Introduction to Aircraft Structural Analysis (Elsevier Aerospace Engineering)

572 CHAPTER 20 Wing Spars and Box Beams and σz,r= − 190 × 106 5.22× 108 yr=−0.364yr Hence, P 1 =P 3 =−P 4 =−P 6 =−0.364× 295 × 9 ...

20.3 Beams Having Variable Stringer Areas 573 Fig.20.9 Change in boom loads/unit length of beam. Fig.20.10 Equilibrium of boom. ...

574 CHAPTER 20 Wing Spars and Box Beams Themomentresultantoftheinternalshearflows,togetherwiththemomentsofthecomponentsPy,r ofth ...

Problems 575 Fig. P.20.1 P.20.2 IfthewebinthewingsparofP.20.1hasathicknessof2mmandisfullyeffectiveinresistingdirectstresses, cal ...

Thispageintentionallyleftblank ...

CHAPTER 21 Fuselages................................................................................. Aircraftfuselagesconsist,a ...

578 CHAPTER 21 Fuselages Fig.21.1 (a) Actual fuselage section; (b) idealized fuselage section. B 11 =B 15 ,B 4 =B 6 =B 12 =B 14 ...

21.2 Shear 579 Table 21.1 Stringer/boom y(mm) σz(N/mm^2 ) 1 381.0 302.4 2,16 352.0 279.4 3,15 269.5 213.9 4,14 145.8 115.7 5,13 ...

580 CHAPTER 21 Fuselages Fig.21.2 Idealized fuselage section of Example 21.2. Thefirsttermontheright-handsideofEq.(ii)isthe“open ...

21.3 Torsion 581 Table 21.2 Skin panel Boom Br(mm^2 ) yr(mm) qb(N/mm) 12 −− − 0 2 3 2 216.6 352.0 −30.3 3 4 3 216.6 269.5 −53.5 ...

582 CHAPTER 21 Fuselages Fig.21.3 Shear flow (N/mm) distribution in fuselage section of Example 21.2. Itisimmaterialwhetherornot ...

21.3 Torsion 583 Fig.21.4 Alternative solution of Example 21.2. Substitutingforq 32 ,q 43 ,andq 54 fromthepreceding,weobtain 4 ( ...

584 CHAPTER 21 Fuselages 21.4 CutoutsinFuselages................................................................................ ...

Problems 585 wouldbethevalueoftheshearflowinthepanelwithoutcutouts.Consideringahorizontallengthof thepanelthroughthecutouts,wese ...

586 CHAPTER 21 Fuselages directstressesintheboomsandtheshearflowsinthepanelswhenthesectionissubjectedtoashearloadof50kN andabend ...

CHAPTER 22 Wings...................................................................................... WehaveseeninChapters11and ...

588 CHAPTER 22 Wings Fig.22.1 Three-boom wing section. Weshallreturntothesimplecaseofathree-boomwingsectionwhenweexaminethedistr ...

22.2 Bending 589 Fig.22.2 Idealized section of a multicell wing. Fig.22.3 Wing section of Example 22.1. Table 22.1 Boom y(mm) σz ...

590 CHAPTER 22 Wings 22.3 Torsion............................................................................................... ...

22.3 Torsion 591 Fig.22.5 Shear flow distribution in theRth cell of anN-cell wing section. TheshearflowinEq.(22.5)isconstantalon ...