Arresting wall and fuselage flexible connection structure and aircraft

Abstract

The present invention relates to a flexible connection structure between an arresting wall and a fuselage, which is used to fix the arresting wall to the interior of an aircraft, and comprises: a first connection joint, which is pivotally connected to a second connection joint arranged on the arresting wall; a flexible transition piece, the first end of which is fixed to the free end of the first connection joint; and a short beam between frames, which is fixed to adjacent frames and long beams on the aircraft wall panel and fixed to the second end of the flexible transition piece, wherein the flexible transition piece is used to transfer the load from the arresting wall to the frames and long beams. Through this structure, the heading load transferred to the aircraft fuselage via the arresting wall can be carried by means of the flexible transition piece, and the excessive constraint of the rigid arresting wall on the deformation of the local skin of the fuselage under the pressurized working condition is effectively avoided. Compared with the connection structure of the prior art, the influence on the fatigue performance of the fuselage structure is eliminated, and it is easy to be implemented on the existing aircraft. In addition, the present invention also relates to an aircraft including such a flexible connection structure between an arresting wall and a fuselage.

Description

Technical Field

[0001] The invention belongs to the field of aircraft body design and relates to a flexible connection structure between an arresting wall and a fuselage, which is used for connecting an emergency landing arresting wall and a fuselage of an aircraft such as a cargo plane.

[0002] In addition, the present invention also relates to an aircraft comprising such a flexible connection structure between the barrier wall and the fuselage. Background Art

[0003] The conversion of passenger aircraft into cargo aircraft ("passenger-to-cargo") in civil aircraft is an important means to maximize the residual value of aircraft and expand the business scope of airlines. In the process of passenger-to-cargo conversion, since the main cargo hold of the cargo aircraft (the original cabin of the civil aircraft) needs to be loaded with a large amount of cargo, in order to meet the requirements of CCAR25.561, it is necessary to set up a barrier wall between the escort cabin and the main cargo hold of the cargo aircraft to prevent the passengers from being impacted by the cargo in emergency landing and other situations, which may endanger their lives.

[0004] For operational cost and benefit considerations, cargo planes are generally loaded close to their maximum payload, which directly leads to a huge design load for the emergency landing arresting wall. This also puts forward new requirements for the connection structure between the arresting wall and the fuselage: it is required to be able to withstand the 9g load of the maximum payload in the along-course direction in the event of an emergency landing, and to transfer this load to the aircraft's long stringers and other longitudinal structures; it is also required to avoid excessive constraints as much as possible to avoid adverse effects on the force transmission of structures such as the fuselage skin during normal flight.

[0005] In the Chinese invention patent, entitled "A connection structure between cargo hold floor longitudinal beam and arresting wall" and published on December 26, 2016 with publication number CN106672197B, a connection method between cargo hold arresting wall and fuselage floor structure is proposed, which mainly provides lateral movement space through oblong holes and joint bearings. However, this connection structure is located in the same frame position as the arresting wall (for example, between the same two frames), which occupies the design space of the arresting wall structure, affects the overall structural efficiency, and is not convenient for use in small and medium-sized cargo aircraft.

[0006] In the Chinese utility model patent, entitled "A Civil Aircraft Cargo Hold Arresting Wall Slot Connection Structure" and with publication number CN207045664U, filed on August 1, 2017, a civil aircraft cargo hold arresting wall slot connection structure is proposed, which mainly positions the cargo hold arresting wall through the slot formed by the front and rear blocks. This connection method uses a small number of fasteners, the force transmission is not direct enough, and the reliability is difficult to guarantee. It cannot release the lateral load, and there are also problems such as low upper limit of load bearing and insufficient reliability.

[0007] In the Chinese invention patent filed on December 26, 2016, with publication number CN106672196A and titled "A Civil Aircraft Cargo Hold Arresting Wall Pin-Type Connection Structure", a civil aircraft cargo hold arresting wall pin-type connection structure is proposed, which mainly fixes the cargo hold arresting wall through a pin box and bolts, transfers its load to the fixed tooth plate through the pin, and transfers the load parallel to the tooth arrangement direction to the fuselage structure through the tooth surface bite. This scheme is a non-fastener connection form, and because the load is transferred through the tooth surface bite, it is impossible to release the transfer of lateral loads to the fuselage, and it cannot withstand large loads, and reliability is difficult to guarantee.

