนกทถายเขาเสา )

นาหนกทถายจากแผนพนไปยงคานดานยาว = 694 กก./ม. ( เพอการคานวนหานาหนกทถายเขาเสา )

เหลกเสรมตานการยดหดในทศทางดานสน = 2.50 ตร.ซม./ม. เลอกใช RB 9มม @ 0.25

เหลกเสรมตานการยดหดในทศทางดานยาว = 2.50 ตร.ซม./ม. เลอกใช RB 9มม @ 0.25

สมประสทธ R j d Mc M As เหลกเสรมทางสน

โมเมนต ซม. กก.-ม./ม. กก.-ม./ม. ตร.ชม./ม. ม.

ทขอบ AB -0.0410 17.1709 0.859 6.55 737 -273 4.04 RB 9มม @ 0.15

ทขอบ CD -0.0820 17.1709 0.859 6.55 737 -546 8.09 RB 9มม @ 0.075

กลางชวง +0.0620 17.1709 0.859 6.55 737 +413 6.12 RB 9มม @ 0.10

สมประสทธ R j d Mc M As เหลกเสรมทางยาว


ทขอบ DA -0.0290 17.1709 0.859 6.55 737 -193 2.86 RB 9มม @ 0.22

ทขอบ BC -0.0290 17.1709 0.859 6.55 737 -193 2.86 RB 9มม @ 0.22

กลางชวง +0.0440 17.1709 0.859 5.65 548 +293 5.03 RB 9มม @ 0.125

A

B C

D

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. . . . . . . . . . . . . . . . . . . . . . . 0.10

RB 9มม @ 0.20

RB 9มม @ 0.10

RB 9มม @ 0.15

RB 9มม @ 0.25

RB 9มม @ 0.075

1.00 1.00

0.60 1.80 0.60

3.00

S2 รปตดทางดานสน

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.10

RB 9มม @ 0.25

RB 9มม @ 0.125

RB 9มม @ 0.22

RB 9มม @ 0.25

RB 9มม @ 0.22

1.35 1.35

0.80 2.40 0.80

4.00

S2 รปตดทางดานยาว

VisStructure 03 Cantilevered Slab



Input Data

คอนกรตหมเหลก .................. = 3.00 ซม.

fc ....................................... = 95 กก./ตร.ซม.

fc' ...................................... = 210 กก./ตร.ซม.





นาหนกบรรทก ...................... = 100 กก./ตร.ม.

ความยาวชวง ......................... = .80 ม.

Point Load ตอความยาว 1 เมตร = 168 กก./ม.

ระยะจาก Point Load ถงทรองรบ = 0.70 ม.

ความหนาของแผนพน ............. = 10 ซม.

Result

นาหนกทถายเขาคาน ........... = 440 กก./ม.

เหลกเสรมตานการยดหด ..... = 2.50 ตร.ซม./ม.

โมเมนต ........................... = 226 กก.-ม./ม.

Mc .................................. = 737 กก.-ม./ม.

As ................................... = 3.35 ตร.ซม./ม.

R .................................... = 17.1709

j ...................................... = 0.859

d ..................................... = 6.55 ซม.

ระยะโกงทนทเมอถอดแบบหลอ = 0.0195 ซม.

ระยะโกงประสทธผล ............ = 0.0429 ซม.

ระยะโกงประสทธผลทยอมให = 0.3333 ซม.

0.10

RB 9มม @ 0.18

RB 9มม @ 0.25

0.80

F3

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VisStructure 03 Two-way Slab



Input Data

คอนกรตหมเหลก ................. = 3.00 ซม.

fc ..................................... = 95 กก./ตร.ซม.

fc' .................................... = 210 กก./ตร.ซม.





นาหนกบรรทก...................... = 150 กก./ตร.ม.

ความยาวชวง, Lx .................. = 3.00 ม.

ความยาวชวง, Ly .................. = 4.00 ม.

ความหนาแผนพน ................. = 10.00 ซม.

Result

นาหนกทถายจากแผนพนไปยงคานดานสน = 390 กก./ม. ( เพอการคานวนหาโมเมนตดดของคาน )

นาหนกทถายจากแผนพนไปยงคานดานยาว = 475 กก./ม. ( เพอการคานวนหาโมเมนตดดของคาน )

นาหนกทถายจากแผนพนไปยงคานดานสน = 293 กก./ม. ( เพอการคานวนหานาหนกทถายเขาเสา )

นาหนกทถายจากแผนพนไปยงคานดานยาว = 366 กก./ม. ( เพอการคานวนหานาหนกทถายเขาเสา )

เหลกเสรมตานการยดหดในทศทางดานสน = 2.50 ตร.ซม./ม. เลอกใช RB 9มม @ 0.25

เหลกเสรมตานการยดหดในทศทางดานยาว = 2.50 ตร.ซม./ม. เลอกใช RB 9มม @ 0.25

สมประสทธ R j d Mc M As เหลกเสรมทางสน


ทขอบ AB -0.0410 17.1709 0.859 6.55 737 -144 2.13 RB 9มม @ 0.25

ทขอบ CD -0.0820 17.1709 0.859 6.55 737 -288 4.26 RB 9มม @ 0.14

กลางชวง +0.0620 17.1709 0.859 6.55 737 +218 3.22 RB 9มม @ 0.18

สมประสทธ R j d Mc M As เหลกเสรมทางยาว


ทขอบ DA -0.0290 17.1709 0.859 6.55 737 -102 1.51 RB 9มม @ 0.25

ทขอบ BC -0.0290 17.1709 0.859 6.55 737 -102 1.51 RB 9มม @ 0.25

กลางชวง +0.0440 17.1709 0.859 5.65 548 +154 2.65 RB 9มม @ 0.20

A

B C

D

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. . . . . . . . . . . . . . . 0.10

RB 9มม @ 0.18

RB 9มม @ 0.25

RB 9มม @ 0.25

RB 9มม @ 0.14

1.00 1.00

3.00

S4 รปตดทางดานสน

. . . . . . . . . . . . . . . . . . . . . . 0.10

RB 9มม @ 0.20

RB 9มม @ 0.25

RB 9มม @ 0.25

RB 9มม @ 0.25

1.35 1.35

4.00

S4 รปตดทางดานยาว

MIDAS/Gen RC Beam Design Result Output PROJECT TITLE :

Company

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Client

File Name Untitled.rcs

------------------------------------------------------------------------------------------ MIDAS/Gen - RC-Beam Design [ ACI318-89 ] Version 7.0.2==========================================================================================

+============================================================+ | MIDAS(Modeling, Integrated Design & Analysis Software) | | MIDAS/Gen - Design & checking system for windows | +============================================================+ | RC-Member(Beam/Column/Brace/Wall) Analysis and Design | | Based On ACI318-02, ACI318-99, ACI318-95, ACI318-89, | | CSA-A23.3-94, BS8110-97, Eurocode2 | | | | | | | | | | (c)1989-2006 | +============================================================+ | MIDAS Information Technology Co.,Ltd. (MIDAS IT) | | MIDAS IT Design Development Team | +============================================================+ | HomePage : www.MidasUser.com | | Tel : 360-753-5540, Fax : 360-753-5542 | +============================================================+ | MIDAS/Gen Version 7.0.2 | +============================================================+

*. DEFINITION OF LOAD COMBINATIONS WITH SCALING UP FACTORS.-------------------------------------------------------------------------------------- LCB C Loadcase Name(Factor) + Loadcase Name(Factor) + Loadcase Name(Factor)-------------------------------------------------------------------------------------- 1 1 DL( 1.400) + LL( 1.700) 2 1 DL( 1.050) + LL( 1.275) + Wx( 1.275) 3 1 DL( 1.050) + LL( 1.275) + Wy( 1.275) 4 1 DL( 1.050) + LL( 1.275) + Wx(-1.275) 5 1 DL( 1.050) + LL( 1.275) + Wy(-1.275) 6 1 DL( 0.900) + Wx( 1.300) 7 1 DL( 0.900) + Wy( 1.300) 8 1 DL( 0.900) + Wx(-1.300) 9 1 DL( 0.900) + Wy(-1.300)--------------------------------------------------------------------------------------

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*.MIDAS/Gen - RC-BEAM Analysis/Design Program.

*.PROJECT : *.DESIGN CODE : ACI318-89, *.UNIT SYSTEM : kgf, m *.MEMBER : Member Type = BEAM, MEMB = 606

*.DESCRIPTION OF BEAM DATA (iSEC = 16) : B11 Section Type : Rectangle (RECT) Beam Length (Span) = 10.500 m. Section Depth (Hc) = 0.600 m. Section Width (Bc) = 0.450 m. Concrete Strength (fc) = 2100000.000 kgf/m^2. Main Rebar Strength (fy) = 30000000.000 kgf/m^2. Stirrups Strength (fys) = 24000000.000 kgf/m^2. Modulus of Elasticity (Es) = 2.039e+010 kgf/m^2.

*.FORCES AND MOMENTS AT CHECK POINT <I> : Positive Bending Moment P-Mu = 9137.12 kgf-m., LCB = 1 Negative Bending Moment N-Mu = 28584.63 kgf-m., LCB = 1 Shear Force Vu = 24062.01 kgf. , LCB = 1

*.REINFORCEMENT PATTERN : --------------------------------------------------------- Location i di( m.) Rebar Asi( m^2.) --------------------------------------------------------- Top 1 0.064 6- 2-P25 0.00393 Bottom 2 0.548 6-P25 0.00295 --------------------------------------------------------- Stirrups : P9

=============================================================================== [[[*]]] ANALYZE POSITIVE BENDING MOMENT CAPACITY. ===============================================================================

( ). Compute design parameter. -. beta1 = 0.8500 ( fc < 4000 psi.)

( ). Compute required ratio of reinforcement. -. Rhomi1 = 200/fy = 0.0047 -. Rhomi2 = (4/3)*Mu/[ phi*fy*b*d*(d-a/2) ] = 0.0034 -. Rhomin = MIN[ Rhomi1, Rhomi2 ] = 0.0034 -. Rhob = 0.85*beta1*(fc/fy)*(0.003/(0.003+fy/Es)) = 0.0339 -. Rhomax = 0.75*Rhob = 0.0254

( ). Check ratio of tensile reinforcement. -. Rho = As/(bw*d) = 0.0119 -. Rhomin < Rho < Rhomax ---> O.K !

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( ). Compute moment capacity. -. a = As*fy/(0.85*fc*bw) = 0.110 m. -. Mn = As*fy*(d-a/2) = 43604.03 kgf-m. -. phi = 0.90 -. phiMn = phi*Mn = 39243.63 kgf-m.

( ). Check ratio of positive moment capacity. -. Rat_P = Mu/phiMn = 0.233 < 1.000 ---> O.K.

=============================================================================== [[[*]]] ANALYZE NEGATIVE BENDING MOMENT CAPACITY. ===============================================================================





( ). Check ratio of negative moment capacity. -. Rat_N = Mu/phiMn = 0.583 < 1.000 ---> O.K.

=============================================================================== [[[*]]] ANALYZE SHEAR CAPACITY. ===============================================================================

( ). Compute shear strength of concrete. -. Vu = 24062.01 kgf. -. Vc = 2*SQRT(fc)*bw*d = 18532.55 kgf. -. phi = 0.85 -. phiVc = phi*Vc = 15752.67 kgf. -. Vu > phiVc ---> Required shear reinforcement.

( ). Compute required shear reinforcement. ( Av1 = 0.00006 m^2. ) -. Vs = (Vu-phiVc)/phi = 9775.70 kgf. -. 4*SQRT(fc)*bw*d = 37065.10 kgf. -. 8*SQRT(fc)*bw*d = 74130.19 kgf.

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-. Vs < 4*SQRT(fc)*bw*d ---> O.K ! -. Avmin = 50*bw/fys = 0.00066 m^2/m. -. Avreq = Vs/(fys*d) = 0.00076 m^2/m. -. Av = MAX[ Avmin, Avreq ] = 0.00076 m^2/m. -. N_leg = 4 -. Maximum spacing smax = MIN[ d/2, 24 in ] = 0.268 m. -. Calculate spacing s1 = N_leg*Av1 / Av = 0.33471 m. -. Applied spacing s = MIN[ smax, s1 ] = 0.268 m.

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*.FORCES AND MOMENTS AT CHECK POINT <M> : Positive Bending Moment P-Mu = 23105.35 kgf-m., LCB = 1 Negative Bending Moment N-Mu = 0.00 kgf-m., LCB = 9 Shear Force Vu = 13780.30 kgf. , LCB = 1

*.REINFORCEMENT PATTERN : --------------------------------------------------------- Location i di( m.) Rebar Asi( m^2.) --------------------------------------------------------- Top 1 0.052 6-P25 0.00295 Bottom 2 0.523 7- 7-P25 0.00687 --------------------------------------------------------- Stirrups : P9




( ). Check ratio of tensile reinforcement. -. Rho = As/(bw*d) = 0.0292 -. Rho > Rhomax ---> Not Acceptable !!!

( ). Search for neutral axis...... Unit : kgf., m. ------------------------------------------------------- Trial c Cc Ts Ratio -------------------------------------------------------

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1-st 0.262 178644.81 206165.40 86.65 2-nd 0.392 267967.21 140117.04 8.75 3-rd 0.327 223306.01 206165.40 91.69 4-th 0.294 200975.41 206165.40 97.48 5-th 0.311 212140.71 206165.40 97.10 6-th 0.303 206558.06 206165.40 99.81 7-th 0.298 203766.73 206165.40 98.84 8-th 0.300 205162.40 206165.40 99.51 -------------------------------------------------------

( ). Compute allowable moment capacity. -. a = beta1*c = 0.255 m. -. Mn = As*fy*(d-a/2) = 81160.67 kgf-m. -. Assumed phi = 0.90 -. phiMn = phi*Mn = 73044.60 kgf-m.




