US 12,469,919 B2
Flight control system and method for an aircraft
Joshua E. Auerbach, Waterbury Center, VT (US); Andrew Giroux, Georgia, VT (US); Timothy Gerard Richter, South Burlington, VT (US); and Herman Wiegman, South Burlington, VT (US)
Assigned to BETA AIR LLC, South Burlington, VT (US)
Filed by BETA AIR, LLC, South Burlington, VT (US)
Filed on Jan. 13, 2023, as Appl. No. 18/097,035.
Application 18/097,035 is a continuation in part of application No. 17/878,006, filed on Jul. 31, 2022, granted, now 11,742,546.
Application 18/097,035 is a continuation in part of application No. 17/855,376, filed on Jun. 30, 2022, granted, now 12,006,024.
Application 17/878,006 is a continuation of application No. 17/479,828, filed on Sep. 20, 2021, granted, now 11,469,473, issued on Jun. 9, 2022.
Application 17/855,376 is a continuation of application No. 17/404,614, filed on Aug. 17, 2021, granted, now 11,407,496, issued on Aug. 9, 2022.
Prior Publication US 2023/0170570 A1, Jun. 1, 2023
Int. Cl. H01M 50/249 (2021.01); B60L 3/00 (2019.01); B60L 50/60 (2019.01); B60L 50/64 (2019.01); H01M 10/48 (2006.01)
CPC H01M 50/249 (2021.01) [B60L 3/0046 (2013.01); B60L 50/64 (2019.02); B60L 50/66 (2019.02); H01M 10/48 (2013.01); H01M 2220/20 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A flight control system for an aircraft, the flight control system comprising:
a plurality of flight components coupled to an aircraft, wherein the plurality of flight components comprises a plurality of redundant control surfaces; and
a plurality of redundant low voltage buses communicatively connected to the plurality of flight components, wherein the plurality of redundant control surfaces include:
a first aileron located on a first fixed wing of the aircraft that is connected to a first redundant low voltage bus;
a second aileron located on the first fixed wing of the aircraft that is connected to a second redundant low voltage bus;
a third aileron located on a second fixed wing of the aircraft that is connected to a third redundant low voltage bus; and
a fourth aileron located on the second fixed wing of the aircraft that is connected to a fourth redundant low voltage bus, wherein the first aileron, the second aileron, the third aileron, and the fourth aileron are each independently electronically controllable; and
a plurality of booms, the plurality of booms including:
a first boom coupled to a first vertical take-off propulsor and a second vertical take-off propulsor, the first boom being perpendicularly coupled to the first fixed wing; and
a second boom coupled to a third vertical take-off propulsor and a fourth vertical take-off propulsor, the second boom being perpendicularly coupled to the second fixed wing.