WO2011041991A2 - Aéronef utilisant une soufflante carénée pour la portance - Google Patents

Aéronef utilisant une soufflante carénée pour la portance Download PDF

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Publication number
WO2011041991A2
WO2011041991A2 PCT/CZ2010/000102 CZ2010000102W WO2011041991A2 WO 2011041991 A2 WO2011041991 A2 WO 2011041991A2 CZ 2010000102 W CZ2010000102 W CZ 2010000102W WO 2011041991 A2 WO2011041991 A2 WO 2011041991A2
Authority
WO
WIPO (PCT)
Prior art keywords
ring
rotor
aircraft
segment
wall jet
Prior art date
Application number
PCT/CZ2010/000102
Other languages
English (en)
Other versions
WO2011041991A3 (fr
Inventor
Zdenek Janda
Original Assignee
Zdenek Janda
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 Zdenek Janda filed Critical Zdenek Janda
Publication of WO2011041991A2 publication Critical patent/WO2011041991A2/fr
Publication of WO2011041991A3 publication Critical patent/WO2011041991A3/fr

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms

Definitions

  • This invention deals with aircraft in which the lifting force is produced by one central ducted fan (rotor in a ring) drawing air from above and pushing it downwards to the ground.
  • the flight direction of this aircraft is controlled by tilting of the aircraft, which produces a horizontal component of the total lifting force, inducing the aircraft to lateral, horizontal, movement in the required direction.
  • aircrafts using a ducted fan to produce lifting force are made in diameters of up to one metre.
  • Means of their control known so far are not sufficiently safe and effective for use in larger aircraft and for flights with a human crew.
  • Cyclic control of the rotor blades has been tested in the world for the tilt control, similarly to helicopters, but aircrafts using ducted fan for lift have a considerably smaller diameter of the rotor as compared to helicopters with comparable useful load, and therefore cyclic aerodynamic control forces take effect in a small distance from the aircraft's centre of gravity. This leads to big problems with flight stability and moreover this type of control is very complicated and subject to high dynamic stresses.
  • an aircraft using ducted fan to produce lifting force comprising a rotor surrounded by a ring, the substance of which consists in that the bottom surface of the ring is shaped continuously from the rotor towards the outer perimeter of the ring in such a way that in the axial - radial cross-section it contains three consecutive path segments where in the first segment the tangent of the bottom surface of the ring directs downwards from the rotor, in the second segment it directs upwards and in the third segment, up to the trailing edge, it directs downwards again, inside the central opening of the ring there is a group of control flaps arranged in such a way that between their surface and the opposite first segment of the bottom surface of the ring they form a slot for conversion of a part of the air flow leaving the rotor (2) to a wall jet held by the Coanda effect at the bottom surface of the ring, and the flaps have controllably adjustable positions and/or shape of their surface with regard
  • An aircraft according to the invention contains a group of control flaps inside the central opening of the ring that direct a part of the air leaving the rotor to a thin wall jet flowing on the bottom surface of the ring from the rotor to the trailing edge of the bottom surface of the ring and from there to the free space downwards to the ground.
  • the wall jet is held at the bottom surface of the ring by the effect of underpressure caused by the so called Coanda effect.
  • the bottom surface of the ring means such a part of the ring surface that lies below the plane passing through the rotor blades.
  • the bottom surface of the ring is shaped continuously from the rotor towards the outer perimeter of the ring in such a way that in the axial - radial cross-section it contains three consecutive path segments where in the first segment the tangent of the bottom surface of the ring directs downwards from the rotor, in the second segment it directs upwards and in the third segment, up to the trailing edge, it directs downwards again.
  • control flaps are arranged in such a way that the position and/or shape of their surface can be adjusted in a controlled way with regard to the opposite first segment of the ring surface, e.g. by swivelling, moving or deformation.
  • control flaps determine the volume of air that flows from the rotor to the slot between each flap and the ring, changing the mass flow and/or velocities of the wall jet in the corresponding places of the trailing edge of the bottom surface of the ring. This causes changes of aerodynamic forces at the corresponding sides of the aircraft, which produce the required tilting moment for tilt and movement of the aircraft in the required direction.
  • the control of the tilt and therefore the flight direction of the aircraft in accordance with the invention does not require any heavy body over ducted fan or complicated cyclic mechanisms, and as the aerodynamic forces produced this way act near the outer perimeter of the aircraft, the new control is effective and precise. Therefore, the new control is suitable even for aircrafts with a human crew.
  • figure 1 schematically shows a perspective view of an example of embodiment of an aircraft in accordance with the invention
  • figure 2 shows a cross-section of the example of embodiment of an aircraft in accordance with the invention from fig. 1.
  • fig. 2 shows, in the middle of the aircraft I there is a rotor 2 driven by the engine 3_.
  • the trailing edge 11_ of the bottom surface of the ring 4 is positioned on the outer perimeter of the ring _4.
  • the ring is connected to the reinforcing ring 8_ through fixed radial vanes 5_. Swivelling radial vanes 6, ensuring control of heading of the aircraft around the axial axis, are attached to fixed radial vanes.
  • the engine _3 is connected to the reinforcing ring 8 ⁇ through connection elements _9.
  • Landing gear parts 10_ are connected to the reinforcing ring _8.
  • the aircraft 1 contains the swivelling control flaps 7_ that are connected to the fixed radial blades _5 in a rotary way. Between the swivelling control flaps 1_ and the bottom surface of the ring _ there is a slot 12.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne un aéronef utilisant une soufflante carénée pour créer une force portante, comprenant des volets de commande (7) qui produisent au niveau de la surface inférieure de la bague (4) entourant le rotor (2), à partir d'une partie de l'air quittant le rotor (2), un jet de paroi maintenu à la surface par l'effet Coanda et s'écoulant vers la périphérie extérieure de la bague (4). La surface inférieure de la bague (4) est profilée de sorte qu'à proximité de la périphérie extérieure de la bague (4) le jet de paroi s'écoule vers le bas en direction du sol. Lors d'un changement de leur position et/ou de la forme de leur surface par rapport à la surface opposée de la bague (4), les volets de commande (7) modifient les vitesses et/ou les valeurs de débit massique à divers endroits du bord de fuite (11) de la surface inférieure de la bague (4). Ainsi, des modifications de forces aérodynamiques sur différents côtés de l'aéronef (1) sont commandées, et par conséquent, son inclinaison et son vol dans la direction requise
PCT/CZ2010/000102 2009-10-08 2010-09-24 Aéronef utilisant une soufflante carénée pour la portance WO2011041991A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CZPV2009-664 2009-10-08
CZ20090664A CZ303326B6 (cs) 2009-10-08 2009-10-08 Letadlo pohánené dmychadlem

