DE102022000073A1 - Adjustable auxiliary wing as lift support for vertical take-off aircraft with non-pivotable lift rotors - Google Patents

Adjustable auxiliary wing as lift support for vertical take-off aircraft with non-pivotable lift rotors Download PDF

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Publication number
DE102022000073A1
DE102022000073A1 DE102022000073.3A DE102022000073A DE102022000073A1 DE 102022000073 A1 DE102022000073 A1 DE 102022000073A1 DE 102022000073 A DE102022000073 A DE 102022000073A DE 102022000073 A1 DE102022000073 A1 DE 102022000073A1
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Prior art keywords
auxiliary wing
lift
rotors
aircraft
vertical take
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Pending
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DE102022000073.3A
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German (de)
Inventor
gleich Anmelder Erfinder
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Individual
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Individual
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Priority to DE102022000073.3A priority Critical patent/DE102022000073A1/en
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    • 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
    • B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C25/52—Skis or runners

Abstract

Es handelt sich um einen Hilfsflügel für senkrecht startende und landende Fluggeräte mit einem oder mehreren, nicht schwenkbaren Rotoren.Dieser Hilfsflügel befindet sich im Bereich der Auftriebslinie des oder der Rotoren.Beim Vertikalflug und beim Übergang vom Vertikalflug in den Horizontalflug ist es notwendig, dass dieser Hilfsflügel mit seinem Anstellwinkel derart nachgestellt wird, dass er im Wesentlichen strömungsparallel zur Resultierenden vom Rotorabwind und Vorwärtsgeschwindigkeit ist.Erst im Horizontalfug wird ein Anstellwinkel gegenüber der Resultierenden aus Rotorabwind und Vorwärtsgeschwindigkeit eingestellt. Damit entlastet dieser Hilfsflügel mit seinem Auftrieb den oder die Hauptrotoren bei deren Auftriebserzeugung, was zur Reduzierung des Energieaufwandes führt.It is an auxiliary wing for vertically taking off and landing aircraft with one or more non-pivotable rotors. This auxiliary wing is located in the area of the lift line of the rotor or rotors. During vertical flight and the transition from vertical flight to horizontal flight, it is necessary that this Auxiliary wing is adjusted with its angle of attack in such a way that it is essentially flow-parallel to the resultant of rotor downwash and forward speed. This auxiliary wing thus relieves the load on the main rotor(s) with its buoyancy when generating lift, which leads to a reduction in the energy expenditure.

Description

Bei diesem Erfindung handelt es sich um einen Hilfsflügel für senkrecht startende und landende Fluggeräte mit einem oder mehreren, nicht schwenkbaren Rotoren.This invention is an auxiliary wing for vertical take-off and landing aircraft with one or more non-pivotable rotors.

Dieser Hilfsflügel befindet sich zum Beispiel im Bereich der Auftriebslinie des oder der Rotoren, damit sich das Nickmoment um die Querachse nicht wesentlich ändert. Im Falle eines Hubschraubers ist dies in der Rotorlinie (siehe Zeichnung 1).This auxiliary wing is located, for example, in the area of the lift line of the rotor or rotors, so that the pitching moment around the transverse axis does not change significantly. In the case of a helicopter, this is in the rotor line (see drawing 1).

Beim Vertikalflug und beim Übergang vom Vertikalflug in den Vorwärtsflug ist es notwendig, dass dieser Hilfsflügel mit seinem Anstellwinkel derart nachgestellt wird, dass er im Wesentlichen strömungsparallel zur Resultierenden vom Rotorabwind und Vorwärtsgeschwindigkeit ist.During vertical flight and the transition from vertical flight to forward flight, it is necessary for this auxiliary wing to be adjusted with its angle of attack in such a way that it is essentially flow-parallel to the resultant of rotor downwash and forward speed.

Damit wird sichergestellt, dass er keinen Auftrieb erzeugt und damit das Fluggerät nicht beeinflusst (siehe Zeichnung 2).This ensures that it does not generate any lift and therefore does not affect the aircraft (see drawing 2).

Erst im Vorwärtsflug wird ein Anstellwinkel gegenüber der Resultierenden aus Rotorabwind und Vorwärtsgeschwindigkeit eingestellt.Only in forward flight is an angle of attack set against the resultant of rotor downwash and forward speed.

