Vibration damper for aircraft nacelle
View Patent ↗The invention relates to a vibration damper ( 5 ) that can be provided between an electronic housing ( 1 ) and the fixed structure of an aircraft nacelle ( 3 ). It comprises a block of an elastic material ( 10 ), a screw ( 7 ) for securing the block ( 10 ) to said fixed structure ( 3 ), and means ( 11, 29 a, 29 b ) for securing said housing ( 1 ) onto said block ( 10 ). It is characterized in that it comprises means ( 13, 15 ) for limiting the travel of said attachment means ( 11, 29 a, 29 b ) relative to said securing screw ( 7 ) in at least two directions of the space, wherein the limitation means ( 13, 15 ) are sized so as to prevent any strain on the screw ( 7 ) that could lead to the fatigue and/or breakage thereof.
1. A vibration damper interposed between an electronic module and a fixed structure of an aircraft nacelle, the vibration damper comprising:
a block made of elastic material;
a screw fastening the block to said fixed structure, said screw passing through a fastening washer;
fastening means to fasten said electronic module to said block; and
means for limiting the travel of said fastening means relative to said fastening screw in at least two directions, said limiting means comprising a cup capable of being fastened to said fixed structure and an impactor moving freely inside said cup, the impactor being secured to said electronic module by at least two fasteners and said electronic module fastened between the fastening washer and the impactor, and the at least two fasteners passing through the fastening washer, wherein the impactor is separated from the cup over its radially-outer periphery by a gap “J 1 ” and from an axially-outer periphery of the cup by a gap “J 2 ”, the gap “J 1 ” being smaller than a gap “J′ 1 ” separating a radially inner periphery of said impactor from a spacer, which said screw passes through.
2. The damper as claimed in claim 1 , wherein said limiting means are capable of limiting said travel in a plane perpendicular to said screw.
3. The damper as claimed in claim 1 , wherein said limiting means are capable of limiting said travel in at least one direction of a line parallel to said screw.
4. The damper as claimed in claim 2 , wherein the cup and the impactor are separated in directions perpendicular and parallel to said screw by the “J 1 ” and “J 2 ” gaps, respectively, such that strain on said screw corresponding to an abutment of said impactor inside said cup is situated beyond a threshold of fatigue and/or of breakage of said screw.
5. The damper as claimed in claim 4 , wherein said impactor is coated with an elastomer on a face interacting with said cup.
6. The damper as claimed in claim 4 , wherein a portion of said electronic module is sandwiched between said fastening means and said impactor.
7. The damper as claimed in claim 1 , further comprising a pull-out prevention stop.
8. An aircraft nacelle comprising the fixed structure and the electronic module mounted on the fixed structure by means of at least one damper as claimed in claim 1 .
9. The damper as claimed in claim 3 , wherein the cup and the impactor are separated in directions perpendicular and parallel to said screw by the “J 1 ” and “J 2 ” gaps, respectively, such that strain on said screw corresponding to an abutment of said impactor inside said cup is situated beyond a threshold of fatigue and/or of breakage of said screw.
10. The damper as claimed in claim 9 , wherein said impactor is coated with an elastomer on a face interacting with said cup.
11. The damper as claimed in claim 9 , wherein said impactor is mounted on said fastening means, a portion of said electronic module being sandwiched between said fastening means and said impactor.