CN110450937A - Composite material " work " type stringer wall panel structure, molding die and forming method - Google Patents

Abstract

The present invention relates to technique for aircraft composite technical field, providing a kind of composite material " work " type stringer wall panel structure, molding die and forming method, the wall panel structure includes several " C " type layings, intermediate intercalation, flange intercalation and covering laying；In covering laying, closure and covering the laying solidification of " C " type laying connect " C " type laying lying side-by-side；Intermediate intercalation is set in the gap between adjacent " C " type laying, and intermediate intercalation and the solidification of covering laying connect；The upper flange of " work " type stringer is collectively formed in " C " type laying, the top of intermediate intercalation in the setting of flange intercalation.The present invention can get the splicing area much larger than tradition work shape stringer Material Stiffened Panel, while increasing stringer bearing capacity, reduce the processing capacity of stringer；" C " type laying is supported using Collapsible mould, the release problems of composite material " work " type stringer is solved, the preparation of stringer structure can be fast implemented.

Description

Composite "I" type long truss panel structure, molding die and molding method

technical field

The invention relates to the technical field of aircraft composite materials, in particular to an "I" type long truss panel structure of composite materials, a molding die and a molding method.

Background technique

Composite "I" type long truss reinforced panels are widely used in the main load-bearing structure of the fuselage, especially in the wing panel structure. The common "I" type long truss structure is shown in Figure 1.

The main problems of the traditional structural form are analyzed as follows:

1. Compared with the T-shaped long truss siding, the "I" type long truss siding has higher structural efficiency, and its bending resistance and long truss edge impact resistance are improved;

2. For the existing "I" type long truss panel structure design scheme, sufficient margins must be reserved for the upper and lower flanges to meet the processing requirements of the manufacturing boundary;

3. The traditional "I" type long truss reinforced wall panel has a small margin of bonding area, which will affect the overall wall panel structure when degumming.

Contents of the invention

One of the purposes of the present invention is to overcome the deficiencies of the prior art and provide a composite material "I" type long truss panel structure, molding die and molding method, which can reduce the waste of raw materials, improve the laying efficiency, and reduce the cost of tooling preparation , improve the bonding quality of the bottom layer of the stringer and the skin, and ensure the quality and precision of the product.

The present invention adopts following technical scheme:

A composite material "I" type long truss panel structure, which is used for aircraft wing panels. and skin layup;

Several "C"-shaped layups are laid side by side on the skin layup, the closed part of the "C"-shaped layup is flat, and the closed part is solidified and connected to the skin layup There is a gap between the two adjacent "C" type layups, the intermediate intercalation is set in the gap, the intermediate intercalation and the "C" type layup and the skin layup are all solidified and connected; the flange interposer is arranged on the top of the "C" type layup and the middle interposer to form the upper flange of the "I" type stringer; the flange interposer and the "C" "Type layup and the top of the intercalation layer are solidified and connected.

Further, co-curing or co-cementing process is adopted among the "C" type layup, intermediate insert, flange insert and skin layup to realize overall curing and molding.

Further, the "C"-shaped layups at both ends of the long stringer panel structure are all semi-C-shaped.

A molding die for the above-mentioned "I" type long truss panel structure of the composite material, comprising:

"C" type ply forming tooling, used for laying up and forming "C" type ply;

Flange tooling, used to lay up and form the upper flange of the "I" type stringer;

Skin tooling is used for laying up skin layers and realizing the solidified connection between "C" type layers and skin layers.

Further, the "C" type ply forming tooling includes detachable left stopper, right stopper, upper stopper and lower stopper;

The lower block is an inverted T-shaped block; the left block and the right block both include a body and a protrusion, and the left block and the right block are symmetrically supported on the wings of the lower block through the protrusion. on the edge surface; the upper block is arranged on the upper part of the lower block; the left block, the right block, the upper block and the lower block can be closely fitted as a whole;

The "C"-shaped layup is preformed by the outer peripheral edges of the left block body, the upper block body, and the right block body.

Further, the flange tooling and the skin tooling are both flat plate structures.

Further, the upper block and the lower block are correspondingly provided with a positioning mechanism; the positioning mechanism is a groove and a protrusion corresponding to the groove;

When the upper stopper is provided with the groove, the lower stopper is provided with the corresponding protrusion; when the lower stopper is provided with the groove, the upper stopper is provided with the corresponding protrusion head.

