JP2774253B2 - Repair method for brazed honeycomb panel unbonded parts - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a method of repairing a non-joined portion of a brazed honeycomb panel, and more particularly, to a method of repairing a non-joined portion between a face plate and an edge material of an aluminum honeycomb panel formed by brazing. .

[0002]

2. Description of the Related Art As shown in FIG. 4, an aluminum brazed honeycomb panel is formed of an end portion of a honeycomb core 2 formed from a thin plate or foil of aluminum (including an aluminum alloy, the same applies hereinafter), and an intermediate portion if necessary. An edge member 4 made of an aluminum profile is disposed in the portion, and a face plate 3 made of an aluminum brazing sheet is placed on the upper and lower sides, fixed with a jig, and then put into a brazing furnace to form a brazing unit. In the fields of space, vehicles, automobiles, and the like, they have been applied as members requiring light weight and high specific rigidity.

[0003] Aluminum brazed honeycomb panel 1
As shown in FIG. 4, brazing is performed between the honeycomb core 2 and the honeycomb core 2, between the honeycomb core 2 and the face plate 3, between the honeycomb core 2 and the edge material 4, and between the honeycomb core 2 and the edge material 4. 3 and the edge material 4, the bonding D between the face plate 3 and the edge material 4 which is a strength member is particularly complete. It is extremely important in maintaining the characteristics.

[0004] Conventionally, if a defective joint at the joint D is found during the manufacture of an aluminum brazed honeycomb panel, remanufacturing is performed. After the honeycomb panel is assembled to a vehicle or the like, the defective joint becomes apparent. When it did, the part was cut off and replaced with a new honeycomb panel. Also, after being assembled as a member in a vehicle, an automobile, or the like, and traveling for a certain distance or a certain time or more, the joint D
In the event that a bonding failure occurs, the honeycomb panel must be replaced only for that reason, which requires a lot of man-hours and time, and a lot of waste in material.

[0005]

SUMMARY OF THE INVENTION The present invention has been made to solve the above-mentioned problems in the aluminum brazed honeycomb panel, and an object of the present invention is to provide a face plate and an edge material of the aluminum brazed honeycomb panel. An object of the present invention is to provide a method of repairing a non-joined portion by welding without causing a problem in strength when a non-joined portion occurs between the two.

[0006]

According to the present invention, there is provided a method for repairing a non-joined portion of a brazed honeycomb panel according to the present invention. When repairing the unjoined portion between the face plate and the edge material of the aluminum honeycomb panel formed by brazing, the unjoined portion between the face plate and the edge material is cut to at least a depth where the brazing material layer does not remain, and the cut portion After inert gas welding under conditions that do not dissolve into the back surface of the edge material, the excess portion of the welded portion is removed.

In addition, the edge material is cut to a depth not exceeding 3/4 of its thickness, and a backing plate and an anti-strain agent are arranged around a cut portion formed at an unjoined portion. Are the second and third features of the present invention.

In the present invention, as shown in FIG. 1, the upper and lower face plates 3, a honeycomb core 2 disposed between the face plates 3, and an edge member 4 are formed by mutually brazing aluminum. In the honeycomb panel 1, when a non-joined portion occurs between the face plate 3 and the edge member 4, a cut portion 5 is formed in the non-joined portion, and the non-joined portion is repaired by welding the cut portion 5. Things.

The cutout 5 is formed by shaving with a grinder or an end mill. The depth H of the resection is
As shown in FIG. 2, the brazing material layer 6 formed between the face plate 3 and the edge material 4 is set to such a depth that the brazing material layer 6 does not remain, and the brazing material layer 6 is removed. If the brazing material layer 6 is not removed, a gas that causes blowholes is likely to be generated from the brazing material layer during welding.

