CN213384779U

CN213384779U - Bridging repair structure of damaged bolt hole is born to aircraft height

Info

Publication number: CN213384779U
Application number: CN202022076264.9U
Authority: CN
Inventors: 陈亮; 管宇; 邸洪亮; 杨翔宁
Original assignee: Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC
Current assignee: Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC
Priority date: 2020-09-21
Filing date: 2020-09-21
Publication date: 2021-06-08
Anticipated expiration: 2030-09-21

Abstract

The utility model belongs to aircraft maintenance field, in particular to high bridging repair structure who bears impaired bolt hole of aircraft. The method comprises the following steps: a center wing, a vertical wall, a wall panel, a bushing, a bridge stiffener, and a bolt. A damaged first bolt hole is formed in the lower edge strip of a certain longitudinal wall of the central wing; the wall plate is abutted against a certain longitudinal wall of the central wing, and a second bolt hole corresponding to the first bolt hole is formed in the wall plate; the bushing is disposed in the second bolt hole; the cross section of the bridging reinforcement part is L-shaped, the bridging reinforcement part is abutted against the wall plate, a third bolt hole corresponding to the second bolt hole is formed in the bridging reinforcement part, and the aperture of the third bolt hole is smaller than that of the first bolt hole; the bolt is matched with the third bolt hole, sequentially penetrates through the third bolt hole, the second bolt hole and the first bolt hole, and is fixed through a nut. This application simple structure can satisfy the aircraft life cycle user demand.

Description

Bridging repair structure of damaged bolt hole is born to aircraft height

Technical Field

The utility model belongs to aircraft maintenance field, in particular to high bridging repair structure who bears impaired bolt hole of aircraft.

Background

A certain longitudinal wall of the central wing is a key bearing component of an airplane body structure, and the load borne by a phi 12mm bolt hole on the lower edge strip of the central wing is higher than that of peripheral bolt holes, so that the central wing is easy to crack in fatigue tests and outfield use, and cannot meet the use requirement of the whole life period. The reinforcing plate is limited by the structural form and the loading condition, the bolt hole bearing can still be avoided by simply using the reinforcing plate for repairing, the crack can continue to expand, and the service requirement of the whole life cycle of the airplane is difficult to meet.

Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.

SUMMERY OF THE UTILITY MODEL

The utility model aims at providing an aircraft height bears bridge connection repair structure of damaged bolt hole to solve at least one problem that prior art exists.

The technical scheme of the application is as follows:

a bridge repair structure for an aircraft high load bearing damaged bolt hole, comprising:

the lower edge strip of the certain longitudinal wall of the central wing is provided with a damaged first bolt hole;

the wall plate is abutted against a certain longitudinal wall of the central wing, and a second bolt hole corresponding to the first bolt hole is formed in the wall plate;

a bushing disposed in the second bolt hole;

the cross section of the bridging reinforcing piece is L-shaped, the bridging reinforcing piece is abutted against the wall plate, a third bolt hole corresponding to the second bolt hole is formed in the bridging reinforcing piece, and the aperture of the third bolt hole is smaller than that of the first bolt hole;

and the bolt is matched with the third bolt hole, sequentially penetrates through the third bolt hole, the second bolt hole and the first bolt hole, and is fixed through a nut.

Optionally, the first bolt hole has a diameter of Φ 12 mm.

Optionally, the aperture of the third bolt hole is Φ 8 mm.

Optionally, the bridging reinforcement is made of an aluminum alloy.

Optionally, the bolt further comprises a washer for matching the connection of the bolt and the nut.

Optionally, the bridging reinforcement is provided with a plurality of third bolt holes, and when the damaged first bolt holes on a longitudinal wall of the central wing are multiple, the repairing is performed through one bridging reinforcement.

Optionally, the bridging reinforcement is provided with a reinforcing rib adapted to a longitudinal wall of the central wing.

