US 12,071,253 B2
Systems and methods for fault detection and control in an electric aircraft
Nicholas Moy, Burlington, VT (US); and Hamid-Reza Ossareh, South Burlington, VT (US)
Assigned to BETA AIR, LLC, South Burlington, VT (US)
Filed by BETA AIR, LLC, South Burlington, VT (US)
Filed on Feb. 27, 2023, as Appl. No. 18/114,611.
Application 18/114,611 is a continuation in part of application No. 17/855,651, filed on Jun. 30, 2022, granted, now 11,639,231.
Application 17/855,651 is a continuation of application No. 17/365,049, filed on Jul. 1, 2021, granted, now 11,420,756, issued on Aug. 23, 2022.
Prior Publication US 2023/0286665 A1, Sep. 14, 2023
This patent is subject to a terminal disclaimer.
Int. Cl. B64D 31/00 (2006.01); B64D 27/24 (2006.01); B64D 31/06 (2006.01); B64F 5/60 (2017.01); G01L 5/22 (2006.01); H02P 29/024 (2016.01)
CPC B64D 31/00 (2013.01) [B64D 27/24 (2013.01); B64F 5/60 (2017.01); H02P 29/024 (2013.01); B64D 31/06 (2013.01); G01L 5/22 (2013.01)] 21 Claims
OG exemplary drawing
 
1. A system for fault detection and control in an electric aircraft, the system comprising:
at least a sensor, wherein the at least a sensor configured to detect a sensed datum associated with at least a flight component, wherein the at least a flight component comprises a plurality of propulsors configured to propel the electric aircraft in a fluid medium; and
a flight controller, the flight controller configured to determine a failure state of a first plurality of propulsors of the plurality of propulsors as a function of the sensed datum, wherein the flight controller further comprises:
a mixer configured to switch from a first mode in which the mixer is configured to control the plurality of propulsors with a first control allocation to a second mode in which the mixer is configured to control a second plurality of propulsors of the plurality of propulsors with a second control allocation, wherein the mixer comprises a circuitry configured to:
generate, as a function of the failure state, a torque priority command datum;
transmit, to the second plurality of propulsors, the torque priority command datum configured to alter a trajectory of the electric aircraft by a change in pitch and yaw utilizing the second plurality of propulsors; and
wherein the second control allocation has less attitude control in at least one axis than the first control allocation.