Publications (2)

Publication Number Publication Date
WO2011041991A2 true WO2011041991A2 (fr) 2011-04-14
WO2011041991A3 WO2011041991A3 (fr) 2011-07-14

Family

ID=43708957

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CZ2010/000102 WO2011041991A2 (fr) 2009-10-08 2010-09-24 Aéronef utilisant une soufflante carénée pour la portance

Country Status (2)

Country Link
CZ (1) CZ303326B6 (fr)
WO (1) WO2011041991A2 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2016000668A1 (fr) * 2014-07-04 2016-01-07 Zdenek Janda Aéronef à décollage et atterrissage verticaux
WO2016170419A3 (fr) * 2015-04-24 2016-12-15 KREITMAYER MCKENZIE, Janja Réservoir d'air
US10464668B2 (en) 2015-09-02 2019-11-05 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles
US10875658B2 (en) 2015-09-02 2020-12-29 Jetoptera, Inc. Ejector and airfoil configurations
US11001378B2 (en) 2016-08-08 2021-05-11 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles
US11148801B2 (en) 2017-06-27 2021-10-19 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018027315A1 (fr) * 2016-08-08 2018-02-15 Cleo Robotics Inc. Véhicule aérien sans pilote et système de commande d'un véhicule aérien sans pilote

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH367715A (it) * 1958-03-20 1963-02-28 Bianchi Faustina Dispositivo di sostentazione per mezzi aerei
GB909466A (en) * 1960-03-26 1962-10-31 Temple Leslie Vertical take-off aircraft
GB2270510B (en) * 1992-09-11 1996-07-17 Charles John Cochrane Lift device
DE29914928U1 (de) * 1999-08-26 2001-02-08 Eckert, Jörg, 75323 Bad Wildbad Schwebe-/Gleit-Fluggerät
US20040164203A1 (en) * 2003-02-21 2004-08-26 Charles Billiu Vertical take-off and landing aircraft
AT500009A1 (de) * 2003-10-03 2005-10-15 Franz Autherith Flugkörper

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2016000668A1 (fr) * 2014-07-04 2016-01-07 Zdenek Janda Aéronef à décollage et atterrissage verticaux
WO2016170419A3 (fr) * 2015-04-24 2016-12-15 KREITMAYER MCKENZIE, Janja Réservoir d'air
US10464668B2 (en) 2015-09-02 2019-11-05 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles
US10875658B2 (en) 2015-09-02 2020-12-29 Jetoptera, Inc. Ejector and airfoil configurations
US11001378B2 (en) 2016-08-08 2021-05-11 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles
US11148801B2 (en) 2017-06-27 2021-10-19 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles

Also Published As

Publication number Publication date
CZ2009664A3 (cs) 2011-04-20
CZ303326B6 (cs) 2012-08-01
WO2011041991A3 (fr) 2011-07-14

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