Patent ID: 9143029
Filing Date: 2015-09-22
Classification: B64D,H02J,H02M

Abstract:
1. A direct current (DC) power distribution system for an aircraft, the system comprising: a DC system bus configured to carry electrical power from an alternating current (AC) power 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 source power converter module comprising an AC to DC converter and a DC to DC converter comprising two switches, the source power converter module being, configured to convert AC power to DC power and being electrically coupled in series to the DC system bus on a source side of the DC system bus and being electrically coupled to the source for supplying the DC system bus with DC power; a plurality of load 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, wherein at least one of the load power converter modules is configured to be short circuited in response to a fault such that the at least one load power converter module does not supply electrical power to the corresponding subset of the electrical loads; and a controller electrically coupled to the DC system bus, the controller being configured to operate the two switches of the DC to DC converter of the source power converter module to maintain an electrical current of the DC system bus at a commanded value.