CN219381694U - Composite material forming die for lower shell structure of target aircraft fuselage plate - Google Patents

Abstract

A composite material forming die for a shell structure at the lower part of a target aircraft fuselage plate belongs to the technical field of composite material part forming. The insert, two locating blocks and four drilling template mounting seats are respectively located and fixed on an upper platform of the frame, the two locating blocks are symmetrically arranged on the left side and the right side of a middle molded surface area of the frame, the insert is placed in the middle molded surface area and arranged at a position corresponding to an R area of a part to be formed, the two drilling template mounting seats are symmetrically arranged on the left side and the right side of the two locating blocks, the two drilling templates are located and fixedly connected with the two drilling template mounting seats, the remaining two drilling template mounting seats are symmetrically arranged behind the two locating blocks, the two angle drilling templates are located and fixedly connected with the remaining two drilling template mounting seats, the two locator assemblies are arranged across the two locating blocks, and the two locator assemblies are located and fixed on the upper platform of the frame. The utility model adopts the positioning blocks and the inserts to control the rebound of the side wall of the composite material and the deformation of the molded surface, thereby avoiding the deformation of the mold.

Description

Composite material forming die for lower shell structure of target aircraft fuselage plate

Technical Field

The utility model belongs to the technical field of composite material part forming, and particularly relates to a composite material forming die for a shell structure at the lower part of a target aircraft fuselage plate.

Background

The target plane is used as a shooting training target and belongs to an unmanned plane. Target drone technology has been rapidly developed in recent years, and is primarily highly mobile and agile, and the target drone is versatile and modular.

The forming die of the target machine is complex in structure, and in order to save weight and reduce weight, a plurality of parts on the target machine are integrated into one part. However, the mode has the defects that the die structure is complex, the die requirement precision is high, the die is difficult to manufacture and difficult to demould, the die deformation is easy to occur, the die and the product laminating degree are very poor, the precision of the formed part is low, the profile deviation is easy to occur, and the design requirement cannot be met. Therefore, a molding die with a more reasonable design structure and a molding method matched with the molding die are needed to meet the molding requirement of the lower shell part of the body plate of the molding target aircraft.

Disclosure of Invention

The utility model aims to solve the problems in the prior art and provides a composite material forming die for a lower shell structure of a target aircraft fuselage plate. The utility model utilizes the positioning block and the insert to control the rebound of the side wall and the deformation of the molded surface of the composite material.

The technical scheme adopted by the utility model is as follows:

a composite material forming die for a shell structure at the lower part of a target aircraft fuselage plate comprises two positioning blocks, an insert, a frame, two angle vertical drilling templates, two angle drilling templates, four drilling template mounting seats and two positioner components;

the two positioning blocks are symmetrically arranged at the left side and the right side of the middle molded surface area of the frame, the insert is placed in the middle molded surface area and arranged at the corresponding position of the R area of the part to be molded, two drill plate mounting seats in the four drill plate mounting seats are symmetrically arranged at the left side and the right side of the two positioning blocks, two angle vertical drill plates are arranged in one-to-one correspondence with the two drill plate mounting seats, the two angle vertical drill plates are respectively positioned and fixed on the corresponding drill plate mounting seats, the remaining two drill plate mounting seats are symmetrically arranged behind the two positioning blocks, the two angle drill plates are respectively positioned and fixed on the corresponding drill plate mounting seats, the two locator assemblies are arranged across the two positioning blocks, and the two locator assemblies are respectively positioned and fixed on the upper platform of the frame.

Further, the two locator assemblies comprise clamping plates, two locators, two corner seats and two supports; the two supports are symmetrically arranged left and right, the two supports are positioned and fixed on an upper platform of the frame, the upper end of each support is positioned and fixedly connected with a corresponding corner seat, the two corner seats are respectively positioned and fixedly connected with two ends of the clamping plate, the two positioners are symmetrically arranged, and the straight handles of the two positioners are respectively positioned and fixedly connected with the clamping plate.

Further, the positioner consists of a straight handle, a bent handle and a positioning head fixedly connected with the outer end of the bent handle.

Further, the support comprises roof, bottom plate, stand and two strengthening ribs, is fixed with the stand between roof and the bottom plate, and stand bilateral symmetry is equipped with two strengthening ribs, two strengthening ribs respectively with stand and bottom plate fixed connection.

