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KR20230145238A - 유체 추진 시스템 - Google Patents

유체 추진 시스템 Download PDF

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KR20230145238A
KR20230145238A KR1020237033734A KR20237033734A KR20230145238A KR 20230145238 A KR20230145238 A KR 20230145238A KR 1020237033734 A KR1020237033734 A KR 1020237033734A KR 20237033734 A KR20237033734 A KR 20237033734A KR 20230145238 A KR20230145238 A KR 20230145238A
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vehicle
coupled
propulsion system
airfoil
primary
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KR1020237033734A
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안드레이 에불렛
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제톱테라 잉크.
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • B64C9/38—Jet flaps
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C15/00—Attitude, flight direction, or altitude control by jet reaction
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C15/00—Attitude, flight direction, or altitude control by jet reaction
    • B64C15/14—Attitude, flight direction, or altitude control by jet reaction the jets being other than main propulsion jets
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
    • B64C23/005—Influencing air flow over aircraft surfaces, not otherwise provided for by other means not covered by groups B64C23/02 - B64C23/08, e.g. by electric charges, magnetic panels, piezoelectric elements, static charges or ultrasounds
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/02—Aircraft not otherwise provided for characterised by special use
    • B64C39/024—Aircraft not otherwise provided for characterised by special use of the remote controlled vehicle type, i.e. RPV
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/10—Aircraft characterised by the type or position of power plants of gas-turbine type 
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/16—Aircraft characterised by the type or position of power plants of jet type
    • B64D27/18—Aircraft characterised by the type or position of power plants of jet type within, or attached to, wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • B64D29/02—Power-plant nacelles, fairings, or cowlings associated with wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/10—Wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/15—Propulsion using combustion exhausts other than turbojets or turbofans, e.g. using rockets, ramjets, scramjets or pulse-reactors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/002—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto with means to modify the direction of thrust vector
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/36—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto having an ejector
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/04—Boundary layer controls by actively generating fluid flow
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/06—Boundary layer controls by explicitly adjusting fluid flow, e.g. by using valves, variable aperture or slot areas, variable pump action or variable fluid pressure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/16—Boundary layer controls by blowing other fluids over the surface than air, e.g. He, H, O2 or exhaust gases
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0266—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants
    • B64D2033/0273—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants for jet engines
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/25—Fixed-wing aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U20/00—Constructional aspects of UAVs
    • B64U20/60—UAVs characterised by the material
    • B64U20/65—Composite materials
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/90—Application in vehicles adapted for vertical or short take off and landing (v/stol vehicles)
    • 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
    • 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
    • Y02T50/30—Wing lift efficiency
    • 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
    • Y02T50/40—Weight reduction
    • 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
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Jet Pumps And Other Pumps (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Other Liquid Machine Or Engine Such As Wave Power Use (AREA)
  • Toys (AREA)
  • Valves And Accessory Devices For Braking Systems (AREA)
  • Pipeline Systems (AREA)

Abstract

본 발명은 운송수단에 결합된 추진 시스템에 관한 것이다. 상기 시스템은 볼록 표면, 상기 볼록 표면에 결합된 분산 구조물, 및 상기 볼록 표면에 결합된 하나 이상의 관을 포함한다. 상기 관은 운송수단에 의해 형성된 일차 유체를 볼록 표면에 주입시키도록 구성된다. 상기 시스템은 볼록 표면에 결합되고 운송수단에 접근 가능한 이차 유체를 분산 구조물에 주입시키도록 구성된 흡기 구조물을 추가로 포함한다. 상기 분산 구조물은, 주입된 일차 유체와 이차 유체를 위해, 시스템으로부터 배출을 제공하도록 구성된 말단 단부를 포함한다.

Description

유체 추진 시스템{Fluidic propulsive system}
본 발명은 운송수단에 결합된 추진 시스템에 관한 것이다.
본 특허출원은 2015년 9월 2일에 출원된 미국 가특허출원번호 62/213,465호를 기초로 우선권을 주장하고 있으며, 상기 미국 특허출원은 전반적으로 본 명세서에 설명된 것과 같이 참조문헌으로서 통합된다.
일반적으로, 호버링(hovering) 할 수 있으며, 수직으로 이륙하고 착륙할 수 있는 항공기는 수직 이착륙(Vertical Take-Off and Landing: VTOL) 항공기로 지칭된다. 이러한 분류에는, 고정익 항공기(fixed-wing aircraft) 뿐만 아니라 헬리콥터 및 틸트형 파워 로터(tiltable powered rotor)가 장착된 항공기가 포함된다. 일부 VTOL 항공기는 그 밖의 모드(mode), 가령, 단거리 이착륙(Short Take-Off and Landing: STOL) 모드에서 작동할 수 있다. VTOL은 V/STOL(수직 및/또는 단거리 이착륙)의 한 부분에 속한다.
