Structural analysis and design of airplanes (1920)
United States. Army. Air Corps · [Washington] · leaf 281
s,L2 W d: EL IT^X SXX° + 2 6 + — + - 6 Deflection for part of beam between x = C and L. mxx2 sxxa W(x—C)3 fn^L s^L2 W dJ __ i ^ 1 I . EIv= 1 1 2 6 Case 2—Uniform Loads. 6 I 2 6L t t * t t * I/ f La 2 Ji 1 FT, ^ . Origin at Support 2. w.,L.,:; w,L,:; 6EIv, 6EIvm1L2+2m2(L1+L2)-\-m3L2==——-\ 1— --f Li… … 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
Airplanes
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