US3456904A - Jet flap control - Google Patents

Jet flap control Download PDF

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Publication number
US3456904A
US3456904A US647509A US3456904DA US3456904A US 3456904 A US3456904 A US 3456904A US 647509 A US647509 A US 647509A US 3456904D A US3456904D A US 3456904DA US 3456904 A US3456904 A US 3456904A
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US
United States
Prior art keywords
jet
flap
axis
flaps
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.)
Expired - Lifetime
Application number
US647509A
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English (en)
Inventor
Pierre Rene Leon Bernar Dorand
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Individual
Original Assignee
Individual
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Filing date
Publication date
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Publication of US3456904A publication Critical patent/US3456904A/en
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/325—Circulation-control rotors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
    • B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
    • B64C21/08—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like adjustable
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/12—Rotor drives
    • B64C27/16—Drive of rotors by means, e.g. propellers, mounted on rotor blades
    • B64C27/18—Drive of rotors by means, e.g. propellers, mounted on rotor blades the means being jet-reaction apparatus
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/04—Boundary layer controls by actively generating fluid flow
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/06—Boundary layer controls by explicitly adjusting fluid flow, e.g. by using valves, variable aperture or slot areas, variable pump action or variable fluid pressure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/16—Boundary layer controls by blowing other fluids over the surface than air, e.g. He, H, O2 or exhaust gases
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/28—Boundary layer controls at propeller or rotor blades
    • 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
    • Y02T50/10—Drag reduction

