Page 213 - Aircraft Stuctures for Engineering Student

Problems 197

1 Timoshenko, S. P. and Gere, J. M., Theory of Elastic Stability, 2nd edition, McGraw-Hill
Book Company, New York, 1961.
2 Gerard, G., Introduction to Structural Stability Theory, McGraw-Hill Book Company,
New YQrk, 1962.
3 Murray, N. W., Introduction to the Theory of Thin-walled Structures, Oxford Engineering
Science Series, Oxford, 1984.
4 Handbook of Aeronautics No. 1: Structural Principles and Data, 4th edition, The Royal
Aeronautical Society, 1952.
5 Bleich, F., Buckling Strength of Metal Structures, McGraw-Hill Book Company, New
York, 1952.
6 Gerard, G. and Becker, H., Handbook of Structural Stability, Pt. I, Buckling of Flat Plates,
NACA Tech. Note 3781, 1957.
7 Rivello, R. M., Theory and Analysis of Flight Structures, McGraw-Hill Book Company,
New York, 1969.
8 Stowell, E. Z., Compressive Strength of Flanges, NACA Tech. Note 1323, 1947.
9 Mayers, J. and Budiansky, B., Analysis of Behaviour of Simply Supported Flat Plates Com-
pressed Beyond the Buckling Load in the Plastic Range, NACA Tech. Note 3368, 1955.
10 Gerard, G. and Becker, H., Handbook of Structural Stability, Pt. IV, Failure of Plates and
Composite Elements, NACA Tech. Note 3784, 1957.
11 Gerard, G., Handbook of Structural Stability, Pt. V, Compressive Strength of Flat Stiffened
Panels, NACA Tech. Note 3785, 1957.
12 Gerard, G. and Becker, H., Handbook of Structural Stability, Pt. VU, Strength of Thin
Wing Construction, NACA Tech. Note D-162, 1959.
13 Gerard, G., The crippling strength of compression elements, J. Aeron. Sci. 25(1), 37-52
Jan. 1958.
14 Kuhn, P., Stresses in Aircraft and Shell Structures, McGraw-Hill Book Company, New
York, 1956.

L

P.6.1 The system shown in Fig. P.6.1 consists of two bars AB and BC, each of
bending stiffness EZ elastically hinged together at B by a spring of stiffness K (i.e.
bending moment applied by spring = K x change in slope across B).
Regarding A and C as simple pin-joints, obtain an equation for the first buckling
load of the system. What are the lowest buckling loads when (a) K + 00, (b)
EZ + 00. Note that B is free to move vertically.
Am. pKltan pl.

P A BdStif f ness K C P
le.
v 0-
* I - -
2 1

Fig. P.6.1