Abstract
This chapter describes the methods by which an aeroplane’s main flight structure is proven to be fit for purpose, through a combination of analysis and test, explaining that the use of numerical (finite element) methods is usually unsuitable as an approval tool. Special cases where approval by test only are described. Materials fatigue is also considered, describing the philosophy behind achieving fatigue resistant structures.
We might add several other hints to inventors who desire to enter on this enticing field, but we will conclude with only one more. The newly discovered metal aluminum, from its extraordinary combination of lightness and strength, is the proper material for flying machines.
Scientific American, 8 September, 1860.
This is a preview of subscription content, log in via an institution to check access.
Access this chapter
Tax calculation will be finalised at checkout
Purchases are for personal use only
Notes
- 1.
If the reader is unfamiliar with these concepts, a good introduction is in JE Gordon’s The New Science of Strong Materials, ISBN: 978-0140135978
Author information
Authors and Affiliations
Corresponding author
Rights and permissions
Copyright information
© 2015 Springer International Publishing Switzerland
About this chapter
Cite this chapter
Gratton, G. (2015). Approving an Aircraft’s Main Flight Structure. In: Initial Airworthiness. Springer, Cham. https://doi.org/10.1007/978-3-319-11409-5_6
Download citation
DOI: https://doi.org/10.1007/978-3-319-11409-5_6
Published:
Publisher Name: Springer, Cham
Print ISBN: 978-3-319-11408-8
Online ISBN: 978-3-319-11409-5
eBook Packages: EngineeringEngineering (R0)