WO2018056484A1 - 다목적 비행체 - Google Patents
다목적 비행체 Download PDFInfo
- Publication number
- WO2018056484A1 WO2018056484A1 PCT/KR2016/010730 KR2016010730W WO2018056484A1 WO 2018056484 A1 WO2018056484 A1 WO 2018056484A1 KR 2016010730 W KR2016010730 W KR 2016010730W WO 2018056484 A1 WO2018056484 A1 WO 2018056484A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- cabin
- frame
- propeller
- connector
- present
- Prior art date
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Classifications
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- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/061—Frames
- B64C1/062—Frames specially adapted to absorb crash loads
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
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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
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
- B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
- B64C29/0033—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being tiltable relative to the fuselage
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C35/00—Flying-boats; Seaplanes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C35/00—Flying-boats; Seaplanes
- B64C35/001—Flying-boats; Seaplanes with means for increasing stability on the water
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C35/00—Flying-boats; Seaplanes
- B64C35/006—Flying-boats; Seaplanes with lift generating devices
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
- B64U10/13—Flying platforms
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/70—Constructional aspects of the UAV body
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
- B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
- B64U30/296—Rotors with variable spatial positions relative to the UAV body
Definitions
- the present invention relates to a multi-purpose manned vehicle.
- it has a plurality of linear propellers as commonly seen in the drone relates to a vehicle provided with a cabin in which the pilot enters the center of the body.
- the present invention has been made to solve almost all of the above problems with questions.
- a propeller installed on one or more shafts including the body and the front and rear axes of the body, and having two to five rotary vanes, and a power unit for generating lift in the propeller by rotating the propeller.
- Aircraft consisting of a helicopter has been known under the name.
- a helicopter gains lift by the main propeller and floats it, and at the same time, inclines the rotation angle of the main propeller, thereby obtaining the propulsion force in the direction of flight. Therefore, these helicopters have the drawback of slow forward speed, and in particular, the aircraft itself does not generate lift.
- the helicopter that gains both lift and propulsion by the main propeller needs to have a long propeller length, and thus requires a wide landing pad and a large hangar.
- the conventional aircraft is not equipped with a safety device for the fall, there is a drawback of great damage to life when falling.
- the present invention by reducing the length of the propeller to reduce the area of the landing and hangar, to enhance the propulsion of the propeller to fly at a relatively high speed, to reduce the damage of distress accidents To solve the problem of providing.
- the present invention to solve the above problems,
- It is composed of a frame installed with a propeller and an engine on which the engine is mounted, and a cabin coupled to the inside of the frame,
- the frame has at least two arms (arm) that can be installed to be raised, the propeller is installed at the tip of each arm with a bent joint,
- the cabin has four connectors installed at the front and rear and left and right ends of the cabin, and the front end of the connector is installed on the rail of the frame to provide a multipurpose vehicle characterized by guiding the rotation of the cabin.
- the present invention further provides a flying body by installing a circular plate around the cabin so that the connector is installed in the front, rear, left and right of the plate, and also provides a multi-purpose aircraft having a frame having wings that can float on both sides. do.
- the present invention provides a multi-purpose aircraft having a receiving space frame at the bottom of the frame when a larger receiving space is required.
- two or more propellers are provided so that the propellers can be lifted out of the frame, so that the propellers can be formed relatively small, and the area occupied in the mooring area or hangar is reduced by immersing the arm in which the propellers are installed. It can be effected.
- the present invention is to control the installation angle of the propeller to enable the propeller to perform the selected action of lifting lift or propulsion increase, if there is enough lift, the propeller is switched from the lift lift action to the propulsion boost action to increase the forward speed of the aircraft It has the effect of strengthening.
- the circular plate body provided around the cabin has the effect of generating lift. Since the circular plate around the cabin generates lift, the propeller can use the power of the propulsion rather than the rotation to gain lift, further improving the forward speed of the vehicle.
- the cabin can have a sufficient buoyancy in the water can perform the function as a boat (Boat), at this time, the circular plate installed around the cabin has the function of hydrofoil so that the cabin floats on the water running This allows you to drive at high speeds while saving power.
- the present invention has an effect of improving the safety of the occupant in the cabin in which the frame absorbs the impact force in case of an emergency, such as a fall.
- FIG. 1 is a side view of an embodiment to which the lower accommodation space is applied in the present invention.
- FIG. 2 is a plan view of an embodiment to which the wing which can be mounted is applied.
- Figure 3 is a perspective view showing only the frame and the cabin without the mechanical part.
- FIG. 4 is a plan view of another embodiment of the present invention in which eight propellers each having two pairs of front, rear, left, and right sides are partially cut away.
- 5 to 9 are 3D modeling diagrams of one embodiment of the present invention.
