CN219598546U

CN219598546U - Clamp for in-situ repair of broken hole damage of hard aluminum main bearing structure of airplane

Info

Publication number: CN219598546U
Application number: CN202320579841.7U
Authority: CN
Inventors: 王春雨; 卿华; 张献逢; 杜晓伟; 赵叶曼; 侯日立; 张争明
Original assignee: Air Force Engineering University of PLA Aircraft Maintenace Management Sergeant School
Current assignee: Air Force Engineering University of PLA Aircraft Maintenace Management Sergeant School
Priority date: 2023-03-23
Filing date: 2023-03-23
Publication date: 2023-08-29
Anticipated expiration: 2033-03-23

Abstract

The utility model provides a clamp for in-situ repair of hole breaking damage of an aircraft duralumin main bearing structure, which comprises a C-shaped clamp body, a pressure head module arranged on the clamp body and a gas container cavity arranged at the lower part of the clamp body, wherein the pressure head module is arranged on the clamp body; the pressure head module comprises a front rotary pressure head vertically threaded at the top end part of the clamp body, two support arms transversely arranged on the inner side wall of the upper end of the clamp body in a splayed shape and side screws Niu Yatou vertically threaded at the end parts of the two support arms respectively; the inside of gas container chamber still vertically is provided with the ejector pin that is used for supporting prefabricated patch, the top of ejector pin and the top parallel and level of gas container chamber. The fixture for in-situ repair of the hole breaking damage of the hard aluminum main bearing structure of the airplane can be used for rapidly and firmly fixing the patch at the position to be welded of the main bearing structure, so that the welding repair of the damaged position of the main bearing structure is rapidly and firmly realized.

Description

Clamp for in-situ repair of broken hole damage of hard aluminum main bearing structure of airplane

Technical Field

The utility model relates to the technical field of clamps, in particular to a clamp for in-situ rush repair of an aircraft duralumin main bearing structure breaker Kong Sunshang.

Background

When the aircraft is under fight, when the aircraft is attacked by enemy weapons, a large number of penetration breaks Kong Sunshang are easily formed in the hard aluminum main bearing structure densely distributed on the aircraft body, and the size of the break Kong Sunshang is between 10mm and 25mm according to experiments. The main bearing structure maintains the strength of the aircraft body, and once serious hole breaking damage occurs, the strength of the main bearing structure of the aircraft is seriously affected, so that the aircraft cannot continue to be put into combat. Therefore, in order to make the aircraft rapidly put into combat again, the broken hole damage of the main bearing structure must be repaired in time.

For broken hole damage of an aircraft duralumin main bearing structure, a method of welding a prefabricated patch at a broken hole can be adopted for in-situ repair, but the patch is required to be fixed in the welding process, otherwise, the welding cannot be rapidly and conveniently implemented.

Disclosure of Invention

In view of the defects in the prior art, the utility model provides the clamp for in-situ repair of the hole breaking damage of the main bearing structure of the hard aluminum of the airplane, which can quickly and firmly fix the patch to the to-be-welded part of the main bearing structure of the airplane body, thereby quickly and firmly realizing the welding repair of the damaged part of the main bearing structure of the airplane body.

In order to solve the technical problems, the utility model adopts the following technical scheme: the fixture comprises a C-shaped fixture body, a pressure head module arranged on the fixture body and a gas container cavity arranged at the lower part of the fixture body; the pressure head module comprises a front rotary pressure head vertically threaded at the top end of the clamp body, two support arms transversely arranged on the inner side wall of the upper end of the clamp body in a splayed shape, and side screws Niu Yatou vertically threaded at the ends of the two support arms respectively; the inside of gas container chamber still vertically is provided with the ejector pin that is used for supporting prefabricated patch, the top of ejector pin and the top parallel and level of gas container chamber.

The front rotary pressure head comprises a main threaded rod, a main pressing block and a main rotating handle, wherein the main threaded rod is in vertical threaded connection with the top end part of the clamp body, the main pressing block is arranged at the bottom of the main threaded rod, the main rotating handle is arranged at the upper end of the main threaded rod, the main pressing block is in threaded connection with the lower end of the main threaded rod, and the main rotating handle is further provided with a main anti-skid sleeve. The contact area between the main pressing block and the prefabricated patch can be increased, so that the prefabricated patch placed on the repairing hole of the machine body is pressed down more stably, and the prefabricated patch is pressed into the repairing hole of the machine body; the main screw rod can be conveniently screwed and adjusted through the main rotary handle, so that the main screw rod can be conveniently vertically moved up and down; through the main anti-slip sleeve, a user can conveniently operate the main rotary handle and rotate and adjust the main threaded rod by bare hands, so that the vertical positions of the main threaded rod and the main pressing block are adjusted.