오직, 예시적인 목적으로, 현재, VTOL 기능을 가진 비행기의 한 예는 F-35 라이트닝 전투기이다. 수직 상승 기류(vertical lift airflow)를 벡터링(vectoring) 하는 종래의 방법들은, 서로 90°로 배열되며 외부 노즐(external nozzle)에 위치된 2개 세트의 평평한 플래퍼 베인(flapper vane)을 사용하여 한 방향으로 스위블회전(swiveled) 할 수 있는 노즐을 사용하는 방법을 포함한다. 이와 비슷하게, F-35 라이트닝 전투기의 추진 시스템은, 수직으로 배열된 리프트 팬(lift fan)과 터빈 엔진(turbine engine)으로부터 나오는 벡터링 추력(vectored thrust)의 조합을 이용하는 수직 양력(vertical lifting force)을 제공한다. 리프트 팬은 상측 및 하측 좌우대향형 도어(clamshell door)를 가진 베이(bay)의 조종석(cockpit) 뒤에 위치된다. 엔진은 추력을 수평 방향으로부터 단지 수직의 전방으로 편향시킬(deflect) 수 있는 3-베어링 스위블 노즐(swivel nozzle)을 통해 배기한다(exhaust). 각각의 윙(wing)에서 롤 컨트롤 덕트(roll control duct)가 연장되며, 엔진 팬으로부터 나온 공기와 함께 추력이 공급된다. 리프트 팬/엔진 추력 스플릿(engine thrust split)에 의해 피치 컨트롤(pitch control)이 구현된다. 엔진 스위블 노즐의 요 운동(yaw motion)을 통해 요 컨트롤(yaw control)이 수행된다.롤 컨트롤은 2개의 롤 컨트롤 덕트의 단부(end)에 있는 구멍(aperture)을 선택적으로(differentially) 개폐함으로써 제공된다. 리프트 팬은 선수 및 선미 방향으로 추력 편향(thrust deflection)을 제공하기 위해 텔레스코프식(telescoping) "D" 형태의 노즐을 가진다. 이러한 D-형태의 노즐은 배출구(exit aperture)에서 고정 베인(fixed vane)을 가진다.
항공기 또는 드론(drone)의 디자인은 일반적으로 추진 요소(propulsive element) 및 이러한 추진 요소들이 통합된(integrated) 기체(airframe)로 구성된다. 통상, 항공기 내의 추진 장치는 터보제트(turbojet), 터보팬(turbofan), 터보프롭(turboprop) 또는 터보샤프트(turboshaft), 피스톤 엔진(piston engine), 또는 프로펠러(propeller)가 구비된 전기 모터(electric motor)일 수 있다. 소형 무인항공기(Unmanned Aerial Vehicle: UAV) 내의 추진 시스템(propulsive system)(추진기(propulsor))은 통상 피스톤 엔진 또는 샤프트에 의해 하나 이상의 프로펠러에 파워를 제공하는 전기 모터이다. 대형 항공기의 추진기는, 무인항공기 또는 유인 항공기 경우 모두, 통상적으로 제트 엔진 또는 터보프롭이다. 추진기는 일반적으로 힘(force)을 항공기에 전달할 수 있으며 하중을 지탱할 수 있는 스트럿(strut) 또는 지시탑(pylon)에 의해 동체(fuselage) 또는 항공기 바디(body) 또는 윙(wing)에 결부된다(attached). 가스(gas)와 공기의 혼합 제트(mixed jet)(제트 이플럭스(jet efflux))는 항공기를 제트 이플럭스의 흐름 방향과 반대 방향으로 추진시키는 제트이다.
일반적으로, 대형 프로펠러의 공기 스트림 이플럭스(air stream efflux)는 수평 비행(level flight)에서 상승 목적으로는 사용되지 않으며, 그에 따라, 오늘날 존재하는 일부 용도에서 스위블회전(swiveled) 되지 않는 한(가령, 벨 보잉사의 V-22 오스프리 항공기), 상당한 양의 운동에너지(kinetic energy)는 항공기에 사용되지 않는다. 대신, 대부분의 기존 항공기의 양력은 윙(wing)과 테일(tail)에 의해 생성된다. 게다가, 특히, 오스프리에서 발견되는 VTOL 용도(예컨대, 이륙 후 수평 비행으로의 전환)에서, 프로펠러 자체에 의해 야기되는 양력은 수평 비행 동안에는 최소가 되며, 대부분의 양력은 윙으로부터 생성된다.
현재, 항공기에서 양력을 생성하기 위한 기술은 윙 및 일반적으로 에어포일(airfoil)인 윙 요소(wing element)에 고속의 기류(airflow)를 생성하는 것이다. 에어포일은 축방향으로, 에어포일의 리딩 에지(leading edge)로부터 트레일링 에지(trailing edge)로 연장되는 시위선(chord line)을 특징으로 한다. 시위선과 입사 기류(incident airflow) 사이의 형성된 받음각(angle of attack), 및 에어포일 양력 생성 원리에 따르면, 흡입 면(상측 면)에는 저압의 공기가 흐르지만, 베르누이 법칙에 의해, 하측 면(압력 면)보다 더 높은 속도로 이동한다. 항공기의 공기속도(airspeed)가 낮으면 낮을수록, 양력이 낮아지고, 이륙 시를 포함하여, 윙의 큰 표면적 또는 큰 입사각(angle of incidence)이 요구된다.