For welding, it is preferable to apply TIG or MIG welding, which is widely used for welding aluminum, and to weld the cutout 5 under conditions that do not melt into the back surface of the rim 4. If the edge material 4 is melted to the back surface, microfischer cracks are likely to occur around the back bead, which affects the strength of the welded portion. In order to reliably perform repair and obtain a weld having excellent strength, it is necessary to form and weld a cut portion in which the edge material 4 is cut to a depth not exceeding 3/4 of its thickness. preferable. If the cut is made to exceed 3/4 of the thickness of the edge material, there is a possibility that the edge material may melt into the back surface of the edge material during welding.

After welding, the excess portion of the welded portion is removed by a grinder, an end mill, or the like to obtain a welded portion 8 as shown in FIG. In inert gas welding, as shown in FIG. 1, the face plate 3 is restrained by a backing plate 7 to prevent distortion of the honeycomb core portion and to reduce the influence of heat. Preferably, an agent (not shown) is provided. In addition, when the non-joined portion is welded from the surface of the face plate without forming the cutout portion 5 at the non-joined portion, blow holes are easily generated in the welded portion, and the fatigue strength of the welded portion is reduced.

[0012]

According to the present invention, a poorly brazed portion between the face plate and the edge material in the aluminum brazed honeycomb panel is cut to a predetermined depth from the face plate to the edge material, and the formed cut portion is subjected to specific penetration conditions. After the inert gas welding, by removing the excess of the welded portion, a repair welded portion having no problem in strength is formed, and the unbonded portion between the face plate of the brazed honeycomb panel and the edge material is reliably repaired and joined.

[0013]

Hereinafter, examples of the present invention will be described in comparison with comparative examples. Example 1 A 6951 alloy plate having a thickness of 0.5 mm and a cell size of 20 mm
Is formed, and an edge member made of a 6N01 alloy extruded shape (30 mm × 30 mm, thickness 3 mm) is arranged at the end of the core, and an aluminum brazing sheet (core material: 6951 alloy) , Thickness 2 mm.
A skin material: Al-10 wt% Si alloy, clad of 10% on one side) was arranged and brazed to form an aluminum brazed honeycomb panel.

In order to repair by welding the non-joined portion (dimensions: 20 mm × 50 mm, position: center portion of the edge material) between the face plate and the edge material generated in the brazed honeycomb panel, the non-joined portion (2
0 mm x 50 mm) with an end mill to remove the brazing material layer to a depth of 1 mm on the surface of the edge material, and remove 1 mm from the cut and cut part.
At a position 0 mm away, a 5 mm-thick backing plate is fixed and constrained. Further, at a position 10 mm away from the cut and cut portion, a clay for preventing distortion is attached, and a rim material using a 5356 alloy welding rod having a diameter of 2.4 mm. TI so as not to melt into the back of
After the G welding, the excess of the weld was removed by an end mill.

From the welded portion from which the excess was removed, a test piece having a 20 mm × 50 mm weld at the center of the test piece was cut out and subjected to a tensile test.
Repetition rate 1800 cpm, test stress 11 kgf / m
The fatigue strength was evaluated under the condition of m ² . As a result, the static strength is 70% of the strength of the welded portion of the 6N01 alloy constituting the edge material.
And the fatigue strength of the welded part of 6N01 alloy is 70% or more of the load that can be maintained 10 ⁶ times or more, and the weld repaired part having the same strength as the strength of the welded part of 6N01 alloy is obtained. Been formed.

Example 2 In Example 1, the repair welding was performed using a 404 having a diameter of 2.4 mm.
After performing TIG welding using a 3 alloy welding rod so as not to melt into the back surface of the edge material, an excess of the welded portion was removed by an end mill. A test piece similar to that of Example 1 was cut out, and Example 1 was cut out.
As a result of the same strength measurement as above, the strength was slightly lower than that of the test piece of Example 1, but both the static strength and the fatigue strength showed strength characteristics almost equivalent to the strength of the welded portion of 6N01 alloy constituting the edge material. A weld repaired part having no problem in strength was obtained.

