• 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:
    The invention comprises a cabin space (34) dedicated to passengers and, below, a sub-cabin space (30) which extends along the longitudinal axis of said aircraft, characterized in that the under-cabin space (30) ) comprises, distributed along two lines parallel to the longitudinal axis of the aircraft, two sets of systems which are capable of performing functions necessary for the operation of the aircraft, the two sets of systems being arranged respectively in two lateral zones (Z1, Z2) of the sub-cabin space which are spaced transversely from one another and enclose a free central zone (E1) extending along the longitudinal axis (X) of the aircraft . This arrangement thus removes any technical area from the sub-cabin space, which facilitates internal layout and maintenance.
    公开号:FR3035072A1
    申请号:FR1553495
    申请日:2015-04-20
    公开日:2016-10-21
    发明作者:Frederic Vinches；Bernard Guering
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    [0001] BACKGROUND OF THE INVENTION The invention relates to an aircraft comprising a cabin space dedicated to passengers and, below, an under-cabin space housing systems that are capable of performing necessary functions. operation of the aircraft. PRIOR ART Most commercial aircraft comprise a front tip housing a cockpit, a rear tip and, in between, a central portion. This central part located in the pressurized zone of the fuselage includes a cabin space dedicated to the passengers and, below, an under-cabin space. Conventionally, the under-cabin space or bunker contains both containers for transporting freight and various systems necessary to perform various functions, for example electrical, electronic and avionics (electrical cores and associated components, avionics computers. .), aeraulic, especially in terms of air conditioning and ventilation of the various pressurized areas of the fuselage (for the comfort of people and the operation of equipment), and hydraulic, especially in terms of water distribution for spaces dedicated to catering and toilets as well as wastewater recovery from these spaces. It is known that these systems or at least some of them are distributed in the sub-cabin space in equipment arranged within different dedicated technical areas, namely: a main electrical and electronic technical zone before located at the both in the forward tip and in the central part, - a central electrical and electronic technical zone situated in the central region of the central part when the wing of the aircraft is connected to the fuselage in the said central region, - a technical aeraulic zone located behind the central electrical and electronic engineering zone, - a rear electrical and electronic engineering zone located in the rear region of the central part, 3035072 2 - a hydraulic technical zone located behind the electrical and electronic technical zone annex back and before the rear tip. It should be noted that the principle of the geographical dispersion of the different technical zones also applies for aircraft in which the wing is positioned differently. The location of these technical areas can then vary. The integration of the various electrical, electronic, aeraulic and hydraulic systems respectively in equipment of the aforementioned dedicated areas leads to complex installations.
    [0002] Indeed, this integration must take into account: on the one hand, installation constraints that make it difficult, if not impossible, for the physical integration in the same place of objects of different natures and shapes, and on the other hand, security constraints that require duplicating at least some of the systems by installing the same two systems as far as possible from each other. Moreover, because of these constraints, the functional links between the systems (electrical, aerial, hydraulic links) are not optimized with respect to their length and their complexity.
    [0003] SUMMARY OF THE INVENTION An object of the invention is to propose a new internal aircraft architecture making it possible to simplify the integration of the aforementioned systems. The present invention thus relates to an aircraft comprising a cabin space dedicated to passengers and, below, a sub-cabin space which extends along the longitudinal axis of said aircraft, characterized in that the sub-cabin space comprises , distributed along two lines parallel to the longitudinal axis of the aircraft, two sets of systems which are capable of performing functions necessary for the operation of the aircraft, the two sets of systems being arranged respectively in two lateral areas of the under-cabin space which are spaced transversely from one another and enclose a free central area which extends along the longitudinal axis of the aircraft, thereby removing under-cabin space any technical area.
