Aircraft tail

Abstract

According to the aircraft tail, a tail cone can be conveniently assembled and disassembled relative to a rear fuselage, and the assembling and disassembling time is saved. The aircraft tail comprises a rear fuselage and a tail cone assembled on the rear fuselage along the course, the aircraft tail comprises a positioning mechanism, the positioning mechanism comprises a clamping piece and a receiving piece allowing the clamping piece to be inserted along the course, the clamping piece is arranged on any one of the rear fuselage and the tail cone, and the receiving piece is arranged on the other one of the rear fuselage and the tail cone; the clamping piece is limited to move in a plane crossed with the course; the locking and unlocking mechanism comprises a stopping piece and a locking piece, the stopping piece is arranged on any one of the rear fuselage and the tail cone, the locking piece is arranged on the other one of the rear fuselage and the tail cone and can be switched between a first position and a second position, and the locking piece is arranged on the other one of the rear fuselage and the tail cone at the first position. At the first position, the locking piece is locked with the stop piece to prevent the tail cone from being separated relative to the rear fuselage in the heading direction, and at the second position, the locking piece is unlocked from the stop piece to allow the tail cone to be separated relative to the rear fuselage in the heading direction.

Description

Technical Field

[0001] The invention relates to a tail of an aircraft, and in particular to a connection structure between a tail cone and a rear fuselage. Background Art

[0002] The tail of a civil aircraft usually includes a rear fuselage and a tail cone. The tail cone is assembled on the rear fuselage along the heading direction and the APU exhaust system is wrapped inside.

[0003] In the past, in order to connect the tail cone to the rear fuselage, the tail cone was sometimes sleeved on the rear fuselage, and a number of fasteners connecting the tail cone and the rear fuselage were arranged in the circumferential direction around the axis extending along the heading.

[0004] When the above-mentioned connection structure is adopted, since the docking interface between the tail cone and the rear fuselage is a curved surface, the shape control accuracy is required to be high, and the docking curved surface may not fit well. For example, there is a certain gap when the tail cone is sleeved on the docking frame or strip plate of the rear fuselage. During assembly, it is necessary to cut process gaskets of different thicknesses according to the size of the gap to fill the gap. If the gasket has detached during route maintenance, it is necessary to re-pad it. In addition, the installation and removal of numerous fasteners also takes a lot of operating time, making it difficult to achieve simple interchangeability.

[0005] In addition, in order to connect the tail cone and the rear fuselage, multiple lug joints are sometimes arranged on the rear fuselage and the tail cone, each lug joint includes a rear fuselage ear piece and a tail cone ear piece, the rear fuselage ear piece protrudes toward the rear side from the rear end surface of the rear fuselage, and the tail cone ear piece protrudes toward the front side from the front end surface of the tail cone, and is connected to the rear fuselage ear piece via bolts.

[0006] When the above connection structure is adopted, since a plurality of bolt connection operations are required, the assembly time of the tail cone relative to the rear fuselage tends to be prolonged, and accordingly, the disassembly time of the tail cone relative to the rear fuselage tends to be prolonged.

[0007] In addition, when the above connection structure is adopted, if the bolts are installed from the inside, a large internal operating space is required. Therefore, for a tail cone with limited internal operating space, the lug joint cannot be used to butt-connect the tail cone and the rear fuselage. On the other hand, if the bolts are installed from the outside, a maintenance cover is usually required on the skin of the tail of the civil aircraft to cover the bolts. Therefore, when disassembling or installing the tail cone, the cover needs to be opened first, and then the rear fuselage ear piece and the tail cone ear piece are connected or disassembled by bolts, which is a cumbersome process. Summary of the invention

[0008] The object of the present invention is to provide an aircraft tail part, which is convenient for assembling and disassembling the tail cone relative to the rear fuselage and saves assembly and disassembly time.