- the present invention is composed of a frame (1) on which a propeller (11) and a mechanical part (10) on which an engine is mounted is installed, and a cabin (2) (cabin) coupled to the inside of the frame (1).
- (1) is composed of bent pillars (111, 112, 113, 114) connecting the upper and lower circular plates (101, 102) and the upper and lower circular plates (101, 102), two or more arms (12; ),
- the propeller 11 is installed at the tip of each arm 12,
- the cabin 2 has a connector 21 which is installed at the front and rear ends of the cabin 2, and the tip of the connector 21 is installed on the rail 13 of the frame 1 to guide the rotation of the cabin 2. It is preferred to be configured.
- one or more of the arms 12 of the arm 12 having the propeller 11 is installed so as to be sunk in the frame 1 has a bent joint 121 at the tip, to the bent joint 121 It is preferable that the propeller 11 is connected and installed so that the propeller 11 can switch a direction to 90 degrees.
- the frame 1 has the blade
- the cabin 2 preferably has a circular plate body 3 on the periphery, and the connector 21 is preferably provided with a multipurpose vehicle characterized in that the front and rear ends of the plate body 3 are installed.
- the rail 13 of the frame 1 has a stopper 16 on the upper and lower sides, so that the connector 21 of the cabin 2 is controlled by the stopper 16 to prevent excessive rotation of the connector 21.
- the winding wire (22; Winding wire) for providing a forward and backward rotational force of the cabin (2) is installed to connect the heat inlet 21 and the frame (1).
- the present invention combines the principles of aircraft, aircraft helicopters, drones, and the like, to date, to reduce and reduce the fear and safety concerns of the most feared and vulnerable of all these vehicles.
- the energy source is combined with an engine that uses fossil fuels, and a high capacity battery is used to prevent the battery from running. It is designed to replace the operation to avoid falling, save fuel and reduce air pollution.
- the frame (1) is provided with a propeller (11) and the engine unit on which the engine 10 is mounted, and the cabin (2) coupled to the inside of the frame (1); Cabin), the frame 1 includes a power unit, such as an engine using fossil fuel and a motor unit using a high performance battery (detailed illustration and description of the power unit including the engine is omitted), Two or more arms (111, 112, 113, 114) connecting the upper and lower circular plates (101, 102) and the upper and lower circular plates (102, 102), which can be mounted and mounted It is preferable that the propeller 11 is provided in the front-end
- the cabin 2 has a connector 21 which is installed at the front and rear ends of the cabin 2, and the tip of the connector 21 is installed on the rail 13 of the frame 1 to guide the rotation of the cabin 2. It is desirable to.
- the cabin 2 is provided with a circular plate 3, such as a ring of Saturn, and the connector 21 is provided at the front, rear, left and right ends of the plate 3.
- the cabin 2 installed on the rail 13 of the frame 1 by the connector 21 is provided with a large lifting force by the plate body 3.
- the machine unit 10 and the cabin 2 may be detachably coupled.
- the detachable coupling structure of the mechanical part 10 and the cabin 2 may be selected by a general coupling structure, but as shown in FIG. 1, the shaft 1 is installed on the frame 1 of the cabin 2.
- a plurality of hooks 20 may be configured to hook the bottom plate of the mechanical part 10. This hook coupling structure can be easily carried out from the coupling structure of the cable and the lift in the lift installed in the ski resort.
- the mechanical unit 10 includes an engine using fossil fuel and a motor device using a high performance battery (the detailed illustration and description thereof are omitted).
- the frame 1 has a multi-purpose aircraft characterized in that it has a receiving space frame 15 in the lower portion, so that the lower receiving space frame 15 for cargo loading It can be used as a cargo compartment of a passenger compartment or as a compartment for patient transportation or passenger transportation, thereby diversifying the use of the aircraft.
- the frame 1 preferably has wings 14 that can be sunk on both sides.
- the wing 14 may provide lift as the wing in a general airplane so that the wing 14 provides lift in flight, thereby allowing the propeller 11 to provide only the driving force. Therefore, the present invention makes it possible to expect a marked improvement in flight speed.
- the wing 14 serves to stabilize the shaking of the left and right when driving.
- the present invention also provides a cabin (2) installed on the frame (1) is rotated back and forth in the up and down direction by the axis of the connector on the left and right ends thereof to facilitate the horizontal maintenance of the cabin to facilitate the front of the front, It is configured to lift the front floor at a lift-producing angle so that the bottom of the cabin 2 can provide lift in the forward flight, thereby providing a multipurpose vehicle that enables replenishment of lift.
- the present invention further extends to this, out of the arm 12 having a propeller (11) installed so that it can be mounted on the frame (1), one or more arms (12) has a bent joint 121 at the tip, 121) provides a multi-purpose aircraft characterized in that the propeller 11 is installed.