Definitions

  • the present invention relates to jet flaps in the trailing edge of an aerofoil such as an aircraft wing or helicopter rotor blade of the kind in which a gaseous jet emitted through a jet slit enables the lift of the wing or blade to be controlled by adjusting the sense and degree of vertical deflection of said jet in such a manner that when the jet is emitted neutrally, that is without deflection, it produces a suction effect which tends to make the airflow cling to the aerofoil section surface, thus affording boundary layer control.
  • this invention there is provided means for controlling the jet orifice both as to its effective crosssectional area and as to its splitting into two streams; this involves the provision of a secondary flap in addition to a jet deflector flap, and arrangements for the control thereof.
  • a jet flap of an aerofoil comprises a jet deflector flap hingedly mounted on the aerofoil on a spanwise axis which is thus parallel to the jet slit such axis also being adjacent to and preferably aft of the jet slit.
  • a secondary flap of aerofoil section which is mounted to swing articulately on the same axis.
  • Operating and actuating means are provided, of any suitable known kind not forming part of the invention, which can swing either or both of the deflector flap and the secondary flap.
  • the secondary flap both splits and controls the jet stream; this control is by varying the effective cross-sectional area of one of the split streams relative to the other and varying their total effective area.
  • a jet slit according to this invention is characterised by the fact that it combines a jet deflector flap which is hinged so as to be virtually a continuation of a well of the jet slit, and an aerofoil section secondary flap situated in the jet stream from the slit and which is articulated about the same axis as the jet deflector flap, the secondary flap being capable of movement independently of, or simultaneously with the deflector flap, in such a way as to vary the jet slit aperture which it divides into two adjustable sections.
  • the aperture configuration may be adljusted according to the temperature of the jet efflux: for example, when the fluid is heated in order to increase the force of the jet, it is desirable to increase the effective cross-sectional area of the jet aperture.
  • the forward speed may be increased by cyclic control of the jet aperture, enabling the jet efllux to be increased along the trailing edge of the advancing blade and reduced along the trailing edge of the retreating blade, thus providing additional propulsive thrust.
  • the control device may enable the jet slit aperture to 'be reduced so as to adjust it to the air suppply provided by the action of centrifugal force on the air contained in the blade, taking advantage of boundary layer control to increase the effectiveness of the "ice deflector flap.
  • simultaneous movement of both the aerofoil section flap and the deflector flap tends to give the jet the desired direction and has an eflect analogous to a form of swivelling jet slit.
  • FIGURES 1 and 2 represent the jet slit in vertical section with the secondary flap in two different positions, the deflector flap being maintained in its neutralposition.
  • FIGURES 3 and 4 represent the jet slit in two positions in which the deflector flap and secondary flap assembly is collectively moved respectively upward and downward.
  • a jet slit 1 is formed in the trailing edge of the aircraft wing or helicopter rotor blade and it is supplied with fluid under pressure.
  • a deflector flap 3 is hinged on the axis at 2, adjacent to the lower edge of the jet slit 1. It is controlled by an appropriate mechanism which does not constitute part of the present invention and is therefore not described or represented.
  • Supporting lugs 4 of aerofoil section secondary flap 5 are pivoted about the same axis 2, so that the secondary flap 5 is capable of rocking about this axis in the throat of the jet slit which it divides into two outlets 6 and 7, the flap 5 being so situated that its upper convex surface moves in close proximity to the upper edge of the jet slit 1.
  • the upper outlet 6 always remains much narrower than the lower section 7; the main object of the narrow slit 6 is to improve the airflow over the upper surface of the wing or rotor blade and over the upper surface of the secondary flap 5, whilst the larger slit 7 produces the main aerodynamic effect, acting as a jet flap.
  • the secondary flap 5 is shown tipped backward with its leading edge close to the upper edge of jet slit 1, whilst its trailing edge is close to the deflector flap 3, this latter being in its neutral position, the total aperture area of the jet slit being thus considerably reduced.
  • the secondary flap is tipped forward in such a manner that the aperture, constituted principally by the lower section 7, is considerably increased whilst aperture 6 is reduced, though not commensurately.
  • FIGURES 3 and 4 the 'whole assembly is shown in two positions in which the jet slit aperture remains constant, the jet being deflected upward in FIGURE 3 and downward in FIGURE 4 by simultaneously rotating deflector flap 3 and secondary flap 5 about axis 2.
  • the convex upper surface of the flap 5 is, or is nearly, arcuate about the axis 2.
  • the secondary flap 5 may, in the case of a helicopter rotor blade, be control-led by a cyclic mechanism in such a way as to open the aperture 7 along the trailing edge of the advancing blade and to close it along the trailing edge of the retreating blade,' thus providing additional propulsive thrust by cyclically differentiating between the ejected mass-flows in these two respec tive cases.
  • the deflector flap may be constructed in any appropriate manner.
  • the device according to the invention may be used with advantage in conjunction with a variable profile flap assembly constituted by a flexible metallic strip 8, of which the leading edge is attached to flap 3 and its trailing edge is attached to the trailing edge of a second flap part 9 freely hinged at its leading edge 10 to the trailing edge of deflector flap 3.
  • the adjunction of such a variable profile flap to the rigid deflector flap 3 improves its jet flap effect.
  • the operating means for controlling the angular positions of the deflector flap and of the secondary flap which per se do not form part of the invention. are of any suitable type, for instance such as described in my copending patent application Ser. No. 647,513 filed on June 20, 1967 for Jet Flaps or in the copending patent application Ser. No. 645,711 filed in the name of Marcel Kretz on June 13, 1967 for Jet Flap Controlling Means and assigned to the same assignee.
  • An aerofoil such as an aircraft wing or a helicopter rotor blade provided with a jet slit on its trailing edge, with means for discharging a gaseous jet from said jet slit and with jet deflecting means comprising a deflector flap having a first main rigid part hinged on an axis parallel to and adjacent to an edge of the jet slit, a second rigid part hingedly attached to the first rigid part on a second axis parallel to the jet slit adjacent to the rear edge of said main part, a flexible surface element exposed to the gaseous jet discharged from said jet slit and attached to the main part of said deflector flap and to the trailing edge of the second rigid part of said flap, operating means to swing said main and second parts of the deflector flap 'whereby relative angular movements of the main and second parts cause curvilinear deflections of said surface element, and an aerofoil section secondary flap situated in the jet discharged from the slit and articulated about the same axis as the
  • An aerofoil according to claim 1 further comprising means to swing the secondary flap independently of the deflector flap.
  • An aerofoil according to claim 1 further comprising means to swing the secondary flap simultaneously with the deflector flap.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Control Of Turbines (AREA)
  • Air-Flow Control Members (AREA)
US647509A 1966-06-20 1967-06-20 Jet flap control Expired - Lifetime US3456904A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR66167A FR1496152A (fr) 1966-06-20 1966-06-20 Tuyère pour aile d'avion ou pale d'hélicoptère soufflée

