Military aeroplanes, simplified, enlarged; an explanatory consideration of their characteristics, performances, construction, maintenance, and operation, specifically arranged for the use of aviators and students . account the weakening due to an example, spruce, ordinarily, stands 5600 lbs. per sq. inch in directcompression, whereas one of the most practical strut formulae takinginto account the average dimensions of aeroplane struts, reduces this * These formulae and data are ordinarily furnished by the manufacturer, andif need be are readily checked by actual breakage test on a s
Military aeroplanes, simplified, enlarged; an explanatory consideration of their characteristics, performances, construction, maintenance, and operation, specifically arranged for the use of aviators and students . account the weakening due to an example, spruce, ordinarily, stands 5600 lbs. per sq. inch in directcompression, whereas one of the most practical strut formulae takinginto account the average dimensions of aeroplane struts, reduces this * These formulae and data are ordinarily furnished by the manufacturer, andif need be are readily checked by actual breakage test on a strut. A typical formulais the RAF strut formula. FA Crippling Strength^ ?—, in which F = allowable compression stress, 1 + 6500 IVk A = area of section 1 = length of strut in inches, andk = least radius of gyration. 116 to about l/5th, giving 1100 lbs. per sq. in., as the ultimate strengthto be expected. If UL is made of spruce, with sq. in. cross section,it may be expected to have a strength of about x 1100= 2500 lbs.,and since the stress induced is 310 lbs., there is a safety factor of 8 (seep. 108). .Frorrh RearSpar Wing cutout formovable flapjt\ hinged torear spar Strut Rib-,for Driftgracing. The constiuction of a wing showing the spars to which ribs and cloth covering transmit the load,and also showing the Drift wiring. The stresses in the Spars may be divided into the following elements: (1) The stresses, due to their part in the general bracing of thewing truss as found by the stress diagram, p. 108, which indicatesat once that as members of the rigid truss the lower spars are sub-jected to tension and the upper spars to compression. (2) The stresses, due to the loading of the spar as a beam carry-ing the air pressure loads transmitted by the wing covering and ribs. X The result of the application of these stresses to the spar may be taken up as follows: (a) Compression or Tension Stress in Spar. — The allowablebreaking load in lbs. per sq. in., for the parti
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Keywords: ., bookcentury1900, bookdecade1910, booksubjectairplanes, bookyear19
