• 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 relates to an aircraft tail (16) comprising a fuselage in which avionic equipment is housed. The rear tip comprises two lateral hatches (26, 28) arranged in the fuselage, at least one hatch being arranged on each of the two opposite sides of the fuselage. Each hatch is removably mounted relative to the fuselage to occupy a first closed position in which the door closes a lateral opening of the fuselage and a second open position in which the open door allows access to the interior of the tip back through the corresponding opening. The avionics equipment (34a, 34b) requiring regular maintenance and / or inspection operations are housed in a part of the rear tip which is accessible through the two lateral openings (30, 32) of the fuselage by a person remaining at the outside of the fuselage.
    公开号:FR3032419A1
    申请号:FR1551014
    申请日:2015-02-09
    公开日:2016-08-12
    发明作者:Henning Scheel；Eric Bouchet；Julien Guillemaut；Esteban Martino-Gonzalez
    申请人:Airbus Operations GmbH；Airbus Operations SL；Airbus Operations SAS；
    IPC主号:
    专利说明:

    [0001] FIELD OF THE INVENTION The invention relates to an aircraft tail tip. BACKGROUND ART Most aircraft incorporate avionics equipment into their rear tip.
    [0002] This equipment includes, for example, the power supply systems for the control surfaces located in the empennage. On certain aircraft, the engines are arranged at the rear tip of these aircraft. The rear tip then incorporates additional equipment to those listed above, namely power supply systems for engines and auxiliary power units (APU), fuel systems (kerosene), hydraulic and electrical circuits, circuits air supplying the cabin with hot air that is taken from the engines and cooled, fire extinguishing systems and equipment (bottles with extinguishing agent) ...
    [0003] In the rear-drive type of aircraft, the rear tip is relatively longer than on aircraft with the engine under the wing in order to integrate all the equipment mentioned above. Generally, the rear spikes of aircraft (with rear engine and under wing motorization) are equipped, under the fuselage, an access hatch. Such a trap allows qualified operators to get inside the rear tip and perform maintenance and / or inspection on all or part of the avionics equipment present. For some equipment the operations must be carried out on a regular basis, for example before each flight or at regular intervals of time. However, the movement of the operators inside the rear tip is often difficult because of the space generated by the equipment and thus the small space left free for the circulation of 30 people. 3032419 2 The accessibility of the equipment of the rear tip to the operators for maintenance and / or inspection operations is therefore greatly reduced. As a result, the maintenance and / or inspection operations take time. Difficult access also increases the risk of equipment damage during maintenance operations. In view of the foregoing, it would therefore be useful to facilitate the maintenance and / or inspection of equipment housed in a rear tip of aircraft. SUMMARY OF THE INVENTION The subject of the present invention is thus an aircraft tail-tip comprising a fuselage inside which avionics equipment is housed, characterized in that the rear tip comprises at least two lateral hatches which are arranged in the fuselage, at least one side hatch being arranged on each of the two opposite sides of the fuselage on either side of the longitudinal axis of the aircraft, said at least two side hatches being each mounted detachably relative to the fuselage to occupy two positions, namely a first closed position in which each side door closes a lateral opening in the fuselage and a second open position in which each side door is open and allows access to the inside of the fuselage. the rear tip through the corresponding side opening, the avionics equipment that require operations maintenance and / or regular inspection being housed in a part of the rear tip which is accessible from the outside of the fuselage through the two lateral openings of the fuselage. Avionics equipment requiring regular maintenance and / or inspection is located in an area of the rear tip that is accessible to a person remaining outside the rear tip through each of the lateral openings in the fuselage.
    [0004] Most of these devices are thus arranged in an area located opposite the lateral openings or in an area adjacent to this zone and which remains easily accessible from at least one of the openings.
