• 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:
    To optimize the structure of an aircraft tail (17), there is provided an aircraft rear portion (12), comprising a fuselage section (16), a rear tip (17), and a vertical stabilizer (17). 15) having a box structure (18) which has an upper portion (34) extending out of the rear tip (17), and a lower portion (36) housed within the rear tip ( 17), and wherein the rear tip (17) is integrally supported by the box structure (18).
    公开号:FR3040686A1
    申请号:FR1558311
    申请日:2015-09-08
    公开日:2017-03-10
    发明作者:Guillaume Gallant；Munoz Jose Luis Martinez
    申请人:Airbus Operations SL；Airbus Operations SAS；
    IPC主号:
    专利说明:

    AIRCRAFT REAR PART COMPRISING A VERTICAL STABILIZER WHOSE STRUCTURE FORMING A BOX COMPRISES A LOWER PART LODGED IN THE
    FUSELAGE
    DESCRIPTION
    TECHNICAL AREA
    The present invention relates to the field of aircraft and relates more particularly to a rear part of aircraft and an aircraft comprising such a rear part of aircraft. In particular, the invention relates to a structural arrangement of an aircraft tail-tip and to a method of connecting a vertical stabilizer to the fuselage of the aircraft. The invention also relates to a method of assembling a rear part of an aircraft.
    STATE OF THE PRIOR ART
    In commercial aircraft with high or low wing types known, the vertical stabilizer, also called vertical tail, generally comprises a box structure which stops at the skin of the fuselage, in the upper part of the rear tip of the aircraft. At its lower end, the box structure of the vertical stabilizer is attached to the internal structure of the rear tip.
    The internal structure of the rear tip forms a primary structure, in the sense that this structure takes up the loads induced by the bending of the vertical stabilizer (in the form of shear forces and torsion), but also the loads induced by the auxiliary power unit. , also called APU (Auxiliary Power Unit), when it is installed in the rear tip, or the loads induced by the horizontal stabilizer, whether directly when the horizontal stabilizer is mounted on the fuselage or indirectly when the horizontal stabilizer is mounted on the vertical stabilizer.
    It is therefore desirable to optimize the structure of the rear tip.
    DISCLOSURE OF THE INVENTION The invention aims in particular to provide a simple, economical and effective solution to this problem.
    For this purpose, it proposes a rear part of an aircraft, comprising in particular a fuselage and a vertical stabilizer, and in which the fuselage is divided into a fuselage section located on a front side of the rear part of the aircraft and a rear tip. located on a rear side of the rear part of the aircraft, and wherein the vertical stabilizer comprises a box structure.
    According to the invention, the box structure comprises an upper part extending outside the rear tip, and a lower part housed inside the rear tip, and the rear tip is integrally supported by said structure forming caisson. The invention thus makes it possible to make the structure of the vertical stabilizer play a structural role within the fuselage. By structural role, one must understand the support of the empennage comprising the vertical stabilizer, but also the support of the rear tip. The connection of the rear tip to the fuselage section is thus fully ensured by the box structure belonging to the vertical stabilizer.
    The fuselage elements forming the rear tip can then be lightened, these elements can therefore no longer perform structural function.
    Preferably, the rear tip comprises at least one outer cover pivotally mounted on the box structure.
    Preferably, the rear portion further comprises an auxiliary power unit carried by the box structure.
    In a preferred embodiment of the invention, the fuselage section comprises at least a first anchor point arranged in an upper part of the fuselage section and at least a second anchor point arranged in a lower part of the section of the fuselage section. fuselage, and the lower portion of the box structure comprises at least a third anchor point connected to a corresponding first anchor point of the fuselage section, and at least a fourth anchor point connected to a second point of corresponding anchorage of the fuselage section.
    Preferably, the or each first anchor point is connected to the third corresponding anchor point by means of a traction bolt capable of transmitting longitudinal forces between the box structure and the fuselage section, and the or each second anchor point is connected to the fourth anchor point by means of a traction bolt adapted to transmit longitudinal forces between the box structure and the fuselage section.
