WO2008103735A2 - Avion, et composants de rattrapage pour ce dernier - Google Patents

Avion, et composants de rattrapage pour ce dernier Download PDF

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Publication number
WO2008103735A2
WO2008103735A2 PCT/US2008/054427 US2008054427W WO2008103735A2 WO 2008103735 A2 WO2008103735 A2 WO 2008103735A2 US 2008054427 W US2008054427 W US 2008054427W WO 2008103735 A2 WO2008103735 A2 WO 2008103735A2
Authority
WO
WIPO (PCT)
Prior art keywords
spar
wing
tension
torque box
former
Prior art date
Application number
PCT/US2008/054427
Other languages
English (en)
Other versions
WO2008103735A3 (fr
Inventor
Harry T. Snow, Jr.
Original Assignee
Snow Aviation International, Inc.
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 Snow Aviation International, Inc. filed Critical Snow Aviation International, Inc.
Publication of WO2008103735A2 publication Critical patent/WO2008103735A2/fr
Publication of WO2008103735A3 publication Critical patent/WO2008103735A3/fr

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/18—Spars; Ribs; Stringers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/26—Attaching the wing or tail units or stabilising surfaces
    • 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
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/10—Aircraft characterised by the type or position of power plants of gas-turbine type 
    • B64D27/12—Aircraft characterised by the type or position of power plants of gas-turbine type  within, or attached to, wings