A method for forming a composite material "I" type long truss panel structure, using the above-mentioned forming die, comprising the following steps:

S1, the left block, the right block, the upper block and the lower block together form a "C"-shaped layup forming tool, which is used for the lay-up of a single "C"-shaped layup; keep the "C"-shaped layup and The relative position of the "C" type layup forming tooling remains unchanged, and the "C" type layup and the "C" type layup tooling form the first combination;

S2. A plurality of the first assemblies are placed side by side in parallel, an intermediate intercalation layer is set between the adjacent "C"-shaped layers, and the R area is filled with twist strips to form a second assembly; the R area It is the gap formed between the "C" type layup and the intercalation layer; then the second assembly is turned over 180° as a whole;

S3. Pull the lower block away, keep the relative position of the left block, right block, upper block and "C"-shaped layup unchanged; place the flange insert and flange tooling according to the design to form the third assembly ;

S4. Position the third assembly with the skin tooling, then combine with the skin layer, and complete the overall co-curing molding after vacuum packaging.

Further, the molding method also includes:

S5. When removing the "C"-shaped ply forming tool, first remove the upper block, and then remove the left block and right block.

Further, in step S2, firstly, several first assemblies are turned over by 180°, and then an intercalation layer is arranged between adjacent "C"-shaped layups to obtain the second assembly.

The present invention also provides an aircraft, which uses the composite material "I" type long girder panel structure.

The beneficial effects of the present invention are: the "C"-shaped layup is fully bonded to the skin layup, and the bonding area of the traditional I-shaped long truss reinforced wall plate is obtained, which increases the bearing capacity of the long truss and reduces The processing amount of the long stringer is reduced, and at the same time, the problem of affecting the entire panel structure due to the degumming of the stringer is effectively avoided; the co-curing or co-gluing process can be used to complete the overall solidification of the panel structure, which greatly improves the manufacturing efficiency. Reduce the loss rate of composite materials; use a detachable mold to support the "C"-shaped layup, solve the problem of demoulding the "I"-shaped stringer of composite materials, and can quickly realize the preparation of the stringer structure; the process of the invention is simple and easy , has great promotional value.

Description of drawings

Figure 1 is a schematic diagram of the traditional "I" type long truss panel structure.

Fig. 2 is a schematic diagram showing the structure of a composite material "I" long truss panel according to an embodiment of the present invention.

Figure 3 is a schematic diagram of the structure of the "C" type layup forming tooling.

Fig. 4 is a schematic structural diagram of the second assembly.

Fig. 5 is a schematic diagram of the structure of the third assembly.

Figure 6 shows the demoulding schematic diagram of the mandrel structure of the composite "I" type long truss panel structure.

Figure 7 shows a schematic structural view of the left block (right block).

In the figure: 1-left stopper; 2-upper stopper; 3-right stopper; 4-lower stopper; 5-"C" type layup; 6-middle intercalation; -flange intercalation; 9-flange tooling; 10-skin layup; 11-skin tooling; 101-body; 102-protrusion.

Detailed ways

Specific embodiments of the present invention will be described in detail below in conjunction with specific drawings. It should be noted that the technical features or combinations of technical features described in the following embodiments should not be regarded as isolated, and they can be combined with each other to achieve better technical effects.

As shown in Figure 2, the embodiment of the present invention is a composite material "I" type long girder panel structure, including several "C" type layups 5, intermediate inserts 6, flange inserts 8 and skin layups 10; Several "C" type layups 5 are laid side by side on the skin layup 10, the closed part of the "C" shaped layup 5 is plane, and the closed part and the covering The skin layer 10 is solidified and connected; there is a gap between the two adjacent "C" type layers 5, and the intermediate layer 6 is arranged in the gap, and the bottom of the intermediate layer 6 is connected to the The skin layer 10 is solidified and connected; the flange interlayer 8 is arranged on the top of the "C" type layer 5 and the middle interposer 6 to jointly form the upper flange of the "I" type stringer; the flange The tops of the edge intercalation layer 8 and the "C" type layup layer 5 and the intermediate intercalation layer 6 are solidified and connected.

Preferably, a co-curing or co-bonding process is used between the "C"-shaped layup 5, the intermediate intercalation layer 6, the flange intercalation layer 8 and the skin layup layer 10 to achieve overall curing and molding.

