Systems and methods for power distribution in electric aircraft
A electric aircraft power distribution system includes a first battery pack connected to at least a first load and to a common bus that connects the first battery pack in parallel to at least a second battery pack; a first electrical component electrically connected between the first battery pack and the first load and configured to disconnect the first load from the first battery pack in response to current above a first threshold current, wherein the first electrical component has a first disconnection time at the first threshold current; and a second electrical component electrically connected between the first battery pack and the common bus and configured to disconnect the first battery pack from the common bus in response to current above a second threshold current, wherein the second electrical component has a second disconnection time at the second threshold current that is higher than the first disconnection time.
1 . An electric aircraft, comprising:
a fuselage;
two fixed wings mounted on opposite sides of the fuselage;
a first set of one or more electric propulsion units (EPUs) and a second set of one or more EPUs disposed on one side of the fuselage, wherein the first set is disposed forward of the second set;
a third set of one or more EPUs and a fourth set of one or more EPUs disposed on another side of the fuselage, wherein the third set is disposed forward of the fourth set; and
a plurality of battery packs, wherein each battery pack of the plurality of battery packs is configured to power at least:
a portion of at least one EPU of the first set of one or more EPUs and a portion of at least one EPU of the fourth set of one or more EPUs, or
a portion of at least one EPU of the second set of one or more EPUs and a portion of at least one EPU of the third set of one or more EPUs,
wherein each battery pack is configured to power a respective portion of an EPU via a different dedicated electric power bus, and
wherein at least one battery pack is connected to at least one EPU via at least one of a contactor or a fuse.
2 . The electric aircraft of claim 1 , wherein:
at least two battery packs are connected to a common bus via at least one of a contactor or a fuse, and
the common bus connects positive terminals of the at least two battery packs.
3 . The electric aircraft of claim 1 , wherein at least two battery packs are connected to a common bus via at least one of a contactor or a fuse and configured to power different EPUs.
4 . The electric aircraft of claim 3 , wherein the different EPUs are of different sets of one or more EPUs.
5 . The electric aircraft of claim 1 , wherein at least two battery packs are connected to a common bus via at least one of a contactor or a fuse and configured to power different portions of one of the EPUs.
6 . The electric aircraft of claim 1 , wherein the portion of at least one EPU is a partial motor.
7 . The electric aircraft of claim 1 , wherein at least one of the plurality of battery packs is configured to power at least:
a portion of one EPU of the first set of one or more EPUs and a portion of one EPU of the fourth set of one or more EPUs, both EPUs disposed farthest from the fuselage relative to their respective sets; or
a portion of one EPU of the second set of one or more EPUs and a portion of one EPU of the third set of one or more EPUs, both EPUs disposed farthest from the fuselage relative to their respective sets.
8 . The electric aircraft of claim 1 , wherein at least one of the plurality of battery packs is configured to power at least:
a portion of one EPU of the first set of one or more EPUs and a portion of one EPU of the fourth set of one or more EPUs, both EPUs disposed nearest to the fuselage relative to their respective sets; or
a portion of one EPU of the second set of one or more EPUs and a portion of one EPU of the third set of one or more EPUs, both EPUs disposed nearest to the fuselage relative to their respective sets.
9 . The electric aircraft of claim 1 , wherein at least one of the plurality of battery packs is configured to power at least:
(i) a portion of one EPU that is in the first set of one or more EPUs and is arranged between a nearest-from-the-fuselage disposed EPU and a farthest-from-the-fuselage disposed EPU in the first set of one or more EPUs, and (ii) a portion of one EPU that is in the fourth set of one or more EPUs and is arranged between a nearest-from-the-fuselage disposed EPU and a farthest-from-the-fuselage disposed EPU in the fourth set of one or more EPUs; or
(iii) a portion of one EPU that is in the second set of one or more EPUs and is arranged between a nearest-from-the-fuselage disposed EPU and a farthest-from-the-fuselage disposed EPU in the second set of one or more EPUs, and (iv) a portion of one EPU that is in the third set of one or more EPUs and is arranged between a nearest-from-the-fuselage disposed EPU and a farthest-from-the-fuselage disposed EPU in the third set of one or more EPUs.
