WO1997000200A1 - Avion a decollage et atterrissage verticaux - Google Patents

Avion a decollage et atterrissage verticaux Download PDF

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Publication number
WO1997000200A1
WO1997000200A1 PCT/JP1995/002095 JP9502095W WO9700200A1 WO 1997000200 A1 WO1997000200 A1 WO 1997000200A1 JP 9502095 W JP9502095 W JP 9502095W WO 9700200 A1 WO9700200 A1 WO 9700200A1
Authority
WO
WIPO (PCT)
Prior art keywords
rotor
wing
shaft
landing aircraft
main wing
Prior art date
Application number
PCT/JP1995/002095
Other languages
English (en)
Japanese (ja)
Inventor
Kazuhiro Takahashi
Original Assignee
Kazuhiro Takahashi
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 Kazuhiro Takahashi filed Critical Kazuhiro Takahashi
Priority to AU36735/95A priority Critical patent/AU3673595A/en
Publication of WO1997000200A1 publication Critical patent/WO1997000200A1/fr

Links

Classifications

    • 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

Definitions

  • the vertical take-off and landing aircraft of the present invention is an economical model because it can freely set the rotor mounting position with respect to the main wing, has the convenience of not requiring a runway, and has the functionality of flying at high speed.
  • the rotor is mounted at the bottom of the wing, and the rotor can be moved to the rear of the wing during flight, and can be rotated vertically at right angles to the wing, so that the wind pressure can be used to the maximum.
  • a helicopter has been known as a vertical take-off and landing aircraft using a rotor.
  • Helicopters usually have a rotor at the top of the fuselage and a small rotor at the rear for fuselage correction and have no wings. Due to its structure, it is not suitable for high-speed cruising.
  • the shape of the helicopter with the main wing as in the present invention is referred to as a VZS TOL aircraft, that is, a vertical short-range take-off and landing aircraft.
  • Such models have four rotors at the top of the main wing, and the engines and rotors are attached to the 20 tips of both the left and right main wings. It is known that the rotor is turned upward and the rotor of each engine is directed to the front while flying.
  • V / STOL aircraft have achieved their objectives in terms of vertical takeoff and landing, but due to their slow cruising speed, V / STOL aircraft are being developed.
  • the VZS TOL aircraft also had a rotor attached to the wing, and the entire wing was turned around to turn the rotor in the direction of travel.
  • the engine and rotor are attached to the tip of both main wings as one independent part, and the direction of the rotor is changed by changing the direction of the engine and the rotor integrally.
  • it is easy to change the direction of the mouth but since the engines are provided separately for the left and right main wings, it is necessary to separately install a transmission to match the rotation speeds of both rotors. Because the rotor is attached to the tip of the main wing, the length of the wing becomes shorter when the rotor is closer to the fuselage, and the rotor becomes farther when the wing is longer, causing a problem in strength. Disclosure of the invention
  • the main wing is attached to the fuselage, the rotor is installed under both the left and right wings, and the air flow is sent downward so that vertical takeoff and landing can be performed.
  • the rotor is high enough above the ground to prevent people from touching the rotor.
  • the engine that gives rotation to the rotor is housed separately. Because the same engine transmits the rotational motion of the two rotors on the left and right through the shaft, the rotational speeds of the left and right rotors are always the same, making it easier to balance.
  • storing the heavy engine inside the vehicle increases the stability of the aircraft.
  • Rotational motion transmitted by the shaft from the engine is transmitted to the rotor shaft, and imparts rotational force to the rotor.
  • the rotor is horizontal to the ground when taking off and landing, but in high altitude air, the rotor moves behind the wings and moves perpendicular to the ground due to forward movement. That is, during takeoff and landing, the rotor is parallel to the lower part of the wing, and during flight, the rotor moves to the rear of the wing and is oriented perpendicular to the wing.
  • the rotor The mechanism.
  • the position where the rotor is mounted is determined by the length of the wing and the length of the rotor, but it will be located 30% below the leading edge of the wing. For this reason, to move the rotor out of the rear of the wing, the rotor attached to the wing must be moved.
  • the rotation of the engine rotates the rotor shaft by means of belts and gears, and rotates the rotor below the main wing.
  • the rotor shaft is attached to the case together with the gears. Therefore, by moving the case to the rear of the wing and changing the direction of the case, the position and direction of the rotor can be changed.
  • An arm that integrates a pulley at the end of a belt attached to a shaft with a fulcrum at the rear of the main wing, a shaft at the tip of the belt, a shaft at the burry, and a case that supports the shaft of the rotor with a built-in gear coaxial with the booley shaft.
  • the rotor can be extended to the rear of the wing by moving it with a wire or by changing the direction of the case.
  • FIG. 1 is a perspective view of the vertical take-off and landing aircraft according to the present invention, in which a part is cut away
  • FIG. 2 is a perspective view of a part of a rotor on one side
  • FIG. Fig. 4 is a cross-sectional view of a part of the rotor when the rotor described in claim 2 is moved to the rear of the main wing.
  • Fig. 5 is a view when the vertical take-off and landing aircraft according to the present invention is hovering.
  • FIG. 6 shows an example of use when the vertical take-off and landing aircraft according to the present invention flies.
  • BEST MODE FOR CARRYING OUT THE INVENTION The present invention will be described in more detail with reference to the accompanying drawings.
  • FIG. 1 is a partially cutaway perspective view of a vertical take-off and landing aircraft according to the present invention.
  • Housing 1 has engine 2 and rotors 5 and 6 are provided below left wing 3 and right wing 4 .
  • the rotation of engine 2 is transmitted to rotors 5 and 6 by shaft 7, and after vertical ascent, rotor Features 5 and 6 turn to the rear of the wing to gain forward thrust.
  • the aircraft stabilizers 8 and 9 are set up to prevent the aircraft from tilting.
  • FIG. 2 is a perspective view of a part of one rotor.
  • a belt 13 is applied between the bullies 11 attached to the tip of the shaft 7 passing through the inside of the wing and the 12 attached to the shaft 10 to transmit the rotation of the engine to the shaft 10.
  • the shaft 10 is held between bearings 14 and 15 attached to the upper part of the cut portion of the wing, and is fitted into the central portion of the shaft 10 to bevel gear 16 and the tip of the rotor shaft 18 The rotation is transmitted to the bevel gears 1 and 7 and the rotor 5 is turned.
  • the rotor shaft 18 is held by a bearing 19 fixed inside the case 20.
  • Case 20 is attached to outer case 21. Further, the case 20 has servo motor containers 23 and 24 for operating the rotor controller 22 so as to house the servo motor.
  • the direction of case 20 is changed by the arm to move rotor 5 to the rear of the main wing and rotate it vertically.
  • FIG. 3 is a sectional view of a part of the rotor described in claim 2.
  • the pulley 25 has a shaft coaxial with the pulley 26 and is attached to the rear of the main wing.
  • the pulley 25 rotates, the pulley 26 also rotates, and the belt 27 transmits the rotation to the pulley 12.
  • the bevel gear 16 coaxial with the pulley 12 transmits the rotation to the bevel gear 19 attached to the tip of the rotor shaft 18 so that the rotor 5 can be turned.
  • the rotor shaft 18 is held by a bearing 19 attached to a case 20.
  • FIG. 4 is a sectional view of a part of the rotor when the rotor described in claim 2 is moved to the rear part of the main wing.
  • rotor 5 In order for rotor 5 to rotate vertically behind the wing, rotor 5 must not touch the wing. At a position 30% behind the leading edge of the wing where rotor 5 is fixed for vertical takeoff and landing, rotor 5 cannot rotate vertically without touching the wing. Therefore, it is necessary to move the rotor 5 backward.
  • FIG. 5 is an example of use when the vertical take-off and landing aircraft according to the present invention is hovering.
  • the rotor is rotating below the main wing.
  • FIG. 6 is an example of use when the vertical take-off and landing aircraft according to the present invention is flying, and shows a state where the rotor is rotating at the rear part of the main wing.
  • the vertical take-off and landing aircraft according to the present invention efficiently climbs vertically, flies at high speed, and is used for carrying people and cargo.

