Patent · US Active

Systems and methods for fault detection and control in an electric aircraft

US11420756B1 · kind B1 · utility

10Cited by
12References
18Claims
0Family size

Assignee

Inventors

Key dates

Filing dateJul 1, 2021
Grant dateAug 23, 2022
Priority date—
Expiry dateJul 1, 2041

Classification

  • Technology area (CPC H)Electricity
  • CPC primaryH02P23/12
  • WIPO fieldTransport
  • WIPO sectorMechanical engineering

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.

Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.