Connecting element including a sacrificial ball joint, particularly for engine mounts

FR3162070A1Active Publication Date: 2025-11-14SKF AEROSPACE FRANCE SAS
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Patent Information

Application Number
FR2024004804
Authority / Receiving Office
FR · FR
Patent Type
Applications
Current Assignee / Owner
Filing Date
2024-05-07
Publication Date
2025-11-14
Estimated Expiration
2044-05-07

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Abstract

Connecting element comprising a sacrificial ball joint, particularly for motor support. Connecting element (1), particularly for supporting a motor, comprising a body (2) and a first ball joint (3a) and a second ball joint (3b) mounted on the body (2). The connecting element (1) comprises a third sacrificial ball joint (3c), separate from the first and second ball joints (3a, 3b) and supported by the body (2), comprising an outer ring (4) and an inner ring (5) having respectively a spherical inner surface (4a) and a spherical outer surface (5b) in contact with each other, the outer ring (4) extending laterally in projection on either side of the body (2), said connecting element (1) further comprising a device for fixing said sacrificial ball joint (3c) to said body (2). Reference: Figure 1
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Claims

and on which is fixed the inner ring (5) of the sacrificial ball joint (3c).

7. Connecting element (1) according to claim 6, wherein the fastening device further comprises a groove (8) formed on the body (2) or on the shaft (9) in the extension of the thread (7) and inside which is housed a protrusion of the inner ring (5) of the sacrificial ball joint (3c).

8. Connecting element (1) according to claim 6, wherein the fastening device further comprises a locking nut (12) for the sacrificial ball joint (3c), mounted on the body (2) or on the shaft (9).

9. Connecting element (1) according to any one of claims 1 to 8, wherein the first and second ball joints (3a, 3b) comprise two parallel axes of rotation (RI) and wherein the sacrificial ball joint (3c) comprises an axis of rotation (R2) orthogonal to said axes of rotation (RI).

10. Connecting element (1) according to any one of claims 1 to 9, wherein a first principal face A of the body 2 comprises a nickel and / or cobalt alloy and a second opposite principal face B of the body 2 comprises a titanium and / or nickel alloy. [Fig. 1] [Fig. 3] [Fig. 4]

Citation Information

Patent Citations

  • Engine assembly for aircraft

    US20070205323A1

  • Rear engine attachment for an aircraft engine

    US20200361618A1