Kỹ thuật máy bay chiến đấu Episode 2 Part 7

Tham khảo tài liệu 'kỹ thuật máy bay chiến đấu episode 2 part 7', kỹ thuật - công nghệ, cơ khí - chế tạo máy phục vụ nhu cầu học tập, nghiên cứu và làm việc hiệu quả | 386 AIRCRAFT DESIGN Fig. Shear web buckling. NACA TN3781 Figure shows a typical braced wing. The compression load p is the horizontal component of the force on the strut S . The vertical component of s is found from summing the moments about the pin at the wing root using the equivalent concentrated lift loads as discussed earlier. The shear loads of the braced wing are analyzed as before taking into account the large concentrated vertical load of the strut. The bending moment must be analyzed with special equations provided below. The portion of the wing outboard of the strut is analyzed as before and the bending moment at the strut location is determined Af2 . The root bending moment Mi is usually zero unless the hinge point is above or below the neutral axis causing a bending moment due to the compression load p. The lift distribution on the portion of the wing inboard of the strut must be approximated by a uniform load distribution w . This is usually a reasonable approximation inboard of the strut. The following equations describe bending-moment distribution maximum bending moment and spanwise location of the maximum bending moment Ref. 60 M x Cl sin x j c2 cos x j wj2 STRUCTURES AND LOADS 387 h f - 1 4- w 2 cos x j 1 7 tan - 2 Di COS L j j J Di sin L j where J y EI P r D2 Dt cos L j 1 sin Z j c2 Dt Mt - wj2 D2 M2- wj2 Torsion Figure shows a solid circular shaft in torsion. The applied torque T produces a twisting deformation Ộ that depends upon the length of the shaft. As shown at the right of the figure the torque is resisted by shearing stresses that increase linearly with distance from the center if the stresses remain within the elastic limit. The shear stresses due to torsion are calculated with Eq. and are at a maximum at the surface of the shaft r R . The angular deflection in Fig. Braced wing analysis. 388 AIRCRAFT DESIGN radians is determined from Eq. . These equations also

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