Aircraft fuselage curved frame hoop bending moment load loading device and method thereof

Abstract

The present application belongs to the technical field of design for loading circumferential bending moment loads on aircraft fuselage curved frames, and specifically relates to a device and method for loading circumferential bending moment loads on aircraft fuselage curved frames, which utilizes the coordinated action of the extension and retraction of loading actuators located on the inner and outer sides of the aircraft fuselage curved frame to steadily apply circumferential bending moment loads to the aircraft fuselage curved frame through transmission beams and loading beams. During the loading process, the two transmission beams are suspended in the air and are in a free state, which can drive the two loading beams to rotate. Since the axes of the two loading beams connected to the edges of the aircraft fuselage curved frame on both sides are on the arc where the aircraft fuselage curved frame is located, the accuracy of the circumferential bending moment load loading on the aircraft fuselage curved frame can be guaranteed. Compared with the four-point bending loading method, it can effectively avoid the stress concentration in the local area of ​​the aircraft fuselage curved frame and the premature failure.

Description

Technical Field

[0001] The present application belongs to the technical field of design for loading hoop bending moment loads on curved frames of aircraft fuselages, and in particular relates to a device and method for loading hoop bending moment loads on curved frames of aircraft fuselages. Background Art

[0002] The aircraft fuselage curved frame is an important component of the fuselage frame structure. It is responsible for maintaining the fuselage shape and providing support for the fuselage skin. In practice, it withstands large circumferential bending moment loads, including positive bending loads with tension on the outside and compression on the inside, and negative bending loads with compression on the outside and tension on the inside.

[0003] Currently, in order to evaluate the aircraft fuselage curved frame, a circumferential bending moment load test for the aircraft fuselage curved frame is designed. During the test, a circumferential bending moment load is applied to the aircraft fuselage curved frame using a testing machine based on a four-point bending loading method. This technical solution has the following drawbacks:

[0004] 1) The four-point bending loading method will cause stress concentration at the two middle load application points, resulting in premature failure of the corresponding areas on the aircraft fuselage curved frame, making it difficult to achieve the test purpose;

[0005] 2) Due to the limitation of the column-type structure of the test machine, only the circumferential bending moment load loading test of the aircraft fuselage curved frame with small size and small load can be carried out. In addition, the space is limited, the force arm for applying the load is small, the accuracy control of the load application is poor, and it is difficult to apply the anti-instability device. As a result, the aircraft fuselage curved frame is prone to unexpected failure during the test, making it difficult to complete the test smoothly.

[0006] This application is proposed in view of the above-mentioned technical defects.

[0007] It should be noted that the disclosure of the above background technology content is only used to assist in understanding the inventive concept and technical solution of the present invention, and it does not necessarily belong to the prior art of this patent application. In the absence of clear evidence that the above content has been disclosed on the filing date of this application, the above background technology should not be used to evaluate the novelty and creativity of this application. Summary of the Invention

[0008] The purpose of the present application is to provide a device and method for loading circumferential bending moment loads on a curved frame of an aircraft fuselage, so as to overcome or alleviate at least one of the existing technical deficiencies.

[0009] The technical solution of this application is:

[0010] On the one hand, a device for loading a circumferential bending moment load on a curved frame of an aircraft fuselage is provided, comprising:

[0011] Support seat;

[0012] Two fixed end pillars connected to the support base;

[0013] Two hinged end supports, hinged to the support base;

[0014] Two loading beams, wherein one loading beam is hinged between two fixed end struts and connected to an edge of one side of the aircraft fuselage curved frame, with its axis lying on the arc of the aircraft fuselage curved frame; the other loading beam is hinged between two hinged end struts and connected to an edge of the other side of the aircraft fuselage curved frame, with its axis lying on the arc of the aircraft fuselage curved frame;

[0015] Two transmission beams, each transmission beam is connected to a corresponding loading beam;

[0016] Two loading actuators are hinged between the two transmission beams, wherein one loading actuator is located outside the aircraft fuselage curved frame, and the other loading actuator is located inside the aircraft fuselage curved frame.

[0017] According to at least one embodiment of the present application, the aforementioned aircraft fuselage curved frame hoop bending moment load loading device further includes:

[0018] Two adapters are provided with adapter grooves; each adapter is correspondingly connected to a loading beam, and the adapter groove is clamped on the edge of the corresponding side of the aircraft fuselage curved frame.

