Electric fuse for an aircraft solid state power controller and aircraft solid state power controller comprising an electric fuse
An electric fuse for an aircraft solid-state power controller comprising at least one electric conductor, which is connected between an electric input terminal and an electric output terminal, and which is configured to blow when an electric current (I) flowing through the at least one electric conductor exceeds a predefined threshold (I max ). The at least one electric conductor is encapsulated in a potting and at least one outer surface of the potting is covered with a polymeric coating.
1 . An electric fuse for an aircraft solid-state power controller comprising:
at least one electric conductor, which is connected between an electric input terminal and an electric output terminal, and which is configured to blow when an electric current (I) flowing through the at least one electric conductor exceeds a predefined threshold (I max );
wherein the at least one electric conductor is encapsulated in a potting comprising a polymeric potting material; and
wherein at least one outer surface of the potting is covered with a coating comprising a polymeric coating material;
wherein the potting has the configuration of a dam-and-fill potting, comprising a polymeric potting material and a dam material enclosing the polymeric potting material.
2 . The electric fuse according to claim 1 , wherein the coating is made from a deformable, extensible, ductile, or elastic polymeric coating material.
3 . The electric fuse according to claim 1 , wherein the polymeric coating material has a density of 1000 to 1100 kg/m 3 .
4 . The electric fuse according to claim 1 , wherein the polymeric coating material is a polybutadiene based polymeric coating material, wherein the polymeric coating material is in particular a polymeric material that is available as DOLPHON® CB-1128.
5 . The electric fuse according to claim 1 , wherein the polymeric coating material is a two-component resin material.
6 . The electric fuse according to claim 1 , wherein the potting material has a good heat conductivity and/or, wherein the potting material has good arc discharge energy absorption properties.
7 . The electric fuse according to claim 1 , wherein the potting material includes mineral fillers.
8 . The electric fuse according to claim 1 , wherein the at least one electric conductor is an aluminum wire.
9 . Aircraft electric circuit board of an aircraft solid-state power controller, the aircraft electric circuit board comprising:
at least one electric fuse according to claim 1 .
10 . An aircraft electric circuit board according to claim 9 , wherein the board is a printed electric circuit board, comprising:
electric paths, wherein the at least one electric conductor is electrically coupled to two electric paths providing an electric connection between the two electric paths.
11 . An aircraft solid-state power switch module comprising:
a solid-state power switch mounted to a circuit board by chip-on-board technology; and
an electric fuse according to claim 1 , wherein the solid-state power switch and the electric fuse are in particular encapsulated in a common potting.
12 . An aircraft comprising:
an aircraft electric circuit board according to claim 9 .
13 . A method of forming an electric fuse on an aircraft electric circuit board comprising at least two electric paths, the method comprising:
connecting at least two of the electric paths with at least one electric conductor, which is configured to blow when an electric current (I) flowing through the at least one electric conductor exceeds a predefined threshold (I max );
encapsulating the at least one electric conductor in a potting comprising a polymeric potting material, wherein the potting has the configuration of a dam-and-fill potting, comprising a polymeric potting material and a dam material enclosing the polymeric potting material; and
coating at least one surface of the potting with a coating comprising a polymeric coating material, particularly a deformable, extensible, ductile, or elastic polymeric coating material.
14 . An electric fuse for an aircraft solid-state power controller comprising:
at least one electric conductor, which is connected between an electric input terminal and an electric output terminal, and which is configured to blow when an electric current (I) flowing through the at least one electric conductor exceeds a predefined threshold (I max );
wherein the at least one electric conductor is encapsulated in a potting comprising a polymeric potting material; and
wherein at least one outer surface of the potting is covered with a coating comprising a polymeric coating material;
wherein the at least one electric conductor includes a plurality of electric conductors, which are connected in parallel between the electric input terminal and the electric output terminal.
15 . The electric fuse according to claim 14 , wherein the coating is made from a deformable, extensible, ductile, or elastic polymeric coating material.
16 . The electric fuse according to claim 14 , wherein the polymeric coating material has a density of 1000 to 1100 kg/m 3 .
17 . The electric fuse according to claim 14 , wherein the polymeric coating material is a polybutadiene based polymeric coating material.
18 . The electric fuse according to claim 14 , wherein the polymeric coating material is a two-component resin material.
19 . The electric fuse according to claim 14 , wherein the potting material includes mineral fillers.