The present invention refers to a harness routing electrically connecting a rear fuselage section of an aircraft and a trimmable Horizontal Tail Plane (HTP) installed at this rear section. The aircraft rear section comprises a first clipping point wherein the harness is attached to a fuselage frame located in front of the torsion box front spar, and a second clipping point wherein the harness is attached to a front spar of the HTP torsion box. The second clipping point is located downstream the first clipping point from the fuselage towards the torsion box interior, and the harness passes through the front spar towards the interior of the torsion box downstream the second clipping point. The harness installation and routing is optimized, in order to reduce harness length and weight, but at the same time assuring that any damage to the harness cables are prevented during the entire aircraft operative life.
AIRCRAFT FUSELAGE SECTION INCORPORATING A DYNAMIC HARNESS
FLUGZEUGRUMPFABSCHNITT MIT EINEM DYNAMISCHEN KABELBAUM
SECTION DE FUSELAGE D'AÉRONEF INCORPORANT UN HARNAIS DYNAMIQUE
12.12.2018
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
AIRCRAFT FUSELAGE SECTION INCORPORATING A DYNAMIC HARNESS
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