Utility model has the following beneficial technical effects:

the utility model provides a bridge connection repair structure of impaired bolt hole is born to aircraft height, simple structure can solve the high bolt hole repair problem that bears of certain vertical wall of central authorities' wing, satisfies the aircraft life cycle user demand.

Drawings

FIG. 1 is a schematic illustration of a longitudinal wall of a center wing of a bridge repair structure for high load bearing damaged bolt holes of an aircraft according to an embodiment of the present application;

FIG. 2 is a schematic illustration of a bridge reinforcement of a bridge repair structure for an aircraft high load bearing damaged bolt hole according to an embodiment of the present application;

FIG. 3 is a schematic illustration of a bridge reinforcement installation for a bridge repair structure for an aircraft high load bearing damaged bolt hole according to an embodiment of the present application;

fig. 4 is a view a-a of fig. 3.

Wherein:

1-a longitudinal wall of the central wing; 11-a first bolt hole; 2-wall plate; 3-bridging reinforcements; 4-a bolt; 5-lining.

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. 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 a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.

In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.

The present application is described in further detail below with reference to fig. 1 to 4.

The application provides structure is repaired in bridging of impaired bolt hole is born to aircraft height, includes: a center wing vertical wall 1, a wall plate 2, a bushing 5, a bridge reinforcement 3 and a bolt 4.

Specifically, the structure of a vertical wall 1 of the central wing, as shown in fig. 1, has a damaged first bolt hole 11 on its lower edge strip; the wall plate 2 is abutted against a certain longitudinal wall 1 of the central wing, and a second bolt hole corresponding to the first bolt hole 11 is formed in the wall plate 2; the bush 5 sets up in the second bolt hole, and the bolt hole of wallboard 2 is pressed bush 5 and can be ensured wallboard 1 and bridging part's cooperation and be connected.

Further, as shown in fig. 2 to 3, the bridging reinforcement 3 is designed according to the actual structure and aerodynamic configuration requirements of the aircraft, the cross section of the bridging reinforcement 3 is L-shaped, the bridging reinforcement 3 abuts against the wall plate 2, a third bolt hole corresponding to the second bolt hole is formed in the bridging reinforcement 3, and the aperture of the third bolt hole is smaller than that of the first bolt hole 11.

As shown in fig. 4, the bolt 4 is fitted into the third bolt hole, and the bolt 4 is fixed by a nut after passing through the third bolt hole, the second bolt hole, and the first bolt hole 11 in this order. The bolts 4 with small diameters are selected, so that the bolts 4 are not in contact with the first bolt holes 11 of the certain longitudinal wall 1 of the central wing, and the nail transmission load caused by the bolts 4 is avoided.

In one embodiment of the application, the first bolt hole 11 has a diameter of phi 12mm, the third bolt hole has a diameter of phi 8mm, and the bolt 4 is adapted to the third bolt hole with a diameter of phi 8 mm. In this embodiment, it is preferable that the diameter of the second bolt hole of the wall plate 2 is equal to the diameter of the first bolt hole 11 by Φ 12mm, the thickness of the bushing 5 is 2mm, and after the bushing 5 is installed in the second bolt hole, the wall plate 2 has an installation hole with a diameter of Φ 8mm, and is capable of fitting with the third bolt hole.

In one embodiment of the present application, the bridging stiffener 3 is made of aluminum alloy of the same grade as the structure to be repaired.

In one embodiment of the present application, a washer is further included for mating the connection of the bolt 4 to the nut.

In one embodiment of the present application, the bridging stiffener 3 is designed to have a certain process margin in length, depending on the actual structural and aerodynamic profile requirements of the aircraft. A plurality of third bolt holes may be formed in the bridging reinforcement 3, and when a plurality of first bolt holes 11 are formed in the damaged vertical wall 1 of the central wing, the repair can be performed by one bridging reinforcement 3. Advantageously, in this embodiment, the bridging reinforcement 3 is further provided with a reinforcing rib adapted to the longitudinal wall 1 of the central wing.

