KR20060032226A - Plate flying - Google Patents

Plate flying Download PDF

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Publication number
KR20060032226A
KR20060032226A KR1020040080779A KR20040080779A KR20060032226A KR 20060032226 A KR20060032226 A KR 20060032226A KR 1020040080779 A KR1020040080779 A KR 1020040080779A KR 20040080779 A KR20040080779 A KR 20040080779A KR 20060032226 A KR20060032226 A KR 20060032226A
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South Korea
Prior art keywords
air
airfoil
aircraft
generated
donut
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KR1020040080779A
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Korean (ko)
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김이섭
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김이섭
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Priority to KR1020040080779A priority Critical patent/KR20060032226A/en
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/06—Aircraft not otherwise provided for having disc- or ring-shaped wings
    • 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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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Wind Motors (AREA)

Abstract

본 고안 발명은 전체적인 모양이 원반형인 비행체에 관한 것이다.

Figure 112004045918263-PAT00001

비행, 접시, 원반형, 수평비행, 수직비행

The present invention relates to an aircraft having a disk-shaped overall shape.

Figure 112004045918263-PAT00001

Flight, saucer, disc, horizontal flight, vertical flight

Description

접시형 비행체{plate flying} Plate flying             

도면1에서In Figure 1

원반비행체의 지붕 가운데의 공기흡입로를 통해 공기팬에 의해 유입되는 공기는 The air introduced by the air fan through the air intake center in the roof of the disc vehicle

비행체의 내부에 설치된 에어포일의 윗면과 아랫면을 따라 흐르는데 ,에어포일의 윗면으로 흐르는 공기는 그 속도가 빠르고 에어포일 아랫면으로 흐르는 공기는 그 속도가 느리다.따라서 에어포일은 베르누이의 원리에 의해 기압이 낮은 윗면으로Air flows along the top and bottom of the airfoil installed inside the aircraft, and the air flowing to the top of the airfoil is faster and the air flowing to the bottom of the airfoil is slower. To the top

부양력이 생긴다. 이 힘으로 비행체는 양력을 얻어 수직 부상하며, 에어포일 아랫면에 형성된 나선형 공기통로를 통해 흐르는 공기에 의해 발생되는 비행체의 회전력을 비행체의 수평비행의 추력으로 사용한다.Flotation is created. With this force, the aircraft gains lift and rises vertically, and uses the rotational force of the aircraft generated by the air flowing through the spiral air passage formed on the lower surface of the airfoil as the thrust of the aircraft.

도면2는 Figure 2

도넛형 에어포일(3)의 단면구조를 보여준다.The cross-sectional structure of the toroidal airfoil 3 is shown.

도면 3은Figure 3

공기방출구를 제어하는 제어밸브(8)의 구조도이다.It is a structural diagram of the control valve 8 which controls an air discharge port.

도면4는 Figure 4

도면1의 공기통로(4)의 나선형 공기통로구조(2)의 상세도이다.1 is a detailed view of the spiral air passage structure 2 of the air passage 4 in FIG.

종래의 모든 비행체는 비행체가 뜨기 위한 양력을 얻는 방법으로서 비행체를 고속으로 추진시켜 날개에 양력을 발생시키거나 회전날개를 통해 양력을 발생시킨다.All conventional vehicles are a method of obtaining lift for floating aircraft to propel the aircraft at high speed to generate lift on the wings or lift through the rotor blades.

그래서 긴거리의 활주로가 필요하게 되며,급격하게 수평수직 이동할수 없다.So you need a long runway, and you can't move quickly and horizontally.

본고안 발명은 비행체 내부에 설치된 도넛형 에어포일형 날개에 공기팬을 통해 공기를 흘려주므로서 양력을 얻어 비행하게 되며,고정익 날개와 회전일 날개를 갖는 비행체의 장점을 모두 취할수 있다.즉, 활주로가 필요없으며, 급격한 수직상승,혹은 모든 방향으로의 급격한 수평비행을 실시할수 있다.
This invention is to fly by lifting the air by flowing air through the air fan to the donut-type airfoil-type wings installed inside the aircraft, it can take all the advantages of the aircraft having a fixed blade wing and a rotary blade wing. There is no need for a rapid rise, or a rapid horizontal flight in all directions.