    Preferably, the rear portion further comprises two lateral connecting rods respectively connecting two fifth anchor points, arranged on two opposite side portions of the fuselage section, to two sixth anchor points, respectively arranged on two opposite sides of a portion. rear of the lower part of the box structure, so that the two lateral rods participate in the lateral stabilization of the box structure with respect to the fuselage section.
    Preferably, the rear portion further comprises a sealed fuselage bottom mounted in the fuselage section and disposed in front of the box structure and at a distance therefrom.
    Preferably, the rear portion further comprises a horizontal stabilizer integrally supported by said box structure. The invention also relates to an aircraft, comprising an aircraft rear part of the type described above. The invention finally relates to a method of assembling an aircraft rear part, comprising the following steps: on the one hand, a step consisting in pre-assembling a fuselage section, and, on the other hand, a step of preassembling an aircraft rear assembly, the aircraft aft assembly comprising a vertical stabilizer having a box structure, and a rear tip attached to the box structure such that a lower portion of the box structure is housed at the inside of the rear tip while an upper portion of the box structure extends out of the rear tip, and then - a step of assembling the fuselage section to the rear aircraft assembly by fixing the lower part of the box structure to the fuselage section, so as to obtain an aircraft rear portion of the type described above.
    Preferably, the fuselage section comprises at least a first anchor point arranged in an upper part of the fuselage section and at least a second anchor point arranged in a lower part of the fuselage section, and the lower part of the fuselage section. box structure comprises at least a third anchor point and at least a fourth anchor point, and wherein the step of assembling the fuselage section to the aircraft rear assembly comprises a substep of connecting the or each first anchor point to a corresponding third anchor point and connecting the or each second anchor point to a corresponding fourth anchor point.
    Preferably, the step of preassembling the aircraft rear assembly comprises a substep of mounting at least one rotatable outer cover on the box structure.
    Preferably, the step of preassembling the aircraft rear assembly includes a substep of attaching an auxiliary power unit to the box structure.
    Preferably, the step of preassembling the aircraft rear assembly includes a substep of attaching a horizontal stabilizer to the box structure.
    BRIEF DESCRIPTION OF THE DRAWINGS The invention will be better understood, and other details, advantages and characteristics thereof will appear on reading the following description given by way of non-limiting example and with reference to the appended drawings in which: Figure 1 is a schematic side view of an aircraft according to a preferred embodiment of the invention; FIG. 2 is a partial schematic perspective view of a rear part of the aircraft of FIG. 1; - Figures 3 and 4 are partial schematic perspective views of the rear part of the aircraft of Figure 1; - Figures 5 and 6 are partial schematic views, respectively from the rear and from above, of the rear part of the aircraft of Figure 1; FIG. 7 is a partial schematic perspective view of a fuselage section belonging to the rear part of the aircraft of FIG. 1; FIG. 8 is a partial schematic perspective view of a rear assembly belonging to the aircraft of FIG. 1; Figure 9 is a partial schematic view from above of the rear portion of the aircraft of Figure 1; Figure 9a is an enlarged view of detail IXa of Figure 9; FIG. 10a is a partial schematic view from above of the rear part of the aircraft of FIG. 1; FIGS. 10b and 10c are partial schematic side views of the rear part of the aircraft of FIG. 1; FIG. 10d is a partial schematic view of the rear part of the aircraft of FIG. 1, viewed from the rear; - Figure 11 is a partial schematic side view of the rear part of the aircraft of Figure 1, illustrating a method of assembly thereof. DETAILED DESCRIPTION OF A PREFERRED EMBODIMENT
    FIG. 1 illustrates an aircraft 10 comprising a rear part of aircraft 12 according to a preferred embodiment of the invention.
    In the following description, X is called the longitudinal direction of the aircraft, Z is the vertical direction (thus defined when the aircraft is parked on a horizontal surface), and Y is the transverse direction, orthogonal to the two preceding directions.
    The rear part of aircraft 12 comprises in particular a fuselage 14 and a vertical stabilizer 15. In the terminology adopted in the present description, the fuselage 14 is divided into a fuselage section 16 on the front side of the aircraft and a rear tip 17 the rear side of the aircraft.