The utility model provides a structure is repaired in bridging of impaired bolt hole is born to aircraft height, when needs bear impaired first bolt hole 11 to aircraft height and bridge the repair, at first, according to the purpose-built bridging reinforcement 3 of actual need, bridging reinforcement 3 adopts L type cross-section, will originally shift to the stile by the load of the border strip transmission of certain vertical wall 1 of central wing, and the load passes through the stile and strides behind impaired first bolt hole 11 and transmits back the border strip. Secondly, the installation of the bridging reinforcement 3 is carried out, the fastener in the area needing to install the bridging reinforcement 3 is firstly disassembled, the bridging reinforcement 3 adopts the bolt hole of the original structure, the two are matched with the hinge hole, and the corresponding bolt 4 is installed to realize the fastening.

The utility model provides a structure is repaired in bridging of impaired bolt hole is born to aircraft height, further expands for avoiding the damage of impaired first bolt hole 11, should reduce the load that impaired bolt hole was undertaken, uses the less bolt 4 in impaired first bolt hole 11 aperture, eliminates the nail that is brought by bolt 4 and passes the load. Finally, regular inspection is required, and the state of the bridging reinforcement 3 is regularly inspected, and if cracks appear on the bridging reinforcement 3, the bridging reinforcement can be replaced in time.

The utility model provides a structure is repaired in bridging of impaired bolt hole is born to aircraft height through installation bridging reinforcement 3, replaces certain vertical wall 1 of impaired central wing to bear load, has avoided the further extension of crackle, even bridging reinforcement 3 damages, also only needs to change bridging reinforcement 3, has reduced the cost of maintenance of former part.

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. A bridge repair structure for an aircraft high load bearing damaged bolt hole, comprising:

a certain longitudinal wall (1) of the central wing, wherein a damaged first bolt hole (11) is formed in the lower edge strip of the certain longitudinal wall (1) of the central wing;

the wall plate (2) is abutted against the certain longitudinal wall (1) of the central wing, and a second bolt hole corresponding to the first bolt hole (11) is formed in the wall plate (2);

a bushing (5), the bushing (5) being disposed in the second bolt hole;

the cross section of the bridging reinforcement piece (3) is L-shaped, the bridging reinforcement piece (3) is abutted to the wall plate (2), a third bolt hole corresponding to the second bolt hole is formed in the bridging reinforcement piece (3), and the aperture of the third bolt hole is smaller than that of the first bolt hole (11);

the bolt (4), the bolt (4) with third bolt hole looks adaptation, bolt (4) pass in proper order third bolt hole, second bolt hole and first bolt hole (11), fix through the nut.

2. Bridge repair structure for aircraft high load bearing damaged bolt holes according to claim 1, characterized in that the first bolt hole (11) has a hole diameter of Φ 12 mm.

3. The aircraft high load bearing damaged bolt hole bridge repair structure of claim 2, wherein the third bolt hole has a hole diameter of Φ 8 mm.

4. The bridging repair structure for high load bearing damaged bolt holes of an aircraft according to claim 1, characterized in that the bridging reinforcement (3) is of aluminum alloy.

5. The aircraft high load bearing damaged bolt hole bridge repair structure of claim 1, further comprising a shim for mating the bolt (4) to nut connection.

6. The bridging repair structure of high load-bearing damaged bolt holes of airplane according to claim 1, characterized in that a plurality of third bolt holes are opened on the bridging reinforcement (3), and when a plurality of damaged first bolt holes (11) are opened on a longitudinal wall (1) of the central wing, the repairing is performed by one bridging reinforcement (3).

7. The bridging repair structure of high-load-bearing damaged bolt holes of aircraft according to claim 6, characterized in that the bridging reinforcement (3) is provided with a reinforcing rib adapted to a longitudinal wall (1) of the central wing.