Publications (1)

Publication Number Publication Date
US3456904A true US3456904A (en) 1969-07-22

Family

ID=8611345

Family Applications (1)

Application Number Title Priority Date Filing Date
US647509A Expired - Lifetime US3456904A (en) 1966-06-20 1967-06-20 Jet flap control

Country Status (4)

Country Link
US (1) US3456904A (fr)
DE (1) DE1506591B1 (fr)
FR (1) FR1496152A (fr)
GB (1) GB1174496A (fr)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3940092A (en) * 1974-11-07 1976-02-24 The Boeing Company Jet flow deflector for aircraft
US6554229B1 (en) * 1997-12-18 2003-04-29 Lawrence Y. Lam Aileron for fixed wing aircraft
RU2220072C1 (ru) * 2002-06-07 2003-12-27 Дябин Николай Васильевич Самолет с плоским хвостовым оперением
US20090206208A1 (en) * 2006-03-22 2009-08-20 The Boeing Company Reaction drive rotor/wing variable area nozzle
US20100320332A1 (en) * 2007-02-23 2010-12-23 Airbus Operations Gmbh Spoiler for an aerodynamic body of an aircraft
US20110024556A1 (en) * 2009-08-03 2011-02-03 Airbus Operations (S.A.S) Aircraft with yaw control by differential drag
EP2774843A1 (fr) * 2013-03-05 2014-09-10 Bell Helicopter Textron Inc. Système et procédé pour réduire le bruit de pales de rotor
CN104176236A (zh) * 2013-05-22 2014-12-03 波音公司 波纹管合成射流

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102745329A (zh) * 2012-08-08 2012-10-24 南昌航空大学 涡流旋翼式飞行器

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2617487A (en) * 1948-09-30 1952-11-11 Edward A Stalker Wing for helicopters and other aircraft
US3102704A (en) * 1955-10-05 1963-09-03 Ii Roger W Griswold Airfoil jet reaction control means

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2617487A (en) * 1948-09-30 1952-11-11 Edward A Stalker Wing for helicopters and other aircraft
US3102704A (en) * 1955-10-05 1963-09-03 Ii Roger W Griswold Airfoil jet reaction control means

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3940092A (en) * 1974-11-07 1976-02-24 The Boeing Company Jet flow deflector for aircraft
US6554229B1 (en) * 1997-12-18 2003-04-29 Lawrence Y. Lam Aileron for fixed wing aircraft
RU2220072C1 (ru) * 2002-06-07 2003-12-27 Дябин Николай Васильевич Самолет с плоским хвостовым оперением
US20090206208A1 (en) * 2006-03-22 2009-08-20 The Boeing Company Reaction drive rotor/wing variable area nozzle
US7837141B2 (en) * 2006-03-22 2010-11-23 The Boeing Company Reaction drive rotor/wing variable area nozzle
US8651430B2 (en) * 2007-02-23 2014-02-18 Airbus Operations Gmbh Spoiler for an aerodynamic body of an aircraft
US20100320332A1 (en) * 2007-02-23 2010-12-23 Airbus Operations Gmbh Spoiler for an aerodynamic body of an aircraft
US20110024556A1 (en) * 2009-08-03 2011-02-03 Airbus Operations (S.A.S) Aircraft with yaw control by differential drag
US8876044B2 (en) * 2009-08-03 2014-11-04 Airbus Operations S.A.S. Aircraft with yaw control by differential drag
EP2774843A1 (fr) * 2013-03-05 2014-09-10 Bell Helicopter Textron Inc. Système et procédé pour réduire le bruit de pales de rotor
US9464532B2 (en) 2013-03-05 2016-10-11 Bell Helicopter Textron Inc. System and method for reducing rotor blade noise
CN104176236A (zh) * 2013-05-22 2014-12-03 波音公司 波纹管合成射流
CN104176236B (zh) * 2013-05-22 2018-07-31 波音公司 波纹管合成射流

Also Published As

Publication number Publication date
FR1496152A (fr) 1967-09-29
GB1174496A (en) 1969-12-17
DE1506591B1 (de) 1970-01-22

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