    In the illustrated example, the fuselage is formed of a skin, circumferential frames, and longitudinal or smooth stiffeners. These elements, which may be of a conventional type, are not visible in detail in the figures.
    The vertical stabilizer 15 comprises a box structure 18 (FIG. 2), as well as an aerodynamic fairing 20 and a rudder 22 (FIG. 1) mounted on the box structure 18. For the sake of clarity, the aerodynamic fairing 20 and the rudder 22 are not visible in Figures 2 to 10a.
    In the example shown, the vertical stabilizer 15 carries a horizontal stabilizer 23, visible only in Figure 1, provided with a elevator. The assembly formed by the vertical stabilizer 15 and the horizontal stabilizer 23 thus constitutes a T-shaped tail. In a manner known per se, the box structure 18 of the vertical stabilizer 15 is formed of two opposite side walls 24 (FIG. 2). , a front spar 26, a rear spar 28, an upper spar 30 and a lower spar 32, and internal stiffening ribs 33. It should be noted that each of these elements can be realized in one piece or in several parts assembled to each other.
    According to a feature of the present invention, as illustrated in Figures 2 to 4, the box structure 18 of the vertical stabilizer 15 has an upper portion 34 extending out of the rear tip 17 and a lower portion 36 housed inside the rear tip 17.
    The lower portion 36 of the box structure 18 of the vertical stabilizer 15 is connected to the fuselage section 16 in a manner which is described in detail in the following description.
    The rear part of aircraft 12 further comprises a sealed fuselage bottom 41, which is provided to form, in a manner known per se, the rear limit of a pressurized region of the aircraft, and which is situated in front of the structure forming caisson 18, so that the lower part 36 of this structure 18 is housed in an unpressurized part of the fuselage 14.
    In the illustrated example, as shown in Figure 2, the rear part of aircraft 12 comprises two outer caps 42 pivotally mounted on the box structure 18 of the vertical stabilizer 15, on either side of the latter. Each of these outer hoods 42 is movable between an open position (visible in FIG. 2) allowing access to the inside of the fuselage, and a closed position in which the outer hoods 42 form part of the aerodynamic profile of the fuselage. For this purpose, the box structure 18 comprises for example fittings arranged at the upper end of the lower portion 36 of the box structure 18 and on which the outer caps 42 are hinged, as will be clearer in this case. following.
    In the illustrated embodiment, the rear part of aircraft 12 also comprises an auxiliary power unit 44 or APU carried by the box structure 18 and housed within the rear tip 17 (Figure 4).
    More specifically, the box structure 18 of the vertical stabilizer 15 has an extension in the form of a box and extending rearwardly so as to form a support pole 46 to which the auxiliary power unit 44 is hung. support mast 46 is thus formed of two lateral walls 48 respectively consisting of extensions of the side walls 24 of the box structure 18, and an upper wall 50 and a lower wall 52 respectively consisting of extensions of two internal ribs of the box structure 18 (Figure 4).
    Alternatively, the mast of the auxiliary power unit 44 may consist of a structure attached to the box structure 18, for example by bolting.
    In the example illustrated, the support mast 46 further comprises support beams 54 which bear on the box structure 18, under the support mast 46.
    The aircraft rear tip 17 has a generally conical fuselage rear end portion 56 (FIG. 2) arranged around an exhaust duct 58 of the auxiliary power unit 44 (FIG. 4) and fixed on the support mast 46. The rear fuselage end portion 56 is thus indirectly carried by the box structure 18 of the vertical stabilizer 15.
    In a variant, the rear aircraft tip 17 may be devoid of pivoting outer covers and be entirely formed of a fixed skin, possibly stiffened by frames and / or heddles, without departing from the scope of the invention.
    FIGS. 5 and 6 illustrate the means for articulating the outer covers 42 on the box structure 18 and on the support pole extension 46. FIGS. 5 and 6 thus show a part of this support pole 46, on which is fixed a first fitting 46a having an end articulated to a second fitting 46b on which is fixed one of the outer covers 42 (not visible in Figures 5 and 6). The fixing of this outer cover 42 to the box structure 18 is carried out in a similar manner, as is the fixing of the other outer cover 42 to the box structure 18 and to the support pole extension 46.