The side knob pressure head comprises a side threaded rod vertically in threaded connection with the end part of the support arm, a side pressure block arranged at the bottom of the side threaded rod and a side rotary handle arranged at the upper end of the side threaded rod; the side pressing block is in threaded connection with the lower end of the side threaded rod; the side twist grip is also provided with a side anti-skid sleeve. The contact area between the side pressing blocks and the machine body can be increased, so that the fixture and the machine body can be fixed more stably; the side screw rod can be conveniently screwed and adjusted through the side screw handle, so that the side screw rod can be conveniently vertically moved up and down; through the side anti-slip sleeve, a user can conveniently operate the side rotary handle and rotate and adjust the side threaded rod by bare hands, so that the vertical positions of the side threaded rod and the side pressing block are adjusted.

The diameter of the ejector rod in the gas container cavity is 5mm.

The gas container cavity is positioned at the lower part of the hole to be welded and repaired on the machine body, and the hole to be welded and repaired on the machine body can be wrapped.

Compared with the prior art, the utility model has the following beneficial effects: firstly, according to the fixture for in-situ repair of the prefabricated patch of the hard aluminum main bearing structure of the airplane, the patch can be quickly and firmly fixed to a to-be-welded part of the airplane body under the cooperation of the fixture body, the front rotary pressure head, the two support arms, the gas container cavity and the ejector rod, so that the welding repair of the damaged part of the airplane body is quickly and firmly realized; in addition, because the diameter of the ejector rod in the gas container cavity is 5mm, the technical scheme can also be used for clamping patches with various specific sizes (10 mm, 15mm, 20mm, 25mm and the like), and the realization principle is that the size of a metal disc at the front end of the middle pressure head is 5mm, and the implementation of welding the patches and a hole butt joint area is not interfered; thereby fully meeting the auxiliary requirement of welding repair work of hole breaking damage of the main bearing structure of the hard aluminum of the airplane.

Secondly, the back inert gas protection clamp for in-situ repair of the prefabricated patch of the hard aluminum main bearing structure of the aircraft can be used for clamping the prefabricated patch and protecting the back inert gas during in-situ repair of broken holes of the hard aluminum main bearing structure of the aircraft, so that the air hole defect is prevented during welding of aluminum alloy, and the timeliness and repair effect of rush repair are ensured; the principle is realized in that the diameter of the gas container cavity is 55 mm, about 30 mm beyond the maximum prefabricated patch, whereby the back of the weld is at the cavity between the gas container cavity and the metal rod, and inert gas enters the gas container cavity from the inert gas inlet and is discharged from the exhaust hole during welding. When the inert gas flow is constant, the inert gas with certain pressure and no pollution can be ensured to continuously exist at the back of the welding seam, and the welding seam is well protected

Drawings

The utility model will be described in further detail with reference to the drawings and the detailed description.

FIG. 1 is a schematic diagram of the structure of the present utility model;

FIG. 2 is a schematic side view of the present utility model;

FIG. 3 is a schematic elevational view of the present utility model;

fig. 4 is a schematic structural view of the protection clamp of the present utility model.

In the figure: 101. a clamp body; 102. a gas container cavity; 103. a support arm; 104. a push rod; 201. a main threaded rod; 202. A main pressing block; 203. a main knob; 204. a main anti-skid sleeve; 301. a lateral threaded rod; 302. a side pressing block; 303. a side knob; 304. A lateral anti-skid sleeve; 401. an air inlet nozzle; 402. and an exhaust hole.

Detailed Description

For a better understanding of the present utility model, the following examples are set forth to further illustrate the utility model, but are not to be construed as limiting the utility model. In the following description, numerous specific details are set forth in order to provide a more thorough understanding of the present utility model. It will be apparent, however, to one skilled in the art that the utility model may be practiced without one or more of these details.