Definitions

  • the present disclosure relates to modifications of propeller driven airplanes and particularly multi-engine aircraft having wing mounted engines, such as, for example high wing type aircraft employing turboprop propulsion systems for cargo carrying service and/or commercial passenger service.
  • Aircraft of this type are known to have a service life of several decades and have found widespread usage for their short field landing and takeoff capabilities in addition to their very large payload with respect to the maximum gross takeoff weight.
  • the aforesaid type of air craft typically have the wing mounted engines attached to the front face of the torque box by attachment to the front spar and extending in cantilever forward of the wing leading edge.
  • problems have been encountered with stress cracking in the spar webs and caps where the aircraft is operated at maximum gross weight for a substantial percentage of the flight time.
  • problems have also been encountered with stress cracking at the points where the engine mounts are attached to the wing torque box or spar.
  • the aluminum alloys employed for the spar webs, caps and wing skins such as 7075-T6 aluminum have experienced stress corrosion cracking resulting in shortened fatigue life of the wing structure.
  • the present disclosure presents modifications or retrofits to a multi-engine cargo or commercial airplane of the type having wing mounted engines and particular turbine-propeller powered aircraft.
  • the modifications may be performed to existing aircraft after an extended period in service and are intended to increase the fatigue resistance and increase the service life of the aircraft.
  • the front and rear spars may be formed of webs of increased thickness having bosses formed thereon by machining away material surrounding the boss thus leaving integrally formed bosses through which apertures may be formed for passage of fasteners or auxiliary items such as hydraulic tubing in a manner reducing the stress concentration about the aperture.
  • the spar caps are formed with increased radius fillets between the web and flanges of the spar cap; and, the upper and lower wing skins may be riveted to the spar caps and the caps to the webs with interference fit rivets.
  • vertical stiffeners having a T-shaped cross- section may be employed on the spar web for increased spanwise bending resistance of the spar.
  • solution heat treated aluminum for the spar webs and caps; and, in the present practice 7075- T7351 or 7075-6511 temper material has been found satisfactory.
  • other suitable materials may be employed that have greater resistance to stress corrosion cracking than 7075-T6 material.
  • the spar caps of generally T-shaped configuration have the vertical web portion thereof tapered smoothly, and generally linearly, in the spanwise direction to minimize stress concentrations in the areas surrounding the riveted attachment to the spar web.
  • the improved engine mount structure of the presently proposed modification for retrofit to the aircraft utilizes a pair of spaced trusses with diagonal bracing forming a first space frame attached to the front face of the torque box or front spar with extending forward therefrom and with a first engine nacelle former or bulkhead attached to the forward edge of the first space frame.
  • a second space frame of tubular tension compression members is attached to the front face of the first nacelle former and extends forward with a second nacelle former attached to the front or leading edge of the second space frame.
  • a tension compression strut is attached to the first nacelle former or the leading edge of the truss; and, the tension compression strut extends aftward and has the aft end thereof connected to the torque box at a location aft of the front spar, such as to the rear spar.
  • a downwardly extending strut may be provided from the front edge of the torque box or the front spar downwardly to the aftward extending tension-compression strut to provide lateral stability to the tension- compression strut.
  • the first and second engine nacelle formers have cutouts therein for receiving the engine.
  • the engine mount structure presented herein thus provides additional strengthening of the attachment to the torque box and reduces the loads and thus stress concentrations at any one of the attachment points.
  • a further modification of existing aircraft of the type having wing mounted turbine engines driving the propeller through a speed reducer, particularly the C-130 Aircraft, is the replacement of the four or six bladed propeller with eight bladed propellers for reducing the propeller rotational speed (rpm) and reducing interruption of power pulses from the blades which reduces the disturbance to the airflow over the wing surface and increases the lift. Additionally, the lower speed eight bladed propeller reduces the vibration on the airframe.
  • laterally extending fins are provided between the wing and the empennage extending outwardly from the fuselage and flaring in an aftwise direction to connect with the horizontal stabilizer for providing additional stability of the aircraft about its pitching axis.
  • An optional modification which may be employed is relocating the auxiliary fuel tanks from the wing pylons, to the wing tips; and, the wing pylons may then have additional turbine engines attached thereto if desired.
  • FIGURE 1 is a plan view of the aircraft presented herein showing the laterally extending fins or horsals on the fuselage flaring into the stabilizer;
  • FIGURE 2 is an isometric view of a portion of the wing torque box of the present modification
  • FIGURE 3 is an enlarged view of a portion of FIGURE 2;
  • FIGURE 4 is a section view taken along section indicating lines 4-4 of
  • FIGURE 3
  • FIGURE 5 is a pictorial view of the engine mount modification of the present disclosure
  • FIGURE 6 is a view showing a turbo fan engine mounted to the wing tank pylon;
  • FIGURE 7 is a section view taken along section indicating lines 7-7 of
  • FIGURE 3 The figure.
  • FIGURE 8 is a view of the eight bladed propeller modification.
  • a cargo plane having turbo prop engines mounted on each wing such as a C-130, is illustrated generally at 10 and has a pair of oppositely disposed laterally outwardly extending fins 12, 14 provided along the fuselage aft of the wings, the fins 12, 14 having flared portions 16, 18 respectively formed thereon which intersect the horizontal stabilizers 20, 22 which form part of the empennage indicated generally at 24.
  • the fuselage fins or horsals 12, 14 with the flared portion 16, 18 are added to the aircraft to increase the stability about the pitching axis of the aircraft.
  • the existing wing pylons on the wing previously utilized for mounting auxiliary fuel tanks, one of which is shown at 30 have optional turbo fan engines 32, 34 as shown in FIGURE 1.
  • the modified torque box for the wing structure is indicated generally at 40 and includes a spanwise extending front spar indicated generally at 42 and a spanwise extending rear spar indicated generally at 44 disposed in fore and aft spaced relationship with upper and lower wing skins 46, 48 attached thereto as will hereinafter be described.
  • the spars 42, 44 each have a web respectively 47, 49 which is formed with increased thickness; and, it has raised bosses such as boss 50 formed integrally thereon by machining away material from the web 47, 49 in the area surrounding the boss.
