WO2010005390A1 - Concept de pale de rotor pour adav - Google Patents

Concept de pale de rotor pour adav Download PDF

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Publication number
WO2010005390A1
WO2010005390A1 PCT/SE2009/050906 SE2009050906W WO2010005390A1 WO 2010005390 A1 WO2010005390 A1 WO 2010005390A1 SE 2009050906 W SE2009050906 W SE 2009050906W WO 2010005390 A1 WO2010005390 A1 WO 2010005390A1
Authority
WO
WIPO (PCT)
Prior art keywords
rotor
blades
mode
wings
wing
Prior art date
Application number
PCT/SE2009/050906
Other languages
English (en)
Inventor
Johan Olsson
Original Assignee
Swedish Control Systems Aktiebolag
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 Swedish Control Systems Aktiebolag filed Critical Swedish Control Systems Aktiebolag
Publication of WO2010005390A1 publication Critical patent/WO2010005390A1/fr

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Classifications

    • 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
    • B64C27/10—Helicopters with two or more rotors arranged coaxially
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
    • B64C27/24—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with rotor blades fixed in flight to act as lifting surfaces

Definitions

  • the presented invention relates to a new type of rotor wing that enables vertical takeoff and landing, like a helicopter and cruise flight like a normal aircraft.
  • Tilt-wing and tilt-rotor Of the different kind of prop or rotor based solutions that exist, there are two main types called Tilt-wing and tilt-rotor respectively.
  • the tilt wing type means that the complete wing, usually with a rotor arrangement at each wingtip can be tilted to horizontal for flying and vertical for take-off and landing.
  • tilt-wing is Canadair CL-84, a big plane with 2 x 1500 hp. This type of aircraft always has too small wings to be able to operate well for normal flight. This depends mostly on the fact that when tilted vertically - the wing will act as a sail, resulting in hazardous instability in windy circumstances.
  • a VTOL craft of the Tilt-rotor type has a solid wing mount where only the rotor arrangement can be tilted.
  • the rotor is positioned horizontally for flying and vertically for take-off and landing.
  • this configuration has the typical short and chubby wings. In this case, increased wing area would obstruct the airflow in hover mode.
  • a good example of tilt-rotor craft is the Bell Boeing V22. Also a large aircraft with two engines of 6000 hp each.
  • the invention relates to two counter rotating, two bladed rotors on a common geometric axis where each of these rotors can change the angle between the two rotor blades from 180 degrees when rotating in hover mode to app. 30.40 degrees when stopped in flight mode.
  • Hover mode consists of the two counter rotating rotors where normal pitch control is replaced by wing rudder.
  • one rotor blade is stopped at a desired position, e.g. app 90 degrees from the fuselage, while the other blade keeps rotating until another desired position, e.g. app 120.130 degrees angle from flight direction and stops.
  • This activity takes place at the same time for both rotors and results in two stationary wing pairs with the right orientation for the normal flight mode.
  • the rudder arrangement will be used as normal ailerons in flight mode.
  • VTOL-aircraft that has flying characteristics close to a normal aircraft - but with capacity for hovering and vertical take-off and landing.
  • the wing profile can be adapted for optimum performance in hover mode or in flight mode.
  • the wing profile In order to optimise for efficient hovering, the wing profile has to be adapted for low air speeds close to the hub and high airspeeds towards the tip. The cost of doing this, is of course decreased performance in flying mode. But this drawback has to be compared to more fundamental drawbacks of other solutions (see prior art above).
  • Figure 1 depicts an aircraft with a preferred embodiment of a rotor arrangement according to the invention, in normal flight mode.
  • Figure 2 depicts an aircraft with the preferred embodiment of a rotor arrangement according to the invention, in hover mode.
  • Figure 3 depicts an aircraft with the preferred embodiment of a rotor arrangement according to the invention, in an alternative flight mode.
  • An aircraft depicted in hover mode in fig. 2 and in flight mode in fig. 1 has aside from the rotor arrangements according to the invention, a normal fuselage 6 , normal elevators 10 and normal rudder 9 . On each side of the fuselage is arranged ducted fans 7,8 that are preferred to be electric.
  • the aircraft comprises two rotor wings 1,2 ; 3,4 formed by four rotor/wing blades 1, 2, 3, 4, wherein each blade has a leading edge L and a trailing edge T.
