WO1999067130A1 - Plan fixe horizontal pour giravion - Google Patents

Plan fixe horizontal pour giravion Download PDF

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Publication number
WO1999067130A1
WO1999067130A1 PCT/US1998/013192 US9813192W WO9967130A1 WO 1999067130 A1 WO1999067130 A1 WO 1999067130A1 US 9813192 W US9813192 W US 9813192W WO 9967130 A1 WO9967130 A1 WO 9967130A1
Authority
WO
WIPO (PCT)
Prior art keywords
horizontal stabilizer
incidence
angle
stabilizer
spanwise
Prior art date
Application number
PCT/US1998/013192
Other languages
English (en)
Inventor
James Richard Lamb
Original Assignee
Sikorsky Aircraft Corporation
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 Sikorsky Aircraft Corporation filed Critical Sikorsky Aircraft Corporation
Priority to PCT/US1998/013192 priority Critical patent/WO1999067130A1/fr
Priority to AU79876/98A priority patent/AU7987698A/en
Publication of WO1999067130A1 publication Critical patent/WO1999067130A1/fr

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C5/00—Stabilising surfaces
    • B64C5/02—Tailplanes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
    • B64C2027/8263—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising in addition rudders, tails, fins, or the like
    • B64C2027/8281—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising in addition rudders, tails, fins, or the like comprising horizontal tail planes

