High power distribution architectures
A power distribution system for an aircraft, comprising: a plurality of electric propeller units (EPUs), a first paired battery pack unit, the first paired battery pack unit, and a second paired battery pack unit. The first paired battery pack unit may include a first battery electrically connected to a second battery via a first high voltage bus. The first battery may be configured to provide power to a first set of EPUs of the plurality of EPUs, the second battery may be configured to provide power to a second set of EPUs of the plurality of EPUs, the first battery may be configured to act as a backup battery for powering the second set of EPUs, and the first high voltage bus and the second high voltage bus may be electrically separate from one another.
1 . A power distribution system for an aircraft, comprising:
a plurality of electric propeller units (EPUs);
a first paired battery pack unit, the first paired battery pack unit comprising a first battery pack electrically connected to a second battery pack via a first battery pack cross-link, wherein the first battery pack is configured to provide power to a first set of EPUs of the plurality of EPUs, wherein the second battery pack is configured to provide power to a second set of EPUs of the plurality of EPUs; and
a second paired battery pack unit, the second paired battery pack unit comprising a third battery pack electrically connected to a fourth battery pack via a second battery pack cross-link, wherein the third battery pack is configured to provide power to a third set of EPUs of the plurality of EPUs, wherein the fourth battery pack is configured to provide power to a fourth set of EPUs of the plurality of EPUs,
wherein the first battery pack is configured to provide backup power across the first battery pack cross-link to the second set of EPUs; and
wherein the first battery pack cross-link and the second battery pack cross-link are electrically separate from one another.
2 . The system of claim 1 , wherein:
the first battery pack is configured to provide backup power across the first battery pack cross-link to the second set of EPUs;
the second battery pack is configured to provide backup power across the first battery pack cross-link to the first set of EPUs;
the third battery pack is configured to provide backup power across the second battery pack cross-link to the fourth set of EPUs;
the fourth battery pack is configured to provide backup power across the second battery pack cross-link to the third set of EPUs.
3 . The system of claim 1 , wherein:
the first battery pack cross-link comprises a first pyro-technical fuse and the power to the first set of EPUs is separated from the power to the second set of EPUs upon activation of the first pyro-technical fuse.
4 . The system of claim 3 , wherein the second battery pack cross link comprises a second pyro-technical fuse and the power to the third set of EPUs is separated from the power to the fourth set of EPUs upon activation of the second pyro-technical fuse.
5 . The system of claim 1 , wherein each battery pack is associated with a pyro-technical fuse configured to disconnect the associated battery pack from an operating portion of a corresponding one of the paired battery pack units.
6 . The system of claim 1 , wherein the first paired battery pack unit and the second paired battery pack unit are electrically separate from one another.
7 . The system of claim 1 , wherein each EPU of the plurality of EPUs comprises an associated fuse for high voltage power supply, wherein, upon activation of the fuse, the associated EPU is disconnected from an operating portion of the aircraft.
8 . The system of claim 1 , wherein each battery pack comprises an associated charging contactor, wherein, upon opening the charging contactor, the associated battery pack is disconnected from a high voltage charging bus.
9 . The system of claim 1 , wherein each one of the sets of EPUs comprises two EPUs.
10 . The system of claim 9 , wherein each one of the sets of EPUs comprises two diagonally symmetric EPUs.
11 . The system of claim 10 , wherein:
the first paired battery pack unit is configured to provide power to a front outboard EPU, a front inboard EPU, a rear outboard EPU, and a rear inboard EPU.
12 . The system of claim 1 , wherein the first battery pack is configured to independently power the first set of EPUs and the second battery pack is configured to independently power the second set of EPUs.
13 . An aircraft, comprising:
a plurality of electric propeller units (EPUs);
a battery management system;
a first paired battery pack unit, the first paired battery pack unit comprising a first battery pack electrically connected to a second battery pack via a first battery pack cross-link, wherein the first battery pack is configured to provide power to a first set of EPUs of the plurality of EPUs, wherein the second battery pack is configured to provide power to a second set of EPUs of the plurality of EPUs;
a second paired battery pack unit, the second paired battery pack unit comprising a third battery pack electrically connected to a fourth battery pack via a second battery pack cross-link, wherein the third battery pack is configured to provide power to a third set of EPUs of the plurality of EPUs, wherein the fourth battery pack is configured to provide power to a fourth set of EPUs of the plurality of EPUs, wherein:
the first battery pack is configured to provide backup power across the first battery pack cross-link to the second set of EPUs after the first battery pack is disconnected from the second battery pack by the battery management system; and
the first battery pack cross-link and the second battery pack cross-link are electrically separate from one another.
14 . The aircraft of claim 13 , wherein:
the first battery pack is configured to provide backup power across the first battery pack cross-link to the second set of EPUs;
the second battery pack is configured to provide backup power across the first battery pack cross-link to the first set of EPUs;
the third battery pack is configured to provide backup power across the second battery pack cross-link to the fourth set of EPUs;
the fourth battery pack is configured to provide backup power across the second battery pack cross-link to the third set of EPUs.
15 . The aircraft of claim 13 , wherein:
the first battery pack cross-link comprises a first pyrotechnical fuse and the power to the first set of EPUs is separated from the power to the second set of EPUs upon activation of the first pyro-technical fuse.
16 . The aircraft of claim 15 , wherein:
the second battery pack cross-link comprises a second pyrotechnical fuse and the power to the third set of EPUs is separated from the power to the fourth set of EPUs upon activation of the second pyro-technical fuse.
17 . The aircraft of claim 13 , wherein each battery pack comprises a pyro-technical fuse, each pyro-technical fuse being configured to disconnect the battery pack from an operating portion of a corresponding one of the paired battery pack units.
18 . The aircraft of claim 13 , wherein the first paired battery pack unit and the second paired battery pack unit are electrically separate from one another.
19 . The aircraft of claim 13 , wherein each EPU of the plurality of EPUs comprises an associated fuse for high voltage power supply, wherein, upon activation of the fuse, the associated EPU is disconnected from an operating portion of the aircraft.
20 . The aircraft of claim 13 , wherein each battery pack comprises an associated charging contactor, wherein, upon opening the charging contactor, the associated battery pack is disconnected from a high voltage charging bus.
21 . The aircraft of claim 13 , wherein each one of the sets of EPUs comprises two EPUs.
22 . The aircraft of claim 21 , wherein each one of the sets of EPUs comprises two diagonally symmetric EPUs.
23 . The aircraft of claim 22 , wherein:
the first paired battery pack unit is configured to provide power to a front outboard EPU, a front inboard EPU, a rear outboard EPU, and a rear inboard EPU.
24 . The aircraft of claim 13 , wherein the first battery pack is configured to independently power the first set of EPUs and the second battery pack is configured to independently power the second set of EPUs.