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公开(公告)号：US20240101253A1
公开(公告)日：2024-03-28
申请号：US18303032
申请日：2023-04-19
Applicant: Archer Aviation Inc.
Inventor： Geoffrey C. BOWER , Benjamin M. GREEK , Nathan T. DEPENBUSCH , John MELACK
CPC classification number: B64C29/0033 , B64D27/24 , H02J7/0063 , B60L2200/10 , B64D2221/00
Abstract: The present disclosure relates generally to electric aircraft, and more specifically to electric power distribution for electric aircraft. In one embodiment, an electric aircraft is disclosed, comprising: a fuselage; two wings mounted on opposite sides of the fuselage; a plurality of first electric propulsion units, arranged on both sides of the fuselage, aft of the wings during forward flight; a plurality of second electric propulsion units arranged on both sides of the fuselage, forward of the wings during forward flight; and a plurality of battery packs, each battery pack configured to power at least: a portion of one of the first electric propulsion units on one side of the fuselage, and a portion of one of the second electric propulsion units on the other side of the fuselage.
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Patent Agency Ranking
公开(公告)号：US20230382543A1
公开(公告)日：2023-11-30
申请号：US18357055
申请日：2023-07-21
Applicant: Archer Aviation, Inc.
Inventor： John MELACK
CPC classification number: B64D27/24 , B64C29/0033 , B64D2221/00
Abstract: 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.
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公开(公告)号：US20220177145A1
公开(公告)日：2022-06-09
申请号：US17115119
申请日：2020-12-08
Applicant: Archer Aviation, Inc.
Inventor： John MELACK
Abstract: 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.
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公开(公告)号：US20240246686A1
公开(公告)日：2024-07-25
申请号：US18593702
申请日：2024-03-01
Applicant: Archer Aviation Inc.
Inventor： John MELACK
CPC classification number: B64D27/24 , B64C29/0033 , B64D2221/00
Abstract: 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.
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公开(公告)号：US20230166854A1
公开(公告)日：2023-06-01
申请号：US17937936
申请日：2022-10-04
Applicant: Archer Aviation, Inc.
Inventor： John MELACK
CPC classification number: B64D27/24 , B64C29/0033 , B64D2221/00
Abstract: 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.
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公开(公告)号：US20220009625A1
公开(公告)日：2022-01-13
申请号：US16923939
申请日：2020-07-08
Applicant: Archer Aviation, Inc.
Inventor： Geoffrey C. BOWER , Benjamin M. GREEK , Nathan T. DEPENBUSCH , John MELACK
Abstract: An electric aircraft includes rotors for providing lift for vertical take-off and landing of the aircraft, proprotors that are tiltable between lift configurations for providing lift for vertical take-off and landing of the aircraft and propulsion configurations for providing forward thrust to the aircraft, a first battery pack for powering a first rotor and a first proprotor, a second battery pack for powering a second rotor and a second proprotor, a first electric power bus electrically connecting the first battery pack to the first rotor and proprotor, and a second electric power bus electrically connecting the second battery pack to the second rotor and proprotor, wherein the second electric power bus is electrically isolated from the first electric power bus.
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