The "C"-shaped layups 5 at both ends of the long stringer wall structure are all semi-C-shaped (half or part of a complete "C"-shaped layup), and the ends of the flange inserts 8 (with the skin layup 10. Fill the R-angle filler 7 in the R-angle gap formed by the “C”-shaped layup 5 together.

The embodiment of the present invention can increase the effective bonding area between the long stringer and the skin structure and increase the load bearing capacity of the long stringer by automatic tape laying or manual laying. At the same time, the processing amount of the stringer is reduced.

As shown in Figure 3, an embodiment of the present invention is a molding die for the above-mentioned "I" type long truss panel structure of the composite material, including:

"C" type layup forming tooling is used for laying up and forming "C" type layup 5; preferably, the "C" type layup forming tooling includes detachable left stopper 1, right stopper 3, Upper block 2 and lower block 4; Described lower block 4 is an inverted T block; Described left block 1, right block 3 all comprise body 101 and protrusion 102, as shown in Figure 7 (body 101 It is used for forming the "C" type layup 5, and the protruding part 102 is used for the pavement and positioning of the flange interlayer 8 and the flange tooling 9), the left stopper 1 and the right stopper 3 are symmetrical through the protruding part 102 Supported on the flange surface of the lower block 4; the upper block 2 is arranged on the upper part of the lower block 4; the left block 1, the right block 3, the upper block 2 and the lower block 4 can be tightly fitted as a whole; the "C"-shaped layup 5 is preformed by the outer peripheral edges of the left block body, the upper block 2, and the right block body

The flange tooling 9 is a flat plate structure, which is used to lay up and form the upper flange of the "I" type stringer;

The skin tooling 11 is a flat plate structure, and is used for laying up the skin layer 10 and realizing the solidified connection between the "C"-shaped layer 5 and the skin layer 10 .

Preferably, the upper block 2 and the lower block 4 are correspondingly provided with a positioning mechanism; the positioning mechanism is a groove and a protrusion corresponding to the groove; when the upper block 2 is provided with the groove , the lower stop 4 is provided with the corresponding protrusion; or when the lower stop 4 is provided with the groove, the upper stop 2 is provided with the corresponding protrusion.

The molding die provided by the invention solves the demoulding problem of the "I"-shaped stringer of composite materials, can quickly realize the preparation of the stringer structure, and improves the production efficiency of stringer forming.

In an embodiment of the present invention, a method for forming a composite material "I" type long truss panel structure, using the above-mentioned forming mold, includes the following steps:

S1, left stopper 1, right stopper 3, upper stopper 2 and lower stopper 4 together form a "C"-shaped layup forming tool, which is used for the layup and molding of a single "C"-shaped layup 5 (and later with The solidified molding after the overall combination of the skin layer 10); the matching structure between the left stopper 1, the right stopper 3 and the lower stopper 4, and the cooperation between the grooves and the protrusions between the upper stopper 2 and the lower stopper 4 The structure ensures that the overall matching clearance of the combined molding tooling meets the requirements; the relative position of the "C" type layup 5 and the "C" type layup forming tooling remains unchanged, and the "C" type layup 5 and the "C" type layup Layers of tooling form the first assembly; as shown in Figure 3;

S2. A plurality of the first assemblies are placed side by side in parallel, an intermediate intercalation layer 6 is arranged between the adjacent "C"-shaped layups 5, and the filling of the R area is completed by using twist strips to form a second assembly; The R zone is the gap formed between the "C" type layup 5 and the intercalation layer 6; Turn over 180 °, and then set the intermediate intercalation layer 6 between the adjacent "C" type layups 5 to obtain the second assembly); as shown in Figure 4;

S3. Pull the lower block 4 away, keep the relative positions of the left block 1, the right block 3, the upper block 2 and the "C" type layup 5 unchanged; place the flange interlayer 8 and the flange tooling according to the design 9, forming a third assembly; as shown in Figure 5;

S4. Position the third assembly with the skin tooling 11, then combine with the skin layer 10, and complete the overall co-curing molding after vacuum packaging, as shown in Figure 5;

In view of the difficulty in demoulding the I-shaped long truss co-cured panel structure, this application also designed the demoulding process S5 for removing the "C"-shaped layer forming tooling as shown in Figure 6: removing the "C" " type layup forming tooling, first remove the upper block 2, then remove the left block 1, right block 3.

