ACI COLUMNAS CUADRADAS

DISEÑO DE COLUMNAS COLUMNA DATOS DE ENTRADA

E-3

CARGA AXIAL kg P

MOMENTO 2-2 kg*m M2-2

110572

1730.5


1904.36

FRAME

10

f'c = fy = r =

210 4200 4

kg/cm2 kg/cm2 cm

∅=

0.7

DISEÑO A COMPRESION DATOS Ag = b*h

b= h= Ag = Pumax = 0.8 * ∅ * [ As*fy + 0.85*f'c*(Ag-As) ]

As = Verificar : ρ = As/(b*h) Si 0.01 ≤ ρ ≤ 0.08 → OK, cumple! As = ρ * b * t = Acero Longitudinal DISEÑO A PANDEO CALCULO DE Kx ψb = ψa = ψmin =

35 35 1225

-5.27 ρ=

0

12.25 4Ø20 (M1/M2) x = lu = rx =

-0.36 340 10.1

Kx=

0.82

→

OK

(M1/M2)y= lu = ry =

0.27 340 10.1

Ky =

0.78

26.23 ≤ 30.72

→

OK

b= t=

35 35

1 1.44 1

k x=0 . 70 . 05 ∗

ψ

a

ψ

b

k x=0 . 85 0 . 05 ∗ψ min



Si Kx * lu / rx ≤ 34 -12(M1/M2) → OK!

27.66 ≤ 38.28

CALCULO DE K_y ψb = ψa = ψmin =

1 0.59 0.59

k y =0 . 70 . 05 ∗

ψ ψ a

y

b



k a lig n l

¿ ¿¿ = 0 . 8 5 0 . 0 5 ∗ψ m in

Si Ky * lu / ry ≤ 34 -12(M1/M2) → OK!

¿

DISEÑO FLEXION COMPUESTA DATOS Muy = Mux = β= Acero Longitudinal

1730.5 1904.36 0.65 4Ø20 M ox = M uy

 

 

b 1− β M oy = M ux α⋅ ⋅  M uy t β

1 t 1− β ⋅ ⋅  M ux α b β

Si Mux ≥ Muy Mox = 2836.17 PARAMETROS DE DISEÑO PARA LA TABLA 8 Pu 0.48 = Φf ' c bt

Mu Φf ' c bt 2

0

=

t− 2rdlong  = t

0.71

Si 0.01 ≤ ρ ≤ 0.08 → OK, cumple! As = ρ * b * t = Acero Longitudinal DISEÑO ESTRIBOS

12.25 4Ø20

g=

Si Muy > Mux Mox > Mux

}

ρ= ρ=

→

OK

∅=

0.9

q=

0.08

q∗ f ' c = fy

0 0

Øestribo = 8 mm Separcion estribos s <

{

16Ølong 48Øestribo b

32 38.4 35

35

4Ø20

35

→ Estribos Ø8 cada 30

→ Tomar el menor s<

eØ8c/30

32


D-3

CARGA AXIAL kg P


150148.8

245.03


1136.38

FRAME

9

f'c = fy = r =

210 4200 4

kg/cm2 kg/cm2 cm

∅=

0.7




40 40 1600

-4.35 ρ=

0

16 4Ø20 (M1/M2) x = lu = rx =

-0.36 340 11.55

Kx=

0.82

→

OK

(M1/M2)y= lu = ry =

-0.12 340 11.55

Ky =

0.78

22.95 ≤ 35.44

→

OK

b= t=

40 40

1 1.44 1

k x=0 . 70 . 05 ∗

ψ

a

ψ

b

k x=0 . 85 0 . 05 ∗ψ min



Si Kx * lu / rx ≤ 34 -12(M1/M2) → OK!

24.2 ≤ 38.26


1 0.59 0.59

k y =0 . 70 . 05 ∗

ψ ψ a

y

b



k a lig n l

¿ ¿¿ = 0 . 8 5 0 . 0 5 ∗ψ m in

Si Ky * lu / ry ≤ 34 -12(M1/M2) → OK!

¿


245.03 1136.38 0.65 4Ø20 M ox = M uy

 

 


1 t 1− β ⋅ ⋅  M ux α b β


Mu Φf ' c bt 2

0

=


0.75


16 4Ø20

g=


}

ρ= ρ=

→

OK

∅=

0.9

q=

0.08

q∗ f ' c = fy

0 0


{


32 38.4 40

40

4Ø20

40



eØ8c/30

32


C-3

CARGA AXIAL kg P


181949.4

271.88


157.47

FRAME

8

f'c = fy = r =

210 4200 4

kg/cm2 kg/cm2 cm

∅=

0.7



As = Verificar : ρ = As/(b*h) Si 0.01 ≤ ρ ≤ 0.08 → OK, cumple! As = ρ * b * t = Acero Longitudinal DISEÑO A PANDEO CALCULO DE Kx

40 40 1600

9.77 ρ=

0.01

16 4Ø20

ψb = ψa = ψmin =

(M1/M2) x = lu = rx =

-0.95 340 11.55

Kx=

0.83

→

OK

(M1/M2)y= lu = ry =

-0.99 340 11.55

Ky =

0.8

23.56 ≤ 45.91

→

OK

b= t=

40 40

1 1.7 1

k x=0 . 70 . 05 ∗

ψ

a

ψ

b

k x=0 . 85 0 . 05 ∗ψ min



Si Kx * lu / rx ≤ 34 -12(M1/M2) → OK!

