Fluidic propulsive system and thrust and lift generator for aerial vehicles
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-021/04
B64D-029/02
B64C-039/02
B64D-027/18
B64D-033/02
B64D-033/04
B64C-009/38
B64C-015/00
B64C-021/00
B64D-027/10
출원번호
US-0256178
(2016-09-02)
등록번호
US-10207812
(2019-02-19)
발명자
/ 주소
Evulet, Andrei
출원인 / 주소
JETOPTERA, INC.
대리인 / 주소
Born, P. G. Scott
인용정보
피인용 횟수 :
0인용 특허 :
85
초록▼
A vehicle includes a main body and a gas generator producing a gas stream. At least one fore conduit and tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the at least one fore conduit. At least one tail ejector is fluidly coupled to the at leas
A vehicle includes a main body and a gas generator producing a gas stream. At least one fore conduit and tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the at least one fore conduit. At least one tail ejector is fluidly coupled to the at least one tail conduit. The fore ejectors respectively include an outlet structure out of which gas from the at least one fore conduit flows. The at least one tail ejector includes an outlet structure out of which gas from the at least one tail conduit flows. First and second primary airfoil elements have leading edges respectively located directly downstream of the first and second fore ejectors. At least one secondary airfoil element has a leading edge located directly downstream of the outlet structure of the at least one tail ejector.
대표청구항▼
1. A vehicle, comprising: a main body having a fore portion, a tail portion, a starboard side and a port side;a gas generator coupled to the main body and producing a gas stream;at least one fore conduit fluidly coupled to the generator;at least one tail conduit fluidly coupled to the generator;firs
1. A vehicle, comprising: a main body having a fore portion, a tail portion, a starboard side and a port side;a gas generator coupled to the main body and producing a gas 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 gas 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 gas from the at least one tail conduit flows at a predetermined adjustable velocity;first and second primary airfoil elements having leading edges, the primary airfoil elements respectively coupled to the starboard side and port side, the leading edges of the first and second primary airfoil elements being respectively located directly downstream of the first and second fore ejectors such that the gas from the fore ejectors flows over the leading edges of the primary airfoil elements;at least one secondary airfoil element having a leading edge 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 gas from the at least one tail ejector flows over the leading edge of the at least one secondary airfoil; andfirst 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, wherein the first and second fore electors 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. 2. The vehicle of claim 1, wherein the gas generator is disposed in the main body. 3. The vehicle of claim 1, wherein the gas stream produced by the generator is the sole means of propulsion of the vehicle. 4. 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. 5. 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 perpendicular to the leading edge. 6. 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. 7. 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 perpendicular to the leading edge. 8. The vehicle of claim 1, wherein at least one of the outlet structures is non-circular. 9. The vehicle of claim 1, further comprising a cockpit portion configured to enable manned operation of the vehicle. 10. The vehicle of claim 1, wherein: the gas generator comprises a first region in which the gas stream is at a first temperature and a second region in which the gas stream is at a second temperature, the second temperature higher than the first temperature;the at least one fore conduit provides gas from the first region to the first and second fore ejectors; andthe at least one tail conduit provides gas from the second region to the at least one tail ejector. 11. A vehicle, comprising: a main body having a fore portion, a tail portion, a starboard side and a port side;a gas generator coupled to the main body and producing a gas stream, the gas generator including a first region in which the gas stream is at a first temperature and a second region in which the gas stream is at a second temperature, the second temperature higher than the first temperature;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 gas from the at least one fore conduit flows at a predetermined adjustable velocity, the at least one fore conduit providing gas from the first region to the first and second fore ejectors; andat 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 gas from the at least one tail conduit flows at a predetermined adjustable velocity, the at least one tail conduit providing gas from the second region to the at least one tail ejector. 12. The vehicle of claim 11, further comprising first and second primary airfoil elements having leading edges, the primary airfoil elements respectively coupled to the starboard side and port side, the leading edges of the first and second primary airfoil elements being respectively located directly downstream of the first and second fore ejectors such that the gas from the fore ejectors flows over the leading edges of the primary airfoil elements. 13. The vehicle of claim 11, 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 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. 15. The vehicle of claim 11, wherein the gas generator is disposed in the main body. 16. The vehicle of claim 11, 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. 17. The vehicle of claim 11, 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 perpendicular to the leading edge. 18. The vehicle of claim 11, 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. 19. The vehicle of claim 11, 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 perpendicular to the leading edge. 20. The vehicle of claim 11, wherein at least one of the outlet structures is non-circular. 21. The vehicle of claim 11, further comprising a cockpit portion configured to enable manned operation of the vehicle.
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이 특허에 인용된 특허 (85)
Eigenbrode Daniel E. ; Field Robert E., Aerodynamically controlled ejector.
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Novikov-Kopp, Ivan, Method for comprehensively increasing aerodynamic and transport characteristics, a wing-in-ground-effect craft for carrying out said method (variants) and a method for realizing flight.
Hirt William J. (Bellevue WA) Grotz Charles A. (Seattle WA), Method of and apparatus for enhancing Coanda flow attachment over a wing and flap surface.
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Kress Robert W. (4308 Ulster Landing Rd. Saugerties NY 12477) Stump Joseph W. (42 Derby Pl. Smithtown NY 11787), Unmanned aerial aircraft having a single engine with dual jet exhausts.
Lendriet William C. (8814 Sylmar Ave. Panorama City CA 91402), Vertical/short takeoff or landing aircraft having a rotatable wing and tandem supporting surfaces.
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