    [0005] According to other possible characteristics taken individually or in combination with each other: the aircraft rear tip comprises a flat pressurized partition and which transversely closes the upstream end of the rear tip; The flat transverse partition is provided with at least one access hatch which can occupy a closed position in which the hatch closes a partition opening made in the partition and an open position allowing access to the interior of the partition; a rear tip through said partition opening; The rear tip comprises one or more motors connected to its fuselage; two engines are connected to the fuselage on either side of it each via a mast; at least one side hatch is arranged on each side under the corresponding mast; said at least two lateral hatches are structurally reinforced; at least one of said at least two side hatches contributes to the transmission of forces in the fuselage; At least one side hatch participating in the transmission of forces in the fuselage comprises one or more panels which are each able to be opened and closed independently of one another; - The panel or panels are fixed on the fuselage removably; At least one side hatch participating in the transmission of forces in the fuselage comprises at least one flap of smaller size than that of said at least one side hatch and which is capable of occupying two positions, a first closed position in which said at least one shutter closes a so-called shutter opening which is formed in the side hatch and a second open position in which the at least one shutter is open and allows access to the inside of the rear tip through the opening shutter At least one of said at least two side hatches does not participate in the transmission of forces in the fuselage; at least one side door is slidably mounted relative to the fuselage; 5 -ladite at least one side door is mounted articulately via a hinge system (s) relative to the fuselage. The invention also relates to an aircraft, characterized in that it comprises an aircraft rear tip as briefly described above.
    [0006] BRIEF DESCRIPTION OF THE DRAWINGS 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 general schematic view one half of an aircraft; FIG. 2 is a general diagrammatic front view of the aircraft of FIG. 1; FIGS. 3a-c schematically illustrate an aircraft rear tip provided with lateral hatches according to a first embodiment of the invention; FIG. 4 represents in perspective the inside of the rear tip of the aircraft of FIG. 1 in a view of the side opposite to that illustrated in FIG. 1; FIG. 5 is a diagrammatic view from above showing, in a comparative manner, on one side, the rear tip of the aircraft of FIGS. 1 to 3c and, on the opposite side, the rear tip of FIG. an aircraft of the prior art; FIGS. 6a-b schematically illustrate an aircraft rear tip provided with lateral hatches according to a second embodiment of the invention; FIG. 7 is a schematic view of an aircraft rear tip according to an alternative embodiment of the embodiment of FIGS. 3a-c; FIGS. 8a-c schematically illustrate an aircraft rear tip provided with lateral hatches on the pressurized flat partition according to a third embodiment of the invention; FIGS. 9a-c schematically illustrate an aircraft tail 5 provided on each side with a sliding side hatch according to a fourth embodiment of the invention. DETAILED DESCRIPTION As shown in FIG. 1, only one half of an aircraft 10 according to a first embodiment of the invention is shown. The other half not shown is obtained by symmetry with respect to the axial vertical plane which comprises the longitudinal axis X of the aircraft. The aircraft comprises a fuselage 12, a central wing 14 connected to the fuselage and a rear tip 16. The rear tip 16 comprises the rear part of the fuselage 18, a rear engine 20 connected to the rear part of the fuselage 18 and a stabilizer 22 The rear engine comprises here a motor, for example with counter-rotating propellers, connected to the rear tip 16 by a mast 24a fixed to the side of the rear tip shown in Figure 1. In Figure 2 are shown the two wings 14a, 14b of the wing 20 and the two motors 20a, 20b respectively connected to the rear tip 16 by a mast 24a, 24b. Only one of the two opposite sides of the fuselage is shown in Figures 3a-b which further illustrate the first embodiment: it is the opposite side to that shown in Figure 1. The following description relates to this side of the aircraft but is identical for the other side which is symmetrical with respect to the vertical plane containing the longitudinal axis X. As shown in Figure 3a, the rear tip is delimited in its front portion by a pressurized partition 25 separating the inside the unpressurized rear tip of the fuselage cabin pressurized interior. The rear end comprises, arranged on the same side of the fuselage, two side hatches 26, 28. Each side door 26, 28 is removably mounted relative to the fuselage so as to occupy at least two positions: first closed position (FIG. 3a) in which each lateral trap 26, 28 closes a lateral opening made in the fuselage, and a second open position in which each lateral trapdoor 26, 28 is open and allows access to the inside of the fuselage; the rear tip through the corresponding respective lateral opening 30, 32. In this example, the side openings and the side hatches have identical shapes and substantially corresponding dimensions. However, the shapes and dimensions of the openings and hatches may not match. Thus, for example, one and / or the other hatch may be larger than those of the corresponding opening. The side hatch 28 is located under the mast 24b (fig.2) and the other symmetrical side hatch 28 'is located under the mast 24a (fig.3c). In this first mode, the side hatches are slidably mounted relative to the fuselage in the known manner of the side doors of a helicopter and open, as for the latter, towards the rear. Note that the system of fixing these hatches on the fuselage is much simpler than that of a passenger door of an aircraft because, here, it is not a pressurized area. The structure and mounting of these hatches will be explained in more detail with reference to the fourth embodiment illustrated in Figs. 9a-c. The sliding mounted side hatches 26, 28 are "non-working", that is to say they do not participate in the transmission of forces in the fuselage. These traps are used when maintenance and / or inspection operations are frequent.
