WO2005058696A1 - Dispositif capable de decoller verticalement sans l'aide de rotors - Google Patents

Dispositif capable de decoller verticalement sans l'aide de rotors Download PDF

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Publication number
WO2005058696A1
WO2005058696A1 PCT/CN2004/000113 CN2004000113W WO2005058696A1 WO 2005058696 A1 WO2005058696 A1 WO 2005058696A1 CN 2004000113 W CN2004000113 W CN 2004000113W WO 2005058696 A1 WO2005058696 A1 WO 2005058696A1
Authority
WO
WIPO (PCT)
Prior art keywords
fan
wing
link
vertical lift
rotorless
Prior art date
Application number
PCT/CN2004/000113
Other languages
English (en)
Chinese (zh)
Inventor
Kaixing Gao
Zhiguo Li
Shengjun Liu
Original Assignee
Tangshan Da Tang Power Machinery Co., Ltd
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 Tangshan Da Tang Power Machinery Co., Ltd filed Critical Tangshan Da Tang Power Machinery Co., Ltd
Publication of WO2005058696A1 publication Critical patent/WO2005058696A1/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
    • B64C29/0025—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 fixed relative to the fuselage

Definitions

  • the invention relates to the technical field of an active vertical lift-off aircraft, in particular to a rotorless vertical lift-off device.
  • Object of the present invention is to provide an off vertically and overcome the drawbacks of the background art (2), a high CL: C D wing stay provided cruise lift, to overcome the drawbacks of the background art (2) In order to achieve the voyage-free vertical lift-off device.
  • the technical solution for achieving the above-mentioned object of the invention is:
  • the rotorless vertical lift-off device includes an engine, a gearbox, a fan, and other components, and it also includes wind shields at the left and right ends constituting a half-wind tunnel structure, and the fan is accommodated therein.
  • the fan blast air direction is provided with a stern wing group mechanism composed of fins, and each fin is movably installed on the left and right wind deflectors through its end shaft, and the fins are arranged from high to low along the air flow direction.
  • the sternwing group is equipped with a blade angle of attack adjustment mechanism.
  • the good aerodynamic shape formed by the upper and lower breathable "semi-wind tunnel structure" and the stern wing first generates lift, and after lift-off, it generates forward pull and thrust.
  • the formation of lift and pull depends on The angle-of-attack adjustment mechanism of the fins constituting the wing group.
  • the rotorless vertical lift-off device of the present invention is called "active vertical lift-off aircraft”.
  • the rotorless vertical lift-off device implemented in accordance with the above technical solution can only realize its value when installed on an aircraft.
  • the manufacture of a class of rotorless long-range helicopter WVH which is popularized and used, reduces the aircraft cost by a factor of two or more, reduces aircraft fuel consumption by 50% or less, reduces aircraft passenger and freight costs by 1/3 or less, and reduces aircraft failure rates. To about 1/10. So I actually used this hair
  • FIG. 1 is a schematic diagram of a connecting component / implementable structure of a lift device of the present invention.
  • the rotorless vertical lift-off device described in this embodiment is composed of an engine 1, a gearbox 2, a fan 3, a windshield 4, a fin 5, a link shaft knot 6, a posture adjustment link 7, a link hook 8, a slide Rail 9, handle 10, fixed axle wheel 11, attitude adjustment knot 12, directional knot 13, movable link 14, rectifying grid mechanism 15, engine 1-gearbox 2 behind the left and right windshields 4 (Figure The left and right panels are shown in the middle (the left and right panels are omitted) to form a half-wind tunnel structure, and the fan 3 is accommodated in the half-wind tunnel structure.
  • the fins 5 are movably mounted on the left and right windshields 4 through their end shafts.
  • the fins 5 are arranged from high to low along the airflow direction.
  • the wing group is equipped with an angle of attack adjustment mechanism of the fins 5.
  • -Each stern wing group in this embodiment is composed of 1 to 8 fins.
  • the wing angle of attack adjustment mechanism in this embodiment is a manual link mechanism.
  • the movable link 14 and the attitude adjustment link 7 of the linkage mechanism are positioned by the slide rail 9.
  • the upper end of the attitude adjustment link 7 passes through the link shaft.
  • the knot 6 is connected to the wing 5 and its lower end is connected to the movable link 14 through a link hook 8.
  • the movable link 14 forms a manual control mechanism through the directional knot 13, the posture adjusting knot 12, the fixed shaft wheel 11 and the handle 10.
  • the adjustment range of the angle of attack of the fins in this embodiment is 4 ° -15 °.
  • a rectifying grid 15 composed of upright and parallel rectifying plates is provided between the fan 3 and the wing group.
  • the rectifying grid is composed of 0 to 10 rectifying plates.
  • the fan 3-blade wing combination may be single-stage or multi-stage, and the range is 1 to 5 stages.
  • Fan 3 has a radius of 0.5 to 2.5 m and fan 3 has 2 to 30 blades.
  • the wing angle of attack adjustment mechanism described in the present invention may also be an electronic control mechanism, a servo control mechanism, or other mechanical control mechanisms.
  • the rotor-less vertical lift-off device belongs to a small aspect ratio.
  • the page is replaced (Details * 26) Force, and prevent the airflow from escaping to the left and right, and two baffles 4 are erected to accommodate the fan 3 and the stern wings, forming a "half wind tunnel" with upper and lower ventilation, each end of each small wing 5 It is sticky with dense fluff and elastically contacts the baffle 4 to form a dynamic airtightness in a "semi-wind tunnel".
  • SURE 0.42CL P oS W U 2 , system quality factor
  • the target of total takeoff weight / total engine power 6Kgf / KW can be achieved.
  • a multi-stage semi-wind tunnel structure can be used to distribute power on several fans, and lift is provided by several groups of wing.
  • a hollow shaft is used for the shaft, and nylon is used for the universal joint; a carbon fiber composite material is used for the combination of the shaft and the wing; and the fan blade is also made of a carbon fiber composite material.
  • the angle of attack ⁇ of each winglet 5 is 15 ° ⁇ Adjust within a range of 4 °.
  • the angle of attack ⁇ of each small fin 5 is 4 °, and the system resistance is minimal at this time to achieve high-speed cruising. Because each small wing 5 is staggered up and down, it can make This is a new set of lift. Thrust combination, high quality, can achieve vertical take-off and landing at zero speed, and can also achieve a range of R 1600 km.
  • the rotorless vertical lift-off device implemented in accordance with the above technical solution can only realize its value when installed on an aircraft.
  • the manufacture of a class of rotorless long-range helicopter WVH which is popularized and used, can reduce the cost of flying aircraft by 100% or more, reduce aircraft fuel consumption by 50% or less, reduce passenger and freight costs to 1/3 or less, and reduce aircraft failure.