[0008] In the US patent with publication number US6010286A and titled "Apparatus for rigidly retaining cargo" filed on March 13, 1997, a design scheme for an emergency landing arresting wall in the main cargo hold of a cargo aircraft was proposed. In the patent, the arresting wall and the fuselage structure connection structure are mainly connected to the fuselage structure through front and rear tie rods. This connection structure is also located in the same station (frame station) as the arresting wall, which occupies the design space of the arresting wall structure, affects the overall structural efficiency, and is not convenient for the use of small and medium-sized cargo aircraft; in addition, this structure has the problem of excessive constraints on the fuselage structure. During the normal operation of the cargo aircraft, it may restrain the expansion of the fuselage under the condition of pressurization, affecting the fatigue performance of the local skin of the fuselage and other structures.

[0009] In the French patent with publication number FR2945027A1 and titled "Rigid stop partition for separating section of cabin of aircraft into zones" filed on April 30, 2009, a design scheme for emergency landing arresting wall of the main cargo cabin of a cargo aircraft is proposed. In the patent, the arresting wall and the fuselage structure are connected together mainly through two sets of single and double ear connection structures. The parts of this scheme are complex in shape and have high processing requirements. At the same time, due to the existence of two sets of single and double ear structures, a large installation space is required, which affects the use in small and medium-sized cargo aircraft.

[0010] In the Chinese utility model patent filed on March 1, 2018, with publication number CN207902756U and titled "A full-size arresting device for aircraft cargo hold", a full-size arresting device for aircraft cargo hold is proposed, including: a mesh formed by a plurality of transverse flame-retardant polyester ribbons and a plurality of longitudinal flame-retardant polyester ribbons, a plurality of belt length adjustment mechanisms, and a plurality of self-locking connection devices. This solution is mainly applicable to the cargo hold of passenger aircraft, and the arresting effect is achieved through the net. However, this structure will produce a large deformation under the impact of cargo, and the protection of passengers is insufficient.

[0011] Therefore, there is an urgent need for a flexible connection structure between a barrier wall and a fuselage, which can overcome one or more shortcomings in the prior art. Summary of the invention

[0012] The purpose of the present invention is to provide a flexible connection structure with a fuselage for use with an arresting wall for emergency landing of a cargo aircraft. On the one hand, the flexible connection structure can withstand the maximum commercial load of 9g along the course transmitted by the arresting wall in the case of emergency landing. On the other hand, through the design of flexible transition pieces, it can also effectively avoid the constraint of the rigid arresting wall on the deformation of the fuselage in the case of pressurization, etc., better meet the provisions of CCAR25.561, improve the reliability of cargo aircraft route operation and emergency response, and at the same time, it is easy to modify on existing passenger aircraft, reducing the difficulty of parts processing and assembly.

[0013] According to one aspect of the present invention, a flexible connection structure between an arresting wall and a fuselage is provided, which is used to fix the arresting wall between the escort cabin and the main cargo cabin of an aircraft, and may include:

[0014] a first connection joint pivotally connected to a second connection joint disposed on the retaining wall;

[0015] a flexible transition piece, a first end of the flexible transition piece being fixed to a free end of the first connection joint;

[0016] and an inter-frame short beam fixed to adjacent frames and long stringers of the aircraft and to the second end of the flexible transition piece,

[0017] Among them, flexible transition pieces are used to transfer loads from the barrier wall to the frames and stringers on the aircraft fuselage.

[0018] This structure can not only bear the heading force transmitted to the aircraft fuselage through the arresting wall, but also effectively avoid excessive constraints on the deformation of the local skin and other structures of the fuselage by the rigid arresting wall under pressurized conditions by virtue of the flexibility of the flexible transition piece in the radial direction of the aircraft fuselage. Compared with the connection structure of the prior art, the influence on the fatigue performance of the fuselage structure is eliminated. In addition, the various parts of the device are simple in shape, easy to manufacture, and can be adjusted according to the actual situation of the aircraft fuselage. The scheme is flexible and controllable, so it is easy to implement on existing aircraft.