24.58 ≤ 45.38


1 1 1

k y =0 . 70 . 05 ∗

ψ ψ a

y

b



k a lig n l

¿ ¿¿ = 0 . 8 5 0 . 0 5 ∗ψ m in

Si Ky * lu / ry ≤ 34 -12(M1/M2) → OK!

¿


271.88 157.47 0.65 4Ø20 M ox = M uy

 

 


1 t 1− β ⋅ ⋅  M ux α b β

Si Mux ≥ Muy Moy = 356.67 PARAMETROS DE DISEÑO PARA LA TABLA 8 Pu 0.6 = Φf ' c bt

Mu Φf ' c bt 2

0

=


0.75


16 4Ø20

g=

Si Muy > Mux Moy > Muy

}

ρ= ρ=

→

OK

∅=

0.9

q=

0.08

q∗ f ' c = fy

0 0


{


32 38.4 40

40

4Ø20

40



eØ8c/30

32


A-3

CARGA AXIAL kg P


128914.3

339.1


1268.01

FRAME

7

f'c = fy = r =

210 4200 4

kg/cm2 kg/cm2 cm

∅=

0.7




35 35 1225

2.87 ρ=

0

12.25 4Ø20 (M1/M2) x = lu = rx =

-0.77 340 10.1

Kx=

0.85

→

OK

(M1/M2)y= lu = ry =

-0.98 340 10.1

Ky =

0.78

26.23 ≤ 45.78

→

OK

b= t=

35 35

1 2.06 1

k x=0 . 70 . 05 ∗

ψ

a

ψ

b

k x=0 . 85 0 . 05 ∗ψ min



Si Kx * lu / rx ≤ 34 -12(M1/M2) → OK!

28.7 ≤ 43.24


1 0.59 0.59

k y =0 . 70 . 05 ∗

ψ ψ a

y

b



k a lig n l

¿ ¿¿ = 0 . 8 5 0 . 0 5 ∗ψ m in

Si Ky * lu / ry ≤ 34 -12(M1/M2) → OK!

¿


339.1 1268.01 0.65 4Ø20 M ox = M uy

 

 


1 t 1− β ⋅ ⋅  M ux α b β


Mu Φf ' c bt 2

0

=


0.71


12.25 4Ø20

g=


}

ρ= ρ=

→

OK

∅=

0.9

q=

0.08

q∗ f ' c = fy

0 0


{


32 38.4 35

35

4Ø20

35



eØ8c/30

32


E-2

CARGA AXIAL kg P


86265.6

1007.41


2768.95

FRAME

6

f'c = fy = r =

210 4200 4

kg/cm2 kg/cm2 cm

∅=

0.7




35 35 1225

-16.07 ρ=

-0.01

12.25 4Ø20 (M1/M2) x = lu = rx =

-0.14 340 10.1

Kx=

0.82

→

OK

(M1/M2)y= lu = ry =

0.77 340 10.1

Ky =

0.86

28.93 ≤ 24.81

→

ERROR

b= t=

35 35

1 1.44 1

k x=0 . 70 . 05 ∗

ψ

a

ψ

b

k x=0 . 85 0 . 05 ∗ψ min



Si Kx * lu / rx ≤ 34 -12(M1/M2) → OK!

27.66 ≤ 35.71


1 2.19 1

k y =0 . 70 . 05 ∗

ψ ψ a

y

b



k a lig n l

¿ ¿¿ = 0 . 8 5 0 . 0 5 ∗ψ m in

Si Ky * lu / ry ≤ 34 -12(M1/M2) → OK!