[0019] According to at least one embodiment of the present application, the aforementioned aircraft fuselage curved frame hoop bending moment load loading device further includes:

[0020] Two mounts;

[0021] The aircraft fuselage curved frame hoop bending moment load loading device has:

[0022] In the installed state, each mounting seat is connected between a transmission beam and a support seat;

[0023] In the test state, each mounting seat is separated from the corresponding transmission beam and / or support seat.

[0024] According to at least one embodiment of the present application, the aforementioned aircraft fuselage curved frame hoop bending moment load loading device further includes:

[0025] Two adapters, each adapter is connected to a loading beam and connected to the corresponding transmission beam. When the aircraft fuselage curved frame circumferential bending moment load loading device is in the installed state, the transmission beam is perpendicular to the support seat.

[0026] According to at least one embodiment of the present application, the aforementioned aircraft fuselage curved frame hoop bending moment load loading device further includes:

[0027] A lateral support, connected to the support base;

[0028] The lateral support rod is connected to the lateral pillar, and one end thereof is axially pressed against the aircraft fuselage curved frame.

[0029] According to at least one embodiment of the present application, in the aforementioned aircraft fuselage curved frame hoop bending moment load loading device, the lateral support rod is threadedly connected to the lateral strut.

[0030] According to at least one embodiment of the present application, in the aforementioned aircraft fuselage curved frame hoop bending moment load loading device, there are a plurality of lateral struts and their corresponding lateral support rods.

[0031] According to at least one embodiment of the present application, in the aforementioned aircraft fuselage curved frame hoop bending moment load loading device, both ends of the two loading beams have hinge holes;

[0032] The two fixed end pillars are provided with fixed end support holes;

[0033] The two hinged end pillars are provided with hinged end support holes;

[0034] The aircraft fuselage curved frame hoop bending moment load loading device also includes:

[0035] Two fixed end support shafts, each fixed end support shaft is correspondingly arranged in a fixed end support hole and inserted into the support hole at the corresponding end of the corresponding loading beam;

[0036] Two hinged end support shafts, each hinged end support shaft is correspondingly arranged in a hinged end support hole and inserted into the support hole at the corresponding end of the corresponding loading beam.

[0037] According to at least one embodiment of the present application, the aforementioned aircraft fuselage curved frame hoop bending moment load loading device further includes:

[0038] Two fixed end support bearings, each fixed end support bearing is sleeved on a fixed end support shaft and installed in a corresponding fixed end support hole;

[0039] Two hinged end support bearings, each hinged end support bearing is correspondingly sleeved on a hinged end support shaft and installed in a corresponding hinged end support hole.

[0040] Another aspect provides a method for applying a circumferential bending moment load to a curved frame of an aircraft fuselage, comprising:

[0041] In the installation state, the aircraft fuselage curved frame hoop bending moment load loading device is assembled with the aircraft fuselage curved frame;

[0042] Under the test state, the aircraft fuselage curved frame circular bending moment load is applied to the aircraft fuselage curved frame using the aircraft fuselage curved frame circular bending moment load loading device, wherein,

[0043] When a positive bending load is applied to the aircraft fuselage curved frame, the loading actuator located on the inner side of the aircraft fuselage curved frame contracts, and the loading actuator located on the outer side of the aircraft fuselage curved frame extends;

[0044] When a reverse bending load is applied to the aircraft fuselage curved frame, the loading actuator cylinder located on the outside of the aircraft fuselage curved frame contracts, and the loading actuator cylinder located on the inside of the aircraft fuselage curved frame extends.

[0045] This application has at least the following beneficial technical effects:

[0046] Provided are a device and method for loading a circumferential bending moment load on a curved frame of an aircraft fuselage. The device utilizes the coordinated telescopic action of loading actuators located on the inner and outer sides of the curved frame to steadily apply a circumferential bending moment load to the curved frame of the aircraft fuselage via a transmission beam and a loading beam. During the loading process, the two transmission beams are suspended in the air and in a free state, driving the two loading beams to rotate. Since the axes of the two loading beams connected to the edges of the curved frame of the aircraft fuselage are located on the arc of the curved frame, the accuracy of loading the circumferential bending moment load on the curved frame of the aircraft fuselage can be ensured. Compared with a four-point bending loading method, the device can effectively avoid the formation of stress concentration in local areas of the curved frame of the aircraft fuselage, thereby preventing premature damage. BRIEF DESCRIPTION OF THE DRAWINGS