- the bending joint 121 can change the propulsion direction of the propeller arbitrarily, so that the propeller can mainly gain the lift force or mainly the propulsion force, and select the direction of action of the force such that the lift force and the propulsion force can be obtained together.
- the rotation surfaces of all the propellers are aligned to be horizontal, and when the vehicle is advanced, all or some of the propellers may be bent in the direction for forward propagation. It can be arbitrarily determined according to the required lift and the required propulsion speed, thus enabling efficient operation.
- FIG. 2 As shown in FIG. 2, four propellers 11 may be installed. However, as illustrated in FIG. 4, eight propellers may be installed.
- the rail 13 of the frame 1 has a stopper 16 at its upper and lower parts, which prevents the connector 21 of the cabin 2 from excessively rotating in the rail 13 so that the connector 21 is connected to the rail 13. It is desirable not to deviate.
- the rotational force that the cabin 2 rotates the front and rear portions in the up and down direction about the left and right coupling end is connected to a winding wire 22 connecting the front and rear end fitting 21 and the upper and lower ends of the frame 1. It is desirable to be able to obtain by winding and unwinding operation.
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Body Structure For Vehicles (AREA)
- Wind Motors (AREA)
- Forklifts And Lifting Vehicles (AREA)
- Toys (AREA)
Abstract
Description
캐빈(2)은 캐빈(2)의 앞뒤 선단에 설치되는 연결구(21)를 가지며, 연결구(21)의 선단은 프레임(1)의 레일(13)에 설치되어 캐빈(2)의 회동을 안내하도록 구성되는 것이 바람직하다.
또한 본 발명은, 캐빈(2)은 둘레에 원형의 판체(3)를 가지며, 상기의 연결구(21)가 판체(3)의 전후 좌우 단부에 설치된 것임을 특징으로 하는 다목적 비행체를 가지는 것이 바람직 하다.
또한 본 발명은, 프레임(1)의 레일(13)은 상하부에 스토퍼(16)를 가져서 캐빈(2)의 연결구(21)가 스토퍼(16)에 의해 제어되어 연결구(21)의 과도 회동이 방지되게 하며, 캐빈(2)의 앞뒤 방향 회동력을 제공하는 와인딩 와이어(22; Winding wire)가 열결구(21)와 프레임(1)을 연결하도록 설치된 것을 특징으로 하는 다목적 비행체를 제공한다.
본 발명은, 도1에 도시된 바와 같이, 프로펠러(11)와 엔진을 탑재한 기계부(10)가 설치되는 프레임(Frame)(1)과, 프레임(1) 내부에 결합된 캐빈(2; Cabin)으로 구성되고, 상기 프레임(1)은, 화석 연료를 사용하는 엔진과 고성능 배터리를 이용하는 모터 장치등으로 되는 동력 장치를 포함하며(엔진을 포함한 동력장치의 상세한 도시와 설명은 생략함), 상부와 하부의 각 원형판(101, 102)과 상하 원형판(102, 102)을 연결하는 4개의 굴곡 지주(111, 112, 113, 114)로 구성되고, 출몰이 가능하게 설치되는 2개 이상의 아암(12; arm)을 가지며, 각 아암(12)의 선단에 상기의 프로펠러(11)가 설치되며, 프로펠러(11)는 4개 또는 8개가 설치되는 것이 바람직하다. 이러한 프로펠러 중 좌우의 프로펠러는 양력을 일으키게 하고, 앞뒤의 프로펠러는 추진력을 담당하게 하는 것이 바람직하다.
캐빈(2)은 캐빈(2)의 앞뒤 선단에 설치되는 연결구(21)를 가지며, 연결구(21)의 선단은 프레임(1)의 레일(13)에 설치되어 캐빈(2)의 회동을 안내하게 하는것이 바람직 하다.
상기 기계부(10)는, 화석 연료를 사용하는 엔진과 고성능 배터리를 이용하는 모터 장치를 포함한다(이들의 상세한 도시와 설명은 생략함).
Claims (5)
- [규칙 제91조에 의한 정정 07.09.2017]
프로펠러(11)와 엔진을 탑재한 기계부(10)가 설치되는프레임(Frame)(1)과, 프레임(1) 내부에 결합된 캐빈(2; Cabin)으로 구성되고, 상기 프레임(1)은 상하부의 원형판(101,102)과 상하 원형판(101, 102)을 연결하는 굴곡지주(111, 112, 113, 114)로 구성되고, 출몰이 가능하게 설치되는 2개 이상의 아암(12; arm)을 가지며, 각 아암(12)의 선단에 상기의 프로펠러(11)가 설치되며, 캐빈(2)은 캐빈(2)의 앞뒤 좌우 선단에 설치되는 연결구(21)를 가지며,연결구(21)의 선단은 프레임(1)의 레일(13)에 설치되어 캐빈(2)의 회동을 안내하는 것을 특징으로 하는 다목적 비행체. - 제1항에 있어서,프레임(1)에 출몰이 가능하게 설치되어 프로펠러(11)를 가지는 아암(12) 중 하나 이상의 아암(12)은 선단에 절곡관절(121)을 가져, 절곡관절(121)로 프로펠러(11)가 연결 설치된 것을 특징으로 하는 다목적 비행체.