Definitions

  • This invention is directed to lift/moment-producing airfoil structures for rotorcraft, and, more particularly, to an improved horizontal stabilizer therefor having asymmetric lift characteristics for balancing the bending moments about its mounting interface, thereby reducing the structural weight requirements thereof.
  • a rotorcraft typically includes various lifting/moment-producing airfoil structures/surfaces for stabilizing the rotorcraft in various flight regimes.
  • One such airfoil structure, to which the present invention is directed, is the horizontal stabilizer which is typically mounted to a rearward portion of the tail boom assembly.
  • the principle function of the horizontal stabilizer is to produce a downwardly-directed force vector, i.e., negative lift, when the rotorcraft is in a forward flight operating mode so as to produce a pitching moment which counteracts or balances the pitching moment produced by the main rotor system. That is, the horizontal stabilizer counteracts the nose-down pitching moment produced by the main rotor system in forward flight so as to "level out" the fuselage and, consequently, reduce profile drag.
  • the horizontal stabilizer may be fixed or pivotable with respect to the tail boom assembly.
  • a fixed horizontal stabilizer which is optimally oriented and configured for a single, most frequently occupied, operating regime. Examples of fixed horizontal stabilizers are described and depicted in U.S. Patents 5,102,067 and Des. 361,053.
  • a pivotable horizontal stabilizer for the purpose of minimizing impingement of the rotor downwash on the horizontal stabilizer. For example, by controllably pivoting the stabilizer, it may assume a position parallel to the freestream downwash to minimize profile area, and consequently, profile drag.
  • a prior art horizontal stabilizer typically defines a rectangular planform and a substantially constant angle of incidence along its length, i.e., the angle of incidence from one cross-section to another is equal. Furthermore, in cross-section, such horizontal stabilizers commonly comprise conventional symmetric or cambered airfoil shapes which may include a constant or tapering thickness dimension. To avoid the introduction of large bending moments at the structural interface of the horizontal stabilizer, it is generally desirable to attach the horizontal stabilizer in substantially symmetrical relation to is adjoining structure, e.g., a vertical fin. That is, it is desirable to mount the horizontal stabilizer about its center of mass to balance the bending moments acting on the structural interface.
  • a horizontal stabilizer defining first and second spanwise stations wherein the first spanwise station defines a first angle of incidence and the second spanwise station defines a second angle of incidence and wherein the angles of incidence from one station to the other are different, e.g., one is greater than the other.
  • Various embodiments of the horizontal stabilizer include the use of vertically extending tabs along the trailing edge of the horizontal stabilizer, a stepped-transition to abruptly change the angle of incidence from one station to another, and a distributed twist which gradually changes the angle of incidence.
  • Fig. la depicts a side view of a rotorcraft employing a horizontal stabilizer according to the present invention
  • Fig. lb depicts a top view of the rotorcraft illustrated in Fig. la;
  • Fig. lc depicts a rear view of the rotorcraft illustrated in Fig. la
  • Fig. 2 depicts an isolated perspective view of the horizontal stabilizer according to the present invention including upwardly and downwardly extending tabs along the trailing edge of the horizontal stabilizer;
  • Fig. 2a is a cross-sectional view taken substantially along line 2a - 2a of Fig. 2;
  • Fig. 2b is a cross-sectional view taken substantially along line 2b - 2b of Fig. 2;
  • Fig. 3 depicts an isolated perspective view of an alternate embodiment of the inventive horizontal stabilizer including a stepped transition along a midplane thereof;
  • Fig. 3a is a cross-sectional view taken substantially along line 3a - 3a of Fig. 3;
  • Fig. 3b is a cross-sectional view taken substantially along line 3b - 3b of Fig. 3;
  • Fig. 4 depicts an isolated perspective view of an alternate embodiment of the inventive horizontal stabilizer which defines multiple angles of incidence, i.e., a distributed twist, along the span of the horizontal stabilizer;
  • Fig. 4a is a cross-sectional view taken substantially along line 4a - 4a of Fig. 4;
  • Fig. 4b is a cross-sectional view taken substantially along line 4b - 4b of Fig. 4;
  • Fig. 4c is a cross-sectional view taken substantially along line 4c - 4c of Fig. 4;
  • Fig. 4d is a cross-sectional view taken substantially along line 4d - 4d of Fig. 4;
  • Fig. 5 is a graph comparing the bending moment loads/stresses produced by a prior art horizontal stabilizer and the horizontal stabilizer according to the present invention.
  • Figs, la - lb show a rotorcraft 10 having a main rotor 12, a tail boom assembly 14 employing a FANTAILTM anti -torque system 16, a vertical fin 18, and a horizontal stabilizer 20 according to the present invention.
  • the horizontal stabilizer 20 is fixedly mounted to the upper end of the vertical fin 18 and defines a "mean angle of attack" of about seven (7) degrees relative to the horizontal.
  • the horizontal stabilizer 20 defines at least two (2) angles of incidence at two spanwise stations, and. in at least one embodiment of the invention, defines multiple angles of incidence to form a distributed twist along is span.
  • the downwash 26 skews to the right as illustrated in Fig. lb. Furthermore, due to the normal coning of the main rotor 12. the downwash 26 produces strong vortices which impinge on the stabilizer in an asymmetric manner. More specifically, and referring to Fig. lc, the vortex pattern 28 illustrates that the high energy vortices 30 are distally spaced relative to the left side 20 of the stabilizer 20 and are in close proximity to the stabilizer 20 on its right side 20R.
  • the various aerodynamic effects on the stabilizer 20 can be summarized as follows.
  • a region A thereof operates at a different angle of attack than in a region B, which is operating in substantially less-affected or "clean" airflow.
  • the affected airflow in region A tends to increase the angle of attack of the stabilizer producing an excess force V] on the right side 20R relative to the left side 20 L -
