Electrical wiring system for a rotor hub

The electrical harness system (301) is configured for routing a harness (303b) between a rotor yoke (109) and a rotor blade (103). A recess (307) in an inboard cap member (311) is configured to house a connector (313b) and an associated harness (303b). As the recess (307) extends along a radial path...

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Bibliographische Detailangaben
Hauptverfasser:	SHERRILL, PAUL B, SELF, ROBERT A, DAVIS, HUNTER J
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AEROPLANES AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION COSMONAUTICS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS HELICOPTERS PARACHUTES PERFORMING OPERATIONS TRANSPORTING
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Beschreibung
Zusammenfassung:	The electrical harness system (301) is configured for routing a harness (303b) between a rotor yoke (109) and a rotor blade (103). A recess (307) in an inboard cap member (311) is configured to house a connector (313b) and an associated harness (303b). As the recess (307) extends along a radial path in the chordwise direction of the rotor blade (103), the harness (303b) is configured to lie within the recess (307). Operationally induced centrifugal forces promote positioning the slack of harness (303b) within the recess (307), while the slack in the harness (303b) remains available for relative dynamic movements between the rotor blade (103) and the rotor yoke (109). Such a routing of the harness (303b) reduces aerodynamic drag and minimizes damage that could otherwise occur to the harness.