A study on thermal stresses in the aft fuselage part of the Concorde aircraft is presented. Aerodynamic heating and thermal stresses in relation to the specific beam/girder structure are discussed. Temperatures at selected nodes were calculated together with temperature distribution within the structure. Mechanical stresses were calculated using the free beam theory and the results are discussed. Thermal stresses calculated by the displacement method were compared to mechanical stresses and the coupling between thermal state and mechanical state is discussed. Results of in-flight monitoring of extensometers are detailed.
Thermal Loads in the Rear Fuselage of Concorde Aircraft Contraintes Thermiques dans la Partie Arriere du Fuselage Concorde
1973
117 pages
Report
Keine Angabe
Englisch
Aircraft fuselage configuration with upwardly deflected rear fuselage
Europäisches Patentamt | 2023
|Supersonic Passenger Aircraft: Concorde
Online Contents | 2013
TIBKAT | 1991
|SLUB | 1991
|Engineering Index Backfile | 1965
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