    [0007] The interior of the rear tip houses avionic equipment such as engine power systems and auxiliary power units (APU), fuel systems (kerosene), hydraulic and electrical circuits, air conditioning equipment air and air circuits conveying to the cabin the hot air that is taken from the engines and cooled, fire extinguishing systems and equipment (bottles with extinguishing agent), control water supply systems located in the empennage, calculators, measurement systems (for example: the black boxes of the apparatus, but also other types of sensors 3032419 7 for making possible measurements in flight), cooling circuits of different fluids (oil, fuel), oil / fuel filters, fuel flow measurement systems, all kinds of valves to control the flow rates of these fluids ...
    [0008] As shown in FIG. 4, an assembly 34 formed of at least some of these avionics equipment is provided in a portion of the rear tip 16 at or near which the engine masts 24a, 24b are attached and level of which are provided the side hatches 26, 28, 26 ', 28'.
    [0009] FIG. 3b shows that, when the side hatches 26, 28 are open, the physical access from the outside of the aircraft to the equipment or to the plurality of equipment 34a, 34b located opposite the openings 30, 32 is possible for persons in charge of maintenance and / or inspection operations such as, for example, that of FIG. 3c mounted on a lifting platform 38. These persons therefore no longer need to penetrate completely. inside the rear tip and travel there to perform these operations. These people can simply engage their bust inside the back tip for their intervention. A person may also physically access the equipment that is located around the equipment located opposite the openings 30, 32 and within arm's reach when that person is partially engaged within the corresponding opening. Hoses and various wiring connecting these devices are not necessarily located behind the side hatches.
    [0010] Avionic equipment that requires maintenance and / or regular inspection is thus housed in a portion of the rear tip that is accessible from outside the fuselage through the four lateral fuselage openings. By thus arranging the avionics equipment in this part of the rear tip, it is no longer necessary to provide, as in the prior art, an internal space in the rear tip for the circulation of maintenance personnel and / or inspection. In the prior art, the avionics equipment in question were also not grouped in this part of the rear tip and even sometimes were scattered within the rear tip. As a result, the internal and therefore external dimensions of the new rear tip can be reduced. FIG. 5 illustrates, artificially combined on the same view from above, at the bottom, a rear tip A of an aircraft according to the prior art and, at the top, a rear tip B of an aircraft according to the embodiment of FIG. FIG. 1 to 4. This comparative view shows that the rear tip B is shorter and less wide (transverse dimension perpendicular to the longitudinal axis X) than the rear tip A of the prior art. The shape and dimensions of the side hatches and their apertures, as well as their number and location, are suitably chosen for rear-end avionics equipment, their dimensions and their position inside the fuselage. Thus, the openings 15 are especially dimensioned to allow the passage of equipment to extract from the rear tip or to introduce into it. It should be noted that the side hatches are structurally reinforced in a known manner so as to act as removable protective shields for the internal avionic equipment at the rear tip in the event of accidental loss of the rotor blade (s) of each engine. The equipment behind these shields are therefore protected, which limits the systematic use of redundancy for all equipment fitted to the rear tip. An on-board weight gain can thus be obtained. For example, the reinforced hatches are made of the same material (eg aluminum, titanium) as that of the fuselage but with a greater thickness (eg 5 to 15 mm, in particular 10 mm) than that of the fuselage (ex: 1 at 3mm). The choice of the thickness is made according to the dimensions and the energy of the engine fragments to stop. Alternatively, the material of the reinforced hatches may be based on carbon fibers or Kevlar.
    [0011] In FIGS. 3a-b, the lateral hatches 26 and 28 are located at different sides, the upstream hatch 28 being lower than the downstream hatch 26. The opening 30 is rectangular but with a small length / width ratio in order to providing a section covering equipment or equipment 34a which extends over a rectangular surface with a small length / width ratio. The aperture 32, in turn, has a rectangular shape with a larger length / width ratio and a length vertically arranged to accommodate the elongated shape of the equipment 34b.
