CN205203348U - Aircraft frame roof beam attach fitting and have its aircraft frame roof beam - Google Patents

Abstract

The utility model discloses an aircraft frame girder connection joint and an aircraft frame girder with the same, belonging to the field of aircraft structure design. The connecting joint is used to connect the upper frame section, the lower frame section, the side beam and the main thrust pin of the engine at the intersection of the frame beam of the aircraft, which mainly includes the connecting hole of the main thrust pin of the engine, the first connection end, the second connection end and the third connection The first connecting end, the second connecting end and the third connecting end are arranged radially on the side wall of the connecting hole of the main thrust pin of the engine, wherein the connecting hole of the main thrust pin of the engine is used to connect the main thrust pin of the engine Thrust pin, the first connecting end is used to connect the upper frame segment or the lower frame segment, the second connecting end is used to connect another frame segment not connected to the first connecting end, and the third connecting end is used to connect the side beam, through The utility model reduces the number of connecting pieces when the traditional corner boxes are connected, achieves the weight reduction effect, and makes the force transmission route more direct, which is beneficial to the load transmission.

Description

Aircraft frame-beam connecting joint and aircraft frame-beam having same

technical field

The utility model belongs to the field of aircraft structure design, in particular to an aircraft frame girder connecting joint and an aircraft frame girder having the same.

Background technique

The connecting parts at the intersection of aircraft frame and girder play an important role in the overall structure of the aircraft. During the design process, it is necessary to realize the tight connection of the structure and the effective transmission of loads. For example, at the end of the main thrust pin of the engine, it needs to be connected by a connecting part. Connect with other frames and beams of the aircraft.

In the prior art, the intersection of aircraft frame and girder mostly uses several corner boxes to realize the connection of structures and the transmission of loads. Due to the large number of corner boxes used in this type of structural connection, high processing and assembly accuracy is required at the joint between the corner box and the multi-faceted structure. There are many fasteners, heavy weight, and poor installation and maintenance.

Utility model content

In order to solve the above problems, the utility model proposes an aircraft frame girder connecting joint and an aircraft frame girder with it, the connecting joint is used to connect the upper frame section, the lower frame section, the side beam and the engine at the intersection of the aircraft frame beam The main thrust pin mainly includes the main thrust pin connection hole of the engine, the first connection end, the second connection end and the third connection end, and the first connection end, the second connection end and the third connection end are arranged radially on the On the side wall of the engine main thrust pin connection hole, wherein the engine main thrust pin connection hole is used to connect the engine main thrust pin, the first connection end is used to connect the upper frame section or the lower frame section, and the second connection end is used for Connect a frame segment that is not connected to the first connecting end, the second connecting end is separated from the first connecting end by 180° in the circumferential direction of the main thrust pin connecting hole of the engine, and the third connecting end is used for connecting As for the side beam, the third connecting end is arranged between the first connecting end and the second connecting end, and is connected with the first connecting end and the second connecting end respectively along the periphery of the connecting hole of the main thrust pin of the engine. 90° apart.

Preferably, the first connection end has the same structure as the second connection end.

In the above solution, preferably, the first connection end includes a web, an inner edge strip and an outer edge strip, the inner edge strip and the outer edge strip are arranged in parallel, and the web is arranged between the inner edge strip and the outer edge strip. Between the outer edge strips, and perpendicular to the inner edge strips and the outer edge strips, the inner edge strips and/or outer edge strips are separated from the inner edge strips and/or the outer edge strips at the end far away from the connecting hole of the main thrust pin of the engine. Or the outer edge strip shrinks to the web to form a step, the step is provided with a belt plate, one end of the belt plate is fastened to the inner edge strip or the outer edge strip, and the other end is connected to the upper frame section or the lower frame section. Frame connection.

In the above solution, preferably, one end of the belt plate is pinned to the inner edge strip or the outer edge strip.

In the above solution, preferably, the third connecting end includes a side web and at least one side edge bar, one end of the side web is vertically connected to one end of the side edge bar, and one end of the side beam is tightly connected to the side edge. It is fixed on the side web and at least one side edge strip.

In the above solution, preferably, one end of the side beam is connected to the side web with pins.

The utility model also provides an aircraft frame girder, which includes the above-mentioned aircraft frame girder connecting joint.

The aircraft frame-beam connection joint of the utility model adopts a cross-beam type centralized connection joint, and the cross-beam type centralized connection joint structure is adopted, which is beneficial to the integration of the structure, reduces the number of connecting parts, and realizes weight reduction. The force transmission route is more direct, which is conducive to load transmission. Compared with the corner box connection structure, the processing and assembly accuracy of the mating surface is reduced, and it is also conducive to the realization of technology and assembly.

Description of drawings

Fig. 1 is a structural schematic diagram of a preferred embodiment of the aircraft frame-girder connection joint of the present invention.

Fig. 2 is a schematic diagram of the connection between the frame and the beam of the embodiment shown in Fig. 1 and the connecting joint between the frame and beam of the aircraft.

FIG. 3 is a schematic diagram of connections at the frame segments of the embodiment shown in FIG. 1 .