  • the clean airflow in region B causes this portion of the stabilizer 20 to function as intended and produces a relatively small downwardly directed force vector V 2 (Fig. lc) when the aircraft is in level unaccelerated flight. Accordingly, it will be appreciated that an imbalance is produced resulting in a bending moment Mi about the structural interfaces 22, 24.
  • the stabilizer 20 has a substantially rectangular planform and comprises a one piece construction, i.e., incorporates a common spar (not shown) along it length or span.
  • the stabilizer 20 comprises a conventional airfoil shape, i.e., symmetric or cambered about its chord, though the angle of incidence from one spanwise station to another varies. While the term “angle of attack” could also be used, this is a term which is relative to the free- stream airflow and not to the horizontal stabilizer 20 in isolation.
  • the inventor uses the term “angle of incidence” for defining the characteristics of various spanwise stations of the same stabilizer 20.
  • the "angle of incidence” is defined as the angle defined by geometric chord of the airfoil section and the horizontal.
  • the horizontal stabilizer 20 defines at least two spanwise stations wherein the angle of incidence is different, i.e., one is greater than the other.
  • Figs. 2, 2a, and 2b a first embodiment of the horizontal stabilizer 20 is shown wherein the left side 20 L of the stabilizer 20 comprises an upwardly extending flap or tab 36 along its trailing edge 20 J E while the right side 20 R comprises a downwardly extending flap or tab 38. Consequently, the angle of incidence ⁇ i (Figs. 2a and 2b) on the left side 20 is different, e.g., less than, the angle of incidence ⁇ 2 on the right side 20 R .
  • this feature changes the effective camber of the airfoil to compensate for differences in local angle of attack whereby the magnitude of the downwardly directed force vectors Vi and V 2 are decreased and increased, respectively. Consequently, in the previously described flow environment illustrated in Figs, lb and lc, bending moment loads/stresses are mitigated or balanced so as to reduce the bending moment stresses at the structural interfaces.
  • FIGs. 3, 3a, and 3b Yet another embodiment of the horizontal stabilizer 20 is depicted Figs. 3, 3a, and 3b, wherein the stabilizer 20 comprises a stepped-transition at a predefined spanwise station.
  • the stepped-transition occurs at the midplane MP of the horizontal stabilizer 20.
  • the left side 20 of the stabilizer defines a nose down angle of incidence ⁇ 3 (Fig. 3 a) relative to the angle of incidence ⁇ 4 on the right side 20 R (Fig. 3b).
  • the functional effects of the stepped-transition are the same as those previously described for the upwardly and downwardly extending tabs 36, 38.
  • the same functional effect may be produced by a uniform or non-uniform twist distribution at a multiplicity of spanwise stations of the stabilizer 20. More specifically, and referring to Figs. 4a - 4d, the horizontal stabilizer 20 defines a multiplicity of incidence angles ⁇ 5 - ⁇ 8 so as to define a substantially nose down angle of incidence ⁇ 5 on the left side 20 of the stabilizer 20 (Fig. 4a), relative to the angle of incidence ⁇ 8 on the right side 20 R (Fig. 4d). In the described embodiment, the stabilizer 20 defines a substantially uniform twist which effects a gradual change in angle of incidence when viewing the cross-sections in sequence, e.g., from Fig. 4a through Fig. 4d.
  • Fig. 5 is a graph which shows the balancing or normalizing effects of the embodiment depicted in Fig. 2.
  • the airspeed of the rotorcraft is plotted along the abscissa in KNOTS, and the bending moment (along the structural interface between the stabilizer and the vertical fin) is plotted along the ordinate axis in LBS/LN.
  • the triangular data points 50 are indicative of a prior art stabilizer having a constant angle of incidence along its span while the square data points 60 are indicative of the horizontal stabilizer 20 according to the present invention.
  • the present invention varies the angle of incidence, and, consequently, the effective angle of attack, to reduce or cancel the bending moment loads/stresses acting on the structural interfaces 22, 24 and, additionally, on the entire tail boom assembly 14. Accordingly, the invention provides a structurally efficient solution for reducing the overall weight of the rotorcraft.
  • the horizontal stabilizer may comprise multiple sections.
  • the inventive horizontal stabilizer is shown mounted atop a vertical fin of the tail boom assembly, it will be appreciated that the stabilizer may be mounted to any portion thereof.
  • teachings of the invention are equally applicable to fixed, moveable or cantilevered stabilizer configurations. For example, it may be desirable to produce axisymmetric lift characteristics on a fixed cantilevered stabilizer such as that shown in U.S. Patent Des. 361,053.
  • controllably blowing air over the surface of the stabilizer may be used at various spanwise stations to alter the stagnation points on the airfoil thereby varying its lift characteristics.
  • vertically extending tabs are employed on both sides of the horizontal stabilizer to varying its lift characteristics, it will be appreciated that a single tab disposed on one side of the stabilizer may be used.
  • the tabs are shown to be substantially vertically aligned and of constant height, it should be understood that the tabs may incorporate a horizontal component, i.e., not entirely vertical, and may vary in height along the span of the stabilizer. While in another embodiment, a single stepped-transition occurs at a midplane of the horizontal stabilizer, it will be appreciated that the invention may employ multiple steps disposed at any spanwise station. While in yet another embodiment described, a uniform distributed twist is employed, the invention contemplates a non-uniform twist distribution, i.e., wherein the change of angle of incidence varies from, for example, rapid to shallow, along the span. Moreover, while the invention has been described in the context of a rotorcraft having a rotor system driven in a counter-clockwise direction, it will be appreciated that the teachings are equally applicable to a rotor system having a clockwise rotation.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)