대형 UAV도 이러한 법칙에 예외는 아니다. 양력은, 적절한 받음각, 코드, 익폭(wingspan), 및 캠버선(camber line)을 가진 윙 에어포일을 디자인함으로써 생성된다. 플랩(flap), 슬롯(slot) 및 그 밖의 다수의 장치들은, 윙의 표면적과 양력 계수(lift coefficient)를 증가시킴으로써 양력을 최대화시키기 위한 종래의 또 다른 도구들이지만 항공기의 공기-속도에 상응하는 양력을 생성할 것이다. (표면적(S)과 양력 계수(CL)를 증가시키면, 공식 L = ½ ρV2SCL에 따라, 낮은 항공기 공기속도(V0)에서 비슷한 크기의 양력이 생성될 수 있지만, 항력과 중량이 늘어난다). 이러한 현재 기술은 거센 측풍(cross wind)의 조건 하에서는 효율성이 현저하게 떨어진다는 점에서 바람직하지 못하다.
소형 UAV가 운송수단을 상승시키기 위해 프로펠러에 의해 생성된 추력(thrust)을 사용하지만, 현재 기술은 전기 모터 속도를 조절하는 방법에 매우 좌우되며, 소형 UAV는 추력과 양력을 생성하거나, 또는 프로펠러를 기울임으로써(tilting) 수평 비행으로 전환시키기 위해 모터를 스위블회전 시키는 기능을 가지거나 가지지 않을 수도 있다. 게다가, 이러한 추진 요소를 이용하는 소형 UAV는 배터리(battery), 파워 밀도(power density)에 있어서 비효율적이며, 대형 프로펠러는 호버링(hovering)에는 효율적이지만 수평 비행에는 비효율적일 수 있고 빠르게 움직이는 블레이드(blade)의 끝단(tip)으로 인해 작동 시에 위험과 문제점을 야기시킬 수 있다. 대부분의 현재의 쿼드콥터(quadcopter)와 그 밖의 전기-작동식 항공기는 오직 매우 짧은 비행시간 동안 작동할 수 있으며, 효율적인 양력을 생성하거나 대형 페이로드(payload)를 운반할 수 없는데, 이는 전기 모터 시스템과 배터리의 중량이 이미 운송수단의 중량의 70%를 초과하기 때문이다. 제트 연료 또는 일반적으로 대중교통(transportation)에 사용되는 임의의 그 밖의 탄화수소 연료를 이용하는, 이와 비슷한 운송수단은 보다 사용가능한 연료를 10배 이상만큼 수용할 것이다. 이는, 배터리 시스템에 비해 탄화수소 연료의 훨씬 높은 에너지 밀도(energy density) 뿐만 아니라 탄화수소 연료-기반의 시스템의 낮은 중량 대 전체 운송수단 중량비(weight ratio)에 의해 설명될 수 있다.
따라서, 항공기, 특히, UAV 및 특정 유인항공기에 있어서, 우수한 효율성, 향상된 성능, 및 그 밖의 진보된 기술에 대한 필요성이 요구된다.
본 특허출원은 본 발명의 하나 또는 그 이상의 실시예들을 기술하기 위한 것이다. 용어, 가령, "해야 한다(must)" 또는 "할 것이다(will)" 등과 같은 용어들과 특정 양을 나타내는 용어를 사용하는 것은, 이러한 실시예들 중 하나 또는 그 이상의 실시예에 적용될 수 있다는 것을 의미하는 것이지, 반드시 이러한 실시예들일 필요는 없는 것으로 이해하면 된다. 그에 따라, 본 발명의 실시예들은 이러한 용어들에 관해 기술한 하나 또는 그 이상의 특징 또는 기능들의 변형예를 생략하거나 또는 포함할 수 있다. 또한, 본 특허출원의 발명의 명칭은 단지 참조 목적으로만 제공될 뿐 본 발명의 의미 또는 해석에 어떠한 방식으로도 영향을 미치는 것이 아니다.
본 발명의 한 실시예는 주변 공기(ambient air)의 혼입(entrainment)과 가속을 위해 유체소자(fluidics)를 사용하고, 고압 가스(가스 생성기로부터 추진기에 공급되는)과 혼입된 주변 공기의 혼합물의 고속 제트 이플럭스(jet efflux)를 전달하는 추진기를 포함한다. 실질적으로, 상기 목적은 가스를 볼록 표면(convex surface)에 인접하게 배출함으로써 구현된다. 볼록 표면은 1936년 9월 1일에 Henri Coanda에 허여된 미국 특허번호 2,052,869호에 기술된 코안다 효과(Coanda effect)에 따른, 소위, 코안다 표면(Coanda surface)이다.
