A hybrid beam (500) for support of a nacelle panel of a jet engine comprises a first longitudinal composite panel (402) and a second longitudinal composite panel (404), wherein the first longitudinal composite panel (402) is integrally affixed to the second longitudinal composite panel (404) along a longitudinal edge (406). The composite panels form a composite beam structure (400) that is substantially open with a cross-section that is generally "L-shaped". A plurality of hinge stations (540) are affixed to a first side of the first longitudinal composite panel (402) and at least one track guide (520) is disposed on a second side of the first longitudinal composite panel (402). The track guides (520) receive a head portion of a slider (550) that is fixed to the translating jet engine nacelle panel. Each hinge station (540) further comprises a bushing for defining a center of rotation for the jet engine nacelle panel relative to the beam (500).
Hybrid hinge and latch beam
Hybrider Scharnier- und Verschlussriegel
Faisceau charnière et verrou hybride
2020-03-11
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
NTRS | 1979
|ACTIVE PEDESTRIAN HOOD HINGE WITH INTEGRATED LATCH ASSEMBLY
European Patent Office | 2020
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