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

Patent metadata

Field	Value
Publication number	US-10464668-B2
Application number	US-201715456450-A
Country	US
Kind code	B2
Filing date	Mar 10, 2017
Priority date	Sep 2, 2015
Publication date	Nov 5, 2019
Grant date	Nov 5, 2019

Abstract

A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one fore conduit and at least one tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the fore conduit, 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 is coupled to the tail portion. A surface of the primary airfoil element is located directly downstream of the first and second fore ejectors such that the fluid from the first and second fore ejectors flows over the such surface.

First claim

I claim:

1. A vehicle, comprising:
a main body having a fore portion, a tail portion, a starboard side and a port side;
a fluid generator coupled to the main body and producing a fluid stream;
at least one fore conduit fluidly coupled to the generator;
at least one tail conduit fluidly coupled to the generator;
first and second fore ejectors fluidly coupled to the at least one fore conduit, 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 from the at least one fore conduit 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 having a surface, the primary airfoil element coupled to the tail portion, the surface of the primary airfoil element being located directly downstream of the first and second fore ejectors such that the fluid from the first and second fore ejectors flows over the surface of the primary airfoil element.

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 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.

4. The vehicle of claim 1 , wherein the fluid generator is disposed in the main body.

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

6. 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.

7. The vehicle of claim 1 , further comprising at least one secondary airfoil element having a surface and coupled to the main body, the leading edge of the at least one secondary airfoil element located directly downstream of the outlet structure of the at least one tail ejector such that the fluid from the at least one tail ejector flows over the surface of the at least one secondary airfoil element.

8. 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.

9. The vehicle of claim 1 , wherein the primary airfoil element comprises a closed wing having a leading edge and a trailing edge, the leading and trailing edges of the closed wing defining an interior region.

10. The vehicle of claim 9 , wherein the at least one tail ejector is at least partially disposed within the interior region.

11. The vehicle of claim 10 , wherein the ejector is controllably movable within the interior region.

12. The vehicle of claim 9 , wherein the closed wing further comprises a plurality of control surfaces.

13. 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.

14. A vehicle, comprising:
a main body having a fore portion, a tail portion, a starboard side and a port side;
a fluid generator coupled to the main body and producing a fluid stream;
at least one fore conduit fluidly coupled to the generator;
at least one tail conduit fluidly coupled to the generator;
first and second fore ejectors fluidly coupled to the at least one fore conduit, 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 from the at least one fore conduit 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 having a surface, the primary airfoil element coupled to the tail portion, the surface of the primary airfoil element being located directly downstream of the first and second fore ejectors such that the fluid from the first and second fore ejectors flows over the surface of the primary airfoil element.

15. The vehicle of claim 14 , 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.

16. The vehicle of claim 15 , 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.

17. The vehicle of claim 14 , wherein the fluid generator is disposed in the main body.

18. The vehicle of claim 14 , 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.

19. The vehicle of claim 14 , wherein the primary airfoil element comprises a closed wing having a leading edge and a trailing edge, the leading and trailing edges of the closed wing defining an interior region.

20. The vehicle of claim 19 , wherein the at least one propeller is at least partially disposed within the interior region.

21. The vehicle of claim 19 , wherein the closed wing further comprises a plurality of control surfaces.

22. The vehicle of claim 14 , 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.

23. The vehicle of claim 14 , further comprising a support assembly extending from the tail portion and parallel to the main body.

24. The vehicle of claim 10 , wherein the outlet structure is entirely disposed within the interior region.

25. The vehicle of claim 24 , wherein the outlet structure is disposed in the center of the interior region.

26. The vehicle of claim 1 , wherein the at least one tail ejector compri

Assignees

• Jetoptera Inc

Inventors

• Evulet Andrei

Classifications

• B64U50/14

  ducted or shrouded · CPC title

• B64C29/04 Primary

  characterised by jet-reaction propulsion · CPC title

• B64C39/12

  Canard-type aircraft · CPC title

• B64C9/38

  Jet flaps · CPC title

• B64D29/02

  associated with wings · CPC title