Further, four hanging rings are symmetrically and fixedly arranged on the left side and the right side of the frame.

Compared with the prior art, the utility model has the beneficial effects that:

1) The composite material forming die for the lower shell structure of the target aircraft fuselage plate can well solve the problems, which is developed by the utility model, because the lower shell structure of the target aircraft fuselage plate is complex in structure, high in precision and difficult to demould after forming.

2) The processing and manufacturing links are improved; according to the utility model, by adopting an optimized process scheme, the rebound of the side wall and the deformation of the molded surface of the composite material are controlled by utilizing the positioning blocks and the inserts, the influences of factors such as deformation of a mold, inaccurate molded surface and the like are avoided, the processing and manufacturing efficiency is improved, the processing time and labor are greatly improved, the manufacturing period is obviously shortened, and the manufacturing cost is reduced.

3) Because the shell structure at the lower part of the target aircraft fuselage plate is made of composite materials, when in molding, the traditional composite material paving technology cannot meet the technological requirements of high precision and complex molded surfaces of molded product parts. The positioning blocks and the inserts are used for controlling the rebound of the side wall and the deformation of the molded surface of the composite material, so that the precision of the manufactured molded part is qualified, the use requirement is met, the operation working hours of workers can be reduced, and the problems of time and labor waste of the workers in operation are solved.

Drawings

FIG. 1 is an isometric view of a composite forming mold for a lower shell structure of a drone fuselage panel of the present utility model;

FIG. 2 is a front view of a composite forming mold for a lower shell structure of a target aircraft fuselage panel according to the present utility model;

FIG. 3 is a top view of a composite forming mold for a lower shell structure of a target aircraft fuselage panel according to the present utility model;

FIG. 4 is a left side view of a target aircraft fuselage panel lower shell structure composite molding die of the present utility model;

FIG. 5 is a top view of two locating blocks symmetrically disposed;

FIG. 6 is a left side view of FIG. 5;

fig. 7 is a front view of fig. 5;

FIG. 8 is a three view of an insert;

FIG. 9 is a left side view of FIG. 8;

FIG. 10 is a top view of FIG. 8;

FIG. 11 is a front view of the frame;

FIG. 12 is a left side view of FIG. 11;

FIG. 13 is a top view of FIG. 11;

FIG. 14 is a three view of the bushing plate;

fig. 15 is a left side view of fig. 14;

FIG. 16 is a top view of FIG. 14;

FIG. 17 is a front view of the angle bushing plate;

fig. 18 is a left side view of fig. 17;

FIG. 19 is a top view of FIG. 17;

FIG. 20 is a front view of the bushing plate mount;

FIG. 21 is a top view of FIG. 20;

fig. 22 is a left side view of fig. 21;

FIG. 23 is a front view of the positioner assembly;

FIG. 24 is a left side view of FIG. 23;

FIG. 25 is a top view of FIG. 23;

FIG. 26 is a front view of the positioner;

FIG. 27 is a left side view of FIG. 26;

FIG. 28 is a top view of FIG. 26;

FIG. 29 is a front view of the card;

FIG. 30 is a left side view of FIG. 29;

FIG. 31 is a top view of FIG. 29;

FIG. 32 is a front view of the corner seat;

FIG. 33 is a top view of FIG. 32;

FIG. 34 is a view in the A direction of FIG. 33;

FIG. 35 is a front view of the mount;

FIG. 36 is a left side view of FIG. 35;

fig. 37 is a top view of fig. 35.

The component names and numbers referred to in the above figures are as follows:

the angle drilling machine comprises a positioning block 01, an insert 02, a frame 03, a drilling template 04, an angle drilling template 05, a drilling template mounting seat 06, a positioner assembly 07, a positioner 08, a clamping plate 09, an angle seat 10, a support 11, a lifting ring 12, a straight handle 13, a bent handle 14, a positioning head 15, a top plate 16, a bottom plate 17, a stand column 18, a reinforcing rib 19 and a middle profile area 20.