[0009] In order to achieve the above-mentioned purpose, the present invention provides a tail of an aircraft, including a rear fuselage and a tail cone assembled on the rear fuselage along a heading, wherein the positioning mechanism includes: a positioning mechanism, the positioning mechanism includes a locking member and a receiving member for the locking member to be inserted along the heading, the locking member is provided on any one of the rear fuselage and the tail cone, the receiving member is provided on any other of the rear fuselage and the tail cone, and limits the movement of the locking member in a plane intersecting the heading; and a locking and unlocking mechanism, the locking and unlocking mechanism includes a stop member and a locking member, the stop member is provided on any one of the rear fuselage and the tail cone, the locking member is provided on any other of the rear fuselage and the tail cone, and can be switched between a first position and a second position, in the first position, the locking member is locked with the stop member to prohibit the tail cone from separating relative to the rear fuselage along the heading, and in the second position, the locking member is released from the lock with the stop member to allow the tail cone to separate relative to the rear fuselage along the heading.

[0010] According to the tail of the aircraft of the present invention, with the aid of a positioning mechanism, the tail cone can be conveniently and quickly positioned relative to the rear fuselage in a plane perpendicular to the heading, and with the aid of a locking and unlocking mechanism, the tail cone can be conveniently connected to the rear fuselage or the connection between the tail cone and the rear fuselage can be released, thereby making it convenient to install and disassemble the tail cone relative to the rear fuselage, saving installation and disassembly time.

[0011] Furthermore, in the aircraft tail portion of the present invention, it is preferred that an outer peripheral surface of a front end of the tail cone and an outer peripheral surface of a rear end of the rear fuselage are offset in heading direction.

[0012] According to the tail of the aircraft of the present invention, the outer circumference of the front end of the tail cone and the outer circumference of the rear end of the rear fuselage do not overlap in heading. Therefore, compared with the case where the tail cone is sleeved on the rear fuselage, the shape control accuracy requirement is lower and the interchangeability function can be easily realized.

[0013] Furthermore, in the aircraft tail portion of the present invention, it is preferred that the positioning mechanism is provided near an outer surface of the aircraft tail portion.

[0014] According to the tail of the aircraft of the present invention, the locking member and the receiving member are easy to observe, and when the rear fuselage and the tail cone are assembled, it is easy to align the locking member with respect to the receiving member.

[0015] Furthermore, in the aircraft tail portion of the present invention, it is preferred that a plurality of the positioning mechanisms are provided in a circumferential direction around the axis extending along the heading direction.

[0016] Furthermore, in the tail portion of the aircraft of the present invention, it is preferred that the front end of the locking member is chamfered, and / or the rear end of the passage of the receiving member into which the locking member is inserted is formed in a flared shape.

[0017] According to the tail of the aircraft of the present invention, the fixing part can be easily inserted into the receiving part by means of the guiding effect of the chamfering and the flaring, thereby further improving the assembly efficiency of the tail cone relative to the rear fuselage.

[0018] Furthermore, in the aircraft tail portion of the present invention, it is preferred that the receiving member is formed integrally with the other of the rear fuselage and the tail cone.

[0019] The aircraft tail according to the present invention can reduce the number of parts and further simplify the assembly process.

[0020] Furthermore, in the aircraft tail of the present invention, it is preferred that the locking member constitutes a part of an outer surface of the aircraft tail.

[0021] According to the tail of the aircraft of the present invention, the connection or disconnection of the tail cone relative to the rear fuselage can be achieved on the outside of the aircraft without performing internal operations.

[0022] Furthermore, in the aircraft tail portion of the present invention, it is preferred that a plurality of the locking and unlocking mechanisms are provided in a circumferential direction around an axis extending along the heading direction.

[0023] Furthermore, in the tail of the aircraft of the present invention, the locking member is preferably rotatable between the first position and the second position about an axis intersecting the heading and has a hook, and the stop member has a stop pin extending along the axis and for the hook to hook.

[0024] According to the aircraft tail of the present invention, the locking element can be conveniently switched between the first position and the second position.

