An aircraft system (fig.2,10) has a moveable second structure (fig.2,14) coupled to a first structure 12, for example a flight control surface coupled to a fixed wing. An electrical connector (fig.2,20) runs between components (fig.2,16,18) housed in the structures, having a cable harness 22 housed in the wing, with a connector body 24 at one end 28, extending through an aperture (fig.4,56) in the wing, the connector couples to the control surface such that extension of the control surface between stowed and deployed positions causes the connector body to move through the aperture. Preferably, the electrical connector is between a power source 16 in the wing and a heater 18 in the control surface preventing ice build-up. The harness preferably includes a power and data cables, the connector having a number of different connection types. Preferably, the connectors movement slides along a pre-defined curved path, exposing an aerodynamically shaped portion of the connector body. The system may include a guide 64 for restricting harness motion in a plane during movement of the structures and a point 62 within the wing where the harness is fixed.
Aircraft systems and electrical connectors
2021-09-29
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / H02G INSTALLATION OF ELECTRIC CABLES OR LINES, OR OF COMBINED OPTICAL AND ELECTRIC CABLES OR LINES , Verlegen oder Installieren elektrischer Kabel oder Leitungen, Verlegen oder Installieren kombinierter optischer und elektrischer Kabel oder Leitungen |