기본적으로, 코안다 효과는, 벽의 곡률(curvature)의 방향이 제트의 축(axis)으로부터 멀어지는 방향이라 하더라도, 제트-발산 가스(jet-emitted gas) 또는 액체가 벽의 윤곽(contour)에 가까이 이동하려는 경향이다. 하나 또는 그 이상의 실시예들에 대해, 본 명세서에서 논의되는 볼록한 코안다 표면은 임의의 특정 재료(material)로 구성될 필요는 없다.
도 1은 내류(internal flow) 속의 온도와 속도의 프로파일과 이젝터의 상측 절반부를 보여주는 본 발명의 한 실시예의 횡단면도;
도 2는 한 실시예에 따른 도 1의 이젝터의 표면의 특징들을 예시한 도면;
도 3-4는 하나 또는 그 이상의 실시예에 따른 흡기 구조물의 부분 투시도;
도 5는 한 실시예에 따른 액츄에이터의 배면 평면도;
도 6은 한 실시예에 따른 이젝터 내부 기하학적 형상의 대안의 횡단면도;
도 7은 대안의 실시예의 측면 투시도;
도 8은 도 7에 예시된 실시예의 한 요소의 측면도;
도 9-11은 본 발명의 또 다른 대안의 실시예를 예시한 도면.
도 1은 운송수단(vehicle)(도시되지 않음), 가령, 비-제한적인 예로서, UAV(Unmanned Aerial Vehicle: 무인항공기) 또는 유인항공기(manned aerial vehicle), 가령, 비행기에 결부될(attached) 수 있는 이젝터(200)의 상측 절반부(upper half)의 횡단면도를 예시한 도면이다. 플리넘(plenum)(211)에는, 예를 들어, 운송수단에 의해 사용될 수 있는 연소-기반의 엔진으로부터, 주변보다 더 뜨거운 공기(즉 압축성 운동 가스 스트림)가 공급된다. 화살표(600)로 표시된, 상기 압축성 운동 가스 스트림(pressurized motive gas stream)은 하나 이상의 관, 가령, 일차 노즐(203)을 통해 이젝터(200)의 내부로 주입된다. 보다 구체적으로, 일차 노즐(203)은 운동 유체 스트림(600)을 벽 제트(wall jet)로서 볼록한 코안다 표면(204)에 걸쳐 가변적인(variable) 사전결정된 원하는 속도로 직접 가속하도록 구성된다. 게다가, 일차 노즐(203)은 조절가능한 부피의 유체 스트림(600)을 제공한다. 또한, 벽 제트는 흡기 구조물(206)을 통해 이차 유체, 가령, 정지 상태에 있거나 혹은 0이 아닌 속도로 화살표(1)로 표시된 방향으로 이젝터(200)에 접근할 수 있는 주변 공기를 혼입하도록 사용된다. 다양한 실시예들에서, 노즐(203)은 어레이(array)로 배열될 수 있으며, 곡선 배열방향, 나선형 배열방향, 및/또는 지그재그 배열방향으로도 위치될 수 있다.
공기(1)와 스트림(600)의 혼합물은 이젝터(200)의 스로트 섹션(225)에서 전적으로 축방향으로 이동될 수 있다. 분산 구조물(diffusing structure), 가령, 디퓨저(210)에서 분산(diffusion)을 통해, 혼합 및 확산(smoothing out) 공정이 지속되어, 이젝터(200)의 축방향으로 속도(700)와 온도(800)의 프로파일(profile)이 더 이상 스로트 섹션(225)에 존재하는 높고 낮은 값들을 가지는 것이 아니라 디퓨저(210)의 말단 단부(100)에서 보다 균일하게 된다. 공기(1)와 스트림(600)의 혼합물이 접근할 때, 말단 단부(100)의 출구 평면(exit plane), 온도 및 속도 프로파일은 거의 균일하다. 특히, 혼합물의 온도는, 에어포일(airfoil), 가령, 윙(wing) 또는 컨트롤 표면(control surface)을 향해 안내되도록 충분히 낮다.
한 실시예에서, 도 2에서 가장 잘 예시된 것과 같이, V-형태의 와류(vortex) 생성 이차 노즐(205)들이 일반적인 직사각형 일차 노즐(203)에 비해 엇갈리게 배열되고(staggered), 유체 스트림 질량흐름(massflow)이 노즐(203)에 의해 추후에 주입되는 순간 전에 전체 유체 스트림(600)의 적어도 25%로 주입된다. 노즐(203)에 의해 주입되기 전에 노즐(205)에 의해 주입되면, 이젝터(200)의 성능을 현저하게 향상시키기에 충분한 높은 혼입 속도(entrainment rate)가 생성된다. 이차 노즐(205)은 전단 층(shear layer)을 통해 보다 바람직한 혼입된 이차 흐름을 주입시키고 일차 노즐(203)에 대해 축방향과 주변 방향으로(circumferentially) 엇갈리게 배열된다.
