• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    In order to help install the doors in the landing gear housing and adjust its position, the invention relates to an aircraft nose (1) comprising a connecting frame (50) between the train housing (20) of landing and the outer skin (16) of the fuselage, the connecting frame extends around an opening (40) in the outer skin (16) and comprises: - a skirt (52) that rests against the outer shell (16) of the fuselage and connects to it, the skirt defines a passage for the landing gear (58) which is configured to be closed by doors (62) when the last ones are in a closing position; y - means (64) for supporting the doors (62). (Machine-translation by Google Translate, not legally binding)
    公开号:ES2585283A2
    申请号:ES201531847
    申请日:2015-12-18
    公开日:2016-10-04
    发明作者:Guillaume Gallant；Hervé BIENNES
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

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    DESCRIPTION
    Aircraft nose provided with a connection frame between the landing gear housing and the outer lining of the fuselage
    Technical field
    The present invention relates to the front part of an aircraft, also known as a nose, which comprises a landing gear housing that houses the front landing gear.
    The invention applies to all types of aircraft.
    State of the art
    The nose of an aircraft has undergone many developments with a view to optimizing its mass, volume, cost, safety, ease of fabrication, maintenance, etc. A nose of this type is known, for example, from FR 2 910 875 and US 7 784 736.
    Despite the fact that there are many designs around the nose, the landing gear housing can still be optimized, in particular to help install the landing gear doors when the nose is assembled or during maintenance.
    Normally, the landing gear housing is defined by three or five reinforced panels. To hinge the doors, plates are connected to the side walls of this landing gear housing, which is the same connected to the fuselage in an opening for the passage of the landing gear made in the outer lining of the fuselage. After the housing has been mounted on the fuselage, an operation is carried out to adjust the position of the doors with respect to said opening made in the outer covering to reduce as much as possible the play between that covering and the edges of the doors.
    In addition to requiring specific equipment to adjust the position of the doors, such as cradles associated with the hinge plates for these doors, the centering operation is expensive in terms of cost and time. Sometimes it even requires adjustments to the perimeter of the doors and / or the opening in the outer lining of the fuselage.
    Therefore there is a need to optimize the design of the front landing gear housing environment with a particular vision to help adjust the doors that close the landing gear housing.
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    Description of the invention
    In order to fulfill this need in the first place the invention relates to an aircraft nose comprising a fuselage, a landing gear housing, front landing gear housed in the landing gear housing and at least one closing door the landing gear housing, said fuselage comprises an outer lining provided with an opening for the landing gear passage. According to the invention, the nose also comprises a connection frame between the landing gear housing and the outer shell of the fuselage, the connection frame extends around said opening in the outer shell and comprises:
    - a skirt that rests against the outer lining of the fuselage and connects to it, the skirt defines a passage for the landing gear that is configured so that it can be closed by said at least one door when the latter occupies a position of close, and
    - means to support said at least one door.
    The invention is advantageous because the assembly of the door / doors is easier compared to the prior art solutions. In fact, these doors are mounted directly in the connection frame, as a result of which it is possible to benefit from a precise placement in relation to the landing gear passage defined by the same connection frame, which thus extends around the edges of the opening in the outer lining. In other words, this precise placement is achieved by construction, without being subject to the precision with which the constituent components of the aircraft's nose have been assembled.
    In addition to this, the connection frame is provided with a skirt configured to rest against the outer lining of the fuselage around the perimeter of the opening made in that liner. Advantageously, this assembly only requires little precision, and has no effect on the centering of the doors in the passage through the connection frame.
    The invention thus offers gains in terms of assembly times and costs and adjustment of the landing gear housing doors. These gains arise not only when the nose is being assembled, but also during maintenance operations with a view to dismantling / replacing the doors.
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    The invention has at least one of the following optional features taken in isolation or in combination.
    The frame also comprises a soul, and said support means are mounted on the skirt and / or the soul.
    The landing gear housing is connected to the soul of the connection frame.
    In cross section the frame has a global inverted T shape.