[0025] Furthermore, in the aircraft tail portion of the present invention, it is preferred that the locking member and the stopper are formed as one piece.

[0026] The aircraft tail according to the present invention can reduce the number of parts and further simplify the assembly process.

[0027] In addition, in the tail portion of the aircraft of the present invention, the tail cone preferably has a front end face of the tail cone which is a plane, and the rear fuselage has a rear end face of the rear fuselage which is a plane, the front end face of the tail cone and the rear end face of the rear fuselage are opposite to each other in heading, and a sealing ring is arranged in a compressed state between the front end face of the tail cone and the rear end face of the rear fuselage.

[0028] According to the tail of the aircraft of the present invention, the butt joint surface between the tail cone and the rear fuselage is a plane, which makes it easy to ensure the manufacturing and assembly accuracy and realize the interchangeability function. In addition, with the help of the sealing ring, it can play a sealing and vibration reduction role.

[0029] In addition, in the tail portion of the aircraft of the present invention, preferably, the tail cone has a front end frame, the front end frame has a front end surface of the tail cone perpendicular to the heading, the rear fuselage has a rear end frame, the rear end frame has a rear end surface of the rear fuselage perpendicular to the heading, the locking member is a locking pin provided on one of the front end surface of the tail cone and the rear end surface of the rear fuselage, the receiving member is a locking groove provided on the other of the front end surface of the tail cone and the rear end surface of the rear fuselage, and the sealing ring has a through hole for the locking member to pass through along the heading.

[0030] According to the tail of the aircraft of the present invention, even if a longitudinal member is provided in the tail cone, the longitudinal member can be extended to the front end frame to avoid a sudden change in stiffness.

[0031] (Effects of the Invention)

[0032] According to the present invention, it includes a positioning mechanism and a locking and unlocking mechanism, the positioning mechanism includes a locking member and a receiving member for the locking member to be inserted along the heading, the locking member is arranged on either one of the rear fuselage and the tail cone, and the receiving member is arranged on either the other of the rear fuselage and the tail cone, the locking and unlocking mechanism includes a stopper and a locking member, the stopper is arranged on either one of the rear fuselage and the tail cone, the locking member is arranged on either the other of the rear fuselage and the tail cone, and can be switched between a first position and a second position, in the first position, the locking member is locked with the stopper to prohibit the tail cone from being separated relative to the rear fuselage along the heading, in the second position, the locking member is released from the lock with the stopper to allow the tail cone to be separated relative to the rear fuselage along the heading, therefore, with the aid of the positioning mechanism, the tail cone can be conveniently and quickly positioned relative to the rear fuselage in a plane perpendicular to the heading, and with the aid of the locking and unlocking mechanism, the tail cone can be conveniently connected to the rear fuselage or the connection between the tail cone and the rear fuselage can be released, thereby, the tail cone can be conveniently assembled and disassembled relative to the rear fuselage, saving assembly and disassembly time. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1A It is a perspective view schematically showing the tail portion of the aircraft according to the first embodiment of the present invention, and shows a state before assembly.

[0034] Figure 1B It is a perspective view schematically showing the tail portion of the aircraft according to the first embodiment of the present invention, and shows a state after assembly.

[0035] Figure 2 It is a partial side sectional view schematically showing the assembly process of the tail portion of the aircraft according to the first embodiment of the present invention, and shows the state before the locking member is inserted into the receiving member.

[0036] Figure 3 It is another partial side sectional view schematically showing the assembly process of the tail of the aircraft according to the first embodiment of the present invention, and shows the state after the locking member is inserted into the receiving member.

[0037] Figure 4A It is a side view schematically showing the locking and unlocking mechanism of the tail portion of the aircraft according to the first embodiment of the present invention, and shows the unlocked state.

[0038] Figure 4B It is a side view schematically showing the locking and unlocking mechanism of the tail of the aircraft according to the first embodiment of the present invention, and shows a locked state.