    [0004] The distribution of the different systems according to two sets of systems respectively distributed in two distinct lateral zones situated on either side of a free central zone (the free central zone is reserved in particular for accommodating a plurality of cargo containers aligned one with the other. Behind the others along the longitudinal axis of the aircraft) provides a simplified undercarriage space architecture. The local technical areas of the under-cabin space which were previously intended to accommodate the various systems in a dedicated manner (eg electrical and electronic zones, air and hydraulic zones) and dispersed in different spaced locations (for example longitudinally) each other have been removed. These dedicated and dispersed technical areas are now replaced by two lateral zones each of longitudinal extension (parallel to the longitudinal axis of the aircraft) which group together at least some, and for example, most systems capable of performing functions. necessary for the operation of the aircraft and which previously were in the above-mentioned dispersed technical areas. The concentration in two lateral zones or parallel lateral volumes of the systems makes it possible to rationalize the arrangement of the functional links (for example electrical, aerial and hydraulic) connected to the systems and links between the systems or at least between some of them. According to other possible characteristics taken separately or in combination with each other: the aircraft comprises two sets of links (for example electrical, air-flow, and hydraulic) which each extend along one of the two sets of system lines, in the part of the lateral zone between said systems of the overall line concerned and the adjacent wall of the fuselage and which comprise branches for their connection to said systems; the two parallel lines of sets of systems extend from one end to the other of the under-cabin space; 3035072 4 -Each of the two parallel lines is interrupted locally to the right of a part of the under-cabin space which is located at the level of the wing of the aircraft (when the aircraft is low-wing); the two parallel lines of sets of systems extend continuously from one end to the other of the under-cabin space; - the systems of each of the two sets of systems are housed in furniture distributed to each other adjacent to the line of the set of systems concerned; at least some of the pieces of furniture are identical; Each piece of furniture has a front face situated opposite the free central zone and which, according to a cross-sectional view, is inclined in the direction of the free central zone so that the upper end of the front face is closer to said free central area than the lower end recessed from said front face; Each piece of furniture has an upper face and a lower face both adjacent to the front face of the piece of furniture and shaped so as to be as close as possible to the ceiling of the under-cabin space and of the adjacent wall of the fuselage respectively; each piece of furniture has, in a cross-sectional view, a generally trapezoidal shape; - the free central zone is delimited laterally by the two lines of systems, at its upper part by the ceiling of the under-cabin space and at its lower part by a floor parallel to the ceiling; the free central zone presents, in a cross-sectional view, a polygonal shape formed by the union of two trapezoids joined by their respective bases; the under-cabin space accommodates cargo containers whose general cross-sectional shape corresponds to the general polygonal shape of the free central zone; The aircraft has a front tip, a rear tip and, in between, a central portion which includes the cabin space dedicated to the passengers and, below, the under-cabin space, the central portion having a cross-section with constant geometry over its entire length.
    [0005] BRIEF DESCRIPTION OF THE FIGURES Other features and advantages will become apparent from the following description, given solely by way of nonlimiting example and with reference to the appended drawings, in which: FIG. 1 is a view schematic assembly of an aircraft according to one embodiment of the invention; FIG. 2 is a schematic view of a cross section of the aircraft of FIG. 1; FIG. 3 is a partial schematic perspective view of the cargo hold of FIG. 2; FIG. 4 is a diagrammatic overall view showing the bi-line architecture of the furniture of FIGS. 2 and 3. DETAILED DESCRIPTION FIG. 1 represents an aircraft 10 which comprises a front tip 12, a rear tip 14 and, both, a central part of the fuselage 16. The central part of the fuselage is an area of the aircraft with a non-evolutive transverse section along its longitudinal dimension, along the longitudinal axis X, while the front and rear points are X-axis evolutionary cross-sectional areas. The aircraft also comprises a central wing 18 on which motors are mounted, only one of which, marked 20, is shown. Figure 2 shows a cross section of the central portion of the fuselage 16 which, in this embodiment, is of constant geometry throughout its length and for example is circular. In this example, the whole 25 of the central part of the fuselage 16, called "current section of the aircraft" is thus, in turn, of cylindrical shape. In the figure there is shown a frame 22 of the primary structure of the fuselage, it being understood that the fuselage comprises, along the axis X, a succession of similar frames parallel to each other and secured together in a known manner.