    FIGS. 7 and 8 make it possible to see the connecting means which ensure the connection of the box structure 18 to the fuselage section 16. In general, these connecting means connect fuselage anchor points to points anchoring the box structure 18.
    More specifically, the fuselage section 16 comprises for example two first anchor points 62 arranged in an upper part 38 of the fuselage section 16 and two second anchor points 64 arranged in a lower part 40 of the fuselage section 16 (FIG. 7). The lower portion 36 of the box structure 18 comprises for example two third anchor points 66 located at its upper end, and two fourth anchor points 68 located at its lower end (Figure 8).
    The fuselage section 16 further comprises two fifth anchor points 70, arranged on two opposite lateral portions 71 of the fuselage (FIG. 7), and the lower portion 36 of the box structure 18 comprises two sixth anchor points 72, arranged respectively on two opposite sides of a rear portion of the lower portion 36 (only one of these sixth anchor points 72 is visible in Figure 8).
    The connecting means comprise, for example, traction bolts, preferably four in number, respectively connecting the first and second anchor points 62, 64 to the third and fourth anchor points 66, 68, so that the bolts of traction participate in particular the transmission of longitudinal forces between the box structure 18 and the fuselage section 16, as will become clearer in the following.
    FIGS. 9 and 9a illustrate in greater detail the method of fixing the box structure 18 to the fuselage section 16. FIG. 9 shows the fuselage section 16 and in particular makes it possible to see a circumferential frame 16a belonging to the fuselage section 16, and third fittings 75 respectively fixed on the two opposite side walls 24 of the box structure 18. The third fittings 75 each comprise a fixing head 75a fixed to the circumferential frame 16a by means of one of the aforementioned traction bolts , bearing the reference 74 in Figure 9a.
    The connecting means furthermore comprise two lateral connecting rods 76 (FIGS. 4 and 8) respectively connecting the fifth anchor points 70 to the sixth anchor points 72, so that the two lateral connecting rods participate in the lateral stabilization of the structure forming caisson 18 with respect to the fuselage section 16.
    The connecting means 74, 76 thus make it possible to ensure the transmission of all the forces between the box structure 18 and the fuselage section 16.
    In particular, the lateral rods 76 allow the recovery of the moment Mz in the vertical direction Z (Figure 10a). The traction bolts 74 are designed to work in traction and in shear, so that these traction bolts 74 allow the recovery of the vertical forces Fz (FIG. 10b), the recovery of the longitudinal forces Fx and the moment My in the transverse direction Y (Figure 10c), and the recovery of transverse forces Fy and moment Mx in the longitudinal direction X (Figure 10d).
    Moreover, the fuselage bottom 41 can be fixed directly to the front spar 26 of the box structure 18.
    Alternatively, as shown in Figures 4 and 7, the fuselage section 16 may be reinforced by one or more vertical beams 78, for example two in number, interposed between the sealed fuselage bottom 41 and the box structure 18 of in order to connect the upper part 38 of the fuselage section 16 to the lower part 40 of the fuselage section 16.
    In this case, the fuselage section 16 is advantageously reinforced by two transverse links 80 respectively connecting the vertical beams 78 to the two lateral portions 71 of the fuselage section 16.
    In the illustrated example, the first fittings 75 are arranged in the extension of second fittings 79 which respectively connect the circumferential frame 16a to the vertical beams 78 and to the fuselage bottom 41. In general, the invention thus proposes to play at the lower part 36 of the box structure 18 of the vertical stabilizer 15 the role of primary structure for the rear tip 17 of the aircraft 10. Unlike known aircraft in which the rear tip has a primary structure independent of the vertical stabilizer and in which the skin and the frames of the fuselage participate in the transmission of forces, the fuselage elements of the rear tip 17, such as the outer hoods 42 and the fuselage rear end portion 56, do not play no structural role in the aircraft 10 according to the invention. These fuselage elements are simply carried by the lower part 36 of the box structure 18 which connect them to the fuselage section 16. The invention thus makes it possible to reduce the bulk and weight of the rear tip 17. The invention allows in particular to avoid the use of a heavy and expensive fixing interface between the box structure 18 of the vertical stabilizer and a rear tip primary structure, as is the case in aircraft of known type. The invention also makes it possible to simplify the assembly of the rear part of aircraft 12.
