Systems and methods for power distribution in electric aircraft

Abstract

To provide a power distribution system for electric aircraft that suppresses weight increase. [Solution] The electric aircraft power distribution system includes: a first battery pack connected to at least a first load and a common bus connecting a 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 a current exceeding a first threshold current, the first electrical component having 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 a current exceeding a second threshold current, the second electrical component having a second disconnection time longer than the first disconnection time at the second threshold current.

Claims

[Claim 1] The invention described in the specification and / or drawings.

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