    [0006] The central part of the fuselage 16 is divided into an upper cabin space dedicated to the passengers (the cabin space comprises a cabin equipped with passenger seats which are not represented for the sake of simplification) and an under-cabin space or bunker space. The undercarriage space 30 is more particularly located under a floor 32 of the cabin or deck space 34. The undercarriage space 30 includes a cargo floor 36 provided in the lowest portion of the cross section and which is parallel to the floor 32. The floor 32 acts as a ceiling for the undercarriage space and extends over the entire length of the central portion 16 (along the X axis of Figure 1). The cargo floor 36 includes a horizontal portion 36a flanked by two symmetrical inclined sidewall portions 36b, 36c which follow the upward profile of the adjacent walls of the fuselage. The floor 32 comprises a central portion 32a flanked by two lateral portions 32b, 32c. As shown in Figure 2, two furniture Ml, M2 are mounted in two side zones Z1, Z2 respectively below the two floor side portions 32b, 32c. The lateral zones Z1, Z2 extend longitudinally from one end of the undercarriage space, located at the front nose, to a central zone 16a of the central portion 16 (FIG. which the wing 18 is connected to the fuselage. The lateral zones Z1, Z2 continue to extend longitudinally, after this interruption due to the zone 16a, to an opposite end of the sub-cabin space situated at the rear tip 14 (FIG.
    [0007] The two lateral zones Z1, Z2 are spaced transversely from one another and frame a free central zone El of longitudinal extension intended to accommodate in particular a plurality of cargo containers arranged along the longitudinal axis of the aircraft such that the container 40 in FIG. The furniture M1 and M2 are arranged facing each other, on either side of the free central zone El. Each piece of furniture has, in a cross-sectional view, for example a shape general trapezoidal. The trapezoidal overall shape of the furniture M1 (or M2) is formed, on the one hand, of two large faces, parallel to one another M12, M13 (respectively M22, M23) and, on the other hand, of two small faces. M14, M15 (respectively M24, M25) inclined towards each other and adjacent to the large faces. For the purposes of the following description, the large parallel faces M12, M13 (respectively M22, M23) are respectively called front and rear faces. The front face M12 (or M22) is the 3035072 7 facing the cabinet which is located opposite the free central area El, while the rear face of the cabinet M13 (respectively M23) is the opposite one located behind the furniture relative to the central zone El. The furniture Ml, M2 each have their respective front faces M12, M22 located opposite the free central zone E1 and inclined toward this free central zone so as to that the respective upper end M121, M221 of the front face is closer to said free central area than the lower end M122, M222 set back from said front face. The lateral faces M14 (upper face), M15 (lower face), M24 (upper face), M25 (lower face) of the respective furniture M1, M2 are shaped so as to be as close as possible to the floor side portions 32b respectively. and 32c and lower adjacent walls of the fuselage in the under-cabin space 30. The furniture thus has outer contours in cross-section which closely follow at least in part the contours of each zone Z1, Z2 of triangular cross-section. . As shown in Figure 3, the furniture M1 (or M2) are arranged next to each other vis-à-vis the central free zone El (these furniture are arranged one behind the other according to a view taken in the longitudinal axis X of the aircraft) in the lateral zone Z1 (or Z2) and 20 extend along a line parallel to the axis X. The furniture pieces of the same furniture line are arranged in an adjacent manner to each other and thus form a parallelepiped over the entire length of the arrangement. The two lines of furniture are thus arranged parallel to each other, on either side of the central zone E1. Each piece M1, M2 is fixed by the upper and lower ends of its front face M12, M22 respectively to free end of the lateral floor portion located above and at a lower edge of the fuselage located below the lateral floor portion, set back from the projection formed by the end of said lateral portion which is connected to the central portion 32a.
    [0008] In the illustrated embodiment the pieces of furniture are all identical and each occupy the same lateral volume. According to a variant not shown, the furniture may differ from each other in shape and volume.