¿


1007.41 2768.95 0.65 4Ø20 M ox = M uy

 

 


1 t 1− β ⋅ ⋅  M ux α b β


Mu Φf ' c bt 2

0

=


0.71


12.25 4Ø20

g=


}

ρ= ρ=

→

OK

∅=

0.9

q=

0.08

q∗ f ' c = fy

0 0


{


32 38.4 35

35

4Ø20

35



eØ8c/30

32


D-2

CARGA AXIAL kg P


173338.3

1275.9


941.99

FRAME

5

f'c = fy = r =

210 4200 4

kg/cm2 kg/cm2 cm

∅=

0.7




40 40 1600

5.95 ρ=

0

16 4Ø20

ψb = ψa = ψmin =

(M1/M2) x = lu = rx =

-0.28 340 11.55

Kx=

0.82

→

OK

(M1/M2)y= lu = ry =

-0.34 340 11.55

Ky =

0.86

25.31 ≤ 38.11

→

OK

b= t=

40 40

1 1.4 1

k x=0 . 70 . 05 ∗

ψ

a

ψ

b

k x=0 . 85 0 . 05 ∗ψ min



Si Kx * lu / rx ≤ 34 -12(M1/M2) → OK!

24.15 ≤ 37.3


1 2.19 1

k y =0 . 70 . 05 ∗

ψ ψ a

y

b



k a lig n l

¿ ¿¿ = 0 . 8 5 0 . 0 5 ∗ψ m in

Si Ky * lu / ry ≤ 34 -12(M1/M2) → OK!

¿


1275.9 941.99 0.65 4Ø20 M ox = M uy

 

 


1 t 1− β ⋅ ⋅  M ux α b β


Mu Φf ' c bt 2

0

=


0.75


16 4Ø20

g=


}

ρ= ρ=

→

OK

∅=

0.9

q=

0.08

q∗ f ' c = fy

0 0


{


32 38.4 40

40

4Ø20

40



eØ8c/30

32


C-2

CARGA AXIAL kg P


207639.6

717.61


297.16

FRAME

4

f'c = fy = r =

210 4200 4

kg/cm2 kg/cm2 cm

∅=

0.7




40 40 1600

21.18 ρ=

0.01

21.18 4Ø20

ψb = ψa = ψmin =

(M1/M2) x = lu = rx =

-0.49 340 11.55

Kx=

0.83

→

OK

(M1/M2)y= lu = ry =

-0.31 340 11.55

Ky =

0.86

25.31 ≤ 37.66

→

OK

b= t=

40 40

1 1.7 1

k x=0 . 70 . 05 ∗

ψ

a

ψ

b

k x=0 . 85 0 . 05 ∗ψ min



Si Kx * lu / rx ≤ 34 -12(M1/M2) → OK!

24.58 ≤ 39.86


1 2.19 1

k y =0 . 70 . 05 ∗

ψ ψ a

y

b



k a lig n l

¿ ¿¿ = 0 . 8 5 0 . 0 5 ∗ψ m in

Si Ky * lu / ry ≤ 34 -12(M1/M2) → OK!

¿


717.61 297.16 0.65 4Ø20 M ox = M uy

 

 


1 t 1− β ⋅ ⋅  M ux α b β


Mu Φf ' c bt 2

0

=


0.75


16 4Ø20

g=


}

ρ= ρ=

→

OK

∅=

0.9

q=

0.08

q∗ f ' c = fy

0 0


{


32 38.4 40

40

4Ø20

40



eØ8c/30

32


A-2

CARGA AXIAL kg P


140886

359.59


1788.34

FRAME

3

f'c = fy = r =

210 4200 4

kg/cm2 kg/cm2 cm

∅=

0.7




35 35 1225

8.19 ρ=

0.01

12.25 4Ø20 (M1/M2) x = lu = rx =

-0.76 340 10.1

Kx=

0.85

→

OK

(M1/M2)y= lu = ry =

-0.12 340 10.1

Ky =

0.81

27.4 ≤ 35.49

→

OK

b= t=

35 35

1 2.06 1

k x=0 . 70 . 05 ∗

ψ

a

ψ

b

k x=0 . 85 0 . 05 ∗ψ min



Si Kx * lu / rx ≤ 34 -12(M1/M2) → OK!

28.7 ≤ 43.1


1 1.29 1

k y =0 . 70 . 05 ∗

ψ ψ a

y

b



k a lig n l

¿ ¿¿ = 0 . 8 5 0 . 0 5 ∗ψ m in

Si Ky * lu / ry ≤ 34 -12(M1/M2) → OK!

¿


359.59 1788.34 0.65 4Ø20 M ox = M uy

 

 


1 t 1− β ⋅ ⋅  M ux α b β


Mu Φf ' c bt 2

0

=


0.71


12.25 4Ø20

g=


}

ρ= ρ=

→

OK

∅=

0.9

q=

0.08

q∗ f ' c = fy

0 0


{


32 38.4 35

35

4Ø20

35



eØ8c/30

32


D-1

CARGA AXIAL kg P


49741.2

603.4


2064.04

FRAME

2

f'c = fy = r =

210 4200 4

kg/cm2 kg/cm2 cm

∅=

0.7




35 35 1225

-32.29 ρ=

-0.03

12.25 4Ø20 (M1/M2) x = lu = rx =

0.28 340 10.1

Kx=

0.9

→

OK

(M1/M2)y= lu = ry =

0.22 340 10.1

Ky =

0.86

28.87 ≤ 31.35

→

OK

b= t=

35 35

1 3.03 1

k x=0 . 70 . 05 ∗

ψ

a

ψ

b

k x=0 . 85 0 . 05 ∗ψ min



Si Kx * lu / rx ≤ 34 -12(M1/M2) → OK!