    At least one of the two elements of the skirt of the connection frame and the outer lining of the fuselage is provided with a double fold or a reduction in order to receive the other of the two elements.
    The outer lining of the fuselage covers the skirt of the outer connection frame, or vice versa.
    The connection frame is also provided with supports to hinge a landing gear leg and / or landing gear strut switch.
    The connection frame is made of a single piece, or using a plurality of bolted or welded parts.
    The landing gear housing is made of five reinforced panels assembled together. As an alternative, you can have only three reinforced panels.
    The invention also relates to an aircraft comprising a nose as described above.
    The invention also relates to an assembly process of this type of nose comprising phases comprising:
    a) connect the connection frame to the outer lining of the fuselage;
    b) connect the connection frame to the landing gear housing; phases a) and b) are carried out in any order.
    According to a first preferred embodiment of the invention, the outer lining of the fuselage covers the skirt of the outer connection frame and phase a) comprises installing the connecting frame from within the fuselage. It should also be noted that phase a) can be carried out before or after phase b).
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    According to a second preferred embodiment of the invention, the skirt of the connection frame covers the outer lining of the fuselage on the outside and phase a) comprises installing the connection frame from outside the fuselage. Preferably phase b) is then carried out before phase a). In this way it comprises a single module comprising the connection frame and the landing gear housing that can be driven from outside the fuselage when phase a) is carried out.
    Whatever the realization of the two described above, it is conceived that the two doors can be mounted in the connection frame before or after operations a) and b), or even between these two operations.
    Other advantages and features of the invention will be apparent from the following detailed non-limiting description.
    Brief description of the drawings
    This description will be provided in relation to the attached drawings in which:
    - Figure 1 shows a side view of an aircraft having a nose according to the invention;
    - Figure 2 represents a partially exploded perspective view of the nose of an aircraft according to the first preferred embodiment;
    - Figure 3 is a perspective view of a connection frame between the outer lining of the fuselage and the landing gear housing;
    - Figures 3a and 3b are views similar to that of Figure 3, in which the connection frame is in the form of other embodiments;
    - Figure 4 is a view similar to that of Figure 3, with the frame supporting the landing gear doors;
    - Figure 5 is a cross-sectional view of the landing gear environment, with one of the doors shown in the closed position;
    - Figure 6 is a perspective view of the landing gear environment, with one of the doors shown in the opening position;
    - Figures 7a and 7b provide diagrams of different phases in a process for assembling the nose illustrated in the previous figures; Y
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    - Figure 8 provides an outline of a phase in a process for assembling a nose according to a second preferred embodiment of the invention.
    Detailed description of preferred embodiments
    With reference to Figure 1, this shows an aircraft 100 of the type of commercial aircraft comprising a nose 1 according to the invention.
    Throughout the following description, by convention X corresponds to the longitudinal direction of the aircraft, Y to the direction oriented transversely with respect to the last one and Z to the vertical direction or elevation, these three directions X, Y and Z are with right angles each.
    In addition to this, the terms "front" and "rear" must be considered in relation to the direction of movement of the aircraft that takes place as a result of the thrust exerted by the turbo-reactors, this direction is shown schematically with arrow 3.
    With reference to FIGS. 1 and 2, the nose 1 comprises firstly at its most aft part a pressurized zone 2 within which there is a separation floor 8 between an upper pressurized compartment 4 which is generally used for transporting people and a pressurized compartment under the 6th floor that is normally used to locate technical equipment related to the aircraft and / or cargo storage. More precisely, from the front back, the upper pressurized compartment 4 generally comprises the cockpit 7 of the aircraft followed by the passenger cabin 9. On the other hand the pressurized compartment below the floor 6 generally comprises, from the front behind, a known area as the technical warehouse designed for the storage of specific technical equipment of the aircraft, followed by an area known as the cargo warehouse used for cargo storage.