일차 노즐(203)은 최내측 면에서 일차 노즐(203) 구조물의 중앙 지점에 연결된 지지 레그가 제공된 델타-윙 구조물(226)을 포함할 수 있는데, 델타-윙 구조물의 정점(apex)은 유체 스트림(600) 흐름에 반대로 향한다(pointing against). 이 델타-윙 구조물은 방향이 서로 반대인 2개의 소용돌이(vortices)를 생성하며, 일차 노즐(203)의 양면에서 강하게 혼입되어, 노즐(205)로부터 일차 및 이차 유체 흐름의 혼입된 혼합물이 흐르게 된다.
추가로, 한 실시예가 요소(element), 가령, 코안다 표면(204)에 배열된 함몰부(221)에 의해 흐름 분리(flow separation)를 지연(delay)시키기 위하여 표면을 향상시킨다(improve). 함몰부(221)는 흐름 분리를 방지하고 이젝터(200)의 성능을 현저하게 향상시킨다. 또한, 디퓨저(210)(도 1 참조)의 표면도 함몰부(222) 및/또는 경계층이 분리되는 것을 지연시키거나 방지하는 그 밖의 요소들을 포함할 수 있다.
한 실시예에서, 흡기 구조물(206)은 원형의 형상을 가질 수 있다. 하지만, 다양한 실시예들에서, 그리고, 도 3-4에서 가장 잘 도시된 것과 같이, 흡기 구조물(206)은 비-원형으로 형성될 수 있으며, 실제로는, 비대칭(즉 흡기 구조물을 양분하는 하나 이상의 또는 대안으로 임의의 주어진 평면의 양쪽에서 똑같지 않은)으로 형성될 수도 있다. 예를 들어, 도 3에 가장 잘 도시된 것과 같이, 흡기 구조물(206)은 제1 및 제2 마주보는 에지(301, 302)를 포함할 수 있는데, 제2 마주보는 에지는 제1 마주보는 에지를 향해 돌출되는 곡선 부분을 포함한다. 도 4에 도시된 것과 같이, 흡기 구조물(206)은 제1 및 제2 횡방향 마주보는 에지(lateral opposing edge)(401, 402)를 포함할 수 있는데, 제1 횡방향 마주보는 에지는 제2 횡방향 마주보는 에지보다 더 큰 곡률반경을 가진다.
도 5를 보면, 한 실시예가 이젝터(200)를 운송수단(502)에 결합하는 하나 이상의 작동 요소(actuating element)(501)를 포함할 수 있다. 작동 요소(501)는 운송수단(502)에 대한 이젝터(200)의 2차원 이상의 운동, 바람직하게는 3차원의 운동(즉 6 자유도)을 제공하도록 구성된다.
도 6을 보면, 한 실시예가 이젝터(200)의 내측 표면(605, 606)과 외측 표면(603, 604) 사이에 배열된 하나 이상의 내부 작동 요소(예컨대, 액츄에이터 및/또는 연결장치(linkage))(601, 602)를 포함할 수 있다. 예시된 실시예에서, 액츄에이터(601)는, 제2 표면이 움직이지 않을 때, 제1 표면(605)을 제2 표면(606)에 대해 움직이도록(예컨대, 이젝터(200)의 중심축을 향해 움직이거나 중심축으로부터 멀어지게끔 움직이도록) 구성된다. 이와 비슷하게, 제2 액츄에이터(602)는, 제1 표면이 움직이지 않을 때, 제2 표면(606)이 제1 표면(605)에 대해 움직이도록 구성된다. 이젝터(200)의 내부 기하학적 형상(internal geometry)을 다수의 형상들로 변경시킬 수 있는 이러한 기능으로 인해, 이젝터는 다수의 비행 조건(예컨대, 이륙, 착륙, 순항 비행 등)에서 최적으로 작동될 수 있다.
도 7은 대안의 실시예에 따른 운송수단(700)을 위한 추진 시스템을 예시한다. 제1 이차 에어포일(702)이 운송수단(700)에 결합되고 운송수단의 일차 에어포일(701)에 흐르는 유체의 하류에(downstream) 위치된다. 에어포일(702)은 액츄에이터(708)에 의해 조절되고 축(707) 주위로 회전되도록 구성된다. 도 8에 가장 잘 예시된 것과 같이, 제1 이차 에어포일(702)은 제1 출력 구조물(output structure), 가령, 마주보는 노즐 표면(705, 706)과 하나 이상의 관, 가령, 노즐 표면들에 의해 형성된 말단 단부(703)와 유체 소통(fluid communication)되는 플리넘(704)을 포함한다. 노즐 표면(705, 706)은 도 1에 관해 위에서 논의된 노즐(203)들과 비슷한 노즐을 포함하거나 또는 포함하지 못할 수도 있다. 또한, 노즐 표면(705, 706) 중 하나 또는 그 이상은 코안다 효과를 촉진하고 날카롭거나 가파른 코너(corner)를 가지지 않은 연속적인 둥근 표면(rounded surface)을 가질 수 있는 볼록 표면을 포함할 수 있다. 플리넘(704)에는 예를 들어, 운송수단(700)에 의해 사용될 수 있는 연소-기반의 엔진으로부터 주변보다 더 뜨거운 공기(즉 압축성 운동 가스 스트림)가 공급된다. 플리넘(704)은 가스 스트림을 말단 단부(703)로 주입시켜, 제1 이차 에어포일(702)로부터 나와서 일차 에어포일(701)을 향하는 가스 스트림의 배출을 제공하도록 구성된다.
