Structural analysis and design of airplanes (1920)
United States. Army. Air Corps · [Washington] · leaf 282
Origin at Support 2. 7w1L13 2w2L23m1L2+2m2(L1+L2)+m3L1 = —- --\ 6EIv« + 60 15 6EIv3 262 Art. 172 Equations for Continuous Beams Case 3A—Deflection in One Span for Uniformly Varying Loads … Origin at Support 1 EIv = x(x—L r m1 sx(x+L) w(x+L) (x^L2)!—+ + 120L m2—m1 w L »i- L 6 Case 3B—Deflection in One Span for Uniformly Varying Loads. Origin at Support 1.EIv=x(x—L)
Airplanes
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