CN215203546U - Bonding and curing tool for electric heating front edge of airplane tail wing - Google Patents
Bonding and curing tool for electric heating front edge of airplane tail wing Download PDFInfo
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- CN215203546U CN215203546U CN202120577616.0U CN202120577616U CN215203546U CN 215203546 U CN215203546 U CN 215203546U CN 202120577616 U CN202120577616 U CN 202120577616U CN 215203546 U CN215203546 U CN 215203546U
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Abstract
An electric heating front edge glue joint curing tool for an airplane empennage relates to the field of aviation maintenance process equipment, and comprises a base and a working profile arranged on the base, wherein the working profile comprises a first concave section, a second concave section and a third concave section; the plane projection of the first concave section is semicircular, the plane projection of the third concave section is semielliptical, and the second concave section is positioned between the first concave section and the third concave section and is respectively connected with the first concave section and the third concave section smoothly; a concave cavity matched with the working molded surface is formed in the upper end surface of the base, and the working molded surface is arranged in the concave cavity and fixed with the base; through setting up dedicated cementing solidification frock structure to set up on this frock and heat leading edge assorted work profile with aircraft fin electricity, make operating personnel when laying formation to aircraft fin electricity front edge that heats, can effectually guarantee the precision of mating formation.
Description
Technical Field
The utility model relates to an aviation maintenance technology equipment field, especially an aircraft fin electrical heating leading edge splices solidification frock.
Background
The electric heating front edge of the airplane tail wing is of a multilayer structure, and referring to fig. 1, an outer skin, an outer insulating layer, an electric heating element, an inner insulating layer and an inner skin are layered and paved on a tool, then vacuum pumping is carried out through a vacuum bag, and the film enters an autoclave for heating, pressurizing, cementing, curing and forming; the function of the aircraft is to ensure that the aircraft is in a normal aerodynamic shape, prevent the aircraft from freezing under the meteorological condition that the aircraft may freeze or remove the ice which is formed, and ensure the flight safety.
The traditional leading edge cementing tool is manufactured by a molding line template method, a phenolic aldehyde laminated cloth plate is used for manufacturing a main body frame, epoxy resin is used for manufacturing a working profile, the working profile is formed by gradually manually grinding the working profile by on-site comparison mainly based on an on-machine physical sampling template, and the defects of complex working procedures, low manufacturing precision, long manufacturing period, high manufacturing cost, low service life and the like exist.
SUMMERY OF THE UTILITY MODEL
To the problem that exists among the prior art, the utility model provides a dedicated joint solidification frock can effective control and guarantee that the product splices the appearance profile precision after shaping through utilizing this frock.
The utility model provides a concrete scheme as follows:
an adhesive curing tool for an electrically heated front edge of an airplane empennage comprises a base and a working profile arranged on the base,
the working profile comprises a first concave section, a second concave section and a third concave section; the plane projection of the first concave section is semicircular, the plane projection of the third concave section is semielliptical, and the second concave section is positioned between the first concave section and the third concave section and is respectively connected with the first concave section and the third concave section smoothly;
the upper end face of the base is provided with a concave cavity matched with the working molded surface, and the working molded surface is arranged in the concave cavity and fixed with the base.
Further, the glue joint curing tool further comprises a first residual edge, a second residual edge and a third residual edge, wherein the first residual edge is the same as the first concave section in shape and is fixedly attached to the first concave section; the second remaining edges are arranged on two sides of the working molded surface to form folded edges; the third remaining edge has the same shape as the third concave section and is fixedly attached to the third concave section.
Furthermore, a chord line is drawn at the bottom of the working molded surface; edge lines and margin lines are drawn between the working profile and the first margin, the second margin and the third margin.
Further, at least three TB point position measuring holes are arranged on the second remaining edge.
Furthermore, the base comprises a plurality of supporting blocks, each supporting block is internally provided with a concave opening, and the curvature radius of each concave opening is different; and a plurality of supporting blocks are arranged in an array to form the concave cavity.
Further, the base further comprises a reinforcing plate located at the bottom of the cavity to support the working profile.
Furthermore, lightening holes are formed in the supporting block and the reinforcing plate.
Furthermore, the base is formed by welding an aluminum alloy material through assembly welding, and the whole body after welding is subjected to stress relief heat treatment to fully eliminate welding stress.
The beneficial effect that adopts this technical scheme to reach does:
by arranging the special glue joint curing tool structure and arranging the working molded surface matched with the electric heating front edge of the airplane tail wing on the tool, the laying precision can be effectively ensured when an operator lays the electric heating front edge of the airplane tail wing in layers; the subsequent steps of vacuum bag making, vacuumizing, heating, pressurizing, cementing, curing and forming and the like are more stable.
Drawings
Fig. 1 is a perspective view of an electrically heated leading edge of an airplane tail.
Fig. 2 is a three-dimensional structure diagram of the glue joint curing tool.
