US20050151030A1 - Lifting surface provided with at least one rotary flap - Google Patents

Lifting surface provided with at least one rotary flap Download PDF

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Publication number
US20050151030A1
US20050151030A1 US10/823,582 US82358204A US2005151030A1 US 20050151030 A1 US20050151030 A1 US 20050151030A1 US 82358204 A US82358204 A US 82358204A US 2005151030 A1 US2005151030 A1 US 2005151030A1
Authority
US
United States
Prior art keywords
flap
lifting surface
surface according
leading edge
trailing edge
Prior art date
Legal status (The legal status 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 status listed.)
Abandoned
Application number
US10/823,582
Other languages
English (en)
Inventor
Gilles Arnaud
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Helicopters SAS
Original Assignee
Eurocopter SA
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 Eurocopter SA filed Critical Eurocopter SA
Assigned to EUROCOPTER reassignment EUROCOPTER ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: ARNAUD, GILLES
Publication of US20050151030A1 publication Critical patent/US20050151030A1/en
Abandoned legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • B64C9/02—Mounting or supporting thereof
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
    • B64C27/58—Transmitting means, e.g. interrelated with initiating means or means acting on blades
    • B64C27/59—Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical
    • B64C27/615—Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical including flaps mounted on blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
    • B64C9/16—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing
    • B64C9/18—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing by single flaps
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
    • B64C27/72—Means acting on blades
    • B64C2027/7205—Means acting on blades on each blade individually, e.g. individual blade control [IBC]
    • B64C2027/7261—Means acting on blades on each blade individually, e.g. individual blade control [IBC] with flaps
    • B64C2027/7266—Means acting on blades on each blade individually, e.g. individual blade control [IBC] with flaps actuated by actuators
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/30—Wing lift efficiency