[0047] Figure 1 1 is a schematic diagram of an aircraft fuselage curved frame hoop bending moment load loading device in an installed state provided by an embodiment of the present application;

[0048] Figure 2 This is a partial schematic diagram of a device for loading circumferential bending moment loads on a curved frame of an aircraft fuselage provided in an embodiment of the present application;

[0049] Figure 3 Schematic diagram of a device for applying a circumferential bending moment load to a curved frame of an aircraft fuselage provided by an embodiment of the present application applying a positive bending load to the curved frame of the aircraft fuselage;

[0050] Figure 4 Schematic diagram of the aircraft fuselage curved frame hoop bending moment load loading device provided in an embodiment of the present application applying a reverse bending load to the aircraft fuselage curved frame;

[0051] in:

[0052] 1-Support seat; 2-Fixed end support pillar; 3-Hinged end support pillar; 4-Loading beam; 5-Aircraft fuselage curved frame; 6-Transmission beam; 7-Loading actuator; 8-Adapter seat; 9-Mounting seat; 10-Adapter; 11-Lateral support pillar; 12-Lateral support rod; 13-Fixed end support shaft; 14-Hinged end support shaft; 15-Fixed end support bearing; 16-Hinged end support bearing.

[0053] In order to better illustrate this embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be understood as limitations on this patent. DETAILED DESCRIPTION

[0054] To make the technical solution and its advantages of the present application clearer, the technical solution of the present application will be described in further detail below in conjunction with the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of the present application and are only used to explain the present application, not to limit the present application. It should be noted that, for ease of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design. In the absence of conflict, the embodiments of the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0055] In addition, unless otherwise defined, the technical or scientific terms used in the description of this application should have the ordinary meanings understood by those of ordinary skill in the art to which this application belongs. The words "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer" used in the description of this application are only used to indicate relative directions or positional relationships, and do not imply that the device or component must have a specific orientation, be constructed, or operate in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. Therefore, they should not be understood as limitations on this application. The words "first," "second," "third," and similar terms used in the description of this application are used only for descriptive purposes to distinguish different components and should not be understood to indicate or imply relative importance. The words "one," "an," or "the" used in the description of this application should not be understood as absolute limitations on quantity, but should be understood as meaning the presence of at least one. The words "include" or "comprises" used in the description of this application mean that the element or object listed before the word includes the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0056] In addition, it should be noted that, unless otherwise clearly stipulated and limited, the words "install", "connect", "connect" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, an indirect connection through an intermediate medium, or a connection between two components. Technical personnel in the field can understand their specific meanings in this application according to the specific circumstances.

[0057] The following is combined with Figures 1 to 4 This application is described in further detail.

[0058] On the one hand, a device for loading circumferential bending moment loads on a curved frame of an aircraft fuselage is provided. Figure 1 As shown, including:

[0059] Support seat 1;

[0060] Two fixed end pillars 2 are connected to the support base 1;

[0061] Two hinged end supports 3 are hinged on the support base 1;

[0062] Two loading beams 4, wherein one loading beam 4 is hinged between the two fixed-end struts 2 and connected to the edge of one side of the aircraft fuselage curved frame 5, with its axis lying on the arc where the aircraft fuselage curved frame 5 is located; the other loading beam 4 is hinged between the two hinged-end struts 3 and connected to the edge of the other side of the aircraft fuselage curved frame 5, with its axis lying on the arc where the aircraft fuselage curved frame 5 is located;

[0063] Two transmission beams 6, each transmission beam 6 is connected to a corresponding loading beam 4;

[0064] Two loading actuator cylinders 7 are hinged between the two transmission beams 6 , wherein one loading actuator cylinder 7 is located outside the aircraft fuselage curved frame 5 , and the other loading actuator cylinder 7 is located inside the aircraft fuselage curved frame 5 .

[0065] The aircraft fuselage curved frame hoop bending moment load loading device disclosed in the above embodiment can be used to apply a hoop bending moment load to the aircraft fuselage curved frame 5, wherein:

[0066] When a positive bending load is applied to the aircraft fuselage curved frame 5, the loading actuator cylinder 7 located inside the aircraft fuselage curved frame 5 contracts, and the loading actuator cylinder 7 located outside the aircraft fuselage curved frame 5 extends. Figure 3 As shown;

[0067] When a reverse bending load is applied to the aircraft fuselage curved frame 5, the loading actuator cylinder 7 located outside the aircraft fuselage curved frame 5 contracts, and the loading actuator cylinder 7 located inside the aircraft fuselage curved frame 5 extends. Figure 4 shown.

