System and method for power distribution

An aircraft comprising:

• an airframe;
• a source of electrical power onboard the airframe;
• a plurality of electrical loads onboard the airframe;
• and
• a direct current (DC) power distribution system comprising:
• a DC system bus comprising a source side and a load side, the DC system bus being electrically coupled to the source on the source side;
• and
• a plurality of power converter modules electrically attached to corresponding subsets of the electrical loads, the power converter modules being electrically coupled in series to the DC system bus on the load side for carrying electrical power from the DC system bus to the electrical loads, wherein at least one of the power converter modules is configured to be short circuited in response to a fault such that the at least one power converter module does not supply electrical power to the corresponding sub-set of the electrical loads.

A direct current (DC) power distribution system for an aircraft, the system comprising:

• a DC system bus configured to carry electrical power from a source of electrical power to a plurality of electrical loads, the electrical loads being onboard the aircraft, the DC system bus comprising a load side;
• a plurality of power converter modules electrically coupled in series to the DC system bus on the load side of the DC system bus, the power converter modules being configured to be electrically attached to corresponding sub-sets of the electrical loads;
• and
• a controller electrically coupled to the DC system bus, wherein the controller is configured to maintain an electrical current of the DC system bus at a commanded value.