Integrated protective device against electrical discharges in fixing elements

1. An integrated device ( 1 ) for the protection against electrical discharges of conductive fixing elements ( 2 ) between one another or of a fixing element and another conductive element of an aircraft, comprising a cap ( 3 ) and an o-ring gasket ( 4 ) made of non-conductive insulating material, wherein the fixing element ( 2 ) works together with the cap ( 3 ) and the o-ring gasket ( 4 ), the fixing element ( 2 ) being surrounded by the cap ( 3 ) and the o-ring gasket ( 4 ) in a non-conductive manner, thus preventing the possibility of electrical discharges such that in the device ( 1 ) a number of necessary components is minimized, the impact in weight for the aircraft being minimum, wherein the cap ( 3 ) comprises a thread ( 11 ) for fixing the cap ( 3 ) to the fixing element ( 2 ).

2. The integrated device ( 1 ) for the protection against electrical discharges of conductive fixing elements ( 2 ) between one another or of a fixing element and another conductive element of an aircraft according to claim 1 , wherein the fixing element ( 2 ) is based on a standard fixing element, and further comprises a thread ( 5 ) on an outer face of an area to be protected.

3. The integrated device ( 1 ) for the protection against electrical discharges of conductive fixing elements ( 2 ) between one another or of a fixing element and another conductive element of an aircraft according to claim 2 , wherein the thread ( 5 ) of the fixing element ( 2 ) comprises a bevel ( 6 ) at its lower part, the cap ( 3 ) in turn comprising a bevel ( 12 ) at its lower part such that the o-ring gasket ( 4 ) is fitted, once installed, in a slit generated by the bevels ( 6 , 12 ).

4. The integrated device ( 1 ) for the protection against electrical discharges of conductive fixing elements ( 2 ) between one another or of a fixing element and another conductive element of an aircraft according to claim 2 , wherein the fixing element ( 2 ) comprises a groove ( 14 ) at the end of the thread ( 5 ), the o-ring gasket ( 4 ) further comprising a bead ( 15 ) in its outer area, such that the o-ring gasket ( 4 ) is fitted to the groove ( 14 ) of the fixing element ( 2 ), the cap ( 3 ) in turn being seated on the bead ( 15 ) of the o-ring gasket ( 4 ).

5. The integrated device ( 1 ) for the protection against electrical discharges of conductive fixing elements ( 2 ) between one another or of a fixing element and another conductive element of an aircraft according to claim 2 , wherein the fixing element ( 2 ) is part of a screw ( 7 ) with the thread ( 5 ) arranged in a head of the screw ( 7 ).

6. The integrated device ( 1 ) for the protection against electrical discharges of conductive fixing elements ( 2 ) between one another or of a fixing element and another conductive element of an aircraft according to claim 2 , wherein the fixing element ( 2 ) is part of a rivet ( 9 ) with the thread ( 5 ) arranged in a head of the rivet ( 9 ).

7. The integrated device ( 1 ) for the protection against electrical discharges of conductive fixing elements ( 2 ) between one another or of a fixing element and another conductive element of an aircraft according to claim 2 , wherein the fixing element ( 2 ) is part of a nut ( 8 ) with the thread ( 5 ) arranged at a lower part of the nut ( 8 ).

8. The integrated device ( 1 ) for the protection against electrical discharges of conductive fixing elements ( 2 ) between one another or of a fixing element and another conductive element of an aircraft according to claim 2 , wherein the fixing element ( 2 ) is part of a bushing ( 10 ) with the thread ( 5 ) arranged at a lower part of the bushing ( 10 ).

9. The integrated device ( 1 ) for the protection against electrical discharges of conductive fixing elements ( 2 ) between one another or of a fixing element and another conductive element of an aircraft according to claim 1 , wherein the thread ( 11 ) has self-locking properties, preventing the cap ( 3 ) from being separated from the fixing element ( 2 ).

10. The integrated device ( 1 ) for the protection against electrical discharges of conductive fixing elements ( 2 ) between one another or of a fixing element and another conductive element of an aircraft according to claim 1 , wherein the cap ( 3 ) comprises a recess ( 13 ) at its upper part to facilitate its installation with conventional tools during application of the installation tightening torque.

11. The integrated device ( 1 ) for the protection against electrical discharges of conductive fixing elements ( 2 ) between one another or of a fixing element and another conductive element of an aircraft according to claim 1 , wherein the cap ( 3 ) is made from a dielectric material.

12. The integrated device ( 1 ) for the protection against electrical discharges of conductive fixing elements ( 2 ) between one another or of a fixing element and another conductive element of an aircraft according to claim 1 , wherein the o-ring gasket ( 4 ) is made of a flexible material with non-conductive properties.

13. The integrated device ( 1 ) for the protection against electrical discharges of conductive fixing elements ( 2 ) between one another or of a fixing element and another conductive element of an aircraft according to claim 11 , wherein the dielectric material of the cap ( 3 ) is nylon or a high-strength plastic.

14. The integrated device ( 1 ) for the protection against electrical discharges of conductive fixing elements ( 2 ) between one another or of a fixing element and another conductive element of an aircraft according to claim 12 , wherein the flexible material with non-conductive properties is nitrile rubber or silicone rubber.