Cargo hold baffle connection structure, cargo hold baffle assembly, and aircraft including the assembly.

Abstract

A connection structure for a cargo hold baffle of an aircraft is disclosed. The main fuselage of the aircraft includes passenger cabin floor longitudinal beams, and the connection structure includes a connecting device that connects the passenger cabin floor longitudinal beams and the cargo hold baffle, thereby allowing the passenger cabin floor longitudinal beams to move vertically relative to the cargo hold baffle at the connection structure. This connection structure includes a flexible connection portion, which avoids stress concentration in the vertical direction at the connection structure caused by aircraft loads during takeoff, flight, and landing, and enables rapid installation and disassembly of the cargo hold baffle to the main aircraft structure. Furthermore, this invention also proposes a cargo hold baffle assembly and an aircraft including the cargo hold baffle assembly.

Description

Technical Field

[0001] This invention relates to aircraft, and more particularly to the field of cargo hold partitions for aircraft. Furthermore, this invention also relates to aircraft including the proposed cargo hold partition. Background Technology

[0002] In aircraft, cargo hold partitions are typically used to separate the cargo hold from other pressurized compartments to prevent cargo from colliding with and damaging other aircraft structures or equipment due to acceleration during flight. Current modifications to aircraft auxiliary fuel tanks require the installation of cargo hold partitions to prevent cargo from impacting fuel tanks and other equipment.

[0003] Cargo hold partitions need to be connected to the main structure of the aircraft. Currently, the known connection methods between cargo hold partitions and the main structure of the aircraft are mainly as follows:

[0004] In US6010286A (publication date: January 4, 2000), the rigid arresting wall is connected to the fuselage structure via a rigid tie rod. This type of connection is detrimental to the fatigue performance of the fuselage structure.

[0005] In FR2945027A1 (publication date: November 5, 2010), the arresting wall is connected to the fuselage via two sets of single and double lug connection structures. Such component structures have complex shapes, high processing requirements, and require a large installation space, making them unsuitable for small and medium-sized cargo aircraft.

[0006] A structure for connecting the longitudinal beams of the cargo hold floor to the barrier wall is known from CN106672197A (publication date: May 17, 2017), wherein the connection structure is provided with space and degrees of freedom for lateral movement through elongated holes and spherical bearings.

[0007] A pin-type connection structure for a cargo hold arresting wall of a civil aircraft is known from CN106672196A (publication date: May 17, 2017). In this connection structure, the cargo hold arresting wall is fixed by a pin box and bolts. Thus, the load is transferred to the fixed tooth plate through the pin, and the load parallel to the tooth arrangement direction is transferred to the fuselage structure through the meshing of the tooth surfaces.

[0008] A slotted connection structure for an aircraft cargo hold arresting wall is known from CN207045664U (publication date: February 27, 2018). In this connection structure, the cargo hold arresting wall is positioned by a slot formed by a front stop and a rear stop. However, the force transmission of this connection method is not direct enough and its reliability is difficult to guarantee.

[0009] The existing connection method between the cargo hold baffle (arresting wall) and the main structure of the aircraft is prone to stress concentration problems.

[0010] Furthermore, the existing cargo hold baffles are structurally complex and difficult to disassemble, making maintenance difficult for personnel and increasing the airline's operating and maintenance costs. Therefore, the industry hopes to improve, or even completely overcome, at least one of the aforementioned defects in the existing cargo hold baffles. Summary of the Invention

[0011] The present invention was made in view of the above-mentioned technical problems, and its object is to provide a connection structure for a cargo hold baffle of an aircraft that improves the defects existing in the prior art.

[0012] To solve the above-mentioned technical problems, the connecting structure for the cargo hold floor of an aircraft of the present invention includes a connecting device that connects the passenger cabin floor longitudinal beam and the cargo hold baffle in the main structure of the aircraft, so that the passenger cabin floor longitudinal beam can move in the vertical direction relative to the cargo hold baffle at the connecting structure, thereby avoiding stress concentration at the connecting structure due to vertical loads during takeoff-flight-landing without reducing the ability to bear forward loads.