[0019] According to the above aspects of the present invention, preferably, the flexible connection structure between the barrier wall and the fuselage can be arranged at a different frame position from the barrier wall body, and wherein the barrier wall body is positioned in front of the flexible connection structure of the fuselage in the heading direction.

[0020] In this way, the utilization rate of the onboard space can be released as much as possible and the available area of ​​the arresting wall can be increased, which is particularly suitable for use in medium and small cargo aircraft.

[0021] According to the above aspect of the present invention, preferably, the flexible connection structure between the barrier wall and the fuselage may further include a joint bearing disposed between the first connection joint and the second connection joint. Through the rotation of the joint bearing, it is possible to further effectively avoid excessive constraint of the rigid barrier wall on the deformation of the local skin and other structures of the fuselage under the pressurized condition.

[0022] According to the above aspect of the present invention, preferably, the first connection joint, the second connection joint and the spherical bearing are pivotally fixed together via a fastener. This fastening connection mode transmits force directly and can cooperate with the spherical bearing to release the lateral load, so that the upper limit of the load can be increased and the reliability of the connection structure can be increased. By preventing the rotation of the spherical bearing in the flexible connection structure between the barrier wall and the fuselage, the transmission of the lateral load to the fuselage structure is effectively avoided.

[0023] According to the above aspect of the present invention, preferably, the short beams between frames can be fixed between adjacent frames by means of matching connecting angle pieces in pairs, thereby making the shape of the components simple, further reducing the difficulty of processing, manufacturing and assembly, and facilitating implementation in medium and small cargo planes.

[0024] According to the above aspect of the present invention, preferably, the inter-frame short beam is composed of a first C-shaped short beam and a second C-shaped short beam fixed back to back, and the connecting angle piece is fixed to the web portion of the first C-shaped short beam and the second C-shaped short beam. This structure facilitates more fitting fixation to the long stringer of the aircraft fuselage, such as the long stringer with a Z-shaped cross section, thereby improving the reliability of connection and force transmission.

[0025] According to the above aspect of the present invention, preferably, the flexible transition piece can be a flexible transition plate, so as to facilitate the processing, manufacturing and matching installation of various components.

[0026] According to the above aspects of the present invention, preferably, in order to improve the corrosion resistance of the flexible transition plate while bearing greater tensile stress, so as to be used for loading various types of cargoes, extend service life and enhance reliability, the material of the flexible transition plate can be stainless steel or titanium alloy or other materials.

[0027] According to the above aspects of the present invention, preferably, the first connection structure may include a double-ear joint, and the second attachment portion may include a single-ear joint that cooperates with the double-ear joint. Through the structural design of single-ear and double-ear joints, joint bearings, stainless steel flexible transition plates, etc., a variety of compensation measures are provided for on-board assembly work, which significantly reduces the difficulty of modification and assembly of existing passenger aircraft / cargo aircraft.

[0028] According to another aspect of the present invention, an aircraft is provided, which may include:

[0029] Frames, the frames are arranged at intervals in the heading direction of the aircraft;

[0030] A long stringer, which extends in the heading direction and is fixedly connected to the frame;

[0031] Arresting walls, which are used to divide the aircraft's load compartment into multiple sections in the heading direction; and

[0032] According to the flexible connection structure of the arresting wall and the fuselage of the above aspect, the flexible connection structure of the arresting wall and the fuselage is used to hold the arresting wall to the frame and the long stringer.

[0033] The characteristics and beneficial effects of the flexible connection structure between the barrier wall and the fuselage according to the present invention may include the following aspects:

[0034] Through the flexible connection structure between the arresting wall and the fuselage used for emergency landing of cargo aircraft, the 9g load of cargo can be carried and transferred under emergency landing conditions;

[0035] The flexible transition piece can effectively avoid excessive constraints on the fuselage structure during normal flight, effectively improving the reliability and safety of the connection structure; and

[0036] The flexible transition piece (flexible connection structure) provided by the present invention is also easy to modify on an aircraft (such as a passenger aircraft / cargo aircraft), and has low difficulty in parts processing and assembly.

