Aircraft Structures 3E Episode 7 pps

... 163 164 165 166 1 67 168 169 170 171 172 173 174 175 176 177 176 179 180 181 182 183 184 185 186 1 87 188 189 190 191 192 193 194 195 196 1 97 1% 199 200 201 ... hydraulic actuator 74 Starboard outrigger wheel 75 BL755 6OO-lb ( 272 -kg) cluster bomb (CBU) 76 Intermediate pylon 77 Reaction control air ducting 78 Alleron control ro...

Ngày tải lên: 13/08/2014, 16:21

... and in-plane loading 1 37 Substitution for MI from Eq. (i) into the expressions for bending moment, Eqs (5 .7) and (5.8), yields [(m2/a2) + v(n2/h2)] . m7rx n7ry sin - sin (iii) ... negative y direction at the point 7. Find the rotation of member 27 about the z axis due to this loading. Note that the plane frames 01234 and 5 678 9 are identical. All members have th...

Ngày tải lên: 13/08/2014, 16:21

... we have 7rx 7ry ab 4 (2 + b2)2 sin2- sin2 - - 2( 1 - v) whence so that 7r4 sin 27rx -sin 27ry - - -cosz~cos2~]} 7r4 [&? a b a2b2 a b 8(~+ V) ~~~~7r~ 4ab (a ... conditions. Substituting for u, v and 8 from Eqs (6.84) into Eqs (6 .74 ), (6 .75 ) and (6.83), we have 7rZ 7rZ 7rz u = AI sin - , 8 = A3 sin - L L L (6.85) 1 (P-~)A~-PX~A...

Ngày tải lên: 13/08/2014, 16:21

... their structural complexity, as can be seen by comparing Figs 7. 7 and 7. 8. In Fig. 7. 7, the wing of the small, light passenger aircraft, the De Havil- land Canada Twin Otter, comprises a relatively ... FT = i.e. FT = 17. 7 kN Hence the direct stress in the top flange produced by the externally applied bending moment and the diagonal tension is 17. 7 x 103/350 = 50.7N/mm...

Ngày tải lên: 13/08/2014, 16:21

... jcfxyds=Ixy, jcty2ds=I, (11 .71 ) d2u d2v M, = -E- I - ED I,, dz2 x” Similarly (1 1 .72 ) d2u d2v c2tx& = -Es I& - E- I . dz2 x’ Equations (1 1 .71 ) and (11 .72 ) are identical ... 0,2A~t dS dz2 ErR Substituting in Eq. (1 1.69) from Eqs (1 1 .70 ), (1 1 .73 ) and (1 1 .74 ), we obtain ( 1 1 .74 ) 486 Structural constraint ______p .__ I...

Ngày tải lên: 13/08/2014, 16:21

... of aircraft components 10.1 Tapered beams 10.2 Fuselages Contents vii 174 175 i 77 180 188 1 97 1 97 209 211 21 1 220 223 225 232 233 233 235 238 244 248 25 1 2 57 27 1 ... I1 Aircraft Structures 7 Principles of stressed skin construction 7. 1 Materials of aircraft construction 7. 2 Loads on structural components 7. 3 Function of structural co...

Ngày tải lên: 13/08/2014, 16:21

... (a2+b2) dw - 2Tx T (a2 +h2) - - - dw dx 7rab3G+G m3b3 y7 % =-E 7ra3b3 - or (vii) Integrating both of Eqs (vii) T(b2 - a2) 7ra3 b3 G T(b2 - a2) nu3 b3 G XY +f2 (XI ... Oo0 = 76 923 N/mm2 G=- E 2(1+v)-2(1+0.3) Hence, from Eqs (1. 47) 48 Two-dimensional problems in elasticity P b2/8 I G r/r ~ -;g I L - - - - - - (a) (b) Fig. 2 .7...

Ngày tải lên: 13/08/2014, 16:21

... 4 .7 Solution of statically indeterminate systems 87 Hence from Eq. (4.22) 4.83lU + 2 .70 7PL = 0 or R = -0.56P Substitution for R ... Eq. (ii) from Eq. (iii) EI ‘v;7r4 7rz L u=- lo L4sin - dz which gives 7r4 EIv; u= 4L3 The total potential energy of the beam is then given by 7r4 EIv; 4L3 TPE=U+V= WVB Then, ... giving -ll&PL3 RL3 +- 76 8EI...

Ngày tải lên: 13/08/2014, 16:21

... Am. P = 2 67 852N, AP = 36257N, AL = 271 931 N, n = 1.19 P.8.8 An aircraft of all up weight 145 000 N has wings of area 50 m2 and mean chord 2.5m. For the whole aircraft CD ... the life of the aircraft in terms of flights is Nflighr = l/l)total 8 .7. 5 Crack propagation (8.60) (8.61) We have seen that the concept of fail-safe structures in aircraf...

Ngày tải lên: 13/08/2014, 16:21

... Similarly B2=y(2+2) (9 .70 ) (9 .71 ) In Eqs (9 .70 ) and (9 .71 ) the ratio of a1 to a2, if not known, may frequently be assumed. The direct stress distribution in Fig. 9. 47( a) is caused by a ... area = 20 OOOmm2. 9.8 Structural idealization 3 27 The torsional rigidity of the complete section is then GJ=5000x 1 07+ 6x 1O7=5O06x 107Nmm2 In all unrestrained torsion prob...

Ngày tải lên: 13/08/2014, 16:21