Damit generiert der Hilfsflügel Auftrieb und entlastet den oder die Hauptrotoren bei deren Auftriebserzeugung, was zur Reduzierung des Energieaufwandes führt (siehe Zeichnung 3). Beim Übergang vom Vorwärtsflug in die Landephase wird das gleiche Verfahren umgekehrt durchgeführt.The auxiliary wing thus generates lift and relieves the main rotor or rotors during their lift generation, which leads to a reduction in energy consumption (see drawing 3). During the transition from forward flight to the landing phase, the same procedure is carried out in reverse.

Merkmale zur Patentbeschreibung:

  • - Einfacher kleiner Tragflügel ohne Klappen und Ruder
  • - Einfacher Strukturaufbau mit verbundenem, durchgehenden Holm, beweglich um die y-Achse zur Veränderung des Anstellwinkels
  • - Aerodynamisch kaum negativer Einfluss beim Vertikal- und beim Transitionsflug
  • - Aerodynamisch optimal einstellbar für den Vorwärtsflug und damit Entlastung des Auftriebes der Rotoren, was zur wesentlichen Erhöhung des Gesamtwirkungsgrades beiträgt.
  • - Erhebliche Reduktion des Gier-Momentes beim Start und bei der Landung
  • - Weiterhin wird der Gleitwinkel bei der Autorotation - falls die Rotoren diese ermöglichen - erheblich erhöht, was zur Sicherheit beiträgt.
  • - Struktur nutzbar als Ausleger für die Landekufen
  • - Geschlossener Flügelkörper nutzbar als Schwimmkörper.
Characteristics of the patent description:
  • - Simple small hydrofoil without flaps and rudder
  • - Simple structural design with connected, continuous spar, movable around the y-axis to change the angle of attack
  • - Hardly any aerodynamic negative influence in vertical and transition flight
  • - Aerodynamically optimally adjustable for forward flight and thus relieving the buoyancy of the rotors, which contributes to a significant increase in overall efficiency.
  • - Significant reduction in yaw moment during takeoff and landing
  • - Furthermore, the glide angle during autorotation - if the rotors allow it - is significantly increased, which contributes to safety.
  • - Structure usable as outrigger for the landing skids
  • - Closed wing body can be used as a float.

Claims (1)

Die Ansprüche beziehen sich auf einen Hilfsflügel für alle Arten von senkrecht startenden Fluggeräten mit nicht schwenkbaren Auftriebs-Rotor / -Rotoren dadurch gekennzeichnet, dass a) der Hilfsflügel durch Verstellung seines Anstellwinkels für die unterschiedlichen Flugzustände einstellbar ist. b) der Hilfsflügel einen Beitrag zum Auftrieb des Fluggerätes im Vorwärtsflug erbringt. c) der Hilfsflügel strömungsparallel zum Abwind des/ der Hauptrotoren gestellt werden kann, um den Vertikalstart nicht aerodynamisch zu mindern. d) der Hilfsflügel auch als Landekufe verwendbar ist. e) Der strukturell geschlossene Hilfsflügel auch als Schwimmkörper verwendbar ist.The claims relate to an auxiliary wing for all types of vertical take-off aircraft with non-pivotable lift rotors, characterized in that a) the auxiliary wing can be adjusted by adjusting its angle of attack for different flight conditions. b) the auxiliary wing contributes to the lift of the aircraft in forward flight. c) the auxiliary wing can be positioned parallel to the downwash of the main rotor(s) in order not to aerodynamically reduce the vertical take-off. d) the auxiliary wing can also be used as a landing skid. e) The structurally closed auxiliary wing can also be used as a floating body.
DE102022000073.3A 2022-01-12 2022-01-12 Adjustable auxiliary wing as lift support for vertical take-off aircraft with non-pivotable lift rotors Pending DE102022000073A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE102022000073.3A DE102022000073A1 (en) 2022-01-12 2022-01-12 Adjustable auxiliary wing as lift support for vertical take-off aircraft with non-pivotable lift rotors

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102022000073.3A DE102022000073A1 (en) 2022-01-12 2022-01-12 Adjustable auxiliary wing as lift support for vertical take-off aircraft with non-pivotable lift rotors

Publications (1)

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DE102022000073A1 true DE102022000073A1 (en) 2023-07-13

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DE102022000073.3A Pending DE102022000073A1 (en) 2022-01-12 2022-01-12 Adjustable auxiliary wing as lift support for vertical take-off aircraft with non-pivotable lift rotors

