CN220929872U

CN220929872U - Connection structure and aircraft

Info

Publication number: CN220929872U
Application number: CN202322843766.3U
Authority: CN
Inventors: 邹湘伏; 杨海超; 谢忠明; 刘意
Original assignee: Hunan Shanhe Huayu Aviation Technology Co ltd
Current assignee: Hunan Shanhe Huayu Aviation Technology Co ltd
Priority date: 2023-10-23
Filing date: 2023-10-23
Publication date: 2024-05-10
Anticipated expiration: 2033-10-23

Abstract

The utility model relates to the technical field of aircraft assembly, and provides a connecting structure and an aircraft, wherein the connecting structure comprises: one end of the matching bush is a plug-in end, a notch is arranged on the side wall of the matching bush, and the notch penetrates through the two ends of the matching bush; a rod-shaped connecting part, one end of which is an insertion end, and the diameter of the insertion end is smaller than the inner diameter of the matching bush; the part of the connecting part close to the insertion end is provided with a transition section, the transition section is gradually reduced towards the direction of the insertion end, and the inner diameter of the matched bushing is larger than the diameter of the small end of the transition section and smaller than the diameter of the large end of the transition section; the transition section is in plug-in fit with the matching bush, so that the matching bush can be propped up by the connecting part which axially moves along the radial direction; the locking part is connected to the end part of the connecting part and is used for providing axial pretightening force for the connecting part; by the arrangement, even if the coaxiality of the two components is slightly deviated, the two components can be smoothly connected, the assembly precision is reduced, the manufacturing precision of the components is reduced due to the reduction of the assembly precision, and the manufacturing cost is reduced.

Description

Connection structure and aircraft

Technical Field

The utility model relates to the technical field of aircraft assembly, in particular to a connecting structure and an aircraft.

Background

At present, bolts are used as most commonly used mechanical connectors and are widely applied to various fields, for example, in the assembly of an aircraft, when the horizontal tail and the rear fuselage of the aircraft are connected, bolt holes on the horizontal tail and bolt holes on a frame are required to be correspondingly coaxial, and then the bolts sequentially penetrate through and are locked through nuts.

In actual work, the horizontal tail and the rear machine body are connected through a plurality of bolts, so that the coaxiality of a plurality of holes in the horizontal tail and the rear machine body is required to be ensured to be within 0.05mm during connection, the assembly precision and the manufacturing precision of components are high, and the manufacturing cost is indirectly improved.

Disclosure of utility model

The embodiment of the utility model provides a connecting structure and an airplane, which are used for reducing the defect of higher manufacturing cost caused by higher assembly and manufacturing precision requirements in the prior art, and reducing the manufacturing cost by reducing the connecting precision.

The utility model provides a connecting structure which is used for connecting two components, wherein holes corresponding to the positions are arranged on the two components; the connection structure includes:

One end of the matching bush is a plug-in end which is suitable for being inserted into a hole of one member, a notch is arranged on the side wall of the matching bush, and the notch penetrates through two ends of the matching bush;

A rod-shaped connecting part, one end of which is an insertion end, wherein the diameter of the insertion end is smaller than the inner diameter of the matching bush, and the rod-shaped connecting part is suitable for sequentially passing through the hole of the other component and the matching bush; the part of the connecting part, which is close to the insertion end, is provided with a transition section, the transition section tapers towards the direction of the insertion end, and the inner diameter of the matching bush is larger than the diameter of the small end of the transition section and smaller than the diameter of the large end of the transition section; the transition section is in plug-in fit with the matching bush, so that the matching bush can be propped up by the connecting part which axially moves along the radial direction;

and the locking part is connected with the end part of the connecting part and is used for providing axial pretightening force for the connecting part and locking the two components.

According to the connection structure provided by the utility model, the connection part further comprises:

One end of the rod-shaped main body is connected with the large end of the transition section;

And the threaded section is connected with the small end of the transition section, and the diameter of the threaded section is smaller than the inner diameter of the matched bushing to form the insertion end.

