US 11,999,502 B2
Aerial vehicle architectures for improved thrust efficiency and internal cooling
Glen Johannesson, Waterloo (CA); Albert Pegg, New Dundee (CA); and Dmytro Silin, Waterloo (CA)
Assigned to FLIR Unmanned Aerial Systems ULC, Vancouver (CA)
Filed by FLIR Unmanned Aerial Systems ULC, Vancouver (CA)
Filed on Apr. 23, 2021, as Appl. No. 17/239,514.
Claims priority of provisional application 63/019,185, filed on May 1, 2020.
Prior Publication US 2022/0009647 A1, Jan. 13, 2022
Int. Cl. B64D 33/08 (2006.01); B64C 27/08 (2023.01); B64C 27/20 (2023.01); B64C 39/02 (2023.01); B64U 10/13 (2023.01); B64U 30/20 (2023.01); B64U 50/14 (2023.01)
CPC B64D 33/08 (2013.01) [B64C 27/08 (2013.01); B64C 27/20 (2013.01); B64C 39/024 (2013.01); B64U 10/13 (2023.01); B64U 30/20 (2023.01); B64U 50/14 (2023.01)] 18 Claims
OG exemplary drawing
 
1. An airframe assembly for an unmanned aerial vehicle (UAV), the airframe assembly comprising:
a top airframe assembly comprising a top foam airframe core at least partially enclosed within a top airframe shell; and
a bottom airframe assembly comprising a bottom foam airframe core at least partially enclosed within a bottom airframe shell and coupled to the top airframe assembly, wherein:
the top and bottom foam airframe cores form one or more rotor ducts;
each rotor duct comprises an inlet and a diffusor outlet shaped to increase a thrust efficiency of a propulsion system for the UAV;
the top airframe assembly comprises a metal heat sink assembly disposed at least partially between the top foam airframe core and the top airframe shell and configured to cool at least power electronics of the UAV; and
the top airframe shell comprises a plurality of cooling air inlet orifices configured to allow ambient air to reach a dissipation surface of the metal heat sink assembly.