[0039] Figure 5 It is a perspective view schematically showing the tail portion of an aircraft according to Embodiment 2 of the present invention, and shows a state before assembly.

[0040] Fig. 6A It is a partial side sectional view schematically showing the assembly process of the tail portion of the aircraft according to the second embodiment of the present invention, and shows the state before positioning by the positioning mechanism.

[0041] Figure 6B It is a partial side sectional view schematically showing the assembly process of the aircraft tail portion according to the second embodiment of the present invention, and shows a state after positioning by the positioning mechanism and locking by the locking mechanism.

[0042] Figure 7 It is a partial stereoscopic view schematically showing a positioning mechanism and a locking and unlocking mechanism at the tail of an aircraft according to a second embodiment of the present invention.

[0043] (Explanation of symbols)

[0044] 1 Aircraft tail

[0045] 100 Tail Cone

[0046] 105 front frame

[0047] 110 Fixing piece

[0048] 115 Stopper

[0049] 150 Integrated device

[0050] 200 Body

[0051] 205 Backend frame

[0052] 210 Acceptance

[0053] 215 Locking piece

[0054] 300 Seal DETAILED DESCRIPTION

[0055] <Implementation Method 1>

[0056] Next, combine Figures 1A to 4B The aircraft tail portion according to the first embodiment of the present invention will be described.

[0057] (The overall structure of the aircraft tail)

[0058] like Figure 1A and Figure 1B As shown, the tail of the aircraft 1 includes a tail cone 100 and a rear fuselage 200, and the tail cone 100 is assembled on the rear fuselage 200 along the heading; the tail of the aircraft 1 also includes: a positioning mechanism, which includes a fixing member 110 and a receiving member 210 for inserting the fixing member 110 along the heading, the fixing member 110 is arranged on the tail cone 100, and the receiving member 210 is arranged on the rear fuselage 200, and limits the fixing member 110 from moving in a plane intersecting the heading; and a locking and unlocking mechanism, which includes a stop The stopper 115 and the locking member 215, the stopper 115 is arranged on the tail cone 100, the locking member 215 is arranged on the rear fuselage 200, and the locking member 215 can be switched between a first position and a second position. In the first position, the locking member 215 is locked with the stopper 115 to prohibit the tail cone 100 from separating along the course relative to the rear fuselage 200. In the second position, the locking member 215 is unlocked from the stopper 115 to allow the tail cone 100 to separate along the course relative to the rear fuselage 200.

[0059] Here, the outer circumference of the front end of the tail cone 100 and the outer circumference of the rear end of the rear fuselage 200 are offset in the heading (ie, they do not overlap in the heading, specifically, they are spliced ​​in the heading).

[0060] In addition, if Figure 1A As shown, the tail portion 1 of the aircraft further includes a sealing ring 300 , which is sandwiched between the tail cone 100 and the rear fuselage 200 in a compressed state in the heading direction.

[0061] (Structure of tail cone)

[0062] like Figure 1A As shown, the tail cone 100 has a tail cone front end surface.

[0063] Here, if Figures 1A to 3 As shown, the tail cone 100 has a front end frame 105, and the front end frame 105 has a front end surface of the tail cone perpendicular to the heading.

[0064] In addition, if Figures 1A to 3 As shown, the front end frame 105 is annular and is continuously formed in the circumferential direction around the axis extending along the heading direction, and the front end surface of the tail cone is also continuously formed in the circumferential direction around the axis extending along the heading direction.

[0065] (Structure of the rear fuselage)

[0066] like Figure 1A As shown, the rear fuselage 200 has a rear fuselage rear end surface.

[0067] Here, if Figures 1A to 3As shown, the rear fuselage 200 has a rear end frame 205, and the rear end frame 205 has a rear fuselage rear end surface perpendicular to the heading.

[0068] In addition, if Figures 1A to 3 As shown, the rear end frame 205 is annular and is continuously formed in the circumferential direction around the axis extending along the heading direction, and the rear end surface of the rear fuselage is also continuously formed in the circumferential direction around the axis extending along the heading direction.