[0068] As for the aircraft fuselage curved frame circumferential bending moment load loading device disclosed in the above embodiment, it can be understood by those skilled in the art that it utilizes the coordinated action of the extension and retraction of the loading actuator 7 located on the inner and outer sides of the aircraft fuselage curved frame 5 to steadily apply the circumferential bending moment load to the aircraft fuselage curved frame 5 through the transmission beam 6 and the loading beam 4. During the loading process, the two transmission beams 6 are suspended in the air and are in a free state, which can drive the two loading beams 4 to rotate. Since the axes of the two loading beams 4 connected to the edges of the aircraft fuselage curved frame 5 on both sides are on the arc where the aircraft fuselage curved frame 5 is located, the accuracy of the circumferential bending moment load loading on the aircraft fuselage curved frame 5 can be guaranteed. Compared with the four-point bending loading method, it can effectively avoid the stress concentration in the local area of ​​the aircraft fuselage curved frame and the premature failure.

[0069] For the aircraft fuselage curved frame circumferential bending moment load loading device disclosed in the above embodiment, technical personnel in the field can also understand that when the circumferential bending moment load is applied to the aircraft fuselage curved frame 5, two fixed end struts 2 and hinged end struts 3 are connected to the two ends of the two loading beams 4, and the two loading beams 4 and their transmission beams 6 and the aircraft fuselage curved frame 5 are supported on the support seat 1 to achieve support for the entire load loading structure, and the two hinged end struts 3 are hinged between a loading beam 4 and the support seat 1, and have rotational freedom. When the aircraft fuselage curved frame 5 is deformed by the circumferential bending moment load, it can rotate accordingly to achieve follow-up support for the structure without affecting the accuracy of the circumferential bending moment load loading on the aircraft fuselage curved frame 5.

[0070] In some optional embodiments, the aforementioned aircraft fuselage curved frame hoop bending moment load loading device further comprises:

[0071] Two adapters 8 have adapter grooves; each adapter 8 is connected to a corresponding loading beam 4, and the adapter groove on it is stuck on the edge of the corresponding side of the aircraft fuselage curved frame 5, and can be connected by bolts.

[0072] In some optional embodiments, the aforementioned aircraft fuselage curved frame hoop bending moment load loading device further comprises:

[0073] Two mounting seats 9;

[0074] The aircraft fuselage curved frame hoop bending moment load loading device has:

[0075] In the installed state, each mounting seat 9 is connected between a transmission beam 6 and a support seat 1;

[0076] In the test state, each mounting seat 9 is separated from the corresponding transmission beam 6 and / or support seat 1 .

[0077] As for the aircraft fuselage curved frame circumferential bending moment load loading device disclosed in the above-mentioned embodiment, it can be understood by those skilled in the art that the aircraft fuselage curved frame circumferential bending moment load loading device is designed to have an installation state and a test state. When the aircraft fuselage curved frame circumferential bending moment load loading device is in the installation state, each mounting seat 9 is correspondingly connected between a transmission beam 6 and a support seat 1, and the corresponding transmission beam 6 can be fixed on the support seat 1 to realize the positioning of the transmission beam 6 on the support seat 1, which is convenient for assembling the overall structure. When the aircraft fuselage curved frame circumferential bending moment load loading device is in the installation state, each mounting seat 9 is separated from the corresponding transmission beam 6 and / or support seat 1, that is, the fixation between the corresponding transmission beam 6 and the support seat 1 is released, and no interference is caused to the movement of the transmission beam 6, thereby ensuring the accuracy of the circumferential bending moment load loading on the aircraft fuselage curved frame 5.

[0078] In some optional embodiments, the aforementioned aircraft fuselage curved frame hoop bending moment load loading device further comprises:

[0079] There are two adapters 10, each adapter 10 is connected to a loading beam 4 and a corresponding transmission beam 6. When the aircraft fuselage curved frame circumferential bending moment load loading device is in the installed state, the transmission beam 6 is perpendicular to the support seat 1 to facilitate the assembly of the overall structure.