[0037] Therefore, the flexible connection structure between the barrier wall and the fuselage of the present invention can meet the use requirements, overcome the shortcomings of the prior art and achieve the predetermined purpose of the invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] In order to further clearly describe the flexible connection structure between the barrier wall and the fuselage according to the present invention, the present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments. In the accompanying drawings:

[0039] Figure 1 is a schematic perspective view of a portion of a flexible connection structure between an arresting wall and a fuselage according to a non-limiting embodiment of the present invention;

[0040] Figure 2 is a schematic side view of a portion of a flexible connection structure of a barrier wall and a fuselage according to a non-limiting embodiment of the present invention; and

[0041] Figure 3 It is a schematic diagram of a portion of a flexible connection structure between an arresting wall and a fuselage according to a non-limiting embodiment of the present invention, viewed along the heading direction.

[0042] The above drawings are merely schematic and are not drawn strictly to scale.

[0043] List of reference numerals in the figures and embodiments:

[0044] 100- Flexible connection structure between arresting wall and fuselage, including;

[0045] 10-First connecting joint, comprising;

[0046] 11 – free end;

[0047] 12 - pivot end;

[0048] 20 - flexible transition piece;

[0049] 21 – first end;

[0050] 22 – second end;

[0051] 30 - short beam between frames;

[0052] 31 - first C-shaped short beam;

[0053] 32 - second C-shaped short beam;

[0054] 40 - spherical plain bearings;

[0055] 50 - Fasteners, including;

[0056] 51 - bolt;

[0057] 52 - nut;

[0058] 60 - connecting corner piece;

[0059] 200 - Retaining wall, including;

[0060] 201 - second connection joint;

[0061] 202-blocking wall body;

[0062] 300 - aircraft, including;

[0063] 301 - Frame;

[0064] 302 - long stringer;

[0065] F – Heading direction. DETAILED DESCRIPTION

[0066] It should be understood that, unless expressly stated otherwise, the present invention may adopt various alternative orientations and step sequences. It should also be understood that the specific connection structures shown in the drawings and described in the specification are merely exemplary embodiments of the inventive concepts disclosed and defined herein. Therefore, unless otherwise expressly stated, the specific orientations, directions or other physical characteristics involved in the various embodiments disclosed should not be considered as limiting.

[0067] Aircraft such as cargo planes or cargo planes converted from passenger planes usually include a main cargo hold for loading cargo, and frames and long stringers are usually provided in the circumferential direction of the main cargo hold. As an example, the frames can be arranged at intervals in the heading direction of the aircraft, and the long stringers can extend on the fuselage along the heading direction and be fixedly connected to the frames to form a supporting structure of the aircraft body, and are used to carry various aircraft structures such as floors, engines, and cargo.

[0068] According to the emergency landing conditions of the transport category airplane airworthiness standards (CCAR-25-R4), although the airplane may be damaged in an emergency landing on land or water, the occupants should be protected from serious injury by being subjected to a maximum inertia load factor of 9g forward.

[0069] Therefore, it is necessary to set up an arresting wall between the escort cabin and the main cargo cabin of a cargo plane (or a passenger-to-cargo aircraft) to prevent passengers from being impacted by cargo in the main cargo cabin during an emergency landing, which could endanger their lives. In order to fix the arresting wall inside the aircraft, a corresponding flexible connection structure between the arresting wall and the fuselage needs to be provided.

[0070] The flexible connection structure 100 between the barrier wall and the fuselage of a civil aircraft according to the present invention will be described in detail below with reference to the accompanying drawings.

[0071] Figure 1 and 2 are respectively a schematic perspective view and a side view of a portion of a flexible connection structure 100 between an arresting wall and a fuselage according to a non-limiting embodiment of the present invention; Figure 3 Schematic diagram of a portion of a flexible connection structure 100 between an arresting wall and a fuselage according to a non-limiting embodiment of the present invention, viewed along a heading F.

[0072] As shown in the figures and according to a non-limiting embodiment of the present invention, a flexible connection structure 100 between an arresting wall and a fuselage may include a first connection joint 10 , a flexible transition piece 20 and an inter-frame short beam 30 .

[0073] For example, the first connection joint 10 may be pivotally connected to a second connection joint 201 provided on the retaining wall 200. The second connection joint 201 may be, for example, a portion protruding from the retaining wall 200, or may be separately manufactured from the retaining wall 200 and fixedly connected to the retaining wall 200 (e.g., screwed, riveted, etc.), for example, fixed to the peripheral portion of the retaining wall 200.