[0069] (Structure of positioning mechanism)

[0070] like Figure 1A and Figure 1B As shown, the positioning mechanism is arranged near the outer surface of the tail 1 of the aircraft.

[0071] Here, if Figure 1A As shown, a plurality of positioning mechanisms are provided in the circumferential direction around the axis extending along the heading direction (four are provided in the example shown in the figure, but it is not limited thereto, and other numbers such as two or three may also be provided). Preferably, the positioning mechanisms are provided at equal intervals in the circumferential direction around the axis extending along the heading direction (in the example shown in the figure, one is provided at the top, bottom, left, and right of the tail of the aircraft respectively), but they may also be provided at unequal intervals.

[0072] In addition, if Figures 1A to 3 As shown, the locking member 110 is a locking pin (preferably formed in a cylindrical shape, but not limited to this) provided on the front end surface of the tail cone 100, and protrudes from the front end surface of the tail cone toward the front side (i.e., toward the rear fuselage 200 side). The front end of the locking member 110 is provided with a chamfer, and the taper angle is, for example, 15° to 30°. The receiving member 210 is provided on the rear fuselage 200. Specifically, the receiving member 210 is a slot formed integrally on the rear fuselage 200. The through hole (channel) of the receiving member 210 for inserting the locking member 110 is substantially equivalent to the outer diameter of the locking member 110. By inserting the locking member 110 into the through hole (channel) of the receiving member 210, the front end frame 105 of the tail cone 100 can be restricted in terms of the vertical, horizontal (in-plane) freedom. The rear end of the through hole (channel) of the receiving member 210 for inserting the locking member 110 is formed in a flared shape, and the taper angle is, for example, 15° to 30°.

[0073] (Structure of the locking and unlocking mechanism)

[0074] like Figure 1A and Figure 1B As shown, the locking and unlocking mechanism is arranged near the outer surface of the tail 1 of the aircraft.

[0075] Here, if Figures 1A to 3As shown, a plurality of locking and unlocking mechanisms are provided in the circumferential direction around the axis extending along the heading direction (four are provided in the example shown in the figure, but it is not limited thereto, and other numbers such as two or three may also be provided). Preferably, the locking and unlocking mechanisms are provided at equal intervals in the circumferential direction around the axis extending along the heading direction (in the example shown in the figure, two are provided on the left and right of the tail of the aircraft respectively), but they may also be provided at unequal intervals.

[0076] In addition, if Figures 1A to 3 As shown, the locking member 215 constitutes a part of the outer surface of the tail portion 1 of the aircraft. Specifically, the locking member 215 constitutes a part of the outer surface near the rear end of the rear fuselage 200. The locking member 215 can rotate around an axis intersecting the heading between a first position and a second position. More specifically, as shown in FIG. Figure 4A and Figure 4B As shown, the locking and unlocking mechanism includes a quick release lock disposed near the rear end of the rear fuselage 200, and the quick release lock includes a locking member 215 having a hook portion.

[0077] In addition, if Figures 1A to 3 As shown, the stopper 115 is disposed near the outer surface of the tail 1 of the aircraft. Specifically, the stopper 115 is disposed near the outer surface of the front end of the tail cone 100, and protrudes from the rear end frame 205 toward the rear side (i.e., the side of the tail cone 100). More specifically, the stopper 115 has a base portion and a protrusion protruding from the base portion toward the front side (i.e., the side of the rear fuselage 200). The base portion is connected to the front end frame 105 via a connector such as a screw. The protrusion includes a stop pin and a connecting portion. The stop pin extends in a direction intersecting the heading, and can be hooked by the hook portion of the locking member 215. The connecting portion extends approximately along the heading and connects the stop pin to the base portion.

[0078] (Structure of sealing ring)

[0079] like Figures 1A to 3 As shown, the sealing ring 300 is arranged in a compressed state between the front end surface of the tail cone and the rear end surface of the rear fuselage.