10 . The electric aircraft of claim 1 , wherein each dedicated electric power bus is electrically isolated from another dedicated electric power bus.
11 . The electric aircraft of any of claim 1 , wherein no two battery packs of the plurality of battery packs power a same portion of any EPU of the aircraft.
12 . The electric aircraft of claim 1 , wherein:
at least two battery packs are connected to a common bus via at least one of a contactor or a fuse, and
each EPU of the first set of one or more EPUs and each EPU of the fourth set of one or more EPUs is powered by only one of the at least two battery packs.
13 . The electric aircraft of claim 1 , wherein:
at least two battery packs are connected to a common bus via at least one of a contactor or a fuse, and
each EPU of the second set of one or more EPUs and each EPU of the third set of one or more EPUs is powered by only one of the at least two battery packs.
14 . The electric aircraft of claim 1 , wherein the first set of one or more EPUs and the third set of one or more EPUs are configured to provide lift.
15 . The electric aircraft of claim 1 , wherein the second set of one or more EPUs and the fourth set of one or more EPUs are configured to provide lift.
16 . The electric aircraft of claim 1 , wherein the first set of one or more EPUs and the third set of one or more EPUs are tiltable between vertical lift and forward propulsion configurations.
17 . The electric aircraft of claim 1 , wherein the second set of one or more EPUs and the fourth set of one or more EPUs are tiltable between vertical lift and forward propulsion configurations.
18 . The electric aircraft of claim 1 , wherein each set of one or more EPUs includes three EPUs.
19 . An electric aircraft, comprising:
a fuselage;
a first set of one or more electric propulsion units (EPUs) and a second set of one or more EPUs, both disposed on one side of the fuselage, wherein the first set is disposed forward of the second set;
a third set of one or more EPUs and a fourth set of one or more EPUs, both disposed on another side of the fuselage, wherein the third set is disposed forward of the fourth set;
a plurality of battery packs, each battery pack configured to power at least:
a portion of at least one of the first set of one or more EPUs and a portion of at least one of the fourth set of EPUs, or
a portion of at least one of the second set of one or more EPUs and a portion of at least one of the third set of EPUs; and
a charger port configured for connection to an external charger for charging at least two battery packs of the plurality of battery packs, wherein the at least two battery packs are connected to the charger port via at least one of a contactor or a fuse.
20 . The electric aircraft of claim 19 , wherein each of the at least two battery packs is connected to the charger port via at least one of a contactor or a fuse.
21 . The electric aircraft of claim 19 , wherein the at least two battery packs are configured to power different EPUs.
22 . The electric aircraft of claim 21 , wherein the at least two battery packs are configured to power different EPUs from different sets of EPUs.
23 . The electric aircraft of claim 19 , wherein at least two of the plurality of battery packs each power different portions of one EPU.
24 . The electric aircraft of claim 19 , wherein at least two of the plurality of battery packs each power a partial motor associated with a different EPU.
25 . The electric aircraft of claim 19 , wherein each battery pack is configured to power a portion of an EPU via a dedicated electric power bus.
26 . The electric aircraft of claim 19 , wherein the first set of one or more EPUs and the third set of one or more EPUs are configured to provide lift.
27 . The electric aircraft of claim 19 , wherein the second set of one or more EPUs and the fourth set of one or more EPUs are configured to provide lift.
28 . The electric aircraft of claim 19 , wherein the first set of one or more EPUs and the third set of one or more EPUs are tiltable between vertical lift and forward propulsion configuration.
29 . The electric aircraft of claim 19 , wherein the second set of one or more EPUs and the fourth set of one or more EPUs are tiltable between vertical lift and forward propulsion configuration.
30 . The electric aircraft of claim 19 , wherein at least one battery pack is configured to power at least:
a portion of at least one of the first set of one or more EPUs and a portion of at least one of the third set of EPUs.
31 . The electric aircraft of claim 19 , wherein at least one battery pack is configured to power at least:
a portion of at least one of the second set of one or more EPUs and a portion of at least one of the fourth set of EPUs.
32 . The electric aircraft of claim 19 , wherein:
a first battery pack of the at least two battery packs is connected to the charger port via at least one of a first contactor or a first fuse, and
a second battery pack of the at least two battery packs is connected to the charger port via at least one of a second contactor or a second fuse.