[0013] Unlike the existing fixed connection structure described above, the flexible connection structure according to the present invention can effectively avoid stress concentration caused by vertical loads on the aircraft, thus eliminating the need for corresponding design and analysis for stress concentration during the design phase.

[0014] Ideally, the connection structure also includes a reinforcing member arranged along the flight direction of the aircraft to enhance the connection structure and cargo hold baffle of the present invention in terms of their ability to withstand forward loads.

[0015] In a preferred embodiment, the connection structure includes a connection device having a connecting corner box and a flexible connector. The flexible connector is fastened to the floor longitudinal beam of the passenger cabin, while the connecting corner box is fastened to the cargo hold baffle. The flexible connector and the connecting corner box cooperate with each other so that the flexible connector can move in the vertical direction relative to the connecting corner box.

[0016] From the perspective of fuselage design, the connection structure of the present invention is a flexible connection structure. By releasing the vertical movement freedom of the connection between the connecting corner box and the flexible connector, the flexible connection structure will not transfer the vertical load to the cargo hold baffle structure, but will be borne entirely by the floor beams and longitudinal structure of the cabin.

[0017] In a non-limiting embodiment, the flexible connector includes a base and a shaft protruding from the base, and a guide portion is provided in the connecting corner box for guiding the shaft portion of the flexible connector to slide freely therein.

[0018] Specifically, a receiving hole may be provided on one side of the connecting corner box, and a wear-resistant bushing is embedded in the receiving hole to form the aforementioned guide portion. The flexible connector achieves the connection and engagement between the flexible connector and the connecting corner box by extending its shaft portion through the receiving hole and inserting it into the wear-resistant bushing. The wear-resistant bushing ensures the sliding guidance of the shaft portion of the flexible connector and protects the shaft portion from wear caused by sliding.

[0019] Ideally, the aforementioned reinforcing member is also provided in the form of a reinforcing corner box. The connection structure according to the invention includes at least one reinforcing corner box, which is arranged back-to-back directly or indirectly adjacent to the connecting corner box, for bearing non-vertical loads.

[0020] Preferably, the opening directions of both the reinforcing corner box and the connecting corner box are set along the straight line of the baffle frame, and the opening direction of the reinforcing corner box is opposite to that of the connecting corner box.

[0021] According to the connection structure of the present invention, by inserting the shaft portion of the flexible connector into the corresponding receiving hole of the connecting corner box and without imposing axial constraints on the shaft portion, the vertical load is reasonably released. This effectively prevents the load from the passenger cabin from being transmitted to the cargo hold baffle via the passenger cabin floor longitudinal beams. The implementation of the connection structure is simple, the structure is simple, it is easy to connect the cargo hold baffle to the main body of the aircraft fuselage, and it is also easy to disassemble the cargo hold baffle when maintenance is required.

[0022] The present invention also proposes a cargo hold baffle assembly, including a cargo hold baffle and a connection structure according to any of the above embodiments.

[0023] In this cargo hold baffle assembly, the cargo hold baffle adopts a modular design, consisting of at least two sub-baffles, and has a baffle frame disposed on its outer perimeter. The aforementioned connection structure is used to connect the cargo hold baffle to the longitudinal beams of the aircraft's cargo hold floor at the baffle frame. In addition, the circumferential arrangement of the baffle frame around the cargo hold baffle enhances the overall strength of the modular cargo hold baffle design.

[0024] The modular design of the cargo hold baffles allows for easy maintenance by simply removing the corresponding sub-baffle and replacing it when a part of the cargo hold baffle needs repair or replacement, thus improving maintenance efficiency and convenience.

[0025] In a non-limiting embodiment, the baffle frame includes an upper baffle frame, side baffle frames, a lower baffle frame, and a middle baffle frame. Each sub-baffle of the cargo hold baffle has a corresponding baffle frame on its periphery and is connected to the baffle frame via a threaded connector. The threaded connector includes a support nut mounted on the baffle frame and a bolt passing through a hole in the sub-baffle. The bolt is screwed into the support nut at the baffle frame after passing through the hole. This facilitates the installation and removal of the sub-baffle from the baffle frame.