    [0012] It should be noted that the presence of several lateral hatches allows simultaneous intervention on internal avionic equipment at the rear tip via all (intervention time saving) or only some of these traps. According to a variant not shown, the side hatches slide forward to open, which provides additional security vis-à-vis a possible inadvertent opening in flight. However, the choice to open the hatches backwards or forwards depends in particular on the number and positioning of all the hatches (positioning of a hatch relative to the others but also with respect to the structure of the hatch. mast for supporting engines). Figures 6a-b illustrate a second embodiment of a rear tip 46 provided with two side hatches 48, 50 on each side of the fuselage as for the mode of Figures 3a-c. The shapes and dimensions of these traps and their locations are identical to those of the traps of the mode of FIGS. 3a-c. The characteristics described with reference to FIGS. 1, 2 and 4 apply to the mode of FIGS. 6a-b. In this mode the side hatches 48, 50 are mounted each hinged to the fuselage via a hinge system (s) 52, 54 of the type used for aircraft nacelle cowlings.
    [0013] The opening of the lateral hatches 48, 50 releases respective corresponding lateral openings 56, 58 whose characteristics are identical to those of the mode of FIGS. 3a-c. The articulated mounted lateral hatches 48, 50 are "non-working", that is to say they do not participate in the transmission of forces in the fuselage. These traps are used when maintenance and / or inspection operations are frequent. The downward positioning of the upstream hatches 50 and 50 'with respect to the downstream hatch 48 and the symmetrical downstream hatch (not visible in the figures) 3032419 10 allows their opening from the top while they are each located under the corresponding engine mast 24b, 24a (Fig. 6b). A person 60 mounted on a platform 62 can easily access the corresponding opening. The raised positioning of the downstream traps 48 and 48 'with respect to the 5 upstream traps 50 and 50' and outside the zone located directly above the corresponding engine pylon 24b, 24a makes it possible to open these downstream traps from the top without risk. to interfere with the mast (Fig. 6b). A person 64 mounted on a platform 66 can easily access the corresponding opening. According to an alternative embodiment shown in Figure 7, the side hatches 10 of the rear tip 70 are "working", that is to say they participate in the transmission of forces in the fuselage. As for the embodiments of the preceding figures, the rear tip comprises two lateral hatches 72, 74 on each side of the fuselage downstream of the pressurized plane partition 76.
    [0014] Each side door may be formed of a single removable panel or of several removable panels adjacent to each other and which are each able to be opened and closed independently of one another. In the example of FIG. 7 each side hatch comprises a single panel removably mounted on the outer face of the fuselage, for example, via bolts. When necessary each panel is disassembled and removed in a simple manner, without resorting to complex tools, to clear the opening it closes (when mounted as shown in Figure 7) and which has substantially same dimensions as the panel. This provides access to the avionics equipment located behind the panel considered (as the equipment 34a and 34b of Figure 3b). When the maintenance and / or inspection tasks of avionics equipment prove to be more regular (for example, at each flight) disassembly and reassembly of the removable panel (s) is undesirable. Also, each side hatch comprises one or more shutters or "non-working" secondary hatches each having a size smaller than that of the main hatch or the panel which constitutes it.
    [0015] In FIG. 7 there are two flaps 72a-b, 74a-b per trapdoor / respective panel 72, 74. Each flap is capable of occupying two positions, a first closed position in which the flap closes a flap opening which is made in the side hatch / panel and a second open position in which the flap is open and allows access to the inside of the rear tip through the flap opening. In Figure 7, the flaps are slidably mounted on the hatch / panel and are shown in dashed in the open position.
    [0016] These small sized shutters allow, without the need to disassemble and remove the corresponding hatch / panel, to view and access certain equipment arranged behind said hatch and which require interventions and / or frequent inspections such as each flight.
    [0017] Lateral doors 72, 74 working in a structural manner make it possible to achieve an onboard weight saving compared to non-structural side hatches for which the fuselage needs to be significantly reinforced around the hatches, in the same manner as for a passenger or cargo door.
