Search

CN-122008594-A - Process cover plate structure of co-cured fuselage wall plate and manufacturing method thereof

CN122008594ACN 122008594 ACN122008594 ACN 122008594ACN-122008594-A

Abstract

The invention belongs to the technical field of composite material manufacturing, and discloses a process cover plate structure of a co-cured fuselage wallboard and a manufacturing method thereof. The cover plate body comprises connecting fixing pieces which are pre-buried at two ends of the cover plate body, and the connecting fixing pieces at two ends are at least partially protruded out of the cover plate body. The connecting assembly comprises a first connecting piece, a second connecting piece and a locking piece, wherein the first connecting piece is connected with a connecting fixing piece at one end of the cover plate body, the second connecting piece is connected with a connecting fixing piece at the other end of the cover plate body, and the locking piece can connect and fix the first connecting piece and the second connecting piece. According to the invention, the connecting fixing pieces are pre-buried on the cover plate bodies, the first connecting pieces and the second connecting pieces are respectively butted with the connecting fixing pieces at the adjacent end parts, and then the first connecting pieces and the second connecting pieces are stably connected through the locking pieces, so that the positioning and matching of the two adjacent cover plate bodies are simple and easy to place, and the field assembly efficiency is remarkably improved.

Inventors

  • HU CHENGHAO
  • YU JINGJING
  • ZHAO ZHIBO
  • LI TONG
  • ZHANG KAI

Assignees

  • 上海飞机制造有限公司

Dates

Publication Date
20260512
Application Date
20260401

Claims (10)

  1. 1. The process cover plate structure of the co-cured fuselage wallboard is characterized by comprising at least two cover plate bodies (1) and a connecting assembly (2), wherein the cover plate bodies (1) comprise connecting fixing pieces (11) pre-buried at two ends of the cover plate bodies (1), and the connecting fixing pieces (11) at two ends at least partially protrude out of the cover plate bodies (1); The connecting assembly (2) comprises a first connecting piece (21), a second connecting piece (22) and a locking piece (23), wherein the first connecting piece (21) is connected with the connecting fixing piece (11) at one end of the cover plate body (1), the second connecting piece (22) is connected with the connecting fixing piece (11) at the other end of the cover plate body (1), and the locking piece (23) can connect and fix the first connecting piece (21) and the second connecting piece (22).
  2. 2. The process cover plate structure of the co-cured fuselage panel according to claim 1, wherein the first connecting piece (21) and the second connecting piece (22) comprise a connecting seat (24) and a switching part, the connecting seat (24) is used for being connected with the corresponding connecting fixing piece (11), one end, far away from the cover plate body (1), of the connecting fixing piece (11) is provided with a clamping block, the connecting seat (24) is provided with a clamping groove matched with the clamping block, the clamping block is placed in the clamping groove, and the switching parts on the first connecting piece (21) and the second connecting piece (22) can be connected with the locking piece (23).
  3. 3. The process cover structure of a co-cured fuselage panel according to claim 2, characterized in that the transition of one of the first and second connection pieces (21, 22) is provided as a projection (25), the transition of the other of the first and second connection pieces (21, 22) is provided as a recess (26) corresponding to the projection (25), the locking piece (23) being able to pass through one side wall of the recess (26), the projection (25) and the other side wall of the recess (26) in sequence.
  4. 4. A process cover structure of a co-cured fuselage panel according to claim 3, characterized in that the locking element (23) comprises a bolt and a nut, the bolt being lockable with the nut through the first and second connection elements (21, 22).
  5. 5. The process cover plate structure of the co-cured fuselage panel according to claim 2, wherein the connecting fixing piece (11) comprises an embedded part and a connecting part, the embedded part is embedded in the cover plate body (1), the connecting part protrudes out of the cover plate body (1), and the connecting part is provided with the clamping block for connecting with the first connecting piece (21) or the second connecting piece (22).
  6. 6. The process cover plate structure of the co-cured fuselage panel according to claim 5, wherein an end of the embedded portion, which is far away from the connecting portion, is provided with an anti-drop structure.
  7. 7. The process cover plate structure of the co-cured fuselage panel according to claim 1, wherein a plurality of connecting fixtures (11) are arranged at the end of the cover plate body (1) along a first direction, and a plurality of connecting assemblies (2) respectively connect and fix the corresponding two connecting fixtures (11), wherein the first direction is perpendicular to the connecting direction of the cover plate body (1).
  8. 8. A method of making a process cover structure for a co-cured fuselage panel, the process cover structure (200) adapted for use with a co-cured fuselage panel of any one of claims 1-7, comprising: Placing the cover plate body (1) according to a preset position; The first connecting piece (21) and the second connecting piece (22) are respectively connected with the connecting fixing piece (11); The locking piece (23) connects the first connecting piece (21) and the second connecting piece (22) until the cover plate body (1) is connected end to end.
  9. 9. The method for manufacturing the process cover plate structure of the co-cured fuselage panel according to claim 8, wherein the method further comprises the steps of laying a cover plate layer (12) on a forming die (3) before the cover plate body (1) is placed according to a preset position, and burying a connecting fixing piece (11) on the cover plate layer (12) in the laying process; and (3) curing the cover plate layering (12) in an autoclave.
  10. 10. The method for manufacturing the process cover plate structure of the co-cured fuselage panel according to claim 8, wherein the step of placing the cover plate body (1) according to a preset position is preceded by placing the cover plate body (1) on the co-cured hat-shaped ribs (100) according to the preset position.

