CN202702639U - Molding device of aircraft wing-shaped member pelvic fin - Google Patents

Molding device of aircraft wing-shaped member pelvic fin Download PDF

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Publication number
CN202702639U
CN202702639U CN 201220296141 CN201220296141U CN202702639U CN 202702639 U CN202702639 U CN 202702639U CN 201220296141 CN201220296141 CN 201220296141 CN 201220296141 U CN201220296141 U CN 201220296141U CN 202702639 U CN202702639 U CN 202702639U
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CN
China
Prior art keywords
template
right template
cavity
shaped member
die cavity
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Expired - Fee Related
Application number
CN 201220296141
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Chinese (zh)
Inventor
杨江波
何华锋
王华东
邓德凤
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Hubei Sanjiang Space Jiangbei Mechanical Engineering Co Ltd
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Hubei Sanjiang Space Jiangbei Mechanical Engineering Co Ltd
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Priority to CN 201220296141 priority Critical patent/CN202702639U/en
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Publication of CN202702639U publication Critical patent/CN202702639U/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

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Abstract

The utility model provides a molding device of an aircraft wing-shaped member pelvic fin. The molding device of the aircraft wing-shaped member pelvic fin comprises a left template and a right template, a cavity of the pelvic fin is formed by matching surfaces of the left template and the right template, glue injection port is arranged below the right template, and glue outlets with valves are arranged on the left template and the right template along the outer edge of the cavity. A double-layer sealing groove is respectively arranged on the left template and the right template along the outer edge of the cavity, and requirements of a resin transfer molding process for vacuumizing and sealing are met. A guide plate capable of sliding vertically in the cavity is arranged at the bottom of the cavity, and a guide hole is arranged on the guide plate. The molding device of the aircraft wing-shaped member pelvic fin is high in positioning accuracy, good in sealing performance, reasonable in resin runner and capable of guaranteeing inner quality and apparent quality of large-size foam sandwich carbon cloth skin composite wing-shaped member pelvic fin molding.

