UNIVERSAL PLATFORM ARCHITECTURE FOR HYBRID MORE ELECTRIC AIRCRAFT
FIG5 is a block diagram illustrating the flow of battery power between the battery chargers and the voltage converter circuits when operating in the battery power mode according to a non-limiting embodiment
In response to invoking the battery power mode, the power distribution controller 132 activates a third combination of switches 130 while deactivating a third combination of switches 131. Accordingly, a different third electrical path is established between the front-end power converter 102 and the backend power converter sub-system 106. The third electrical path connects an output of the bi-directional battery charger circuit 122 to one or more voltage converter circuits 124. Further, the third electrical path is configured to share the output of one or more bi-directional battery charger circuits between the voltage converter circuits 124, e.g., one or more DC-to-DC converter circuits 124 and one or more DC-to-AC converter circuits 124. The flow of battery power between the battery chargers 124 and the voltage converter circuits 124 is illustrated in FIG5.
block diagram
122
battery charger circuit battery charger circuits
128
motor load
113
rectifier circuit
126
battery
104
active power distribution system
108
source
110
DC bus
124
converter circuits converter circuit
['1. An aircraft power system (100) comprising: a front-end power converter (102) configured to generate a first direct current (DC) supply voltage or a second DC supply voltage based on a voltage level of an alternating current (AC) supply voltage output from an AC voltage source (108); a backend power converter sub-system (106) configured to convert the first DC supply voltage or the second DC supply voltage into a backend supply voltage; and an active power distribution system configured to select different electrical paths between the front-end converter and the backend converter subsystem in response to detecting output of the first DC supply voltage and the second DC supply voltage.', '2. The aircraft power system of claim 1, wherein the active power distribution system comprises: a multi-phase rectifier circuit (113) including a plurality of switches operable in an open state and a closed state; and a power distribution controller (132) configured to invoke the open and closed states of the switches, wherein different combinations of open and closed switches establish the different electrical paths between the front-end power converter (102) and the backend power converter sub-system (106).', '4. The aircraft power system of claim 3, wherein the backend power converter sub-system (106) comprises: at least one bi-directional battery charger circuit (122) including an input in signal communication with the front-end power converter (102) and an output in signal communication with a battery installed on the aircraft; and at least one voltage converter circuit including at least one of a DC-to-DC converter circuit and a DC-AC converter circuit.', '13. The aircraft power system of claim 12, wherein the DC-to-DC converter circuit is configured to convert the first DC supply voltage or the second DC supply voltage into a third DC supply voltage having a different voltage level that drives a DC load installed on the aircraft, wherein the DC-to-AC converter circuit is configured to convert the first DC supply voltage or the second DC supply voltage into a second AC supply voltage that drives a motor installed on the aircraft, and wherein the power distribution controller is configured to invoke a hybrid power exchange mode, and in response to invoking the hybrid power exchange mode, deliver at least one of the first and second AC supply voltages along with battery power output from the battery to drive the DC load.']