This chapter presents a brief introduction to the origin of internal loads in a wing and fuselage. It describes the general case of an aircraft wing experiencing vertical shear/bending/torsion loads under the action of inertia and aerodynamic lift forces during a manoeuvre or gust encounter. The chapter also considers the treatment of turbulence. The inertia and aerodynamic forces per unit span for a symmetric gust encounter are determined and then substituted into the general expression for internal loads in the continuous wing. The generation of internal loads has been sought in the time domain using the output from simulations of steady/dynamic manoeuvres and discrete gust encounters. However, in the analysis of a continuous turbulence response, it is normally required to express the loads behaviour in the frequency domain in terms of spectral incremental loads quantities.
Aircraft Internal Loads
2014-12-02
28 pages
Article/Chapter (Book)
Electronic Resource
English
NTIS | 2001
|Engineering Index Backfile | 1964
|NTIS | 1964
|Engineering Index Backfile | 1961
|FUTURE AIRCRAFT ELECTRICAL LOADS
SAE Technical Papers | 1945
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