Download e-book for iPad: Aircraft Structures by David J. Peery

By David J. Peery

ISBN-10: 0486485803

ISBN-13: 9780486485805

ISBN-10: 1621986152

ISBN-13: 9781621986157

Nonetheless correct many years after its preliminary ebook, this mythical reference textual content on plane rigidity research is taken into account the easiest ebook at the topic. It emphasizes uncomplicated structural concept, which continues to be unchanged with the advance of latest fabrics and building tools, and the applying of ordinary rules of mechanics to research of airplane constructions.

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Sample text

10. Analyse the structure of Example 1, Art. 5, assuming the vertical load of 20 lb/i. to act midway between the spars and the drag load of 5 lb/in. to act in the aft direction. ~ 3 U ~ ~ J O ; t . 3 ~ ; t . 3 0 . ~ ~ ~ ~ 3 ~ ~ T- 9 c LA C PBOB. 11. 6) (-@f w i n d the loads in the fuselage truss structure shown by analyzing the '\ e i i w as coplanar structurea each carrying half the vertical load and by /b) h O B . 12. k) euperimpo&ngthe forces resulting from torsion about the oenter line. 5.

From the front sparJand the torsional moment is the product of the 4,000-lb resultant air load and its moment arm about the elastic axia -. T 2 4,000 X 6 = 24,OOO in-lb The area obtained by projecting the envelope members on the plane of the bulkhead BCDE is 240 sq in. 7 8s follows: The forces in the envelope members of the torsion structure shown in Fig. 4 Member L,in. 4 Dcv DP Fomj rL -1,560 +2,120 -1,m +2,120 42 AIRCRAFT STRUCTURES It will be noticed that members BE' and DC' are fictitiousmembers which represent the portions of the spars acting as torsion structure.

Resulting from torsion. The multmt forces in the members from combined bending and torsion are tabulated in column (4). There are no forces in members C,C,, C44, and C4C5 for a vertical loading, but these members would resist chordwise bending f n m drag l d ~ . Care must be exercised in finding the load in member A&. In thia case, a 44 AIRCRAFT STRUCTURES summstion of vertical form at joint BS gives no load in the member, but the member would be loaded if the torque varied along the span, or if there were drag loads acting.

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Aircraft Structures by David J. Peery


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