    The pressurized zone 2 is limited in front by a wall 10 which also defines in its front part an area of non-pressurized radome 14 used to house a radar unit. Behind the radome wall 10 the nose is radially limited by a fuselage 15, which comprises an outer lining 16 supported on fuselage frames 17.
    In front of the pressurized compartment under the floor 6 is a front landing gear housing 20, the interior of which is preferably not pressurized. The landing gear housing 20 houses the front landing gear 30, shown in the lowered position in Figure 1. The front landing gear 30 is of the conventional type and is
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    known to those skilled in the art. In general, it comprises a landing leg 32 that is mounted so that it is hinged on one of its extremities and rests on a wheel assembly 34 on its other extremity. It also comprises one or more deployment pistons (not shown), as well as a strut switch 36 generally comprising two hinged segments together, whose lower end is hingedly mounted on leg 32.
    With reference to Figures 2 to 6, the environment of the landing gear housing 20, which is specific to the invention, will now be described. First of all, it should be noted that this front landing gear housing 20 is generally solid in rectangular shape formed of five reinforced panels assembled together. The sixth side of the housing 20 is open at the bottom for the passage of the landing gear 30. This open side corresponds to an opening 40 made in the liner 16 of the fuselage 15, again to allow the passage of the front landing gear 30 .
    One of the special features of the invention is in the use of a connection frame 50 that provides a mechanical interface between the front landing gear housing 20 and the liner 16. More specifically, the connection frame 50 generally has a shape rectangular that follows the perimeter of the opening 40 in the cladding, thus ensuring that it fills it.
    In cross section the connection frame 50 has the general shape of an inverted T, with a skirt 52 facing down in relation to the reinforcing member 54, parallel to the direction Z. The angle between the core and the skirt is not necessarily a right angle, in fact it can be curved and inclined in such a way as to coincide locally with the fuselage lining 16 at the perimeter of this opening 40. In fact the skirt 52 is placed in the liner 16 in the Z direction, preferably being in Direct contact between the two elements that are connected together by means of rivets, bolts or similar.
    The connection frame 50 therefore comprises four sections that are joined end to end to obtain their overall rectangular shape. These sections are made in one piece from a single molded or machined element, or these four sections are welded together. The frame 50 is preferably made of metal.
    The skirt 52 of the frame 50 has an inner edge 56 that internally defines a through hole 58 for the landing gear, this through hole also has a section
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    transverse with global rectangular shape. The passage through 58 is intended to be closed by doors 62, for example three doors, including two side doors and a rear door.
    The connection frame 50 comprises support members that are used to hinge these doors 62. Here these are ribs 64 that are perforated for the passage of a hinge shaft. Alternatively they can be in the form of plates.
    Each rib 64 is preferably supported by a core 54 and a skirt 52. It is made of a piece with the rest of the frame 50, or is applied to the core and the skirt by welding. Each door 62 has several mechanical connection members in the form of a gooseneck, reference 66, each hinged on a rib 64.
    In the closed position, the doors 62 close the passage through 58 in such a way as to provide a satisfactory aerodynamic joint, in particular by limiting the play between the outer edge of the doors 62 and the inner edge 56 of the skirt 52. mounted directly on the connection frame, the doors 62 are thus precisely placed inside the through hole 58 as a result of their construction.
    The lower end of the landing gear housing 20 is connected to the core 54 of the frame 50, again by rivets, bolts or the like. This connection is made along the entire length of the frame, in the overlapping areas between the reinforced panels of the housing 20 and the core 54. Also, as mentioned above, the skirt 52 of the joint frame 50 is connects to the lining 16, covering the last one to the skirt on the outside. As a consequence, this assembly only requires little precision, and has no effect on the placement of the doors, which remain perfectly centered in the through hole 58 of the connection frame 50.
    The installation of the doors 62 and the adjustment of their position is facilitated both during the assembly of the nose 1 and during the maintenance work with a view to dismantling / replacing the doors.
