683APPENDIX B Properties of Rolled-Steel Shapes(SI Units)Continued from page 681w ShapesWide Flange Shapes)FlangeWebThick-Axis X-XAxis YYThick-AreaDepthWidhS.nessnessto, mm 10° mm 10 mm mm 1o mm 10 mm mmDesignationt A, mm d, mm b, mm s mmW310 x 1431820013600942032331022914.0347215013811272878.51077431231030520517.016.313.110.99.402481631600105013581.223.453177.249.8132605275503023182031677.497.6212884413013318.410.218040.339.1665013.211974712244.556703121661126.6099.154.96331321318.4510287.537.938.638.749403101659.655.845477.2038.4327418031210210.86.6064.94161251.9421.521830403051016.735.5042.92501191.1723.1196waso x 16731.5192206012402120020026426425729616411811396.255.874243368.165.81011290019.611.9501020025725415.69.412695342.933865.06725720415.78.8910357.011022.221851.158742025220313.5S.0010618.718550.320049.1 626044.8570024726711.013.07.3771.270.857410615.26.9515194.249.334.81487.6253132728.4419036302502591461029.1410.06.106.3540.140.13503091061054.751.7965.135.133.822.220.62232541026.965.8428.7226100w200 x 8622220920.613.085292731.353.311000910094.93007121620617.410276.670591.725.324652.85975302102051429.1460.858289.720.420051.85246.16650206203204203126I107.877.2452.945.851145189217.715.417451.6513589015241.72051661187.2440.839587.69.0310041.13594570397020116510.210.26.2234.434266.97.624.0792.340.932.031.32102951341336.3531.388.660.S26.633902078.385.8425.824987.13.3249.631.22252500206102S.006.4862220.01938361.4227.922.319.324802031025.8416.5162S151.1421.4W150 x 37.17.125544740162154116S.1322.227468.691.938.629.8243790306092710.372336.138.124.61571536.6017.213.423016767.61601026.6066.01.841822901531027.115.849.201206321.2424.623.313517301501005.464.326.8391.162.70.91618.223.0W130 x 28.139013112810.96.8610.916755.13.6058.532.523830401271279.146.108.9114054.13.1349.232.0W100 x 19.324701061038.767.114.7089.543.71.6131.125.4la wide-flange shape ts destgnanod by the leer W folkwed by the nommal depeh tn llmosers and the mass in kakgrams per meter.HE Figure 1 ilustrates a cross-section af an aircraft fuselage. The floor beam of the aircraft issupported by the fuselage at its both ends. The floor beam has an I-shaped cross-sectionand is subjected to 1.2 kNim uniformly distributed load at ts center. It is assumed that thefuselage only exerts vertical reactions on the ends of the beam and El is constant1.2 kNim-24 mFigure 1: Cross-section of an aircraft fuselage.(a) Construct a free body diagram (FBD) of the floor beam, with al necessary labes.(b) Determine the support reactions at A and D.(c) Construct shear force and bending moment diagrams for the floor beam.(d) Derive equation of beam defiection under the uniformly distributed load, in terms of E,1, and distance x.(e) Determine the maximum deflection of the floor beam in terms of E and I.() if the floor beam is made of rolled-steel w250-58 with Young's modulus of 200 GPa,calculate the maximum deflection of the floor beam to the nearest mm.

Answered: Image /qna-images/answer/c66bbcf5-31be-4f8c-bea8-b2ef94661d31.jpg

Figure 1 ilustrates a cross-section of an aircraft fuselage. The floor beam of the aircraft is supported by the fuselage at its both ends. The floor beam has an I-shaped cross-section and is subjected to 1.2 kNim uniformly distributed load at ts center. It is assumed that the fuselage only exerts vertical reactions on the ends of the beam and El is constant 1.2 kNim -2.4 m- 0.6 m Figure 1: Cross-section of an alrcraft fuselage. (a) Construct a free body diagram (FBD) of the floor beam, with al necessary labels. (b) Determine the support reactions at A and D. (c) Construct shear force and bending moment diagrams for the floor beam. (d) Derive equation aof beam defiection under the uniformly distributed load, in terms of E. 1, and distance x. (e) Determine the maximum deflection af the floor beam in terms of E and 1. ( # the floor beam is made of roled-steel w250-58 with Young's modulus of 200 GPa, caloulate the maximum deflection of the floor beam to the nearest mm.

Figure 1 ilustrates a cross-section of an aircraft fuselage. The floor beam of the aircraft is supported by the fuselage at its both ends. The floor beam has an I-shaped cross-section and is subjected to 1.2 kNim uniformly distributed load at ts center. It is assumed that the fuselage only exerts vertical reactions on the ends of the beam and El is constant 1.2 kNim -2.4 m- 0.6 m Figure 1: Cross-section of an alrcraft fuselage. (a) Construct a free body diagram (FBD) of the floor beam, with al necessary labels. (b) Determine the support reactions at A and D. (c) Construct shear force and bending moment diagrams for the floor beam. (d) Derive equation aof beam defiection under the uniformly distributed load, in terms of E. 1, and distance x. (e) Determine the maximum deflection af the floor beam in terms of E and 1. ( # the floor beam is made of roled-steel w250-58 with Young's modulus of 200 GPa, caloulate the maximum deflection of the floor beam to the nearest mm.

