KR20070100092A - A perpendicular take-off and landing airplane - Google Patents

A perpendicular take-off and landing airplane Download PDF

Info

Publication number
KR20070100092A
KR20070100092A KR1020060119538A KR20060119538A KR20070100092A KR 20070100092 A KR20070100092 A KR 20070100092A KR 1020060119538 A KR1020060119538 A KR 1020060119538A KR 20060119538 A KR20060119538 A KR 20060119538A KR 20070100092 A KR20070100092 A KR 20070100092A
Authority
KR
South Korea
Prior art keywords
landing
rotary shaft
airplane
wings
sides
Prior art date
Application number
KR1020060119538A
Other languages
Korean (ko)
Inventor
함동호
Original Assignee
함동호
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 함동호 filed Critical 함동호
Priority to KR1020060119538A priority Critical patent/KR20070100092A/en
Publication of KR20070100092A publication Critical patent/KR20070100092A/en

Links

Images

Classifications

    • 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
    • B64C11/46—Arrangements of, or constructional features peculiar to, multiple propellers
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)

Abstract

A perpendicular taking-off and landing airplane is provided to allow the airplane to take off and land in a narrow space by shortening a distance for taking-off and landing and to reduce energy required for taking-off and landing. A perpendicular taking-off and landing airplane comprises wings(2) provided with propellers that vertically rotates. A rotary shaft(4) is projected on two sides of the body(1) of the airplane. The wings(2) are fastened at two sides of the rotary shaft(4). A rotating motor(3) is installed in the body(1). The rotary shaft(4) is coupled to the rotating motor(3). A fixing cylinder(5) for fixing the wings(2) is installed at two sides of the rotary shaft(4). The wings(2) has a plurality of grooves into which the rods of the fixing cylinder(5) are inserted.

Description

수직이착륙 비행체{A perpendicular take-off and landing airplane}A vertical take-off and landing airplane}

도 1은 본 발명의 전체 사시도1 is an overall perspective view of the present invention

도 2는 본 발명의 내부구조도2 is an internal structure diagram of the present invention

도 3은 본 발명의 요부 상세도Figure 3 is a detailed view of the main part of the present invention

도 4는 날개가 회전된 상태도4 is a state in which the blade is rotated

※ 도면의 주요 부분에 대한 부호의 설명※ Explanation of codes for main parts of drawing

1 : 동체 2 : 날개1: fuselage 2: wings

3 : 회전모터 4 : 회전축3: rotating motor 4: rotating shaft

5 : 고정실린더5: fixed cylinder

본 발명은 수직으로 이륙 및 착륙하는 비행체에 관한 것으로, 보다 상세하게는 프로펠러가 장착된 비행체의 날개를 이착륙시에 수직으로 회전되게 함으로써, 날개에 부착된 프로펠러가 비행체를 수직으로 이륙시키고 착륙시키는데 필요한 힘 을 발생시키도록 한 비행체에 관한 것이다.The present invention relates to a vehicle which takes off and lands vertically, and more particularly, by allowing the wing of the vehicle equipped with the propeller to rotate vertically during takeoff and landing, a propeller attached to the wing is required to take off and land the vehicle vertically. It is about a vehicle that is designed to generate force.

비행체는 추력에 의해 날개가 받는 양력으로 이착륙하는데, 추력은 프로펠러나 제트엔진에 의해 얻는 구조이고, 추력과 날개의 구조 등에 의한 항력의 비율에 의하여 이착륙과 운항이 이루어진다.The aircraft takes off and lands by the lifting force received by the wing by thrust. The thrust is a structure obtained by a propeller or a jet engine.

이와 같은 종래의 비행체는 이착륙을 위하여 충분한 활주거리를 필요로 하는데, 이를 위한 시설공사는 물론이고 이착륙에 의한 에너지의 소모가 과다한 문제점이 있다.Such a conventional vehicle needs a sufficient run distance for takeoff and landing, and there is a problem of excessive energy consumption due to takeoff and landing as well as facility construction for this.

본 발명의 목적은 이착륙거리를 단축시켜 좁은 공간에서 용이하게 이착륙할 수 있도록 하고, 이착륙에 소요되는 에너지를 절감할 수 있도록 한 비행체의 제공에 있다. 따라서 본 발명은 프로펠러가 설치된 날개를 수직으로 회전시켜, 프로펠러가 이착륙시에는 이착륙에 필요한 힘을 발생토록한 비행체의 제공에 구체적 목적이 있다.An object of the present invention is to provide a vehicle to shorten the take-off and landing distance to easily take off and land in a narrow space, and to reduce the energy required for take-off and landing. Therefore, the present invention has a specific object to provide a flying vehicle to generate the force necessary for takeoff and landing when the propeller is rotated vertically, the propeller is installed and landed.

