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Executive Summary Neuro-Cognitive Warfare: Accelerated Cultural Evolution (ACE) To Prevent Terrorism and Mass Atrocities Presented By: Dr. Robert Finkelstein President, Robotic Technology Inc...
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Page 1 of 12
17 TON PADEYE 1.0 Inputs 1.1 Padeye characteristics
R_eye R_main R_cheek th_main th_cheek a_weld H_stiff1 H_stiff2 th_stiff1 th_stff2 H_eye V V_s1 Lenth W idth1 W idth2
= = = = = = = = = = = = = = = =
15 45 0 35 0 0
50 45 45 90 0 0
mm mm mm mm mm mm mm mm mm mm mm mm mm mm mm mm
eye radius mai n pl at ate ra radi us us chee cheek k pla plate tes s rad radius ius main plate late thic thickn knes ess s chee cheek k pla plate te thic thickn kne ess weldi welding ng dimen dimensio sion n betwe between en main main & che cheek ek plat plates es stiffner 1 height stiffner 2 height stiffner 1 thickness stiffner 2 thickness height of eye dista distanc nce e betw betwee een n cent center er of of stiff stiffne ners rs dista distanc nce e eye eye-ce -cent nter er to stiff stiffne nerr 1 total total leng length th of of padey padeye e (stiff (stiffner ners s inclu included ded)) widt width h of of sti stiff ffne nerr 1 at feet feet widt width h of of sti stiff ffne nerr 2 at feet feet
1.2 Applied loads
F
=
83.4 kN
Nomi na nal appl ie ied load
a
= = =
60 deg. deg. 7.13 deg. deg. 2.00
angle angle betwe between en appl applied ied load load & Y-Z Y-Z plan plane e addi additi tion onal al slin sling g devia deviatio tion n safety coefficient applied to get design load
= = = =
28.7 95.5 8.5 42.9
pin di diameter Inside length Safe wo working lo load Sha Shackle ckle insi insid de wid width th
b S 1 . 3a 3a S h a c k l e c h a r a c t e r i s t i c s
d_pin in_length shackle_safe_load Ash
THIS CHECK IS NOT PART OF STRENGTH CHECK CALCULATIONS
1 . 3b 3b N e e d f o r c e n t r a l i z e r p l a t e s d u r i n g l i f t i n g :
Tt Ash - Tt
mm mm MT mm
= =
35.00 mm 7.90 mm
Total Total pade padeye ye thickn thickness ess (both (both main main & cheek cheek plates plates)) provid provide e centra centraliz lizer er plate plates s with with total total thickn thickness ess of of -2.1 -2.1 mm
The lifting eye is checked for a maximum static sling load of 83.4 kN together with an inclination angle of 60 deg. to Y-Z plane, and 7.13 deg. additional sling deviation x F
=
a
166.80 kN
y
This results in the following padeye loading
Hole
e y e _ H
Design load applied in the plane of padeye FDy = FD*cosa*cosb FDx = FD*sina
Main
1
Applying a safely factor of 2 gives a design load of: FD = F*S
Cheek
h
Stiffner 1 = =
82.76 kN 144.45 kN
Stiffner 2
1
Design load applied perpendicular to padeye plane
H FDz = FD*cosa*sinb+0.05*FD
=
18.69 kN
as per per API API-R -RPP-2A 2A reco recomm mmen enda dati tion ons s
Page 2 of 12
17 TON PADEYE 3.0 Check stresses at eye location
th_cheek
3.1 Check shear stress: fy = FD/As
th main As = 2*(th_main*(R_main R_eye)+(2*th_cheek)*(R_cheek - R_eye)) fv = FD*10^3/As fallowable_v = 0.4*Fy
= = =
2100.00 mm^2 79.43 Mpa 138.00 Mpa
Stress ratio: Rv = fv / fallowable_v
=
0.58 < 1 ok
z
z 3.2 Check bearing sh ear stress or radial pressu re: fp = FD/Ax
Checking in line with the Hertz Formula (Roark -Table 33-2c) Kb=2*R_eye*d_pin/(2*R_eye-d_pin) = fm=0.591*sqrt(F*E/(2*th_cheek+th_main)) = fallowable_m = 2.5*Fy = Stress ratio: m = m a owa e_m
=
3.4 Check welding betw een cheek plates & main plate:
Shear force b/w stiffner 1 and Main plate Shear force b/w stiffner 2 and Main plate
5.0 Check Shear in the Chord at Chord / Main Plate Connection T = Fdy t (Chord thickness)
= =
Tv = T/(2*H*t)<=0.4*FY
=
Stress ratio: RTV = Tv/(0.4*FY)
=
82.76 kN 31.75 mm 14.480328
0.10 < 1 ok
6.0 Checking of I-shaped section based on AISC formulae 6.1. Applied load parameters toward the checked section:
6.2.
