SYSTEMS AND ARCHITECTURES FOR CHARGING INFRASTRUCTURE
Embodiments are provided for charging system for an aircraft. The charging system may comprise a plurality of electric propeller units (EPUs), a plurality of battery packs configured to power the plurality of EPUs, a charge port configured to accept high voltage power to charge the plurality of battery packs, a common high voltage charging bus connected to the charge port, and a charge control unit configured to determine battery pack charge contactor commands based on flight information for an aircraft and a current state of each battery pack of the plurality of battery packs. The plurality of battery packs may be chargeable through the common high voltage charging bus and each of the plurality of battery packs may include a disconnection device configured to disconnect the battery pack from charging.
1 - 58 . (canceled)
59 . A charging system for an aircraft, comprising:
a plurality of electric propeller units (EPUs);
a plurality of battery packs configured to power the plurality of EPUs;
a charge port configured to accept high voltage power to charge the plurality of battery packs;
a common high voltage charging bus connected to the charge port; and
a charge control unit, wherein:
the plurality of battery packs are chargeable through the common high voltage charging bus;
the charge control unit is configured to determine battery pack charge contactor commands based on flight information for an aircraft and a current state of each battery pack of the plurality of battery packs; and
each of the plurality of battery packs include a disconnection device configured to disconnect the battery pack from charging.
60 . The system of claim 59 , wherein the common high voltage charging bus is electrically separate from other high voltage wiring in the aircraft that provides a power connection from the plurality of battery packs to the plurality of EPUs.
61 . The system of claim 59 , further comprising: a high voltage channel at each respective battery pack, wherein the high voltage channel connects its respective battery pack to the common high voltage charging bus.
62 . The system of claim 61 , wherein the disconnection device for each battery pack is located on the high voltage channel.
63 . The system of claim 62 , wherein the disconnection device comprises a contactor.
64 . The system of claim 63 , wherein the disconnection device comprises a contactor on both the positive and negative side of the high voltage channel.
65 . The system of claim 59 , wherein the plurality of EPUs comprise all EPUs on one wing of the aircraft.
66 . The system of claim 59 , wherein the charge port is located on a fuselage of the aircraft.
67 . The system of claim 59 , wherein the charge port is further configured to accept communication from a ground charging subsystem configured to supply the high voltage power to charge the plurality of battery packs.
68 . The system of claim 67 , wherein the charge port is further configured to accept communications from a charge control unit inside the aircraft.
69 - 95 . (canceled)
96 . A control unit for charging an aircraft, comprising:
at least one processor, configured to:
accept high voltage power, from a charge port, to charge a plurality of battery packs configured to power a plurality of electric propeller units (EPUs), wherein the plurality of battery packs are chargeable through a common high voltage charging bus;
determine battery pack charge contactor commands based on flight information for an aircraft and a current state of each battery pack of the plurality of battery packs; and
provide the determined commands to charge the plurality of battery packs through the common high voltage charging bus.
97 . The control unit of claim 96 , wherein the common high voltage charging bus is electrically separate from other high voltage wiring in the aircraft that provides a power connection from the plurality of battery packs to powers the plurality of EPUs.
98 . The control unit of claim 96 , further comprising: a high voltage channel at each respective battery pack, wherein the high voltage channel connects its respective battery pack to the common high voltage charging bus.
99 . The control unit of claim 98 , wherein each battery pack comprises a disconnection device located on the high voltage channel.
100 . The control unit of claim 99 , wherein the disconnection device comprises a contactor.
101 . The control unit of claim 100 , wherein the disconnection device comprises a contactor on both the positive and negative side of the high voltage channel.
102 . The control unit of claim 96 , wherein the plurality of EPUs comprise all EPUs on one wing of the aircraft.
103 . The control unit of claim 96 , wherein the charge port is located on a fuselage of the aircraft.
104 . The control unit of claim 96 , wherein the charge port is further configured to accept communication from a ground charging subsystem configured to supply the high voltage power to charge the plurality of battery packs.
105 . The control unit of claim 104 , wherein the charge port is further configured to accept communications from a charge control unit inside the aircraft.