( ). Compute required ratio of reinforcement. -. Rhomi1 = 200/fy =1.0000e-007 -. Rhomi2 = (4/3)*Mu/[ phi*fy*b*d*(d-a/2) ] = 0.0000 -. Rhomin = MIN[ Rhomi1, Rhomi2 ] = 0.0000 -. Rhob = 0.85*beta1*(fc/fy)*(0.003/(0.003+fy/Es)) = 0.0339 -. Rhomax = 0.75*Rhob = 0.0254





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( ). Compute shear strength of concrete. -. Vu = 13780.30 kgf. -. Vc = 2*SQRT(fc)*bw*d = 18096.81 kgf. -. phi = 0.85 -. phiVc = phi*Vc = 15382.29 kgf. -. phiVc/2 < Vu < phiVc ---> Required minimum shear reinforcement.

( ). Compute required shear reinforcement. ( Av1 = 0.00006 m^2. ) -. Av = Avmin = 50*bw/fys =6.591e-004 m^2/m. -. N_leg = 4 -. Calculate spacing s1 = N_leg*Av1 / Av = 0.386 m. -. Applied spacing s = MIN[ s1, d/2, 24 in ] = 0.262 m.

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*.FORCES AND MOMENTS AT CHECK POINT <J> : Positive Bending Moment P-Mu = 4430.58 kgf-m., LCB = 1 Negative Bending Moment N-Mu = 46887.19 kgf-m., LCB = 1 Shear Force Vu = 26963.05 kgf. , LCB = 1

*.REINFORCEMENT PATTERN : --------------------------------------------------------- Location i di( m.) Rebar Asi( m^2.) --------------------------------------------------------- Top 1 0.064 6- 2-P25 0.00393 Bottom 2 0.548 6-P25 0.00295 --------------------------------------------------------- Stirrups : P9





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( ). Compute shear strength of concrete. -. Vu = 26963.05 kgf. -. Vc = 2*SQRT(fc)*bw*d = 18532.55 kgf. -. phi = 0.85 -. phiVc = phi*Vc = 15752.67 kgf. -. Vu > phiVc ---> Required shear reinforcement.

( ). Compute required shear reinforcement. ( Av1 = 0.00006 m^2. ) -. Vs = (Vu-phiVc)/phi = 13188.69 kgf. -. 4*SQRT(fc)*bw*d = 37065.10 kgf. -. 8*SQRT(fc)*bw*d = 74130.19 kgf.

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-. Vs < 4*SQRT(fc)*bw*d ---> O.K ! -. Avmin = 50*bw/fys = 0.00066 m^2/m. -. Avreq = Vs/(fys*d) = 0.00103 m^2/m. -. Av = MAX[ Avmin, Avreq ] = 0.00103 m^2/m. -. N_leg = 4 -. Maximum spacing smax = MIN[ d/2, 24 in ] = 0.268 m. -. Calculate spacing s1 = N_leg*Av1 / Av = 0.24809 m. -. Applied spacing s = MIN[ smax, s1 ] = 0.248 m.

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1. Design Information Design Code : ACI318-89

Unit System : kgf, m

Material Data : fc = 2.1e+006, fy = 3e+007, fys = 2.4e+007 kgf/m^2

Beam Span : 4 m

Section Property: B1 (No : 6)

2. Section Diagram

[END-I]

0.4

0.0

42

0.0

42

0.1

TOP : 1-P12

BOT : 1-P12

STIRRUPS : 2-P6 @150

[MID]0.4

0.0

42

0.0

42

0.1

TOP : 1-P12

BOT : 1-P12


[END-J]

0.4

0.0

42

0.0

42

0.1

TOP : 1-P12

BOT : 1-P12


3. Bending Moment Capacity END-I MID END-J

Negative Moment (Mu)

Load Combination No.

Strength (PhiMn)

Check Ratio (Mu/PhiMn)

Positive Moment (Mu)


Strength (PhiMn)


Using Rebar Top (As_top)

Using Rebar Bot (As_bot)

1089.00

1

1091.07

0.9981

770.85

1

1091.07

0.7065

0.0001

0.0001

416.14

9

1091.07

0.3814

1027.80

1

1091.07

0.9420

0.0001

0.0001

946.16

1

1091.07

0.8672

770.85

1

1091.07

0.7065

0.0001

0.0001

4. Shear Capacity END-I MID END-J

Factored Shear Force (Vu)

Shear Strength by Conc.(PhiVc)

Using Shear Reinf. (AsV)

Using Stirrups Spacing

Check Ratio

1284.94

2338.52

0.0004

2-P6 @150

0.2524

1284.36

2338.52

0.0004

2-P6 @150

0.2523

1517.88

2338.52

0.0004

2-P6 @150

0.2981

Company

Author

Project Title

File Name D:\...\New folder\STA(Design).mgb

Modeling, Integrated Design & Analysis Softwarehttp://www.MidasUser.comMIDAS/Gen V 7.2.5

Print Date/Time : 03/10/2010 19:03

MIDAS/Gen RC Beam Checking Result Output

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Beam Span : 4 m


2. Section Diagram

[END-I]

0.4

0.0

44

0.0

44

0.2

TOP : 4-P16

BOT : 2-P16


[MID]0.4

0.0

44

0.0

44

0.2

TOP : 2-P16

BOT : 2-P16


[END-J]

0.4

0.0

44

0.0

44

0.2

TOP : 4-P16

BOT : 2-P16





Strength (PhiMn)




Strength (PhiMn)




4614.74

5

6595.64

0.6997

2755.15

7

3778.22

0.7292

0.0008

0.0004

2578.37

3

3656.67

0.7051

3021.29

1

3656.67

0.8262

0.0004

0.0004

5607.47

3

6595.64

0.8502

3630.32

9

3778.22

0.9609

0.0008

0.0004






Check Ratio

5487.20

4380.48

0.0004

2-P6 @150

0.7885

5318.10

4650.91

0.0004

2-P6 @150

0.7198

6028.01

4380.48

0.0004

2-P6 @150

0.8663

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Beam Span : 4 m


2. Section Diagram

[END-I]

0.4

0.0

44

0.0

44

0.2

TOP : 2-P16

BOT : 3-P16


[MID]0.4

0.0

44

0.0

44

0.2

TOP : 2-P16

BOT : 3-P16


[END-J]

0.4

0.0

44

0.0

44

0.2

TOP : 2-P16

BOT : 3-P16





Strength (PhiMn)




Strength (PhiMn)




1613.93

4

3674.49

0.4392

2153.84

1

5376.80

0.4006

0.0004

0.0006

98.49

6

3674.49

0.0268

2828.19

1

5376.80

0.5260

0.0004

0.0006

1815.03

1

3674.49

0.4940

1192.02

1

5376.80

0.2217

0.0004

0.0006






Check Ratio

4257.84

4650.91

0.0004

2-P6 @150

0.5763

1488.56

4650.91

0.0004

2-P6 @150

0.2015

2669.04

4650.91

0.0004

2-P6 @150

0.3612

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Beam Span : 4 m


2. Section Diagram

[END-I]

0.4

0.0

44

0.0

44

0.2

TOP : 3-P16

BOT : 2-P16


[MID]0.4

0.0

44

0.0

44

0.2

TOP : 2-P16

BOT : 3-P16


[END-J]

0.4

0.0

44

0.0

44

0.2

TOP : 3-P16

BOT : 2-P16





Strength (PhiMn)




Strength (PhiMn)




4073.99

1

5376.80

0.7577

1673.67

1

3674.49

0.4555

0.0006

0.0004

174.70

6

3674.49

0.0475

2214.42

1

5376.80

0.4118

0.0004

0.0006

3848.06

1

5376.80

0.7157

937.44

4

3674.49

0.2551

0.0006

0.0004






Check Ratio

5816.76

4650.91

0.0004

2-P6 @150

0.7873

3201.26

4650.91

0.0004

2-P6 @150

0.4333

5707.11

4650.91

0.0004

2-P6 @150

0.7724

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Beam Span : 10.5 m


2. Section Diagram

[END-I]

0.6

0.0

44

0.0

44

0.25

TOP : 4-P16

BOT : 2-P16


[MID]0.6

0.0

44

0.0

44

0.25

TOP : 2-P16

BOT : 4-P16


[END-J]

0.6

0.0

44

0.0

44

0.25

TOP : 4-P16

BOT : 2-P16





Strength (PhiMn)




Strength (PhiMn)




8415.38

5

11415.16

0.7372

3325.68

3

5927.36

0.5611

0.0008

0.0004

2464.54

3

5927.36

0.4158

3325.68

3

11415.16

0.2913

0.0004

0.0008

9251.75

3

11415.16

0.8105

3036.15

9

5927.36

0.5122

0.0008

0.0004






Check Ratio

2922.12

9079.72

0.0004

2-P6 @150

0.2188

2089.48

9079.72

0.0004

2-P6 @150

0.1565

3081.73

9079.72

0.0004

2-P6 @150

0.2308

Company

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Beam Span : 10.5 m


2. Section Diagram

[END-I]

0.6

0.0

44

0.0

44

0.25

TOP : 4-P16

BOT : 4-P16


[MID]0.6

0.0

44

0.0

44

0.25

TOP : 2-P16

BOT : 6-P16


[END-J]

0.6

0.0

44

0.0

44

0.25

TOP : 4-P16

BOT : 4-P16





Strength (PhiMn)




Strength (PhiMn)




3235.36

9

11426.84

0.2831

2737.29

3

11426.84

0.2395

0.0008

0.0008

1961.99

3

6016.40

0.3261

2737.29

3

16544.72

0.1654

0.0004

0.0012

8988.06

1

11426.84

0.7866

534.23

9

11426.84

0.0468

0.0008

0.0008






Check Ratio

2047.97

9079.72

0.0005

2-P6 @120

0.1441

2146.99

8854.36

0.0005

2-P6 @120

0.1549

3469.99

9079.72

0.0005

2-P6 @120

0.2442

Company

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Project Title



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Beam Span : 10.5 m


2. Section Diagram

[END-I]

0.6

0.0

51

50

.05

15

0.25

TOP : 3-P25

BOT : 3-P25


[MID]0.6

0.0

51

50

.05

15

0.25

TOP : 2-P25

BOT : 5-P25


[END-J]

0.6

0.0

51

50

.05

15

0.25

TOP : 3-P25

BOT : 3-P25





Strength (PhiMn)




Strength (PhiMn)




8260.40

5

20179.88

0.4093

3464.85

3

20179.88

0.1717

0.0015

0.0015

2436.01

3

13642.62

0.1786

3464.85

3

31600.50

0.1096

0.0010

0.0025

9293.43

3

20179.88

0.4605

3077.06

9

20179.88

0.1525

0.0015

0.0015






Check Ratio

2912.05

8957.24

0.0008

2-P9 @150

0.1579

2116.22

8628.02

0.0008

2-P9 @150

0.1191

3108.47

8957.24

0.0008

2-P9 @150

0.1685

Company

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Project Title



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Beam Span : 10.5 m


2. Section Diagram

[END-I]

0.6

0.0

51

50

.05

15

0.4

TOP : 5-P25

BOT : 5-P25


[MID]0.6

0.0

51

50

.05

15

0.4

TOP : 5-P25

BOT : 10-P25


[END-J]

0.6

0.0

51

50

.05

15

0.4

TOP : 5-P25

BOT : 5-P25





Strength (PhiMn)




Strength (PhiMn)




18128.49

1

33660.79

0.5386

10950.00

3

33660.79

0.3253

0.0025

0.0025

4863.36

9

32986.26

0.1474

14819.84

1

62310.21

0.2378

0.0025

0.0049

31977.16

1

33660.79

0.9500

5108.11

5

33660.79

0.1518

0.0025

0.0025






Check Ratio

15932.39

14331.59

0.0006

2-P9 @200

0.7428

9125.57

13673.15

0.0006

2-P9 @200

0.4460

17602.22

14331.59

0.0006

2-P9 @200

0.8207

Company

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Project Title



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Beam Span : 10.5 m


2. Section Diagram

[END-I]

0.6

0.0

51

50

.05

15

0.45

TOP : 8-P25

BOT : 6-P25


[MID]0.6

0.0

51

50

.05

15

0.45

TOP : 6-P25

BOT : 12-P25


[END-J]

0.6

0.0

51

50

.05

15

0.45

TOP : 8-P25

BOT : 6-P25





Strength (PhiMn)




Strength (PhiMn)




28494.95

1

51847.60

0.5496

13716.95

3

39840.42

0.3443

0.0039

0.0029

2809.80

9

39428.43

0.0713

20977.99

1

74465.41

0.2817

0.0029

0.0059

43135.09

1

51847.60

0.8320

5694.37

5

39840.42

0.1429

0.0039

0.0029






Check Ratio

23421.20

15752.67

0.0013

4-P9 @200

0.7897

12463.11

15382.29

0.0013

4-P9 @200

0.4303

23727.51

15752.67

0.0013

4-P9 @200

0.8000

Company

Author

Project Title



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Beam Span : 10.5 m


2. Section Diagram

[END-I]

