Network-based aircraft secondary electric power distribution system

A system for sensing electrical power transferred to a load within an aircraft comprising:

• a load comprising at least one electrical component of said aircraft;
• a source of electrical power within said aircraft connected by a conductor to said load;
• a sensor within said aircraft connected to said conductor, said sensor detecting a current passing through said conductor to said load;
• a microcontroller within said aircraft connected to said sensor;
• and
• a wireless communication network within said aircraft coupled to said sensor and to said microcontroller, said wireless communication network being configured to transmit information a distance of between about 10 and 50 meters, within said aircraft, regarding said current detected by said sensor.

A method for controlling an electric power distribution system within an aircraft comprising:

• transferring electrical power from a source within an aircraft to a load through a conductor, said conductor having a switch connected to a control node, said load being an electrical component of said aircraft;
• receiving at least one command from at least one component of said aircraft with a master node comprising an avionics full-duplex switched Ethernet (AFDX) system;
• sending a plurality of commands from said master node to said control node through a powerline carrier communication network, said plurality of commands including commands to open said switch and commands to close said switch;
• receiving said plurality of commands in said control node through said powerline carrier communication network;
• sending a plurality of signals to said switch from said control node, a first type of said plurality of signals causing said switch to open and a second type of said plurality of signals causing said switch to close;
• opening said switch in response to said command to open said switch and closing said switch in response to said command to close said switch;
• and
• said step of opening and said step of closing said switch effectuating the operation of said electrical component of said aircraft.