[0074] As a non-limiting example, the first connection joint 10 may include a double-ear joint, and the second connection joint 201 may include a single-ear joint that cooperates with the double-ear joint. Alternatively, the first connection joint 10 may include a single-ear joint, and the second connection joint 201 may include a double-ear joint that cooperates with the single-ear joint. Of course, those skilled in the art can envision other types of connection joints.

[0075] The first end 21 of the flexible transition piece 20 may be fixed to the free end 11 of the first connection joint 10, and the second end 22 of the flexible transition piece 20 may be attached to the fuselage panel of the aircraft 300, for example by means of inter-frame short beams 30, which may be fixed to adjacent frames 301 and long stringers 302 of the aircraft 300. The flexible transition piece 20 may be used to transfer loads from the barrier wall 200 to the frames 301 and long stringers 302.

[0076] In the embodiment shown in the accompanying drawings, the arresting wall and fuselage flexible connection structure 100 and the arresting wall body 202 of the arresting wall 200 can be positioned at different frame positions. At this time, preferably, the arresting wall body 202 can be positioned in front of the arresting wall and fuselage flexible connection structure 100 in the heading direction F, for example, respectively positioned at adjacent frame positions.

[0077] As used herein, the term "frame position" may be used to indicate the position of the frame 301 of the aircraft 300 in terms of heading, and the qualifier "flexible" may be the conventional understanding in the art, indicating that the connection structure can bend or deform when a load is applied, and can return to its original shape after the load disappears.

[0078] In a preferred embodiment, the flexible connection structure 100 between the barrier wall and the fuselage can be positioned at two adjacent frame positions with the barrier wall body 202 of the barrier wall 200. It should be understood that the barrier wall 200 according to the present invention is a rigid barrier wall.

[0079] As shown in the figure and as a non-limiting example, the flexible transition piece 20 can be in the form of a flexible transition plate, and the material of the flexible transition plate can be selected from stainless steel, titanium alloy, etc. The size of the flexible transition piece 20 can be selected based on the size of the internal space of the fuselage of the aircraft, the load conditions that need to be carried, and the material conditions.

[0080] For example, when the flexible transition piece 20 is a flexible transition plate made of stainless steel, the stainless steel flexible transition plate may have a substantially rectangular thin plate shape.

[0081] As a preferred embodiment, the inter-frame short beam 30 may include a first C-shaped short beam 31 and a second C-shaped short beam 32 fixed back to back to match the long stringer 302 having a substantially Z-shaped cross section. Figure 3 As shown in the upper middle part. Figure 3 As shown in FIG. 1 , the first C-shaped short beam 31 on the right is higher in height than the second C-shaped short beam 32 on the left to match the shape of a corresponding portion of the long stringer having a Z-shaped cross section and be fixed to the long stringer.

[0082] The first C-shaped short beam 31 and the second C-shaped short beam 32 may also be fixedly connected to each other, for example, by riveting, bolting, etc. at substantially flat web portions in back-to-back contact.

[0083] In addition, the connecting angle piece 60 can also be fixed to the web portion of the first C-shaped short beam 31 and the second C-shaped short beam 32, for example, by riveting, bolting, etc. The connecting angle piece 60 can be in the form of an L-shaped angle piece, and its two ends are respectively connected to the frame 301 and the web portion of the first C-shaped short beam 31 or the second C-shaped short beam 32, so that the inter-frame short beam 30 is also fixedly connected between adjacent frames 301.

[0084] At this time, preferably, the flexible transition piece 20 can be connected to the first connection joint 10 and the inter-frame short beam 30 by fasteners such as bolts and nuts.

[0085] According to a non-limiting embodiment of the present invention and as Figure 3 As shown in , the barrier wall and fuselage flexible connection structure 100 may further include a spherical bearing 40 disposed between the first connection joint 10 and the second connection joint 201. The first connection joint 10, the second connection joint 201 and the spherical bearing 40 are pivotally connected together via a fastener 50, such as a bolt 51 and a nut 52. Preferably, a bushing may also be provided, which may be inserted between the bolt 51 and the attachment hole to protect the corresponding contact structure from wear.