Fig. 4 is a schematic diagram of connection at the side beams of the embodiment shown in Fig. 1 .

Among them, 1 is the connection joint, 2 is the belt plate, 3 is the upper frame section, 4 is the lower frame section, 5 is the side beam, 11 is the connecting hole of the main thrust pin of the engine, 12 is the first connection end, and 13 is the second connection 14 is the third connecting end, 121 is a web, 122 is an inner edge strip, 123 is an outer edge strip, 124 is a step, 141 is a side web, and 142 is a side edge strip.

detailed description

In order to make the purpose, technical solutions and advantages of the utility model more clear, the technical solution in the utility model embodiment will be described in more detail below in conjunction with the accompanying drawings in the utility model embodiment. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some embodiments of the present utility model, but not all embodiments. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention, but should not be construed as limiting the present invention. Based on the embodiments of the present utility model, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the scope of protection of the present utility model. Embodiments of the utility model are described in detail below in conjunction with the accompanying drawings.

In describing the present invention, it should be understood that the terms "central", "longitudinal", "transverse", "front", "rear", "left", "right", "vertical", "horizontal" , "top", "bottom", "inner", "outer" and other indicated orientations or positional relationships are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the utility model and simplifying the description, rather than indicating or It should not be construed as limiting the protection scope of the present invention by implying that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation.

The utility model firstly provides an aircraft frame-beam connecting joint, which is used to connect the upper frame section 3, the lower frame section 4, the side beam 5 and the main thrust pin of the engine at the intersection of the aircraft frame-beam, as shown in Figure 2, its main It constitutes a connecting joint 1 which is integrally machined. The specific structure of the connecting joint 1 is shown in FIG. The connection end 14, the first connection end 12, the second connection end 13 and the third connection end 14 are arranged radially on the side wall of the connecting hole 11 of the main thrust pin of the engine, wherein the main thrust pin of the engine is connected to The hole 11 is used to connect the main thrust pin of the engine, the first connecting end 12 is used to connect the upper frame segment 3 or the lower frame segment 4, and the second connecting end 13 is used to connect a frame segment not connected to the first connecting end 12, The third connecting end 14 is used for connecting the side beam 5 .

It can be understood that when the first connecting end 12 is used to connect the upper frame segment 3, the second connecting end 13 is connected to the lower frame segment 4, and vice versa.

It should be noted that, the second connecting end 13 is separated from the first connecting end 12 by 180° in the circumferential direction of the main thrust pin connecting hole 11 of the engine, and the third connecting end 14 is arranged on the first connecting end 12 . Between the connecting end 12 and the second connecting end 13 , and apart from the first connecting end 12 and the second connecting end 13 along the circumferential direction of the main thrust pin connecting hole 11 of the engine, there is a distance of 90°.

In this embodiment, the structural shapes of the first connecting end 12, the second connecting end 13 and the third connecting end 14 are adapted to the connecting parts, for example, when the first connecting end 12 When connected to the upper frame segment 3, it adapts to the structural shape of the upper frame segment 3 at the connection point. As an alternative implementation of this embodiment, the first connecting end 12 and the second connecting end 13 have the same structure.

Under the above circumstances, this embodiment takes the first connecting end 12 as a specific embodiment for description. As shown in FIG. The inner edge strip 122 is arranged parallel to the outer edge strip 123, and the web 121 is arranged between the inner edge strip 122 and the outer edge strip 123, and is perpendicular to the inner edge strip 122 and the outer edge strip 123, so The inner edge strip 122 and/or the outer edge strip 123 shrinks from the inner edge strip 122 and/or the outer edge strip 123 to the web 121 at the end away from the connecting hole 11 of the main thrust pin of the engine to form a step 124, so A belt plate 2 is provided at the step 124 , one end of the belt plate 2 is fastened to the inner edge strip 122 or the outer edge strip 123 , and the other end is connected to the upper frame section 3 or the lower frame section 4 .

Referring to Fig. 2 again, when the upper and lower frame sections are connected together by the connection joint 1, a closed ring structure is formed, at this time, the inner edge strip 122 is located on the inner wall of the ring, and the inner edge strip 122 is located on the outer wall of the ring. Outer edge strip 123, the right part in Fig. 2 has provided an alternative embodiment, promptly is provided with belt plate 2 at the inner edge strip 122 place, has provided another embodiment in the left part in Fig. 2 and Fig. 3 , that is, a belt plate 2 is provided at the outer edge strip 123. Referring to FIG. 3, the belt plate 2 is loaded at the outer edge strip 123 as an example. When extending in the direction at 12, a section is recessed to the inside to form a step 124. Like this, a part of the band plate 2 can be placed at the step 124, and the thickness of the band plate 2 is the same as the depth of the depression, so that the band plate 2 just complements Throughout the entire connecting piece, it can be understood that the other part of the belt plate 2 extends to the upper frame section 3, because a suitable step is also recessed inwardly at the upper frame section 3, for placing the belt plate 2 one end.

After the belt plate 2 is placed in the depression, one end of the belt plate 2 is fastened to the inner edge strip 122 or the outer edge strip 123 , such as pin connection, screw connection and the like.