[0026] In a non-limiting embodiment, at least the upper upper edge of the baffle frame is made of an I-beam. The connecting corner box of the connecting structure is bolted to the upper upper edge of the baffle, and the connecting structure includes two reinforcing corner boxes arranged back-to-back with the connecting corner boxes. These two reinforcing corner boxes are respectively disposed in the grooves of the I-beam of the upper frame, and are connected to each other on their respective first sides by means of threaded connectors to the web of the I-beam, and on their respective second sides are respectively bolted to one side of the corresponding connecting corner box.

[0027] In a non-limiting embodiment, the bottom edge of the flexible connector in the connection structure is connected to the bottom edge of the connecting strip plate by bolts, and the connecting strip plate is fastened to the longitudinal beam of the cabin floor.

[0028] Ideally, at least one sub-baffle of the cargo hold baffle assembly has a pressure relief port, and the pressure relief port contains a sealing membrane made of sealing material. When the pressure difference across the cargo hold baffle exceeds a preset threshold, the sealing membrane ruptures, thereby allowing the pressure across the cargo hold baffle to be rebalanced.

[0029] To protect the sealing membrane in the pressure relief vent from impacts from cargo in the cargo hold during aircraft operation, a pressure relief vent protective cover is installed on one side of the vent. This protective cover, for example, is a bent sheet metal piece that covers the pressure relief vent and is connected to the area of ​​the sub-baffle surrounding the pressure relief vent by threaded fasteners.

[0030] Ideally, to further enhance the support for the pressure relief port protective cover, at least one support member is provided in the area between the main body of the pressure relief port protective cover and the periphery of the pressure relief port. The two ends of this support member are fixedly connected to the main body of the pressure relief port protective cover and the sub-baffle, respectively.

[0031] The present invention also proposes an aircraft comprising a cargo hold baffle assembly, a passenger cabin floor longitudinal beam, and a cargo hold floor longitudinal beam as described in any of the above embodiments.

[0032] In a non-limiting embodiment, the aircraft includes four passenger cabin floor longitudinal beams, and the cargo hold baffle assembly is flexibly connected to each of these four passenger cabin floor longitudinal beams via a connection structure that allows for axial sliding. The cargo hold baffle assembly is also connected to the cargo hold floor longitudinal beams via threaded fasteners.

[0033] Preferably, in the threaded connection, the support plate nut is located at the inner edge of the longitudinal beam of the cargo hold floor, and the bolt passes through the hole pre-set in the lower frame of the cargo hold baffle assembly and is screwed into the support plate nut at the bottom edge of the lower frame of the baffle, thereby achieving a fixed connection between the cargo hold baffle assembly and the cargo hold floor.

[0034] The aforementioned connection structure is simple and facilitates the connection and disassembly of the cargo hold baffle assembly with the aircraft's cargo hold floor and passenger cabin floor. Attached Figure Description

[0035] With reference to the above objectives, the technical features of the present invention will be specifically explained below with reference to the non-limiting drawings and in conjunction with a detailed description. The drawings illustrate preferred embodiments of the invention by way of example, but do not limit the scope of the inventive concept.

[0036] Figure 1 A front perspective view of an embodiment of the cargo hold baffle assembly of the present invention is shown;

[0037] Figure 2 Show Figure 1 Rear-view perspective view of the cargo hold baffle assembly shown;

[0038] Figure 3 It shows Figure 2 Details of the protective cover for the cargo hold baffle assembly shown;

[0039] Figure 4 A detailed diagram showing the connection structure between the cargo hold baffle and the passenger cabin floor longitudinal beams, viewed from the side;

[0040] Figure 5 Shown as a three-dimensional view from above Figure 4 The connection structure shown;

[0041] Figure 6 Shown in a three-dimensional view from below Figure 4 The connection structure shown;

[0042] Figure 7 A detailed diagram of the connection structure between the cargo hold baffle and the longitudinal beams of the cargo hold floor, viewed from the side.