[0086] The spherical bearing 40 allows the first connection joint 10 and the second connection joint 201 to pivot in the circumferential direction, and allows the first connection joint 10 to deflect relative to the second connection joint 201 in the lateral direction within a certain range.

[0087] When the barrier wall 200 bears the 9g load of the cargo in the main cargo hold along the heading, the load transmitted to the second connection joint 201 is not a complete heading load due to the deformation of the barrier wall 200. The heading load component is finally transmitted to the long stringer 302 of the longitudinal load-bearing member of the fuselage through the fastener 50, the first connection joint 10, the flexible transition piece 20 and the short beam between the frames 30; the lateral load component is transmitted through the rotation of the joint bearing 40 between the first connection joint 10 and the second connection joint 201. Such a flexible connection structure design of the fuselage not only meets the design requirements of the heading load, but also effectively avoids the effect of the lateral load on the long stringer 302 of the fuselage.

[0088] When an aircraft such as a cargo plane is in normal operation, under the condition of fuselage pressurization, the flexible connection structure 100 between the barrier wall and the fuselage according to the present invention can expand along with the fuselage of the aircraft through the bending of the flexible transition piece 20 and the rotation of the joint bearing 40, thereby enabling the short inter-frame beams 30 and the connecting angle pieces 60 directly connected to the fuselage structure to expand together with the fuselage of the aircraft. This effectively avoids excessive constraint of the rigid barrier wall 200 on the local deformation of the fuselage and prevents its fatigue performance from being affected.

[0089] Compared with the prior art, the flexible connection structure 100 between the barrier wall and the fuselage for a cargo plane proposed by the present invention may include the following advantages:

[0090] 1) The rotation of the joint bearing in the flexible connection structure between the barrier wall and the fuselage effectively avoids the transmission of lateral loads to the fuselage structure. Compared with the existing connection structure, the load transmission is more reasonable;

[0091] 2) Through the bending of the flexible transition piece in the flexible connection structure between the arresting wall and the fuselage and the rotation of the joint bearing, the excessive constraint of the rigid arresting wall on the deformation of the local skin and other structures of the fuselage under the pressurized condition is effectively avoided. Compared with the existing connection structure, the influence on the fatigue performance of the fuselage structure is eliminated;

[0092] 3) The components of the flexible connection structure between the arresting wall and the fuselage provided are simple in shape, easy to manufacture, and can be adjusted according to the actual situation on the aircraft, making the solution flexible and controllable;

[0093] 4) The flexible connection structure between the arresting wall and the fuselage of the present invention is not arranged at the same station as the arresting wall, so that the utilization rate of the onboard space can be released as much as possible, and the available area of ​​the arresting wall is increased, which is particularly suitable for use in medium and small cargo aircraft;

[0094] 5) The flexible connection structure between the arresting wall and the fuselage of the present invention provides a variety of compensation measures for on-board assembly work through structural designs such as single-ear and double-ear structures, joint bearings, and flexible transition pieces, which significantly reduces the difficulty of aircraft modification and arresting wall assembly.

[0095] The following describes an exemplary installation process of the barrier wall and fuselage flexible connection structure 100 according to the present invention in the main cargo hold of an aircraft.

[0096] As a non-limiting example, the spherical bearing 40 can be first installed on the second connection joint 201 of the retaining wall 200; connected to the fuselage long girder 302 through a pair of back-to-back short beams 30, and then connected to the front and rear frames 301 through connecting angle pieces 60; the position of the first connection joint 10 is appropriately adjusted, and it is connected to the second connection joint 201 with bolts 51 and nuts 52; the position of the flexible transition piece 20 is appropriately adjusted, and it is connected to the first connection joint 10 and the short beam 30 between the frames, thereby completing the connection between the retaining wall 200 and the fuselage.

[0097] Preferably, the barrier wall and fuselage flexible connection structure 100 used for cargo planes are both metal parts, and the type of material, part shape and processing method (sheet metal / machining) can be selected according to the actual project. The solution is flexible and controllable and can adapt to a variety of complex scenarios.