    Indeed, this assembly can be achieved by means of a method comprising the following steps: on the one hand, a step of pre-assembling the fuselage section 16, and secondly, a step of pre-assembling an aircraft rear assembly 84 comprising the vertical stabilizer 15 and the rear tip 17, then a step of assembling the fuselage section 16 to the aircraft rear assembly 84 by attaching the lower portion 36 of the box structure to the fuselage section 16, for example by connecting the or each first anchor point 62 to a third corresponding anchor point 66 and connecting the or each second anchor point 64 to a fourth corresponding anchor point 68.
    In the illustrated example, the step of preassembling the aircraft rear assembly comprises a substep of articulating the connecting rods 76 at the sixth anchor points 72 on the box structure 18, and the step of assembling the fuselage section 16 to the aircraft rear assembly 84 comprises a substep of articulating the connecting rods 76 at the fifth anchor points 70 on the fuselage section 16.
    In the illustrated example, the step of preassembling the aircraft rear assembly includes a substep of mounting the outer hoods 42 in rotation on the box structure 18, as well as a substep of the auxiliary power unit 44 to the box structure 18.
    Figure 11 illustrates the mutual approximation of the fuselage section 16 and the rear aircraft assembly 84 (the latter being shown devoid of outer hoods 42), this mutual approximation being made before the mutual assembly of these elements.
    An advantage of this method is that it allows the aircraft rear assembly 84 to be preassembled, including in particular all the servitudes intended for the control surfaces of the tail tail unit and the auxiliary power unit, before the final assembly of the aircraft. the aircraft.
    权利要求:
    Claims (14)
    [1" id="c-fr-0001]
    An aircraft aft portion (12), comprising a fuselage (14) and a vertical stabilizer (15), wherein the fuselage (14) splits into a fuselage section (16) located on a front side of the fuselage (14). aircraft rear portion (12) and a rear tip (17) located on a rear side of the aircraft rear portion (12), and wherein the vertical stabilizer (15) has a box structure (18), characterized in that the box structure (18) has an upper portion (34) extending out of the rear tip (17), and a lower portion (36) housed within the rear tip ( 17), and in that the rear tip (17) is integrally supported by said box structure (18).
    [2" id="c-fr-0002]
    2. Aircraft rear portion according to claim 1, wherein the rear tip (17) comprises at least one outer cover (42) pivotally mounted on the box structure (18).
    [3" id="c-fr-0003]
    The aircraft rear portion of claim 1 or 2, further comprising an auxiliary power unit (44) carried by the box structure (18).
    [4" id="c-fr-0004]
    4. Aircraft rear part according to any one of claims 1 to 3, wherein - the fuselage section (16) comprises at least a first anchor point (62) arranged in an upper portion (38) of the section fuselage and at least one second anchor point (64) arranged in a lower portion (40) of the fuselage section; and - the lower portion (36) of the box structure (18) comprises at least a third anchor point (66) connected to a corresponding first anchor point (62) of the fuselage section, and at least a fourth anchor point (68) connected to a corresponding second anchor point (64) of the fuselage section.
    [5" id="c-fr-0005]
    The aircraft rear portion according to claim 4, wherein the or each first anchor point (62) is connected to the corresponding third anchor point (66) by means of a pull bolt (74) adapted to transmitting longitudinal forces (Fx) between the box structure (18) and the fuselage section (16), and the or each second anchor point (64) is connected to the corresponding fourth anchor point (68) by means of a traction bolt (74) capable of transmitting longitudinal forces (Fx) between the box structure and the fuselage section.
    [6" id="c-fr-0006]
    6. Aircraft rear part according to any one of claims 4 to 5, further comprising two lateral connecting rods (76) respectively connecting two fifth anchor points (70), arranged on two opposite side portions (71) of the section. fuselage (16), with two sixth anchor points (72), respectively arranged on two opposite sides of a rear portion of the lower portion (36) of the box structure (18), so that the two connecting rods lateral members (76) participate in the lateral stabilization of the box structure with respect to the fuselage section.