Figure 3 is a perspective view of the working profile.
Fig. 4 is a plan view of the first concave section.
Fig. 5 is a plan view of the third concave section.
Fig. 6 is a schematic cross-sectional view a-a of fig. 3, showing the cross-sectional structure of the working profile.
Fig. 7 is a perspective view of the base.
Wherein: the structure comprises a base 10, a supporting block 11, a concave opening 12, a reinforcing plate 13, a working profile 20, a first concave section 21, a second concave section 22, a third concave section 23, a first surplus edge 31, a second surplus edge 32 and a third surplus edge 33.
Detailed Description
The principles and features of the present invention are described below in conjunction with the following drawings, the examples given are only intended to illustrate the present invention and are not intended to limit the scope of the present invention.
The embodiment provides a glue joint curing tool for an electrically heated front edge of an airplane empennage, which is used for realizing a multilayer paving procedure of the electrically heated front edge of the airplane empennage, so that the aim of effectively controlling and ensuring the accuracy of the appearance profile of a product after glue joint forming is fulfilled.
Specifically, referring to fig. 2 to 6, the glue bonding curing tool comprises a base 10 and a working profile 20 arranged on the base 10, wherein the shape of the working profile 20 is the same as the shape of the electric heating front edge of the real tail wing of the airplane; i.e. the working profile 20 comprises a first female section 21, a second female section 22 and a third female section 23; wherein the planar projection of the first concave section 21 is semicircular, which is shown in fig. 4, the planar projection of the third concave section 23 is semielliptical, which is shown in fig. 5, the second concave section 22 is located between the first concave section 21 and the third concave section 23 and is smoothly connected with the first concave section 21 and the third concave section 23, respectively, see fig. 3 and 6.
The working profile 20 can be integrally formed by an integral aluminum plate through numerical control machining, but in consideration of cost input and machining difficulty, a plurality of sections of aluminum plates can be formed through tailor welding; it should be noted that after the tailor welding is completed, flaw detection needs to be performed on the welded seam, and after the tailor welding is completed, room temperature and high temperature air tightness tests are respectively performed on the working profile 20 according to the use state to ensure the sealing performance of the working profile 20.
Meanwhile, the working profile 20 is made of an aluminum plate, and the main purpose is to ensure that the expansion coefficient of the tool is consistent with that of a product because the working profile is the same as that of the electric heating front edge of the airplane empennage; the influence on the shape profile precision of a formed product due to the fact that the expansion coefficients of the working profile 20 and the front edge product are different due to different materials is avoided; the defects of local cracking and air leakage, incapability of bag making and vacuum pumping and the like after the multi-time hot-pressing tank works in a high-temperature and high-pressure environment occur.
In this embodiment, referring to fig. 2 to 3, the adhesive bonding curing tool further includes a first margin 31, a second margin 32 and a third margin 33, wherein the first margin 31 has the same shape as the first concave section 21 and is attached and fixed to the first concave section 21; the second margins 32 are arranged on both sides of the working profile 20 to form hems; the third remaining edge 33 has the same shape as the third concave section 23 and is attached and fixed to the third concave section 23.
It is understood that the working profile 20 is provided with a margin at the periphery, where the first margin 31, the second margin 32 and the third margin 33 are mainly used for forming a vacuum bag sealing area, so that an operator can perform the next bag-making and vacuum-pumping operation after finishing the laying of the outer skin, the outer insulating layer, the electric heating element, the inner insulating layer and the inner skin on the working profile 20.
Optionally, a chord line is drawn at the bottom of the working profile 20; edge lines and margin lines are drawn between the working profile 20 and the first margin 31, the second margin 32 and the third margin 33; the front edge product can be used as a positioning reference and a reference line on the tool through a chord line, an edge line and a margin line, and simultaneously, the outline of the product can be aligned, trimmed and shaped on the tool.
In this embodiment, at least three TB point location measuring holes are disposed on the upper end surface of the second remaining edge 32, and the TB point location measuring holes are used as reference holes for laser measurement detection and respectively mark the detection coordinate values thereof, so that the working profile 20 can be periodically detected by way of digital-to-analog comparison to determine whether it is deformed.
The working profile 20 is fixed on the base 10, and in particular, referring to fig. 2 and 7, a cavity matched with the working profile 20 is arranged on the upper end surface of the base 10, and the working profile 20 is arranged in the cavity and fixed with the base 10.
Optionally, the base 10 includes a plurality of supporting blocks 11, each supporting block 11 is provided with a concave opening 12 therein, and the curvature radius of each concave opening 12 is different; a plurality of support blocks 11 are arranged in an array to form the cavities described above.
At the same time, the base 10 also comprises a reinforcement plate 13, the reinforcement plate 13 being located at the bottom of the cavity to support the working profile 20.