도 9-11을 보면, 한 실시예가 에어포일(702)과 비슷한 제2 이차 에어포일(902)을 포함할 수 있는데, 이들은 다른 트레일링 에지(trailing edge)로부터 분기되는(diverging) 각각의 트레일링 에지(714, 914)를 가진다. 보다 구체적으로, 제2 이차 에어포일(902)은 운송수단(700)에 결합되며 운송수단의 일차 에어포일(701)에 흐르는 유체의 하류에 위치된다. 에어포일(902)은 에어포일(702)에 관해 위에서 논의된 것과 유사하게 회전하도록 구성된다. 에어포일(902)은 제1 출력 구조물, 가령, 마주보는 노즐 표면(905, 906)과 하나 이상의 관, 가령, 노즐 표면들에 의해 형성된 말단 단부(903)와 유체 소통되는 플리넘(904)을 포함한다. 노즐 표면(905, 906)은 도 1에 관해 위에서 논의된 노즐(203)들과 비슷한 노즐을 포함하거나 또는 포함하지 못할 수도 있다. 또한, 노즐 표면(905, 906) 중 하나 또는 그 이상은 코안다 효과를 촉진할 수 있는 볼록 표면을 포함할 수 있다. 플리넘(704)에는 예를 들어, 운송수단(700)에 의해 사용될 수 있는 연소-기반의 엔진으로부터 주변보다 더 뜨거운 공기(즉 압축성 운동 가스 스트림)가 공급된다. 플리넘(904)은 가스 스트림을 말단 단부(903)로 주입시켜, 제2 이차 에어포일(902)로부터 나와서 일차 에어포일(701)을 향하는 가스 스트림의 배출을 제공하도록 구성된다.
각각의 제1 및 제2 이차 에어포일(702, 902)은 일차 에어포일을 향해 배열된 리딩 에지(716, 916)를 가지며, 제1 이차 에어포일은 제2 이차 에어포일과 마주보는 상태로 배열된다. 작동 시에, 제1 및 제2 이차 에어포일(702, 902)은, 위에서 논의된 디퓨저(210)와 기능이 비슷하며, 길이를 따라 그 사이에 위치된 분산 영역(802)을 형성한다. 리딩 에지(716, 916)들은, 일차 에어포일(701)에 흐르는 유체와 플리넘(704, 904)으로부터 나오는 가스 스트림을 분산 영역(802)에 수용하고 주입시키도록 구성된 흡기 영역(804)을 형성한다. 분산 영역(802)은 일차 에어포일(701)에 흐르는 유체와 주입된 가스 스트림을 위한 분산 영역으로부터 배출을 제공하도록 구성된 일차 말단 단부(806)을 포함한다.
위에서 기술된 설명 내용이 다수의 상이한 실시예들을 상세하게 기술하고 있지만, 본 발명의 보호 범위는 하기 청구항들에 의해 정의된다는 것을 이해해야 한다. 따라서, 발명의 상세한 설명은, 모든 가능한 실시예들을 기술하는 것이 실용적이지도 않으며 가능하지도 않기 때문에, 단지 대표적인 예들만을 기술하는 것이며 모든 가능한 실시예를 기술하는 것이 아니라는 사실도 이해해야 한다. 현재 기술 또는 본 특허출원을 출원하고 난 뒤에 개발된 기술을 이용하여, 다수의 대안의 실시예들도 수행될 수 있으며, 이들 또한 청구범위 내에 있는 것이다.
따라서, 하기 청구범위의 범위 및 사상으로부터 벗어나지 않고도, 본 명세서에 기술되고 예시된 구성 및 기술 내에서, 다수의 변형예 및 변경예들이 가능할 것이다. 그에 따라, 본 명세서에 기술된 장치 및 방법들은 오직 예시적인 것들이며 하기 청구항들의 범위를 제한하는 것이 아닌 것으로 이해해야 한다.

Claims (20)

  1. 운송수단에 결합된 추진 시스템에 있어서, 상기 시스템은:
    볼록 표면;
    상기 볼록 표면에 결합된 분산 구조물;
    볼록 표면에 결합되고 운송수단에 의해 형성된 일차 유체를 볼록 표면에 주입시키도록 구성된 하나 이상의 관; 및
    볼록 표면에 결합되고 운송수단에 접근 가능한 이차 유체를 분산 구조물에 주입시키도록 구성된 흡기 구조물을 포함하되, 상기 분산 구조물은, 주입된 일차 유체와 이차 유체를 위해, 시스템으로부터 배출을 제공하도록 구성된 말단 단부를 포함하는 것을 특징으로 하는 운송수단에 결합된 추진 시스템.
