US 11,866,205 B2
Flying wing aircraft having a two-dimensional thrust array
Levi Charles Hefner, Dallas, TX (US); and Dakota Charles Easley, Dallas, TX (US)
Assigned to Textron Innovations Inc., Providence, RI (US)
Filed by Textron Innovations Inc., Providence, RI (US)
Filed on Apr. 5, 2022, as Appl. No. 17/714,096.
Application 17/714,096 is a continuation of application No. 16/031,786, filed on Jul. 10, 2018, granted, now 11,319,066.
Prior Publication US 2022/0388652 A1, Dec. 8, 2022
This patent is subject to a terminal disclaimer.
Int. Cl. B64D 27/26 (2006.01); B64C 29/02 (2006.01); B64C 11/46 (2006.01); B64U 50/19 (2023.01); B64U 80/00 (2023.01); B64U 30/293 (2023.01); B64U 10/25 (2023.01); B64U 30/20 (2023.01)
CPC B64U 30/293 (2023.01) [B64C 11/46 (2013.01); B64C 29/02 (2013.01); B64D 27/26 (2013.01); B64D 2027/262 (2013.01); B64U 10/25 (2023.01); B64U 30/20 (2023.01); B64U 50/19 (2023.01); B64U 80/00 (2023.01); B64U 2201/10 (2023.01); B64U 2201/20 (2023.01)] 19 Claims
OG exemplary drawing
 
1. An unmanned aircraft system operable for wing-borne lift in a flying wing orientation, the unmanned aircraft system comprising:
an airframe having a leading edge, a trailing edge, a root chord, a first wingtip and a second wingtip, the airframe having an airfoil cross-section along chord stations thereof;
a thrust array coupled to the airframe including first and second motor mounts rotatably coupled to the leading edge respectively between the root chord and the first and second wingtips, the motor mounts each having first and second propulsion assemblies coupled to respective first and second distal ends thereof, the motor mounts each having a flight configuration substantially perpendicular with the leading edge forming a two-dimensional distributed thrust array such that the airframe extends outboard of the first and second motor mounts;
an electric power system operably associated with the thrust array and operable to provide power to each of the propulsion assemblies; and
a flight control system operably associated with the thrust array and operable to independently control the speed of each of the propulsion assemblies;
wherein, the leading edge extends from the root chord to each wingtip with a first positive sweep angle and the trailing edge extends from the root chord to each wingtip with a second positive sweep angle, the first positive sweep angle incongruent with the second positive sweep angle; and
wherein, each of the motor mounts has a storage configuration substantially parallel with the leading edge and extending substantially at the first positive sweep angle.