Description

Process cover plate structure of co-cured fuselage wall plate and manufacturing method thereof Technical Field The invention relates to the technical field of composite material manufacturing, in particular to a process cover plate structure of a co-cured fuselage wall plate and a manufacturing method thereof. Background In the manufacturing process of the composite material co-cured wallboard, a male mold forming scheme is often adopted for skin forming, in order to ensure skin forming quality, auxiliary forming is carried out on a skin surface by virtue of a process cover plate, the skin is ensured to be attached to a male mold surface, and forming precision meets design requirements, and the process cover plate becomes a key auxiliary tool part in the forming process of the composite material component, and is particularly widely applied to the manufacturing field of high-end composite material structures such as aerospace and the like. However, in the actual production process, the method is limited by the conditions such as structural complexity, size specification and the like of the composite material co-cured wallboard, if the integral type process cover plate is adopted for design and manufacture, the method has obvious technical and cost defects that on one hand, the manufacturing cost of the integral type process cover plate is high, and on the other hand, the process application difficulty of the integral type process cover plate is greatly improved due to the fact that the integral type process cover plate is large in size and high in structural rigidity, the process application difficulty is particularly represented by inconvenient transportation and assembly in the personnel operation process, and meanwhile, the positioning profile matching difficulty of the cover plate and the male die and the skin is large, positioning deviation is easy to occur, so that the skin forming precision is influenced, and on the other hand, for part of the composite material co-cured wallboard part with a special appearance structure, the integral type process cover plate cannot be used for auxiliary forming due to the structural profile, curvature change and the like of the integral type process cover plate, and the process cover plate must be subjected to block design, block manufacturing and block application to adapt to the special structural requirements of the part. At present, each block cover plate of the conventional block composite material process cover plate is required to complete prepreg paving, curing and forming and subsequent machining processes through independent forming tools, and the manufacturing processes of each block cover plate are independent. In practical application, the split process cover plates are required to be combined and then used for skin auxiliary forming, the existing combination mode mostly adopts positioning pin holes to connect the split cover plates, but the connection mode has obvious defects that as dimensional deviation, profile errors and the matching precision of the positioning pin holes and the positioning pins are difficult to accurately control in the independent manufacturing process of the split cover plates, the split cover plates are difficult to position and match in combination, the split cover plates are difficult to rapidly and accurately place, good lamination of the split cover plates and the outer surface of the skin paving can not be realized, the pressurizing uniformity and the forming quality of the skin are further influenced, the internal defects such as angle folding protrusions, resin enrichment, layering and the like of the skin are easily caused, and the high-precision manufacturing requirement of the composite material co-cured wallboard can not be met. In summary, the existing process cover plate for forming the composite material co-cured panel skin has the problems of high manufacturing cost, large process application difficulty, poor positioning and attaching effects and the like, whether the existing process cover plate is of an integral type or a conventional block type structure, so that the manufacturing efficiency and the forming quality of the composite material co-cured panel are restricted, and a process cover plate structure of the co-cured fuselage panel and a manufacturing method thereof are needed to solve the technical problems. Disclosure of Invention The invention aims to provide a process cover plate structure of a co-cured fuselage wall plate and a manufacturing method thereof, which are used for solving the technical problems of high manufacturing cost, high process application difficulty, poor positioning and laminating effects and the like in the prior art. The technical scheme adopted by the invention is as follows: in one aspect, a process cover plate structure of a co-cured fuselage panel is provided, which comprises at least two cover plate bodies and a connecting assembly, wherein the cover plate bodies comprise