CN217729739U

CN217729739U - Mechanical pressurizing and dismantling tool for composite material gluing repair

Info

Publication number: CN217729739U
Application number: CN202221470960.0U
Authority: CN
Inventors: 孙运刚; 吴晓儒; 黄任昌
Original assignee: State Run Wuhu Machinery Factory
Current assignee: State Run Wuhu Machinery Factory
Priority date: 2022-06-14
Filing date: 2022-06-14
Publication date: 2022-11-04
Anticipated expiration: 2032-06-14

Abstract

The utility model relates to a mechanical pressurization and demolish the frock field, specifically be a mechanical pressurization and demolish frock for combined material splices repair, including both sides can stretch out and draw back the bracing piece that has certain range, with bracing piece normal running fit be convenient for the king-rod that the facade was exerted pressure, set up the clamp plate that is used for the facade to exert pressure at the king-rod, the bracing piece both ends be provided with the exposed fault position framework to the aircraft structure and carry out the exposed fault position centre gripping's exposed fault position framework, to the typical frame structure of aircraft, it is narrow and small that mostly to be the facade and repair the space, adopt the utility model discloses exert the splicing pressure of continuous stability, satisfy facade processing, can only vertical processing for ordinary frock, the utility model discloses can satisfy the processing demand of aircraft frame structure.

Description

Mechanical pressurizing and dismantling tool for composite material gluing repair

Technical Field

The utility model relates to a mechanical pressurization and demolish the frock field, specifically be a mechanical pressurization and demolish frock for combined material splices the repair.

Background

The composite material glue joint repair has the advantages of small structural weight increment, good fatigue resistance and corrosion resistance, strong designability, short repair time, suitability for rapid repair of an outfield and the like, and is widely applied to aircraft repair. The composite material gluing and repairing process includes scheme design, surface repairing treatment, soaking and spreading of composite material, pressure application, heating curing, post-curing finishing and other steps.

For the application of the adhesive bonding pressure, a heavy object such as a sand bag is often adopted to provide uniform pressure under the laboratory condition, but as most aircraft structures are bulkhead structures, namely, most aircraft frames are vertical surfaces, the repair working condition is limited, and the pressure required by adhesive bonding repair is difficult to meet; even if a fixing method is adopted to apply pressure to the glued joint repair, the glued joint repair is difficult to remove after curing, and the repair quality is greatly influenced by adopting a mechanical violence to remove the tool.

Disclosure of Invention

In order to solve the problem, the utility model provides a mechanical pressurization and demolish frock for combined material splices the repair.

The utility model provides a mechanical pressurization and demolish frock for combined material splices repair, includes that both sides can stretch out and draw back have a certain range bracing piece, with bracing piece normal bar, the setting of being convenient for the facade to exert pressure that the bracing piece normal bar is used for the facade to exert pressure, the bracing piece both ends be provided with the exposed core that the trouble position framework of aircraft structure height carries out the centre gripping.

The application range of the support rod is 100-200 mm, and the support rod is provided with a threaded hole matched with the middle rod.

The length of the middle rod is 150mm, threads matched with threaded holes of the supporting rods are tapped on the middle rod and are all made of steel.

The shape of the pressing plate is not limited, the pressing plate can be square, oval or trapezoidal, the thickness of the pressing plate is 5mm, and the gravity center position needs to be determined and a threaded hole needs to be drilled.

The clamping end comprises a C-shaped support, threaded rods which are arranged at two ends of the support and screwed down with the support through threads, and contact ends fixedly connected with the threaded rods.

The clamping range of the two groups of contact ends is 2-10mm.

The contact surface of the contact end is soft rubber.

The utility model has the advantages that: to typical frame structure of aircraft, it is mostly the facade and repairs the space narrow and small, adopt the utility model discloses apply the continuous and stable pressure that splices, satisfy facade processing, can only vertical processing for ordinary frock, the utility model discloses can satisfy the processing demand of aircraft frame structure.

Drawings

The present invention will be further explained with reference to the drawings and examples.

Fig. 1 is a schematic view of the structure of the present invention;

fig. 2 is a schematic side view of the present invention;

fig. 3 is a schematic top view of the present invention;

fig. 4 is a schematic diagram of a typical frame structure of an airplane in the background art of the present invention;

FIG. 5 is a schematic view of the structure of the clamping end of the present invention;

fig. 6 is a schematic view of the front view structure of the support rod of the present invention;

fig. 7 is a schematic top view of the support rod of the present invention;

FIG. 8 is a schematic view of the square pressing plate of the present invention;

fig. 9 is a schematic structural view of a trapezoidal pressing plate of the present invention;

FIG. 10 is a schematic view of the structure of the oval pressing plate of the present invention;

fig. 11 is a schematic view of the square pressing plate assembly structure of the present invention;

fig. 12 is a schematic view of the structure of the middle rod of the present invention.