Detailed Description

The first embodiment is as follows: as shown in fig. 1-37, the present embodiment discloses a composite material forming mold for a lower shell structure of a target aircraft fuselage plate, which comprises two positioning blocks 01, an insert 02, a frame 03, two angle vertical drilling templates 04, two angle drilling templates 05, four drilling template mounting seats 06 and two positioner assemblies 07;

the insert 02, the two positioning blocks 01 and the four drilling jig mounting seats 06 are respectively positioned and fixed on an upper platform of the frame 03 (the frame 03 is composed of a frame body and an upper platform fixedly connected with the top end of the frame body), the two positioning blocks 01 are symmetrically arranged at the left side and the right side of a middle molded surface area 20 of the frame 03, the insert 02 is placed in the middle molded surface area 20 and arranged at a position corresponding to an R area of a part to be molded, the two drilling jig mounting seats 06 in the four drilling jig mounting seats 06 are symmetrically arranged at the left side and the right side of the two positioning blocks 01, the two angle vertical drilling jig 04 and the two drilling jig mounting seats 06 are arranged in one-to-one correspondence, the two angle vertical drilling jig 04 are respectively positioned and fixed on the corresponding drilling jig mounting seats 06 (through screw bolts), the rest two drilling jig mounting seats 06 are symmetrically arranged behind the two positioning blocks 01, the two angle drilling jig 05 and the rest two drilling jig mounting seats 06 are arranged one-to-one correspondence, the two angle drilling jig mounting seats 05 are respectively positioned and fixed on the corresponding drilling jig mounting seats 06 (through the screw bolts), and the two positioning jig mounting seats 07 are arranged on the two positioning blocks 03 and the two positioning blocks 07 are respectively positioned on the two positioning blocks.

The insert 02, two angle vertical die plates 04 and angle die plate 05 configuration are prior art.

Further, the two positioner assemblies 07 each comprise a clamping plate 09, two positioners 08, two corner seats 10 and two supports 11; the two supports 11 are symmetrically arranged left and right, the two supports 11 are positioned and fixed on an upper platform of the frame 03 (through screw pins), the upper end of each support 11 is positioned and fixedly connected with a corresponding corner seat 10 (through screw pins), the two corner seats 10 are positioned and fixedly connected with two ends of the clamping plate 09 (through screw pins), the two positioners 08 are symmetrically arranged, and straight handles 13 of the two positioners 08 are positioned and fixedly connected with the clamping plate 09 (through screw pins).

Further, the positioner 08 is composed of a straight handle 13, a bent handle 14 and a positioning head 15 fixedly connected with the outer end of the bent handle 14.

Further, the support 11 is composed of a top plate 16, a bottom plate 17, a column 18 and two reinforcing ribs 19, the column 18 is fixed between the top plate 16 and the bottom plate 17, the two reinforcing ribs 19 are symmetrically arranged on two sides of the column 18, and the two reinforcing ribs 19 are respectively fixedly connected with the column 18 and the bottom plate 17.

Further, four hanging rings 12 (for die lifting) are symmetrically and fixedly arranged on the left side and the right side of the frame 03.

The second embodiment is as follows: as shown in fig. 1-37, the present embodiment discloses a method for forming a composite material of a lower shell structure of a target fuselage panel by using the mold according to the first embodiment, the method comprising the steps of:

step one: blanking (ensuring blanking angle and size) according to process requirements (adopting a blanking machine);

step two: paving mould surfaces on the surfaces of the two positioning blocks 01, the inserts 02 and the middle mould surface area 20 of the frame 03, packaging the two positioning blocks 01 and the inserts 02 paved with the mould surfaces in a vacuum bag after finishing leveling paving, carrying out primary packaging, pumping a complete vacuum of at least 0.08MPa after finishing packaging, carrying out hot compaction, setting the temperature at 60-70 ℃ and the pressure at 0.2MPa, preserving heat and maintaining the pressure for 30min (complete vacuum leakage inspection, pumping the complete vacuum of at least 0.08MPa, connecting with a vacuum system for at least 15 min before leakage inspection, turning off the vacuum system, and reducing the reading of a vacuum meter by not more than 0.017MPa after 5 min), and then disassembling the vacuum bag;

step three: placing the thermally compacted die face, two positioning blocks 01 and an insert 02 in a vacuum bag, sequentially placing a peelable cloth, a separation film and an airfelt on the surface of the die face, removing the positioner assembly 07 after the placement is finished, sequentially placing the peelable cloth, the separation film and the airfelt at the removed position of the positioner assembly 07, carrying out secondary packaging, and vacuumizing to a minimum of 0.08MPa (a minimum of 0.08MPa is pumped after the packaging is finished) (a minimum of 0.08MPa is pumped, the vacuum system is connected with the vacuum system for at least 15 minutes before the leakage inspection, and the vacuum meter reading is reduced by not more than 0.017MPa after 5 minutes);