    [7" id="c-fr-0007]
    7. Aircraft rear part according to any one of claims 1 to 6, further comprising a sealed fuselage bottom (41) mounted in the fuselage section (16) and disposed in front of the box structure (18). and away from it.
    [8" id="c-fr-0008]
    An aircraft rear end according to any one of claims 1 to 7, further comprising a horizontal stabilizer (23) integrally supported by said box structure (18).
    [9" id="c-fr-0009]
    Aircraft (10), comprising an aircraft rear portion (12) according to any one of claims 1 to 8.
    [10" id="c-fr-0010]
    10. A method of assembling an aircraft rear portion (12), characterized in that it comprises the following steps: - on the one hand, a step of pre-assembling a fuselage section (16), and on the other hand, a step of pre-assembling an aircraft rear assembly (84), the aircraft rear assembly including a vertical stabilizer (15) having a box structure (18) and a rear tip (17) attached on the box structure (18) such that a lower portion (36) of the box structure is housed within the rear tip (17) while an upper portion (34) of the box structure (18) extends outwardly from the rear tip (17), then - a step of assembling the fuselage section (16) to the aircraft rear assembly (84) by attaching the lower portion (36) ) of the box structure to the fuselage section (16), so as to obtain an ar aircraft (12) according to any one of claims 1 to 8.
    [11" id="c-fr-0011]
    11. The method of claim 10, wherein the fuselage section (16) comprises at least a first anchor point (62) arranged in an upper portion (38) of the fuselage section (16) and at least a second point anchor (64) arranged in a lower portion (40) of the fuselage section, and the lower portion (36) of the box structure (18) comprises at least one third anchor point (66) and at least one fourth anchor point (68), and wherein the step of assembling the fuselage section (16) to the aircraft rear assembly (84) comprises a substep of connecting the or each first point of the anchoring (62) to a corresponding third anchor point (66) and connecting the or each second anchor point (64) to a corresponding fourth anchor point (68).
    [12" id="c-fr-0012]
    The method of claim 10 or 11, wherein the step of preassembling the aircraft rear assembly comprises a substep of mounting at least one outer cover (42) rotatably on the box structure (18). ).
    [13" id="c-fr-0013]
    The method of any one of claims 10 to 12, wherein the step of preassembling the aircraft tail assembly includes a substep of attaching an auxiliary power unit (44) to the box structure (18).
    [14" id="c-fr-0014]
    The method of any one of claims 10 to 13, wherein the step of preassembling the aircraft rear assembly comprises a substep of attaching a horizontal stabilizer (23) to the box structure (18). ).
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    同族专利:
    公开号 | 公开日
    FR3040686B1|2018-09-07|
    US20170066518A1|2017-03-09|
    引用文献:
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    法律状态:
    2016-09-21| PLFP| Fee payment|Year of fee payment: 2 |
    2017-03-10| PLSC| Publication of the preliminary search report|Effective date: 20170310 |
    2017-09-28| PLFP| Fee payment|Year of fee payment: 3 |
    2018-09-24| PLFP| Fee payment|Year of fee payment: 4 |
    2019-09-26| PLFP| Fee payment|Year of fee payment: 5 |
    2020-09-14| PLFP| Fee payment|Year of fee payment: 6 |
    2021-09-21| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1558311A|FR3040686B1|2015-09-08|2015-09-08|REAR AIRCRAFT PART COMPRISING A VERTICAL STABILIZER WHOSE STRUCTURE FORMING HOUSING INCLUDES A LOWER PART IN THE FUSELAGE|FR1558311A| FR3040686B1|2015-09-08|2015-09-08|REAR AIRCRAFT PART COMPRISING A VERTICAL STABILIZER WHOSE STRUCTURE FORMING HOUSING INCLUDES A LOWER PART IN THE FUSELAGE|
    US15/259,585| US20170066518A1|2015-09-08|2016-09-08|Aircraft rear portion comprising a vertical stabilizer having a box-section structure including a lower portion accommodated in the fuselage|
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