[0098] As used herein, the terms indicating position or orientation and the terms "first", "second", etc. used to indicate order are only intended to enable those of ordinary skill in the art to better understand the concept of the present invention as shown in the form of a preferred embodiment, and are not intended to limit the present invention. Unless otherwise specified, all orders, positions or orientations are only used for the purpose of distinguishing one element / component / structure from another element / component / structure, and unless otherwise specified, do not represent any specific order, order of operation, direction or orientation. For example, in alternative embodiments, the "first end" may be the "second end" depending on the actual use environment or the function to be achieved.

[0099] In summary, the barrier wall and fuselage flexible connection structure 100 according to the embodiment of the present invention overcomes the shortcomings of the prior art and achieves the intended purpose of the invention.

[0100] Although the flexible connection structure between the barrier wall and the fuselage of the present invention is described above in combination with the preferred embodiments, those skilled in the art should realize that the above examples are only for illustration and cannot be used as a limitation of the present invention. Therefore, various modifications and variations can be made to the present invention within the spirit of the claims, and these modifications and variations will fall within the scope of the claims of the present invention.

Claims

1. A flexible connection structure (100) between an arresting wall and a fuselage, characterized in that: The arresting wall and fuselage flexible connection structure is used to fix the arresting wall (200) into the aircraft (300), and comprises: A first connection joint (10), the first connection joint being pivotally connected to a second connection joint (201) provided on the retaining wall (200); a flexible transition piece (20), wherein a first end (21) of the flexible transition piece is fixed to a free end (11) of the first connection joint (10); and a short inter-frame beam (30), the short inter-frame beam being fixed to adjacent frames (301) and long stringers (302) of the aircraft (300), and being fixed to the second end (22) of the flexible transition piece (20), The flexible transition piece (20) is used to transfer the load from the retaining wall (200) to the frame (301) and the long stringer (302).

2. The barrier wall and fuselage flexible connection structure (100) according to claim 1, characterized in that: The arresting wall and fuselage flexible connection structure (100) and the arresting wall body (202) of the arresting wall (200) are positioned at different frame positions, and the arresting wall body (202) is positioned in front of the arresting wall and fuselage flexible connection structure (100) in a heading direction (F).

3. The barrier wall and fuselage flexible connection structure (100) according to claim 2, characterized in that: The barrier wall and fuselage flexible connection structure (100) further comprises a joint bearing (40) arranged between the first connection joint (10) and the second connection joint (201).

4. The barrier wall and fuselage flexible connection structure (100) according to claim 3, characterized in that: The first connection joint (10), the second connection joint (201) and the spherical bearing (40) are pivotally fixed together via a fastener (50).

5. The barrier wall and fuselage flexible connection structure (100) according to claim 4, characterized in that: The inter-frame short beams (30) are fixed between adjacent frames (301) by means of paired connecting angle pieces (60).

6. The barrier wall and fuselage flexible connection structure (100) according to claim 5, characterized in that: The inter-frame short beam (30) comprises a first C-shaped short beam (31) and a second C-shaped short beam (32) fixed back to back, and the connecting angle piece (60) is fixed to the web portions of the first C-shaped short beam (31) and the second C-shaped short beam (32).

7. The barrier wall and fuselage flexible connection structure (100) according to any one of claims 1 to 6, characterized in that: The flexible transition piece (20) is a flexible transition plate.

8. The barrier wall and fuselage flexible connection structure (100) according to claim 7, characterized in that: The material of the flexible transition plate is stainless steel or titanium alloy.

9. The barrier wall and fuselage flexible connection structure (100) according to any one of claims 1 to 6, characterized in that: The first connection joint (10) comprises a double-ear joint, and the second connection joint (201) comprises a single-ear joint cooperating with the double-ear joint.

10. An aircraft (300), characterized in that: The aircraft include: Frames (301), the frames being arranged at intervals in a heading direction (F) of the aircraft (300); A long stringer (302), the long stringer extending along the heading direction (F) and fixedly connected to the frame (301); an arresting wall (200), the arresting wall being used to divide the load compartment of the aircraft (300) into a plurality of sections in the heading direction (F); and According to any one of claims 1 to 9, the flexible connection structure (100) between the barrier wall and the fuselage is used to fix the barrier wall (200) to the frame (301) and the long stringer (302).

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