  • the bosses have apertures such as aperture 52 formed therein for accommodating fasteners and/or auxiliary fittings such as hydraulic tubes and control cables; and, the bosses serve to reduce stress concentrations around the apertures.
  • the spars 42, 44 have vertical stiffeners such as stiffener 54 provided thereon in spanwise spaced relationship which are attached to the webs 47, 49 by riveting and which stiffeners have a T-shaped configuration for providing additional stiffness to the spar webs 47, 49.
  • stiffener 54 provided thereon in spanwise spaced relationship which are attached to the webs 47, 49 by riveting and which stiffeners have a T-shaped configuration for providing additional stiffness to the spar webs 47, 49.
  • the torque box 40 contains spanwise spaced wing ribs for forming the airfoil shape of the upper and lower wing surfaces which ribs have been omitted from the drawing for simplicity of illustration.
  • Each of the spars 42, 44 has an upper and lower spar cap denoted respectively 56, 58 and 60, 62 having a generally T-shaped configuration in transverse section and attached thereto along the upper and lower edges of the webs 47, 49 by riveting.
  • the spar caps are formed integrally as a one piece member, such as, for example, by extrusion, and have increased-radius fillets between the flanges of the T- shape and the vertically extending central web portion.
  • the spar caps are subsequently machined as will be further described.
  • the riveting of the spar caps may employ rivets with an interference fit in the range of about .001 to ,003 inches (.025-,075mm).
  • the upper wing skin 46 is shown as attached to one of the flanges of the upper spar caps 56, 60 by two rows of rivets indicated generally at 62,
  • FIGURE 4 a further aspect of the attachment of the spar caps to the webs is illustrated for the attachment of rear spar cap 60 to the upper skin 46 is shown in enlarged detail wherein the rivets 64 are flush on the upper surface of the skin.
  • the spar cap 60 is attached to the rear spar web 49 by two rows of rivets indicated generally at 66 which may also be in interference fit as described above.
  • a downwardly extending integrally formed web portion 68 of the T-shape of the rear spar cap 60 is shown as smoothly tapering in the spanwise direction, such as by linear tapering, as opposed to step wise reduction in the vertical direction in the existing aircraft, particularly the C-130 aircraft.
  • the smooth tapering of the spar cap web 68 thus reduces stress concentration about the rivets 66 and increases the structural strength of the torque box 40.
  • the attachment of the spar cap 56 onto front spar web 47 is similar to that of the rear spar 44.
  • the modified engine mount of the present modification or retrofit kit is illustrated generally at 70 and is shown attached to the front face of the wing torque box or front spar 42 and extends forwardly therefrom in cantilever relationship.
  • the engine mount 70 includes a pair of trusses 72, 74 which are disposed in spanwise spaced relationship with a first engine nacelle former or bulkhead 76 disposed at the leading end or edge of the trusses 72, 74.
  • the trusses 72, 74 are diagonally braced by tension compression members 78, 80; and, the combination of trusses 72, 74 and the diagonal braces 78, 80 effectively form a first space frame.
  • the first engine nacelle former 76 extends downwardly below the spar 42 and has a pair of elongated tension compression members or struts attached thereto, with one such member 82 illustrated in FIGURE 5.
  • the forward or leading end of the tension compression member or strut 82 is denoted by reference numeral 84 and is attached to the first former 76.
  • the aft end of the strut 82 is attached to the wing torque box 40 at a position aft of the front spar 42; and, the strut 82 may be attached to the rear spar 44 at or near its lower edge.
  • a secondary strut 86 has one end attached to the lower edge of front spar 42 and extends downwardly to the strut 82 as denoted by reference numeral 86.
  • a second space frame indicated generally at 90 is attached to the forward face of the first former 76 and extends forward therefrom in cantilever arrangement to a second engine nacelle former 92 attached thereto.
  • the space frame 90 is comprised of a plurality of tension compression members, such as members 94, 96, 98, 100 on the outboard side of the engine nacelle, it being understood that corresponding set of tubular members are provided on the inboard of the nacelle. In the present practice it has been found satisfactory to form the tension-compression members of the space frame 90 from tubular metal.
  • the first and second engine nacelle formers 76, 92 each have cutouts or voids therein for receiving the aircraft engine therein.
  • the engine mount of FIGURE 5 thus provides additional rigidity to the mount and distributes the mounting loads over the front spar and the rear spar and reduces the stress concentrations at the mounting points thereon.
  • FIGURE 8 another modification is illustrated, wherein eight bladed propellers 102 have been installed to reduce the propeller rpm and reduce pressure pulses of air flowing over the wing surface particularly on a C-130 aircraft.
  • the propeller v blades may have a curved configuration and may be formed of non-metallic composite material with metal strips provided on the leading edge of the blade for protecting the composite material against impact with solid particles.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Details Of Gearings (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Composants de modification ou de rattrapage pour un avion doté de moteurs logés dans ses ailes. Un caisson de torsion d'aile de remplacement comporte des âmes de longeron épaissies usinées avec des bossages surélevés autour de trous dans l'âme pour réduire la concentration de tension. Les semelles de longeron ont l'âme verticale de leur forme en T doucement effilée dans le sens de l'envergure pour réduire la concentration de tension. Les semelles de longeron sont attachées aux âmes et aux revêtements d'aile avec des rivets de raccordement d'interférence. Un bâti-moteur présente une première structure spatiale attachée à l'avant du caisson de torsion d'aile, ou un longeron avant avec un premier cadre courant de fuseau-moteur disposé sur le bord d'attaque d'un premier espace vers l'avant et s'étendant vers le bas en dessous du longeron avant. Une seconde structure spatiale formée de tubes de compression de tension s'étend vers l'avant entre le premier cadre courant et un second cadre courant de fuseau-moteur. Un montant de compression de tension raccorde le premier cadre courant au longeron arrière pour étaler la charge sur le caisson de torsion. Un montant auxiliaire renforce le montant de compression de tension de façon latérale. L'avion peut être modifié pour ajouter des ailettes horizontales au fuselage, lesquelles s'évasent à l'arrière pour se raccorder aux stabilisateurs pour une stabilité de tangage accrue. Une autre modification à un avion turbopropulseur à moteurs multiples et à ailes élevées est l'ajout de propulseurs à huit pales.
PCT/US2008/054427 2007-02-22 2008-02-20 Avion, et composants de rattrapage pour ce dernier WO2008103735A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US90272607P 2007-02-22 2007-02-22
US60/902,726 2007-02-22