[0043] List of reference numerals

[0044] 1. Baffle assembly;

[0045] 4. Baffle frame;

[0046] 4.1 Upper edge of the baffle;

[0047] 4.2 Side frame of the baffle;

[0048] 4.3 Bottom edge of the baffle;

[0049] 4.4 Baffle intermediate frame;

[0050] 4.5 bolts (between the lower edge of the baffle and the longitudinal beam of the cargo hold floor);

[0051] 4.6 (Between the lower edge of the baffle and the longitudinal beam of the cargo hold floor) tray nut;

[0052] 5.1 First reinforcing angle box;

[0053] 5.2 Second reinforcing corner box;

[0054] 5.3 Bolts (between the reinforcing corner box and the connecting corner box);

[0055] 5.4 Bolts (connecting the corner boxes);

[0056] 6. Cabin floor longitudinal beams;

[0057] 7. Cargo hold floor longitudinal beams;

[0058] 8.1 Sub-baffle;

[0059] 8.2 Sub-baffle;

[0060] 8.3 Sub-baffle;

[0061] 8.4 Bolts (between the sub-baffle and the baffle frame);

[0062] 8.5 (between the sub-baffle and the baffle frame) support plate nut;

[0063] 9. Pressure relief port;

[0064] 10. Pressure relief port protective cover;

[0065] 10.1 Support components;

[0066] 20 Flexible connection parts;

[0067] 21 Connecting corner boxes;

[0068] 21.1 Wear-resistant bushing;

[0069] 21.2 Receiving hole;

[0070] 21.3 Bolts (connecting the corner box and the upper edge of the baffle);

[0071] 22 Flexible connectors;

[0072] 22.1 Base;

[0073] 22.2 Shaft section;

[0074] 23 Connecting plate;

[0075] 23.1 Bolts (between the flexible connector and the connecting strip);

[0076] 30 baffle - threaded connection of cargo hold floor. Detailed Implementation

[0077] Reference will now be made in detail to various embodiments of the invention, examples of which are shown in the accompanying drawings and described below. Although the invention will be described in conjunction with exemplary embodiments, it should be understood that this specification is not intended to limit the invention to those exemplary embodiments. Rather, the invention is intended to cover not only these exemplary embodiments, but also various alternatives, modifications, equivalents, and other embodiments that may be included within the spirit and scope of the invention as defined by the appended claims.

[0078] For ease of interpretation and precise definition in the appended claims, the terms “upper,” “lower,” “inner,” and “outer” are used to describe features with reference to their location in the exemplary embodiments shown in the figures.

[0079] Figure 1 The diagram schematically illustrates the connection between the cargo hold partition and the main structure of a passenger aircraft. For clarity, only the cargo hold floor longitudinal beam 7 and the passenger cabin floor longitudinal beam 6 are shown for the main structure of the aircraft; the rest of the structure is omitted.

[0080] As shown in the figure, the baffle assembly 1 of the passenger aircraft includes a cargo hold baffle consisting of three sub-baffles 8.1, 8.2 and 8.3. The sub-baffle 8.1 has a through opening, which is used as a pressure relief port 9.

[0081] The baffle assembly 1 includes a baffle frame 4 surrounding the perimeter. In the illustrated embodiment, the baffle frame 4 includes an upper baffle frame 4.1, a side baffle frame 4.2, and a lower baffle frame 4.3.

[0082] The baffle assembly 1 is connected to the main structure of the aircraft at the baffle frame 4. Specifically, the baffle assembly 1 is flexibly connected to the passenger cabin floor longitudinal beam 6 at the upper upper frame 4.1 via a flexible connection part 20, and is fixedly connected to the cargo hold floor longitudinal beam 7 at the lower frame 4.3 via a baffle-cargo hold floor threaded connection part 30. The flexible connection part 20 and the threaded connection part 30 will be further explained below.