  2. 제1항에 있어서, 볼록 표면은 복수의 리세스를 포함하는 것을 특징으로 하는 운송수단에 결합된 추진 시스템.
  3. 제1항에 있어서, 하나 이상의 관은 곡선 배열방향, 나선형 배열방향, 및 지그재그 배열방향 중 하나 이상의 배열방향으로 배열된 관의 어레이(array)를 포함하는 것을 특징으로 하는 운송수단에 결합된 추진 시스템.
  4. 제1항에 있어서, 흡기 구조물은 비대칭인 것을 특징으로 하는 운송수단에 결합된 추진 시스템.
  5. 운송수단에 결합된 추진 시스템에 있어서, 상기 시스템은:
    분산 구조물;
    상기 분산 구조물에 결합되고 운송수단에 의해 형성된 일차 유체를 분산 구조물에 주입시키도록 구성된 하나 이상의 관; 및
    상기 분산 구조물에 결합되고 운송수단에 접근 가능한 이차 유체를 분산 구조물에 주입시키도록 구성된 비대칭의 흡기 구조물을 포함하되, 상기 분산 구조물은, 주입된 일차 유체와 이차 유체를 위해, 시스템으로부터 배출을 제공하도록 구성된 말단 단부를 포함하는 것을 특징으로 하는 운송수단에 결합된 추진 시스템.
  6. 제5항에 있어서, 흡기 구조물은 제1 및 제2 횡방향 마주보는 에지를 포함하되, 제1 횡방향 마주보는 에지는 제2 횡방향 마주보는 에지보다 더 큰 곡률반경을 가지는 것을 특징으로 하는 운송수단에 결합된 추진 시스템.
  7. 제5항에 있어서, 흡기 구조물은 제1 및 제2 마주보는 에지를 포함하되, 제2 마주보는 에지는 제1 마주보는 에지를 향해 돌출되는 곡선 부분을 포함하는 것을 특징으로 하는 운송수단에 결합된 추진 시스템.
  8. 제5항에 있어서, 하나 이상의 관은 곡선 배열방향, 나선형 배열방향, 및 지그재그 배열방향 중 하나 이상의 배열방향으로 배열된 관의 어레이를 포함하는 것을 특징으로 하는 운송수단에 결합된 추진 시스템.
  9. 제5항에 있어서, 볼록 표면을 추가로 포함하며, 하나 이상의 관은 운송수단에 의해 형성된 일차 유체를 볼록 표면에 주입시키도록 구성되는 것을 특징으로 하는 운송수단에 결합된 추진 시스템.
  10. 운송수단에 결합된 추진 시스템에 있어서, 상기 시스템은:
    분산 구조물;
    상기 분산 구조물에 결합되고 운송수단에 의해 형성된 일차 유체를 분산 구조물에 주입시키도록 구성된 하나 이상의 관;
    상기 분산 구조물에 결합되고 운송수단에 접근 가능한 이차 유체를 분산 구조물에 주입시키도록 구성된 흡기 구조물; 및
    상기 분산 구조물을 운송수단에 결합하고 운송수단에 대해 분산 구조물의 2차원 이상의 운동을 제공하도록 구성된 작동 요소를 포함하되, 상기 분산 구조물은, 주입된 일차 유체와 이차 유체를 위해, 시스템으로부터 배출을 제공하도록 구성된 말단 단부를 포함하는 것을 특징으로 하는 운송수단에 결합된 추진 시스템.
  11. 제10항에 있어서, 하나 이상의 관은 곡선 배열방향, 나선형 배열방향, 및 지그재그 배열방향 중 하나 이상의 배열방향으로 배열된 관의 어레이를 포함하는 것을 특징으로 하는 운송수단에 결합된 추진 시스템.
  12. 제10항에 있어서, 볼록 표면을 추가로 포함하며, 하나 이상의 관은 운송수단에 의해 형성된 일차 유체를 볼록 표면에 주입시키도록 구성되는 것을 특징으로 하는 운송수단에 결합된 추진 시스템.