    [0009] It will be noted that the floor has been represented here (FIG. 3) in the form of three distinct floor portions: the central portion 32a, of smaller thickness than the lateral portions 32b, 32c which surround it, is fixed to the latter at its opposite ends. One of the two free ends of the central portion 32a is attached to a free end of one of the two floor side portions, via complementary fasteners engaged with each other, so as to be able to move transversely under the effect of the pressurization of the fuselage. More particularly, the cooperation between the fastening elements which are complementary to one another forms, on the one hand, an articulated connection 31 between the central portion 32a and the lateral portion 32c and, on the other hand, a link 40 between the central portion 32a and the lateral portion 32b. The link 40 is such as to allow a possible transverse displacement (in the plane of the floor 32, namely here in a horizontal plane) between the two linked portions 32a, 32b. The connection is a sliding connection for example made by an axis which is slidable inside an oblong hole. This arrangement is useful during the pressure deformation of the fuselage with circular cross section. Under the effect of the pressurization of the fuselage, the set of lateral portions 32c and central 32a interconnected deviate from the other lateral portion 32b, which makes it possible not to impose mechanical loads in tension at the central portion 32a. The central floor portion 32a is for example divided along the longitudinal axis of the central fuselage portion 16 into a plurality of longitudinal floor segments each having a length reduced with respect to the total length of the central fuselage portion. The longitudinal floor segments once in place form a central portion of continuous floor. Note that the floor side portions 32b, 32c may, for their part, be each made of a single elongated module of length equal to or less than that of the central portion 16.
    [0010] The free central zone E1 has, according to the view of FIG. 2, a polygonal shape formed by the union of two trapeziums Ti, T2 joined by their respective bases along a fictitious line illustrated in dotted lines. The contours of this zone or space follow the profile of the lower face of the floor 32, the front faces of the furniture Ml, M2, the inclined lateral portions 36b, 36c of the cargo floor and the horizontal central portion 36a. The under-cabin space 30 thus accommodates cargo containers such as the container 40, the general cross-sectional shape of which corresponds to the general polygonal shape of the free central zone El in order to occupy all the available space. As shown in FIG. 3, the front face of each piece of furniture (such as furniture M2) comprises two parallel elongated elements 11, 12, such as connecting rods, framing a central panel p. The elements 11, 12 are mounted each articulated on longitudinal bars high and low b1 and b2, via their opposite ends M121, M122, M221, M222 respectively fixed to the lower face of the floor 32 and the bottom wall of the fuselage in the undercarriage space 30 by known techniques (the front of the cabinet 15 thus has two high and low joints). The lower ends M122 and M222 furniture are articulated via articulated connections of known type (clevis, tenon and axis). The upper ends of the furniture M121 and M221 are, in turn, articulated so that the joint can be opened to pivot the furniture downwards as shown in Figure 4. For example, the tenon used for the high articulation of the furniture is configured in the form of hook or carabiner in order to be able to open and close as needed. The furniture is likely to tilt down (see Figure 3 one of the furniture M2 in position extracted from its housing in support of the central portion 36a) to perform various operations and, in particular, access the space the Z2 side area behind the furniture. In the service position (not tilted), the elements 11, 12 act as oblique force transmission elements between the floor side portions 32b, 32c and the lower edges of the fuselage.
    [0011] The furniture installed between the floor side portions and the lower fuselage in the under-cabin space 30 are thus capable of supporting said floor side portions which rest on these furniture via their structural uprights.
    [0012] Each of the furniture of the set of furniture M1, on the one hand, and the set of furniture M2, on the other hand, is able to accommodate systems that are capable of performing functions necessary for the operation of the machine. 'aircraft. In other words, systems are the set of functions whose role is to ensure the proper functioning of the aircraft, outside the functions related to the structure of the aircraft and the passenger cabin. Only here are considered the integrated systems in the pressurized fuselage of the aircraft. These systems include electrical systems (for example electrical cores and their associated components) and / or electronics (for example various computers), air conditioning and ventilation systems, distribution and water recovery systems and avionics systems. These systems were previously dispersed in the cargo hold within specific local technical areas (ex: air zones, hydraulic zones, etc.) which have now been removed (technical front and rear technical zones, technical air zone in central zone and zone technical water in rear area). These zones included equipment providing a set of functions necessary for the proper functioning of the aircraft.