0.6

0.0

51

50

.05

15

0.45

TOP : 8-P25

BOT : 6-P25


[MID]0.6

0.0

51

50

.05

15

0.45

TOP : 6-P25

BOT : 14-P25


[END-J]

0.6

0.0

51

50

.05

15

0.45

TOP : 8-P25

BOT : 6-P25





Strength (PhiMn)




Strength (PhiMn)




30416.31

1

51847.60

0.5866

12647.78

3

39840.42

0.3175

0.0039

0.0029

4139.79

9

39474.75

0.1049

23105.35

1

84761.33

0.2726

0.0029

0.0069

47350.21

1

51847.60

0.9133

6716.94

5

39840.42

0.1686

0.0039

0.0029






Check Ratio

24392.93

15752.67

0.0017

4-P9 @150

0.7113

13780.30

15382.29

0.0017

4-P9 @150

0.4115

26963.05

15752.67

0.0017

4-P9 @150

0.7862

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Beam Span : 4 m

Section Property: BST-B4A (No : 17)

2. Section Diagram

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Strength (PhiMn)




Strength (PhiMn)




3580.37

5

3656.67

0.9791

2108.56

1

3656.67

0.5766

0.0004

0.0004

1764.42

5

3778.22

0.4670

2222.54

5

6595.64

0.3370

0.0004

0.0008

2844.16

1

3656.67

0.7778

2022.04

1

3656.67

0.5530

0.0004

0.0004






Check Ratio

5662.78

4650.91

0.0004

2-P6 @150

0.7664

4455.18

4380.48

0.0004

2-P6 @150

0.6402

4514.84

4650.91

0.0004

2-P6 @150

0.6111

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Beam Span : 1.5 m

Section Property: B2C (No : 18)

2. Section Diagram

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Strength (PhiMn)




Strength (PhiMn)




2373.10

1

5376.80

0.4414

1478.56

1

3674.49

0.4024

0.0006

0.0004

1528.86

1

5376.80

0.2843

513.89

1

3674.49

0.1399

0.0006

0.0004

2606.94

1

5376.80

0.4848

1363.94

1

3674.49

0.3712

0.0006

0.0004






Check Ratio

2692.96

4650.91

0.0004

2-P6 @150

0.3645

2824.47

4650.91

0.0004

2-P6 @150

0.3823

2925.27

4650.91

0.0004

2-P6 @150

0.3959

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Beam Span : 4 m

Section Property: B1(N) (No : 26)

2. Section Diagram

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Strength (PhiMn)




Strength (PhiMn)




1218.41

3

1948.05

0.6254

280.86

3

1169.04

0.2402

0.0002

0.0001

622.68

1

1091.07

0.5707

904.83

3

1091.07

0.8293

0.0001

0.0001

1295.58

1

1948.05

0.6651

617.83

1

1169.04

0.5285

0.0002

0.0001






Check Ratio

1350.32

2216.37

0.0004

2-P6 @150

0.2798

993.36

2338.52

0.0004

2-P6 @150

0.1951

1426.06

2216.37

0.0004

2-P6 @150

0.2955

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Beam Span : 3 m


2. Section Diagram

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Strength (PhiMn)




Strength (PhiMn)




2188.22

9

8293.21

0.2639

4205.29

3

5376.68

0.7821

0.0010

0.0006

3448.97

3

3674.49

0.9386

3013.75

3

5376.80

0.5605

0.0004

0.0006

7199.62

3

8293.21

0.8681

0.00

9

5376.68

0.0000

0.0010

0.0006






Check Ratio

4438.59

4650.91

0.0004

2-P6 @150

0.6008

6787.92

4650.91

0.0004

2-P6 @150

0.9187

7492.45

4434.56

0.0006

2-P6 @100

0.8973

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Beam Span : 3 m


2. Section Diagram

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Strength (PhiMn)




Strength (PhiMn)




1798.61

9

8284.70

0.2171

2130.28

7

3738.31

0.5699

0.0010

0.0004

2839.11

3

3656.67

0.7764

3388.56

3

3656.67

0.9267

0.0004

0.0004

7727.14

3

8284.70

0.9327

0.00

9

3738.31

0.0000

0.0010

0.0004






Check Ratio

3216.55

4650.91

0.0008

4-P6 @150

0.3177

7297.36

4650.91

0.0004

2-P6 @130

0.9614

8877.98

4434.56

0.0008

4-P6 @150

0.9195

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Beam Span : 3 m


2. Section Diagram

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Strength (PhiMn)




Strength (PhiMn)




2213.37

5

9661.99

0.2291

2364.90

7

3774.78

0.6265

0.0012

0.0004

2789.63

3

3674.49

0.7592

4034.98

3

5376.80

0.7504

0.0004

0.0006

8858.40

3

9661.99

0.9168

0.00

9

3774.78

0.0000

0.0012

0.0004






Check Ratio

4599.96

4380.48

0.0011

4-P6 @100

0.3797

8413.09

4650.91

0.0011

4-P6 @100

0.6540

11661.98

4380.48

0.0011

4-P6 @100

0.9626

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Beam Span : 4 m

Section Property: BST-B4A(N) (No : 30)

2. Section Diagram

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Strength (PhiMn)




Strength (PhiMn)




5290.36

5

8293.21

0.6379

4052.96

7

5376.68

0.7538

0.0010

0.0006

4704.26

3

5354.34

0.8786

3716.27

1

5354.34

0.6941

0.0006

0.0006

7339.31

3

8293.21

0.8850

3992.60

9

5376.68

0.7426

0.0010

0.0006






Check Ratio

7224.75

4434.56

0.0006

2-P6 @100

0.8653

6573.95

4650.91

0.0004

2-P6 @150

0.8898

7479.65

4434.56

0.0006

2-P6 @100

0.8958

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MIDAS/Gen RC Column Checking Result Output PROJECT TITLE :

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------------------------------------------------------------------------------------------ MIDAS/Gen - RC-Column Checking [ ACI318-89 ] Version 7.0.2==========================================================================================

+============================================================+ | MIDAS(Modeling, Integrated Design & Analysis Software) | | MIDAS/Gen - Design & checking system for windows | +============================================================+ | RC-Member(Beam/Column/Brace/Wall) Analysis and Design | | Based On ACI318-02, ACI318-99, ACI318-95, ACI318-89, | | CSA-A23.3-94, BS8110-97, Eurocode2 | | | | | | | | | | (c)1989-2006 | +============================================================+ | MIDAS Information Technology Co.,Ltd. (MIDAS IT) | | MIDAS IT Design Development Team | +============================================================+ | HomePage : www.MidasUser.com | | Tel : 360-753-5540, Fax : 360-753-5542 | +============================================================+ | MIDAS/Gen Version 7.0.2 | +============================================================+

*. DEFINITION OF LOAD COMBINATIONS WITH SCALING UP FACTORS.-------------------------------------------------------------------------------------- LCB C Loadcase Name(Factor) + Loadcase Name(Factor) + Loadcase Name(Factor)-------------------------------------------------------------------------------------- 1 1 DL( 1.400) + LL( 1.700) 2 1 DL( 1.050) + LL( 1.275) + Wx( 1.275) 3 1 DL( 1.050) + LL( 1.275) + Wy( 1.275) 4 1 DL( 1.050) + LL( 1.275) + Wx(-1.275) 5 1 DL( 1.050) + LL( 1.275) + Wy(-1.275) 6 1 DL( 0.900) + Wx( 1.300) 7 1 DL( 0.900) + Wy( 1.300) 8 1 DL( 0.900) + Wx(-1.300) 9 1 DL( 0.900) + Wy(-1.300)--------------------------------------------------------------------------------------

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*.MIDAS/Gen - RC-COLUMN Analysis/Design Program.

*.PROJECT : *.DESIGN CODE : ACI318-89, *.UNIT SYSTEM : kgf, m *.MEMBER : Member Type = COLUMN , MEMB = 22, LCB = 1, POS = I

*.DESCRIPTION OF COLUMN DATA (iSEC = 3) : C2 (30x50) Section Type : Rectangular with Ties (RT) Section Height (HTc) = 1.500 m. Section Depth (Hc) = 0.300 m. Section Width (Bc) = 0.500 m. Concrete Cover to C.O.R. (do) = 0.051 m. Concrete Strength (fc) = 2100000.000 kgf/m^2. Main Rebar Strength (fy) = 30000000.000 kgf/m^2. Ties/Spirals Strength (fys) = 24000000.000 kgf/m^2. Modulus of Elasticity (Es) = 2.039e+010 kgf/m^2.

*.DESCRIPTION OF APPLIED FACTORS FOR DESIGN/CHECKING. Live Load Reduction Factor = 0.700 (Axial, Moment, Shear)

*.REBAR PATTERN = RT - 10 - 3 - P25 Unit : m. -------------------------------------------------------- i dyi dzi Rebar Asi -------------------------------------------------------- 1 -0.199 -0.099 1-P25 0.00049 2 -0.199 0.000 1-P25 0.00049 3 -0.199 0.099 1-P25 0.00049 4 -0.066 0.099 1-P25 0.00049 5 0.066 0.099 1-P25 0.00049 6 0.199 0.099 1-P25 0.00049 7 0.199 0.000 1-P25 0.00049 8 0.199 -0.099 1-P25 0.00049 9 0.066 -0.099 1-P25 0.00049 10 -0.066 -0.099 1-P25 0.00049 --------------------------------------------------------

=============================================================================== [[[*]]] CACULATE SLENDERNESS RATIOS, MAGNIFIED FORCES/MOMENTS. ===============================================================================

( ). Factored forces/moments caused by unit load case. Unit : kgf., m. *.Load combination ID = 1 ------------------------------------------------------------------------------- Load Case Pu Myi Myj Mzi Mzj ------------------------------------------------------------------------------- DL 126953.97 -192.94 479.83 90.19 -1355.64 LL 53721.65 -55.90 129.35 -461.72 508.63 DL+LL 180675.62 -248.84 609.19 -371.52 -847.01 WL or EL -0.00 0.00 0.00 0.00 0.00 ------------------------------------------------------------------------------- DL+LL+WL(EL) 180675.62 -248.84 609.19 -371.52 -847.01 -------------------------------------------------------------------------------

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( ). Compute member end moments(M1,M2). Unit : kgf-m. -. For Dead Load(DL). My1D = 192.94, My2D = 479.83 Mz1D = 90.19, Mz2D = 1355.64 -. For Gravity Load(DL+LL). My1G = 248.84, My2G = 609.19 Mz1G = 371.52, Mz2G = 847.01

( ). Check slenderness ratios of BRACED/UNBRACED frame. -. Slenderness ratio limits. SRy(Unbraced) = 22.00 SRz(Unbraced) = 22.00 -. Radii of gyration. ry = 0.30*Hc = 0.090 m. rz = 0.30*Bc = 0.150 m. -. Unbraced lengths. Ly = 1.500 m. Lz = 1.500 m. -. Effective length factors. Ky = 1.000 Kz = 1.000 -. SLENy = Ky*Ly/ry = 16.667 < SRy ---> NOT SLENDER. -. SLENz = Kz*Lz/rz = 10.000 < SRz ---> NOT SLENDER.

( ). Moment magnification factors for major axis(DBy,DSy). -. DBy = 1.00 (Default value) -. DSy = 1.00 (Default value)

( ). Moment magnification factors for minor axis(DBz,DSz). -. DBz = 1.00 (Default value) -. DSz = 1.00 (Default value)

( ). Compute minimum moments(Mmin). -. emin_y = 0.6 in. + 0.03*Hc = 0.024 m. -. emin_z = 0.6 in. + 0.03*Bc = 0.030 m. -. Mmin_y = Pu * emin_y = 4379.58 kgf-m. -. Mmin_z = Pu * emin_z = 5463.63 kgf-m.

( ). Compute magnified moments. (Pos : I, Local-y : Unbraced, Local-z : Unbraced). -. No sidesway moments. QMb_y = My_G = -248.84 kgf-m. QMb_z = Mz_G = -371.52 kgf-m. -. Sidesway moments. QMs_y = My_S = 0.00 kgf-m. QMs_z = Mz_S = 0.00 kgf-m. -. Compute magnified moments(Mcy,Mcz). Mcy(No-Slender) = DBy*QMb_y + DSy*QMs_y = -248.84 kgf-m. Mcz(No-Slender) = DBz*QMb_z + DSz*QMs_z = -371.52 kgf-m.

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( ). Design forces/moments of column(brace). -. Axial Force (Compression) Pu = 180675.62 kgf. -. Combined Bending Moment Mc = 447.16 kgf-m. -. Bending Moment about Local-y Mcy = -248.84 kgf-m. -. Bending Moment about Local-z Mcz = -371.52 kgf-m. -. Shear Force of Local-y Vuy = 5596.64 kgf. -. Shear Force of Local-z Vuz = 1005.48 kgf.

=============================================================================== [[[*]]] ANALYZE CAPACITY OF BIAXIALLY LOADED RC_COLUMN(RC-BRACE). ===============================================================================

( ). Compute design parameters. -. Ag = 0.1500 m^2. -. Ast = 0.0049 m^2. -. Rhot = Ast/Ag = 0.032725 -. esu = fy/Es = 0.001471 -. beta1 = 0.8500 ( fc < 4000 psi.)

( ). Compute eccentricities of biaxially loaded column. -. Ecny = ABS(Mcz/Pu) = 0.0021 m. -. Ecnz = ABS(Mcy/Pu) = 0.0014 m. -. Eccn = ABS(Mc/Pu) = 0.0025 m. -. Rota = ATAN(Ecny/Ecnz) = 56.1865 deg. -. Rotation of neutral axis = 21.0700 deg.

