Aircraft Structures 3E Episode 12 pptx

... - ' mm mm P.10 .12 A singly symmetric wing section consists of two closed cells and one open cell (see Fig. P.10 .12) . The webs 25, 34 and the walls 12, 56 are straight, while ... distance of lOOmm from and parallel to side 12. The modulus of rigidity G is constant throughout the section. Wall 12 34 23 Length (mm) 375 125 500 11.2 Built-in end of a cl...

Ngày tải lên: 13/08/2014, 16:21

... taken to be 1 m the solution would have been q12 = -6000N/m, q23 = -120 00N/m, 9.9 Effect of idealization 335 12 N/mm S 4.8 kN 120 0 mm Fig. 9.51 Idealized channel section ... Eegative; similarly for booms 3 and 4 the right- hand side is positive. Thus q12 = -6N/= q23 = -6 + q12 = -12N/mm and q34 = +6 + q23 = -6N/mm giving the same solution as...

Ngày tải lên: 13/08/2014, 16:21

... 1933 250 1792 233 2073 233 1933 CI,II = - = 0 .129 CII!J = - = 0.140 C,,,J,, = - = 0.1 12 CII1,II = - = 0 .121 Also 258000 = 287.9N/mm ‘I = 1792 ‘I1 = 1933 ... 0.0833 0.0417 327.3 163.8 3945.6 0 90 -29457 0 3 2619.0 0 .125 0 0.0417 327.4 109.2 2641.6 200 90 -29466 21840 4 -2619.0 0 .125 0 -0.0417 -327.4 109.2 -2641.6 200 90 -29466 21840 5 -392...

Ngày tải lên: 13/08/2014, 16:21

... References Problems 12 Matrix methods of structural analysis 12. 1 Notation 12. 2 Stiffness matrix for an elastic spring 12. 3 Stiffness matrix for two elastic springs in line 12. 4 Matrix analysis ... frameworks 12. 5 Application to statically indeterminate frameworks 12. 6 Matrix analysis of space frames 12. 7 Stiffness matrix for a uniform beam 12. 8 Finite element method for c...

Ngày tải lên: 13/08/2014, 16:21

... shear. and Eq. (xiii) may be rewritten to include the effect of shear as Px3 P12x PI3 Pb2 (zl)y=o = 6EI - E 3EI 8IG + - + - (1 - x) (xiv) Let us now examine the distorted shape ... directions at a point on the surface of the shaft. A~S. aI = 121 .4~/mm~, e = 31043' aII = -46.4~/m~, e = 121 043' P.1.7 An element of an elastic body is subjected...

Ngày tải lên: 13/08/2014, 16:21

... 000 0 0 C = 126 8 C = 880 92 Energy methods of structural analysis Table 4.5 (Tension positive) 0 Member 0 Length 0 Area @ F AB -R/2 -1 12 ~14~~ -R/2 - 112 ~14~~ AB ... are ignored but may be calculated when required for particular cases. Of greater interest in aircraft structures is the calculation of the deflections produced by the large shear stresse...

Ngày tải lên: 13/08/2014, 16:21

... transverse load 129 whence from Eq. (5 .12) or M -Gt3 6% xy 6 axay Replacing G by the expression E/2( 1 + v) established in Eq. (1.45) gives Et3 @w M, = 12( 1 + v) axay ... material for which G = 0.38E. Ans. 0.72P. A Fig. P.4.11 P.4 .12 In the plane pin-jointed framework shown in Fig. P.4 .12, bars 25, 35, 15 and 45 are linearly elastic with modulus...

Ngày tải lên: 13/08/2014, 16:21

... 42 EI EI PCR = - = 2.471 - 1 712 12 This value of critical load compares with the exact value (see Table 6.1) of 7r2EI/ 412 = 2.467EI /12; the error, in this case, is seen to be ... bifurcation point; further bifurcation points occur at the higher values of PcR(4~2EI /12, 9.ir2EI /12, . . .). We have shown that the critical stress, Eq. (6.8), depends only on th...

Ngày tải lên: 13/08/2014, 16:21

... control rizontal tail countering e aircraft s tendency to pitch in a vertical plane Aircraft weight Fig. 7.3 Principal aerodynamic forces on an aircraft during flight. The force on ... loads encountered in landing and taxiing subject the aircraft to concen- trated shock loads through the undercarriage system. The majority of aircraft have their main Undercarriage loc...

Ngày tải lên: 13/08/2014, 16:21

... seven) 120 Intermediate pylon 121 Port outrigger pylon 122 Missile launch rail 123 AlMBL Sidewinder air-to-air misslle 124 Port ieadlng-edge root extension (LERX) 125 Inboard pylon 126 ... given type of aircraft will satisfy them. Thus, of the total number 8.3 Aircraft inertia loads 241 A \", , Wheel reaction R / Arrester hook Fig. 8.5 Forces on the ai...

Ngày tải lên: 13/08/2014, 16:21