[0083] Sub-baffle 8.1 has three sides on its outer peripheral surface (specifically...) Figure 1 The upper, left, and lower sides of the sub-baffle are respectively fixedly connected to the upper upper frame 4.1, the side frame 4.2, and the lower frame 4.3 of the baffle. The sub-baffle 8.3 is also fixedly connected to the three sides of its outer periphery (specifically...) Figure 1The upper, right, and lower sides of the sub-baffle 81 are fixedly connected to the upper upper frame 4.1, the side frame 4.2, and the lower frame 4.3 of the baffle, respectively. The sub-baffle 8.2, located between sub-baffles 8.1 and 8.3, is connected to the upper upper frame 4.1 and the lower frame 4.3 of the baffle on its upper and lower sides, respectively. In the baffle assembly 1, the middle sub-baffle 8.2 is connected to the sub-baffles 8.1 and 8.3 on either side of it via additional baffle middle frames 4.4. This allows the cargo hold baffle in the cargo hold baffle 1 to achieve a modular structural design. When maintenance personnel need to maintain the cargo hold baffle, they only need to disassemble the relevant sub-baffles, such as sub-baffle 8.1, without disassembling the entire baffle as a single piece. This further reduces the maintenance cost of the baffle assembly 1 and improves maintenance convenience.

[0084] It should be noted that, in embodiments not shown in this invention, the baffle assembly 1 may include more or fewer sub-baffles as needed.

[0085] Figure 2 The baffle assembly 1 is shown from a rear view. As can be seen in the figure, a pressure relief port cover 10 for the pressure relief port 9 is provided on the rear side of the sub-baffle 8.1.

[0086] exist Figure 1 and Figure 2 It can also be noted that sub-baffles 8.1, 8.2, and 8.3 are connected to the upper frame 4.1, side frame 4.2, and lower frame 4.3 of the baffle via threaded connections consisting of bolts 8.4 and support nuts 8.5. Support nuts 8.5 are installed at the upper frame 4.1, side frame 4.2, and lower frame 4.3 of the baffle, respectively, while bolts 8.4 are screwed onto support nuts 9 through holes located at the sub-baffles 8.1, 8.2, and 8.3. This allows for the removal of sub-baffles 8.1, 8.2, and 8.3 simply by loosening or tightening the bolts 8.4 connecting the corresponding sub-baffle to its corresponding frame. This enables the rapid removal of the required sub-baffles without disassembling the baffle frame 4 during maintenance and disassembly of sub-baffles 8.1, 8.2, and 8.3. The same procedure applies to the installation of sub-baffles 8.1, 8.2, and 8.3.

[0087] Next, combine Figure 3The installation of the pressure relief port protective cover 10 is explained. As shown in the figure, the pressure relief port protective cover 10, located on the rear side of the sub-baffle 8.1, is in the form of a bent right-angled piece. The pressure relief port protective cover 10 is typically positioned away from the cargo in the cargo hold, particularly sharp or heavy cargo. In actual use of the baffle assembly 1, a sealing membrane (not shown in the figure) made of sealing material is installed at the pressure relief port 9 in the sub-baffle 8.1. This sealing membrane is designed to automatically rupture when the pressure difference across the baffle assembly 1 exceeds a preset threshold, thereby restoring the pressure balance across the baffle assembly 1, specifically the pressure relief port 9. The pressure relief port protective cover 10 is installed to protect the sealing membrane from rupture due to impacts from cargo in the cargo hold during normal use.

[0088] The pressure relief port protective cover 10 is fastened to the sub-baffle 8.1 at its upper and lower ends by threaded connections, such as screws. To enhance the support for the main body of the pressure relief port protective cover 10 and thus strengthen the protection of the sealing membrane in the pressure relief port 9, at least one short column-shaped support member 10.1 is provided on each side (specifically, on both sides of the long side) of the main body of the pressure relief port protective cover 10. In the illustrated embodiment, a total of four such support members 10.1 are provided, and the two ends of the support members 10.1 are respectively fastened to the peripheral area of ​​the pressure relief port 9 in the sub-baffle 8.1 and the main body of the pressure relief port protective cover 10.

[0089] Next, we will refer to Figures 4 to 7 The connection between the baffle assembly 1 of the present invention and the main structure of the aircraft is explained in detail.

[0090] First refer to Figures 4 to 6 The flexible connection 20 between the baffle assembly 1 and the cabin floor longitudinal beam 6 is shown at different angles.