Example 3 In Example 1, repair welding was performed by MIG welding. In the MIG welding, a tab plate was applied to a welding start portion, and welding was started from there in consideration of the fact that the penetration was deeper and cracks were more likely to occur than in the TIG welding. After welding, the excess was removed by an end mill, a test piece similar to that of Example 1 was cut out, and the same strength measurement as that of Example 1 was performed. As a result, it showed almost the same strength characteristics as the test piece of Example 1. .

Comparative Example 1 For the unbonded portion having the same dimensions as in Example 1 generated on the brazed honeycomb panel produced in Example 1, only the face plate was cut by an end mill to leave a brazing material layer remaining. Was formed and subjected to TIG welding using a 5356 alloy welding rod having a diameter of 2.4 mm so as not to melt into the back surface of the edge material, and then the excess was removed by an end mill. A test piece similar to that of Example 1 was cut out, and the same strength measurement as that of Example 1 was performed. As a result, a blowhole was formed in the weld metal, and both the static strength and the fatigue strength were 70% of the 6N01 alloy weld. Was less than.

Comparative Example 2 In Comparative Example 1, when repair welding was formed by performing welding that completely melts into the back surface of the edge material, a number of small cracks occurred in the back bead, and the static strength was 6N01 alloy. Approximately 60% of the weld and the fatigue strength were as low as about 30% of the 6N01 alloy weld, and a repair weld having no problem in strength could not be obtained.

COMPARATIVE EXAMPLE 3 A non-bonded portion having the same dimensions as that of Example 1 generated in the brazed honeycomb panel manufactured in Example 1 was formed at 5356 mm in diameter 2.4 mm from the surface of the face plate without forming a cut portion.
When TIG welding was performed using an alloy welding rod, a large number of blowholes were generated in the weld metal. After removing excess metal, a tensile test and a fatigue test were performed using test pieces cut out in the same manner as in Example 1. As a result, all showed low strength of less than 70% of the 6N01 alloy weld.

[0021]

As described above, according to the present invention, it is possible to easily repair a defective bonding portion in an aluminum brazed honeycomb panel. This eliminates the need to replace the honeycomb panel at that location, and is particularly useful for periodic repairs of vehicles and the like.

[Brief description of the drawings]

FIG. 1 is a partially sectional perspective view showing the formation of a cut portion and the arrangement of a backing plate in a repair method of the present invention.

FIG. 2 is a cross-sectional view showing formation of a cut portion in the repair method of the present invention.

FIG. 3 is a partially sectional perspective view showing a repair welded portion of the present invention.

FIG. 4 is a perspective view showing a brazed honeycomb panel with a face plate turned up.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Brazing honeycomb panel 2 Honeycomb core 3 Face plate 4 Edge material 5 Cut-out part 6 Brazing material layer 7 Patch plate 8 Welded part

──────────────────────────────────────────────────続 き Continued on the front page (72) Inventor Hideto Okada 5-11-3 Shimbashi, Minato-ku, Tokyo Inside Sumitomo Light Metal Industries Co., Ltd. (72) Inventor Keizo Namba 5-11-3 Shimbashi, Minato-ku, Tokyo No. Sumitomo Engineering Co., Ltd. (58) Field surveyed (Int. Cl. ⁶ , DB name) B23K 31/00 B21D 47/00 B23K 101: 02

Claims (3)

(57) [Claims] When repairing an unjoined portion between a face plate and an edge material of an aluminum honeycomb panel formed by brazing a honeycomb core and an edge material to each other between the upper and lower surface plates and the upper and lower surface plates, the face plate and the edge material are repaired. Is cut to at least a depth where the brazing material layer does not remain, and the cut portion is subjected to inert gas welding under the condition that it does not melt into the back surface of the edge material, and then the excess portion of the welded portion is removed. Repair method for brazed honeycomb panel unbonded parts. 2. The method according to claim 1, wherein the edge material is cut off to a depth not exceeding 3/4 of its thickness. 3. The method for repairing a brazed honeycomb panel non-joined part according to claim 1, wherein a backing plate and a distortion preventing agent are arranged around a cut part formed in the non-joined part.