Definitions

  • This invention concerns a lifting surface provided with at least one rotary flap.
  • said lifting surface at the trailing edge of which the flap is mounted is a helicopter rotor blade, in particular a blade of the helicopter main advance and lifting rotor.
  • a helicopter rotor blade in particular a blade of the helicopter main advance and lifting rotor.
  • it may also consist of a rotorcraft blade or that of a convertible aircraft or the lifting device of such an aircraft such as a horizontal stabilizer wing, for instance.
  • This invention is designed to overcome these drawbacks by proposing a rotary flap with minimized hinge moment.
  • the rotary flap that is liable to rotate about a longitudinal axis of rotation defined according to the first span of said flap, with said flap having a profile extending along the flap chord and including a first leading edge, a first trailing edge, and inner surface and an outer surface, is remarkable in that:
  • the flap described in the invention has a very reduced hinge moment when it Is mounted on a lifting surface, but without losing any efficiency in doing so. This results in an energy gain for the actuator (by rotating) the flap and therefore, in particular, also a gain in mass.
  • said inner and said outer surfaces may have forms that are approximately linear or may be convex.
  • said first trailing edge has an elliptical shape whose major axis to minor axis quotient is greater than or equal to 1.5 and preferably, to approximately equal to 2.
  • the first trailing edge should be beveled but it is impossible to produce a perfect bevel by industrial means because a very slight rounding off of the first trailing edge is necessary to prevent the breakage of the composite fibers enclosing this first trailing edge.
  • the curve radius of the first trailing edge must not be too large, so as to set the confluence points of the air flows on the inner and outer surface and thus prevent a diversion around the first trailing edge by the air flows, which would be detrimental to the aerodynamic efficiency of the flap.
  • said main angle of the first trailing edge is approximately 20° and/or said axis of rotation of the flap Is situated at a first distance from the first leading edge, corresponding approximately 25.5% of the chord so as to bring the axis of the hinge, the aerodynamic focus and the center of gravity of said flap to correspond as accurately as possible.
  • This invention also concerns a lifting surface, for instance the rotor blade of a helicopter or an aircraft wing, provided with a second leading edge, as well as a second trailing edge, and which includes in addition at least one flap mounted to rotate on the second trailing edge while leaving a clearance between said second trailing edge of the lifting surface, and the first leading edge of the flap.
  • a lifting surface for instance the rotor blade of a helicopter or an aircraft wing, provided with a second leading edge, as well as a second trailing edge, and which includes in addition at least one flap mounted to rotate on the second trailing edge while leaving a clearance between said second trailing edge of the lifting surface, and the first leading edge of the flap.
  • said lifting surface is outstanding in that said flap is of the aforementioned type.
  • the second trailing edge of the lifting surface partially covers the first leading edge of the flap.
  • said partial overlapping of the first leading edge of the flap by the second trailing edge of the lifting surface is less than approximately 10% of the flap chord.
  • the lifting surface conforming to the invention includes in addition, at least one filling means, preferably deformable, to fill the opening created by said clearance, in addition, in an advantageous manner, said filling means is located in a reference surface of the lifting surface.
  • said lifting surface includes a multitude of flaps arranged according to the second span of said lifting surface.
  • This arrangement of said flaps Is chosen to prevent them blocking under the effect of the overall deformation in the lifting surface (for instance a blade) during the flight.
  • a succession of (elementary) flaps is recommended whose first span does not exceed (in each case) 15% of the second span and Is preferably included between 7% and 10%.
  • FIG. 1 is a schematic view of the profile of a flap conforming to the invention provided with a rotary flap.
  • FIG. 2 is a schematic view of the profile of a lifting surface conforming to the invention.
  • FIG. 3 is a schematic view of the profile of a flap conforming to the invention, combined with a lifting surface represented in part.
  • FIG. 4 is a schematic view of the profile of a lifting surface provided with a multitude of flaps conforming to the invention.
  • a flap 1 conforming to the invention and shown schematic only in FIG. 1 is liable to be mounted to rotate on the second trailing edge 2 of a lifting surface 3 , as shown in FIG. 2 .
  • said flap 1 is liable to rotate about an axis of rotation 4 (or hinged axis), defined according to the first span 5 of said flap 1 and therefore according to the span of the lifting surface 3 specified below.
  • said flap 1 has a profile 6 (the contour of the section represented in FIG. 1 ) extending according to the chord CO and includes a first leading edge 7 , a first trailing edge 8 , an inner surface 9 and an outer surface 10 .
  • said flap 1 has the following combined characteristics;
  • said first trailing edge 8 has an elliptical shape of which the second major axis to minor axis quotient Is greater than 1.5, and preferably approximately equal to 2.
  • said axis of rotation 4 of flap 1 is placed at a first distance C 1 from the first leading-edge 7 corresponding approximately to 25.5% of chord CO.
  • flap 1 described in the invention has a very reduced hinge moment when it is mounted on a lifting surface 3 , but without losing too much efficiency in doing so. This results in an energy gain for actuating (by rotating) flap 1 and a gain in mass. In this way, it is possible to use the customary means of actuation to ensure optimum actuation of said flap I conforming to the invention.
  • flap 1 may be mounted on a lifting surface 3 (for instance on a helicopter blade or an aircraft wing or stabilizer) so as to be moved in rotation through the customary actuating means 12 as depicted diagrammatically,
  • these actuating means 12 may be of the electromagnetic type or based on so-called “intelligent” materials of the piezo-electric, magneto-restrictive or shape memory type, for instance.
  • Flap 1 is mounted on lifting surface 3 in such a way as to create a clearance 13 between the second trailing edge 2 of lifting surface 3 and the first leading edge of 7 of flap 1 , to prevent mechanical locking during the actuation of flap 1 , for instance because of the mechanical deformation of lifting surface 3 or flap 1 , or of its actuator, under centrifugal and aerodynamic forces.
  • said clearance 13 is :
  • flap 1 includes the customary filling means 14 , of a seal type, to block said clearance 13 (i.e., the opening created by clearance 13 ) and thus avoid unwanted aerodynamic recirculation which could considerably increase the hinge moment and decrease the lifting efficiency of flap 1 .
  • These filling means 14 could be rubber padding attached to the first leading edge 7 of flap 1 or pieces of fabric attached to lifting surface 3 and flat 1 , preferably within a reference surface 11 defined by all the straight lines joining the first leading edge 7 to the first trailing edge 8 when flap 1 is in the neutral position, i.e. when the first 7 , 8 and the second 16 , 2 leading and training edges are more or less aligned.
  • the second trailing edge 2 of lifting surface 3 partially overlaps the first leading edge 7 of flap 1 .
  • said partial overlapping P of the first leading edge 7 by the second trailing edge 2 Is less than 10% of the chord CO of flap 1 .
  • lifting surface 3 includes a multitude of flaps 1 of the aforementioned type, set out along the second span of lifting surface 3 in addition, the first span 5 of each of said flaps 1 Is less than or equal to 15% of the second span and is preferably included between 7% and 10% of this second span.
  • this invention Is applied to the main advance and lifting rotor blades of a helicopter in which the lifting surface 3 part illustrated in FIG. 2 (or in FIG. 4 ) represents in this case, a blade section.
  • this invention and allows the vertical trajectory of each blade to be controlled on each revolution of the helicopter rotor, together with local distribution of the lifting force on the blade and up for the generation of turbulence from the blade in order to minimize the interaction between each blade and the turbulence formed in the outer wake of the blade, known as BVI or Played Vortex interaction.
  • BVI Played Vortex interaction.
  • This will reduce the noise because the impact of the marginal vortex causes local variations in pressure, generating impulsive noise. It will minimize the components in (b ⁇ 1) ⁇ , b ⁇ and (b+1) ⁇ of the forces on the blade (where b is the number of blades and ⁇ the rotor rotation configuration), resulting in a considerable reduction of helicopter vibration levels and accordingly, a substantial Improvement of comfort in the cabin.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Toys (AREA)
  • Operating, Guiding And Securing Of Roll- Type Closing Members (AREA)
US10/823,582 2003-04-14 2004-04-14 Lifting surface provided with at least one rotary flap Abandoned US20050151030A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0304635 2003-04-14
FR0304635A FR2853622B1 (fr) 2003-04-14 2003-04-14 Volet rotatif et element sustentateur, en particulier pale d'helicoptere, muni d'un tel volet rotatif

