Page 533 - Aircraft Stuctures for Engineering Student
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- LO -- Lb
i
Fig. 12.10 Assemblage of two beam-elements.
The complete stiffness matrix is formed by superimposing [K12] and [K23] as described
in Example 12.1. Hence
0 0
0 0
[K] = E (12.53)
Example 12.2
Determine the unknown nodal displacements and forces in the beam shown in Fig.
12.1 1. The beam is of uniform section throughout.
IW
Fig. 12.11 Beam of Example 12.2.