    [0013] These systems are now grouped, for example for the majority of them, in the furniture M1, M2 of the lateral zones Z1 and Z2 which extend along two parallel lines. As shown in FIG. 2, the arrangement of the furniture M1 and M2 (whose shape has been adapted) in an inclined position in the lateral zones 25 makes it possible to create, between the rear faces of these and the wall opposite the fuselage. , a space or secondary volume of substantially triangular cross section E2, E3, relatively reduced. This space which extends along the furniture lines accommodates the links (cables, conduits .....) electrical, air, and hydraulic 50a-c necessary for the operation of 30 systems housed in the furniture. Derivatives dl, d2, d3 make it possible to connect these links to the systems and act as inputs / outputs of the system furniture. The derivations d1, d2, d3 have either a role of power supply (power supply components of the system furniture) or a role of 3035072 11 communication. Ventilation air interfaces I1, 12 are arranged between the lower side walls of the furniture and the adjacent fuselage wall (Figure 2). FIG. 4 illustrates the dual-line architecture of the systems which has been arranged in the under-cabin space 30: the two furniture lines L1, L2 are the farthest possible from each other and the electrical links , aeraulic, and hydraulic 50a-c extend behind the furniture, along the fuselage wall 52. The furniture surround the central area El designed to accommodate cargo containers with optimized shapes adapted to that of the central area left free . The elimination of the technical compartments dedicated to the under-cabin space and their equipment makes it possible to recover the storage volume that is integrated into the furniture M1 and M2 arranged in lateral volumes. The volume of the sub-cabin space from which the technical bunkers have been removed (this volume is now homogeneous) is thus better arranged and therefore easier to equip than in the difficult-to-access areas and complex shapes of the art. prior. This architecture reduces the length of the links that are connected to furniture systems compared to the prior art and simplifies their arrangement since only sets of longitudinal system links (rectilinear) associated with taps are necessary. It follows a gain in terms of onboard weight, compactness and cost. The M1 and M2 furniture are all identical, their mounting methods are the same, which simplifies their installation in the under-cabin space and reduces the integration time.
    [0014] The furniture is able to integrate systems of different types (air, water, electricity) into standardized volumes, which gives them a certain flexibility of use. Simplified maintenance will also be noted since the access to the systems is done only by the under-cabin space which offers a large volume available for working (FIG 3) compared to the very small traditional technical bunkers. Industrialization is also simplified. The new arrangement of the under-cabin space allows for the removal of a large number of parts which were directly attached to the aircraft structure. It follows a gain in terms of onboard weight, compactness and cost. Furniture M1 and M2 which house identical systems and equipment for redundancy purposes are more particularly offset along the longitudinal axis so as not to be transversely opposite one another. Thus, in the event of an engine burst, the risks of damage to the two identical systems and equipment are greatly reduced. Such an arrangement does not complicate the arrangement of system links that remain straight.
    [0015] It will be noted that the spacing between the furniture and therefore between the systems housed in the furniture already offers an improved security since the redundant systems and equipment are distant from one another (segregation). In the architecture presented above, all the elements have been optimized in their shapes in order to obtain an optimal integration and a reduced bulk. According to a variant not shown, the two parallel lines of furniture assemblies and therefore of systems extend continuously from one end to the other of the under-cabin space without being interrupted to the right of connection of the wing to the fuselage as in the mode previously described. This arrangement is possible on aircraft in which the wing is connected in the upper position of the fuselage. 25
    权利要求:
    Claims (14)
    [0001]
    REVENDICATIONS1. Aircraft comprising a cabin space (34) dedicated to passengers and, below, an under-cabin space (30) extending along the longitudinal axis of said aircraft, characterized in that the under-cabin space (30) comprises , distributed along two lines parallel to the longitudinal axis of the aircraft, two sets of systems which are capable of performing functions necessary for the operation of the aircraft, the two sets of systems being arranged respectively in two lateral zones (Z1, Z2) of the sub-cabin space which are spaced transversely from one another and frame a free central zone (El) extending along the longitudinal axis (X) of the aircraft, suppressing as well as under-cabin space any technical area.
