Streamline airframe with boundary ingestion fluidic propulsive elements

Patent metadata

Field	Value
Publication number	US-12466547-B2
Application number	US-202418772910-A
Country	US
Kind code	B2
Filing date	Jul 15, 2024
Priority date	May 29, 2018
Publication date	Nov 11, 2025
Grant date	Nov 11, 2025

Abstract

A vehicle includes a main body and at least one wing coupled to the main body. A source of compressed fluid is coupled to the main body. The vehicle further includes first and second thrusters, each said first and second thruster having an intake structure and each said first and second thruster in fluid communication with the source. The first thruster is coupled to the main body and the second thruster is coupled to the at least one wing. The first and second thrusters are positioned, when in a first configuration, such that at least a portion of a boundary layer produced due to motion of the vehicle is ingested by the intake structures of the first and second thrusters. The vehicle further includes a system for selectively providing the compressed fluid to the first and second thrusters.

First claim

The embodiments of the present disclosure in which an exclusive property or privilege is claimed are defined as follows:

1 . A method, comprising:
ingesting, with a first intake structure of an active first thruster in response to a compressed fluid, at least a portion of a boundary layer produced due to motion of whichever of a vehicle body or a vehicle wing the first thruster is coupled; moving a first internal surface and a first external surface of the active first thruster relative to each other; and activating the first thruster by moving the first thruster to a position outside of whichever of the vehicle body or the vehicle wing the first thruster is coupled.

2 . The method of claim 1 , further comprising:
mixing the compressed fluid with a secondary fluid in a first diffusing structure of the first thruster; and smoothening a spatial temperature profile of a mixture of the compressed fluid and the secondary fluid as the mixture travels from a first throat section to a first terminal end of the first diffusing structure.

3 . The method of claim 1 , further comprising:
mixing the compressed fluid with a secondary fluid in a first diffusing structure of the first thruster; and smoothening a spatial velocity profile of a mixture of the compressed fluid and the secondary fluid as the mixture travels from a first throat section to a first terminal end of the first diffusing structure.

4 . The method of claim 1 , further comprising ingesting, with a second intake structure of an active second thruster in response to the compressed fluid, at least a portion of a boundary layer produced due to motion of the other of the vehicle body or the vehicle wing to which the second thruster is coupled.

5 . The method of claim 4 , further comprising moving a second internal surface and a second external surface of the active second thruster relative to each other.

Assignees

• Jetoptera Inc

Inventors

• Evulet Andrei

Classifications

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F02K1/36

  having an ejector · CPC title

• F02C3/04 Primary

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• B64D2033/0226

  comprising boundary layer control means · CPC title

• B64C23/005

  by other means not covered by groups B64C23/02 - B64C23/08, e.g. by electric charges, magnetic panels, piezoelectric elements, static charges or ultrasounds · CPC title