Aircraft Structures 3E Episode 14 docx

... uniform beam Our discussion so far has been restricted to structures comprising members capable of resisting axial loads only. Many structures, however, consist of beam assemblies in which ... aCL/aa is the wing lift curve slope. Rearranging gives or (13.2) Elementary aeroelasticity Aircraft structures, being extremely flexible, are prone to distortion under load. When t...

Ngày tải lên: 13/08/2014, 16:21

... Broddle of British Aerospace for supplying photographs and drawings of aircraft structures. T.H.G. Megson 1989 Aircraft Structures for engineering students viii Contents 10.3 Wings 10.4 ... 6.13 Tension field beams References Problems Part I1 Aircraft Structures 7 Principles of stressed skin construction 7.1 Materials of aircraft construction 7.2 Loads on struct...

Ngày tải lên: 13/08/2014, 16:21

... (3 .14) From Fig. 3.5 the normal and tangential components of shear stress are r2, = rZx1 + rzyrn, rzs = rzyl - rzxm (3.15) Comparing the first of Eqs (3.15) with Eq. (3 .14) ... (3.9) 28 Basic elasticity (-290 x 1 04, Y Q, (360 x 1 04, ix 650 x 1 04) Fig. 1 .14 Mohr's circle of strain for Example 1.3. Now substituting in Eq. (1.35) for E,, E...

Ngày tải lên: 13/08/2014, 16:21

... 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 stresses experienced ... Table 4.5 (Tension positive) 0 Member 0 Length 0 Area @ F AB -R/2 -1 12 ~14~ ~ -R/2 -112 ~14~ ~ AB =I2 BC Ll2 CD LI2 DE LIZ BD LIZ EB LI2 A€ LI2 AB A...

Ngày tải lên: 13/08/2014, 16:21

... only, then M,, = 0 and from Eq. (5 .14) @w/axay = 0, so that Eq. (5.37) simplifies to 5.6 Energy method for the bending of thin plates 145 a' T z (b) Fig. 5.1 5 (a) ... equation by the factor (1 - v) yields a2W Mxy = D(1 - v)- axay (5 .14) Equations (5.7), (5.8) and (5 .14) relate the bending and twisting moments to the plate deflection and are ....

Ngày tải lên: 13/08/2014, 16:21

... yf dA) + e 2 (. y1 dA - Et J” 0 y2 d A) = - Pv (6 .14) The second term on the left-hand side of Eq. (6 .14) is zero from Eq. (6.13). Therefore we have in which Il =Jd’y;dA ... nn is unchanged. Since these (a) (b) Fig. 6.7 Determination of reduced elastic modulus. 148 Bending of thin plates The above solution is exact since we know the true deflected...

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...

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... 139 Gun pack strake 140 Fuselage centrellne pylon 141 Zero scarf forward (fan air) nozzle 142 Ventral gun pack (two) 143 Aden 25-mm cannon 144 Engine drain mast 145 Hydraulic system ... Hydraulic system ground connectors 146 Forward fuselage flank fuel tank 147 Engine electronic control unlla 148 Engine accessory equipment gearbox 149 Gearbox driven alternator 150 Rol...

Ngày tải lên: 13/08/2014, 16:21

... 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 = 0.021 + O.O41C;, for the wings ... 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 air...

Ngày tải lên: 13/08/2014, 16:21

... beams 37. Fig. 9.56 Shear flow distribution Wmm in walls of the beam section of Example 9 .14. q34 = -34.3N/mm = q56 q45 = -37.9N/= and qgl = 17.0N/~ giving the shear flow distribution ... ‘cut’ in a skin for which tD = 0 extends from the ‘cut’ to the adjacent booms. Example 9 .14 The thin-walled single cell beam shown in Fig. 9.55 has been idealized into a combi...

Ngày tải lên: 13/08/2014, 16:21