According to the connecting structure provided by the utility model, the main body, the transition section and the thread section are integrally formed.

According to the connection structure provided by the utility model, the locking part comprises:

A large end connected to the end of the main body remote from the threaded section for abutment with one of the members;

And the locking nut is connected with the threaded section and is used for abutting against the other member.

According to the connecting structure provided by the utility model, the outer peripheral surface of the transition section is a conical surface.

According to the connecting structure provided by the utility model, the big end is integrally formed on the main body.

According to the connecting structure provided by the utility model, the opening of the matching bush is gradually widened towards the direction of the inserting end.

According to the connecting structure provided by the utility model, one end of the matching bush, which is far away from the plug-in end, is provided with the stop part for abutting against the component.

According to the connecting structure provided by the utility model, the stop part is annular and is coaxially arranged with the matching bush, and the notch penetrates through the stop part.

According to the present utility model there is provided a connection structure further comprising a protective bush adapted to be inserted into the holes of two of said members for passage of said mating bush and said connection portion.

According to the connecting structure provided by the utility model, the end part of the protective bush is provided with the baffle ring for abutting against the component.

According to the connecting structure provided by the utility model, the baffle ring is integrally formed on the protective lining.

According to the connecting structure provided by the utility model, the connecting structure further comprises a locking structure for preventing the locking nut from loosening.

The utility model also provides an aircraft, which comprises the connecting structure.

According to the aircraft provided by the utility model, the two components comprise the rear fuselage frame and the flat tail beam, and the rear fuselage frame is connected with the flat tail beam through the connecting structure.

According to the connecting structure and the airplane, due to the fact that the matching bush, the connecting part and the locking part are arranged, when two components are actually connected, even if the coaxiality of the holes in the two components is slightly insufficient, the connecting part can pass through smoothly, at the moment, the transition section is in plug-in fit with the matching bush, then the locking part is connected to the end part of the connecting part, the locking part can provide axial pretightening force for the connecting part, so that the connecting part moves along the axial direction of the matching bush, the transition section continuously extrudes the inner wall of the matching bush, the gap exists, the matching bush can adaptively deform in the holes of the rear frame when being extruded by the transition section, finally, the matching bush is tightly pressed in the holes of one component, the transition section is tightly pressed in the matching bush, and under the combined action of the matching bush, the connecting part and the locking part, compared with the existing bolt and nut direct locking mode, even if the coaxiality of the two components is slightly deviated, the smooth connection of the two components can be realized, the assembly precision is reduced, and the manufacturing precision of the components is reduced, and the manufacturing cost is reduced.

Drawings

In order to more clearly illustrate the utility model or the technical solutions of the prior art, the following description will briefly explain the drawings used in the embodiments or the description of the prior art, and it is obvious that the drawings in the following description are some embodiments of the utility model, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.

Fig. 1 is a schematic structural diagram of a connection structure according to an embodiment of the present utility model;

Fig. 2 is a schematic structural view of a mating bushing according to an embodiment of the present utility model.

Reference numerals:

1. A rear fuselage frame; 2. a flat tail beam; 3. matching with a bushing; 30. a notch; 31. a stop portion; 4. a connection part; 40. a transition section; 41. a main body; 42. a threaded section; 5. a locking part; 50. a lock nut; 51. a large end; 6. an anti-loosening structure; 60. positioning holes; 61. a cotter pin; 7. a frame bushing; 70. a first baffle ring; 8. a beam bushing; 80. and a second baffle ring.

Detailed Description

For the purpose of making the objects, technical solutions and advantages of the present utility model more apparent, the technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings, and it is apparent that the described embodiments are some embodiments of the present utility model, not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.