Publications (1)

Publication Number Publication Date
US20050151030A1 true US20050151030A1 (en) 2005-07-14

Family

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Family Applications (3)

Application Number Title Priority Date Filing Date
US10/823,582 Abandoned US20050151030A1 (en) 2003-04-14 2004-04-14 Lifting surface provided with at least one rotary flap
US10/823,604 Abandoned US20050001104A1 (en) 2003-04-14 2004-04-14 Rotary flap
US11/601,681 Expired - Fee Related US7891610B2 (en) 2003-04-14 2006-11-20 Rotary flap

Family Applications After (2)

Application Number Title Priority Date Filing Date
US10/823,604 Abandoned US20050001104A1 (en) 2003-04-14 2004-04-14 Rotary flap
US11/601,681 Expired - Fee Related US7891610B2 (en) 2003-04-14 2006-11-20 Rotary flap

Country Status (3)

Country Link
US (3) US20050151030A1 (de)
EP (1) EP1468909B1 (de)
FR (1) FR2853622B1 (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20050001104A1 (en) * 2003-04-14 2005-01-06 Gilles Arnaud Rotary flap
US20100181415A1 (en) * 2007-06-28 2010-07-22 Eurocopter Deutschland Gmbh Rotor blade for a rotary wing aircraft
US8591174B1 (en) * 2008-11-20 2013-11-26 David Wenzhong Gao Wind aeolipile
US8915710B2 (en) 2005-12-09 2014-12-23 Sikorsky Aircraft Corporation Brushless direct current (BLDC) motor based linear or rotary actuator for helicopter rotor control

