Special hole positioning tool after coating construction

Abstract

The invention relates to a special hole positioning tool after coating construction, and belongs to the field of special coating forming. Comprising a front skirt outer circular hole positioning tool and a rear skirt outer circular hole positioning tool. The front skirt outer circular hole positioning tool is arranged on the outer wall of the front skirt of the solid rocket engine shell in a sleeving mode. The outer wall of the rear skirt of the solid rocket engine shell is sleeved with the rear skirt outer circular hole positioning tool; connecting bolts on the outer wall of the front skirt of the solid rocket engine shell are positioned through the front skirt outer circular hole positioning tool; connecting bolts on the outer wall of the rear skirt of the solid rocket engine shell are positioned through a rear skirt outer circular hole positioning tool; the problems that the positioning efficiency is low, the coating is prone to being damaged and the repairing frequency is high when a worker removes the large-thickness coating of the hole are solved.

Description

Technical Field

[0001] The invention belongs to the field of special coating forming, and relates to a special hole positioning tool after coating construction. Background Art

[0002] With the development of aerospace technology, the flight speed of aircraft has increased, the distance has increased, and the time has increased. During the flight, a large amount of aerodynamic heat will be generated, and the thermal environment faced by its structural components is becoming more and more severe. As an effective measure to ensure the stable operation of aircraft, heat-resistant coatings have been widely used in various models and series of products. The external protective coating of solid rocket engines has developed from resin-based external protective coatings to rubber-based flexible external protective coatings, and the coating structure has also developed from a single coating to a composite coating structure.

[0003] After a thick coating is sprayed on the solid engine casing, the holes used for connection on the outer circle of the front and rear skirts of the upper barrel section of the casing are covered by the coating, and the position of the holes cannot be accurately identified. When removing the protection of the holes, the coating around the holes is easily damaged, resulting in coating repair. The repair will add a new coating bonding interface, affecting the coating bonding performance and coating surface quality. Summary of the invention

[0004] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art and to propose a special hole positioning tool after coating construction, which solves the problems of low positioning efficiency, easy damage to the coating and high repair frequency when personnel are removing thick coating from the hole.

[0005] The solution of the present invention is:

[0006] A special hole positioning tool for coating structure, including a front skirt outer circular hole positioning tool and a rear skirt outer circular hole positioning tool;

[0007] The front skirt outer circular hole positioning tooling is mounted on the outer wall of the front skirt of the solid rocket engine case; the rear skirt outer circular hole positioning tooling is mounted on the outer wall of the rear skirt of the solid rocket engine case; the front skirt outer circular hole positioning tooling is used to position the connecting bolts on the outer wall of the front skirt of the solid rocket engine case; the rear skirt outer circular hole positioning tooling is used to position the connecting bolts on the outer wall of the rear skirt of the solid rocket engine case.

[0008] In the above-mentioned coating structure rear special hole positioning tool, the front skirt outer circular hole positioning tool and the rear skirt outer circular hole positioning tool are both made of copper metal material.

[0009] In the above-mentioned coating structure, the special hole positioning tooling is a front skirt outer circular hole positioning tooling that is an arc-shaped plate-like structure; the curvature of the front skirt outer circular hole positioning tooling is adapted to the curvature of the outer wall of the front skirt of the solid rocket engine casing.

[0010] In the above-mentioned coating structure, the four corners of the front skirt outer circular hole positioning tooling are rounded transition structures; the radius of the rounded corners is 10mm; the surface of the front skirt outer circular hole positioning tooling is provided with through holes according to the positions of the connecting bolts on the outer wall of the front skirt of the solid rocket engine casing.

[0011] In the above-mentioned coating structure, the special hole positioning tool is characterized in that: 7 through holes are arranged on the surface of the front skirt outer circular hole positioning tool; 1 through hole is arranged at the center position of the front skirt outer circular hole positioning tool, and the other 6 through holes are symmetrically distributed on both sides of the center through hole; 7 connecting bolts of the outer wall of the front skirt of the solid rocket engine casing extend from the corresponding through holes respectively to achieve positioning.