( ). Compute concentric axial load capacity. -. Po = (0.85*fc)*(Ag-Ast) + fy*Ast = 406248.97 kgf. -. Maximum Axial Load : Pomax = 0.8*Po = 324999.18 kgf. -. Maximum Axial Tension : Pt = -fy*Ast = -147261.00 kgf.

---------------------------------------------------------------------------- *. Analysis of balanced condition. ----------------------------------------------------------------------------

( ). Compute capacity of concrete stress block. -. cb = (0.003/(0.003+esu))*d = 0.264 m. -. ab = beta1*cb = 0.224 m. -. Acom = 0.072 m^2. -. DCcy = 0.056 m. -. DCcz = 0.067 m. -. Cc = 0.85*fc*Acom = 128469.64 kgf. -. MnCy = Cc*DCcz = 8644.33 kgf-m. -. MnCz = Cc*DCcy = 7163.53 kgf-m.

( ). Compute capacity of reinforcement. ------------------------------------------------------------------------------------------------ i dsi esi fsi Asi Fsi dzi MnPyi dyi MnPzi ------------------------------------------------------------------------------------------------ 1 0.393 -0.001471 -3.00e+007 4.909e-004 -14726.10 -0.099 1450.52 -0.199 2923.13 2 0.301 -0.000426 -8684698.96 4.909e-004 -4263.06 0.000 -0.00 -0.199 846.22

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3 0.209 0.000619 1.26e+007 4.909e-004 6199.98 0.099 610.70 -0.199 -1230.70 4 0.162 0.001161 2.37e+007 4.909e-004 11615.64 0.099 1144.14 -0.066 -768.57 5 0.114 0.001702 3.00e+007 4.909e-004 14726.10 0.099 1450.52 0.066 974.38 6 0.067 0.002243 3.00e+007 4.909e-004 14726.10 0.099 1450.52 0.199 2923.13 7 0.158 0.001197 2.44e+007 4.909e-004 11983.91 0.000 0.00 0.199 2378.81 8 0.250 0.000152 3098312.35 4.909e-004 1520.87 -0.099 -149.81 0.199 301.89 9 0.298 -0.000389 -7934458.44 4.909e-004 -3894.79 -0.099 383.64 0.066 -257.71 10 0.346 -0.000930 -1.90e+007 4.909e-004 -9310.44 -0.099 917.08 -0.066 616.04 ------------------------------------------------------------------------------------------------ -. Ps = SUM [ Fsi ] = 28578.21 kgf. -. MnPy = SUM [ MnPyi ] = 7257.31 kgf-m. -. MnPz = SUM [ MnPzi ] = 8706.63 kgf-m.

( ). Compute nominal capacity(Pb,Mb) of Balanced Condition. -. Pb = Cc + Ps = 157047.86 kgf. -. Mny = MnCy + MnPy = 15901.64 kgf-m. -. Mnz = MnCz + MnPz = 15870.16 kgf-m. -. Mb = SQRT(Mny^2+Mnz^2) = 22466.06 kgf-m.

( ). Compare actual eccentricity with balanced eccentricity. -. Balanced eccentricity : eb = Mb/Pb = 0.143 m. -. Minimum eccentricity : Emin (not defined) = 0.000 m. -. Actual eccentricity : Eccn = Mu/Pu = 0.002 m. -. Emin < Eccn < eb ---> Compression controls.

( ). Search for neutral axis...... Unit : kgf., m. ------------------------------------------------------------------------------- Trial c Pn Mn Ecn Eccn Ratio ------------------------------------------------------------------------------- 1-st 0.541 401931.88 2095.35 0.005 0.002 47.47 -------------------------------------------------------------------------------

---------------------------------------------------------------------------- *. Final analysis with searched neutral axis. ----------------------------------------------------------------------------

( ). Compute capacity of compression stress block. -. a = beta1*c = 0.460 m. -. Acom = 0.150 m^2. -. DCcy = 0.000 m. -. DCcz = 0.000 m. -. Cc = 0.85*fc*Acom = 267750.00 kgf. -. MnCy = Cc*DCcz = 0.00 kgf-m. -. MnCz = Cc*DCcy = 0.00 kgf-m.

( ). Compute capacity of reinforcement. ------------------------------------------------------------------------------------------------ i dsi esi fsi Asi Fsi dzi MnPyi dyi MnPzi ------------------------------------------------------------------------------------------------ 1 0.393 0.000819 1.67e+007 4.909e-004 8199.66 -0.099 -807.67 -0.199 -1627.63 2 0.301 0.001329 2.71e+007 4.909e-004 13302.55 0.000 0.00 -0.199 -2640.56 3 0.209 0.001839 3.00e+007 4.909e-004 14726.10 0.099 1450.52 -0.199 -2923.13

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4 0.162 0.002103 3.00e+007 4.909e-004 14726.10 0.099 1450.52 -0.066 -974.38 5 0.114 0.002367 3.00e+007 4.909e-004 14726.10 0.099 1450.52 0.066 974.38 6 0.067 0.002631 3.00e+007 4.909e-004 14726.10 0.099 1450.52 0.199 2923.13 7 0.158 0.002121 3.00e+007 4.909e-004 14726.10 0.000 0.00 0.199 2923.13 8 0.250 0.001611 3.00e+007 4.909e-004 14726.10 -0.099 -1450.52 0.199 2923.13 9 0.298 0.001347 2.75e+007 4.909e-004 13482.16 -0.099 -1327.99 0.066 892.07 10 0.346 0.001083 2.21e+007 4.909e-004 10840.91 -0.099 -1067.83 -0.066 -717.31 ------------------------------------------------------------------------------------------------ -. Ps = SUM [ Fsi ] = 134181.88 kgf. -. MnPy = SUM [ MnPyi ] = 1148.07 kgf-m. -. MnPz = SUM [ MnPzi ] = 1752.84 kgf-m.

( ). Compute nominal capacity(Pn,Mn) of given neutral axis. -. Pn = Cc + Ps = 401931.88 kgf. -. Mny = MnCy + MnPy = 1148.07 kgf-m. -. Mnz = MnCz + MnPz = 1752.84 kgf-m. -. Mn = SQRT(Mny^2+Mnz^2) = 2095.35 kgf-m. -. Pn > Pomax ---> Pn = Pomax = 324999.18 kgf.

( ). Compute strength reduction factor. -. Pa = MIN[0.118*fc*Ag, Pb ] = 37170.00 kgf. -. Pn > Pa ---> phi = 0.85

( ). Compute axial load and moment capacities(phiPn,phiMn). -. phiPn = phi*Pn = 276249.30 kgf. -. phiMn = phi*Mn = 1781.05 kgf-m. -. phiMny = phi*Mny = 975.86 kgf-m. -. phiMnz = phi*Mnz = 1489.91 kgf-m.

( ). Check ratios of axial load and moment capacity. -. Rat_P = Pu/phiPn = 0.654 < 1.000 ---> O.K. -. Rat_M = Mc/phiMn = 0.251 < 1.000 ---> O.K.

=============================================================================== [[[*]]] ANALYZE SHEAR CAPACITY OF BIAXIALLY LOADED RC-COLUMN(RC-BRACE). ===============================================================================

( ). Compute maximum spacing of ties. -. smax = MIN[ 16*Dbar, 48*Dstir, Hc, Bc ] = 0.300 m.

( ). Compute concrete shear strength in local-z direction. ( LCB = 4, POS = J ) -. Applied axial force : Pu = 134980.44 kgf. -. Applied shear force : Vuz = 1005.48 kgf. -. d = Hc-do = 0.248 m. -. Bw = Bc = 0.500 m. -. Acv = Bw*d = 0.124 m^2. -. Vc = 2*(1+Pu/(2000*Ag))*SQRT(fc)*Acv = 15659.14 kgf. -. phi = 0.85 -. phiVc = phi*Vc = 13310.27 kgf. -. Vuz < phiVc/2 ---> Not required shear reinforcement.

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( ). Compute concrete shear strength in local-y direction. ( LCB = 9, POS = J ) -. Applied axial force : Pu = 80161.73 kgf. -. Applied shear force : Vuy = 5596.64 kgf. -. d = Bc-do = 0.448 m. -. Bw = Hc = 0.300 m. -. Acv = Bw*d = 0.135 m^2. -. Vc = 2*(1+Pu/(2000*Ag))*SQRT(fc)*Acv = 14269.84 kgf. -. phi = 0.85 -. phiVc = phi*Vc = 12129.37 kgf. -. Vuy < phiVc/2 ---> Not required shear reinforcement.

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y

z1. Design Condition

Design Code : ACI318-89


Member Number: 46 (PM), 46 (Shear)


Column Height : 4.5 m

Section Property: C1 (FL0-2) (No : 31)

Rebar Pattern : 8 - 3 - P16

Total Rebar Area Ast = 0.00160848 m^2 (Rhost = 0.018)

2. Applied LoadsLoad Combination : 5 AT (I) Point

Pu = 45983.9 kgf

Mcy = 1554.56, Mcz = 3133.76 kgf-m

Mc = SQRT(Mcy^2+ Mcz^2) = 3498.16 kgf-m

3. Axial Forces and Moments Capacity CheckConcentric Max. Axial Load PhiPn-max = 140103 kgf

Axial Load Ratio Pu/PhiPn = 45983.9 / 92208.8 = 0.499 < 1.000 ....... O.K

Moment Ratio Mc/PhiMn = 3498.16 / 7051.52 = 0.496 < 1.000 ....... O.K

Mcy/PhiMny = 1554.56 / 3046.34 = 0.510 < 1.000 ....... O.K

Mcz/PhiMnz = 3133.76 / 6359.55 = 0.493 < 1.000 ....... O.K

4. P-M Interaction Diagram

215456

188241

922

161025

1843

133810

2765

106594

3687

79379

4608

52163

5530

24948

6452

-2268

7374

-29484

8295

-56699

9217

(92209,7052)

(45984,3498)

140103

0

0

P(kgf)

M(kgf-m)

Theta=64.40Deg.N.A=59.64Deg.

PhiPn(kgf) PhiMn(kgf-m)

175128.27 0.00

166099.69 1514.79

150372.70 3381.92

129278.09 5215.93

105477.31 6554.28

85002.00 7262.84

73065.79 7534.06

62162.03 7552.41

40759.34 7242.04

15384.74 6153.10

-12335.35 4204.58

-34574.07 1441.04

-43428.96 0.00

5. Shear Force Capacity CheckApplied Shear Strength Vu = 2744.25 kgf (Load Combination : 7)

Design Shear Strength PhiVc+PhiVs = 5476.99 + 1476.37 = 6953.36 kgf (As-H_req = 0.00028 m^2/m, 2-P6 @200)

Shear Ratio Vu/PhiVn = 0.395 < 1.000 ....... O.K

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0.3

0.0

44

0.3

y







Section Property: C1 (FL3-Roof) (No : 32)



2. Applied LoadsLoad Combination : 3 AT (I) Point

Pu = 17100.9 kgf

Mcy = 1222.30, Mcz = 1956.19 kgf-m





Mcy/PhiMny = 1222.30 / 3464.90 = 0.353 < 1.000 ....... O.K

Mcz/PhiMnz = 1956.19 / 5542.18 = 0.353 < 1.000 ....... O.K


204117

179169

806

154221

1613

129274

2419

104326

3226

79379

4032

54431

4839

29484

5645

4536

6452

-20412

7258

-45359

8065

(49257,6536)

(17101,2307)

132387

0

0

P(kgf)

M(kgf-m)



165484.33 0.00

157965.05 1344.99

143490.74 3100.06

123747.61 4797.02

101322.98 6002.40

81850.25 6589.18

70611.52 6779.23

60598.63 6714.74

41129.09 6351.47

17200.12 5396.03

-6228.41 3812.95

-23783.16 1431.48

-32571.72 0.00


Design Shear Strength PhiVc+PhiVs = 6147.31 + 1476.37 = 7623.68 kgf (As-H_req = 0.00028 m^2/m, 2-P6 @200)


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0.3

0.0

51

5

0.5

y







Section Property: C2 (FL0-2) (No : 33)



2. Applied LoadsLoad Combination : 1 AT (J) Point

Pu = 175853 kgf

Mcy = 4453.85, Mcz = 14985.2 kgf-m



Axial Load Ratio Pu/PhiPn = 175853 / 223328 = 0.787 < 1.000 ....... O.K


Mcy/PhiMny = 4453.85 / 5525.87 = 0.806 < 1.000 ....... O.K

Mcz/PhiMnz = 14985.2 / 18904.1 = 0.793 < 1.000 ....... O.K


408233

352668

3456

297103

6913

241538

10369

185973

13825

130408

17282

74843

20738

19278

24195

-36287

27651

-91852

31107

-147418

34564

(223328,19695)

(175853,15633)

276249

0

0

P(kgf)

M(kgf-m)



345311.62 0.00

324517.63 5437.23

293716.55 10723.56

251864.33 16432.51

205749.47 21311.37

164628.00 24265.83

140157.04 25627.40

116138.36 26157.17

68939.89 26028.05

11834.67 22849.77

-51295.59 15621.69

-109687.26 5258.04

-132534.90 0.00


Design Shear Strength PhiVc+PhiVs = 10869.5 + 5158.62 = 16028.2 kgf (As-H_req = 0.00102 m^2/m, 2|4-P9 @250)