  • the rotor wings are arranged on a central hub 5 on the topside of the fuselage 6.
  • Each one of the blades 1, 2, 3, 4 is attached to its corresponding hub part 5A', 5A", 5B', 5B" which all can rotate/pivot in relation to each other.
  • the rotation of hub parts during hover mode are effectuated by the clockwise rotation of the top half of the hub 5 A and counter clockwise rotation of the lower half of the hub 5B (or vice versa) where the blades 1, 2 and 3, 4 respectively form two counter rotating wings as opposed to the normal flight mode where the hub parts 5A', 5A", 5B', 5B" are fixed in locations as shown in f ⁇ g.2, in such a way that the blades 1, 2 of one rotor wing effectively act as the left wing pair of the aircraft and the blades 3, 4 of the other rotor wing act as the right wing pair.
  • the hub 5 is divided into four coaxial, axially offset, hub parts 5A', 5A", 5B', 5B" which have separate rotational control.
  • Every hub part has a blade 1, 2, 3, 4, attached to it, and preferably every blade (normally at least two) has a controllable rudder arrangement 12, arranged at the trailing edge T .
  • the rudder arrangement acts as a normal ailerons in flight mode and it replaces the elevator and roll cyclic control of a helicopter in hover mode.
  • the revolution rate will mostly be considerably lower, the wing span mostly much bigger and the blade profile will mostly be more like a normal aircraft wing then a helicopter rotor blade.
  • Transit from hover to normal flight mode may be accomplished by the following steps:
  • Hub parts 5A', 5B' and their attached blades 1,3 are stopped abruptly into the positions shown in figure 1.
  • Hub parts 5A", 5B" with its blades 2 resp. 4 continue their respective rotation more than 90 degrees until they reach positions as shown in figure 1 where they are stopped.
  • the fans 7, 8 are set to maximum thrust until cruising speed is obtained.
  • the rudder arrangements 12 are operating as ailerons in a normal aircraft.
  • the tail also operates as any normal aircraft with its elevator and rudder controls.
  • Airspeed is lowered as much as possible.
  • the foremost rotor blades 1, 3 are started in their respective direction of rotation until they are lined up (on opposite sides of the rotor 5) with their respective counterpart blade 2, 4 .
  • the blades 1, 2; 3, 4 start in their respective direction of rotation with maximum acceleration.
  • VTOL aircraft with flight characteristics close to that of a normal aircraft - but with the capacity of vertical take off and landing and to hover.
  • the airfoil of the blades can be adopted for optimum hover capacity or optimum flight performance, or of course, something in between. If the airfoil is designed for optimum hover capacity - then it has to be optimized for low airspeed close to the hub and considerably higher air speed at the blade tip - which will have a negative impact on flight mode.
  • the rudder arrangement 12 can to some extent help to dynamically change airfoil behaviour in different flight modes, especially considering an embodiment providing the possibility of having multiple rudder arrangements per blade.
  • Figure 3 shows one form of embodiment that allows for a more simple hub mechanism.
  • the driving of hub parts is reduced to hub parts 5A' resp. 5B' and its respective blades 1 resp. 3 which in hover mode are driven in opposite directions.
  • the remaining hub parts 5A", 5B" with their blades 2, 4 are joined with its driven counterpart 5A', 5B' in such a way that the adjustment of angle between attached blades lvs 2, and 3 vs 4 respectively, are limited, e.g. maximised to 180 degrees.

Abstract

L’invention a pou objet un ADAV (aéronef à décollage et atterrissage verticaux) de meilleures performances de vol que ce qui était possible jusqu’alors. A cet effet, l’avion présente deux rotors bipales à rotation inverse sur un axe géométrique commun, chacun de ces rotors pouvant modifier l’angle principal entre les pales de rotor, de l’angle normal de 180 degrés en mode vol stationnaire à un angle d’environ 30/40 degrés en mode vol. Lors de la transition en mode vol, une pale de rotor est arrêtée à environ 90 degrés par rapport au fuselage, tandis que l’autre pale continue à tourner jusqu’à un angle d’environ 120/130 degrés par rapport à la direction du vol puis s’arrête. Cette action a lieu en même temps pour les deux rotors et se traduit par deux paires de pales fixes présentant une orientation correcte pour le mode vol normal.
PCT/SE2009/050906 2008-07-08 2009-07-16 Concept de pale de rotor pour adav WO2010005390A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
SE0801636A SE0801636A0 (sv) 2008-07-08 2008-07-08 Rotorvinge för VTOL flygplan
SE0801636-2 2008-07-08