As shown in fig. 1, 2 and 3, the fixture for in-situ repair of hole damage of an aircraft duralumin main bearing structure comprises a C-shaped fixture body 101, a pressure head module arranged on the fixture body 101 and a gas container cavity 102 arranged at the lower part of the fixture body 101; the pressure head module comprises a front rotary pressure head vertically threaded at the top end of the clamp body 101, two support arms 103 transversely arranged on the inner side wall of the upper end of the clamp body 101 in a splayed shape, and side screws Niu Yatou vertically threaded at the ends of the two support arms 103 respectively; the inside of the gas container cavity 102 is further vertically provided with a push rod 104 for supporting the prefabricated patch, and the top of the push rod 104 is flush with the top of the gas container cavity 102.

The hole with proper size can be formed at the position to be welded and repaired of the machine body, then the clamp body 101 is moved to the side end of the position, which is required to be welded and repaired, of the machine body, the gas container cavity 102 is positioned below the machine body, the gas container cavity 102 is coaxial with the hole, and then the two side knob pressure heads are screwed downwards until the bottoms of the two knob pressure heads are propped against the top of the machine body, the top of the gas container cavity 102 is propped against the bottom of the machine body, and the clamp is positioned and fixed on the machine body.

Then, the prefabricated patch matched with the hole can be placed at a position on the machine body corresponding to the upper part of the hole, then, the front rotary pressure head can be screwed down, so that the front rotary pressure head is in contact with the top of the prefabricated patch, and pushes the prefabricated patch to sink towards the hole until the bottom of the prefabricated patch is in contact with the top of the ejector rod 104, at the moment, the bottom of the prefabricated patch is flush with the bottom of the hole, and the top of the prefabricated patch is flush with the top of the hole, so that the prefabricated patch can be quickly and stably fixed in the hole, and the prefabricated patch is fixed in an auxiliary mode in the processing process of welding the prefabricated patch and the machine body together, so that the firmness of welding and the effect of welding repair are prevented from being influenced due to emission deflection and skew of the prefabricated patch in the welding process; the user can then quickly and firmly weld the prefabricated patch to the fuselage.

After the welding processing of the machine body and the prefabricated patch is finished, the front rotary pressure head can be enabled to move upwards, so that the extrusion part of the prefabricated patch is relieved; then the side rotary pressure head can be moved upwards, so that the fixture and the machine body are released from being fixed, and then the fixture can be removed from the machine body.

According to another embodiment of the present utility model, as shown in fig. 1, 2 and 3, the front rotary press head includes a main threaded rod 201 vertically screwed with the top end of the clamp body 101, a main press block 202 disposed at the bottom of the main threaded rod 201, and a main knob 203 disposed at the upper end of the main threaded rod 201, where the main press block 202 is screwed with the lower end of the main threaded rod 201, and the main knob 203 is further provided with a main anti-slip sleeve 204. The contact area with the prefabricated patch can be increased through the main pressing block 202, so that the prefabricated patch placed on the repairing hole of the machine body is pressed down more stably, and the prefabricated patch is pressed into the repairing hole of the machine body; the main screw rod 201 can be conveniently screwed and adjusted through the main rotary handle 203, so that the main screw rod 201 can be conveniently vertically moved up and down; through the main anti-skid sleeve 204, a user can conveniently operate the main rotary handle 203 by bare hands and rotate and adjust the main threaded rod 201, so that the vertical positions of the main threaded rod 201 and the main pressing block 202 are adjusted.

According to another embodiment of the present utility model, as shown in fig. 1, 2 and 3, the side knob ram comprises a side threaded rod 301 vertically screwed with the end of the arm 103, a side pressing block 302 disposed at the bottom of the side threaded rod 301, and a side knob 303 disposed at the upper end of the side threaded rod 301; the side pressing block 302 is in threaded connection with the lower end of the side threaded rod 301; the side knob 303 is further provided with a side anti-slip sleeve 304. The contact area between the side pressing blocks 302 and the machine body can be increased, so that the fixture and the machine body can be fixed more stably; the side screw rod 301 can be conveniently screwed and adjusted through the side screw handle 303, so that the side screw rod 301 can be conveniently vertically moved up and down; through the side anti-skid sleeve 304, a user can conveniently operate the side rotary handle 303 by bare hands and rotate and adjust the side threaded rod 301, so that the vertical positions of the side threaded rod 301 and the side pressing block 302 are adjusted.