[0080] Here, if Figures 1A to 3 As shown, the sealing ring 300 is formed continuously in the circumferential direction around the axis extending in the course direction.

[0081] In addition, if Figures 1A to 3 As shown, the sealing ring 300 has a through hole for the fixing member 110 and the stopper 115 to pass through along the course. The cross section of the sealing ring 300 can be a long strip or P-shaped shape, and the material of the sealing ring 300 is rubber or other elastic materials suitable for the sealing ring.

[0082] In addition, the seal ring 300 is fixed to, for example, the front end frame 105 of the tail cone 100 or the rear end frame 205 of the rear fuselage 200 .

[0083] (Assembly of tail cone and rear fuselage)

[0084] When assembling the tail cone 100 and the rear fuselage 200, the locking member 110 on the tail cone 100 is inserted into the receiving member 210 of the rear end frame 205 (refer to Figure 3 ), after the gap between the tail cone 100 and the rear fuselage 200 is fitted, continue to compress the sealing ring 300, press the lock buckle of the quick release lock, and hang the locking member 215 on the stopper 115 (refer to Figure 4B ), thereby, the tail cone 100 is fixed to the rear fuselage 200 by the tension of the lock, limiting the heading displacement of the tail cone 100.

[0085] (Main Effects of the Present Embodiment)

[0086] According to the aircraft tail 1 of the present embodiment, it includes a positioning mechanism and a locking and unlocking mechanism. The positioning mechanism includes a locking member 110 and a receiving member 210 for inserting the locking member 110 along the heading. The locking member 110 is arranged on the tail cone 100, and the receiving member 210 is arranged on the rear fuselage 200, and the locking member 110 is restricted from moving in a plane intersecting the heading. The locking and unlocking mechanism includes a stopper 115 and a locking member 215. The stopper 115 is arranged on the tail cone 100, and the locking member 215 is arranged on the rear fuselage 200. Moreover, the locking member 215 can be switched between a first position and a second position. At the first position, the locking member 215 and the stopper 115 are locked. In the first position, the locking member 215 is locked to prohibit the tail cone 100 from separating relative to the rear fuselage 200 along the heading. In the second position, the locking member 215 is unlocked from the stop member 115 to allow the tail cone 100 to separate relative to the rear fuselage 200 along the heading. Therefore, with the help of the positioning mechanism, the tail cone 100 can be conveniently and quickly positioned relative to the rear fuselage 200 in a plane perpendicular to the heading, and with the help of the locking and unlocking mechanism, the tail cone 100 can be conveniently connected to the rear fuselage 200 or the connection between the tail cone 100 and the rear fuselage 200 can be released, thereby making it convenient to assemble and disassemble the tail cone 100 relative to the rear fuselage 200, saving assembly and disassembly time.

[0087] In addition, according to the aircraft tail 1 of this embodiment, the outer peripheral surface of the front end of the tail cone 100 and the outer peripheral surface of the rear end of the rear fuselage 200 do not overlap in the heading direction. Therefore, compared with the case where the tail cone 100 is sleeved on the rear fuselage 200, the shape control accuracy requirements are lower and the interchangeability function can be easily realized.

[0088] Furthermore, according to the aircraft tail 1 of this embodiment, the locking member 215 constitutes a part of the outer surface of the aircraft tail 1, so that the tail cone 100 can be connected or disconnected relative to the rear fuselage 200 on the outside of the aircraft without internal operation.

[0089] In addition, according to the aircraft tail 1 of this embodiment, the mating surface between the tail cone 100 and the rear fuselage 200 is a plane, which makes it easy to ensure the manufacturing and assembly accuracy and realize the interchangeability function. Moreover, with the help of the sealing ring 300, it can play a sealing and vibration reduction role.

[0090] <Implementation Method 2>

[0091] Next, combine Figures 5 to 7 The aircraft tail portion according to the second embodiment of the present invention will be described.