도면1은 Figure 1

비행체의 단면도로서,비행체의 지붕(1)과 도넛형 에어포일(3)의 윗면에 공기통로 ,그리고 도넛형 에어포일 아랫면에 나선으로 형성된 공기터널(4)을 각각 설치하고,As a cross-sectional view of the vehicle, air passages are formed on the roof 1 and the top surface of the donut-type airfoil 3, and spirally formed air tunnels 4 are formed on the bottom surface of the donut-type airfoil, respectively.

엔진(5)에 의해 동력을 공급받는 공기팬(6)에 의해 비행체의 지붕(1)과 비행체의 중심부에 설치된 공기흐름 가이드(7)를 따라 외부공기를 고속흡입하여, 상기의 에어포일 날개면의 공기통로를 따라 흐르게 하므로서 비행체는 양력을 얻어 부상하며, 도넛 모양의 에어포일(3)의 아랫면과 아랫판(2)에 의해 나선으로 형성된 공기통로(4)를 통해 공기가 빠져나갈때 발생하게 되는 비행체의 회전력을 공기방출 조절구(8)을 통해 밸브를 조절하므로서 비행체의 회전 불균형을 발생시켜 회전체에서 발생하는 회전 불균형 벡터값으로 수평추력을 얻어 비행한다.The airfoil wing surface is sucked by the air fan 6, which is powered by the engine 5, along with the airflow guide 7 installed at the roof 1 of the vehicle and the airflow guide 7 installed at the center of the vehicle. The aircraft is lifted and lifted by flowing along the air passage of the aircraft, which is generated when the air escapes through the air passage (4) formed by the spiral by the lower surface and the lower plate (2) of the donut-shaped airfoil (3) By controlling the valve through the air discharge control port 8 of the rotational force generated by the rotational imbalance of the aircraft to obtain a horizontal thrust to the rotational imbalance vector value generated in the rotor to fly.

본 고안발명 비행체는 양력을 얻기 위한 비행활주로가 필요하지 않으며The present invention does not require a runway to gain lift.

어느 방향으로든지 급격한 수평 혹은 수직 이동비행이 가능하다.
Rapid horizontal or vertical flight in either direction is possible.

Claims (1)

원반형 비행체 내에 도넛형 에어포일을 설치하고 ,에어포일과 비행체와의 사이에 공기통로를 설치하여 공기팬에 의해 흡입되는 공기를 에어포일면에 흘려주므로서 에어포일구조에 의해 발생되는 에어포일 윗면과 아랫면의 기압차이에 의한A donut-type airfoil is installed in the disk-shaped aircraft, and an air passage is installed between the airfoil and the aircraft, and the air sucked by the air fan flows on the airfoil surface, and the upper surface of the airfoil generated by the airfoil structure Due to air pressure difference 양력으로 부상하며, 에어포일 아랫면에 형성된 나선형 공기방출구를 통해Lifted by lifting force, through the spiral air outlet formed at the bottom of the airfoil 공기가 방출될때 발생하는 비행체의 회전력을 공기방출조절구를 조절하므로서 회전불균형을 일으키고 그 회전불균형의 벡터값으로 발생되는 수평추력을 얻어 수평비행하는 비행체.An aircraft that causes rotational imbalance by adjusting the air release control of the rotational force of the vehicle generated when the air is released, and obtains the horizontal thrust generated by the vector value of the rotational imbalance.
KR1020040080779A 2004-10-11 2004-10-11 Plate flying KR20060032226A (en)

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR101015954B1 (en) * 2008-12-31 2011-02-23 허일행 Disc type flying object
KR20190042971A (en) * 2017-10-17 2019-04-25 (주)마인드크립션 A fluid propulsion device
KR20190141373A (en) 2018-06-14 2019-12-24 박명준 Disk-shaped vehicle
KR20200034987A (en) 2018-06-14 2020-04-01 박명준 Disk-shaped vehicle

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR101015954B1 (en) * 2008-12-31 2011-02-23 허일행 Disc type flying object
KR20190042971A (en) * 2017-10-17 2019-04-25 (주)마인드크립션 A fluid propulsion device
KR20190141373A (en) 2018-06-14 2019-12-24 박명준 Disk-shaped vehicle
KR20200034987A (en) 2018-06-14 2020-04-01 박명준 Disk-shaped vehicle
CN112292319A (en) * 2018-06-14 2021-01-29 朴明浚 Disk-shaped aircraft
CN112292319B (en) * 2018-06-14 2024-05-14 朴明浚 Disk-shaped aircraft

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