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Citations (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2959373A (en) 1954-12-10 1960-11-08 Daniel R Zuck Convertiplane
DE2236415A1 (en) 1971-08-11 1973-03-08 Westland Aircraft Ltd HELICOPTER
JPH05229490A (en) 1992-02-20 1993-09-07 Mitsubishi Heavy Ind Ltd Helicopter
JPH07132893A (en) 1993-11-12 1995-05-23 Mitsubishi Heavy Ind Ltd Rotary-wing aircraft
US5478029A (en) 1992-11-06 1995-12-26 The United States Of America As Represented By The Administrator Of National Aeronautics And Space Administration Rotorcraft blade-vortex interaction controller
WO2006004416A1 (en) 2004-07-02 2006-01-12 Simicon As Hybrid aircraft
US20060169834A1 (en) 2005-01-28 2006-08-03 Arata Allen A Compound helicopter with combined wings and landing struts
US20110036954A1 (en) 2009-08-14 2011-02-17 Piasecki Frederick W Compound Aircraft with Autorotation
CN205381400U (en) 2016-02-22 2016-07-13 武汉智能鸟无人机有限公司 Aircraft
US20170217577A1 (en) 2016-02-03 2017-08-03 Hattar Tanin LLC Hybrid aircraft
US20170327218A1 (en) 2014-12-12 2017-11-16 Universite Pierre Et Marie Curie (Upmc) Light unmanned vertical take-off aircraft
CN106314761B (en) 2016-08-31 2018-11-23 北京航空航天大学 A kind of all-moving wing mechanism applied to small compound helicopter
CN110418755A (en) 2017-11-28 2019-11-05 深圳市大疆创新科技有限公司 A kind of unmanned vehicle
DE102018133096A1 (en) 2018-12-20 2020-06-25 Volocopter Gmbh Aircraft
US20210107637A1 (en) 2019-10-15 2021-04-15 Helmuth G. Bachmann Universally attachable hinged wing and vlos aid for mutirotor drones
US20210179260A1 (en) 2019-12-12 2021-06-17 Kfir Baranes Aircraft landing gear with wing configuration for enabling a smooth takeoff and landing

Patent Citations (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2959373A (en) 1954-12-10 1960-11-08 Daniel R Zuck Convertiplane
DE2236415A1 (en) 1971-08-11 1973-03-08 Westland Aircraft Ltd HELICOPTER
JPH05229490A (en) 1992-02-20 1993-09-07 Mitsubishi Heavy Ind Ltd Helicopter
US5478029A (en) 1992-11-06 1995-12-26 The United States Of America As Represented By The Administrator Of National Aeronautics And Space Administration Rotorcraft blade-vortex interaction controller
JPH07132893A (en) 1993-11-12 1995-05-23 Mitsubishi Heavy Ind Ltd Rotary-wing aircraft
WO2006004416A1 (en) 2004-07-02 2006-01-12 Simicon As Hybrid aircraft
US20060169834A1 (en) 2005-01-28 2006-08-03 Arata Allen A Compound helicopter with combined wings and landing struts
US20110036954A1 (en) 2009-08-14 2011-02-17 Piasecki Frederick W Compound Aircraft with Autorotation
US20170327218A1 (en) 2014-12-12 2017-11-16 Universite Pierre Et Marie Curie (Upmc) Light unmanned vertical take-off aircraft
US20170217577A1 (en) 2016-02-03 2017-08-03 Hattar Tanin LLC Hybrid aircraft
CN205381400U (en) 2016-02-22 2016-07-13 武汉智能鸟无人机有限公司 Aircraft
CN106314761B (en) 2016-08-31 2018-11-23 北京航空航天大学 A kind of all-moving wing mechanism applied to small compound helicopter
CN110418755A (en) 2017-11-28 2019-11-05 深圳市大疆创新科技有限公司 A kind of unmanned vehicle
DE102018133096A1 (en) 2018-12-20 2020-06-25 Volocopter Gmbh Aircraft
US20210107637A1 (en) 2019-10-15 2021-04-15 Helmuth G. Bachmann Universally attachable hinged wing and vlos aid for mutirotor drones
US20210179260A1 (en) 2019-12-12 2021-06-17 Kfir Baranes Aircraft landing gear with wing configuration for enabling a smooth takeoff and landing

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