step four: curing the die in an autoclave, heating to 120 ℃, increasing the pressure to 0.6MPa, preserving heat and pressure for 120-180min, and detecting that the negative pressure reading of the vacuum degree is reduced by not more than 0.017MPa;

step five: after solidification, removing the strippable cloth, the isolating film, the airfelt and the vacuum bag, manufacturing a molded part blank without opening a die, cooling the die to room temperature, drilling positioning holes on the molded part blank by adopting an angle vertical drilling template 04 and an angle drilling template 05, conveying the die and the molded part blank to a numerical control machining center together, establishing a reference by utilizing a tool reference hole arranged around the frame 03, compressing (vacuum suction) by adopting a vacuumizing mode on the edge of the molded part blank, and carrying out numerical control milling on the edge of the molded part blank, wherein the allowance of 0.5mm is reserved on the thickness without milling thoroughly, so as to manufacture the molded part;

step six: demolding (demolding can be performed by using a wood or plastic wedge composite demolding auxiliary tool to prevent damage to a molded part or a molding die), marking the molded part as a mark, applying force to a flanging position of the molded part by using the composite demolding auxiliary tool (existing part), and controlling the force to be 1000-2000N; note that force should be applied uniformly at the four corners of the molded part;

step seven: transferring the formed part to three-coordinate detection equipment, detecting the formed part, and checking the quality of the formed part: the thickness tolerance is allowed to be +/-5%, the beam and wallboard die bonding degree is less than or equal to 0.75mm, the deviation of the stringer axis (compared with the theoretical position) is +/-2 mm, the porosity is not more than 2%, defect inspection of 100% area is carried out, and the materials are delivered for use after the detection is qualified; if the rebound angle and the radius are found to be insufficient in compensation, compensating according to the actual measurement condition of the formed part; if other problems occur, repairing the molded part.

The positioning block 01 is composed of five positioning block monomers, and the five positioning block monomers are all made of Q235-A.F steel and are sequentially welded and connected. And (3) after welding, removing stress, and programming a processing program according to a three-dimensional die by a numerical control processing method according to the pneumatic profile to process the profile of the positioning block 01. The main functions of the positioning block 01 are as follows: the composite material can be used for forming qualified appearance products. The positioning block 01 is positioned and fixed on the upper platform of the frame 03 through screw pins (the matching relationship is H7/g6 clearance fit, and the demolding is convenient).

The whole insert 02 is formed by welding Q235-A.F steel, is subjected to stress relief after welding, and is processed according to the combination of pneumatic appearance surfaces. And (3) programming according to a three-dimensional die, and processing the molded surface of the insert 02 in a numerical control processing mode. The main functions of the insert 02 are: and forming a qualified appearance product part for the composite material. The insert 02 is positioned and fixed on the upper platform of the frame 03 by screw pins (the matching relationship is H7/g6 clearance fit, and the demolding is convenient).

The frame 03 is used as a base of the whole die, Q235-A.F steel is integrally welded and formed, stress is removed after welding, a frame body of the frame 03 is welded by square steel, the top surface of the frame body of the frame 03 is welded with an upper platform of the frame 03, a firm frame 03 is formed, and a middle molded surface is machined according to a pneumatic appearance surface and a three-dimensional die and a machining program. The frame 03 is a basic platform for installing the positioning block 01, the insert 02, the drill plate installation seat 06, the positioner component 07 and the hanging ring 12.

The drill plate 04 (material: aluminum 6061-T651) is programmed according to a three-dimensional die, and a drill plate positioning hole, a screw hole and a pin mounting hole are drilled on the drill plate 04 by a five-axis numerical control machining method. The drill plate 04 is positioned and fixed on the corresponding drill plate mount 06 by means of screw pins.

The angle drilling template 05 (material: aluminum 6061-T651) is programmed according to a three-dimensional model, and a five-axis numerical control machining method is used for drilling template positioning holes, screw holes and pin mounting holes on the angle drilling template 05. The angle jig plates 05 are positioned and fixed on the corresponding jig plate mounts 06 by means of screw pins.

The drill plate mounting seat 06 (material: metal Q235-A.F) is provided with screw holes and pin holes according to theoretical positions on site, and the mounting screw pins are matched with the frame 03 by adopting the clearance fit of H7/g 6.