Description

Aircraft aerofoil profile part abdomeinal fin shaped device
Technical field
The utility model relates to unmanned plane during flying device airfoil abdomeinal fin forming technique, refers to particularly a kind of aircraft aerofoil profile part abdomeinal fin shaped device that adopts large scale foam core carbon cloth covering composite.
Background technology
Advanced composite material obtains in fields such as boats and ships, automobile, building, sports goods to use more and more widely, and become gradually modern Aviation, aerospace craft is made indispensable critical material.Along with widening of composite application, its moulding process becomes better and approaching perfection day by day, and has developed the advanced moulding process such as resin transfer moulding (Resin Transfer Molding is called for short RTM) technique.Resin transfer moulding is that resin injection is infiltrated the process that reinforcing material also solidifies in close die, the dead size moulding of suitable many kinds, middle batch, high-quality advanced composite material goods.
For satisfying the requirement of lightweight, high strength, heatproof, the version of aircraft aerofoil profile part mainly comprises three kinds: titanium alloy structure, aluminum alloy framework and carbon fiber compression-molded structures, foam core and carbon cloth covering composite construction.Wherein, titanium alloy structure airfoil forming method is simple, and is namely plastic by machining, and its shortcoming is that weight is larger, causes aircraft inertia mass penalty; Aluminum alloy framework and carbon fiber compression-molded structures airfoil are by the molded curing moulding, and technical process is relatively simple, its shortcoming be easy to crack, weight is also relatively large; Foam core and carbon cloth covering composite construction airfoil are by vacuumizing the injecting glue curing molding, and complex technical process is loaded down with trivial details, and its advantage is that light weight, intensity are high, heatproof is effective.
Abdomeinal fin is installed in boost motor afterbody below, function is to increase the stability of unmanned plane and certain lift is provided, the abdomeinal fin working time is about 60s, its stationary point (wing forward position) temperature is 300 ℃, all the other position temperature are 150 ℃, the lower normal force that need bear is 500kgf in working order, and the key technical indexes is as follows: 1) require weight to be not more than 10Kg; 2) the interiors of products quality is even, and ultrasound detection is without defectives such as starved, layerings; 3) product surface is without loose, gauffer, starved, the defective such as subside; 4) the abdomeinal fin performance satisfies the environment for use requirement, examines by the heating power Combined Trials.The best moulding process of aircraft aerofoil profile part abdomeinal fin is resin transfer molding technique.
For large scale foam core carbon cloth covering composite airfoil abdomeinal fin, its resin transfering moulding formation device need guarantee the location of product covering evenness of wall thickness, metal joint, flatness and apparent mass and the internal soundness of assurance aerofoil, need be considered to somatotype, resin flow channel, sealing, injecting glue and the factors such as excessive adhesive plaster office and location of pattern die cavity during design, dead size moulding, positioning accuracy height, good seal performance, dress mould are reliable to satisfy, depanning process requirements simply and easily.
Summary of the invention
The purpose of this utility model will provide a kind of positioning accuracy height, good seal performance, the rational aircraft aerofoil profile of resin flow channel part abdomeinal fin shaped device exactly, guarantees internal soundness and the apparent mass of large scale foam layer carbon cloth covering composite airfoil abdomeinal fin moulding.
For achieving the above object, the designed aircraft aerofoil profile part abdomeinal fin shaped device of the utility model comprises left template and right template, the mating surface of described left template and right template consists of the die cavity of abdomeinal fin jointly, described right template below is provided with gum-injecting port, is provided with the gum outlet with valve on described left template and the right template along the die cavity outer.
Further, described left template and right template are provided with the double-layer seal groove along the outer of die cavity, satisfy resin transfer molding technique and vacuumize and seal request.
Again further, the bottom of described die cavity is provided with the deflector of the upper and lower slip of section within it.Be provided with pod apertures on the described deflector, the below of described deflector is provided with the jack-up screw.Guarantee that resin flow paths is the shortest, avoid the resin turbulent flow, can eliminate the defectives such as poor glue and dry spot.
The utility model has the advantage of: designed aircraft aerofoil profile part abdomeinal fin shaped device is formed the die cavity of abdomeinal fin jointly by left template and right template, below right template, be provided with gum-injecting port, and be provided with the gum outlet with valve on left template and the right template along the die cavity outer.Hole for injecting glue by right template below injecting glue in the die cavity, whether have glue flow out, close the valve of this gum outlet when having glue to flow out if observing simultaneously the gum outlet transparent hose, finish injecting glue when each gum outlet all has glue to flow out.Be provided with the double-layer seal groove in left template and right template along the outer of die cavity, can satisfy resin transfer molding technique and vacuumize and seal request.Be provided with the deflector of the upper and lower slip of section within it in the bottom of die cavity, the below of deflector is provided with the jack-up screw, can guarantee that preform dress mould puts in place; Be provided with pod apertures at deflector, can guarantee that resin flow paths is the shortest, avoid the resin turbulent flow, can eliminate the defectives such as poor glue and dry spot.