Publications (2)

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WO2008103735A2 true WO2008103735A2 (fr) 2008-08-28
WO2008103735A3 WO2008103735A3 (fr) 2008-11-06

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Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2951434A1 (fr) * 2009-10-20 2011-04-22 Airbus Operations Sas Empennage horizontal d'aeronef muni d'un apex de bord d'attaque
FR3054202A1 (fr) * 2016-07-25 2018-01-26 Safran Aircraft Engines Berceau pour turbopropulseur a manche d'entree d'air integree
CN108128474A (zh) * 2017-12-22 2018-06-08 北京安达维尔通用航空工程技术有限公司 一种降水粒子图像探头设备固定装置
EP3421352A1 (fr) * 2017-06-28 2019-01-02 Airbus Operations S.L. Surface de portance modulaire et méthode de fabrication
CN110498036A (zh) * 2019-08-07 2019-11-26 中国商用飞机有限责任公司北京民用飞机技术研究中心 一种尾翼壁板连接结构、尾翼和飞机
CN110510104A (zh) * 2019-08-02 2019-11-29 西安飞机工业（集团）有限责任公司 一种飞机机翼的梁结构
CN112357046A (zh) * 2020-11-02 2021-02-12 中国商用飞机有限责任公司 用于航空飞行器的龙骨梁结构及其构造方法和航空飞行器
US11542023B2 (en) 2018-01-15 2023-01-03 Lord Corporation Engine mount system and elements for reduced force transmission and reduced static motion and associated methods

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB356419A (en) * 1930-08-06 1931-09-10 Boulton & Paul Ltd Improvements in ribs and like members for aircraft
GB864540A (en) * 1957-12-12 1961-04-06 Napier & Son Ltd Turbine-propeller power units for aircraft
US4162777A (en) * 1978-05-02 1979-07-31 The United States Of America As Represented By The Secretary Of The Air Force Canted spar with intermediate intercostal stiffeners
US6123293A (en) * 1997-04-01 2000-09-26 Deutsches Zentrum Fur Luft-Und Raumfahrt E.V. Engine mount, particularly for a propeller-driven aircraft, comprising a tubular frame structure
US20040079839A1 (en) * 2002-10-21 2004-04-29 Bath David L. Method and apparatus for rotatably supporting movable components, including canards
US20060054866A1 (en) * 2004-04-13 2006-03-16 Zyvex Corporation. Methods for the synthesis of modular poly(phenyleneethynlenes) and fine tuning the electronic properties thereof for the functionalization of nanomaterials

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB356419A (en) * 1930-08-06 1931-09-10 Boulton & Paul Ltd Improvements in ribs and like members for aircraft
GB864540A (en) * 1957-12-12 1961-04-06 Napier & Son Ltd Turbine-propeller power units for aircraft
US4162777A (en) * 1978-05-02 1979-07-31 The United States Of America As Represented By The Secretary Of The Air Force Canted spar with intermediate intercostal stiffeners
US6123293A (en) * 1997-04-01 2000-09-26 Deutsches Zentrum Fur Luft-Und Raumfahrt E.V. Engine mount, particularly for a propeller-driven aircraft, comprising a tubular frame structure
US20040079839A1 (en) * 2002-10-21 2004-04-29 Bath David L. Method and apparatus for rotatably supporting movable components, including canards
US20060054866A1 (en) * 2004-04-13 2006-03-16 Zyvex Corporation. Methods for the synthesis of modular poly(phenyleneethynlenes) and fine tuning the electronic properties thereof for the functionalization of nanomaterials

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2951434A1 (fr) * 2009-10-20 2011-04-22 Airbus Operations Sas Empennage horizontal d'aeronef muni d'un apex de bord d'attaque
US10562638B2 (en) 2016-07-25 2020-02-18 Safran Aircfraft Engines Cradle for a turbopropeller engine with integrated air inlet duct
FR3054202A1 (fr) * 2016-07-25 2018-01-26 Safran Aircraft Engines Berceau pour turbopropulseur a manche d'entree d'air integree
WO2018020112A1 (fr) 2016-07-25 2018-02-01 Safran Aircraft Engines Berceau pour turbopropulseur a manche d'entrée d'air intégrée
EP3421352A1 (fr) * 2017-06-28 2019-01-02 Airbus Operations S.L. Surface de portance modulaire et méthode de fabrication
US10981642B2 (en) 2017-06-28 2021-04-20 Airbus Operations S.L. Modular lifting surface
CN108128474A (zh) * 2017-12-22 2018-06-08 北京安达维尔通用航空工程技术有限公司 一种降水粒子图像探头设备固定装置
US11542023B2 (en) 2018-01-15 2023-01-03 Lord Corporation Engine mount system and elements for reduced force transmission and reduced static motion and associated methods
US11787552B2 (en) 2018-01-15 2023-10-17 Lord Corporation Engine mount system and elements for reduced force transmission and reduced static motion
CN110510104A (zh) * 2019-08-02 2019-11-29 西安飞机工业（集团）有限责任公司 一种飞机机翼的梁结构
CN110498036A (zh) * 2019-08-07 2019-11-26 中国商用飞机有限责任公司北京民用飞机技术研究中心 一种尾翼壁板连接结构、尾翼和飞机
CN112357046A (zh) * 2020-11-02 2021-02-12 中国商用飞机有限责任公司 用于航空飞行器的龙骨梁结构及其构造方法和航空飞行器
CN112357046B (zh) * 2020-11-02 2022-06-17 中国商用飞机有限责任公司 用于航空飞行器的龙骨梁结构及其构造方法和航空飞行器

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