Aircraft Structures 3E Episode 13 pps

... anticlockwise. 00 mm2 1.0 mm Fig. P.11.4 Matrix methods of structura I analysis Actual aircraft structures consist of numerous components generally arranged in an irregular manner. These ... idealizations and their effect on structural analysis have been presented in Chapter 9 for aircraft structures. Outside the realms of aeronautical engineering the represen- tat...

Ngày tải lên: 13/08/2014, 16:21

... any'+' + 3.5~ + 0.8 = 0 where x = F23/Po and (Y = Po/Ar0 Fig. P.4.12 P.4 .13 Figure P.4 .13 shows a plan view of two beams, AB 9150mm long and DE 6100mm long. The simply supported ... element possesses curvature in both xz and yz planes. Therefore, from Fig. 5 .13 the component in the 132 Bending of thin plates substitution for M,, My and Mxy...

Ngày tải lên: 13/08/2014, 16:21

... and stresses outside the elastic range is known as the reduced modulus theory. From Eq. (6 .13) we have E y1 dA - Et y2dA = 0 J: (6.19) which, together with the relationship d ... and Bsinpl= 0 For a non-trivial solution @e. v # 0) then sinpl=O or pl=n.rr wheren= 11 2131 giving or Note that Eq. (6.3) cannot be solved for v no matter how many of the availab...

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

... exhaust 130 APU exhaust 131 Engine fuel control unit 132 Engine bay venting ram air Intake 133 Rotary nozzle bearing 134 Nozzle fairing construction 135 Ammunition tank, 100 rounds 136 ... 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...

Ngày tải lên: 13/08/2014, 16:21

... continuum structures References Further reading Problems 13 Elementary aeroelasticity 13. 1 Load distribution and divergence 13. 2 Control effectiveness and reversal 13. 3 Structural vibration 13. 4 ... of thin-walled columns 6 .13 Tension field beams References Problems Part I1 Aircraft Structures 7 Principles of stressed skin construction 7.1 Materials of aircraft c...

Ngày tải lên: 13/08/2014, 16:21

... I/ I Fig. P.1.10 of the beam gave strain readings as follows: E, = -222 x &b = - 213 x lop6, E, = +45 x The longitudinal stress at the point P due to an external compres- ... as predicted. The torsion constant J follows from the substitution of Eq. (3.26) into Eq. (3 .13) , giving St3 J=- 3 (3.29) and 3T - - St3 rzy,max - These equations represent exac...

Ngày tải lên: 13/08/2014, 16:21

... 0 0 16 013 0 0 0 - 160J2/3 0 FB 4000J2 -20000J2 d2pB.f 13 ~ 213 DC 4000 80 000 PB,f13 113 pDsf 1 32 013 320 PD,f 1 32 013 320 1 48 013 240 BA 4000 60 000 2pB,f/3 213 pD,f ... -2J 213 0 0 320J2 0 EF 4000 -60 000 -2pB,f/3 - 213 0 0 160 0 FD 4000J2 -80000J2 -d2PB.f/3 - ~ 213 0 0 640J 213 0 CB 4000 80 000 PB,f/3 113 EB 4000 20...

Ngày tải lên: 13/08/2014, 16:21

... 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 aircraft construction ... complete aircraft less tailplane) based on wing area is C,, = -0.032. Geometric data are given in Fig. P.8.8. During a steady glide with zero thrust at 250m/s EAS in which CL =...

Ngày tải lên: 13/08/2014, 16:21

... Example 9 .13. section. In cases where the shear force is not constant over the unit length of beam the method is approximate. We shall illustrate the method by applying it to Example 9 .13. In ... 03. It follows that for equilibrium of shear flows at 3, q3, in the wall 34, must be equal to -138 .5 - 104 = -242.5N/mm. Hence q34 = -69.0 x 10- 2(75 - ~4) ds4 - 242.5 4r...

Ngày tải lên: 13/08/2014, 16:21