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0.3

0.0

46

0.45

y







Section Property: C2 (FL3) (No : 34)




Pu = 114790 kgf

Mcy = 2784.68, Mcz = 16527.2 kgf-m



Axial Load Ratio Pu/PhiPn = 114790 / 116092 = 0.989 < 1.000 ....... O.K


Mcy/PhiMny = 2784.68 / 2944.91 = 0.946 < 1.000 ....... O.K

Mcz/PhiMnz = 16527.2 / 16816.7 = 0.983 < 1.000 ....... O.K


317515

277825

2304

238136

4608

198447

6913

158757

9217

119068

11521

79379

13825

39689

16130

0

18434

-39689

20738

-79379

23042

(116092,17073)(114790,16760)

212083

0

0

P(kgf)

M(kgf-m)



265104.12 0.00

249786.74 3568.09

222491.62 8016.60

189093.79 12139.12

158848.00 14789.69

133684.70 16353.08

118628.99 17022.36

103970.47 17248.17

73971.72 17097.58

37575.37 14948.77

-5230.08 11040.68

-47136.45 4437.77

-67858.56 0.00




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0.0

46

0.45

y







Section Property: C2 (FL4-Roof) (No : 35)




Pu = 45545.2 kgf

Mcy = 1094.32, Mcz = 15439.3 kgf-m





Mcy/PhiMny = 1094.32 / 1164.13 = 0.940 < 1.000 ....... O.K

Mcz/PhiMnz = 15439.3 / 16487.5 = 0.936 < 1.000 ....... O.K


317515

277825

2304

238136

4608

198447

6913

158757

9217

119068

11521

79379

13825

39689

16130

0

18434

-39689

20738

-79379

23042

(48810,16529)(45545,15478)

212083

0

0

P(kgf)

M(kgf-m)



265104.12 0.00

243192.89 4721.17

212019.61 9688.87

182480.24 13173.42

154964.85 15479.25

131516.34 16907.27

117451.47 17568.41

103760.80 17862.17

79158.55 17684.16

46640.23 16409.29

8419.07 13088.21

-38394.44 5942.60

-67858.56 0.00




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MIDAS/Gen Steel Code Checking Result Output PROJECT TITLE :

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File Name Untitled.acs

------------------------------------------------------------------------------------------ MIDAS/Gen - Steel Code Checking [ AISC-ASD89 ] Version 7.0.2==========================================================================================

+============================================================+ | MIDAS(Modeling, Integrated Design & Analysis Software) | | MIDAS/Gen - Design & checking system for windows | +============================================================+ | Steel Member Applicable Code Checking | | Based On AISC-LRFD2K, AISC-LRFD93, AISC-ASD89, | | AISI-CFSD86, CSA-S16-01, BS5950-90, | | Eurocode3 | | | | | | | | (c)1989-2006 | +============================================================+ | MIDAS Information Technology Co.,Ltd. (MIDAS IT) | | MIDAS IT Design Development Team | +============================================================+ | HomePage : www.MidasUser.com | | Tel : 360-753-5540, Fax : 360-753-5542 | +============================================================+ | MIDAS/Gen Version 7.0.2 | +============================================================+

*. DEFINITION OF LOAD COMBINATIONS WITH SCALING UP FACTORS.-------------------------------------------------------------------------------------- LCB C Loadcase Name(Factor) + Loadcase Name(Factor) + Loadcase Name(Factor)-------------------------------------------------------------------------------------- 1 1 DL( 1.000) + LL( 1.000) 2 1 DL( 0.750) + LL( 0.750) + Wx( 0.750) 3 1 DL( 0.750) + LL( 0.750) + Wy( 0.750) 4 1 DL( 0.750) + LL( 0.750) + Wx(-0.750) 5 1 DL( 0.750) + LL( 0.750) + Wy(-0.750) 6 1 DL( 0.750) + Wx( 0.750) 7 1 DL( 0.750) + Wy( 0.750) 8 1 DL( 0.750) + Wx(-0.750) 9 1 DL( 0.750) + Wy(-0.750) 10 1 DL( 1.000) + LL( 1.000) 11 1 DL( 0.750) + LL( 0.750) + Wx( 0.750) 12 1 DL( 0.750) + LL( 0.750) + Wy( 0.750) 13 1 DL( 0.750) + LL( 0.750) + Wx(-0.750) 14 1 DL( 0.750) + LL( 0.750) + Wy(-0.750) 15 1 DL( 0.750) + Wx( 0.750) 16 1 DL( 0.750) + Wy( 0.750) 17 1 DL( 0.750) + Wx(-0.750) 18 1 DL( 0.750) + Wy(-0.750)--------------------------------------------------------------------------------------

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*. PROJECT : *. MEMBER NO = 993, ELEMENT TYPE = Beam *. LOADCOMB NO = 10, MATERIAL NO = 1, SECTION NO = 19 *. UNIT SYSTEM : kgf, cm

*. SECTION PROPERTIES : Designation = Truss-2, P 48.6x2.8 Shape = P - Section. (Rolled) Outer Dia. = 4.860, Wall Thick = 0.280

Area = 4.02900e+000, Asy = 2.01439e+000, Asz = 2.01439e+000 Ybar = 2.43000e+000, Zbar = 2.43000e+000, Qyb = 5.26370e+000, Qzb = 5.26370e+000 Syy = 4.36000e+000, Szz = 4.36000e+000, Zyy = 5.88071e+000, Zzz = 5.88071e+000 Iyy = 1.06000e+001, Izz = 1.06000e+001, Iyz = 0.00000e+000 ry = 1.62000e+000, rz = 1.62000e+000, rp = 0.00000e+000 J = 2.12063e+001, Cwp = 2.68536e+030

*. DESIGN PARAMETERS FOR STRENGTH EVALUATION : Ly = 9.05865e+001, Lz = 9.05865e+001, Lu = 9.05865e+001 Ky = 1.00000e+000, Kz = 1.00000e+000

*. MATERIAL PROPERTIES : Fy = 2.40000e+003, Es = 2.10000e+006, MATERIAL NAME = SS400

*. FORCES AND MOMENTS AT (1/2) POINT : Axial Force Fxx =-2.53611e+003 Shear Forces Fyy =-2.72715e-002, Fzz = 0.00000e+000 Bending Moments My = 1.81476e+003, Mz =-4.46954e-001 End Moments Myi = 0.00000e+000, Myj = 0.00000e+000 (for Lb) Myi = 0.00000e+000, Myj = 0.00000e+000 (for Ly) Mzi =-1.68217e+000, Mzj = 7.88259e-001 (for Lz)

================================================================================ [[[*]]] CHECK AXIAL STRESS.================================================================================

( ). Check slenderness ratio of axial compression member (Kl/r). [ AISC-ASD89 Specification B7. ] -. Kl/r = 55.9 < 240.0 ---> O.K.

( ). Calculate critical flexural-torsional elastic buckling stress (Fe). [ AISC-ASD89 Specification E3. ] [ AISC-LRFD86 Specification Appendix E3. (A-E3-5) ] -. Gs = Es/(2(1+Poisson Ratio)) = 807692.3077 kgf/cm^2. -. Kx = 1.00 (Conservatively taken value). -. Lx = 90.5865 cm. -. Fe = {Pi^2*Es*Cwp/(Kx*Lx)^2 + Gs*J}/(Iyy+Izz) = 3.1993e+032 kgf/cm^2.

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( ). Check slenderness ratio by flexural-torsional elastic buckling. [ AISC-ASD89 Specification Commentary E3. (C-E2-2) ] -. (Kl/r)e = Pi*SQRT[ Es/Fe ] =2.55e-013 -. (Kl/r)e < Kl/r ---> Need not flexural-torsional buckling

( ). Check Diameter-thickness ratio of pipe (DTR). [ AISC-ASD89 Specification Appendix B. B5.b. ] -. DTR = D/tw = 17.36 < 13000/Fy ---> O.K.

( ). Check Diameter-thickness ratio of pipe (DTR). [ AISC-ASD89 Specification B5.1 ] -. DTR = D/tw = 17.36 < 3300/Fy ---> COMPACT SECTION !

( ). Calculate allowable compressive stress (Fa). [ AISC-ASD89 Specification E2. (E2-1) ] [ 2*(Pi^2)*Es ] -. Cc = SQRT [ ------------- ] = 131.42 [ Fy ] -. Kl/r < Cc [ (Kl/r)^2 ] [ 1 - ---------- ]*Fy [ 2*Cc^2 ] -. Fa = ------------------------------- = 1201.567 kgf/cm^2. 5 3*(Kl/r) (Kl/r)^3 --- + ---------- - ---------- 3 8*Cc 8*Cc^3

( ). Calculate axial compressive stress of member (fa). -. fa = Fxx/Area = -629.464 kgf/cm^2.

( ). Check ratio of axial stress (fa/Fa). fa 629.464 -. ---- = ------------ = 0.524 < 1.000 ---> O.K. Fa 1201.567

================================================================================ [[[*]]] CHECK BENDING STRESSES ABOUT MAJOR AXIS.================================================================================



( ). Calculate allowable bending stresses (FBCy,FBTy). [ AISC-ASD89 Specification F3.1 (F3-1) ] -. FBCy,FBTy = 0.66*Fy = 1584.000 kgf/cm^2.

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( ). Calculate actual bending stresses of member (fbcy,fbty). -. fbcy = (My*Ccom)/Iyy = -416.025 kgf/cm^2. -. fbty = (My*Cten)/Iyy = 416.025 kgf/cm^2.

( ). Check ratios of stresses (fbcy/FBCy,fbty/FBTy). fbcy 416.025 -. ------ = ------------ = 0.263 < 1.000 ---> O.K. FBCy 1584.000 fbty 416.025 -. ------ = ------------ = 0.263 < 1.000 ---> O.K. FBTy 1584.000

================================================================================ [[[*]]] CHECK BENDING STRESSES ABOUT MINOR AXIS.================================================================================



( ). Calculate allowable bending stresses (FBCz,FBTz). [ AISC-ASD89 Specification F3.1 (F3-1) ] -. FBCz,FBTz = 0.66*Fy = 1584.000 kgf/cm^2.

( ). Calculate actual bending stresses of member (fbcz,fbtz). -. fbcz = (Mz*Ccom)/Izz = -0.102 kgf/cm^2. -. fbtz = (Mz*Cten)/Izz = 0.102 kgf/cm^2.

( ). Check ratios of stresses (fbcz/FBCz,fbtz/FBTz). fbcz 0.102 -. ------ = ------------ =6.469e-005 < 1.000 ---> O.K. FBCz 1584.000 fbtz 0.102 -. ------ = ------------ =6.469e-005 < 1.000 ---> O.K. FBTz 1584.000

================================================================================ [[[*]]] CHECK COMBINED STRESSES.================================================================================

( ). Check interaction ratio of combined stresses (Axial compression + bending). [ AISC-ASD89 Specification H1. ] -. Check ratio of axial compressive stress (fa/Fa). fa/Fa > 0.15 ---> Equation (H1-1) and (H1-2)

( ). Compute equivalent moment factor (Cmy, Cmz). -. Cmy = 1.000 (User defined or default value)

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-. Cmz = 1.000 (User defined or default value) 12*(Pi^2)*Es -. F'ey = -------------- = 3458.401 kgf/cm^2. 23*(Kl/r)^2 Cmy -. SFy = -------------- = 1.223 1. - fa/F'ey 12*(Pi^2)*Es -. F'ez = -------------- = 3458.401 kgf/cm^2. 23*(Kl/r)^2 Cmz -. SFz = -------------- = 1.223 1. - fa/F'ez

*. Check interaction ratio of combined stress at member mid point. fa [ | SFy*fbcy |^2 | SFz*fbcz |^2 ] -. Rmax1 = ---- + SQRT [ |----------| + |----------| ] Fa [ | FBCy | | FBCz | ] = 0.845 < 1.000 ---> O.K. fa [ | fbcy |^2 | fbcz |^2 ] -. Rmax2 = -------- + SQRT [ |------| + |------| ] 0.6*Fy [ | FBCy | | FBCz | ] = 0.700 < 1.000 ---> O.K.

================================================================================ [[[*]]] CHECK SHEAR STRESSES.================================================================================

( ). Calculate allowable shear stress (Fv). [ AISC-ASD89 Specification F4 ] -. Fv = 0.40*Fy = 960.000 kgf/cm^2.

( ). Calculate shear stress (fv). ( LCB = 10, POS = J ) -. Applied shear force : Fvv = SQRT[Fzz^2+Fyy^2] = 0.03 kgf. -. fv = Fvv / Area = 0.007 kgf/cm^2.

( ). Check ratio of shear stress (fv/Fv). fv 0.007 -. ---- = ------------ =7.051e-006 < 1.000 ---> O.K. Fv 960.000

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1. Design Information Design Code : AISC-ASD89

Unit System : kgf, cm

Element No : 993

Material : SS400 (No:1)

(Fy = 2400.00, Es = 2100000)

Section Name : Truss-2 (No:19)

(Rolled : P 48.6x2.8).

