| 摘要 |
A mounting assembly (50) for mechanically interconnecting a helicopter rotor blade (12) to a rotor hub assembly (10) and for mechanically interconnecting the rotor blade (12) to a damper assembly (52) and a pitch control input assembly (54). The rotor hub assembly (10) includes a hub plate (16) having a hub plate aperture (22) for mounting a rotor assembly yoke (24). The rotor assembly yoke (24) includes upper and lower radially extending arms (28a, 28b) which are disposed above and below the hub plate (16) and which include a set of mounting apertures (29) formed through the proximal end thereof. The mounting assembly (50) includes upper and lower clevis arms (60a, 60b) formed at the root end (56) of the rotor blade (12), a horn/damper fitting (64) interposed between the upper and lower clevis arms (60a, 60b), and upper and lower spacer plates (90a, 90b) disposed between the clevis arms (60a, 60b) and the radially extending arms (28a, 28b) of the rotor assembly yoke (24). The horn/damper fitting (64) includes first and second end portions (66, 68) which are configured for mounting to the damper assembly (52) and the pitch control input assembly (54). First and second sets of aligned apertures (102, 112) are formed in the upper and lower clevis arms (60a, 60b), the horn/damper fitting (64), and the upper and lower spacer plates (90a, 90b) for accepting first and second fastening members (100, 110). The first fastening members (100) are disposed through the first set of aligned apertures (102) for mechanically coupling the clevis arms (60a, 60b), the horn/damper fitting (64), and the spacer plates (90a, 90b) in combination. The second fastening members (110) are disposed through the mounting apertures (29) of the rotor assembly yoke (24) and the second set of aligned apertures (112) for mechanically coupling the rotor assembly yoke (64) and the spacer plates (90a, 90b) in combination.
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