CN109434380A - A kind of Varying-thickness lightweight missile wing covering manufacturing process - Google Patents
A kind of Varying-thickness lightweight missile wing covering manufacturing process Download PDFInfo
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- CN109434380A CN109434380A CN201811305983.4A CN201811305983A CN109434380A CN 109434380 A CN109434380 A CN 109434380A CN 201811305983 A CN201811305983 A CN 201811305983A CN 109434380 A CN109434380 A CN 109434380A
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Abstract
The invention belongs to precision plastic forming technical fields, and in particular to a kind of Varying-thickness lightweight missile wing covering manufacturing process using whole super modeling diffusion connection method.This method is diffused connection and superplastic forming using two layers of covering outside plate and inner panel, the technological compensa tion face formed during reinforcing rib will be shaped, process allowance is removed by wire cutting, and then the figuration manufacture of different-thickness is realized in the different zones of covering, then cold bending is carried out to windward side bending angle.The present invention realizes the manufacturing process of Varying-thickness lightweight missile wing covering by novelty, the design of reasonable Varying-thickness reinforcement structure covering, the combination forming method combined in conjunction with diffusion connection, superplasticforming, wire cutting and cold bending.By using Varying-thickness lightweight missile wing covering of the invention, while realizing a kind of traditional thickness covering loss of weight, the structural strength of covering can be effectively improved, the width of skeleton rib can be substantially reduced, so that the weight of traditional skeleton declines to a great extent, it can satisfy requirement of the following guided missile model to lightweight load-carrying construction, improve the qualification rate and production efficiency of product, can be realized mass production.
Description
Technical field
The invention belongs to precision plastic forming technical fields, and in particular to a kind of to surpass modeling diffusion connection method using entirety
Varying-thickness lightweight missile wing covering manufacturing process.
Background technique
As missile flight speed is greatly improved, the demand to the heat-resisting load-carrying construction of lightweight is increasing, application
Also more and more extensive, traditional missile wing part mostly uses greatly frame-covering structure, general processing and manufacturing process are as follows: covering is general
Using the cold bending and forming of equal thickness plate, skeleton adds finishing using machine is carried out after casting, and covering and skeleton web sections carry out
Spot welding, covering surrounding and skeleton use high energy beam welding (electron beam welding or Laser Welding).But due to the craftsmanship of spot welding and
The rib width of the features such as strength and stiffness of single thickness covering, skeleton are generally wider, generally in 10mm or more, skeleton covering
Missile wing pts wt after forming is generally bigger than normal, is difficult to meet requirement of the following guided missile model to lightweight load-carrying construction.And its
Although the super modeling diffusion connection missile wing of his four layers of overall structure can also reach certain weight loss effect, loss of weight amplitude still can not
Requirement of the guided missile to significantly loss of weight missile wing is fully met, in addition this method entirety manufacturing process is complicated, and influence factor is more, raw
It produces low efficiency and product qualification rate is lower, be difficult to realize mass production in aerospace field.
Summary of the invention
(1) technical problems to be solved
The present invention proposes a kind of Varying-thickness lightweight missile wing covering manufacturing process, to solve how to reduce skeleton rib number
The technical issues of amount, mitigation missile wing weight.
(2) technical solution
In order to solve the above-mentioned technical problem, the present invention proposes a kind of manufacturing process of Varying-thickness lightweight missile wing covering, should
Manufacturing process includes the following steps:
S1, covering include outside plate and inner panel, and the expansion of covering outside plate and inner panel is calculated by missile wing skin part theoretical size
Blank shape；
S2, the scribing line sample that join domain is spread according to the reinforcing rib shape and Position Design outside plate and inner panel of skin part
Solder flux is stopped in superplastic forming region and the coating of each ventilation groove location by plate, and treats diffusion join domain and carry out sanding and polishing；It will be outer
Plate and inner panel surrounding carry out periphery soldering and sealing in addition to super modeling air channel, form hermetic type chamber；
S3, design covering forming upper mold and forming lower die, wherein the die face of forming upper mold is plane, forming lower die
Die face is the shaping dies with type chamber；Wherein, by the air channel of covering outside plate and inner panel superplastic forming and diffusion connection
The various chamber junction of forming lower die is set, and guaranteeing each type chamber, at least there are two air channels to connect；According to plate in super modeling
Gas vent is arranged in the last mold position of the intracavitary plate of each type in the sequencing that mold has in forming process；On forming lower die
Multiple external air inlets are arranged to covering；
S4, covering, forming upper mold and forming lower die are subjected to positioning molding, are put into heat forming equipment and heat up with furnace, to temperature
Degree reaches 935 DEG C, applies proliferation welding molding pressure tonnage, carries out mechanical pressurization diffusion welding (DW)；
S5, cool down after completing diffusion welding (DW) connection, kept the temperature when temperature is down to 850 DEG C, be passed through inert gas
Superplastic forming is carried out, forming pressure is carried out by step-loaded curve；After completing maximum pressure pressure maintaining, pressure is declined, and
Pressure maintaining is carried out until covering pickup；Covering cools down with furnace, and carries out unloading load air pressure；
S6, will covering that high temperature takes out it is cooling after carry out pickling alkali and collapse, remove surface scale；
S7, the covering after laser cutting pickling alkali collapses is carried out according to covering theoretical model, cut out the illiteracy for meeting matching requirements
Skin shape；
S8, the technological compensa tion face formed during superplastic forming is removed into process allowance by wire cutting, forms part envelope
Close upright reinforcing rib；
S9, the bending position according to covering theoretical model in covering corresponding region are crossed, and true by folding test
Determine bending springback compensation value, realizes the accurate bending of covering.