In order to facilitate understanding of the connecting structure and the aircraft provided by the utility model, firstly, an application background of the connecting structure is described, bolts are used as the most commonly used mechanical connecting pieces, and the connecting structure and the aircraft are widely applied to various fields, for example, when the horizontal tail and the rear fuselage of the aircraft are assembled, holes on the horizontal tail and holes on a frame of the rear fuselage are required to be correspondingly coaxial, and then the bolts are used for locking through nuts after passing through the bolts in sequence. But when actually connecting, the horizontal tail and the rear machine body are connected through a plurality of bolts, so that the coaxiality of every two corresponding holes on the horizontal tail and the rear machine body is ensured to be within 0.05mm, the connection of the parts can be completed, the requirements on assembly and manufacturing precision are high, and the manufacturing cost is indirectly improved.

Based on the above, the utility model provides a connecting structure and an airplane, which further reduce the manufacturing cost by reducing the requirement of assembly precision.

The connection structure and the aircraft of the utility model are described below in connection with fig. 1-2.

Referring to fig. 1 and 2, a connecting structure for connecting two members, the two members being provided with holes corresponding in position; the two components may be two parts to be connected on the aircraft, such as the rear fuselage frame 1 and the tail boom 2, or may be parts on other devices, and for the sake of understanding, the connection structure will be described below by taking the horizontal tail boom 2 and the rear fuselage frame 1 as the two components.

The connecting structure comprises a matching bush 3, a connecting part 4 and a locking part 5; one end of the mating bush 3 is a plugging end, and is suitable for being inserted into a hole of one member, for example, a hole of the rear frame 1, a notch 30 is arranged on the side wall of the mating bush 3, and the notch 30 penetrates through two ends of the mating bush 3, so that the mating bush 3 can be spread out along the radial direction.

The connecting portion 4 has a rod shape, one end of which is an insertion end, and the diameter of the insertion end is smaller than the inner diameter of the mating bush 3, and is suitable for sequentially passing through the hole of the other member and the mating bush 3, for example, penetrating from the hole on the horizontal tail beam 2 and penetrating from the mating bush 3; the part of connecting portion 4 near the insertion end is provided with changeover portion 40, changeover portion 40 towards the direction taper of insertion end, and the internal diameter of cooperation bush 3 is greater than changeover portion 40 tip diameter and is less than changeover portion 40 big end's diameter, passes back flat tail boom 2 and back fuselage frame 1 with connecting portion 4 in proper order, changeover portion 40 and cooperation bush 3 grafting, and when connecting portion 4 moved towards cooperation bush 3 along the axial, cooperation bush 3 can radially be propped up by changeover portion 40 and warp.

The locking part 5 is connected to the end of the connecting part 4 and is used for providing axial pretightening force for the connecting part 4 and locking the flat tail beam 2 and the rear frame 1.

In practice, when the rear frame 1 and the flat tail beam 2 are connected, the holes on the rear frame 1 and the flat tail beam 2 are correspondingly coaxial, then the matching bush 3 is inserted into the hole of the rear frame 1, so that the insertion end of the connecting part 4 sequentially passes through the hole on the flat tail beam 2 and the matching bush 3, and even if the coaxiality of the holes on the rear frame 1 and the flat tail beam 2 is slightly insufficient due to the fact that the diameter of the insertion end is smaller than that of the matching bush 3, the connecting part 4 can still smoothly pass through, at the moment, the transition section 40 is in splicing fit with the matching bush 3, then the locking part 5 is connected with the end part of the connecting part 4, and the locking part 5 can provide axial pretightening force for the connecting part 4, so that the connecting part 4 moves along the axial direction towards the matching bush 3.