Abstract

L'invention concerne un plan fixe horizontal (20) définissant des première et seconde stations d'envergure dont la première définit un premier angle d'incidence (ζ1 ou ζ3 ou ζ5) et dont la seconde définit un second angle (ζ2 ou ζ4 ou ζ8) d'incidence. L'angle d'incidence est différent d'une station à une autre, p. ex., l'un est plus grand que l'autre. Le plan fixe horizontal (20) sert à améliorer la répartition de la portance en envergure afin de réduire les moments de flexion autour de son interface de montage. Selon différentes variantes, le plan fixe horizontal (20) permet l'utilisation de volets compensateurs (36, 38) à prolongement vertical le long du bord de fuite (20TE) du plan fixe horizontal, d'une transition par paliers afin de modifier brusquement l'angle d'incidence d'une station à l'autre et d'un gauchissement réparti qui modifie progressivement l'angle d'incidence.
PCT/US1998/013192 1998-06-25 1998-06-25 Plan fixe horizontal pour giravion WO1999067130A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
PCT/US1998/013192 WO1999067130A1 (fr) 1998-06-25 1998-06-25 Plan fixe horizontal pour giravion
AU79876/98A AU7987698A (en) 1998-06-25 1998-06-25 Horizontal stabilizer for rotorcraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US1998/013192 WO1999067130A1 (fr) 1998-06-25 1998-06-25 Plan fixe horizontal pour giravion

Publications (1)

Publication Number Publication Date
WO1999067130A1 true WO1999067130A1 (fr) 1999-12-29

Family

ID=22267367

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US1998/013192 WO1999067130A1 (fr) 1998-06-25 1998-06-25 Plan fixe horizontal pour giravion

Country Status (2)

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AU (1) AU7987698A (fr)
WO (1) WO1999067130A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108100231A (zh) * 2017-12-01 2018-06-01 中国直升机设计研究所 一种直升机平尾接头
CN108839814A (zh) * 2018-06-13 2018-11-20 江西昌河航空工业有限公司 一种用于拆换直升机尾梁接头的装置
EP3730403A1 (fr) 2019-04-26 2020-10-28 AIRBUS HELICOPTERS DEUTSCHLAND GmbH Giravion comportant une aile stabilisatrice
RU2743306C1 (ru) * 2020-10-19 2021-02-16 Эйрбас Хеликоптерс Дойчланд Гмбх Винтокрылый летательный аппарат с крылом-стабилизатором

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2167249A1 (fr) * 1972-01-11 1973-08-24 Aerospatiale
US4103848A (en) 1977-03-08 1978-08-01 United Technologies Corporation Variable incidence helicopter stabilator and fail safe actuator
US4247061A (en) 1978-07-12 1981-01-27 United Technologies Corporation Helicopter with stabilator detuned in antisymmetric vibration modes from main rotor wake excitation frequency
US4809931A (en) * 1986-06-16 1989-03-07 Aerospatiale, Societe Nationale Industrielle Directional and stabilizing device having a faired and slanted antitorque rotor and a disymmetric "V" empennage, and a helicopter equipped with such a device
US5102067A (en) 1991-04-11 1992-04-07 United Technologies Corporation Integrated helicopter empennage structure

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2167249A1 (fr) * 1972-01-11 1973-08-24 Aerospatiale
US4103848A (en) 1977-03-08 1978-08-01 United Technologies Corporation Variable incidence helicopter stabilator and fail safe actuator
US4247061A (en) 1978-07-12 1981-01-27 United Technologies Corporation Helicopter with stabilator detuned in antisymmetric vibration modes from main rotor wake excitation frequency
US4809931A (en) * 1986-06-16 1989-03-07 Aerospatiale, Societe Nationale Industrielle Directional and stabilizing device having a faired and slanted antitorque rotor and a disymmetric "V" empennage, and a helicopter equipped with such a device
US5102067A (en) 1991-04-11 1992-04-07 United Technologies Corporation Integrated helicopter empennage structure

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108100231A (zh) * 2017-12-01 2018-06-01 中国直升机设计研究所 一种直升机平尾接头
CN108839814A (zh) * 2018-06-13 2018-11-20 江西昌河航空工业有限公司 一种用于拆换直升机尾梁接头的装置
CN108839814B (zh) * 2018-06-13 2021-07-02 江西昌河航空工业有限公司 一种用于拆换直升机尾梁接头的装置
EP3730403A1 (fr) 2019-04-26 2020-10-28 AIRBUS HELICOPTERS DEUTSCHLAND GmbH Giravion comportant une aile stabilisatrice
US11485487B2 (en) 2019-04-26 2022-11-01 Airbus Helicopters Deutschland GmbH Rotorcraft with a stabilizer wing
US11702199B2 (en) 2019-04-26 2023-07-18 Airbus Helicopters Deutschland GmbH Rotorcraft with a stabilizer wing
RU2743306C1 (ru) * 2020-10-19 2021-02-16 Эйрбас Хеликоптерс Дойчланд Гмбх Винтокрылый летательный аппарат с крылом-стабилизатором

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Publication number Publication date
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