|
|
||
|
|
|
|
This and the next image are from:
Tomasz Kopecki (Rzeszów University of Technology, Faculty of Mechanical Engineering and Aeronautics, Rzeszów, Poland)
“Chapter 7: Numerical Simulations of Post-Critical Behaviour of Thin-Walled Load-Bearing Structures Applied in Aviation”, in Computational and Numerical Simulations, edited by Jan Awrejcewicz, ISZBZN 8=978-953-51-1220-4, February 12, 2014, DOI: 10.5772/57218
PARTIAL INTRODUCTION: The design work on aircraft constructions, with applicable standards and requirements imposed by regulations applicable to aircraft design taken into account, represents a discipline significantly different than other fields of modern engineering. In fact, as opposed to rules commonly applicable to design of technical structures, in view of the need to limit the mass, in the case of airframe structures there is a necessity to allow phenomena involving loss of stability with respect to some of their components under the in-flight conditions. From the historical point of view, the issue of the loss of stability was a factor significantly slowing down the progress in aviation at early stage of its development. In aspiration to ensure safety, a large group of designers adhered to the lattice structure concepts for many years. The first attempts to develop some more advanced solutions were based on the use of corrugated sheet metal as the skin material for wings and fuselages. Such solution was adopted in numerous constructions manufactured on a mass scale, e.g. Ford Trimotor or Junkers 52. . .
Page 88 / 444