The diameter of changeover portion 40 towards the direction of inserting the end taper and the diameter of big end is greater than the internal diameter of cooperation bush 3, therefore connecting portion 4 is towards cooperation bush 3 motion in-process, changeover portion 40 constantly extrudees cooperation bush 3 inner wall, the existence of breach 30, can take place self-adaptation deformation in the hole of back fuselage frame 1 when making cooperation bush 3 receive changeover portion 40 extrusion, finally make cooperation bush 3 compressed tightly in the hole of back fuselage frame 1, changeover portion 40 is compressed tightly in cooperation bush 3, realize the connection of back fuselage frame 1 and flat tail beam 2 under cooperation of cooperation bush 3, connecting portion 4 and locking portion 5, compare in the mode that current bolt, nut directly locked, even the axiality of back fuselage frame 1 and flat tail beam 2 upper hole also can realize the smooth connection of two, the assembly precision is reduced, the reduction of assembly precision makes the manufacturing precision of component reduce, thereby manufacturing cost is reduced.

The connection 4 further comprises a body 41 and a threaded section 42; wherein the main body 41 has a rod shape, one end of which is coaxially connected with the large end of the transition section 40, the threaded section 42 is coaxially connected with the small end of the transition section 40, and the diameter of the threaded section 42 is smaller than the inner diameter of the mating bushing 3, thereby forming the above-mentioned insertion end.

The whole metal material that adopts of connecting portion 4, for example steel etc. specifically can select according to actual demand, and main part 41, changeover portion 40 and screw thread section 42 can be through welded fastening, also can integrated into one piece, in this embodiment, main part 41 portion, changeover portion 40 and screw thread section 42 integrated into one piece machine tooling shaping to guarantee connecting portion 4's intensity.

The main body 41 may be a cylindrical rod or a polygonal rod; similarly, the outer peripheral surface of the transition section 40 may be a conical surface or an inclined surface, and may be specifically selected according to practical requirements, and in this embodiment, the main body 41 is a cylindrical rod, and the outer peripheral surface of the transition section 40 is a conical surface.

When the rear frame 1 and the flat tail beam 2 are connected, the insertion end sequentially passes through the hole on the flat tail beam 2 and the matching bush 3, and the matching bush 3 is in plug-in fit with the transition section 40.

The opening of the matching bush 3 is gradually widened towards the inserting end to form an inner conical surface, and when the matching bush is connected, the inserting end of the connecting part 4 can be inserted from one end of the flaring of the matching bush 3, so that the matching of the opening and the inserting end is facilitated; in addition, the transition section 40 is matched with the flaring part of the matched bush 3, so that the contact area of the transition section 40 and the flaring part of the matched bush 3 can be increased, when the matched bush 3 is extruded by the transition section 40, the stressed area of the matched bush 3 is larger, and the deformation is more uniform.

The matching bush 3 is made of metal material, such as steel, and can be specifically selected according to actual requirements, and only the strength required by the matching bush 3 is required to be ensured.

Referring to fig. 2, a stopper 31 is provided at an end of the mating bush 3 away from the insertion end, and after the mating bush 3 is inserted into the hole of the rear frame 1, the stopper 31 abuts against the outside of the rear frame 1 to position the mating bush 3.

Specifically, the stop portion 31 has a plurality of selectable shapes, and only needs to have a stop positioning effect; in addition, the stop portion 31 and the mating bush 3 may be fixedly connected by welding or the like, or may be integrally formed, and may be specifically selected according to actual requirements.

In this embodiment, the stop portion 31 is integrally formed on the mating bush 3, which is annular and coaxially disposed with the mating bush 3, and the notch 30 penetrates through the stop portion 31 to satisfy the deformation requirement of the mating bush 3.

When connecting back fuselage frame 1 and flat tail boom 2, insert the downthehole of back fuselage frame 1 with cooperation bush 3, backstop portion 31 butt is outside back fuselage frame 1 in order to fix a position cooperation bush 3, and behind the hole and cooperation bush 3 on the flat tail boom 2 were passed in proper order to the inserted end of connecting portion 4, locking through locking portion 5.

Referring to fig. 1, the locking part 5 includes a locking nut 50 and a large end 51; the big end 51 is connected to one end of the main body 41 far away from the threaded section 42 and is used for being abutted against the outside of the horizontal tail beam 2; the lock nut 50 is connected to the threaded section 42, and is used for abutting against the outside of the rear frame 1 and providing pretightening force, and under the action of the lock nut 50, the connecting portion 4 is driven to move towards the direction of the matching bush 3, so that the transition section 40 extrudes the matching bush 3, and under the joint locking of the large end 51 and the lock nut 50, the connection and fixation of the rear frame 1 and the flat tail beam 2 are realized.