  13. 운송수단에 결합된 추진 시스템에 있어서, 상기 시스템은:
    제1 및 제2 벽 영역을 포함하는 분산 구조물을 포함하되, 상기 제1 및 제2 벽 영역은 각각의 제1 및 제2 액츄에이터를 포함하고, 상기 제1 및 제2 벽 영역은 각각의 제1 및 제2 내측 표면을 포함하며, 제1 액츄에이터는 제2 표면이 움직이지 않을 때 제1 표면이 제2 표면에 대해 움직이도록 구성되고, 제2 액츄에이터는 제1 표면이 움직이지 않을 때 제2 표면이 제1 표면에 대해 움직이도록 구성되며;
    상기 분산 구조물에 결합되고 운송수단에 의해 형성된 일차 유체를 분산 구조물에 주입시키도록 구성된 하나 이상의 관; 및
    상기 분산 구조물에 결합되고 운송수단에 접근 가능한 이차 유체를 분산 구조물에 주입시키도록 구성된 흡기 구조물을 포함하되, 상기 분산 구조물은, 주입된 일차 유체와 이차 유체를 위해, 시스템으로부터 배출을 제공하도록 구성된 말단 단부를 포함하는 것을 특징으로 하는 운송수단에 결합된 추진 시스템.
  14. 제13항에 있어서, 하나 이상의 관은 곡선 배열방향, 나선형 배열방향, 및 지그재그 배열방향 중 하나 이상의 배열방향으로 배열된 관의 어레이를 포함하는 것을 특징으로 하는 운송수단에 결합된 추진 시스템.
  15. 제13항에 있어서, 볼록 표면을 추가로 포함하며, 하나 이상의 관은 운송수단에 의해 형성된 일차 유체를 볼록 표면에 주입시키도록 구성되는 것을 특징으로 하는 운송수단에 결합된 추진 시스템.
  16. 운송수단에 결합된 추진 시스템에 있어서, 상기 시스템은:
    운송수단에 결합된 일차 에어포일; 및
    운송수단에 결합되고 일차 에어포일에 흐르는 유체의 하류에 위치된 제1 이차 에어포일을 포함하되, 제1 이차 에어포일은 제1 출력 구조물과 상기 제1 출력 구조물에 결합된 하나 이상의 제1 관을 포함하고, 하나 이상의 제1 관은 운송수단에 의해 형성된 일차 유체를 제1 출력 구조물에 주입시키도록 구성되며, 상기 제1 출력 구조물은 제1 이차 에어포일로부터 나와서 일차 에어포일을 향하는 일차 유체의 배출을 제공하도록 구성된 제1 말단 단부를 포함하는 것을 특징으로 하는 운송수단에 결합된 추진 시스템.
  17. 제16항에 있어서, 운송수단에 결합되고 일차 에어포일에 흐르는 유체의 하류에 위치된 제2 이차 에어포일을 추가로 포함하며, 각각의 제1 및 제2 이차 에어포일은 일차 에어포일을 향해 배열된 리딩 에지를 가지고, 제1 이차 에어포일은 제2 이차 에어포일과 마주보는 상태로 배열되며,
    제1 및 제2 이차 에어포일은 분산 영역을 형성하고,
    상기 리딩 에지는 일차 에어포일에 흐르는 유체와 일차 유체를 분산 영역에 주입하고 수용하도록 구성된 흡기 영역을 형성하며, 상기 분산 영역은 일차 에어포일에 흐르는 유체와 일차 유체를 위해 시스템으로부터 배출을 제공하도록 구성된 일차 말단 단부를 포함하는 것을 특징으로 하는 운송수단에 결합된 추진 시스템.
  18. 제17항에 있어서, 제2 이차 에어포일은 제2 출력 구조물과 상기 제2 출력 구조물에 결합된 하나 이상의 제2 관을 포함하고, 하나 이상의 제2 관은 운송수단에 의해 형성된 일차 유체를 제2 출력 구조물에 주입시키도록 구성되며, 상기 제2 출력 구조물은 제2 이차 에어포일로부터 나와서 일차 에어포일을 향하는 일차 유체의 배출을 제공하도록 구성된 제2 말단 단부를 포함하는 것을 특징으로 하는 운송수단에 결합된 추진 시스템.
  19. 제16항에 있어서, 제1 이차 에어포일을 운송수단에 대해 회전시키도록 구성된 제1 액츄에이터를 추가로 포함하는 것을 특징으로 하는 운송수단에 결합된 추진 시스템.
  20. 제17항에 있어서, 제2 이차 에어포일을 운송수단에 대해 회전시키도록 구성된 제2 액츄에이터를 추가로 포함하는 것을 특징으로 하는 운송수단에 결합된 추진 시스템.
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CA2996302A1 (en) 2017-03-09
EP3344537A4 (en) 2019-08-21
HK1257209A1 (zh) 2019-10-18
KR20180073564A (ko) 2018-07-02
BR112018004262A2 (pt) 2018-10-09
US20240228053A1 (en) 2024-07-11
WO2017065858A2 (en) 2017-04-20
CN108349585A (zh) 2018-07-31
IL287449B1 (en) 2023-05-01
EP4306789A2 (en) 2024-01-17
CN108137150A (zh) 2018-06-08
US10501197B2 (en) 2019-12-10
ES2890927T3 (es) 2022-01-25
CN108137149B (zh) 2021-07-06
WO2017065858A3 (en) 2017-07-13
EP3344535B1 (en) 2021-06-09
JP6930743B2 (ja) 2021-09-01
KR102668106B1 (ko) 2024-05-22

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