이하 본 발명의 구성 및 작용을 첨부 도면에 의하여 상세히 설명하면 다음과 같다.Hereinafter, the configuration and operation of the present invention will be described in detail with reference to the accompanying drawings.

본 발명은 동체(1)에 프로펠러가 설치된 날개(2)가 회전되는 구조에 특징이 있다. 따라서 날개(2)는 동체(1)와 독립적으로 분리되어 설치되는 구조이다.The present invention is characterized by a structure in which a wing (2) provided with a propeller on the body (1) is rotated. Therefore, the wing 2 is a structure that is installed separately from the body (1).

그리고 동체(1)에는 회전모터(3)가 설치되고, 날개(2)에는 회전축(4)이 고정설치되며, 상기 회전축(4)은 회전모터(3)에 체결되어 회전되는 구조이다.And the body 1 is provided with a rotary motor 3, the blade 2 is fixed to the rotary shaft 4, the rotary shaft 4 is fastened to the rotary motor 3 is a structure that is rotated.

또한 날개(2)를 고정하기 위한 장치로서, 동체(1)에는 고정실린더(5)가 설치되고, 날개(2)에는 고정실린더(5)의 로드가 삽입되는 홈이 형성되어 있다.Moreover, as an apparatus for fixing the wing | blade 2, the fixed cylinder 5 is provided in the fuselage 1, and the groove | channel 2 is provided with the groove | channel into which the rod of the fixed cylinder 5 is inserted.

이와 같은 구조를 가진 본 발명은 도 1에 전체 사시도가 도시되어 있고, 도 2와 도 3에 본 발명의 요지부분의 상세도가 도시되어 있다.The present invention having such a structure is shown in full perspective view in FIG. 1, and in detail in the gist of the present invention in FIGS.

종래의 경우는 이륙과 착륙을 위하여는 긴 활주로가 필요하였으나 본 발명에 의하면 짧은 활주로나 좁은 공간에서도 이착륙이 가능하게 된다.In the conventional case, a long runway is required for takeoff and landing, but according to the present invention, a short runway or a landing space is possible even in a narrow space.

이착륙을 위하여, 먼저 회전모터(3)를 작동하게 되면, 회전모터(3)와 회전축(4)은 기어 등의 동력전달 기구로 치합되어 있어, 회전축(4)이 회전하게 된다. 회전축(4)은 양측 날개(2)에 고정되어 있으므로, 회전축(4)의 회전은 날개(2)를 회전시키게되어 결국 도 4와 같은 상태를 유지하게 된다.For takeoff and landing, when the rotary motor 3 is first operated, the rotary motor 3 and the rotary shaft 4 are engaged by a power transmission mechanism such as a gear, and the rotary shaft 4 rotates. Since the rotary shaft 4 is fixed to both blades 2, the rotation of the rotary shaft 4 rotates the blades 2 to maintain the state as shown in FIG. 4.

회전된 상태를 유지하기 위하여 날개(2)를 고정할 필요성이 있는데, 이 경우는 고정실린더(5)를 작동하여 날개(2)를 고정시킨다. 고정실린더(5)는 동체(1)의 외측으로 로드가 돌출되게 신장되는 구조를 가지고, 날개(2)의 동체(1)측 단부면에는 고정실린더(5)의 로드가 삽입되는 홈이 형성되어 있다. 따라서 로드가 홈에 삽입되면 회전된 날개(2)의 상태가 유지되어 이착륙시 그대로 유지된다.In order to maintain the rotated state it is necessary to fix the wing (2), in this case to operate the fixed cylinder (5) to fix the wing (2). The fixed cylinder 5 has a structure in which a rod extends to the outside of the fuselage 1, and a groove into which the rod of the fixed cylinder 5 is inserted is formed at the end face of the fuselage 1 side of the blade 2. have. Therefore, when the rod is inserted into the groove, the state of the rotated wing (2) is maintained as it is during takeoff and landing.

이와 같은 상태에서 플로펠러가 작동하게 되면 비행체는 수직으로 이착륙 가능하게 되고, 순항을 하고자 하는 경우는 다시 날개를 반대방향으로 회전시켜 도 1과 같은 상태를 유지시키면 된다.When the floppler is operated in such a state, the aircraft can be taken off and landed vertically, and if it is desired to cruise, the blade is rotated in the opposite direction to maintain the state as shown in FIG. 1.