The locator assembly 07 includes a plurality of locators 08, a card 09, a corner seat 10, and a support 11.

The locator 08 (material: metal Q235-A.F) is processed according to a three-dimensional mould, a processing program is compiled, locating holes, screw holes and pin holes are processed on the locator 08 by a five-axis numerical control processing method, and the locator 08 and the clamping plate 09 are installed at proper positions through screw pins for locating reinforcing ribs of composite material forming parts of a plate shell at the lower part of the machine body plate.

The clamping plate 09 (material: aluminum 6061-T651) is processed according to a three-dimensional die, a processing program is compiled, positioning holes, screw holes and pin holes are processed on the clamping plate 09 through a five-axis numerical control processing method, and the clamping plate 09 and the corner seat 10 are installed at proper positions through bolts.

The corner seat 10 (material: metal Q235-A.F) is provided with positioning holes, screw holes and pin holes, and the corner seat 10 and the clamping plate 09 are mounted at proper positions through screw pins.

The support 11 (material: metal Q235-A.F) is engaged with the frame 03 by means of a screw pin, mounted in a suitable position, with a clearance fit in the relationship H7/g 6.

The lifting ring 12 (standard component) is used for lifting a mould, and the lifting ring 12 adopts a universal rotary lifting ring.

The foregoing is only a preferred embodiment of the present utility model, but the scope of the present utility model is not limited thereto, and any person skilled in the art who is within the scope of the present utility model shall cover the scope of the present utility model.

Claims (5)

1. The utility model provides a target aircraft fuselage plate lower part shell structure combined material forming die which characterized in that: the drilling jig comprises two positioning blocks (01), an insert (02), a frame (03), two angle vertical drilling templates (04), two angle drilling templates (05), four drilling template mounting seats (06) and two positioner assemblies (07);

insert (02), two locating pieces (01) and four bushing plate mount pads (06) are located respectively and fixed on the upper platform of frame (03), two locating pieces (01) are symmetrically arranged on the left and right sides of middle profile area (20) of frame (03), insert (02) is placed in middle profile area (20) and is arranged at the corresponding position of part R district to be formed, two bushing plate mount pads (06) in four bushing plate mount pads (06) are symmetrically arranged on the left and right sides of two locating pieces (01), two angle vertical bushing plates (04) are arranged in one-to-one correspondence with the two bushing plate mount pads (06), and two angle vertical bushing plates (04) are respectively located and fixed on the corresponding bushing plate mount pads (06), the rest two bushing plate mount pads (06) are symmetrically arranged behind the two locating pieces (01), two angle bushing plates (05) are arranged in one-to-one correspondence with the rest two bushing plate mount pads (06), and two angle bushing plates (05) are respectively located and fixed on the two corresponding bushing plate mount pads (06) and are arranged on the two locating pieces (07) respectively, and are arranged on the two locating pieces (07) respectively.

2. The target aircraft fuselage panel lower shell structure composite molding die of claim 1, wherein: the two locator assemblies (07) comprise clamping plates (09), two locators (08), two corner seats (10) and two supports (11); the two supports (11) are symmetrically arranged left and right, the two supports (11) are positioned and fixed on an upper platform of the frame (03), the upper end of each support (11) is positioned and fixedly connected with a corresponding corner seat (10), the two corner seats (10) are respectively positioned and fixedly connected with two ends of the clamping plate (09), the two positioners (08) are symmetrically arranged, and straight handles (13) of the two positioners (08) are respectively positioned and fixedly connected with the clamping plate (09).

3. The target aircraft fuselage panel lower shell structure composite molding die of claim 2, wherein: the locator (08) consists of a straight handle (13), a bent handle (14) and a locating head (15) fixedly connected with the outer end of the bent handle (14).

4. The target aircraft fuselage panel lower shell structure composite molding die of claim 2, wherein: the support (11) comprises a top plate (16), a bottom plate (17), stand columns (18) and two reinforcing ribs (19), wherein the stand columns (18) are fixed between the top plate (16) and the bottom plate (17), the two reinforcing ribs (19) are symmetrically arranged on two sides of the stand columns (18), and the two reinforcing ribs (19) are fixedly connected with the stand columns (18) and the bottom plate (17) respectively.

5. The target aircraft fuselage panel lower shell structure composite molding die of claim 1, wherein: four hanging rings (12) are symmetrically and fixedly arranged on the left side and the right side of the frame (03).