By David J. Peery

ISBN-10: 0486485803

ISBN-13: 9780486485805

ISBN-10: 1621986152

ISBN-13: 9781621986157

Nonetheless proper a long time after its preliminary book, this mythical reference textual content on plane rigidity research is taken into account the simplest booklet at the topic. It emphasizes simple structural conception, which is still unchanged with the improvement of recent fabrics and building tools, and the applying of hassle-free ideas of mechanics to research of airplane constructions.

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December 2016 Wolfgang Demtröder

Kaiserslautern, Germany"

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**Extra resources for Aircraft Structures**

**Example text**

The air load is assumed to be uniformly distributed along the span of the wing. The diagonal drsg-trim members are wires, with the tension diagonal dective and the other diagonal carrying no load. Sdution. The vertical load of 20 Ibfin. is distributed to the spars in inverse proportion to the distance of the center of pressure from the spars. , and that on the rear spar 4 Ib/h. If the front spar is considered as a free body, as shown in Fig. 21(u), the vertical forces at A and G may be obtained.

1. W B . 2. 2 Membem A0 and BO of thie landingetructure are tweforce membera. Member CO ia attached at C by a joint which transmits tomion but no bending. Find the forces acting at all joints. 3. The bending momenta about 2 and e axes in a plane perpendicular to the spanWiee axis of a wing are 400," in-lb and l W J Wi d b as shown. Find the WE. 3. bending momenta about ZI and el axee which are in the same piane but rotated 100 coun~ockwise. 31 SPACE STRUCTUBS 24, The main beam of the wing shown has a sweapba& angle of 300.

8duth. From Fig. 15@), the shaded area iS 800 sq in. 25 Ibjin. The loads are now obtained 88 the product of the length of the member and the tension d c i e n t and are shown in the following table. The &motions of the forces are determined by inspection, and are designstea by positive signs for tension members and negative 8igna for compreseion members. 0 +-a86 -319 +319 --a86 +a9 -319 Example 2. Find the f o m in members EE', BE', BC', CC', CD', and ED' of the stnrcture shown m Fig. 16. Assume rigid bulkhesds in planes BCDE 35 &PAC% STRUCTURBS and B'C'LYE'.

### Aircraft Structures by David J. Peery

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