NZ786055B2 - Configuration for vertical take-off and landing system for aerial vehicles - Google Patents
Configuration for vertical take-off and landing system for aerial vehicles Download PDFInfo
- Publication number
- NZ786055B2 NZ786055B2 NZ786055A NZ78605517A NZ786055B2 NZ 786055 B2 NZ786055 B2 NZ 786055B2 NZ 786055 A NZ786055 A NZ 786055A NZ 78605517 A NZ78605517 A NZ 78605517A NZ 786055 B2 NZ786055 B2 NZ 786055B2
- Authority
- NZ
- New Zealand
- Prior art keywords
- fore
- vehicle
- coupled
- tail
- fluid
- Prior art date
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/001—Shrouded propellers
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
- B64C21/01—Boundary layer ingestion [BLI] propulsion
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
- B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
- B64C21/04—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for blowing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/02—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/02—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
- B64C29/04—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded characterised by jet-reaction propulsion
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/12—Canard-type aircraft
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/10—Drag reduction
Abstract
The invention is a vehicle comprising a main body, a fluid generator coupled to the main body to produce a fluid stream, at least one fore conduit fluidly coupled to the generator and at least one tail conduit fluidly coupled to the generator. The 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, wherein 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, wherein the tail ejector comprises an outlet structure out of which fluid flows. A primary airfoil element is coupled to the tail portion and 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 surface. 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. Conventional VTOL aircrafts lack balance during thrust. The invention aims to distribute thrust generation such that balance is improved.
Claims (20)
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; and 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.
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 at least one tail ejector is at least partially disposed within the interior region.
10. region.
11. The vehicle of claim 9, wherein the ejector is controllably movable within the interior The vehicle of claim 1, wherein the closed wing further comprises a plurality of control surfaces.
12. 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.
13. 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; and 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.
14. The vehicle of claim 13, 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.
15. The vehicle of claim 14, 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.
17. The vehicle of claim 13, wherein the fluid generator is disposed in the main body. The vehicle of claim 13, 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 13, wherein the at least one propeller is at least partially disposed within the interior region.
19. The vehicle of claim 13, wherein the closed wing further comprises a plurality of control surfaces.
20. The vehicle of claim 13, 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.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US201662307318P | 2016-03-11 | 2016-03-11 | |
| NZ746143A NZ746143B2 (en) | 2017-03-10 | Configuration for vertical take-off and landing system for aerial vehicles |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| NZ786055A NZ786055A (en) | 2024-11-29 |
| NZ786055B2 true NZ786055B2 (en) | 2025-03-04 |
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