The large end 51 may be removably attached to the body 41, such as by a threaded connection, or may be non-removably attached to the body 41, such as by welding or by integral molding. In this embodiment, the large end 51 is integrally formed on the main body 41 to ensure the connection strength of the connection portion 4.

When connecting back fuselage frame 1 and flat tail boom 2, insert the cooperation bush 3 in the downthehole of back fuselage frame 1, backstop 31 butt is outside back fuselage frame 1 in order to fix a position cooperation bush 3, the inserted end of connecting portion 4 passes hole and cooperation bush 3 on flat tail boom 2 in proper order, then with lock nut 50 threaded connection on screw thread section 42, through the pretightning force that screws lock nut 50, can provide axial for connecting portion 4, make changeover portion 40 compress tightly and prop open cooperation bush 3, until big end 51 supports tightly outside flat tail boom 2, under the joint locking of big end 51 and lock nut 50, realize the connection fixed of back fuselage frame 1 and flat tail boom 2.

Referring to fig. 1, the thread segments 42 are provided with a locking structure 6 for preventing the lock nut 50 from loosening.

Specifically, the lock nut 50 is a groove-type nut; the locking structure 6 includes a positioning hole 60 and a cotter pin 61; the positioning hole 60 penetrates through the threaded section 42 in the radial direction, and when the lock nut 50 locks the connecting part 4, the positioning hole 60 is close to one end of the lock nut 50, which is away from the rear frame 1; the cotter pin 61 is inserted into the positioning hole 60, and the two tail parts of the cotter pin 61 are bent and clamped on the locking nut 50 with the groove shape, so that the anti-loose purpose is achieved.

It will be appreciated that the above is just one of many anti-lock arrangements for the lock nut 50, and that other arrangements such as double nut anti-lock, spring washer anti-lock, etc. are applicable to the present utility model.

Referring to fig. 1, the connection structure further includes a protection bush adapted to be inserted into holes of two members such as the rear fuselage frame 1 and the horizontal tail beam 2, so that the hole wall of the hole on the member can be protected by the protection bush through which the connection reliability is improved and the service life of the member is prolonged, for example, when the rear fuselage frame 1 and the horizontal tail beam 2 are made of composite materials, the abrasion of the hole wall can be reduced by the protection bush.

Specifically, the end of the protective bush is provided with a stop ring for abutting against the member, and the large end 51 and the stop portion 31 are respectively abutted against the stop rings of the two protective bushes.

Specifically, the protective bush fitted in the hole of the rear frame 1 is set as a frame bush 7, the stop ring provided on the frame bush 7 is a first stop ring 70, the first stop ring 70 abuts against the rear frame 1 after the frame bush 7 is fitted in the hole of the rear frame 1, the mating bush 3 is inserted into the frame bush 7, and the stop portion 31 abuts against the first stop ring 70.

The protective bush embedded in the hole of the horizontal tail beam 2 is set as a beam bush 8, the baffle ring arranged on the beam bush 8 is a second baffle ring 80, after the beam bush 8 is embedded in the hole of the horizontal tail beam 2, the second baffle ring 80 is abutted on the horizontal tail beam 2, the big end 51 is abutted on the second baffle ring 80,

The aircraft provided by the utility model is described below, and the aircraft described below and the connecting structure described above can be referred to correspondingly.

An aircraft comprises a rear fuselage frame 1, a horizontal tail boom 2, and the above-described connection structure for connecting the rear fuselage frame 1 and the horizontal tail boom 2.

It will be appreciated that the two components described above, including but not limited to the aft fuselage frame 1 and the tail boom 2, may also be other components on the aircraft to be joined.

