Aircraft Structures 3E Episode 2 pdf

... satisfied. PX ax = - [5y(x2 - z2) - ioy3 + 6dZy] 20 d3 ay = E( - 3yd2 - 2d3) 4d3 -P 40d3 Txy = - [5(3x2 - Z2)(y2 - d2) - 5y4 + 6y2d2 - $1 The boundary stress ... dO/dz X 2Ty T (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...

Ngày tải lên: 13/08/2014, 16:21

... of aircraft components 10.1 Tapered beams 10 .2 Fuselages Contents vii 174 175 i77 180 188 197 197 20 9 21 1 21 1 22 0 22 3 22 5 23 2 23 3 23 3 23 5 23 8 24 4 24 8 25 1 25 7 27 1 ... 23 5 23 8 24 4 24 8 25 1 25 7 27 1 27 2 27 2 27 6 27 6 29 1 29 5 300 307 316 322 327 331 3 42 345 3 62 3 62 3 74 1.9 Strain 17 Fig. 1. 12 Dis...

Ngày tải lên: 13/08/2014, 16:21

... we have sx = -4 121 12 + q23l23 (10.19) Now resolving vertically sy = q31 (h 12 + h23) - 412h 12 - q23h23 sxqO + sycO = -2A12q 12 - 2A23q23 (10 .20 ) (10 .21 ) Finally, taking ... Zxx = 2 x 21 6.6 x 381. 02 + 4 x 21 6.6 x 3 52. 02 + 4 x 21 6.6 x 26 9 52 + 4 x 21 6.7 x 145. 82 = 2. 52 x lo8 mm4 The solution is completed in Tabl...

Ngày tải lên: 13/08/2014, 16:21

... F~FDD,fIm,,f AE 4000J2 -6OOOOJ2 -2J2pB,f/3 -2J213 0 0 320 J2 0 EF 4000 -60 000 -2pB,f/3 -21 3 0 0 160 0 FD 4000J2 -80000J2 -d2PB.f/3 - ~21 3 0 0 640J213 0 CB 4000 80 000 ... EB 4000 20 000 2PB,f 13 21 3 0 0 16013 0 0 0 - 160J2/3 0 FB 4000J2 -20 000J2 d2pB.f 13 ~21 3 DC 4000 80 000 PB,f13 113 pDsf 1 320 13 320 PD,f 1 320 13 320 1 48...

Ngày tải lên: 13/08/2014, 16:21

... (5.7) and (5.8), yields [(m2/a2) + v(n2/h2)] . m7rx n7ry sin - sin (iii) mn[(m2/a2) + (n2/b2) 12 a mn[(m2/a2) + (n2/h2) 12 a [v(m2/a2) + (n2/h2)] . m7rx . n7ry sin - ... provided that M, 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 curvatures of opposite signs...

Ngày tải lên: 13/08/2014, 16:21

... the minor axis. 3PU - 3) 2~ t3 -+-+- 32 Am. wO= (d a2b2 b4 f3pa2b2(b2 + v2) 9(3b4 + 2a2b2 + 3d) ’ k3pa2b2(d + vb2) uyulmax = t2(3b4 + 2a2b2 + 3d) Centre, ~;r,,.,= ... *6pa4b2 &6pb4d 9(3b4 + 2a2b2 + 3d) ’ = t-(3b4 ’ + 2a2b2 + 3a4) mm nry w= 2 2Amnsin- U sin m=l n=l m 5 nrrr;l 4Wsin- sin U Ans. A,,,,, = r4Dab[(m2/d) + (n2/b...

Ngày tải lên: 13/08/2014, 16:21

... I = 500 mm; b = 25 .0 mm, t = 2. 5 mm, E = 70 000 N/mm2, EIG = 2. 6 AYE. OCR = 28 2 N/m2. Fig. P.6.19 7.1 Materials of aircraft construction 21 5 the aluminium-zinc-magnesium ... mrx 2~ y w = all sin- sin I Fig. P.6.15 1 92 Structural instability at a stiffener and is given by uytb 2 MmaX =- 12 or, substituting for gy from Eq. (6.101...

Ngày tải lên: 13/08/2014, 16:21

... 184 185 186 187 188 189 190 191 1 92 193 194 195 196 197 1% 199 20 0 20 1 20 2 20 3 20 4 20 5 20 6 20 7 20 8 20 9 21 0 21 1 21 2 21 3 21 4 Cross-dam hydraulic jack Nosewheel Nosewheel ... MAD compensator 20 Formation lighting strip 21 Fin construction 22 Fin attachment joint 23 Tailplane pivot seallng plate 24 Aerlals 25 Ventral fin 26 Tail bu...

Ngày tải lên: 13/08/2014, 16:21

... by [2( i2 - t /2) l3 I X.Y - - 2 [ (b + :2/ 2)t3 + (b + i) th’] + c 12 Expanding the cubed term we have Ixx = 2 [ (b + :2/ 2)p + (b +;) th’] +A [(Z)’ (n’ - 3h -2+ 3hq ... and Skqm we have or D, = 16.99 x lo2 ( - : )2 Jm (u;: 2u;5 .26 + u;6 .26 ) due 2/ 10 ur u2 Uf from which or, in terms of the aircraft speed Ve (8.59) It...

Ngày tải lên: 13/08/2014, 16:21

... 2. 0 x 600 ( ;;l) B1 = 300 + 3.0x400 (2- l)+ 6 6 2+ - which gives Also B1(= B6) = 1050mm2 i.e. 1.5 x 600 ( KM)) 2+ - 2. 0 x 600 ( 2M) 2. 5 x 300 2+ - + (2- 1)+ 6 6 6 B2 ... moments of area about this upper surface (4 x 100 x 2+ 4 x 20 0 x 2) y= 2 x 100 x 2 x 50 +2 x 20 0 x 2 x 100 + 20 0 x 2 x 20 0 which gives J = 75 mm...

Ngày tải lên: 13/08/2014, 16:21