By the location of tapering boss and groove, can effectively guarantee the dislocation precision of left template and right template, guarantee the uniformity of die cavity.Deflector is positioned at the bottom of die cavity and is designed to movablely, guarantees that resin flows is smooth and easy and runner is the shortest, eliminates dry spot and poor glue defective; Simultaneously movable deflector is convenient to observe preform and whether is filled mould and put in place, effectively eliminates the defectives such as overlap.Rational gum outlet layout, mobility status that can the Real Time Observation resin is for moulding process optimization and adjustment provide scientific basis.
Description of drawings
Fig. 1 is the structural representation of the utility model aircraft aerofoil profile part abdomeinal fin shaped device.
Fig. 2 is A-A sectional structure schematic diagram among Fig. 1.
Fig. 3 is B-B sectional structure schematic diagram among Fig. 1.
Fig. 4 is the perspective view of aircraft aerofoil profile part abdomeinal fin shaped device.
Fig. 5 is the deflector structure schematic diagram.
Fig. 6 is deflector jack-up structural representation.
Fig. 7 is the foam core perspective view.
The specific embodiment
Below in conjunction with the drawings and specific embodiments the utility model is described in further detail.
As shown in Figures 1 to 4, aircraft aerofoil profile part abdomeinal fin shaped device comprises left template 1 and right template 2, left template 1 and right template 2 adopt boss, groove location, the mating surface of left template 1 and right template 2 consists of the die cavity 3 of abdomeinal fin jointly, for guaranteeing mold cavity surface smoothness and the template deformation of avoiding heat treatment quenching and tempering to cause, selected pre-hardened plastic mold steel P20(3Cr2Mo), do not need heat treatment hardness can reach more than the 30HRC, whole section hardness is even simultaneously, has good polishing performance and mirror effect.Left template 1 be connected template 2 double-screw bolt 8 by 26 M24 of place and connect fasteningly, offer the molding screw in left template 1 simultaneously.Left template 1 and right template 2 are provided with double-layer seal groove 7 along the outer of die cavity 3, take into full account the decrement of sealing ring, and the design groove width is 4.8mm, and groove depth is 4.2mm, and the employing diameter of section is that the heatproof fluororubber O shape circle of ¢ 5 seals.
Right template 2 belows are provided with gum-injecting port 5.For guaranteeing that resin can arrive place, product forward position farthest, path, on left template 1 and right template 2, be provided with the gum outlet 6 with valve along the die cavity outer.The arrangement principle of gum outlet 6 is highest point and the more unattainable places of resin that are positioned at resin flows, is conducive to like this to catch up with most air, soaks into fiber and reduces resin run off.Left template 1 and right template 2 arrange 6 gum outlets 6 along die cavity 3 outers, and the spacing of gum outlet 6 is 180~200mm, simultaneously, for effectively observing resin flows order and situation, are provided with 3 gum outlets 6 at the middle part.The diameter of gum outlet 6 is ¢ 3, and for guaranteeing gum outlet 6 to the impact of product presentation quality, its structural design is the facet that gum outlet 6 sinkings diameter ¢ 15, a degree of depth are about 0.2~0.3mm, and each gum outlet 6 connects a valve.
The bottom of die cavity 3 is provided with the deflector 4 of the upper and lower slip of section within it.Deflector 4 has the binomial function concurrently, is respectively preform is shunted and compressed to resin.Resin is shunted: being provided with 560 place's diameters on the deflector 4 is the pod apertures 4a of ¢ 3, and pod apertures 4a distribution mode is: the every row of width 5 places, and length direction spacing 20mm, as shown in Figure 5.Resin enters in the cavity of deflector 4 by injection system, cavity is upwards filling up symmetrical aerofoil by the pod apertures 4a on the deflector 4 under the effect of pressure after by resin filling simultaneously, can satisfy the forming requirements of aerofoil covering, guarantee that resin flow paths is the shortest, avoid the resin turbulent flow, eliminate the defectives such as poor glue and dry spot; Compress preform: the below of deflector 4 is provided with jack-up screw 13, as shown in Figure 6.During the assembling preform, by jacking screw 13 deflector 4 is upwards held out against, guarantee that preform dress mould is reliable.Two ends are provided with the joint location boss before and after on the deflector 4, are respectively applied to joint 11 behind positioning metal front connector 10 and the metal.
For this shaped device is carried out temperature monitoring, uniformly above left template 1 be provided with 5 thermometer holes 14.For guaranteeing that the utility model is firm along the short transverse placement, thereunder is provided with welded chan frame 9.
Using the utility model, to carry out the operating process of large scale foam core carbon cloth covering composite airfoil abdomeinal fin moulding as follows:
1) with foam core 12 oven dry of machine add-on type, adopt joint 11 and foam core 12 behind positioning tool bonded metal front connector 10 and the metal, outer wall carries out pre-setting and the laying of carbon cloth covering according to technological requirement, forms preform mould to be installed;
2) die cavity of left template 1 and right template 2 is cleaned out, preform is positioned in the die cavity of left template 1 and assembles right template 2 and deflector 4, observe preform and whether have folder cloth, if exist folder cloth then to repair;
3) and adopt jacking screw 13 with deflector 4 top upwards, guarantee that preform dress mould puts in place;
4) carry out the air seal test of 0.2Mpa after with 26 double-screw bolts 8 left template 1 and right template 2 being fixedly connected, whether pressurize is observed gauge pressure and is descended after 5 minutes;
5) air seal test qualified after, the hole for injecting glue 5 by right template 2 bottoms is to die cavity 3 interior injecting glues, whether have glue flow out, close the valve of this gum outlet 6 when having glue to flow out if observing simultaneously gum outlet 6 transparent hoses;
6) all inject die cavity 3 when the glue of appraising and deciding, when each gum outlet 6 all has glue to flow out simultaneously, stop injecting glue, the utility model is together packed into together with product to be incubated in the curing oven;
7) after curing is finished, pull down the connecting stud 8 of left template 1 and right template 2, dismounting deflector 3;
8) pull down product and clear up the utility model shaped device and treat to use next time.