[0092] Here, the same reference numerals are used for the same or corresponding parts in Embodiment 2, and the description will be mainly focused on the differences from Embodiment 1.

[0093] In this embodiment, as in Embodiment 1, the tail of the aircraft also includes a positioning mechanism and a locking and unlocking mechanism. However, unlike Embodiment 1, a portion of the positioning mechanism and a portion of the locking and unlocking mechanism are formed as one piece. Specifically, Figures 5 to 7 As shown, in addition to the receiving member 210 and the locking member 215, the tail of the aircraft also has an integrated device 150, which integrates the locking member 110 and the stopper 115 in embodiment 1. More specifically, the integrated device 150 has a base portion and a protrusion protruding from the base portion toward the front side (i.e., the rear fuselage 200 side). The base portion is connected to the front end frame 105 via a connecting member such as a screw. The protrusion is inserted into the receiving member 210 and includes an axial body and a stopper pin. The axial body extends roughly along the heading and is provided with a groove that is recessed from the front side (i.e., the rear fuselage 200 side) toward the rear side (i.e., the tail cone 100 side). The stopper pin is arranged in the groove and extends in a direction intersecting the heading, so that the hook of the locking member 215 can be hooked.

[0094] According to the tail portion of the aircraft of the present embodiment, as in embodiment 1, with the aid of a positioning mechanism, the tail cone 100 can be conveniently and quickly positioned relative to the rear fuselage 200 in a plane perpendicular to the heading, and with the aid of a locking and unlocking mechanism, the tail cone 100 can be conveniently connected to the rear fuselage 200 or the connection between the tail cone 100 and the rear fuselage 200 can be released, thereby making it convenient to install and remove the tail cone 100 relative to the rear fuselage 200, thus saving installation and disassembly time.

[0095] Furthermore, according to the aircraft tail portion of the present embodiment, by forming a part of the positioning mechanism and a part of the locking and unlocking mechanism as one body, the number of parts can be reduced, and the assembly process can be further simplified.

[0096] The present invention is described above by way of example in conjunction with the accompanying drawings. It is obvious that the specific implementation of the present invention is not limited to the above-mentioned embodiments.

[0097] For example, in the above embodiment, the positioning mechanism is disposed near the outer surface of the aircraft tail 1 , but the present invention is not limited thereto, and the positioning mechanism may also be disposed at a position of the aircraft tail 1 away from the outer surface thereof.

[0098] In addition, in the above-mentioned embodiment, in all the positioning mechanisms, the locking member 110 is provided on the tail cone 100, and the receiving member 210 is provided on the rear fuselage 200, but it is not limited to this. In all the positioning mechanisms, the locking member 110 may be provided on the rear fuselage 200, and the receiving member 210 may be provided on the tail cone 100. Alternatively, in some of the positioning mechanisms, the locking member 110 is provided on the tail cone 100, and the receiving member 210 is provided on the rear fuselage 200, and in another part of the positioning mechanisms, the locking member 110 is provided on the rear fuselage 200, and the receiving member 210 is provided on the tail cone 100.

[0099] Furthermore, in the above embodiment, the locking and unlocking mechanism is disposed near the outer surface of the aircraft tail 1 , but the present invention is not limited thereto. The locking and unlocking mechanism may also be disposed at a position of the aircraft tail 1 away from the outer surface thereof.

[0100] In addition, in the above-mentioned embodiment, in all locking and unlocking mechanisms, the stopper 115 is provided at the tail cone 100, and the locking member 215 is provided at the rear fuselage 200, but it is not limited to this. In all locking and unlocking mechanisms, the stopper 115 may be provided at the rear fuselage 200, and the locking member 215 may be provided at the tail cone 100; or, in a part of the locking and unlocking mechanisms, the stopper 115 is provided at the tail cone 100, and the locking member 215 is provided at the rear fuselage 200, and in another part of the locking and unlocking mechanisms, the stopper 115 is provided at the rear fuselage 200, and the locking member 215 is provided at the tail cone 100.