Abstract

La présente invention concerne un aéronef capable de décoller verticalement, plus spécifiquement un dispositif capable de décoller verticalement sans l'aide de rotors. Outre un moteur, une boîte de vitesses et un ventilateur, le dispositif décrit dans cette invention comprend deux ensembles de panneaux sur les côtés gauche et droit conçus pour barrer le vent, lesquels ensembles définissent une structure en forme de demi tunnel aérodynamique. Le ventilateur est contenu dans ce tunnel. L'ensemble de volets est fixé le long du sens d'écoulement. Chaque volet est monté de manière rotative sur les panneaux de barrage du vent et chaque volet est disposé de haut en bas le long du sens de circulation de l'air. L'ensemble de volets est pourvu d'un mécanisme de réglage de l'angle d'attaque. La caractéristique de l'ensemble de volets est d'atteindre une valeur égale ou supérieure à CL/CD ≈ 20 ? 5. Le dispositif décrit dans cette invention consiste en une nouvelle combinaison de finesse aérodynamique, et il peut permettre un décollage et un atterrissage verticaux à une vitesse de croisière nulle et il peut atteindre une distance de croisière R≥ 1600km.
PCT/CN2004/000113 2003-12-18 2004-02-11 Dispositif capable de decoller verticalement sans l'aide de rotors WO2005058696A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN 200310118479 CN1629037A (zh) 2003-12-18 2003-12-18 无旋翼垂直升空装置
CN200310118479.0 2003-12-18

Publications (1)

Publication Number Publication Date
WO2005058696A1 true WO2005058696A1 (fr) 2005-06-30

Family

ID=34683157

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2004/000113 WO2005058696A1 (fr) 2003-12-18 2004-02-11 Dispositif capable de decoller verticalement sans l'aide de rotors

Country Status (2)

Country Link
CN (1) CN1629037A (fr)
WO (1) WO2005058696A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105947176A (zh) * 2016-04-08 2016-09-21 梁平 复合翼

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103754372B (zh) * 2013-10-01 2015-09-09 魏伯卿 能垂直起降空中停留和倒飞的飞机
CN107089321A (zh) * 2017-04-26 2017-08-25 浙江点辰航空科技有限公司 一种可调升力矢量推进式多旋翼无人机

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2657714A1 (de) * 1976-12-20 1978-06-22 Reinhard Oster Auftriebsvorrichtung fuer ein tragfluegel-flugzeug
WO1988005011A1 (fr) * 1987-01-03 1988-07-14 Christian Taramasco Avion a decollage et atterrissage verticaux
US6446908B1 (en) * 1999-08-12 2002-09-10 Manuel Munoz Saiz Aircraft lift arrangement
US20020139894A1 (en) * 2001-02-01 2002-10-03 Sorensen Bradford T. Roadable aircraft boat that flies in a wind of its own making

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2657714A1 (de) * 1976-12-20 1978-06-22 Reinhard Oster Auftriebsvorrichtung fuer ein tragfluegel-flugzeug
WO1988005011A1 (fr) * 1987-01-03 1988-07-14 Christian Taramasco Avion a decollage et atterrissage verticaux
US6446908B1 (en) * 1999-08-12 2002-09-10 Manuel Munoz Saiz Aircraft lift arrangement
US20020139894A1 (en) * 2001-02-01 2002-10-03 Sorensen Bradford T. Roadable aircraft boat that flies in a wind of its own making

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105947176A (zh) * 2016-04-08 2016-09-21 梁平 复合翼

Also Published As

Publication number Publication date
CN1629037A (zh) 2005-06-22

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