    [0018] In order to simplify disassembly and reassembly of the side hatches in case of intervention, it is preferable to make each hatch in the form of several removable / dismountable panels, each of smaller size, which will be easier to handle individually. In addition, it is conceivable to remove only the panel or panels required for the intervention and not, systematically, all the panels. In FIG. 7, by way of example, four removable lateral panels P1 to P4 have been represented for the side hatch 72. As for the embodiments of FIGS. 1 to 6b, the number and / or the positioning and / or the size of the Side hatches may vary. For example, only one side hatch or more than two side hatches on each side of the rear tip may be considered. Note that the size, number and position of the flaps may vary depending on the arrangement of the equipment located behind. the hatch concerned, their number and size. FIGS. 8a-c illustrate another embodiment of a rear tip 80 in which the pressurized plane partition 82 closing transversely the upstream end of the rear tip is provided with two access hatches 84, 86. Each trapdoor can occupying a closed position in which the hatch closes a partition opening in the partition and an open position for accessing the interior of the rear tip through said partition opening. In this example each hatch 84, 86 is slidably mounted on the partition with a closed high position (Fig.8b) and a low open position clearing a partition opening 88, 90 (Fig.8c).
    [0019] A person 92 in front of the partition 82 and in charge of maintenance and / or inspection operations (FIG 8a) can thus intervene through one and / or the other of the partition openings 88, 90 on the or the avionic equipment 84a, 84b accessible through the opening concerned (FIG 8c). The partition 82 thus equipped may be part of the rear peaks of the modes of FIGS. 3a-c, 6a-b and 7 in order to allow better access to rear tip avionics (in addition to the side hatches) and thus optimize their internal arrangement. to reduce the volume of the rear tip. In addition, the accessibility to the avionics equipment of the rear tip is thus greater since it is permitted on three sides. However, it will be noted that with the partition 82 provided with the hatches 84, 86 it is possible to be content with a single side hatch on each side of the aircraft instead of two as in FIGS. 3a-c, 6a-b and 7. It should be noted that the presence of additional access hatches in the planar partition makes it possible to reduce the dimensions of the side hatches located on both sides of the fuselage. The embodiment of FIGS. 9a-c illustrates an aircraft rear tip 100 equipped on each side of the fuselage 102 with a lateral hatch 104 mounted sliding on the fuselage by opening rearwardly (the principle 3032419 13 is the even if the hatch opens to the front). The hatch 104 is slidably mounted on two parallel rails: an upper rail 106a and a lower rail 106b respectively fixed at the upper edge and the lower edge of an opening 108 formed in the fuselage (along these edges). Aircraft equipment 110 housed opposite aperture 108 is accessible from outside thereof when the trapper is in the open position (FIG. 9a). The panel forming the hatch 104 is equipped with locking pins 112, for example four, which engage (in the closed position of the hatch in FIG. 9b) in holes or locking holes 114 (four in number). in correspondence with the pins, only two holes are shown in Figure 9a, the other two being masked by the panel) to fix the panel in the closed position. The holes 114 are arranged in structural uprights 116, 118 disposed respectively along the two lateral edges of the opening (rear edges 116 and before 118 in FIGS. 9a and 9b), adjacent to the upper and lower edges of that -this. Aerodynamic top covers 120 and bottom 122 respectively extend from the upper and lower edges of the panel 104 by joining the fuselage to reduce stray drag produced by the outcrops of the sliding panel at rails 106a and 106b. FIG. 9c illustrates this arrangement according to a view taken from the rear of the aircraft and shows the curved shape of the panel 104. Other aerodynamic cowls (not shown in the figures) are also mounted on the adjacent rear and front edges of the aircraft. panel 104 to reduce the parasitic drag produced by the outcrops of the sliding panel at the rear uprights 116 and before 118 and the locking pins 112. According to a variant not shown, one of the two side hatches of FIGS. 3a-c and 6a-b is configured to participate in the transmission of forces in the fuselage, as for the variant of Figure 7.
    [0020] According to another variant not shown, one of the two side hatches of FIGS. 3a-c and 6a-b is slidably mounted (for example, the one located under the mast) while the other (for example, the one situated next to the mast) mast) is pivotally mounted via a hinge system (s).
    [0021] 3032419 14 This mounting difference makes it possible to modify the positioning, in particular in height, of the hatches. It will be appreciated that the number of hatches shown in the various embodiments may vary, especially be increased or decreased depending on the applications. Although the side hatches and the (optional) flaps of the plane pressurized partition have been described in connection with a rear tip of a rear-powered aircraft, any type of aircraft can be equipped. Any type of aircraft engine is concerned, namely a turboprop, a turbojet, a non-keeled counter-rotating propeller engine.