In this embodiment, the third connecting end 14 includes a side web 141 and at least one side edge strip 142, one end of the side web 141 is vertically connected to one end of the side edge strip 142, which is determined by the Determined by the structure of the side beam 5, as shown in Figure 4, the cross-section of the side beam 5 at the junction with the connecting joint 1 is an L-shaped structure, which consists of two panels perpendicular to each other, so that when When the third connection end 14 includes the same L-shaped connection structure, it is more suitable for fastening connection with each other. As an alternative implementation of this embodiment, as shown in FIG. 4, the third connection end 14 includes The two side edge strips 142 are respectively vertically arranged on the two sides of the side web 141 . One end of the side beam 5 is fastened to the side web 141 and at least one side edge strip 142 .

In this embodiment, one end of the side beam 5 is pinned to the side web 141 , or connected by other fasteners such as bolts.

The utility model also provides an aircraft frame beam, including the above-mentioned aircraft frame beam connecting joint 1, as shown in Figure 2, it also includes an upper frame section 3, a lower frame section 4, a side beam 5 and an engine main thrust Pin, wherein the upper frame section 3 and the lower frame section 4 are connected on the same straight line, the side beam 5 is perpendicular to the straight line, and the main thrust pin of the engine is perpendicular to the structure formed by the upper frame section 3, the lower frame section 4 and the side beam 5 flat.

The aircraft frame-beam connection joint of the utility model adopts a cross-beam type centralized connection joint, and the cross-beam type centralized connection joint structure is adopted, which is beneficial to the integration of the structure, reduces the number of connecting parts, and realizes weight reduction. The force transmission route is more direct, which is conducive to load transmission. Compared with the corner box connection structure, the processing and assembly accuracy of the mating surface is reduced, and it is also conducive to the realization of technology and assembly.

In addition, it should be noted that when processing the connection joint 1, its structural parameters need to be determined according to the load; after that, determine the number of bolts connected to the upper frame section 3, lower frame section 4, and side beam 5 to determine the length of the connection area.

Finally, it should be pointed out that the above embodiments are only used to illustrate the technical solution of the present utility model, rather than to limit it. Although the utility model has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that: it can still modify the technical solutions described in the aforementioned embodiments, or perform equivalent replacements for some of the technical features; and These modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the various embodiments of the present invention.

Claims (7)

1. a kind of aircraft frame beam connection joint, is used to connect upper frame section (3), lower frame section (4), side beam (5) and engine main thrust pin of aircraft frame beam intersection, it is characterized in that, comprises: Engine main thrust pin connecting hole (11), first connecting end (12), second connecting end (13) and third connecting end (14), described first connecting end (12), second connecting end (13 ) and the third connection end (14) are radially arranged on the side wall of the main thrust pin connection hole (11) of the engine, wherein the main thrust pin connection hole (11) of the engine is used to connect the main thrust pin of the engine, The first connecting end (12) is used to connect the upper frame segment (3) or the lower frame segment (4), and the second connecting end (13) is used to connect a frame segment not connected to the first connecting end (12), The second connection end (13) is separated from the first connection end (12) by 180° along the circumference of the engine main thrust pin connection hole (11), and the third connection end (14) is used to connect the side beam (5), the third connection end (14) is arranged between the first connection end (12) and the second connection end (13), and is connected with the first connection end (12) and the second connection end (12) The ends (13) are respectively separated by 90° along the circumferential direction of the connecting hole (11) of the main thrust pin of the engine. 2. The aircraft frame-girder connecting joint according to claim 1, characterized in that: the first connecting end (12) and the second connecting end (13) have the same structure. 3. The aircraft frame-girder connection joint according to claim 2, characterized in that: the first connection end (12) comprises a web (121), an inner edge strip (122) and an outer edge strip (123), the The inner edge strip (122) is arranged parallel to the outer edge strip (123), and the web (121) is arranged between the inner edge strip (122) and the outer edge strip (123), and is perpendicular to the inner edge strip (123). Edge bar (122) and outer edge bar (123), described inner edge bar (122) and/or outer edge bar (123) is at one end far away from described engine main thrust pin connection hole (11) from described inner edge The strip (122) and/or the outer edge strip (123) shrinks to the web (121) to form a step (124), the step (124) is provided with a strip (2), and one end of the strip (2) It is fastened to the inner edge strip (122) or the outer edge strip (123), and the other end is connected to the upper frame section (3) or the lower frame section (4). 4. The aircraft frame-girder connection joint according to claim 3, characterized in that: one end of the belt plate (2) is pin-connected to the inner edge strip (122) or the outer edge strip (123). 5. The aircraft frame-girder connection joint according to claim 1, characterized in that: the third connection end (14) comprises a side web (141) and at least one side edge strip (142), and the side web One end of (141) is vertically connected to one end of the side edge strip (142), and one end of the side beam (5) is fastened to the side web (141) and at least one side edge strip (142). 6. The aircraft frame-beam connecting joint according to claim 5, characterized in that: one end of the side beam (5) is pin-connected to the side web (141). 7. An aircraft frame girder, characterized in that it comprises the aircraft frame girder connection joint according to any one of claims 1-6.