I
=
50.00 mm
Length between the applied load section and the section checked along x-axis
d
=
0.00 mm
Length between the applied load point and the section checked COG along y-axis
Checked section geometrical parameters :
H ew
= = = = =
B ef dg 6.3.
mm mm mm mm mm
length of the section along y-axis thickness of the section parallel to y-axis length of the section along z-axis thickness of the section parallel to z-axis distance between z-axis and gusset plate axis
eye radius main plate radius cheek plates radius main plate thickness cheek plate thickness welding dimension between main & cheek plates stiffner 1 height stiffner 2 height stiffner 1 thickness stiffner 2 thickness height of eye distance between center of stiffners distance eye-center to stiffner 1 total length of padeye (stiffners included) width of stiffner 1 at feet width of stiffner 2 at feet
F
=
1433.11 kN
a
= = =
63.38 deg. 0 deg. 2.00
angle between applied load & Y-Z plane additional sling deviation safety coefficient applied to get design load
= = = =
133.4 666.8 300 185
pin diameter Inside length Safe working load Shackle inside width
1.2 Applied loads
b S
Nominal applied load
1.3a Shackle characteristics d_pin in_length shackle_safe_load Ash 1.3b Need for centralizer plates during lifting : Tt Ash - Tt
mm mm MT mm
THIS CHECK IS NOT PART OF STRENGTH CHECK CALCULATIONS = =
130.00 mm 55.00 mm
Total padeye thickness (both main & cheek plates) provide centralizer plates with total thickness of 45
1.4 Material characteristics Fy E
= =
412.00 Mpa yield strength 20000.00 Kn/sqcm Young elastic modulus
2.0 Design load
The lifting eye is checked for a maximum static sling load of 1433.11 kN together with an inclination angle of 63.38 deg. to Y-Z plane, and 0 de g. additional sling deviation Applying a safely factor of 2 gives a design load of: FD = F*S
=
2866.22 kN design load
= =
1284.27 kN 2562.39 kN
=
143.31 kN
This results in t he following padeye loading Design load applied in the plane of padeye FDy = FD*cosa*cosb FDx = FD*sina Design load applied perpendicular to padeye plane FDz = FD*cosa*sinb+0.05*FD
3.3 Check Hertz pressure: fm Checking in line with the Hertz Formula (Roark -Table 33-2c) Kb=2*R_eye*d_pin/(2*R_eye-d_pin) = fm=0.591*sqrt(F*E/(2*th_cheek+th_main)) = fallowable_m = 2.5*Fy =
4002.00 mm 438.66 Mpa 1030.00 Mpa
Stress ratio: m = m a owa e_m
=
3.4 Check welding between cheek plates & main plate:
5. Loading : N = FD My = -FDz*I Mz = -FDy*I - FDx*d Ty = FDy Tz = FDz
kN kN.mm kN.mm kN kN
length of the section along y-axis thickness of the section parallel to y-axis length of the section along z-axis thickness of the section parallel to z-axis distance between z-axis and gusset plate axis
Page 8 of 12 6. Resulting stresses : Normal stress Bending stresses
Shear stresses
f a:
=
59.71 N/mm^2
f by1= f by2= f by3= f by4= f bz1= f bz2= f bz3= f bz4=