30.29 ≤ 30.59


1 2.16 1

k y =0 . 70 . 05 ∗

ψ ψ a

y

b



k a lig n l

¿ ¿¿ = 0 . 8 5 0 . 0 5 ∗ψ m in

Si Ky * lu / ry ≤ 34 -12(M1/M2) → OK!

¿


603.4 2064.04 0.65 4Ø20 M ox = M uy

 

 


1 t 1− β ⋅ ⋅  M ux α b β


Mu Φf ' c bt 2

0

=


0.71


12.25 4Ø20

g=


}

ρ= ρ=

→

OK

∅=

0.9

q=

0.08

q∗ f ' c = fy

0 0


{


32 38.4 35

35

4Ø20

35



eØ8c/30

32


B-1

CARGA AXIAL kg P


148211.7

958.75


2103.76

FRAME

1

f'c = fy = r =

210 4200 4

kg/cm2 kg/cm2 cm

∅=

0.7




35 35 1225

11.44 ρ=

0.01

12.25 4Ø20 (M1/M2) x = lu = rx =

0.38 340 10.1

Kx=

0.78

→

OK

(M1/M2)y= lu = ry =

-0.9 340 10.1

Ky =

0.86

28.87 ≤ 44.76

→

OK

b= t=

35 35

1 0.51 0.51

k x=0 . 70 . 05 ∗

ψ

a

ψ

b

k x=0 . 85 0 . 05 ∗ψ min



Si Kx * lu / rx ≤ 34 -12(M1/M2) → OK!

26.1 ≤ 29.41


1 2.16 1

k y =0 . 70 . 05 ∗

ψ ψ a

y

b



k a lig n l

¿ ¿¿ = 0 . 8 5 0 . 0 5 ∗ψ m in

Si Ky * lu / ry ≤ 34 -12(M1/M2) → OK!

¿


958.75 2103.76 0.65 4Ø20 M ox = M uy

 

 


1 t 1− β ⋅ ⋅  M ux α b β


Mu Φf ' c bt 2

0

=


0.71


12.25 4Ø20

g=


}

ρ= ρ=

→

OK

∅=

0.9

q=

0.08

q∗ f ' c = fy

0 0


{


32 38.4 35

35

4Ø20

35



eØ8c/30

32


2-A

CARGA AXIAL kg P


10 DISEÑO A COMPRESION DATOS

47


454

Ag = b*h



ψ

a

ψ

b

ρ=

a

∅=

0.7

(M1/M2) x = lu = rx =

0.79 280 10.1

Kx=

0.83

→

OK

(M1/M2)y= lu = ry =

-0.86 280 10.1

Ky =

0.79

21.84 ≤ 44.32

→

OK

b= t=

35 35

k x=0 . 85 0 . 05 ∗ψ min



22.9 ≤ 24.48

y

b

kg/cm2 kg/cm2 cm

-0.04

1 0.76 0.76

ψ ψ

210 5000 4

12.25 4Ø20

CALCULO DE K_y

k y =0 . 70 . 05 ∗

f'c = fy = r =

-45.35

Si Kx * lu / rx ≤ 34 -12(M1/M2) → OK! ψb = ψa = ψmin =

162

35 35 1225

1 1.53 1

k x=0 . 70 . 05 ∗

FRAME



k a lig n l

¿ ¿¿ = 0 . 8 5 0 . 0 5 ∗ψ m in

Si Ky * lu / ry ≤ 34 -12(M1/M2) → OK!

¿


47 454 0.65 4Ø20 M ox = M uy

 

 


1 t 1− β ⋅ ⋅  M ux α b β

Si Mux ≥ Muy Mox = 479.31 PARAMETROS DE DISEÑO PARA LA TABLA 8 Pu 0 = Φf ' c bt

Mu Φf ' c bt 2

0

=


0.71


12.25 4Ø20

g=


}

ρ= ρ=

→

OK

∅=

0.9

q=

0.08

q∗ f ' c = fy

0 0


{


32 38.4 35

35

4Ø20

35



eØ8c/30

32

Tabla de Phi/As

100000 100000 0.28 7.38 19.92

12 16 20 25 32

4.52 8.04 12.53 19.63 32.17

-7.73 -4.21 0.28 7.38 19.92

100000 100000 0.28 7.38 19.92

0.28

0.28

20

20

12 16 20 25 32

-7.73 -4.21 0.28 7.38 19.92

ACI COLUMNAS CUADRADAS

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