    In order to improve aerodynamic performance, the skirt 52 is provided with a reduction 72 that receives the outer covering 16. This reduction can be replaced by a double fold when it is desired that the skirt has a constant thickness of material. Offers continuity between the outer surface of the liner 16 and the outer surface of
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    the other part of the skirt 52, which also ensures aerodynamic continuity with the outer surface of the doors 62 when it is in the closed position. A similar double fold or reduction can then be provided in the aerodynamic joint between the edges of the doors 62 and the perimeter of the opening 40 in the liner 16.
    Finally, it is indicated that for ease of assembly, the connection frame 50 may also have installed supports 51, 51 ’that hinge the landing leg and / or the strut switch, as shown in Figures 3a and 3b. In order to do this, the supports 51 are connected to the reinforcement member 54 and a strut 53 connects them to the supports 51 'when the latter are provided in the connection frame 50, as is the case in the example in the figure 3b
    Figures 7a and 7b show several phases in a process for assembling the nose 1 of an aircraft. First of all, the connection frame 50 is placed in position on the outer lining of the fuselage 16, from inside the fuselage 15. This takes place when the skirt 52 rests against the perimeter of the opening 40 in the skin 16. The reduction 72 it can help center the frame 50 in the opening 40. Subsequently the overlapping elements 16, 52 are assembled by riveting or by a similar technique.
    The process continues by connecting the landing gear housing to the soul 54 of the frame, again by riveting or by a similar technique.
    In a second preferred embodiment of the invention shown schematically in Figure 8, it is skirt 52 that covers the liner 16 and not the other way around as in the first embodiment. Because of this, the phase of installing and connecting the frame 50 to the liner 16 is carried out from outside the fuselage. In addition, the landing gear housing 20 can first be connected to the frame 50 in order to obtain a module that then moves as a unit from outside the fuselage 1 to the opening 40. This module is secured when the skirt 52 enters in contact with the perimeter of the opening 40 in the liner 16, which is here provided with a reduction 72.
    Of course those skilled in the art can make various modifications to the invention just described merely by way of non-limiting examples.
    权利要求:
    Claims (14)
    [1]
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    1. Aircraft nose (1) comprising a fuselage (15), a landing gear housing (20), front landing gear (30) housed in the landing gear housing and at least one door (62) that closes the landing gear housing, said fuselage comprises an outer lining (16) provided with an opening (40) for the passage of the landing gear (30),
    characterized in that it also comprises a connection frame (50) between the landing gear housing (20) and the outer shell (16) of the fuselage, the connection frame extends around said opening (40) in the outer shell (40). 16) and includes:
    - a skirt (52) that rests against the outer lining (16) of the fuselage and connects to it, the skirt defines a passage (58) for the landing gear that is configured to be closed by said at least one door ( 62) when the last one is in the closing position; Y
    - means (64) for supporting said at least one door (62).
    [2]
    2. Morro according to claim 1, characterized in that the frame (50) also comprises a soul (54), and that said support members (64) are mounted on the skirt (52) and / or the soul (54) .
    [3]
    3. Morro according to claim 2, characterized in that the landing gear housing (20) is connected to the core (54) of the connection frame (50).
    [4]
    4. Morro according to claim 2 or claim 3, characterized in that the frame (50) has the overall shape of an inverted T in cross section.
    [5]
    5. Morro according to any one of the preceding claims, characterized in that at least one of the two elements comprising the skirt (52) of the connection frame and the outer lining (16) of the fuselage is provided with a double fold or a reduction (72) to receive the other of the two elements.
    [6]
    6. A nose according to any one of the preceding claims, characterized in that the outer lining (16) of the fuselage covers the skirt (52) of the connecting frame (50) on the outside, or vice versa.
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    [7]
    7. Nose according to any one of the preceding claims, characterized in that the connection frame (50) is also equipped with hinge supports (51) for a landing leg (32) and / or a strut switch (36) of the landing gear (30).
    [8]
    8. Morro according to any one of the preceding claims, characterized in that the connection frame (50) is made of a single piece, or of a plurality of pieces welded together.
    [9]
    9. Morro according to any one of the preceding claims, characterized in that the landing gear housing (20) is made of five reinforced panels assembled together.