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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Concept explainers

Buckling of columns

The column is described as a vertical member of the structure that carries an axial compressive load, and buckling is a lateral deformation of the column under the application of load.

Question

683
APPENDIX B Properties of Rolled-Steel Shapes
(SI Units)
Continued from page 681
w Shapes
Wide Flange Shapes)
Flange
Web
Thick-
Axis X-X
Axis YY
Thick-
Area
Depth
Widh
S.
ness
ness
to, mm 10° mm 10 mm mm 1o mm 10 mm mm
Designationt A, mm d, mm b, mm s mm
W310 x 143
18200
13600
9420
323
310
229
14.0
347
2150
138
112
728
78.5
107
74
312
310
305
205
17.0
16.3
13.1
10.9
9.40
248
163
1600
1050
135
81.2
23.4
531
77.2
49.8
132
60
52
7550
302
318
203
167
7.49
7.62
128
844
130
133
18.4
10.2
180
40.3
39.1
6650
13.2
119
747
122
44.5
5670
312
166
112
6.60
99.1
54.9
633
132
131
8.45
102
87.5
37.9
38.6
38.7
4940
310
165
9.65
5.84
547
7.20
38.4
327
4180
312
102
10.8
6.60
64.9
416
125
1.94
21.5
218
3040
305
101
6.73
5.50
42.9
250
119
1.17
23.1
196
waso x 167
31.5
192
2060
1240
21200
200
264
264
257
296
164
118
113
96.2
55.8
742
433
68.1
65.8
101
12900
19.6
11.9
50
10200
257
254
15.6
9.4
126
953
42.9
338
65.0
67
257
204
15.7
8.89
103
57.0
110
22.2
218
51.1
58
7420
252
203
13.5
S.00
106
18.7
185
50.3
200
49.1 6260
44.8
5700
247
267
11.0
13.0
7.37
71.2
70.8
574
106
15.2
6.95
151
94.2
49.3
34.8
148
7.62
531
327
28.4
4190
3630
250
259
146
102
9.14
10.0
6.10
6.35
40.1
40.1
350
309
106
105
4.75
1.79
65.1
35.1
33.8
22.2
20.6
223
254
102
6.96
5.84
28.7
226
100
w200 x 86
222
209
20.6
13.0
852
927
31.3
53.3
11000
9100
94.9
300
71
216
206
17.4
102
76.6
705
91.7
25.3
246
52.8
59
7530
210
205
142
9.14
60.8
582
89.7
20.4
200
51.8
52
46.1
6650
206
203
204
203
126
I10
7.87
7.24
52.9
45.8
511
451
892
17.7
15.4
174
51.6
513
5890
152
41.7
205
166
118
7.24
40.8
395
87.6
9.03
100
41.1
359
4570
3970
201
165
10.2
10.2
6.22
34.4
342
66.9
7.62
4.07
92.3
40.9
32.0
31.3
210
295
134
133
6.35
31.3
88.6
60.S
26.6
3390
207
8.38
5.84
25.8
249
87.1
3.32
49.6
31.2
225
2500
206
102
S.00
6.48
622
20.0
193
836
1.42
27.9
22.3
19.3
2480
203
102
5.84
16.5
162
S15
1.14
21.4
W150 x 37.1
7.12
554
4740
162
154
116
S.13
22.2
274
68.6
91.9
38.6
29.8
24
3790
3060
927
10.3
723
36.1
38.1
24.6
157
153
6.60
17.2
13.4
230
167
67.6
160
102
6.60
66.0
1.84
18
2290
153
102
7.11
5.84
9.20
120
632
1.24
24.6
23.3
135
1730
150
100
5.46
4.32
6.83
91.1
62.7
0.916
18.2
23.0
W130 x 28.1
390
131
128
10.9
6.86
10.9
167
55.1
3.60
58.5
32.5
238
3040
127
127
9.14
6.10
8.91
140
54.1
3.13
49.2
32.0
W100 x 19.3
2470
106
103
8.76
7.11
4.70
89.5
43.7
1.61
31.1
25.4
la wide-flange shape ts destgnanod by the leer W folkwed by the nommal depeh tn llmosers and the mass in kakgrams per meter.
HE

Figure 1 ilustrates a cross-section af an aircraft fuselage. The floor beam of the aircraft is
supported by the fuselage at its both ends. The floor beam has an I-shaped cross-section
and is subjected to 1.2 kNim uniformly distributed load at ts center. It is assumed that the
fuselage only exerts vertical reactions on the ends of the beam and El is constant
1.2 kNim
-24 m
Figure 1: Cross-section of an aircraft fuselage.
(a) Construct a free body diagram (FBD) of the floor beam, with al necessary labes.
(b) Determine the support reactions at A and D.
(c) Construct shear force and bending moment diagrams for the floor beam.
(d) Derive equation of beam defiection under the uniformly distributed load, in terms of E,
1, and distance x.
(e) Determine the maximum deflection of the floor beam in terms of E and I.
() if the floor beam is made of rolled-steel w250-58 with Young's modulus of 200 GPa,
calculate the maximum deflection of the floor beam to the nearest mm.

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