Aircraft Structures 3E Episode 9 pptx

... carrying area. 9. 9.1 Bending of open and closed section beams The analysis presented in Section 9. 1 applies and the direct stress distribution is given by any of Eqs (9. 6), (9. 7) or (9. 9), depending ... in Sections 9. 5 and 9. 6 apply. 9. 9.5 Alternative method for the calculation of shear flow distribution Equation (9. 73) may be rewritten in the form apr q2-41 =-&a...

Ngày tải lên: 13/08/2014, 16:21

... 1 26 19. 0 0 0.0417 0 1 09. 2 2621.3 400 90 0 43680 2 392 8.6 0.0833 0.0417 327.3 163.8 394 5.6 0 90 - 294 57 0 3 26 19. 0 0.1250 0.0417 327.4 1 09. 2 2641.6 200 90 - 294 66 21840 4 -26 19. 0 0.1250 ... -327.4 1 09. 2 -2641.6 200 90 - 294 66 21840 5 - 392 8.6 0.0833 -0.0417 -327.3 163.8 - 394 5.6 0 90 - 294 57 0 6 -26 19. 0 0 -0.0417 0 1 09. 2 -2621.3 400 90 0 -4368...

Ngày tải lên: 13/08/2014, 16:21

... 1084 1.220 1 2L 2160 1.625 14,23 127 0 .91 5 34u 797 0 .91 5 34L 797 0 .91 5 I 108400 I1 202 500 I11 528 000 Ans. qI2u = 25.4N/mm, = 33.5N/mm, 91 4 = q32 = 8.1N/mm, q43u = 13.4N/m~i, ... 1525 356 406 356 254 Thickness (mm) 0 .91 5 0 .91 5 0 .91 5 0.711 1.220 1.625 1.220 0 .91 5 Cell areas (mm') AI = 161 500, A11 = 291 000 AI11 291 000, Alv =...

Ngày tải lên: 13/08/2014, 16:21

... various types of manoeuvre 9 Bending, shear and torsion of open and closed, thin-walled beams 9. 1 9. 2 9. 3 9. 4 9. 5 9. 6 9. 7 9. 8 Structural idealization 9. 9 9. 10 Deflection of open and ... Broddle of British Aerospace for supplying photographs and drawings of aircraft structures. T.H.G. Megson 198 9 Aircraft Structures for engineering students viii Conte...

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... = 10- + \/(360 + 290 )2 + 6502 which gives &I = 495 x Similarly, from Eq. (1.36) EII = -425 x IOp6 From Eq. (1.37) 650 x 360 x lop6 + 290 x lop6 = tan20 = ... E = 31 000N/mm2, v = 0.2 Ans. T = 3.17N/mm2, Q = 95 .1 kN 1.16 Experimental measurement of surface strains 29 Fig. 1.1 5 Strain gauge rosette. the form of a rosette,...

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... (N) 64 000R /9 -700 3 OOOR -525 64 000R /9 -700 3 OOOR -525 AB 4000 4R/3 413 CD 4000 4R/3 413 BC 3000 R 1 DA 3000 R 1 AC 5000 -5R/3 -513 125 000R /9 875 DB 5000 ... interest in aircraft structures is the calculation of the deflections produced by the large shear stresses experienced by thin-walled sections. This problem is discussed in Chapter 9....

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... Blackie, London, 195 9. 2 Gregory, M. S., Introduction to Extremum Principles, Buttenvorths, London, 196 9. 3 Megson, T. H. G., Structural and Stress Analysis, Arnold, London, 199 6. 5.4 Combined ... of Structures, John Wiley and Sons, Inc., New York, 195 6. Timoshenko, S. P. and Gere, J. M., Theory of Elastic Stability, McGraw-Hill Book Company, 196 0. Ne...

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... V) ~~~~7r~ 4ab (a + b2)’ - qo- - 0 9- =- aAll 4a3b3 and 1 6qoa4b4 7r6D(a2 + b2)’ All = 6.6 Buckling of thin plates 1 69 from which 42 EI EI PCR = - = 2.471 ... 7 (6.68) (6. 69) Consider now a thin-walled column having the cross-section shown in Fig. 6.21 and suppose that the centroidal axes Cxy are principal axes (see Section 9. 1); S(xs,yS) ......

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... 3781, 195 7. Rivello, R. M., Theory and Analysis of Flight Structures, McGraw-Hill Book Company, New York, 196 9. Stowell, E. Z., Compressive Strength of Flanges, NACA Tech. Note 1323, 194 7. ... thickness 1.5 mm, is capable of resisting diagonal tension only. Ans. 19. 9 kN, 3 .9 kN. P.6.23 The spar of an aircraft is to be designed as an incomplete diagonal tension b...

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... 175 176 177 176 1 79 180 181 182 183 184 185 186 187 188 1 89 190 191 192 193 194 195 196 197 1% 199 200 201 202 203 204 205 206 207 208 2 09 210 21 1 212 213 ... conjidence limits. If 99 .9% of all the results lie between the curves, i.e. only 1 in 1000 falls outside, they represent the 99 .9% confidence limits. If 99 .99 999 % of...

Ngày tải lên: 13/08/2014, 16:21