[0012] In the above-mentioned coating structure, the special hole positioning tooling has a front skirt outer circular hole positioning tooling length of 400mm, the diameter of the outermost through holes on both sides is 15mm; the diameter of the remaining 5 through holes is 5mm; the central angles corresponding to two adjacent through holes from one end to the other are 7.5°, 7.5°, 3.75°, 3.75°, 7.5°, and 7.5° respectively.

[0013] In the above-mentioned coating structure rear special hole positioning tool, the rear skirt outer circular hole positioning tool is an arc-shaped plate structure; the curvature of the rear skirt outer circular hole positioning tool is adapted to the curvature of the outer wall of the rear skirt of the solid rocket engine casing.

[0014] In the above-mentioned coating structure, the four corners of the rear skirt outer circular hole positioning tooling are rounded transition structures; the radius of the rounded corners is 10mm; the surface of the rear skirt outer circular hole positioning tooling is provided with through holes according to the positions of the connecting bolts on the outer wall of the rear skirt of the solid rocket engine casing.

[0015] In the above-mentioned coating structure, a special hole positioning tool is provided, and 9 through holes are arranged on the surface of the rear skirt outer circular hole positioning tool; 1 through hole is arranged at the center position of the rear skirt outer circular hole positioning tool, and the other 8 through holes are symmetrically distributed on both sides of the center through hole; 9 connecting bolts of the outer wall of the rear skirt of the solid rocket engine casing extend from the corresponding through holes respectively to achieve positioning.

[0016] In the above-mentioned coating structure, the special hole positioning tooling has a length of 360 mm for the rear skirt outer circular hole positioning tooling; the diameter of the outermost through holes on both sides is 15 mm; the diameter of the remaining 7 through holes is 5 mm; the central angles corresponding to two adjacent through holes from one end to the other are 3.75°, 3.75°, 3.75°, 1.875°, 1.875°, 3.75°, 3.75°, 3.75°, and 3.75° respectively.

[0017] The beneficial effects of the present invention compared with the prior art are:

[0018] (1) The model positioning tooling body of the present invention is a steel structure, and its appearance is designed to fit the corresponding curvature of the product design, ensuring that the tooling body is completely fitted with the product surface, and characterizing the position characteristics of the fixed part to the coating covering hole;

[0019] (2) The present invention aims at key product features and uses the product positioning hole as a reference to quickly locate the position of the connection holes covered with the coating on the outer circle of the front and rear skirts, without the need for size measurement and positioning, and the operation is simple and convenient;

[0020] (3) The present invention solves the problems of low positioning efficiency, easy damage to the coating, and high repair frequency when personnel are removing thick coatings from holes. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 This is a schematic diagram of the front skirt outer circular hole positioning tooling structure of the present invention;

[0022] Figure 2 It is a schematic diagram of the rear skirt outer circular hole positioning tooling structure of the present invention. DETAILED DESCRIPTION

[0023] The present invention will be further described below in conjunction with the embodiments.

[0024] The invention provides a special hole positioning tool after coating construction, which solves the problems of low positioning efficiency, easy damage to the coating and high repair frequency when personnel remove thick coating from the hole.

[0025] The coating structure is followed by a special hole positioning tool, specifically including a front skirt outer circular hole positioning tool 1 and a rear skirt outer circular hole positioning tool 2. The front skirt outer circular hole positioning tool 1 is mounted on the outer wall of the front skirt of the solid rocket engine case; the rear skirt outer circular hole positioning tool 2 is mounted on the outer wall of the rear skirt of the solid rocket engine case; the front skirt outer circular hole positioning tool 1 is used to position the connecting bolts of the outer wall of the front skirt of the solid rocket engine case; the rear skirt outer circular hole positioning tool 2 is used to position the connecting bolts of the outer wall of the rear skirt of the solid rocket engine case. Both the front skirt outer circular hole positioning tool 1 and the rear skirt outer circular hole positioning tool 2 are made of copper metal material.