    权利要求:
    Claims (15)
    [0001]
    REVENDICATIONS1. An aircraft tail (16; 70; 80) comprising a fuselage (12) inside which avionics equipment is housed, characterized in that the rear tip comprises at least two side hatches (26,28; 72,74). ) which are arranged in the fuselage, at least one side hatch being arranged on each of the two opposite sides of the fuselage on either side of the longitudinal axis (X) of the aircraft, said at least two side hatches being mounted each in a removable manner relative to the fuselage to occupy two positions, namely a first closed position in which each side door (26, 28; 72, 74) closes a lateral opening (30, 32) made in the fuselage and a second open position in which each side hatch (26, 28; 72, 74) is open and allows access to the interior of the rear tip through the corresponding lateral opening, the avionics equipment (34a, 34b) which requires maintenance and / or regular inspection operations being housed in a part of the rear tip which is accessible from outside the fuselage through the two lateral openings (30, 32) of the fuselage.
    [0002]
    2. Aircraft rear end according to claim 1, characterized in that it comprises a pressurized plane partition (25; 76; 82) and which transversely closes the upstream end of the rear tip (16).
    [0003]
    3. A rear end according to claim 2, characterized in that the transverse planar partition (82) is provided with at least one access door (84, 86) which can occupy a closed position in which the door closes an opening of partition (88, 90) formed in the partition and an open position for accessing the interior of the rear tip through said partition opening.
    [0004]
    4. A rear tip according to one of claims 1 to 3, characterized in that the rear tip comprises one or more motors (20a, 20b) connected to its fuselage.
    [0005]
    5. Rear tip according to claim 4, characterized in that two motors (20a, 20b) are connected to the fuselage on either side thereof each via a mast (24a, 24b). 3032419 16
    [0006]
    6. A rear end according to claim 5, characterized in that at least one side door (28, 28 ') is arranged on each side under the corresponding mast (24b, 24a).
    [0007]
    7. A rear end according to one of claims 1 to 6, characterized in that said at least two side hatches are structurally reinforced.
    [0008]
    8. A rear end according to one of claims 1 to 7, characterized in that at least one of said at least two lateral doors (72, 74) participates in the transmission of forces in the fuselage. 10
    [0009]
    9. A rear end according to claim 8, characterized in that said at least one lateral door (72, 74) participating in the transmission of forces in the fuselage comprises one or more panels (P1-P4) which are each able to be opened. and closed independently of each other. 15
    [0010]
    10. A rear tip according to claim 9, characterized in that the panel or panels (P1-P4) are fixed on the fuselage removably.
    [0011]
    11. A rear end according to one of claims 8 to 10, characterized in that said at least one side door (72, 74) participating in the transmission of forces in the fuselage comprises at least one flap (72a-b, 74a). -b) of smaller size than that of said at least one side hatch and which is able to occupy two positions, a first closed position in which said at least one shutter closes a so-called shutter opening which is made in the side hatch and a second open position wherein said at least one flap is open and allows access to the interior of the rear tip through the flap opening.
    [0012]
    12. A rear end according to one of claims 1 to 7, characterized in that at least one of said at least two lateral doors (26, 28; 48, 50) does not participate in the transmission of forces in the fuselage.
    [0013]
    13. A rear end according to claim 12, characterized in that said at least one side door (26, 28) is slidably mounted relative to the fuselage. 3032419 17
    [0014]
    14. A rear tip according to claim 12, characterized in that said at least one side door (48, 50) is hingedly mounted via a hinge system (s) relative to the fuselage.
    [0015]
    15. Aircraft, characterized in that it comprises a rear tip (16; 70; 80) according to one of claims 1 to 14.
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    同族专利:
    公开号 | 公开日
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    引用文献:
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    法律状态:
    2016-02-18| PLFP| Fee payment|Year of fee payment: 2 |
    2016-08-12| PLSC| Publication of the preliminary search report|Effective date: 20160812 |
    2017-02-17| PLFP| Fee payment|Year of fee payment: 3 |
    2018-02-23| PLFP| Fee payment|Year of fee payment: 4 |
    2020-02-19| PLFP| Fee payment|Year of fee payment: 6 |
    2021-02-24| PLFP| Fee payment|Year of fee payment: 7 |
    2022-02-16| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1551014|2015-02-09|
    FR1551014A|FR3032419B1|2015-02-09|2015-02-09|REAR AIRCRAFT TIP|FR1551014A| FR3032419B1|2015-02-09|2015-02-09|REAR AIRCRAFT TIP|
    US15/018,481| US20160229513A1|2015-02-09|2016-02-08|Aircraft tail cone|
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