[0091] The flexible connection 20 includes a connecting device. The connecting device includes a connecting corner box 21, a wear-resistant bushing 21.1, and a flexible connector 22.

[0092] The connecting corner box 21 includes a first side and a second side that are at an angle to each other. In the illustrated embodiment, the first side and the second side are at a 90° angle to each other. The first side has a receiving hole 21.2, in which a wear-resistant bushing 21.1 is embedded.

[0093] The flexible connector 22 includes a base 22.1 and a shaft 22.2 protruding from the base 22.1. The base 22.1 of the flexible connector 22 is connected to the bottom surface of the connecting strip plate 23 by bolts 23.1. The vertical edge of the connecting strip plate 23 is connected to the cabin floor longitudinal beam 6 by fasteners, transmitting forward loads to the main fuselage structure. The shaft 22.2 of the flexible connector 22 extends into the wear-resistant bushing 21.1 of the connecting corner box 21, achieving a flexible fit between the shaft 22.2 of the flexible connector 22 and the connecting corner box 21, allowing free sliding. In other words, the shaft 22.2 of the flexible connector 22 can move freely within the wear-resistant bushing 21.1 within a certain range along its axial direction (usually the vertical direction in aircraft use).

[0094] During aircraft operation, the baffles in the cargo hold baffle assembly 1 primarily bear forward loads (including impacts) along the direction of travel. Simultaneously, for passenger aircraft, the passenger and cargo hold experiences downward loads and deformations due to the inertial forces of carrying passengers and cargo. These loads and deformations are transmitted vertically downwards through the cabin floor longitudinal beams 6. In the flexible connection 20, without reducing the forward load bearing capacity, the flexible connection 22 allows for free sliding within a certain range along the axial direction relative to the connecting corner box 21, preventing vertical stress concentration at the connection between the cargo hold baffles and the cabin floor longitudinal beams 6 caused by passenger and cargo inertial forces.

[0095] To enhance the flexible connection 20 in terms of forward load and impact, the connection device also has a first reinforcing angle box 5.1 and a second reinforcing angle box 5.2 for directional reinforcement.

[0096] like Figure 4 As can be seen, the connecting corner box 21 is connected to the upper frame of the baffle 4.1 by bolts 21.3 on the second side adjacent to the first side having the receiving hole 21.2. In the illustrated embodiment, the upper frame of the baffle 4.1 is made of an I-beam. Figure 5 and Figure 6 As shown, a first reinforcing angle box 5.1 and a second reinforcing angle box 5.2 are respectively provided in the upper and lower grooves of the I-beam. The opening direction of the first reinforcing angle box 5.1 faces the heading direction of the aircraft and is opposite to the opening direction of the connecting angle box 21. The opening direction of the second reinforcing angle box 5.2 is similar to that of the first reinforcing angle box 5.1.

[0097] The first reinforcing angle box 5.1 and the second reinforcing angle box 5.2 are respectively bolted to the connecting angle box 21 5.3 on their first side, specifically to the second side of the connecting angle box. Furthermore, the first reinforcing angle box 5.1 and the second reinforcing angle box 5.2 are interconnected on their second sides, which are at an angle to the first side, by bolts 5.4 passing through the web of the I-beam of the upper upper frame 4.1 of the baffle. The arrangement of the first reinforcing angle box 5.1 and the second reinforcing angle box 5.2 strengthens the flexible connection 20, ensuring that the baffle assembly 1 can withstand forward loads and impacts that may be encountered during aircraft operation.

[0098] Finally, turn to Figure 7 The connection between the baffle assembly 1 and the cargo hold floor longitudinal beam 7 is shown. Figure 7 As shown, the bottom edge of the lower frame 4.3 of the baffle assembly 1 is fastened to the cargo hold floor longitudinal beam 7 via a threaded connection. The support nut 9 is installed at the inner edge of the cargo hold floor longitudinal beam 7. When installing the baffle assembly 1, the bolt 4.5 is passed through the hole located at the bottom edge of the lower frame 4.3 of the baffle and screwed into the support nut 9 at the cargo hold floor longitudinal beam 7 to achieve the connection between the baffle assembly 1 and the cargo hold floor longitudinal beam 7.