[0026] like Figure 1 As shown, the front skirt outer circular hole positioning fixture 1 is an arc-shaped plate-like structure; the curvature of the front skirt outer circular hole positioning fixture 1 is adapted to the curvature of the outer wall of the front skirt of the solid rocket engine case. The four corners of the front skirt outer circular hole positioning fixture 1 are rounded transition structures; the rounded corner radius is 10mm; the surface of the front skirt outer circular hole positioning fixture 1 is provided with through holes according to the positions of the connecting bolts on the outer wall of the front skirt of the solid rocket engine case.

[0027] The surface of the front skirt outer circular hole positioning tool 1 is provided with 7 through holes; a through hole is provided at the center position of the front skirt outer circular hole positioning tool 1, and the other 6 through holes are symmetrically distributed on both sides of the center through hole; the 7 connecting bolts of the outer wall of the front skirt of the solid rocket engine casing extend from the corresponding through holes respectively to achieve positioning.

[0028] The length of the front skirt outer circular hole positioning tool 1 is 400mm, and the diameter of the outermost through holes on both sides is 15mm; the diameters of the remaining 5 through holes are 5mm; the central angles corresponding to two adjacent through holes from one end to the other are 7.5°, 7.5°, 3.75°, 3.75°, 7.5°, and 7.5° respectively.

[0029] like Figure 2 As shown, the rear skirt outer circular hole positioning fixture 2 is an arc-shaped plate-like structure; the curvature of the rear skirt outer circular hole positioning fixture 2 is adapted to the curvature of the outer wall of the rear skirt of the solid rocket engine case. The four corners of the rear skirt outer circular hole positioning fixture 2 are rounded transition structures; the rounded corner radius is 10mm; the surface of the rear skirt outer circular hole positioning fixture 2 is provided with through holes according to the positions of the connecting bolts on the outer wall of the rear skirt of the solid rocket engine case.

[0030] The surface of the rear skirt outer circular hole positioning tool 2 is provided with 9 through holes; one through hole is provided at the center position of the rear skirt outer circular hole positioning tool 2, and the other 8 through holes are symmetrically distributed on both sides of the center through hole; the 9 connecting bolts of the outer wall of the rear skirt of the solid rocket engine casing extend from the corresponding through holes respectively to achieve positioning.

[0031] The length of the rear skirt outer circular hole positioning tool 2 is 360mm; the diameter of the outermost through holes on both sides is 15mm; the diameter of the remaining 7 through holes is 5mm; the central angles corresponding to two adjacent through holes from one end to the other are 3.75°, 3.75°, 3.75°, 1.875°, 1.875°, 3.75°, 3.75°, and 3.75° respectively.

[0032] When in use, the operator uses the positioning holes on the tooling to cover the connecting bolts of the spray tooling, so that the arc surface of the tooling fits with the arc surface of the coating shell after spraying. The center of the reserved hole on the hole positioning tooling is on the same axis as the hole position on the outer circle of the front and rear skirts of the solid rocket engine shell.

[0033] The 7 connecting bolts on the outer wall of the front skirt of the solid rocket motor case are extended from the corresponding through holes of the front skirt outer circular hole positioning tool 1 to achieve the positioning of the 7 connecting bolts and complete the polishing of the connecting bolts. The 9 connecting bolts on the outer wall of the rear skirt of the solid rocket motor case are extended from the corresponding through holes of the rear skirt outer circular hole positioning tool 2 to achieve the positioning of the 9 connecting bolts and complete the polishing of the connecting bolts.

[0034] The model positioning tooling body of the present invention is a steel structure, and its appearance is designed to fit the corresponding curvature of the product design, ensuring that the tooling body is completely fitted with the product surface, characterizing the position characteristics of the fixed part to the coating covering hole.

[0035] The present invention aims at key product features and uses product positioning holes as a reference to quickly locate the positions of the connection holes covered with coatings on the outer circles of the front and rear skirts without the need for size measurement and positioning, and the operation is simple and convenient.

[0036] The invention solves the problems of low positioning efficiency, easy damage to the coating and high repair frequency when personnel remove thick coating from holes.