Member Length : 90.5865

Outer Dia. 4.86000 Wall Thick 0.28000

4.86

0.28

y

z

Area 4.02900 Asz 2.01439Qyb 5.26370 Qzb 5.26370Iyy 10.6000 Izz 10.6000Ybar 2.43000 Zbar 2.43000Syy 4.36000 Szz 4.36000ry 1.62000 rz 1.62000

2. Member Forces Axial Force Fxx = -2536.1 (LCB: 1, POS:1/2)

Bending Moments My = 1814.76, Mz = -0.4470

End Moments Myi = 0.00000, Myj = 0.00000 (for Lb)

Myi = 0.00000, Myj = 0.00000 (for Ly)

Mzi = -1.6822, Mzj = 0.78826 (for Lz)

Shear Forces Fyy = -0.0273 (LCB: 10, POS:J)

Fzz = 80.1337 (LCB: 10, POS:J)

3. Design Parameters Unbraced Lengths Ly = 90.5865, Lz = 90.5865, Lb = 90.5865

Effective Length Factors Ky = 1.00, Kz = 1.00

Moment Factor / Bending Coefficient

Cmy = 1.00, Cmz = 1.00, Cb = 1.00

4. Stress Checking Results Axial Stress

Slenderness Ratio : KL/r = 55.9 < 240.0 ............................... O.K

fa/Fa = 629.46/1201.57 = 0.524 < 1.000 ............................... O.K

Bending Stresses

fby/Fby = 416.02/1584.00 = 0.263 < 1.000 ............................... O.K

fbz/Fbz = 0.10/1584.00 = 0.000 < 1.000 ............................... O.K

Combined Stress (Compression+Bending)

SFy = [Cmy/(1-fa/F'ey)], SFz = [Cmz/(1-fa/F'ez)]

Rmax1 = fa/Fa + SQRT[SFy*(fbcy/Fbcy)^2 + SFz*(fbcz/Fbcz)^2]

Rmax2 = fa/0.60Fy + SQRT[(fbcy/Fbcy)^2 + (fbcz/Fbcz)^2]

Rmax = Max[Rmax1, Rmax2] = 0.845 < 1.000 ............................... O.K

Shear Stresses

fv/Fv = 0.021 < 1.000 ................................................. O.K

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Element No : 1554


(Fy = 2400.00, Es = 2100000)


(Rolled : P 42.7x2.8).



4.27

0.28

y

z


2. Member Forces Axial Force Fxx = -162.88 (LCB: 4, POS:J)

Bending Moments My = 0.00000, Mz = 974.083


Myi = 0.00000, Myj = 0.00000 (for Ly)

Mzi = 442.653, Mzj = 974.083 (for Lz)

Shear Forces Fyy = -5.3143 (LCB: 13, POS:I)

Fzz = -1.0333 (LCB: 13, POS:I)




Cmy = 1.00, Cmz = 1.00, Cb = 1.00



fa/Fa = 46.40/1108.76 = 0.042 < 1.000 ............................... O.K

Bending Stresses

fby/Fby = 0.00/1584.00 = 0.000 < 1.000 ............................... O.K

fbz/Fbz = 296.25/1584.00 = 0.187 < 1.000 ............................... O.K


Rmax = fa/Fa + SQRT[(fbcy/Fbcy)^2 + (fbcz/Fbcz)^2] = 0.229 < 1.000 ..... O.K

Shear Stresses

fv/Fv = 0.002 < 1.000 ................................................. O.K

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*. PROJECT : *. MEMBER NO = 1007, ELEMENT TYPE = Truss *. LOADCOMB NO = 10, MATERIAL NO = 1, SECTION NO = 20 *. UNIT SYSTEM : kgf, cm

*. SECTION PROPERTIES : Designation = Truss-2, P 42.7x2.8 Shape = P - Section. (Rolled) Outer Dia. = 4.270, Wall Thick = 0.280

Area = 3.51000e+000, Asy = 1.75489e+000, Asz = 1.75489e+000 Ybar = 2.13500e+000, Zbar = 2.13500e+000, Qyb = 3.99963e+000, Qzb = 3.99963e+000 Syy = 3.29000e+000, Szz = 3.29000e+000, Zyy = 4.46495e+000, Zzz = 4.46495e+000 Iyy = 7.02000e+000, Izz = 7.02000e+000, Iyz = 0.00000e+000 ry = 1.41000e+000, rz = 1.41000e+000, rp = 0.00000e+000 J = 1.40378e+001, Cwp = 2.68536e+030



*. FORCES AND MOMENTS AT (J) POINT : Axial Force Fxx = 2.03623e+003 Shear Forces Fyy = 0.00000e+000, Fzz = 0.00000e+000 Bending Moments My = 0.00000e+000, Mz = 0.00000e+000 End Moments Myi = 0.00000e+000, Myj = 0.00000e+000 (for Lb) Myi = 0.00000e+000, Myj = 0.00000e+000 (for Ly) Mzi = 0.00000e+000, Mzj = 0.00000e+000 (for Lz)

================================================================================ [[[*]]] CHECK AXIAL STRESS.================================================================================

( ). Check slenderness ratio of axial tension member (l/r). [ AISC-ASD89 Specification B7. ] -. l/r = 64.4 < 300.0 ---> O.K.

( ). Calculate allowable tensile stress (Ft). [ AISC-ASD89 Specification D1. ] -. Ft = 0.6*Fy = 1440.000 kgf/cm^2.

( ). Calculate axial tensile stress of member (ft). -. ft = Fxx/Area = 580.123 kgf/cm^2.

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( ). Check ratio of axial stress (ft/Ft). ft 580.123 -. ---- = ------------ = 0.403 < 1.000 ---> O.K. Ft 1440.000

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Element No : 1007


(Fy = 2400.00, Es = 2100000)


(Rolled : P 42.7x2.8).



4.27

0.28

y

z


2. Member Forces Axial Force Fxx = 2036.23 (LCB: 1, POS:J)



Myi = 0.00000, Myj = 0.00000 (for Ly)

Mzi = 0.00000, Mzj = 0.00000 (for Lz)

Shear Forces Fyy = 0.00000 (LCB: 16, POS:I)

Fzz = 0.00000 (LCB: 16, POS:I)




Cmy = 1.00, Cmz = 1.00, Cb = 1.00


Slenderness Ratio : L/r = 64.4 < 300.0 ............................... O.K

ft/Ft = 580.12/1440.00 = 0.403 < 1.000 ............................... O.K

Bending Stresses

fby/Fby = 0.00/1584.00 = 0.000 < 1.000 ............................... O.K

fbz/Fbz = 0.00/1440.00 = 0.000 < 1.000 ............................... O.K


Rmax = = 0.403 < 1.000 ................................................ O.K

Shear Stresses

fv/Fv = 0.000 < 1.000 ................................................. O.K

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Element No : 1521


(Fy = 2400.00, Es = 2100000)


(Rolled : P 42.7x2.8).



4.27

0.28

y

z


2. Member Forces Axial Force Fxx = -165.30 (LCB: 1, POS:I)



Myi = 0.00000, Myj = 0.00000 (for Ly)

Mzi = 0.00000, Mzj = 0.00000 (for Lz)

Shear Forces Fyy = 0.00000 (LCB: 16, POS:I)

Fzz = 0.00000 (LCB: 16, POS:I)




Cmy = 1.00, Cmz = 1.00, Cb = 1.00



fa/Fa = 47.09/1062.86 = 0.044 < 1.000 ............................... O.K

Bending Stresses

fby/Fby = 0.00/1584.00 = 0.000 < 1.000 ............................... O.K

fbz/Fbz = 0.00/1440.00 = 0.000 < 1.000 ............................... O.K


Rmax = = 0.044 < 1.000 ................................................ O.K

Shear Stresses

fv/Fv = 0.000 < 1.000 ................................................. O.K

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Print Date/Time : 03/10/2010 00:42


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------------------------------------------------------------------------------------------ MIDAS/Gen - Steel Code Checking [ AISI-CFSD86 ] Version 7.0.2==========================================================================================



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*. PROJECT : *. MEMBER NO = 2112, ELEMENT TYPE = Beam *. LOADCOMB NO = 10, MATERIAL NO = 1, SECTION NO = 24 *. UNIT SYSTEM : kgf, cm

*. SECTION PROPERTIES : Designation = LC-100x50x20x2.3 Shape = CC - Section. (Rolled) Depth = 10.000, Width = 5.000, Lip Depth = 2.000 Thickness = 0.230, Fillet Radius = 0.460

Area = 5.17200e+000, Asy = 1.38767e+000, Asz = 1.98260e+000 Ybar = 1.85228e+000, Zbar = 5.00000e+000, Qyb = 2.69718e+001, Qzb = 3.02020e+000 Syy = 1.61000e+001, Szz = 6.06000e+000, Zyy = 0.00000e+000, Zzz = 0.00000e+000 Iyy = 8.07000e+001, Izz = 1.90000e+001, Iyz = 0.00000e+000 ry = 3.95000e+000, rz = 1.92000e+000, rp = 0.00000e+000 J = 8.95937e-002, Cwp = 4.90098e+002



====================================================================================== [[[*]]] COMPUTE MOMENT MAGNIFICATION FACTORS AND MAGNIFIED MOMENTS.======================================================================================

====================================================================================== [[[*]]] CALCULATE FULL SECTION PRORERTIES.======================================================================================

( ). Calculate properties of sections with or without lips. [ AISI-CFSD86 Supplementary III 1.2 ] -. Alpha = 1.0000 -. r = R + t/2 = 0.5750 cm. -. a = H - (2*r+t) = 8.6200 cm. -. a_bar = H - t = 9.7700 cm. -. b = B - [r+t/2 + Alpha*(r+t/2)] = 3.6200 cm. -. b_bar = B - (t/2 + Alpha*t/2) = 4.7700 cm. -. c = Alpha*[C - (r+t/2)] = 1.3100 cm. -. c_bar = Alpha*(C - t/2) = 1.8850 cm. -. u = 1.57*r = 0.9028 cm.

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-. A = t*{ a + 2*b + 2*c + Alpha*(2*c + 2*u) } = 5.0809 cm^2. -. Iyy = (2*t) * { 0.0417*a^3 + b*(a/2+r)^2 + u*(a/2+0.637*r)^2) + 0.149*r^3 + Alpha*[0.0833*c^3 + (c/4)*(a-c)^2 + u*(a/2+0.637*r)^2) + 0.149*r^3] } = 78.3472 cm^4. -. x_bar = (2*t/A) * { b*(b/2+r) + u*(0.363*r) + Alpha*[u*(b+1.637*r) + c*(b+2*r)] }

= 1.7372 cm. -. Izz = (2*t) * { b*(b/2+r)^2 + 0.0833*b^3 + 0.356*r^3 + Alpha*[c*(b+2*r)^2 + u*(b+1.637*r)^2 + 0.149*r^3] } - A*x_bar^2 = 18.3505 cm^4.

-. m = b_bar*t/(12*Iy) * { 6*c_bar*a_bar^2 + 3*b_bar*a_bar^2 - 8*c_bar^3 } = 2.7912 cm. -. x0 = (-1)*(x_bar + m) = -4.5284 cm.

-. Rxx = (t^3/3)*{ a + 2*b + 2*u + Alpha*(2*c + 2*u) } = 0.092897 cm^4. -. Cwp = (t^2/A)*{ (x_bar*A*a_bar^2/t) * [b_bar^2/3 + m^2 - m*b_bar] + [A/(3*t)] * [m^2*a_bar^3 + b_bar^2*c_bar^2*(2*c_bar+3*a_bar)] - (Iyy*m^2/t)*(2*a_bar + 4*c_bar) + (m*c_bar^2/3) * {8*b_bar^2*c_bar + 2*m*[2*c_bar*(c_bar-a_bar) + b_bar*(2*c_bar-3*a_bar)]} + (b_bar^2*a_bar^2/6)*[(3*c_bar+b_bar)*(4*c_bar+a_bar) - 6*c_bar^2] + m^2*a_bar^4/4 } = 490.097680 cm^6.

-. Beta_w = (-1)*[0.0833*(t*x_bar*a_bar^3) + t*x_bar^3*a_bar] = -42.8206 cm^5.

-. Beta_f = (t/2)*[(b_bar-x_bar)^4 - x_bar^4] + (t*a_bar^2/4)*[(b_bar-x_bar)^2-x_bar^2] = 42.5993 cm^5.

-. Beta_l = (2*c_bar*t)*(b_bar-x_bar)^3 + (2/3)*t*(b_bar-x_bar) * [(a_bar/2)^3 - (a_bar/2-c_bar)^3] = 65.8406 cm^5.

-. j = 1/(2*Izz)*(Beta_w + Beta_f + Beta_l) - x0 = 6.3164 cm. -. ry = SQRT( Iyy/A ) = 3.9268 cm. -. rz = SQRT( Izz/A ) = 1.9004 cm. -. r0 = SQRT[ ry^2 + rz^2 + x0^2 ] = 6.2879 cm. -. Beta = 1 - (x0/r0)^2 = 0.4813

( ). Compute moment magnification factors(Alpha_y,Alpha_z). -. This member is a tension member. -. Assumed Alpha_y = 1.00 -. Assumed Alpha_z = 1.00

( ). Given factored axial forces and moments at <J>. ---------------------------------------------------------------- Load Case Pu My Mz ---------------------------------------------------------------- DL 0.25 -3172.69 -12.37 LL 0.31 -4966.39 -22.76 DL+LL 0.55 -8139.08 -35.13 WL or EL 0.00 0.00 0.00 ---------------------------------------------------------------- DL+LL+WL(EL) 0.55 -8139.08 -35.13 ----------------------------------------------------------------

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( ). Compute magnified moments. -. Muy = (Cmy/Alpha_y)*My(DL+LL) + My(WL(EL)) = -8139.08 kgf-cm. -. Muz = (Cmz/Alpha_z)*Mz(DL+LL) + Mz(WL(EL)) = -35.13 kgf-cm.