Publications (1)

Publication Number Publication Date
WO2010005390A1 true WO2010005390A1 (fr) 2010-01-14

Family

ID=41507306

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/SE2009/050906 WO2010005390A1 (fr) 2008-07-08 2009-07-16 Concept de pale de rotor pour adav

Country Status (2)

Country Link
SE (1) SE0801636A0 (fr)
WO (1) WO2010005390A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014089604A1 (fr) * 2012-12-13 2014-06-19 Stoprotor Technology Pty Ltd Avion et ses procédés de fonctionnement
CN105480409A (zh) * 2016-01-06 2016-04-13 珠海市磐石电子科技有限公司 涵道动力装置及飞行器
WO2019241110A1 (fr) * 2018-06-13 2019-12-19 Wing Aviation Llc Pales d'hélice à montage concentrique pliables pour réduction de traînée
CN112389637A (zh) * 2019-08-13 2021-02-23 顺丰科技有限公司 垂起装置及飞行器
CN113895612A (zh) * 2021-09-08 2022-01-07 武汉思众空间信息科技有限公司 一种飞行器及其使用方法

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2653778A (en) * 1949-09-07 1953-09-29 Fairey Aviat Co Ltd Rotary-wing aircraft
US2665859A (en) * 1950-12-19 1954-01-12 Gyrodyne Company Of America In Aircraft with rotary and fixed wings
US3490720A (en) * 1968-11-26 1970-01-20 Ryan Aeronautical Co V/stol aircraft with variable geometry rotor/wing
EP0339098A1 (fr) * 1986-02-06 1989-11-02 John Mecca Véhicule à décollage vertical
US20070131820A1 (en) * 2005-12-09 2007-06-14 Sikorsky Aircraft Corporation Rotorcraft control system and method of using

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2653778A (en) * 1949-09-07 1953-09-29 Fairey Aviat Co Ltd Rotary-wing aircraft
US2665859A (en) * 1950-12-19 1954-01-12 Gyrodyne Company Of America In Aircraft with rotary and fixed wings
US3490720A (en) * 1968-11-26 1970-01-20 Ryan Aeronautical Co V/stol aircraft with variable geometry rotor/wing
EP0339098A1 (fr) * 1986-02-06 1989-11-02 John Mecca Véhicule à décollage vertical
US20070131820A1 (en) * 2005-12-09 2007-06-14 Sikorsky Aircraft Corporation Rotorcraft control system and method of using

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014089604A1 (fr) * 2012-12-13 2014-06-19 Stoprotor Technology Pty Ltd Avion et ses procédés de fonctionnement
CN104870308A (zh) * 2012-12-13 2015-08-26 思道普劳特科技有限公司 飞行器和用于操作飞行器的方法
US9616995B2 (en) 2012-12-13 2017-04-11 Stoprotor Technology Pty Ltd Aircraft and methods for operating an aircraft
CN105480409A (zh) * 2016-01-06 2016-04-13 珠海市磐石电子科技有限公司 涵道动力装置及飞行器
WO2019241110A1 (fr) * 2018-06-13 2019-12-19 Wing Aviation Llc Pales d'hélice à montage concentrique pliables pour réduction de traînée
US10843795B2 (en) 2018-06-13 2020-11-24 Wing Aviation Llc Folding concentrically mounted propeller blades for drag reduction
AU2019284351B2 (en) * 2018-06-13 2021-10-21 Wing Aviation Llc Folding concentrically mounted propeller blades for drag reduction
CN112389637A (zh) * 2019-08-13 2021-02-23 顺丰科技有限公司 垂起装置及飞行器
CN112389637B (zh) * 2019-08-13 2022-04-05 丰翼科技(深圳)有限公司 垂起装置及飞行器
CN113895612A (zh) * 2021-09-08 2022-01-07 武汉思众空间信息科技有限公司 一种飞行器及其使用方法
CN113895612B (zh) * 2021-09-08 2023-08-01 武汉思众空间信息科技有限公司 一种飞行器及其使用方法

Also Published As

Publication number Publication date
SE0801636L (sv) 2010-01-09
SE0801636A0 (sv) 2010-01-09

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