Detailed Description

In order to make the utility model realize, the technical means, the creation characteristics, the achievement purpose and the efficacy are easy to understand and understand, and the utility model is further explained below.

As shown in fig. 1 to 12, a mechanical pressurizing and dismantling tool for composite material bonding repair comprises a support rod 1, a middle rod 2 and a pressing plate 3, wherein two sides of the support rod 1 can stretch out and draw back and have a certain range, the middle rod 2 is in rotating fit with the support rod 1 to facilitate vertical surface pressing, the pressing plate 3 is arranged on the middle rod 2 and used for vertical surface pressing, and two ends of the support rod 1 are provided with clamping ends 4 for clamping a frame body of a high-failure part of an aircraft structure.

To typical frame structure of aircraft, the reference numeral of fig. 4 is c, and it is narrow and small that mostly to be the facade and repair the space, adopts the utility model discloses apply the pressure that splices that lasts stable, satisfy facade processing, can only vertical processing for ordinary frock, the utility model discloses can satisfy the processing demand of aircraft frame structure.

The application range of the support rod 1 is 100-200 mm, and the support rod 1 is provided with a threaded hole 1a matched with the middle rod 2.

Avoid 2 length overlengths of king-rod to lead to the unstability, combine to consider structure repair space open nature, 2 length of king-rod at 150mm, king-rod 2 on tap have with bracing piece 1's screw hole matched with screw thread, all adopt steel to make.

The shape of the pressing plate 3 is not limited, the pressing plate can be square, oval or trapezoidal according to the size and the shape of the high-haired crack web plate, the thickness of the pressing plate 3 is 5mm, and the gravity center position needs to be determined and a threaded hole 3a needs to be drilled.

The clamping end 4 comprises a C-shaped bracket 41, threaded rods 42 which are arranged at two ends of the bracket 41 and screwed with the bracket 41 through threads, and contact ends 43 fixedly connected with the threaded rods 42.

The clamping range of the two sets of contact ends 43 is 2-10mm as indicated by reference d in fig. 5.

In order to avoid the clamping end 4 from damaging the original structure of the airplane, the contact surface of the contact end 43 is made of soft rubber.

As shown in the figure 1 of the assembly drawing, the reference sign a is that the pressurizing direction is vertical downward, and the reference sign b is that the removing direction is vertical upward, so that the problems that the pressurizing is difficult in the actual structure gluing and repairing process of the airplane and the tool cannot be removed after gluing are effectively solved.

The foregoing shows and describes the general principles, essential features, and advantages of the invention. It should be understood by those skilled in the art that the present invention is not limited to the above embodiments, and the above embodiments and what is described in the specification are the principles of the present invention, and that various changes and modifications may be made without departing from the spirit and scope of the present invention, and these changes and modifications are intended to fall within the scope of the present invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.

Claims

1. The utility model provides a mechanical pressurization and demolish frock that is used for combined material to glue to repair which characterized in that: the airplane structure high-rise fault location clamping device comprises a supporting rod (1) with two sides capable of stretching out and drawing back and having a certain range, a middle rod (2) which is matched with the supporting rod (1) in a rotating mode to be convenient for vertical surface pressure application, and a pressing plate (3) which is arranged on the middle rod (2) and used for vertical surface pressure application, wherein clamping ends (4) for clamping a frame body of a high-rise fault location of an airplane structure are arranged at two ends of the supporting rod (1).

2. The mechanical pressing and dismantling tool for composite material gluing repair of claim 1, wherein: the application range of the support rod (1) is 100-200 mm, and a threaded hole (1 a) matched with the middle rod (2) is formed in the support rod (1).

3. The mechanical pressing and dismantling tool for composite material glue joint repair according to claim 1, characterized in that: the length of the middle rod (2) is 150mm, threads matched with threaded holes of the support rods (1) are tapped on the middle rod (2), and the middle rod and the support rods are all made of steel.

4. The mechanical pressing and dismantling tool for composite material gluing repair of claim 1, wherein: the pressing plate (3) can be square, oval or trapezoidal, the thickness of the pressing plate (3) is 5mm, and the gravity center position needs to be determined and the threaded hole (3 a) needs to be drilled.

5. The mechanical pressing and dismantling tool for composite material gluing repair of claim 1, wherein: the clamping end (4) comprises a C-shaped support (41), a threaded rod (42) which is arranged at two ends of the support (41) and screwed with the support (41) through threads, and a contact end (43) fixedly connected with the threaded rod (42).

6. The mechanical pressing and dismantling tool for composite material gluing repair of claim 5, wherein: the clamping range of the two groups of contact ends (43) is 2-10mm.

7. The mechanical pressing and dismantling tool for composite material glue joint repair according to claim 5, characterized in that: the contact surface of the contact end (43) is soft rubber.