Although several embodiments of the present invention have been given herein, those skilled in the art should understand that the embodiments herein can be changed without departing from the spirit of the present invention. The above-mentioned embodiments are only exemplary, and the embodiments herein should not be used as limitations on the scope of rights of the present invention.

Claims (10)

1. a kind of composite material " work " type stringer wall panel structure, which is characterized in that inserted including " C " type laying, intermediate intercalation, flange Layer and covering laying；

" C " type laying side by side parallel described in several is laid in the covering laying, and the closure of " C " the type laying is in flat Face, the closure and covering laying solidification connect；There are gaps between " C " type laying described in adjacent 2, between described The intermediate intercalation is set in gap, and the intermediate intercalation solidifies with " C " type laying and the covering laying to be connect；The flange Intercalation setting forms the upper flange of " work " type stringer at " C " the type laying and the top of intermediate intercalation；The flange intercalation with " C " the type laying, intermediate intercalation top solidify connection.

2. composite material " work " type stringer wall panel structure as described in claim 1, which is characterized in that " C " the type laying, in Between between intercalation, flange intercalation and covering laying using co-curing or altogether cementation process realize integral solidifying.

3. composite material " work " type stringer wall panel structure as described in claim 1, which is characterized in that the stringer wall panel structure " C " the type laying at both ends is half c-type.

4. a kind of molding die of composite material as described in any one of claims 1-3 " work " type stringer wall panel structure, special Sign is, comprising:

" C " type laying forming frock is used for lay-up molding " C " type laying；

Flange tooling is used for the upper flange of lay-up molding " work " type stringer；

Covering tooling is used for laying covering laying, and realizes that " C " type laying is connect with the solidification of covering laying.

5. molding die as claimed in claim 4, which is characterized in that " C " the type laying forming frock, including it is dismountable Left block, right block, upper stopper and lower stopper；

The lower stopper is inverted T shaped piece；The left block, right block include ontology and protruding portion, the left block, right block Through protruding portion symmetric support in the flange surfaces of the lower stopper；The upper stopper is arranged on the lower stopper top； The left block, right block, upper stopper and lower stopper, which can fit closely, to be integral；

" C " the type laying is preforming by the left stop block body, upper stopper, the outer peripheral edge of right stop block body.

6. molding die as claimed in claim 5, which is characterized in that the flange tooling, covering tooling are slab construction.

7. molding die as claimed in claim 5, which is characterized in that the upper stopper, lower stopper are correspondingly arranged positioning mechanism； The positioning mechanism is groove and plush copper corresponding with the groove；

When the groove is arranged in the upper stopper, the corresponding plush copper is arranged in the lower stopper；When the lower stopper is arranged When the groove, the corresponding plush copper is arranged in the upper stopper.

8. a kind of forming method of composite material " work " type stringer wall panel structure, which is characterized in that using such as claim 5 or 6 The molding die, includes the following steps:

S1, left block, right block, upper stopper and lower stopper collectively constitute " C " type laying forming frock, for single " C " type paving The lay-up molding of layer；Keep " C " type laying and the relative position of " C " type laying forming frock constant, " C " type laying and " C " type Laying tooling forms the first assembly；

S2, several described first assembly side by side parallel are placed, and intermediate intercalation is arranged between adjacent " C " the type laying, Zone R is completed using spill item to fill, and forms the second assembly；The Zone R is to be formed between " C " the type laying and intermediate intercalation Gap；Then second assembly is subjected to whole 180 ° of overturning；

S3, lower stopper is detached, keeps left block, right block, upper stopper and " C " type laying relative position constant；According to design Flange intercalation and flange tooling are placed, third assembly is formed；

S4, it will be positioned between the third assembly and covering tooling, be then combined with covering laying, completed after Vacuum Package Whole co-curing molding.

9. forming method as claimed in claim 8, which is characterized in that the forming method further include:

Described in S5, dismounting when " C " type laying forming frock, the upper stopper is first removed, then removes the left block, right gear Block.

10. forming method as claimed in claim 8 or 9, which is characterized in that in step S2, first several described first Assembly carries out 180 ° of overturning, and intermediate intercalation is then arranged between adjacent " C " the type laying, obtains second combination Body.