Systems and methods for fault detection and control in an electric aircraft
AssigneeBeta Air, LLC
InventorsNicholas Moy, Hamid-Reza Ossareh
Life of this patent
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Abstract
A system for fault detection and control in an electric aircraft including an inertial measurement unit, the inertial measurement unit including at least a sensor configured to detect a torque datum associated with at least a propulsor. The system includes an observer, the observer configured to generate a torque prediction datum associated with the at least a propulsor, compare the torque prediction datum with the torque datum, and generate a residual datum as a function of the comparison. The system includes a mixer, the mixer comprising circuitry configured to generate, as a function of the residual datum, a torque priority command datum and transmit, to the at least a propulsor, the torque priority command datum.
Claims18
A system for fault detection and control in an electric aircraft, the system comprising:
- a flight controller, the flight controller comprising:
- at least a sensor, wherein the at least a sensor configured to detect a torque datum associated with at least a propulsor;
- an observer, the observer configured to:
- generate a torque prediction datum associated with the at least a propulsor;
- compare the torque prediction datum with the torque datum;
- and
- generate a residual datum as a function of the comparison;
- a mixer configured to operate in a first mode in which the mixer configured to control a first plurality of the at least a propulsor and a second mode in which the mixer is configured to control a second plurality of the at least a propulsor, the mixer comprising circuitry configured to:
- generate, as a function of the residual datum, a torque priority command datum;
- and
- transmit, to the at least a propulsor, the torque priority command datum configured to command operation of at least one flight component of the electric aircraft.
A method for fault detection and control in an electric aircraft, the method comprising:
- detecting, at an at least a sensor, a torque datum associated with at least a propulsor;
- generating, at an observer, a torque prediction datum associated with the at least a propulsor;
- comparing, at the observer, the torque prediction datum and the torque datum;
- generating, at the observer, as a function of the comparison, a residual datum;
- generating, at a mixer that is configured to operate in a first mode in which the mixer is configured to control a first plurality of the at least a propulsor and a second mode in which the mixer is configured to control a second plurality of the at least a propulsor, as a function of the residual datum a torque priority command datum;
- and
- transmitting, to the at least a propulsor, the torque priority command datum configured to command operation of at least one flight component of the electric aircraft.
Dependencies are inferred from the claim text.