[0099] Similarly, during use, when it is necessary to replace or remove the lower baffle assembly 1, maintenance personnel only need to loosen the connection between the lower baffle assembly 1 and the main aircraft structure. Specifically, this means loosening the bolt 23.1 between the upper upper frame of the baffle and the longitudinal beam 6 of the cabin floor (specifically, loosening the bolt 23.1 between the flexible connector 22 and the connecting strip 23) and the threaded connection at the lower frame of the baffle 4.3 (specifically, loosening the bolt 4.5) to disassemble it; and vice versa. This allows for quick installation, repair, or replacement of the baffle assembly 1.

[0100] This invention proposes a connection structure for cargo hold baffles, which includes a flexible connection portion. This structure enables rapid installation between the cargo hold baffle and the main structure of the aircraft, and allows for quick maintenance and disassembly of the cargo hold baffle, with a simple installation and disassembly process. The flexible connection portion avoids vertical stress concentration at the connection point of the cargo hold baffle caused by the inertial forces of the aircraft carrying passengers and cargo.

[0101] Within the scope of this invention, various embodiments can be freely combined, or appropriately modified or omitted.

Claims

1. A connection structure for a cargo compartment bulkhead of an aircraft, the main structure of the aircraft comprising a passenger compartment floor stringer (6), characterized in that, The connecting structure comprises a connecting device connecting the passenger cabin floor longitudinal beam (6) and the cargo compartment bulkhead, such that the passenger cabin floor longitudinal beam (6) can move in a vertical direction relative to the cargo compartment bulkhead at the connecting structure, wherein the connecting device comprises a connecting corner box (21) and a flexible connecting piece (22), wherein the flexible connecting piece (22) is fastened to the passenger cabin floor longitudinal beam (6), and the connecting corner box (21) is fastened to the cargo compartment bulkhead, and the flexible connecting piece (22) cooperates with the connecting corner box (21) such that the flexible connecting piece (22) can move in a vertical direction relative to the connecting corner box.

2. The connection structure according to claim 1, wherein The flexible connecting piece (22) comprises a shaft portion (22.2) protruding from a base portion (22.1), and the connecting corner box (21) is provided with a guide portion guiding the shaft portion (22.2) to slide therein.

3. The connection structure according to claim 2, wherein The connecting corner box (21) is provided with a receiving hole (21.2) on a first side, and a wear-resistant bushing (21.1) is nested in the receiving hole, and the shaft portion (22.2) of the flexible connecting piece (22) extends into the wear-resistant bushing (21.1).

4. The connection structure according to any one of claims 1 to 3, wherein The connecting device further comprises at least one reinforcing corner box arranged to bear a non-vertical load.

5. A cargo compartment door assembly for an aircraft, comprising: A connecting structure for a cargo compartment bulkhead of an aircraft, comprising a cargo compartment bulkhead and any one of claims 1 to 4.

6. The cargo hold screen assembly (1) according to claim 5, characterized in that The cargo compartment bulkhead is composed of at least two sub-bulkheads (8.1, 8.2, 8.3), and the cargo compartment bulkhead has a bulkhead frame arranged on the outer periphery thereof, and the connecting structure for the cargo compartment bulkhead of the aircraft is used to connect the bulkhead frame with a passenger cabin floor longitudinal beam (6) of the aircraft.

7. A cargo hold baffle assembly (1) according to claim 5 or 6, characterized in that A pressure relief port (9) is arranged on the sub-bulkhead, and a pressure relief port protection cover (10) covering the pressure relief port (9) is arranged on one side of the sub-bulkhead.

8. A cargo hold baffle assembly (1) according to claim 7, characterized in that At least one bearing (10.1) is arranged between the pressure relief port protection cover (10) and the sub-bulkhead.

9. An aircraft comprising a cargo compartment bulkhead assembly (1) according to any one of claims 5 to 8, a passenger compartment floor stringer (6) and a cargo compartment floor stringer (7), wherein, The cargo compartment bulkhead and the cargo compartment floor longitudinal beam (7) are connected by means of a threaded fastener.

Images