[0080] In some optional embodiments, the aforementioned aircraft fuselage curved frame hoop bending moment load loading device further comprises:

[0081] Lateral support 11, connected to the support base 1;

[0082] The lateral support rod 12 is connected to the lateral pillar 11, and one end thereof is axially pressed against the aircraft fuselage curved frame 5 to prevent the aircraft fuselage curved frame 5 from becoming unstable during the loading process of the circumferential bending moment load.

[0083] In some optional embodiments, in the above-mentioned aircraft fuselage curved frame circumferential bending moment load loading device, the lateral support rod 12 is threadedly connected to the lateral pillar 11, so that the end thereof facing the aircraft fuselage curved frame 5 can be adjusted to properly rest axially against the aircraft fuselage curved frame 5, thereby preventing the aircraft fuselage curved frame 5 from becoming unstable during the circumferential bending moment load loading process and avoiding affecting the accuracy of the circumferential bending moment load loading on the aircraft fuselage curved frame 5.

[0084] In some optional embodiments, in the above-mentioned aircraft fuselage curved frame circumferential bending moment load loading device, there are multiple lateral struts 11 and their corresponding lateral support rods 12. The specific number and distribution positions of the lateral support struts 11 and 12 can be set by relevant technical personnel according to specific actual conditions when applying the technical solution disclosed in this application, and no more detailed description will be given here.

[0085] In some optional embodiments, in the above-mentioned aircraft fuselage curved frame hoop bending moment load loading device, both ends of the two loading beams 4 have hinge holes;

[0086] The two fixed end pillars 2 are provided with fixed end support holes;

[0087] The two hinged end pillars 3 are provided with hinged end support holes;

[0088] The aircraft fuselage curved frame hoop bending moment load loading device also includes:

[0089] Two fixed end support shafts 13, each fixed end support shaft 13 is correspondingly arranged in a fixed end support hole and inserted into the support hole at the corresponding end of the corresponding loading beam 4;

[0090] Two hinged end support shafts 14 , each hinged end support shaft 14 is correspondingly arranged in a hinged end support hole, and inserted into the support hole at the corresponding end of the corresponding loading beam 4 .

[0091] In some optional embodiments, the aforementioned aircraft fuselage curved frame hoop bending moment load loading device further comprises:

[0092] Two fixed end support bearings 15, each fixed end support bearing 15 is sleeved on a corresponding fixed end support shaft 13 and installed in the corresponding fixed end support hole;

[0093] Two hinged end support bearings 16 , each hinged end support bearing 16 is correspondingly sleeved on a hinged end support shaft 14 and installed in a corresponding hinged end support hole.

[0094] Another aspect provides a method for applying a circumferential bending moment load to a curved frame of an aircraft fuselage, comprising:

[0095] In the installation state, the aircraft fuselage curved frame hoop bending moment load loading device is assembled with the aircraft fuselage curved frame 5;

[0096] Under the test state, the aircraft fuselage curved frame circumferential bending moment load is applied to the aircraft fuselage curved frame 5 by using the aircraft fuselage curved frame circumferential bending moment load loading device, wherein:

[0097] When a positive bending load is applied to the aircraft fuselage curved frame 5, the loading actuator cylinder 7 located inside the aircraft fuselage curved frame 5 contracts, and the loading actuator cylinder 7 located outside the aircraft fuselage curved frame 5 extends;

[0098] When a reverse bending load is applied to the aircraft fuselage curved frame 5 , the loading ram 7 located outside the aircraft fuselage curved frame 5 contracts, and the loading ram 7 located inside the aircraft fuselage curved frame 5 extends.

[0099] As for the method for loading the circumferential bending moment load on the curved frame of an aircraft fuselage disclosed in the above-mentioned embodiment, those skilled in the art will understand that it is based on the implementation of the circumferential bending moment load loading on the curved frame of an aircraft fuselage disclosed in the above-mentioned embodiment, and the description is relatively simple. For specific related matters, please refer to the relevant description of the circumferential bending moment load loading device for the curved frame of an aircraft fuselage. Its technical effects can also refer to the technical effects of the relevant parts of the circumferential bending moment load loading device for the curved frame of an aircraft fuselage, and will not be repeated here.

[0100] The various embodiments in the specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to in detail.

[0101] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or replacements to the relevant technical features, and the technical solutions after these changes or replacements will fall within the scope of protection of the present application.