    [10]
    10. Aircraft (100) comprising a nose (1) according to any of the preceding claims.
    [11]
    11. Process for assembling a nose (1) according to any one of claims 1 to 9, characterized in that it comprises phases comprising:
    a) connect the connection frame (50) to the outer shell (16) of the fuselage;
    b) connect the connection frame (50) to the landing gear housing (20); phases a) and b) are carried out in any order.
    [12]
    12. Morro according to claim 11, characterized in that the outer lining (16) of the fuselage covers the skirt (52) of the connection frame (50) outside and that phase a) comprises installing the connection frame ( 50) from inside the fuselage (15).
    [13]
    13. Process according to claim 11, characterized in that the skirt (52) of the connection frame (50) covers the outer lining (16) of the fuselage outside and that phase a) comprises installing the connection frame ( 50) from outside the fuselage (15).
    [14]
    14. Process according to claim 13, characterized in that phase b) is carried out before phase a).
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    同族专利:
    公开号 | 公开日
    FR3030442B1|2017-01-27|
    ES2585283R1|2017-02-08|
    US9840321B2|2017-12-12|
    CN105711803A|2016-06-29|
    CN105711803B|2019-09-20|
    ES2585283B2|2018-01-08|
    US20160176513A1|2016-06-23|
    FR3030442A1|2016-06-24|
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    FR2954934B1|2010-01-07|2013-05-24|Eads Europ Aeronautic Defence|AIRCRAFT LANDING TRAIN MODULE, AIRCRAFT COMPRISING THE SAME, AND METHOD OF MANUFACTURING AN AIRCRAFT|
    ES2400768B1|2010-06-30|2014-02-12|Airbus Operations, S.L.|INTERNAL AIRCRAFT STRUCTURE IN COMPOSITE MATERIAL.|
    FR2962410B1|2010-07-09|2013-07-12|Airbus Operations Sas|METHOD FOR ADJUSTING LANDING TRAY CASE TRAPPERS AND TRAPPER FOR IMPLEMENTING THE SAME|
    FR2969119B1|2010-12-17|2013-02-08|Airbus Operations Sas|FRONT PART OF AN AIRCRAFT FUSELAGE INTEGRATING A LANDING TRAIN STORAGE BOX|
    FR2983170B1|2011-11-30|2014-09-19|Airbus Operations Sas|FRONT AIRCRAFT FUSELAGE STRUCTURE COMPRISING A LANDING TRAIN|
    FR2983826B1|2011-12-12|2013-12-20|Airbus Operations Sas|FRONT STRUCTURE IMPROVED WITH COMPARTMENT FOR LANDING TRAIN.|
    FR2999524B1|2012-12-17|2015-02-20|Airbus Operations Sas|AIRCRAFT FRONT SEAL FOUNDATION INCLUDING RENOVATIONS FOR ACCOMMODATION OF COCKPIT EQUIPMENT|
    FR3000016B1|2012-12-21|2016-01-15|Airbus Operations Sas|FRONT AIRCRAFT PART WITH IMPROVED TRAIN BOX|RU2678729C1|2018-03-13|2019-01-31|Общество с ограниченной ответственностью "Конструкторское бюро "Современные авиационные технологии"|Nose part of aircraft fuselage|
    CN112357049A|2020-11-30|2021-02-12|中国特种飞行器研究所|Carbon fiber reinforced aluminum alloy laminated plate impact-resistant unmanned aerial vehicle front cover structure|
    法律状态:
    2018-01-08| FG2A| Definitive protection|Ref document number: 2585283 Country of ref document: ES Kind code of ref document: B2 Effective date: 20180108 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1462796A|FR3030442B1|2014-12-18|2014-12-18|FRONT AIRCRAFT TIP EQUIPPED WITH A JUNCTION FRAME BETWEEN THE LANDING TRAIN BOX AND THE EXTERNAL SKIN OF THE FUSELAGE|
    FR1462796|2014-12-18|
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