The overall strength and rigidity of the base 10 are improved by arranging the supporting blocks 11 and the reinforcing plates 13; and, at the same time, lightening holes are provided on both the supporting block 11 and the reinforcing plate 13.
The lightening holes can be manufactured through a hollow technology, and compared with the structure of the whole supporting block 11 and the whole reinforcing plate 13, the whole weight of the base can be lightened after the lightening holes are formed; meanwhile, lightening holes distributed in the base 10 are convenient for ensuring smooth circulation of airflow at the bottom of the tool in the heating, pressurizing, gluing and forming process of the autoclave.
Optionally, the base 10 is formed by welding an aluminum alloy material by assembly welding, and the whole welded base is subjected to stress relief heat treatment to sufficiently eliminate welding stress.
Optionally, the base 10 is provided with a rotary lifting ring, and a forklift hole position is further arranged, so that the tool can be lifted and hoisted during displacement and transportation, and convenience is improved.
The above description is only for the preferred embodiment of the present invention, and is not intended to limit the present invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included within the protection scope of the present invention.
Claims (8)
1. An electric heating front edge cementing and curing tool for an airplane empennage, which comprises a base (10) and a working molded surface (20) arranged on the base (10), and is characterized in that,
the working profile (20) comprises a first concave section (21), a second concave section (22) and a third concave section (23); the plane projection of the first concave section (21) is semicircular, the plane projection of the third concave section (23) is semielliptical, and the second concave section (22) is positioned between the first concave section (21) and the third concave section (23) and is respectively connected with the first concave section (21) and the third concave section (23) in a smooth manner;
the upper end face of base (10) be provided with the cavity of work profile (20) looks adaptation, work profile (20) are arranged in the cavity and with base (10) are fixed.
2. The bonding and curing tool for the electric heating front edge of the airplane tail wing of claim 1, further comprising a first margin (31), a second margin (32) and a third margin (33), wherein the first margin (31) has the same shape as the first concave section (21) and is fixedly attached to the first concave section (21); the second remaining edges (32) are arranged on two sides of the working profile (20) to form folded edges; the third remaining edge (33) is the same as the third concave section (23) in shape and is attached and fixed with the third concave section (23).
3. The gluing and curing tool for the electric heating front edge of the airplane tail wing as claimed in claim 2, wherein a chord line is drawn at the bottom of the working profile (20); edge lines and margin lines are drawn between the working profile (20) and the first margin (31), the second margin (32) and the third margin (33).
4. The bonding and curing tool for the electric heating front edge of the airplane empennage as claimed in claim 3, wherein at least three TB point position measuring holes are formed in the second surplus edge (32).
5. The gluing and curing tool for the electrically heated front edge of the empennage of an airplane as claimed in any one of claims 1 to 4, wherein the base (10) comprises a plurality of supporting blocks (11), each supporting block (11) is internally provided with a concave opening (12), and the radius of curvature of each concave opening (12) is different; a plurality of support blocks (11) are arranged in an array to form the cavity.
6. The gluing and curing tool for the electrically heated front edge of the airplane tail wing as claimed in claim 5, wherein the base (10) further comprises a reinforcing plate (13), and the reinforcing plate (13) is located at the bottom of the cavity to support the working profile (20).
7. The bonding and curing tool for the electrically heated front edge of the airplane empennage as claimed in claim 6, wherein lightening holes are formed in the supporting block and the reinforcing plate (13).
8. The bonding and curing tool for the electric heating front edge of the airplane empennage is characterized in that the base (10) and the working profile (20) are made of aluminum alloy materials through assembly welding, and the welding stress is fully eliminated by integrally performing stress relief heat treatment after welding.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120577616.0U CN215203546U (en) | 2021-03-22 | 2021-03-22 | Bonding and curing tool for electric heating front edge of airplane tail wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120577616.0U CN215203546U (en) | 2021-03-22 | 2021-03-22 | Bonding and curing tool for electric heating front edge of airplane tail wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215203546U true CN215203546U (en) | 2021-12-17 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120577616.0U Active CN215203546U (en) | 2021-03-22 | 2021-03-22 | Bonding and curing tool for electric heating front edge of airplane tail wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN215203546U (en) |
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2021
- 2021-03-22 CN CN202120577616.0U patent/CN215203546U/en active Active
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Effective date of registration: 20230310 Address after: 444100 No.1 Lingyun Road, Yuyang office, Dangyang city, Yichang City, Hubei Province Patentee after: Lingyun (Yichang) aviation equipment Engineering Co.,Ltd. Patentee after: LINGYUN SCIENCE & TECHNOLOGY GROUP CO.,LTD. Address before: 430000 No. 200, 1st-19th floor, comprehensive office building south of Jinshan Avenue, Jinyinhu District, Dongxihu District, Wuhan City, Hubei Province Patentee before: Wuhan Lingke aviation composite material Co.,Ltd. Patentee before: LINGYUN SCIENCE & TECHNOLOGY GROUP CO.,LTD. |