Configuration for vertical take-off and landing system for aerial vehicles

Patent metadata

Field	Value
Publication number	US-11724803-B2
Application number	US-202117475280-A
Country	US
Kind code	B2
Filing date	Sep 14, 2021
Priority date	Jun 27, 2017
Publication date	Aug 15, 2023
Grant date	Aug 15, 2023

Abstract

A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one tail conduit is fluidly coupled to the generator. First and second fore ejectors are coupled to the main body and respectively coupled to a starboard side and port side of the vehicle. The fore ejectors respectively comprise an outlet structure out of which fluid flows. At least one tail ejector is fluidly coupled to the tail conduit. The tail ejector comprises an outlet structure out of which fluid flows. A primary airfoil element includes a closed wing having a leading edge and a trailing edge. The leading and trailing edges of the closed wing define an interior region. The at least one propulsion device is at least partially disposed within the interior region.

First claim

What is claimed is:

1. A vehicle, comprising:
a main body having a fore portion, a tail portion, a starboard side, a port side and a cockpit formed therein to accommodate a human pilot;
a first fluid generator coupled to the main body and producing a first fluid stream;
at least one tail conduit fluidly coupled to the first generator;
first and second fore ejectors coupled to the portion and respectively coupled to the starboard side and port side, the fore ejectors respectively comprising an outlet structure out of which fluid flows at a predetermined adjustable velocity;
at least one tail ejector fluidly coupled to the at least one tail conduit and coupled to the tail portion, the at least one tail ejector comprising an outlet structure out of which fluid from the at least one tail conduit flows at a predetermined adjustable velocity; and
a primary airfoil element coupled to the tail portion and comprising a closed wing having a leading edge and a trailing edge, the leading and trailing edges of the closed wing defining an interior region, the at least one tail ejector being at least partially disposed within the interior region and detached from the closed wing.

2. The vehicle of claim 1 , further comprising first and second canard wings coupled to the fore portion and respectively coupled to the starboard side and port side, the canard wings configured to develop boundary layers of ambient air flowing over the canard wings when the vehicle is in motion, the canard wings being respectively located directly upstream of the first and second fore ejectors such that the first and second fore ejectors are fluidly coupled to the boundary layers.

3. The vehicle of claim 2 , wherein the first and second canard wings each have a leading edge, and the entirety of each of the first and second canard wings is rotatable about an axis oriented parallel to the leading edge.

4. The vehicle of claim 2 , wherein the first and second fore ejectors respectively comprise first and second inlet portions, and the first and second fore ejectors are positioned such that the boundary layers are ingested by the inlet portions.

5. The vehicle of claim 1 , further comprising:
second and third fluid generators coupled to the main body and respectively producing a second fluid stream and a third fluid stream; and
first and second fore conduits respectively fluidly coupled to the second and third generators, wherein the first and second fore ejectors are respectively fluidly coupled to the first and second fore conduits and respectively receive the second and third fluid streams.

6. The vehicle of claim 1 , wherein the first fluid stream produced by the first generator is the sole means of propulsion of the vehicle.

7. The vehicle of claim 1 , wherein the first and second fore ejectors each have a leading edge, and the entirety of each of the first and second fore ejectors is rotatable about an axis oriented parallel to the leading edge.

8. The vehicle of claim 1 , wherein the first and second fore ejectors are retractable into the main body during a cruise condition of the vehicle.

9. The vehicle of claim 1 , wherein the at least one tail ejector has a leading edge, and the entirety of the at least one tail ejector is rotatable about an axis oriented parallel to the leading edge.

10. The vehicle of claim 1 , wherein the tail ejector is controllably movable relative to the interior region while the vehicle is in flight.

11. The vehicle of claim 1 , wherein:
the fluid generator comprises a first region in which the fluid stream is at a low temperature and a second region in which the fluid stream is at a high temperature;
the at least one fore conduit provides fluid from the first region to the first and second fore ejectors; and
the at least one tail conduit provides fluid from the second region to the at least one tail ejector.

12. A vehicle, comprising:
a main body having a fore portion, a tail portion, a starboard side, a pert side and a cockpit to accommodate a human pilot;
a first fluid generator coupled to the main body and producing a first fluid stream;
at least one tail conduit fluidly coupled to the first generator;
first and second fore ejectors coupled to the fore portion and respectively coupled to the starboard side and port side, the fore ejectors respectively comprising an outlet structure out of which fluid flows at a predetermined adjustable velocity;
at least one propeller fluidly coupled to the at least one tail conduit and coupled to the tail portion, and
a primary airfoil element comprising a closed wing having a leading edge and a trailing edge, the leading and trailing edges of the closed wing, defining, an interior region, the at least one propeller being at least partially disposed within the interior region and detached from the closed wing.

13. The vehicle of claim 12 , further comprising first and second canard wings coupled to the fore portion and respectively coupled to the starboard side and port side, the canard wings configured to develop boundary layers of ambient air flowing over the canard wings when the vehicle is in motion, the canard wings being respectively located directly upstream of the first and second fore ejectors such that the first and second fore ejectors are fluidly coupled to the boundary layers.

14. The vehicle of claim 13 , wherein the first and second canard wings each have a leading edge, and the entirety of each of the first and second canard wings is rotatable about an axis oriented parallel to the leading edge.

15. The vehicle of claim 13 , wherein the first and second fore ejectors respectively comprise first and second inlet portions, and the first and second fore ejectors are positioned such that the boundary layers are ingested by the inlet portions.

16. The vehicle of claim 12 , further comprising:
second and third fluid generators coupled to the main body and respectively producing a second fluid stream and a third fluid stream; and
first and second fore conduits respectively fluidly coupled to the second and third generators, wherein the first and second fore ejectors are respectively fluidly coupled to the first and second fore conduits and respectively receive the second and third fluid streams.

17. The vehicle of claim 12 , wherein the first and second fore ejectors each have a leading edge, and the entirety of each of the first and second fore ejectors is rotatable about an axis oriented parallel to the leading edge.

18. The vehicle of claim 12 , wherein tare first and second fore ejectors are retractable into the main body during a cruise condition of the vehicle.

19. The vehicle of claim 12 , wherein:
the fluid generator comprises a first region in which the fluid stream is at a low temperature and a second region in which the fluid stream is at a high temperature;
the at least one fore conduit provides fluid from the first region to the first and second fore ejectors; and
the at least one tail conduit provides fluid from the second region to a turbine coupled to the at least one propeller.

20. A vehicle, comprising:
a main body having a fore portion, a tail portion, a starboard side, a port side and a cockpit to accommodate a human pilot;
at least one propulsion device coupled to the tail portion, the at least one propulsion device comprising an outlet structure out of which fluid from the at least one propulsion device flows at a predetermined adjustable velocity; and
a primary airfoil element comprising a closed wing having a leading edge and a t

Assignees

• Jetoptera Inc

Inventors

• Evulet Andrei

Classifications

• B64C29/04 Primary

  characterised by jet-reaction propulsion · CPC title

• B64C39/12

  Canard-type aircraft · CPC title

• B64C3/10

  Shape of wings · CPC title

• B64D33/04

  of exhaust outlets or jet pipes · CPC title

• B64C39/066

  having channel wings · CPC title