( ). Factored max. shear forces. -. Vuy = 0.09 kgf. -. Vuz = 103.37 kgf.

====================================================================================== [[[*]]] DETERMINE ALLOWABLE CONCENTRATED LOAD (Pa).======================================================================================

( ). Check slenderness ratio of axial tension member (l/r). [ AISI-CFSD86 Specification I C4 (d) ] -. l/r = 210.5 < 300.0 ---> O.K.

( ). Calculate allowable tension force (Ta). [ AISI-CFSD86 Specification I C2 Eq.C2-1~2 ] -. Tn = An * Fy = 12412.80 kgf. -. Alpha = 0.000 -. Ta = Alpha * Tn / Omega_t = 7432.81 kgf. -. Tao = Ta = 7432.81 kgf.

( ). Check ratio of axial load (Tu/Ta). Tu 0.55 -. ---- = --------------- =7.463e-005 < 1.000 ---> O.K. Ta 7432.81

====================================================================================== [[[*]]] CHECK NOMINAL MOMENT STRENGTH ABOUT MAJOR AXIS (Mny1).======================================================================================

( ). Calculate compression flange. [ AISI-CFSD86 Specification I B4 Eq.B4-1~3, Eq.B4.1-1~11, Eq.B4.2-1~13 ] -. BTR = w/t = 15.74 < 60 ---> O.K. -. S = 1.28 * SQRT(Es / Fy) = 37.8629 -. In case of S/3 < BTR < S, n = 1/2 -. Ia = t^4*399*[(BTR/S)-0.33]^3 = 0.0007 cm^4. -. Is = c^3 * t / 12 = 0.0431 cm^4. -. D/w = 0.5525 -. In case of 0.25 < D/w < 0.8 -. k = MIN[ {4.82-5*(D/w)}*(Is/Ia)^n+0.43, 5.25-5*(D/w) ] = 2.49 -. Lambda = {1.052/SQRT(k)}*BTR*SQRT[ Fy/Es ] = 0.3549 -. In case of Lambda < 0.673 -. be = 3.620 cm. (Fully effective).

( ). Calculate compression lip. [ AISI-CFSD86 Specification I B4 Eq.B4-1~3, Eq.B4.1-1~11, Eq.B4.2-1~13 ] -. HTR = d/t = 5.70 < 60 ---> O.K. -. k = 0.43 -. Lambda = {1.052/SQRT(k)}*HTR*SQRT[ Fy/Es ] = 0.3089

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-. In case of Lambda < 0.673 -. ds = 1.310 cm. (Fully effective). -. z_cg = 5.000 cm.

( ). Calculate effective section properties about y-axis. Unit : cm. ---------------------------------------------------------------------------------- Element Effective Len. z L*z L*z^2 I'1 ---------------------------------------------------------------------------------- Compression Flange 3.620 0.115 0.416 0.0479 --- Compression Lip 1.310 1.345 1.762 2.3698 --- Compression Corners 1.806 0.324 0.585 0.1893 --- Web 8.620 5.000 43.100 215.5000 53.3753 Tension Flange 3.620 9.885 35.784 353.7219 --- Tension Lip 1.310 8.655 11.338 98.1308 0.1873 Tension Corners 1.806 9.676 17.479 169.1352 --- ---------------------------------------------------------------------------------- Sum 22.093 --- 110.464 839.0950 53.5627 ----------------------------------------------------------------------------------

( ). Check if the web is fully effective. [ AISI-CFSD86 Specification I B1.2(a), B2.3 Eq.B2.3-1~4 ] -. HTR = w/t = 37.48 < 200 ---> O.K. -. f1 = Fy * [ {z_cg-(r+t/2)} / (H-z_cg) ] = 2068.800 kgf/cm^2. -. f2 = -Fy * [ {(H-z_cg)-(r+t/2)} / (H-z_cg) ] = -2068.800 kgf/cm^2. -. Psi = f2 / f1 = -1.000 -. k = 4 + 2*(1-Psi)^3 + 2*(1-Psi) = 24.000 -. Lambda = {1.052/SQRT(k)}*HTR*SQRT[ f1/Es ] = 0.2526 -. basis = z_cg - (r+t/2) = 4.310 cm. -. be1 = be / (3 - Psi) = 2.155 cm. -. be2 = MIN[ be/2, be-be1 ] = 4.310 cm. -. In case of be1 + be2 > basis. -. be( = be1 + be2) shall be taken as basis. -. In case of Lambda < 0.673 -. be = 4.310 cm. (Fully effective).

( ). Calculate moment on the basis of initiation of yielding about major axis(Mny1). [ AISI-CFSD86 Specification I C3.1.1 Eq.C3.1.1-1 ] -. I'y = L*z2 + I'1 - L*z_cg^2 = 340.3368 cm^3. -. Iy = I'y * t = 78.2775 cm^4. -. Sey = Iy / (H - z_cg) = 15.6555 cm^3. -. Mny1 = Sey * Fy = 37573.19 kgf-cm.

====================================================================================== [[[*]]] CHECK NOMINAL LATERAL BUCKLING STRENGTH ABOUT MAJOR AXIS (Mny2).======================================================================================

( ). Calculate bending coefficient (Cb). -. Cb = 1.000 (User defined or default value)

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( ). Calculate moment on the basis of lateral buckling stress about major axis(fcy). [ AISI-CFSD86 Specification I C3.1.2 Eq.C3.1.2-1~6 ] -. Sfy = Iyy / Zbar = 15.6694 cm^3. -. My = Sfy * Fy = 37606.65 kgf-cm. -. Mey = Cb * r0 * A * SQRT[ sigma_ez*sigma_t ] = 18307.78 kgf-cm. -. Mcy = Mey = 18307.78 kgf-cm. -. fcy = Mcy / Sfy = 1168.375 kgf/cm^2.

( ). Calculate compression flange. [ AISI-CFSD86 Specification I B4 Eq.B4-1~3, Eq.B4.1-1~11, Eq.B4.2-1~13 ] -. BTR = w/t = 15.74 < 60 ---> O.K. -. S = 1.28 * SQRT(Es / fcy) = 54.2661 -. In case of BTR < S/3 -. Ia = 0.0000 cm^4. -. Is = b^3*t / 12 = 0.9092 cm^4. -. k = 4.00 -. In case of Lambda < 0.673 -. be = 3.620 cm. (Fully effective).

( ). Calculate compression lip. [ AISI-CFSD86 Specification I B4 Eq.B4-1~3, Eq.B4.1-1~11, Eq.B4.2-1~13 ] -. HTR = d/t = 5.70 < 60 ---> O.K. -. k = 0.43 -. Lambda = {1.052/SQRT(k)}*HTR*SQRT[ fcy/Es ] = 0.2155 -. In case of Lambda < 0.673 -. ds = 1.310 cm. (Fully effective). -. z_cg = 5.000 cm.

( ). Calculate effective section properties about y-axis. Unit : cm. ---------------------------------------------------------------------------------- Element Effective Len. z L*z L*z^2 I'1 ---------------------------------------------------------------------------------- Compression Flange 3.620 0.115 0.416 0.0479 --- Compression Lip 1.310 1.345 1.762 2.3698 --- Compression Corners 1.806 0.324 0.585 0.1893 --- Web 8.620 5.000 43.100 215.5000 53.3753 Tension Flange 3.620 9.885 35.784 353.7219 --- Tension Lip 1.310 8.655 11.338 98.1308 0.1873 Tension Corners 1.806 9.676 17.479 169.1352 --- ---------------------------------------------------------------------------------- Sum 22.093 --- 110.464 839.0950 53.5627 ----------------------------------------------------------------------------------

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( ). Check if the web is fully effective. [ AISI-CFSD86 Specification I B1.2(a), B2.3 Eq.B2.3-1~4 ] -. HTR = w/t = 37.48 < 200 ---> O.K. -. f1 = Fy * [ {z_cg-(r+t/2)} / (H-z_cg) ] = 2068.800 kgf/cm^2. -. f2 = -Fy * [ {(H-z_cg)-(r+t/2)} / (H-z_cg) ] = -2068.800 kgf/cm^2. -. Psi = f2 / f1 = -1.000 -. k = 4 + 2*(1-Psi)^3 + 2*(1-Psi) = 24.000 -. Lambda = {1.052/SQRT(k)}*HTR*SQRT[ f1/Es ] = 0.2526 -. basis = z_cg - (r+t/2) = 4.310 cm. -. be1 = be / (3 - Psi) = 2.155 cm. -. be2 = MIN[ be/2, be-be1 ] = 4.310 cm. -. In case of be1 + be2 > basis. -. be( = be1 + be2) shall be taken as basis. -. In case of Lambda < 0.673 -. be = 4.310 cm. (Fully effective).

( ). Calculate moment on the basis of lateral buckling strength about major axis(Mny2). [ AISI-CFSD86 Specification I C3.1.2 Eq.C3.1.2-1 ] -. I'y = L*z2 + I'1 - L*z_cg^2 = 340.3368 cm^3. -. Iy = I'y * t = 78.2775 cm^4. -. Scy = Iy / z_cg = 15.6555 cm^3. -. Mny2 = (Mcy *Scy) / Sfy = 18291.48 kgf-cm.

====================================================================================== [[[*]]] CHECK ALLOWABLE MOMENT STRENGTH ABOUT MAJOR AXIS (May).======================================================================================

( ). Check ratio of bending strength about major axis (Muy/May). [ AISI-CFSD86 Specification I C3.1 Eq.C3.1-1 ] -. Omega_f = 1.670 -. Mny1 = 37573.19 kgf-cm. -. Mny2 = 18291.48 kgf-cm. -. May = MIN[ Mny1, Mny2 ] / Omega_f = 10952.98 kgf-cm. Muy 8139.08 -. ----- = --------------- = 0.743 < 1.000 ---> O.K. May 10952.98

====================================================================================== [[[*]]] CHECK ALLOWABLE MOMENT STRENGTH ABOUT MAJOR AXIS (Mayo, Ly=0).======================================================================================

( ). Check ratio of bending strength about major axis (My/Mayo, L=0). [ AISI-CFSD86 Specification I C3.1 Eq.C3.1-1 ] -. Mnyo = Mny1 -. Mayo = Mnyo / Omega_f = 22498.91 kgf-cm. My 8139.08 -. ------ = --------------- = 0.362 < 1.000 ---> O.K. Mayo 22498.91

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====================================================================================== [[[*]]] CHECK NOMINAL MOMENT STRENGTH ABOUT MINOR AXIS (Mnz1).======================================================================================

( ). Calculate compression web. [ AISI-CFSD86 Specification I B2.1 Eq.B2.1-1~4 ] -. HTR = w/t = 37.48 < 500 ---> O.K. -. k = 4.00 -. y_cg = 1.852 cm. -. fcom = Fy * [ y_cg / (B - y_cg) ] = 1412.281 kgf/cm^2. -. Lambda = {1.052/SQRT(k)}*HTR*SQRT[ fcom/Es ] = 0.5111 -. In case of Lambda < 0.673 -. b = 8.620 cm. (Fully effective).

( ). Calculate effective section properties about z-axis. Unit : cm. ------------------------------------------------------------------------------- Element Effective Len. y L*y L*y^2 I'1 ------------------------------------------------------------------------------- Flanges 7.240 2.500 18.100 45.2500 7.9063 Left Corners 1.806 0.324 0.585 0.1893 --- Right Corners 1.806 4.676 8.447 39.5019 --- Web 8.620 0.115 0.991 0.1140 --- Lips 2.620 4.885 12.799 62.5216 --- ------------------------------------------------------------------------------- Sum 22.093 --- 40.922 147.5768 7.9063 -------------------------------------------------------------------------------

( ). Check if the flange is fully effective. [ AISI-CFSD86 Specification I B1.2(a), B2.3 Eq.B2.3-1~4 ] -. HTR = w/t = 15.74 < 200 ---> O.K. -. f1 = Fy * [ {y_cg-(r+t/2)} / (B-y_cg) ] = 886.187 kgf/cm^2. -. f2 = -Fy * [ {(B-y_cg)-(r+t/2)} / (B-y_cg) ] = -1873.905 kgf/cm^2. -. Psi = f2 / f1 = -2.115 -. k = 4 + 2*(1-Psi)^3 + 2*(1-Psi) = 70.655 -. Lambda = {1.052/SQRT(k)}*HTR*SQRT[ f1/Es ] = 0.0405 -. basis = y_cg - (r+t/2) = 1.162 cm. -. be1 = be / (3 - Psi) = 0.708 cm. -. be2 = MIN[ be/2, be-be1 ] = 1.810 cm. -. In case of be1 + be2 > basis. -. be( = be1 + be2) shall be taken as basis. -. In case of Lambda < 0.673 -. be = 1.162 cm. (Fully effective).

( ). Calculate moment on the basis of initiation of yielding about minor axis(Mnz1). [ AISI-CFSD86 Specification I C3.1.1 Eq.C3.1.1-1 ] -. I'z = L*y2 + I'1 - L*y_cg^2 = 79.6841 cm^3. -. Iz = I'z * t = 18.3273 cm^4. -. Sez = Iz / (B - y_cg) = 5.8224 cm^3. -. Mnz1 = Sez * Fy = 13973.79 kgf-cm.