The novel innovation point of the utility model is that: through setting up mating bush 3, connecting portion 4 and locking portion 5, actually when connecting two components, even the axiality of hole on two components is slightly not enough, connecting portion 4 still can pass smoothly, changeover portion 40 and mating bush 3 grafting cooperation at this moment, then connect locking portion 5 at the tip of connecting portion 4, locking portion 5 can provide axial pretightning force for connecting portion 4, make connecting portion 4 along axial towards mating bush 3's direction, changeover portion 40 constantly extrudees mating bush 3 inner wall, the existence of breach 30, make mating bush 3 receive changeover portion 40 and can take place adaptive deformation in the hole of back fuselage frame 1 when extrusion, finally make mating bush 3 compressed tightly in the hole of a component, changeover portion 40 is compressed tightly in mating bush 3, under the combined action of mating bush 3, connecting portion 4 and locking portion 5, realize the smooth connection of two components, compared with current bolt, nut direct locking's mode, even the axiality of two components has the deviation also can realize the smooth connection of two, the reduction in assembly precision makes the manufacturing precision of component, thereby the manufacturing cost is reduced.

Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present utility model, and are not limiting; although the utility model has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present utility model.

Claims

1. The connecting structure is characterized by being used for connecting two members, wherein holes corresponding to the positions are formed in the two members; the connection structure includes:

One end of the matching bush (3) is a plug-in end, and is suitable for being inserted into a hole of one of the components, a notch (30) is arranged on the side wall of the matching bush (3), and the notch (30) penetrates through two ends of the matching bush (3);

A rod-shaped connecting part (4), one end of which is an insertion end, the diameter of the insertion end is smaller than the inner diameter of the matching bush (3), and the rod-shaped connecting part is suitable for sequentially passing through the hole of the other component and the matching bush (3); the part of the connecting part (4) close to the insertion end is provided with a transition section (40), the transition section (40) tapers towards the direction of the insertion end, and the inner diameter of the matching bush (3) is larger than the diameter of the small end of the transition section (40) and smaller than the diameter of the large end of the transition section (40); the transition section (40) is in plug-in fit with the matching bush (3) so that the matching bush (3) can be spread by the connecting part (4) which axially moves along the radial direction;

And the locking part (5) is connected to the end part of the connecting part (4) and is used for providing axial pretightening force for the connecting part (4) and locking the two components.

2. The connection structure according to claim 1, characterized in that the connection portion (4) further comprises:

a rod-shaped main body (41), wherein one end of the main body (41) is connected with the large end of the transition section (40);

-a threaded section (42), said threaded section (42) being connected to the small end of said transition section (40), and the diameter of said threaded section (42) being smaller than the inner diameter of said mating bushing (3), forming said insertion end.

3. The connection structure according to claim 2, characterized in that the locking portion (5) comprises:

A large end (51) connected to an end of the main body (41) remote from the threaded section (42) for abutment with one of the members;

A lock nut (50) connected to said threaded section (42) for abutment with another of said members.

4. The connection according to claim 1, characterized in that the outer circumferential surface of the transition section (40) is tapered.

5. The connection according to claim 1, characterized in that the opening of the mating bushing (3) diverges towards the plugging end.

6. A connection according to any one of claims 1-5, characterized in that the end of the mating bushing (3) remote from the plug end is provided with a stop (31) for abutment with the component.

7. The connection according to claim 6, characterized in that the stop (31) is annular and is arranged coaxially to the mating bush (3), the notch (30) extending through the stop (31).

8. The connection according to claim 1, characterized in that it further comprises a protective bush adapted to be inserted into the holes of both said members for the passage of said mating bush (3) and of said connecting portion (4).

9. An aircraft comprising a connection according to any one of claims 1 to 8.

10. The aircraft according to claim 9, characterized in that the two components comprise a rear fuselage frame (1) and a flat tail boom (2), the rear fuselage frame (1) being connected to the flat tail boom (2) by means of the connection structure.