Claims

1. A device for loading hoop bending moment loads on a curved frame of an aircraft fuselage, characterized in that: include: Support seat (1); Two fixed end pillars (2) connected to the support base (1); Two hinged end supports (3) hinged on the support base (1); Two loading beams (4), wherein one loading beam (4) is hinged between the two fixed end struts (2), connected to the edge of one side of the aircraft fuselage curved frame (5), and its axis is located on the arc where the aircraft fuselage curved frame (5) is located; the other loading beam (4) is hinged between the two hinged end struts (3), connected to the edge of the other side of the aircraft fuselage curved frame (5), and its axis is located on the arc where the aircraft fuselage curved frame (5) is located; Two transmission beams (6), each transmission beam (6) being connected to a corresponding loading beam (4); Two loading actuators (7) are hinged between the two transmission beams (6), wherein one loading actuator (7) is located outside the aircraft fuselage curved frame (5), and the other loading actuator (7) is located inside the aircraft fuselage curved frame (5); Two adapter seats (8) having adapter slots; each adapter seat (8) is connected to a corresponding loading beam (4), and the adapter slot is clamped on the edge of the corresponding side of the aircraft fuselage curved frame (5); two mounting seats (9); The aircraft fuselage curved frame hoop bending moment load loading device comprises: In the installed state, each of the mounting seats (9) is correspondingly connected between one of the transmission beams (6) and the support seat (1); In the test state, each of the mounting seats (9) is separated from the corresponding transmission beam (6) and / or support seat (1); Also includes: Two adapters (10), each of the adapters (10) is connected to a corresponding loading beam (4) and connected to a corresponding transmission beam (6), so that when the aircraft fuselage curved frame annular bending moment load loading device is in the installed state, the transmission beam (6) is perpendicular to the support seat (1).

2. The device for loading hoop bending moment loads on a curved frame of an aircraft fuselage according to claim 1, characterized in that: Also includes: A lateral support (11) connected to the support base (1); A lateral support rod (12) is connected to the lateral support column (11), and one end of the lateral support rod rests axially on the aircraft fuselage curved frame (5).

3. The device for loading hoop bending moment loads on a curved frame of an aircraft fuselage according to claim 2, characterized in that: The lateral support rod (12) is threadedly connected to the lateral support column (11).

4. The device for loading hoop bending moment loads on a curved frame of an aircraft fuselage according to claim 3, characterized in that: There are a plurality of lateral pillars (11) and corresponding lateral support rods (12).

5. The aircraft fuselage curved frame hoop bending moment load loading device according to claim 4, characterized in that: Both ends of the two loading beams (4) have hinge holes; The two fixed end pillars (2) are provided with fixed end support holes; The two hinged end pillars (3) are provided with hinged end support holes; The aircraft fuselage curved frame hoop bending moment load loading device further comprises: Two fixed end support shafts (13), each of the fixed end support shafts (13) is correspondingly arranged in one of the fixed end support holes and inserted into the support hole at the corresponding end of the corresponding loading beam (4); Two hinged end support shafts (14), each hinged end support shaft (14) is correspondingly arranged in one hinged end support hole and inserted into the support hole at the corresponding end of the corresponding loading beam (4).

6. The aircraft fuselage curved frame hoop bending moment load loading device according to claim 5, characterized in that: Also includes: Two fixed end support bearings (15), each of the fixed end support bearings (15) is sleeved on a corresponding fixed end support shaft (13) and installed in a corresponding fixed end support hole; Two hinged end support bearings (16), each hinged end support bearing (16) is sleeved on a corresponding hinged end support shaft (14) and installed in a corresponding hinged end support hole.

7. A method for loading hoop bending moment load on a curved frame of an aircraft fuselage, characterized in that: include: In the installed state, the aircraft fuselage curved frame hoop bending moment load loading device according to claim 6 is assembled with the aircraft fuselage curved frame (5); Under the test state, a circumferential bending moment load is applied to the aircraft fuselage curved frame (5) using an aircraft fuselage curved frame circumferential bending moment load loading device, wherein: When a positive bending load is applied to the aircraft fuselage curved frame (5), the loading actuator cylinder (7) located inside the aircraft fuselage curved frame (5) contracts, and the loading actuator cylinder (7) located outside the aircraft fuselage curved frame (5) extends; When a reverse bending load is applied to the aircraft fuselage curved frame (5), the loading actuator cylinder (7) located outside the aircraft fuselage curved frame (5) contracts, and the loading actuator cylinder (7) located inside the aircraft fuselage curved frame (5) extends.

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