Aircraft structures for engineering students - part 9 pps

... matrix for a uniform beam 51 1 It is possible to write Eq. (12.44) in an alternative form such that the elements of [KJ are pure numbers. Thus 12 -6 -1 2 -6 -6 4 62 -1 2 6 12 6 -6 2 64 This form ... Aero. SOC., Parts I-IV, Feb. 194 7, Part V, Sept. and Nov. 194 7, Part VI, May and June 194 9. 2 Megson, T. H. G., Extension of the Wagner torsion bendi...

Ngày tải lên: 08/08/2014, 11:21

... (1. 59) EII = -5 02 x Now substituting for and sI1 in Eq. (1.56) 70 000 x CTI = (-5 02 + 0.3 x 1202) = -8 0.9N/mm2 1 - (0.3)2 Similarly, from Eq. (1.57) cII = - 10 .9 N/m2 ... = - [a, + a,, + az - 2v(ax + ay + 41 or In the case of a uniform hydrostatic pressure, a, = a,, = az = -p and 3(1 - 2~) E P e =-...

Ngày tải lên: 08/08/2014, 11:21

... they represent the 99 .9% confidence limits. If 99 .99 999 % of results lie between the curves only 1 in lo7 results will fall outside them and they represent the 99 .99 999 % confidence limits. ... for vertical equilibrium L+P- w=o (8.7) for horizontal equilibrium T-D=O and taking moments about the aircraft s centre of gravity in the plane of symmetry La - Db - Tc...

Ngày tải lên: 08/08/2014, 11:21

... the cross-section of the bar. Rearranging and substituting for u and from Eqs (3 .9) dw rzx dB dw r7 dB -A _- - - +-y, - ax G dz dy G dzX - (3.10) For a particular torsion ... M=-Pz Rz, hence -= 4 2 dR 2z between F and B P d3 dM d3 4 2 dR 2 M = - (L - z) - -Rz, hence - = - -2 and between B an...

Ngày tải lên: 08/08/2014, 11:21

... q(x,y)sin-sin- dxdy . mrx m'rx nry n'ry sin - sin - dx dy = m=l 2 n=l T/:jIamsin-sin- a a b b - ab 4 - since a 2 _- - when m=m' and . nry . n'ry sin-sin- ... and My are known. If either M, or My is zero then d2W - a2W d2W - d2W ax2 - 8Y2 ay2 - dX2 - -v- or - -v- and the plate has...

Ngày tải lên: 08/08/2014, 11:21

... Flexural-torsional buckling of thin-walled columns 185 0 P - ~EIJL~ -Pxs P - ~EI,,JL~ 0 PYS PYS - Pxs IOPIA - .rr2ET/L2 - GJ =O (6.86) d’v dz- d2 u EI, 7 = - PV EI,,,, ... 0 1 2 3 4 I5 I3 II 9- 7- 5, k - - - a/b (b) k 4 0- 36 - Clamped edges Simply supported 12345 a/b (C) Fig. 6.16 (a) Buckl...

Ngày tải lên: 08/08/2014, 11:21

... right-hand side of Eq. (ii) we have r=l qb:23 = qb,34 = -7 .22 X 1 0-4 (400 X 100) = -2 8.9N/mm qb,4j = -2 8 .9 - 7.22 x io-4(ioo x 50) = -3 2.5N/m.m qb,56 = qb:34 = -2 8 .9 ... (3.28) becomes (9. 57) (9. 58) and Eq. (3. 29) is 1 (9. 59) st3 J=C- or J =- t3ds In Eq. (9. 59) the second expression for the torsion constant...

Ngày tải lên: 08/08/2014, 11:21

... P3 = -P4 = -P6 = -0 .364 X 295 X 90 0 = -9 6642N and P2 -Ps = -0 .364 x 295 x 1200 = -1 28 856N At a section 1 .9 m from the built-in end M, = -1 00 x 2.1 = -2 lOkNm and ... Eq. (10.28) for each cell in turn. For cell I X 3880 X (-2 30) = 95 .5N/= X 3230 X 200 = -b9.0N/mm [qs,o:l( 1083 + 95 + 57) - 57qS,o,11 +...

Ngày tải lên: 08/08/2014, 11:21

... substitute in Eq. (1 1.28) for q from Eq. (1 1.25) and for PB from Eq. (1 1.26). Hence 1 #PA - Gt ( PA S,Z PA) - - - - - - - - - - - 2 dz2 dE 2B 2Bh A Rearranging, ... 8 = 0 at z = 0. d8 - - dz-2a2bZG L(b+~)[l-(bt,+Utb) tb CoshpL bt, - atb ’ coshp(L - z) 10.5 Cut-outs in wings and f...

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... method 7 9- 8 5 for buckling of columns 16 5 -9 for bending of thin plates 14 2 -9 potential energy 70, 71, 7 3-6 , 14 4 -9 , principle of stationary value of total Energy methods 6 8-1 09 108 16 5 -9 complementary ... the form shown in Fig. 13.10. Substituting the second natural frequency in Eq. (vii) we have - - ~2 1 - 16Xw2 - 1 - 16 x...

Ngày tải lên: 08/08/2014, 11:21