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US20050127239A1 (en) * 2003-08-25 2005-06-16 Srivastava Varad N. Flying work station
US7014142B2 (en) * 2004-02-03 2006-03-21 The Boeing Company Low-drag rotor/wing flap
US7316539B2 (en) * 2005-04-07 2008-01-08 Siemens Power Generation, Inc. Vane assembly with metal trailing edge segment
US20070131820A1 (en) * 2005-12-09 2007-06-14 Sikorsky Aircraft Corporation Rotorcraft control system and method of using
US20110126699A1 (en) * 2008-10-20 2011-06-02 Mabon Briola Universal weapon stabilizer
DE102012112405B4 (de) * 2012-12-17 2017-06-08 Airbus Defence and Space GmbH Gekrümmter Flügelabschnitt mit einer schwenkbaren Hinterkantenklappe
US10287006B1 (en) 2015-12-18 2019-05-14 Amazon Technologies, Inc. Adjustable propeller blades for sound control
US10370098B1 (en) * 2015-12-18 2019-08-06 Amazon Technologies, Inc. Adjustable propeller blade with sound flaps
US9592910B1 (en) 2015-12-18 2017-03-14 Amazon Technologies, Inc. Geometrically reconfigurable propellers
WO2018199765A1 (en) * 2017-04-27 2018-11-01 Koren Henrik Aas Foldable chair mounted child seat
CN110341935B (zh) * 2019-07-26 2022-07-15 哈尔滨工业大学 一种展向伸缩式变形机翼
CN112173072A (zh) * 2020-09-25 2021-01-05 中国直升机设计研究所 一种高速直升机舵面操纵机构
CN114320736A (zh) * 2022-01-04 2022-04-12 上海电气风电集团股份有限公司 风电叶片及其叶片动态失速控制方法
CN114516386B (zh) * 2022-02-10 2023-12-15 上海衡拓船舶设备有限公司 一种全航速襟翼鱼尾鳍

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US2321837A (en) * 1940-11-12 1943-06-15 Frank R Makwell Airplane and control device therefor
US2349454A (en) * 1941-02-26 1944-05-23 Cons Vultee Aircraft Corp Ammunition container
US2383635A (en) * 1943-03-06 1945-08-28 Budd Edward G Mfg Co Airfoil tip construction
US2478792A (en) * 1946-07-02 1949-08-09 Trey Serge Airship
US2805830A (en) * 1952-07-01 1957-09-10 Helmut P G A R Von Zborowski Annular lift-producing wing
US3118639A (en) * 1961-12-05 1964-01-21 California Inst Res Found Control and propulsion fluid foil
US3174711A (en) * 1963-08-19 1965-03-23 Matthew A Sullivan Wing structure
US4169567A (en) * 1974-12-13 1979-10-02 Tamura Raymond M Helicopter lifting and propelling apparatus
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US5320491A (en) * 1992-07-09 1994-06-14 Northern Power Systems, Inc. Wind turbine rotor aileron
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US6267331B1 (en) * 1997-06-26 2001-07-31 Ramot University Authority For Applied Research & Industrial Development Ltd. Airfoil with dynamic stall control by oscillatory forcing
US6598834B2 (en) * 2000-02-14 2003-07-29 Aerotech Services Inc. Method for reducing fuel consumption in aircraft
US6705838B1 (en) * 1999-08-25 2004-03-16 Forskningscenter Riso Modified wind turbine airfoil
US6764047B2 (en) * 2001-01-26 2004-07-20 Todd Scott Miller Model airplane hinge construction
US6970773B2 (en) * 2004-03-10 2005-11-29 Utah State University Apparatus and method for reducing induced drag on aircraft and other vehicles

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GB734446A (en) * 1953-03-20 1955-08-03 Armstrong Whitworth Co Eng Operating the flaps of aircraft wings
US5374162A (en) * 1993-11-30 1994-12-20 United Technologies Corporation Airfoil having coolable leading edge region
US20020005458A1 (en) * 2000-06-09 2002-01-17 Carter Jay W. Airfoil suitable for forward and reverse flow
FR2853622B1 (fr) * 2003-04-14 2005-05-27 Eurocopter France Volet rotatif et element sustentateur, en particulier pale d'helicoptere, muni d'un tel volet rotatif