    [0002]
    2. Aircraft according to claim 1, characterized in that it comprises two sets of links (50a-c) which each extend along one of the two lines of sets of systems, in the part of the lateral zone (Z1, Z2) located between said systems of the overall line concerned and the adjacent wall of the fuselage and which comprise branches for their connection to said systems.
    [0003]
    3. Aircraft according to claim 1 or 2, characterized in that the two parallel lines of sets of systems each extend from one end to the other of the under-cabin space (30).
    [0004]
    4. Aircraft according to claim 3, characterized in that each of the two parallel lines is interrupted locally to the right of a portion of the under-cabin space (30) which is located at the wing (18) of the aircraft.
    [0005]
    5. Aircraft according to claim 3, characterized in that the two parallel lines of sets of systems extend continuously from one end to the other of the under-cabin space (30).
    [0006]
    6. Aircraft according to one of claims 1 to 5, characterized in that the systems of each of the two sets of systems are housed in furniture (M1, M2) distributed adjacent to each other along the line of the set of systems concerned. 3035072 14
    [0007]
    7. Aircraft according to claim 6, characterized in that at least some of the furniture (M1, M2) are identical.
    [0008]
    8. Aircraft according to claim 6 or 7, characterized in that each piece of furniture (M1, M2) has a front face (M12, M22) located opposite the free central zone (E1) and which, according to a cross-sectional view is inclined towards the free central area so that the upper end (M121, M221) of the front face is closer to said free central area than the lower end (M122, M222 ) recessed from said front face. 10
    [0009]
    9. Aircraft according to claim 8, characterized in that each piece of furniture (M1, M2) has an upper face (M14, M24) and a lower face (M15, M25) both adjacent to the front face of the furniture and shaped so to be as close as possible respectively to the ceiling (32) of the under-cabin space (30) and the adjacent wall of the fuselage. 15
    [0010]
    10. Aircraft according to claim 9, characterized in that each piece of furniture (M1, M2) has, in a cross-sectional view, a generally trapezoidal shape.
    [0011]
    11. Aircraft according to one of claims 1 to 10, characterized in that the free central zone (El) is delimited laterally by the two lines of sets of systems, at its upper part by the ceiling (32) of the under-cabin space and at its lower part by a floor (36) parallel to the ceiling.
    [0012]
    12. Aircraft according to claim 8 or 9 and claim 11, characterized in that the free central zone (E1) has, in a cross-sectional view, a polygonal shape formed by the union of two trapezoids (T1, T2 ) joined by their respective bases.
    [0013]
    13. Aircraft according to claim 12, characterized in that the under-cabin space (30) accommodates cargo containers (40) whose general cross-sectional shape corresponds to the general polygonal shape of the free central zone (El).
    [0014]
    14. Aircraft according to one of claims 1 to 13, characterized in that it comprises a front tip (12), a rear tip (14) and, in between, a central portion (16) which comprises the space cabin (34) dedicated to 3035072 15 passengers and, below, the under-cabin space (30), the central portion (16) having a cross section with constant geometry along its entire length. 5 10 15 20 25 30
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    同族专利:
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    DE102019132292B3|2019-11-28|2020-11-26|Telair International Gmbh|Structure-reinforcing cargo compartment module|
    法律状态:
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    优先权:
    申请号 | 申请日 | 专利标题
    FR1553495A|FR3035072B1|2015-04-20|2015-04-20|AIRCRAFT WITH IMPROVED UNDER CABIN SPACE ARCHITECTURE|FR1553495A| FR3035072B1|2015-04-20|2015-04-20|AIRCRAFT WITH IMPROVED UNDER CABIN SPACE ARCHITECTURE|
    CN201610246842.4A| CN106064667A|2015-04-20|2016-04-20|There is the aircraft of modified model hold structure|
    US15/133,745| US10124879B2|2015-04-20|2016-04-20|Aircraft having improved under-cabin space architecture|
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