[0101] Furthermore, in the above-mentioned embodiment, the receiving member 210 is formed integrally with the rear body 200 , but the present invention is not limited thereto, and a component which is formed separately from the rear body 200 and has the receiving member 210 may also be provided.

[0102] In addition, in the above-mentioned embodiment, the quick-release lock and the lock pin constituting the locking and unlocking mechanism may also be replaced by other single-sided operated locks capable of providing pulling force.

[0103] In addition, in the above embodiment, the aircraft tail portion 1 further includes a sealing ring 300, but is not limited thereto, and the sealing ring 300 may be omitted depending on circumstances.

[0104] It should be understood that within the scope of the present invention, various parts in the embodiments can be freely combined, or various parts in the embodiments can be appropriately deformed or omitted.

Claims

1. An aircraft tail, comprising a rear fuselage and a tail cone assembled to the rear fuselage along a heading direction, characterized in that: include: A positioning mechanism, the positioning mechanism comprising a locking member and a receiving member for inserting the locking member along the heading, the locking member being arranged at any one of the rear fuselage and the tail cone, the receiving member being arranged at any other of the rear fuselage and the tail cone, and limiting the locking member from moving within a plane intersecting the heading; as well as A locking and unlocking mechanism, the locking and unlocking mechanism includes a stopper and a locking member, the stopper is arranged on any one of the rear fuselage and the tail cone, the locking member is arranged on any other of the rear fuselage and the tail cone, and can be switched between a first position and a second position, in which, in the first position, the locking member is locked with the stopper to prohibit the tail cone from separating along the course relative to the rear fuselage, and in the second position, the locking member is released from the lock with the stopper to allow the tail cone to separate along the course relative to the rear fuselage.

2. The aircraft tail portion according to claim 1, characterized in that: The outer peripheral surface of the front end of the tail cone and the outer peripheral surface of the rear end of the rear fuselage are offset in heading.

3. The aircraft tail portion according to claim 1, characterized in that: A plurality of positioning mechanisms are arranged near the outer surface of the tail of the aircraft in a circumferential direction around an axis extending along the heading direction.

4. The aircraft tail portion according to claim 1, characterized in that: The front end of the fixing member is provided with a chamfer. and / or, The rear end of the passage of the receiving member into which the locking member is inserted is formed in a flared shape.

5. The aircraft tail portion according to claim 1, characterized in that: The receiving member is integrally formed with the other of the rear fuselage and the tail cone.

6. The aircraft tail portion according to claim 1, characterized in that: The locking element forms part of the outer surface of the tail of the aircraft, The locking and unlocking mechanisms are provided in a plurality in a circumferential direction around an axis extending along the course direction.

7. The aircraft tail portion according to claim 1, characterized in that: The locking member can rotate between the first position and the second position around an axis intersecting the heading, and has a hook portion. The stopper has a stopper pin extending along the axis and hooked by the hook portion.

8. The aircraft tail portion according to claim 1, characterized in that: The locking member and the stopping member are formed as one body.

9. The aircraft tail portion according to claim 1, characterized in that: The tail cone has a front end surface of the tail cone which is a plane. The rear fuselage has a rear fuselage rear end surface which is a plane, The front end surface of the tail cone is opposite to the rear end surface of the rear fuselage in heading direction. A sealing ring is arranged in a compressed state between the front end surface of the tail cone and the rear end surface of the rear fuselage.

10. The aircraft tail portion according to claim 9, characterized in that: The tail cone has a front end frame, and the front end frame has a front end surface of the tail cone perpendicular to the heading. The rear fuselage has a rear end frame, and the rear end frame has a rear end surface of the rear fuselage perpendicular to the heading. The locking member is a locking pin provided on one of the front end surface of the tail cone and the rear end surface of the rear fuselage. The receiving member is a slot provided on the other of the front end surface of the tail cone and the rear end surface of the rear fuselage. The sealing ring has a through hole for the locking member and the stop member to penetrate along the heading direction.

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