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2112154A (en) * 1935-08-02 1938-03-22 Randolph F Hall Airplane
US2321837A (en) * 1940-11-12 1943-06-15 Frank R Makwell Airplane and control device therefor
US2349454A (en) * 1941-02-26 1944-05-23 Cons Vultee Aircraft Corp Ammunition container
US2383635A (en) * 1943-03-06 1945-08-28 Budd Edward G Mfg Co Airfoil tip construction
US2478792A (en) * 1946-07-02 1949-08-09 Trey Serge Airship
US2805830A (en) * 1952-07-01 1957-09-10 Helmut P G A R Von Zborowski Annular lift-producing wing
US3118639A (en) * 1961-12-05 1964-01-21 California Inst Res Found Control and propulsion fluid foil
US3174711A (en) * 1963-08-19 1965-03-23 Matthew A Sullivan Wing structure
US4169567A (en) * 1974-12-13 1979-10-02 Tamura Raymond M Helicopter lifting and propelling apparatus
US4519563A (en) * 1974-12-13 1985-05-28 Tamura Raymond M Pollution reducing aircraft propulsion
US4519746A (en) * 1981-07-24 1985-05-28 United Technologies Corporation Airfoil blade
US4624203A (en) * 1984-04-19 1986-11-25 Ferguson R Stirling Batten structure for a wing sail
US4770113A (en) * 1985-05-02 1988-09-13 Walker John G Wingsail systems
US4982679A (en) * 1985-05-02 1991-01-08 Walker John G Wingsail flap torque equalization
US5407153A (en) * 1991-02-25 1995-04-18 Valsan Partners System for increasing airplane fuel mileage and airplane wing modification kit
US5167387A (en) * 1991-07-25 1992-12-01 Vigyan, Inc. Porous airfoil and process
US5320491A (en) * 1992-07-09 1994-06-14 Northern Power Systems, Inc. Wind turbine rotor aileron
US5342004A (en) * 1992-10-02 1994-08-30 Eagle Aerospace, Inc. Airfoil trailing flap
US6267331B1 (en) * 1997-06-26 2001-07-31 Ramot University Authority For Applied Research & Industrial Development Ltd. Airfoil with dynamic stall control by oscillatory forcing
US6109567A (en) * 1998-01-14 2000-08-29 Munoz Saiz; Manuel Flight controls with automatic balance
US6705838B1 (en) * 1999-08-25 2004-03-16 Forskningscenter Riso Modified wind turbine airfoil
US6598834B2 (en) * 2000-02-14 2003-07-29 Aerotech Services Inc. Method for reducing fuel consumption in aircraft
US6764047B2 (en) * 2001-01-26 2004-07-20 Todd Scott Miller Model airplane hinge construction
US6970773B2 (en) * 2004-03-10 2005-11-29 Utah State University Apparatus and method for reducing induced drag on aircraft and other vehicles

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20050001104A1 (en) * 2003-04-14 2005-01-06 Gilles Arnaud Rotary flap
US20070063109A1 (en) * 2003-04-14 2007-03-22 Eurocopter Rotary flap
US7891610B2 (en) 2003-04-14 2011-02-22 Eurocopter Rotary flap
US8915710B2 (en) 2005-12-09 2014-12-23 Sikorsky Aircraft Corporation Brushless direct current (BLDC) motor based linear or rotary actuator for helicopter rotor control
US20100181415A1 (en) * 2007-06-28 2010-07-22 Eurocopter Deutschland Gmbh Rotor blade for a rotary wing aircraft
US8591174B1 (en) * 2008-11-20 2013-11-26 David Wenzhong Gao Wind aeolipile
US11619204B2 (en) 2008-11-20 2023-04-04 Tennessee Technological University Wind aeolipile

Also Published As

Publication number Publication date
US7891610B2 (en) 2011-02-22
FR2853622B1 (fr) 2005-05-27
EP1468909B1 (de) 2006-06-21
FR2853622A1 (fr) 2004-10-15
US20070063109A1 (en) 2007-03-22
EP1468909A1 (de) 2004-10-20
US20050001104A1 (en) 2005-01-06

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Owner name: EUROCOPTER, FRANCE

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:ARNAUD, GILLES;REEL/FRAME:014825/0275

Effective date: 20040408

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION