WO2013137915A1 - Avion à aile médiane - Google Patents

Avion à aile médiane Download PDF

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Publication number
WO2013137915A1
WO2013137915A1 PCT/US2012/029549 US2012029549W WO2013137915A1 WO 2013137915 A1 WO2013137915 A1 WO 2013137915A1 US 2012029549 W US2012029549 W US 2012029549W WO 2013137915 A1 WO2013137915 A1 WO 2013137915A1
Authority
WO
WIPO (PCT)
Prior art keywords
fuselage
wing
deck
carry
airplane
Prior art date
Application number
PCT/US2012/029549
Other languages
English (en)
Inventor
Sergey Barmichev
Mithra M. Sankrithi
Original Assignee
The Boeing Company
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 The Boeing Company filed Critical The Boeing Company
Priority to PCT/US2012/029549 priority Critical patent/WO2013137915A1/fr
Publication of WO2013137915A1 publication Critical patent/WO2013137915A1/fr

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Classifications

    • 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
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C2001/0018—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like comprising two decks adapted for carrying passengers only
    • B64C2001/0027—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like comprising two decks adapted for carrying passengers only arranged one above the other
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/02—Undercarriages
    • B64C25/08—Undercarriages non-fixed, e.g. jettisonable
    • B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
    • B64C25/12—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like sideways
    • B64C2025/125—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like sideways into the fuselage, e.g. main landing gear pivotally retracting into or extending out of the fuselage

Definitions

  • This disclosure generally relates to aircraft, and deals more particularly with an airplane having a tube type fuselage and a mid-level wing that passes though a deck in the fuselage.
  • super-high bypass ratio jet engines such as geared turbo fan or open rotor jet engines may be used.
  • These engines typically employ larger diameter engine fans, rotors and/or nacelles which, because of their size, may place design constraints on other components of the airplane.
  • larger diameter engines mounted beneath the primary lifting wing on the airplane may require excessive inboard wing shear and associated large weight penalties on a low-wing airplane configuration, or alternatively may require that the wing be positioned at a higher level on the fuselage in order to provide sufficient ground clearance beneath the engines. This higher placement of the wing on the fuselage may in turn place constraints on the configuration of payload carrying decks within the fuselage.
  • the disclosed embodiments provide an airplane configuration well suited for tube-wing type, relatively large subsonic commercial or military applications where relatively high payload capacity is required along with the use of higher efficiency engines and a minimum of airplane wetted area.
  • These objectives are achieved in part, by optimal positioning of the wing on the fuselage to accommodate relatively large diameter engines beneath the wing, without increasing the height of the fuselage above the ground, and without the need for excessive inboard wing shear or wing dihedral.
  • These features are particularly well suited to use of composite materials to fabricate the wing since the tension-compression load paths on the wing panels are substantially straight.
  • the wing includes carry-through structure passing through a payload carrying deck.
  • the carry-through structure includes one or more full-height passageways allowing free flow of passengers or crew between fore and aft sections of the deck, as well as carry-through structural elements above and below the passageways.
  • the wing carry-through structure may be utilized for passenger or crew support facilities such as galleys, rest areas or lavatories, as well as fuel storage volume(s) appropriately separated from passenger and crew use volume(s).
  • an airplane comprises a fuselage including at least a first longitudinal extending payload carrying deck.
  • a wing is mounted on the fuselage at the level of the first deck and includes first and second wing panels respectively on opposite sides of the fuselage.
  • the wing further includes a carry-through structure within the fuselage that connects the wing panels.
  • the carry-through structure passes transversely through the fuselage and includes at least one full passenger height passageway allowing passage along the first deck through the carry-through structure.
  • At least one engine is mounted beneath each of the wing panels.
  • the airplane may further comprise main landing gear mounted on and retractable substantially entirely within the fuselage beneath the first deck.
  • the carry-through structure may include upper and lower structural panels extending continuously across the fuselage, and spars connected to the upper and lower structural panels and extending across the fuselage.
  • the carry-through structure may include a service area comprising at least one of a of a galley, a galley cart stowage facility, a lavatory, a crew rest facility, a passenger rest facility, a medical facility, a lounge, a bar, a play area, and a storage facility.
  • an airplane comprises a generally tubular fuselage and a wing mounted on the fuselage.
  • the tubular fuselage includes at least a first longitudinal extending payload carrying deck, and a second longitudinally extending payload carrying deck stacked above the first deck.
  • the wing passes transversely through the first deck and divides the first deck into a fore section and an aft section.
  • the wing includes carry-through structure extending continuously across the fuselage and having a longitudinal passageway therein allowing walk-through between a fore and aft sections of the deck.
  • the cross section of the fuselage may comprise a double bubble configuration.
  • a mid-wing, multi-deck airplane comprises a generally tubular fuselage and a mid-level wing having first and second wing panels. At least one engine is mounted on each of the wing panels beneath the wing. Main landing gear is mounted on and retractable substantially entirely within the fuselage.
  • the tubular fuselage includes at least one longitudinally extending mid-level payload deck and a longitudinally extending upper payload deck above the mid-level deck.
  • the wing passes through the mid-level deck and includes a carry-through structure connecting the wing panels.
  • the carry-through structure divides the mid-level deck into fore and aft sections and includes at least one longitudinally extending passageway therein forming a walkthrough aisle between the fore and aft sections of the mid-level deck.
  • the airplane further comprises first and second fuel tanks respectively within the first and second wing panels wherein each of the fuel tanks includes an inboard portion extending into the carry-through structure.
  • an airplane comprising: a generally tubular fuselage including at least a first longitudinally extending payload carrying deck and a second longitudinally extending payload carrying deck stacked above the first deck; and a wing mounted on the fuselage, the wing passing transversely through the first deck and dividing the first deck into fore and aft sections, the wing including carry-through structure extending continuously transversely through the fuselage, the carry-through structure including an upper structural panel, a lower structural panel and a longitudinal passageway between the upper and lower structural panels allowing walk-through between the fore and aft sections of the first deck; wherein the first deck and the passageway may be pressurized: wherein: the fore and aft sections of the first deck each include passenger seating and at least one aisle, and the passageway forms a substantially full passenger height corridor in the wing carry-through structure connecting the aisles in the fore and aft sections of the first deck; wherein a cross section of the fuselage is a
  • a mid-wing, multi-deck airplane comprising: a generally tubular fuselage including at least a lower cargo deck, a longitudinally extending mid-level passenger deck above the cargo deck, and a longitudinally extending upper passenger deck above the mid-level deck; a mid-level wing attached to the fuselage and passing through the mid-level deck, the wing including first and second wing panels respectively on opposite sides of the fuselage and a carry-though structure connecting the wing panels, the carry- through structure extending transversely through the fuselage and dividing the mid-level deck into fore and aft sections, the carry-through structure including at least one longitudinally extending passageway forming a substantially full height walk-though aisle allowing a person to walk between the fore and aft sections; a least one engine mounted on each of the wing panels beneath the wing; and main landing gear mounted on the fuselage and having a majority portion thereof retractable entirely within the fuselage beneath the mid-level passenger deck; wherein: the passenger
  • first and second fuel tanks respectively within the first and second wing panels, each of the fuel tanks including an inboard portion extending into the carry-through structure; wherein each of the engines is a large diameter high efficiency engine; wherein the carry-through structure includes: upper and lower structural panels vertically spaced from each other and extending transversely across the fuselage, a plurality of transversely extending spars connecting the upper and lower panels, and longitudinally extending ribs connecting the spars; and wherein each of the spars include portions extending respectively above and below the upper and lower panels.
  • FIG. 1 is a perspective illustration of an airplane having a mid-wing according to the disclosed embodiments.
  • FIG. 2 is a side view illustration of an airplane similar to FIG. 1 and illustrating the location of multiple decks relative to the mid-wing.
  • FIG. 3 is a sectional illustration taken along the line 3-3 in FIG. 2.
  • FIG. 4 is an illustration of a plan view of the airplane shown in FIGS. 1 and 2.
  • FIG. 5 is an illustration of a front view of the airplane shown in FIGS. 1 and 2.
  • FIG. 6 is an illustration of a plan view of an upper deck of the airplane shown in FIGS. 1 and 2.
  • FIG. 7 is an illustration of a plan view of a mid-level deck of the airplane shown in FIGS. 1 and 2.
  • FIG. 8 is a diagrammatic cross sectional illustration of a double bubble fuselage.
  • FIG. 9 is an illustration similar to FIG. 8 but showing an alternate form of the double bubble fuselage construction.
  • FIG. 10 is an enlarged illustration of the area designated as "A" in FIG. 9.
  • FIG. 11 is an illustration similar to FIGS. 8 and 9 but showing a fuselage construction having a generally oval cross section.
  • FIG. 12 is a perspective illustration of a medium passenger capacity (below 300 passengers in triple class) mid-wing passenger airplane.
  • FIG. 13 is an illustration of a plan view of an upper deck of the airplane shown in FIG.
  • FIG. 14 is an illustration of a plan view of a mid-level deck of the airplane shown in FIG. 12
  • FIG. 15 is an illustration of a plan view of a lower hold of the airplane shown in FIG. 12.
  • FIG. 16 is a sectional illustration taken along the line 16-16 in FIG. 12.
  • FIG. 17 is an illustration of a plan view of a wing wherein the carry-through structure and wing panels form an integrated, single module.
  • FIG. 18 is an illustration similar to FIG. 17 but depicting the carry-through structure as a separate wing central section module connected to the wing panels.
  • FIG. 19 is an illustration similar to FIG. 17 but showing the carry-through structure integrated into the roots of the center-splice wing panels.
  • FIG. 20 is a perspective illustration of one half of the carry-through structure having a single passageway therein.
  • FIG. 21 is an illustration similar to FIG. 20 but depicting two passageways in one half of the carry-through structure.
  • FIG. 22 is an illustration similar to FIG. 20 but showing the passageway being located along the centerline of the airplane.
  • FIG. 23 is a perspective illustration showing further details of the carry-through structure.
  • FIG. 24 is a perspective illustration showing lavatory and rest area facilities located in the carry-through structure.
  • FIG. 25 is an illustration of a top view of the lavatories shown in FIG. 24.
  • FIG. 26 is a perspective illustration of a wing tank that includes portions extending into the carry-through structure.
  • FIG. 27 is a perspective illustration of the main landing gear of the airplane shown in FIGS. 1 and 2.
  • FIG. 28 is an end view showing further details of the landing gear depicted in FIG. 27, the retracted position of the landing gear being shown in dashed lines.
  • FIG. 29 is an illustration similar to FIG. 28, but showing a main landing gear suitable for use with a mid- wing airplane similar to that shown in FIGS. 12-16.
  • FIG. 30 is an illustration of a front view of another mid- wing airplane having engines with open rotor blades.
  • FIG. 31 is a side view illustration of the airplane shown in FIG. 30.
  • an airplane 30 includes a tubular type fuselage 32, a mid- wing 34 and an empennage 36 comprising a vertical stabilizer 38 and horizontal stabilizers 40.
  • the airplane 30 further includes a retractable nose gear 52 and main landing gear 50 which are retractable into a wheel well 54 (FIG. 2) within the fuselage 32 for housing the main landing gear.
  • the wing 34 comprises a left (port) wing panel 42 and a right (starboard) wing panel 44 connected by carry-through structure 46 which passes through and is connected to the fuselage 32.
  • the wing panels 42, 44 include wing spars 119, at least some of which either extend through the carry-through structure 46 or are connected to spars 118 forming part of the carry-through structure 46.
  • the fuselage 32 includes fore and aft pressure bulkheads 66, 68 respectively which permit pressurization of a first, mid-level cabin deck 56 and a second, upper level cabin deck 58 which is stacked above the mid-level cabin deck 56.
  • fore and aft stairways 78 connect the mid-level and upper level decks 56, 58 respectively.
  • cabin decks 56 and 58 are fitted with seats 74 for carrying passengers however, decks 56, 58 may carry any of a variety of payloads such as cargo, military equipment, etc.
  • a third, lower deck (or cargo deck) 60 beneath the mid-level deck 56 includes a cargo area 65 which is divided into fore and aft cargo sections 62, 64 by a wheel well 54 used to store the main landing gear 50.
  • the cargo area 65 may be capable of accommodating at least one or more of a bulk cargo, or a unit load device (not shown) comprising one or more of an LD-3 container, an LD-1 container, an LD-2 container, an LD-3- 46 container and an LD-3 -45 container.
  • mid-wing refers to the mid-level placement of the wing with full-size passengers/crew access passages 34 on the fuselage 32, in contrast to a "high" wing configuration or a “low” wing configuration.
  • the wing 34 is connected to the fuselage 32 at the level of the mid-level deck 56, and the carry-through structure 46 passes transversely through the mid-level deck 56.
  • carry-through structure 46 refers to structural elements, members, or components that connect the wing panels 42, 44 within the fuselage 32. As best seen in FIGS. 2 and 7, the carry-through structure 46 divides the mid-level deck 56 into a fore section 84 and an aft section 86.
  • mounting of the wing 34 at a mid-level on the fuselage 32 i.e. at the mid-level deck 56 provides adequate clearance 78 between the ground 76 and relatively large diameter, high efficiency engines 48, which may be for example, and without limitation, geared turbo fan or open rotor jet engines.
  • Mid-level wing placement also has the benefit of lower values of interference drag with the fuselage 32 and a reduced need for fairings between the wing 34 and fuselage 32. Fairings may not be required or reduced in size for the mid-level wing of the disclosed embodiments, thus resulting in reduced weight and drag due to the additional wetted surface of the fairing.
  • the fuselage 32 may be of a so-called double bubble configuration comprising an upper generally circular lobe 70 and a lower generally circular lobe 72 which are joined together at an intersection area 100, forming a double lobe. Placement of the wing 34 at a mid-level position on the fuselage 32 results in the lower lobe 72 being substantially free of obstructions except for stowed landing gear from front to rear, thereby increasing the volume of space available for revenue cargo.
  • intersection area 100 between the upper and lower lobes 70, 72 respectively is generally V-shaped.
  • a fairing 102 may cover the intersection area 100, thereby forming a longitudinally extending, conduit-like recess 104.
  • Utilities 106 such as communication lines 106 may be mounted within the recess 104.
  • Each of the lobes 70, 72 may comprise a metal or composite frame 96 covered by an outer skin 98 which may also be of either metal or composite materials.
  • the upper deck 58 is contained within the upper lobe 70, while the mid-level deck 56 and lower level decks 60 are contained within the lower lobe 72.
  • a first cabin floor 92 supporting the upper deck 58 extends across the diameter of the upper fuselage section 70, while a second cabin floor 94 supported by stanchions 95 extends across the lower fuselage section 72 to support the mid-level deck 56.
  • the outer skin 98 may be formed continuously over the intersection area 100 in order to form a smooth, aerodynamic transition including a concave segment over area 100 between two convex segments over the upper and lower lobes 70, 72.
  • the frame 96 may include a truss-like portion 104 which supports and back the skin 98 and provides a means for mounting the communication lines 106.
  • the disclosed mid-wing configuration and carry-through structure 46 may be used in connection with an airplane having a fuselage 32 of the type shown in FIG. 11 which is generally oval in cross section.
  • the depth of the frame 98 is generally increases monotonically with increases to the radius of curvature of the fuselage 32.
  • FIGS. 12-16 illustrate a triple class airplane 30a capable of carrying approximately 295 passengers and cargo.
  • Seating 74 is placed on mid-level and upper decks 56, 58 respectively, in a 9+6 configuration.
  • the carry- through section 46 of the wing 34 includes a full height passage center aisle (or corridor) 82a with crew/passenger rest facilities 90 on each side of the aisle 82a.
  • the lower deck 60 may include a hold having an attendant rest area 90a connected to the mid- level deck 56 by stairs 78. As shown in FIG. 16, the lower level deck 60 may also include one or more cargo areas 65 capable for stowing, for example LD-1 and LD-3 container (not shown). Wing spars 119 can be seen to be connected to spars 118 forming part of the carry-through structure 46. Spars 118 include upper and lower spar extensions 118a, 118b the purpose of which will be discussed later in more detail.
  • FIG. 17-19 illustrate various alternate embodiments of the wing 34.
  • Each of the wing panels 42, 44 includes a leading edge 115, a trailing edge 117 and a wing box 108 which includes spars 119.
  • the wing box 108 extends through the fuselage 32 (not shown in FIG. 17) so that the carry-through structure 46 is integrally formed with the wing panels 42, 44 and the wing 44 is essentially a single module or piece, tip-to-tip.
  • FIG. 17-19 illustrate various alternate embodiments of the wing 34.
  • FIG. 17-19 illustrate various alternate embodiments of the wing 34.
  • Each of the wing panels 42, 44 includes a leading edge 115, a trailing edge 117 and a wing box 108 which includes spars 119.
  • the wing box 108 extends through the fuselage 32 (not shown in FIG. 17) so that the carry-through structure 46 is integrally formed with the wing panels 42, 44 and the wing 44 is essentially a single module or piece, tip
  • wing panels 42, 44 are joined to the side of the fuselage 32 and the carry-through structure 46, which forms a central wing section, may be respectively formed as individual modules or sections that are joined together during the production process to form the wing 34.
  • the carry-through structure 46 includes spars 118 that are connected with wing spars 119 during the production process.
  • FIG. 19 depicts a center- line spliced type wing, in which one half of the carry-through structure 46 is integrated into the root of each wing panel 42, 44 so that the wing 34 is formed of two modules or sections that are joined together during the production process.
  • various passenger and crew support facilities and functions e.g., a galley, a galley cart stowage facility, a lavatory, a crew rest facility, a passenger rest facility, a medical facility, a lounge, a bar, a play area, and a storage facility
  • a galley, a galley cart stowage facility e.g., a lavatory, a crew rest facility, a passenger rest facility, a medical facility, a lounge, a bar, a play area, and a storage facility
  • the carry-through structure 46 is well suited for placement of crew and passenger support functions such as lavatories, galleys, galley cart storage and closets, since these areas may not require the full height clearance required for a passenger aisle. During emergency evacuation, the absence of seating along the carry-through structure 46 may improve passenger traffic flow along that length of the cabin since merging passengers would not be present to disrupt flow.
  • the carry-through structure 46 may be formed as an inboard extension of the wing box 108 of the wing panels 42, 44.
  • the carry-through structure 46 may comprise an upper tension panel 110 and a lower compression panel 112 which are joined together by transversely extending, longitudinally spaced spars 1 18.
  • the carry- through structure 46 includes at least one longitudinally extending corridor-like passageway 114 therein which may include a floor 116 forming a walk-through aisle connecting the fore and aft sections 84, 86 (FIG. 7) of the mid-level deck 56.
  • FIG. 21 illustrates one half of a carry-through structure 46 that is provided with two of the passageways 114, while FIG.
  • the passageway 114 may be a full-height passageway that accommodates the full height of a passenger.
  • a the full-height passageway 114 may be one that can at least accommodate a 75 th percentile stature adult male without stooping, or 71 inches height, according to the Centers for Disease Control NHANES III anthropometric study data.
  • the carry-through structure 46 may include upper and lower structural panels 110, 112 respectively which may be fabricated from composite materials, although other materials such as metal may be employed in some embodiments.
  • the panels 110, 112 are connected by transversely extending, longitudinally spaced spars 118 which may comprise panels formed of composite or other materials or other structural elements.
  • Longitudinally extending ribs 120 which may comprise metal or composite truss-like assemblies, are connected to the upper and lower panels 110, 112, as well as adjacent ones of the spars 118 the ribs 120.
  • the ribs 120 are transversely spaced a distance sufficient to form the longitudinally extending passageways 114, and may include openings (not shown) therein to allow access to support facilities in the carry-through structure 46 located on opposite sides of the passageways 114.
  • the spars 118 may include upper and lower spar extensions 118a, 118b respectively to further strengthen the carry-through structure 46, and to compensate for any shear strength losses due to the presence of the openings in the spars 118 that form the passageways 114.
  • the carry-through structure 46 may include a variety of features or support facilities other than passenger seats, although it is also possible that some passenger or crew seats may be included in the carry-through structure 46.
  • support facilities include one or more galleys (not shown), passenger and/or crew rest facilities 90, a galley cart stowage facility (not shown), lavatories 88, storage areas (not shown), a medical facility (not shown), a lounge (not shown), a bar (not shown), and a play area (not shown), to name only a few.
  • the carry-through structure 46 includes a plurality of longitudinally spaced lavatories 88 along the inboard side of a passageway 114, as well as crew rest facilities 90 along the outboard side of the passageway 114.
  • a portion of the carry-through structure 46 may be employed to store fuel.
  • a wing tank 124 includes wing sections 126 as well as an inboard central section 128 and an inboard suspended section 130.
  • the inboard central section 128 of the fuel tank 124 may extend partially into the carry-through structure 46, as indicated by the dashed line 128a shown in FIG. 24.
  • the inboard suspended section 130 of the fuel tank 124 may extend into the carry-through structure 46 within the lower panel 112.
  • a fuel and vapor barrier may be located between each of the said inboard sections 128, 130 and the passageway 114.
  • FIGS. 27 and 28 illustrate additional details of the main landing gear 50.
  • the main landing gear 50 may be completely enclosed within the fuselage 32 when stowed, without the need for fairings, thereby further reducing drag and weight, yet when deployed, extends laterally beyond the OML (outer mold line) 125 of the fuselage 32, as shown in FIG. 28, to provide the airplane 30 with sufficient wheel track.
  • the main landing gear 50 may be mounted on one of more frames 96 (FIG. 28) of the fuselage 32.
  • a main landing gear truck 132 carrying a plurality of ground engaging wheels 134 is connected to an oleo strut 136.
  • the oleo strut 136 in turn is connected to a retractable trunnion support structure 138 which rotates about a trunnion pivot 135.
  • a series of links 138 connect the oleo strut 136 to the fuselage structure (FIG. 28).
  • the gear truck 132 retracts laterally inward to an inboard retracted position as the oleo strut 136 is drawn inboard by the MLG actuators.
  • the links 138 function to transmit force to the oleo strut 136 and assist in locking the landing gear 50 in a deployed outboard position.
  • the landing gear 50 may be deployed under the force of gravity.
  • the main landing gear 50 may employ one or more central landing gear posts 140 for better ground pressure distribution from wheelset 134 to a runway 76.
  • the main landing gear 50 may be advantageously used with airplanes having a fuselage with any of variety of cross sectional shapes and sizes.
  • a fuselage 32a has a slightly elliptical shape which reduces the internal volume of space available to stow the main landing gear 50.
  • a fairing 142 may be needed to cover only a small outboard portion of the gear 50. Because a majority portion of the retracted gear 50 is stowed inboard of the OML 125, the fairing 142 represents a minimal increase in the wetted area of the airplane 30.
  • a mid- wing airplane 30b employing the carry-through structure previously described has open rotor or un-ducted fan type engines 48a mounted beneath the wing 34.
  • the open rotor engines 48a include relatively large diameter open blades 144 which, because of the elevation of the wing 34, are spaced sufficiently above the ground such that adequate ground clearance 78 is achieved.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Body Structure For Vehicles (AREA)

Abstract

L'avion (30) selon l'invention comprend une aile (42, 44) montée à un niveau médian sur un fuselage tubulaire (32). L'aile (42, 44) comprend un support traversant qui traverse transversalement le fuselage (32) et divise une cabine en des sections avant et arrière. Au moins un passage longitudinal dans la structure de support traversant permet aux passagers/à l'équipage de circuler entre les sections avant et arrière de la cabine.
PCT/US2012/029549 2012-03-16 2012-03-16 Avion à aile médiane WO2013137915A1 (fr)

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3138770A1 (fr) * 2015-09-04 2017-03-08 Airbus Operations (Sas) Nervure simplifiee pour caisson central de voilure d'aeronef
CN107776875A (zh) * 2017-10-23 2018-03-09 晨龙飞机（荆门）有限公司 一种新型飞机起落架及起落方式
EP3348470A1 (fr) * 2017-01-16 2018-07-18 Deutsches Zentrum für Luft- und Raumfahrt e.V. Configuration de raccord en t d'un obstacle à l'écoulement d'un flux sur une paroi
WO2018203191A1 (fr) * 2017-05-01 2018-11-08 Bombardier Inc. Unité d'aile d'aéronef à peau de voilure supérieure délimitant un plancher étanche

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1859807A (en) * 1930-03-28 1932-05-24 William B Stout Airplane
FR868162A (fr) * 1938-09-24 1941-12-23 Messerschmitt Boelkow Blohm Chambre d'altitude, surtout dans des grands avions
US5992797A (en) * 1998-09-18 1999-11-30 The Boeing Company Dual upper deck airplane
WO2008102278A2 (fr) * 2007-02-23 2008-08-28 Michael Yavilevich Avion à plusieurs étages
US20100012773A1 (en) * 2008-07-16 2010-01-21 Im Sunstar Aircrft Structure

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1859807A (en) * 1930-03-28 1932-05-24 William B Stout Airplane
FR868162A (fr) * 1938-09-24 1941-12-23 Messerschmitt Boelkow Blohm Chambre d'altitude, surtout dans des grands avions
US5992797A (en) * 1998-09-18 1999-11-30 The Boeing Company Dual upper deck airplane
WO2008102278A2 (fr) * 2007-02-23 2008-08-28 Michael Yavilevich Avion à plusieurs étages
US20100012773A1 (en) * 2008-07-16 2010-01-21 Im Sunstar Aircrft Structure

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3138770A1 (fr) * 2015-09-04 2017-03-08 Airbus Operations (Sas) Nervure simplifiee pour caisson central de voilure d'aeronef
FR3040684A1 (fr) * 2015-09-04 2017-03-10 Airbus Operations Sas Nervure simplifiee pour caisson central de voilure d'aeronef.
US10399663B2 (en) 2015-09-04 2019-09-03 Airbus Operations (S.A.S.) Integrated ribs for central wing box
EP3348470A1 (fr) * 2017-01-16 2018-07-18 Deutsches Zentrum für Luft- und Raumfahrt e.V. Configuration de raccord en t d'un obstacle à l'écoulement d'un flux sur une paroi
WO2018203191A1 (fr) * 2017-05-01 2018-11-08 Bombardier Inc. Unité d'aile d'aéronef à peau de voilure supérieure délimitant un plancher étanche
US11661170B2 (en) 2017-05-01 2023-05-30 Bombardier Inc. Aircraft wing unit with upper wing skin defining pressure floor
CN107776875A (zh) * 2017-10-23 2018-03-09 晨龙飞机（荆门）有限公司 一种新型飞机起落架及起落方式

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