Claims (6)

1. an aircraft aerofoil profile part abdomeinal fin shaped device comprises left template (1) and right template (2), it is characterized in that: the mating surface of described left template (1) and right template (2) consists of the die cavity (3) of abdomeinal fin jointly; Described right template (2) below is provided with gum-injecting port (5); The upper gum outlet (6) that is provided with along the die cavity outer with valve of described left template (1) and right template (2).
2. aircraft aerofoil profile part abdomeinal fin shaped device according to claim 1, it is characterized in that: described left template (1) and right template (2) are provided with double-layer seal groove (7) along the outer of die cavity (3).
3. aircraft aerofoil profile part abdomeinal fin shaped device according to claim 1 and 2, it is characterized in that: the bottom of described die cavity (3) is provided with the deflector (4) of the upper and lower slip of section within it.
4. aircraft aerofoil profile part abdomeinal fin shaped device according to claim 3 is characterized in that: be provided with pod apertures (4a) on the described deflector (4).
5. aircraft aerofoil profile part abdomeinal fin shaped device according to claim 3, it is characterized in that: the below of described deflector (4) is provided with jack-up screw (13).
6. aircraft aerofoil profile part abdomeinal fin shaped device according to claim 4, it is characterized in that: the below of described deflector (4) is provided with jack-up screw (13).
CN 201220296141 2012-06-25 2012-06-25 Molding device of aircraft wing-shaped member pelvic fin Expired - Fee Related CN202702639U (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN 201220296141 CN202702639U (en) 2012-06-25 2012-06-25 Molding device of aircraft wing-shaped member pelvic fin

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN 201220296141 CN202702639U (en) 2012-06-25 2012-06-25 Molding device of aircraft wing-shaped member pelvic fin

Publications (1)

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104175575A (en) * 2014-08-18 2014-12-03 北京航空航天大学 Whole-stepping (Resin Transfer Molding) RTM technology for large-sized composite material workpiece
CN106182790A (en) * 2016-07-08 2016-12-07 湖北三江航天江北机械工程有限公司 Slender type dovetail shaped airvane leading edge forming method and moulding pressing mould and appliance special for detecting
CN107297925A (en) * 2017-06-15 2017-10-27 湖北航天技术研究院总体设计所 A kind of light-high-strength high temperature resistant abdomeinal fin and forming method
CN112537056A (en) * 2020-11-20 2021-03-23 上海复合材料科技有限公司 Vacuum-assisted RTM (resin transfer molding) molding grid single-module forming die

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104175575A (en) * 2014-08-18 2014-12-03 北京航空航天大学 Whole-stepping (Resin Transfer Molding) RTM technology for large-sized composite material workpiece
CN106182790A (en) * 2016-07-08 2016-12-07 湖北三江航天江北机械工程有限公司 Slender type dovetail shaped airvane leading edge forming method and moulding pressing mould and appliance special for detecting
CN107297925A (en) * 2017-06-15 2017-10-27 湖北航天技术研究院总体设计所 A kind of light-high-strength high temperature resistant abdomeinal fin and forming method
CN107297925B (en) * 2017-06-15 2019-11-12 湖北航天技术研究院总体设计所 A kind of light-high-strength high temperature resistant abdomeinal fin and forming method
CN112537056A (en) * 2020-11-20 2021-03-23 上海复合材料科技有限公司 Vacuum-assisted RTM (resin transfer molding) molding grid single-module forming die

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C14 Grant of patent or utility model
GR01 Patent grant
CF01 Termination of patent right due to non-payment of annual fee

Granted publication date: 20130130

Termination date: 20150625

EXPY Termination of patent right or utility model