[0037] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. A special hole positioning tool after coating construction, characterized in that: It comprises a front skirt outer circular hole positioning tool (1) and a rear skirt outer circular hole positioning tool (2); The front skirt outer circular hole positioning tool (1) is mounted on the outer wall of the front skirt of the solid rocket engine case; the rear skirt outer circular hole positioning tool (2) is mounted on the outer wall of the rear skirt of the solid rocket engine case; the connection bolts of the outer wall of the front skirt of the solid rocket engine case are positioned by the front skirt outer circular hole positioning tool (1); and the connection bolts of the outer wall of the rear skirt of the solid rocket engine case are positioned by the rear skirt outer circular hole positioning tool (2).

2. The special hole positioning tool after coating construction according to claim 1, characterized in that: The front skirt outer circular hole positioning tool (1) and the rear skirt outer circular hole positioning tool (2) are both made of copper metal material.

3. The special hole positioning tool after coating construction according to claim 1, characterized in that: The front skirt outer circular hole positioning tool (1) is an arc-shaped plate-shaped structure; the curvature of the front skirt outer circular hole positioning tool (1) is adapted to the curvature of the outer wall of the front skirt of the solid rocket engine casing.

4. The special hole positioning tool after coating construction according to claim 3 is characterized in that: The four corners of the front skirt outer circular hole positioning tool (1) are rounded transition structures; the rounded corner radius is 10 mm; and through holes are arranged on the surface of the front skirt outer circular hole positioning tool (1) according to the positions of the connecting bolts on the outer wall of the front skirt of the solid rocket engine casing.

5. The tooling for positioning special holes after coating construction according to claim 4, characterized in that: The surface of the front skirt outer circular hole positioning tool (1) is provided with 7 through holes; a through hole is provided at the center position of the front skirt outer circular hole positioning tool (1), and the other 6 through holes are symmetrically distributed on both sides of the center through hole; and 7 connecting bolts of the outer wall of the front skirt of the solid rocket engine casing extend from the corresponding through holes respectively to achieve positioning.

6. The special hole positioning tool after coating construction according to claim 4, characterized in that: The front skirt outer circular hole positioning tool (1) has a length of 400 mm, the diameter of the outermost through holes on both sides is 15 mm; the diameters of the remaining five through holes are 5 mm; and the central angles of two adjacent through holes from one end to the other are 7.5°, 7.5°, 3.75°, 3.75°, 7.5°, and 7.5°, respectively.

7. The special hole positioning tool after coating construction according to claim 1, characterized in that: The rear skirt outer circular hole positioning tool (2) is an arc-shaped plate-shaped structure; the curvature of the rear skirt outer circular hole positioning tool (2) is adapted to the curvature of the outer wall of the rear skirt of the solid rocket engine casing.

8. The tooling for positioning holes after coating construction according to claim 7, characterized in that: The four corners of the rear skirt outer circular hole positioning tool (2) are rounded transition structures; the rounded corner radius is 10 mm; and through holes are arranged on the surface of the rear skirt outer circular hole positioning tool (2) according to the positions of the connecting bolts on the outer wall of the rear skirt of the solid rocket engine casing.

9. The special hole positioning tool after coating construction according to claim 8, characterized in that: The surface of the rear skirt outer circular hole positioning tool (2) is provided with 9 through holes; a through hole is provided at the center position of the rear skirt outer circular hole positioning tool (2), and the other 8 through holes are symmetrically distributed on both sides of the center through hole; and 9 connecting bolts of the outer wall of the rear skirt of the solid rocket engine casing extend from the corresponding through holes respectively to achieve positioning.

10. The special hole positioning tool after coating construction according to claim 9, characterized in that: The length of the rear skirt outer circular hole positioning tool (2) is 360 mm; the diameter of the outermost through holes on both sides is 15 mm; the diameter of the remaining 7 through holes is 5 mm; and the central angles of two adjacent through holes from one end to the other are 3.75°, 3.75°, 3.75°, 1.875°, 1.875°, 3.75°, 3.75°, 3.75°, respectively.

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