According to another embodiment of the present utility model, as shown in fig. 4, the gas container cavity 102 further comprises an inert gas inlet nozzle 401 disposed at a side end of the gas container cavity 102 and an exhaust hole 402 disposed at a side end of the gas container cavity 102 and located at an upper side of the inert gas inlet nozzle 401, wherein the gas container cavity 102 is located at a lower portion of a hole to be welded and repaired on the machine body, and can wrap the hole to be welded and repaired on the machine body.

The principle is achieved that the diameter of the gas container cavity is 55 mm, about 30 mm beyond the maximum prefabricated patch, whereby the weld back is at the cavity between the gas container cavity and the metal rod, and inert gas enters the gas container cavity from the inert gas inlet and is exhausted from the exhaust hole during welding. When the flow of the inert gas is constant, the inert gas with certain pressure and no pollution can be ensured to continuously exist at the back of the welding line, and the welding line is well protected.

In order to prevent the air hole defect generated during the welding of the aluminum alloy, the clamp can realize inert gas protection on the back of the welding seam through the gas container cavity 102. The principle is achieved that the diameter of the gas container cavity 102 exceeds the prefabricated maximum patch by about 30 a mm a, whereby the weld back is at the cavity between the gas container cavity 102 and the metal rod, and inert gas enters the gas container cavity 102 from the inert gas inlet and exits the vent hole 402 during welding. When the flow of the inert gas is constant, the inert gas with certain pressure and no pollution can be ensured to continuously exist at the back of the welding line, and the welding line is well protected.

Finally, it is noted that the above-mentioned embodiments are merely for illustrating the technical solution of the present utility model, and that other modifications and equivalents thereof by those skilled in the art should be included in the scope of the claims of the present utility model without departing from the spirit and scope of the technical solution of the present utility model.

Claims

1. A anchor clamps that is used for broken hole of aircraft duralumin main bearing structure to damage normal position to salvage, anchor clamps body (101) including C, its characterized in that: the device also comprises a pressure head module arranged on the clamp body (101) and a gas container cavity (102) arranged at the lower part of the clamp body (101);

the pressure head module comprises a front rotary pressure head vertically threaded at the top end part of the clamp body (101), two support arms (103) transversely arranged on the inner side wall of the upper end of the clamp body (101) in a splayed shape and side screws Niu Yatou respectively vertically threaded at the end parts of the two support arms (103);

the inside of gas container chamber (102) is still vertically provided with ejector pin (104) that are used for supporting prefabricated patch, the top of ejector pin (104) is parallel and level with the top of gas container chamber (102).

2. The fixture for in-situ repair of hole damage in an aircraft duralumin main bearing structure of claim 1, wherein: the front rotary pressure head comprises a main threaded rod (201) vertically in threaded connection with the top end part of the clamp body (101), a main pressing block (202) arranged at the bottom of the main threaded rod (201) and a main rotary handle (203) arranged at the upper end of the main threaded rod (201).

3. The fixture for in-situ repair of hole damage of hard aluminum main bearing structure of aircraft as claimed in claim 2, wherein: the side knob pressure head comprises a side threaded rod (301) vertically in threaded connection with the end part of the support arm (103), a side pressure block (302) arranged at the bottom of the side threaded rod (301) and a side knob (303) arranged at the upper end of the side threaded rod (301).

4. The fixture for in-situ repair of hole damage in an aircraft duralumin main bearing structure of claim 3, wherein: the main pressing block (202) is in threaded connection with the lower end of the main threaded rod (201).

5. The fixture for in-situ repair of hole damage in an aircraft duralumin main bearing structure of claim 4, wherein: the side pressing block (302) is in threaded connection with the lower end of the side threaded rod (301).

6. The fixture for in-situ repair of hole damage in an aircraft duralumin main bearing structure of claim 5, wherein: the main knob (203) is also provided with a main anti-skid sleeve (204).

7. The fixture for in-situ repair of hole damage in an aircraft duralumin main bearing structure of claim 6, wherein: and a side anti-skid sleeve (304) is further arranged on the side rotating handle (303).

8. The fixture for in-situ emergency repair of hole damage in an aircraft duralumin main bearing structure as recited in any one of claims 1-7, wherein: the diameter of the ejector rod (104) in the gas container cavity (102) is 5mm.

9. The fixture for in-situ repair of hole damage in an aircraft duralumin main bearing structure of claim 1, wherein: the gas container cavity (102) is positioned at the lower part of a hole to be welded and repaired on the machine body, and the hole to be welded and repaired on the machine body can be wrapped.