- 제1항에 있어서, 프레임(1)은 양측에 출몰 가능한 날개(14)를 가지는 것을 특징으로 하는 다목적 비행체.
- 제1항에 있어서,캐빈(2)은 둘레에 원형의 판체(3)를 가지며, 상기의 연결구(21)가 판체(3)의 전후 좌우 단부에 설치된 것임을 특징으로 하는 다목적 비행체.
- [규칙 제91조에 의한 정정 07.09.2017]
제1항 내지 제4항 중 어느 하나의 항에 있어서, 프레임(1)의 레일(13)은 상하부에 스토퍼(16)를 가져서 캐빈(2)의 연결구(21)가 스토퍼(16)에 의해 제어되어 연결구(21)의 과도 회동이 방지되게 하며, 캐빈(2)의 앞뒤 방향 회동력을 제공하는 와인딩 와이어(22; Winding wire)가 열결구(21)와 프레임(1)을 연결하도록 설치된 것을 특징으로 하는 다목적 비행체.
Priority Applications (8)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU2018137699A RU2721030C1 (ru) | 2016-09-26 | 2016-09-26 | Многоцелевой летательный аппарат |
PCT/KR2016/010730 WO2018056484A1 (ko) | 2016-09-26 | 2016-09-26 | 다목적 비행체 |
JP2018566394A JP6616024B2 (ja) | 2016-09-26 | 2016-09-26 | 多目的航空機 |
US15/575,806 US10279905B2 (en) | 2016-09-26 | 2016-09-26 | Multipurpose air vehicle |
CN201680084546.7A CN109071009B (zh) | 2016-09-26 | 2016-09-26 | 多用途空中车辆 |
KR1020197007577A KR102054161B1 (ko) | 2016-09-26 | 2016-09-26 | 다목적 비행체 |
EP16916858.0A EP3434593B1 (en) | 2016-09-26 | 2016-09-26 | Multipurpose air vehicle |
CA3022862A CA3022862C (en) | 2016-09-26 | 2016-09-26 | Multipurpose air vehicle |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/KR2016/010730 WO2018056484A1 (ko) | 2016-09-26 | 2016-09-26 | 다목적 비행체 |
Publications (1)
Publication Number | Publication Date |
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WO2018056484A1 true WO2018056484A1 (ko) | 2018-03-29 |
Family
ID=61690895
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/KR2016/010730 WO2018056484A1 (ko) | 2016-09-26 | 2016-09-26 | 다목적 비행체 |
Country Status (8)
Country | Link |
---|---|
US (1) | US10279905B2 (ko) |
EP (1) | EP3434593B1 (ko) |
JP (1) | JP6616024B2 (ko) |
KR (1) | KR102054161B1 (ko) |
CN (1) | CN109071009B (ko) |
CA (1) | CA3022862C (ko) |
RU (1) | RU2721030C1 (ko) |
WO (1) | WO2018056484A1 (ko) |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US11161605B2 (en) * | 2017-08-10 | 2021-11-02 | Kawasaki Jukogyo Kabushiki Kaisha | Air vehicle and method of controlling air vehicle |
CN109927875B (zh) * | 2019-04-08 | 2023-12-15 | 武夷学院 | 一种飞行器机架 |
CN110203406B (zh) * | 2019-05-15 | 2021-06-04 | 中国科学院深圳先进技术研究院 | 一种无人机及便携式动力设备 |
KR102208350B1 (ko) * | 2019-05-31 | 2021-01-27 | 유콘시스템 주식회사 | 2 자유도 관절을 이용하여 비행 성능을 유지 가능한 회전익형 비행체 |
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US20180346113A1 (en) | 2018-12-06 |
KR20190057056A (ko) | 2019-05-27 |
EP3434593A1 (en) | 2019-01-30 |
CA3022862A1 (en) | 2018-03-29 |
CN109071009B (zh) | 2019-09-24 |
US10279905B2 (en) | 2019-05-07 |
JP2019529199A (ja) | 2019-10-17 |
EP3434593B1 (en) | 2020-08-19 |
JP6616024B2 (ja) | 2019-12-04 |
RU2721030C1 (ru) | 2020-05-15 |
KR102054161B1 (ko) | 2019-12-10 |
CA3022862C (en) | 2020-04-21 |
EP3434593A4 (en) | 2019-10-09 |
CN109071009A (zh) | 2018-12-21 |
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