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====================================================================================== [[[*]]] CHECK NOMINAL LATERAL BUCKLING STRENGTH ABOUT MINOR AXIS (Mnz2).======================================================================================

( ). Calculate moment on the basis of lateral buckling stress about minor axis(fcz). [ AISI-CFSD86 Specification I C3.1.2 Eq.C3.1.2-1~6 ] -. Cs = -1.000 (Tension). -. Sfz = Izz / Ybar = 9.9070 cm^3. -. Mz = Sfz * Fy = 23776.79 kgf-cm. -. Mez = Cs * A * sigma_ey *{j+Cs*SQRT[j^2+r0^2*(sigma_t/sigma_ey)]}/Ctfz = 10172.23 kgf-cm. -. Mcz = Mez = 10172.23 kgf-cm. -. fcz = Mcz / Sfz = 1026.773 kgf/cm^2.

( ). Calculate compression web. [ AISI-CFSD86 Specification I B2.1 Eq.B2.1-1~4 ] -. HTR = w/t = 37.48 < 500 ---> O.K. -. k = 4.00 -. y_cg = 1.852 cm. -. Lambda = {1.052/SQRT(k)}*HTR*SQRT[ fcom/Es ] = 0.4359 -. In case of Lambda < 0.673 -. b = 8.620 cm. (Fully effective).

( ). Calculate effective section properties about z-axis. Unit : cm. ------------------------------------------------------------------------------- Element Effective Len. y L*y L*y^2 I'1 ------------------------------------------------------------------------------- Flanges 7.240 2.500 18.100 45.2500 7.9063 Left Corners 1.806 0.324 0.585 0.1893 --- Right Corners 1.806 4.676 8.447 39.5019 --- Web 8.620 0.115 0.991 0.1140 --- Lips 2.620 4.885 12.799 62.5216 --- ------------------------------------------------------------------------------- Sum 22.093 --- 40.922 147.5768 7.9063 -------------------------------------------------------------------------------

( ). Check if the flange is fully effective. [ AISI-CFSD86 Specification I B1.2(a), B2.3 Eq.B2.3-1~4 ] -. HTR = w/t = 15.74 < 200 ---> O.K. -. f1 = Fy * [ {y_cg-(r+t/2)} / (B-y_cg) ] = 886.187 kgf/cm^2. -. f2 = -Fy * [ {(B-y_cg)-(r+t/2)} / (B-y_cg) ] = -1873.905 kgf/cm^2. -. Psi = f2 / f1 = -2.115 -. k = 4 + 2*(1-Psi)^3 + 2*(1-Psi) = 70.655 -. Lambda = {1.052/SQRT(k)}*HTR*SQRT[ f1/Es ] = 0.0405 -. basis = y_cg - (r+t/2) = 1.162 cm. -. be1 = be / (3 - Psi) = 0.708 cm. -. be2 = MIN[ be/2, be-be1 ] = 1.810 cm. -. In case of be1 + be2 > basis. -. be( = be1 + be2) shall be taken as basis. -. In case of Lambda < 0.673 -. be = 1.162 cm. (Fully effective).

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( ). Calculate moment on the basis of lateral buckling strength about minor axis(Mnz2). [ AISI-CFSD86 Specification I C3.1.2 Eq.C3.1.2-1 ] -. I'z = L*y2 + I'1 - L*y_cg^2 = 79.6841 cm^3. -. Iz = I'z * t = 18.3273 cm^4. -. Scz = Iz / y_cg = 9.8945 cm^3. -. Mnz2 = (Mcz * Scz) / Sfz = 10159.38 kgf-cm.

====================================================================================== [[[*]]] CHECK ALLOWABLE MOMENT STRENGTH ABOUT MINOR AXIS (Maz).======================================================================================

( ). Check ratio of bending strength about minor axis (Muz/Maz). [ AISI-CFSD86 Specification I C3.1 Eq.C3.1-1 ] -. Omega_f = 1.670 -. Mnz1 = 13973.79 kgf-cm. -. Mnz2 = 10159.38 kgf-cm. -. Maz = MIN[ Mnz1, Mnz2 ] / Omega_f = 6083.46 kgf-cm. Muz 35.13 -. ----- = --------------- = 0.006 < 1.000 ---> O.K. Maz 6083.46

====================================================================================== [[[*]]] CHECK ALLOWABLE MOMENT STRENGTH ABOUT MINOR AXIS (Mazo, Lz=0).======================================================================================

( ). Check ratio of bending strength about minor axis (Mz/Mazo, L=0). [ AISI-CFSD86 Specification I C3.1 Eq.C3.1-1 ] -. Mnzo = Mnz1 -. Mazo = Mnzo / Omega_f = 8367.54 kgf-cm. Mz 35.13 -. ------ = --------------- = 0.004 < 1.000 ---> O.K. Mazo 8367.54

====================================================================================== [[[*]]] CHECK SHEAR STRENGTH.======================================================================================

( ). Calculate shear strength in local-y direction (Vay). -. Vay = 0.4*Fy*(2*b + Pi*r + 2*c)*t = 2575.94 kgf.

( ). Check ratio of shear strength (Vuy/Vay). ( LCB = 13, POS = J ) -. Applied shear force : Vuy = 1.37 kgf. Vuy 1.37 -. ----- = --------------- =5.323e-004 < 1.000 ---> O.K. Vay 2575.94 [ Mz ]^2 [ Vuy ]^2 -. [ ---- ] + [ ----- ] =1.791e-005 < 1.000 ---> O.K. [ Mazo ] [ Vay ]

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( ). Calculate shear strength in local-z direction (Vaz). [ AISI-CFSD86 Specification I C3.2 Eq.C3.2-1~2 ] -. HTR = h/t = 37.478 -. kv = 5.340 (Default value) -. HTRa = 1.38*SQRT[ Es*kv/Fy ] = 94.331 -. Vaz1 = 0.38*t^2*SQRT[ kv*Fy*Es ] = 3297.81 kgf. -. Vaz2 = 0.4 * Fy * h * t = 1903.30 kgf. -. Vaz = MIN[ Vaz1, Vaz2 ] = 1903.30 kgf.

( ). Check ratio of shear strength (Vuz/Vaz). ( LCB = 10, POS = J ) -. Applied shear force : Vuz = 103.37 kgf. Vuz 103.37 -. ----- = --------------- = 0.054 < 1.000 ---> O.K. Vaz 1903.30 [ My ]^2 [ Vuz ]^2 -. [ ---- ] + [ ----- ] = 0.134 < 1.000 ---> O.K. [ Mayo ] [ Vaz ]

====================================================================================== [[[*]]] CHECK INTERACTION OF COMBINED AXIAL LOAD AND BENDING.======================================================================================

( ). Check interaction ratio of combined strength. [ AISI-CFSD86 Specification I C5 Eq.C5-1~3 ] -. In case of Tu/Ta < 0.15 ---> Eq.C5-3 -. ComRat = Tu/Ta + My/May + Mz/Maz =7.463e-005 + 0.743 + 0.006 = 0.749 < 1.000 ---> O.K.

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1. Design Information Design Code : AISI-CFSD86


Element No : 2112


(Fy = 2400.00, Es = 2100000)

Section Name : LC-100x50x20x2.3 (No:24)

(Rolled : LC-100x50x20x2.3).


Depth 10.0000 Thickness 0.23000Width 5.00000 Rounding 0.46000Lip Depth 2.00000

5

10

2

0.46

0.23

y

z

5.0

0

1.85


2. Member Forces Axial Force Fxx = 0.55472 (LCB: 1, POS:J)

Bending Moments My = -8139.1, Mz = -35.128

End Moments Myi = -6040.6, Myj = -8139.1 (for Lb)

Myi = -6040.6, Myj = -8139.1 (for Ly)

Mzi = -0.5644, Mzj = -35.128 (for Lz)

Shear Forces Fyy = 1.37110 (LCB: 13, POS:J)

Fzz = 103.366 (LCB: 10, POS:J)




Cmy = 1.00, Cmz = 1.00, Cb = 1.00

4. Strength Checking Results Axial Strength


Tu/Ta = 0.55/7432.81 = 0.000 < 1.000 ............................ O.K

Bending Strength

Muy/May = 8139.1/10953.0 = 0.743 < 1.000 ............................ O.K

Muz/Maz = 35.13/6083.46 = 0.006 < 1.000 ............................ O.K

Combined Strength (Tension+Bending)

Tu/Ta = 0.00 < 0.15

Rmax = Tu/Ta + My/May + Mz/Maz = 0.749 < 1.000 ......................... O.K

Shear Strength

Vuy/Vay = 0.001 < 1.000 ............................................ O.K

Vuz/Vaz = 0.134 < 1.000 ............................................ O.K

Company

Author

Project Title



Print Date/Time : 03/10/2010 00:44


pawarit

Text Box

VisStructure 03 Pile Footing


วศวกร : สมบรณ แซลม ชอฐานราก : F1

Input Data

คอนกรตหมเหลก = 6 ซม.

หนวยแรงอดในคอนกรต ............. fc = 94.50 กก./ตร.ซม.

กาลงอดของคอนกรต ................. fc' = 210 กก./ตร.ซม.

หนวยแรงของเหลกเสรมคอนกรต, fs = 1,500 กก./ตร.ซม.

กาลงคลากของเหลกเสรม ............ fy = 3,000 กก./ตร.ซม.

เสาเขมรบนาหนกปลอดภยไดตนละ = 50,000 กก.

ขนาดของเสา = 0.30 x 0.30 ม. x ม.

โมเมนตของเสารอบแกน X ........ Mx = 0 กก.-ม.

โมเมนตของเสารอบแกน Y ........ My = 0 กก.-ม.

นาหนกจากเสาตอมอ = 36,568 กก..

นาหนกดนทกดทบบนฐานราก = 389 กก.

Result

ขนาดของฐานราก (ม.) ................... = 0.60 x 0.60 x 0.60

จานวนเสาเขมทใช .......................... = 1 ตน

นาหนกของตวฐานราก .................... = 518 กก.

เสาเขมรบนาหนก ........................... = 37,475 กก.

เหลกยน 16 DB12มม.

เหลกปลอก DB12มม.

เหลกตะแกรง 2 x 2 DB12มม.

pawarit

Text Box

.05

.10

.60

.30

.30

.60

.30

.60

.30 .30

.60

.30

.30

.30

.30

DB12 มม.(เหลกปลอก)

16 DB12 มม.(เหลกยน)

2 x 2 DB12มม.(เหลกตะแกรง)

คอนกรตกนหลม

ทรายอดแนน

เสาเขมจานวน 1 ตน รบนาหนกปลอดภยไดไมนอยกวา 50,000 กโลกรม

F1

VisStructure 03 Pile Footing


วศวกร : สมบรณ แซลม ชอฐานราก : F3

Input Data

คอนกรตหมเหลก = 6 ซม.

หนวยแรงอดในคอนกรต ............. fc = 94.50 กก./ตร.ซม.

กาลงอดของคอนกรต ................. fc' = 210 กก./ตร.ซม.

หนวยแรงของเหลกเสรมคอนกรต, fs = 1,500 กก./ตร.ซม.

กาลงคลากของเหลกเสรม ............ fy = 3,000 กก./ตร.ซม.

เสาเขมรบนาหนกปลอดภยไดตนละ = 50,000 กก.

ระยะหางของศนยกลางเสาเขม = 0.90 ม.

ขนาดของเสา = 0.30 x 0.50 ม. x ม.

โมเมนตของเสารอบแกน X ........ Mx = 325 กก.-ม.

โมเมนตของเสารอบแกน Y ........ My = 185 กก.-ม.

นาหนกจากเสาตอมอ = 122,282 กก..

นาหนกดนทกดทบบนฐานราก = 1,904 กก.

Result

n / j / R ................................. = 9.3117 / 0.8768 / 15.3170

ความหนาของฐานราก ..................... = 0.60 ม.

จานวนเสาเขมทใช .......................... = 3 ตน

นาหนกของตวฐานราก .................... = 2,120 กก.

เสาเขมรบนาหนกเฉลยตนละ = 42,102 กก.

เสาเขมตนทรบนาหนกมากทสด = 42,582 กก.

เสาเขมตนทรบนาหนกนอยทสด = 41,622 กก.

ความลกประสทธผล ................... d = 51 ซม.

โมเมนตดดของฐานราก = 15,243 กก.-ม.

แรงเฉอนแบบคาน = 0 กก.

หนวยแรงเฉอนแบบคาน = 0.0000 กก./ตร.ซม.

หนวยแรงเฉอนแบบคานทยอมให = 4.2025 กก./ตร.ซม.

แรงเฉอนแบบเจาะทะล = 122,282 กก.

หนวยแรงเฉอนแบบเจาะทะล = 6.7409 กก./ตร.ซม.

หนวยแรงเฉอนแบบเจาะทะลยอมให = 7.6804 กก./ตร.ซม.

เหลกตะแกรงฐานราก 3 x 21 DB12มม.

pawarit

Text Box

......................05

.10

1.593

.60

.30

.45 .45

.50

.30

.346

.30

.26

.52

.30

1.379

.45 .45

1.246

1.593

เสรม 3 ทางๆละ 21 DB 12 มม.

เหลกรดรอบ DB 12 มม.

คอนกรตกนหลม

ทรายอดแนน

เสาเขมจานวน 3 ตน รบนาหนกปลอดภยไดไมนอยกวา 50,000 กโลกรมตอตน

F3

1. REINFORCED CONCRETE - TumCivil.com · 2010-03-25 · Load Combination List ACI 318-89 & AISC-ASD89 & AISI-CFSD86. 21.80. Structural Design Criteria. Combination (LCB) ACI 318-89

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