상기와 같은 본 발명은 프로펠러가 부착된 날개(2)가 수직으로 회전되어 고정되는 구조를 가짐으로써, 비행체의 이착륙에 필요한 긴 거리의 활주로가 불필요하고, 좁은 공간에서도 수직으로 이착륙이 가능한 효과가 있다.As described above, the present invention has a structure in which the propeller-attached wing 2 is vertically rotated and fixed, thus eliminating the need for a long distance runway required for takeoff and landing of a vehicle, and capable of vertical takeoff and landing in a narrow space. .

Claims (2)

프로펠러가 설치된 날개(2)가 수직으로 회전되는 비행체를 구성함에 있어서, 회전되는 회전축(4)이 동체(1)의 양측으로 돌출되게 설치되고, 상기 회전축(4)의 양측에 각각 날개(2)가 고정설치됨을 특징으로 하는 수직이착륙 비행체.In the configuration of a wing in which the propeller is installed 2 is rotated vertically, the rotating shaft (4) is rotated is installed to protrude to both sides of the body (1), each of the wings (2) on both sides of the rotating shaft (4) Vertical landing and landing vehicle, characterized in that the fixed installation. 제 1항에 있어서, 동체(1)에는 날개(2)를 고정시키는 고정실린더(5)가 회전축(4)의 양측에 설치된 수직이착륙 비행체.The vertical take-off and landing vehicle according to claim 1, wherein a fixed cylinder (5) is fixed to the fuselage (1) on both sides of the rotation shaft (4).
KR1020060119538A 2006-11-30 2006-11-30 A perpendicular take-off and landing airplane KR20070100092A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
KR1020060119538A KR20070100092A (en) 2006-11-30 2006-11-30 A perpendicular take-off and landing airplane

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
KR1020060119538A KR20070100092A (en) 2006-11-30 2006-11-30 A perpendicular take-off and landing airplane

Publications (1)

Publication Number Publication Date
KR20070100092A true KR20070100092A (en) 2007-10-10

Family

ID=38805238

Family Applications (1)

Application Number Title Priority Date Filing Date
KR1020060119538A KR20070100092A (en) 2006-11-30 2006-11-30 A perpendicular take-off and landing airplane

Country Status (1)

Country Link
KR (1) KR20070100092A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018155739A1 (en) * 2017-02-24 2018-08-30 기술융합협동조합 Vertical take-off and landing aircraft and transition method therefor
KR20220100248A (en) * 2021-01-08 2022-07-15 주식회사 엠지아이티 Driving method for vertical take-off and landing and flight conversion of vertical take-off and landing drones and vertical take-off and landing drones

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018155739A1 (en) * 2017-02-24 2018-08-30 기술융합협동조합 Vertical take-off and landing aircraft and transition method therefor
KR20220100248A (en) * 2021-01-08 2022-07-15 주식회사 엠지아이티 Driving method for vertical take-off and landing and flight conversion of vertical take-off and landing drones and vertical take-off and landing drones

Similar Documents

Publication Publication Date Title
US10526068B2 (en) Tilrotor aircraft having rotary and non rotary flight modes
RU2704771C2 (en) Aircraft capable of vertical take-off
EP2484587B1 (en) Tilt rotor aircraft with fixed engine arrangement
US11629541B2 (en) Versatile door systems for vehicles
US10183745B2 (en) Tiltrotor with inboard engines
US8011613B2 (en) Aircraft with reduced environmental impact
US8376264B1 (en) Rotor for a dual mode aircraft
US20170225780A1 (en) Maintaining Drive System Alignment in Aircraft
RU2724006C1 (en) Aircraft
US10220936B2 (en) Wing pivot structures for tiltrotor aircraft
JP5728688B2 (en) Vertical takeoff and landing airplane
BR112016025875B1 (en) VTOL AIRCRAFT
US10196127B2 (en) Wing pivot structure for tiltrotor aircraft
US20190047691A1 (en) Rolling Gimbal Lock Systems for Rotorcraft
US10875640B2 (en) Mast lockout systems for tiltrotor aircraft
US10421540B1 (en) Tiltrotor aircraft having optimized hover capabilities
KR20090057504A (en) Taking off and landing airplane using variable rotary wings
US10843798B2 (en) Mast lockout systems for tiltrotor aircraft
US9139298B2 (en) Rotorcraft control system for rotorcraft with two or more rotor systems
KR20140079174A (en) Blade pitch control device for Airplane propeller
KR20070100092A (en) A perpendicular take-off and landing airplane
US9725166B2 (en) Counter-rotating rotor system with static mast
WO2006119190A3 (en) Rotary wing aircraft
US11718403B2 (en) Extremely quiet short take-off and landing (STOL) aircraft
RU2605466C1 (en) Vertical take-off and landing aircraft

Legal Events

Date Code Title Description
A201 Request for examination
E902 Notification of reason for refusal
G15R Request for early opening
E601 Decision to refuse application