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

Abstract

La présente invention concerne un avion à décollage et atterrissage verticaux. Cet avion est d'un type économique. Les emplacements de montage des rotors sur la voilure peuvent être choisis librement. Il présente l'avantage de ne pas avoir besoin de piste et il est en mesure de voler à vitesse élevée en service normal. Les rotors sont réalisés de manière à pouvoir être décalés en direction du bord de fuite de la voilure pendant le vol, pour qu'ils tournent verticalement et perpendiculairement à la voilure, de telle sorte que la pression du vent peut être exploitée au maximum.
PCT/JP1995/002095 1995-06-15 1995-10-13 Avion a decollage et atterrissage verticaux WO1997000200A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU36735/95A AU3673595A (en) 1995-06-15 1995-10-13 Vertical takeoff and landing aircraft

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP18318695A JPH092395A (ja) 1995-06-15 1995-06-15 垂直離着陸機
JP7/183186 1995-06-15

Publications (1)

Publication Number Publication Date
WO1997000200A1 true WO1997000200A1 (fr) 1997-01-03

Family

ID=16131282

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/JP1995/002095 WO1997000200A1 (fr) 1995-06-15 1995-10-13 Avion a decollage et atterrissage verticaux

Country Status (3)

Country Link
JP (1) JPH092395A (fr)
AU (1) AU3673595A (fr)
WO (1) WO1997000200A1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9570639B2 (en) 2011-07-12 2017-02-14 Paulo Alexandre Teixeira E. Silva Cardoso System with gradual change of light distribution or shadow distribution on a surface comprising light elements or photovoltaic elements
JP5150001B1 (ja) * 2011-07-27 2013-02-20 和博 高橋 垂直離着陸機
JP5277342B1 (ja) * 2012-12-11 2013-08-28 和博 高橋 垂直離着陸機
JP6831756B2 (ja) * 2017-06-19 2021-02-17 株式会社日立製作所 飛行機械、輸送システム、および、輸送システムの運用方法

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH07502297A (ja) * 1991-12-17 1995-03-09 ザ　ダウ　ケミカル　カンパニー エポキシ樹脂の硬化に有用な水相溶性アミン末端樹脂

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH07502297A (ja) * 1991-12-17 1995-03-09 ザ　ダウ　ケミカル　カンパニー エポキシ樹脂の硬化に有用な水相溶性アミン末端樹脂

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
KOKU JOHO, No. 523, September 1, 1988 (Tokyo) TETSUO HARADA, "High Tech VTOL Planes in a Next Generation V-22 Osprey", p. 52-63. *
KOKU JOHO, No. 575, August 1, 1992 (Tokyo) TETSUO HARADA, "History and Future of VTOL Planes", p. 18-31. *

Also Published As

Publication number Publication date
AU3673595A (en) 1997-01-15
JPH092395A (ja) 1997-01-07

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