Further, covering outside plate and inner panel use TA15 titanium alloy, and thickness is 0.5mm.
Further, in step s 2, antioxidant coating is coated in hermetic type chamber outer surface.
Further, in step s3, ventilate groove width 3-5mm, depth 0.3-0.6mm.
Further, in step s3, it is vented bore dia 1-3mm.
Further, in step s 4, in temperature-rise period, the hermetic type chamber formed to outside plate and inner panel is persistently taken out
The vacuum degree of vacuum, hermetic type chamber is not more than 0.001Pa.
Further, in step s 4, when applying proliferation welding molding pressure tonnage, guarantee mechanical pressurization compressive load per unit area
5-8MPa, the mechanical pressurization diffusion welding (DW) time is about 150-200min.
Further, in step s 5, it is passed through argon gas and carries out superplastic forming.
Further, in step s 5, when forming pressure is carried out by step-loaded curve, using every 0.5MPa as increment shape
At a ladder, each load time in stage is 10min, pressure maintaining 15min, until being loaded onto 2.0-2.5MPa.
Further, in step s 5, after completing maximum pressure pressure maintaining, pressure is depressurized to 0.01-0.03MPa, and
Pressure maintaining is carried out until covering pickup；Covering is cooled to 300 DEG C with furnace, and carries out unloading load air pressure.
(3) beneficial effect
Varying-thickness lightweight missile wing covering manufacturing process proposed by the present invention, is expanded using two layers of covering outside plate and inner panel
Connection and superplastic forming are dissipated, the technological compensa tion face formed during reinforcing rib will be shaped, process allowance is removed by wire cutting, into
And the figuration manufacture of different-thickness is realized in the different zones of covering, then cold bending is carried out to windward side bending angle.
The present invention by the design of novel, reasonable Varying-thickness reinforcement structure covering, in conjunction with diffusion connection, superplasticity at
The combination forming method that shape, wire cutting and cold bending combine realizes the manufacturing process of Varying-thickness lightweight missile wing covering.Pass through
It can be effectively improved while realizing a kind of traditional thickness covering loss of weight using Varying-thickness lightweight missile wing covering of the invention
The structural strength of covering can be substantially reduced the width (being reduced to less than 4mm by 15mm) of skeleton rib, so that traditional skeleton
Weight declines to a great extent, and can satisfy requirement of the following guided missile model to lightweight load-carrying construction, improve product qualification rate and
Production efficiency can be realized mass production.
Detailed description of the invention
Fig. 1 is the covering and Skeleton assembly structural schematic diagram after the lightweight loss of weight of the present embodiment；
Fig. 2 is the covering outside plate and inner plate structure schematic diagram of the present embodiment；
Fig. 3 is the covering different zones structural schematic diagram of the present embodiment；
Fig. 4 is the covering diffusion connection and superplastic forming die structural schematic diagram of the present embodiment；
Fig. 5 is the covering forming lower die mold structure diagram of the present embodiment.
Specific embodiment
To keep the purpose of the present invention, content and advantage clearer, with reference to the accompanying drawings and examples, to tool of the invention
Body embodiment is described in further detail.
The present embodiment proposes a kind of Varying-thickness lightweight missile wing covering manufacturing process, especially suitable for loss of weight require it is high and
High-intensitive covering forming, it is therefore an objective to ultimately form by the assembling structure of covering 1 and skeleton 2 after lightweight loss of weight, such as Fig. 1 institute
Show.
The manufacturing process specifically includes the following steps:
S1, covering include outside plate 1-1 and inner panel 1-2, and outside plate 1-1 and inner panel 1-2 use TA15 titanium alloy, and thickness is selected as
0.5mm, as shown in Fig. 2, calculating the spread material shape of covering outside plate 1-1 and inner panel 1-2 by missile wing skin part theoretical size；
S2, drawing for join domain is spread according to the reinforcing rib shape and Position Design outside plate 1-1 and inner panel 1-2 of skin part
Line tempte as shown in figure 3, superplastic forming region 1-4 and the coating of each ventilation groove location are stopped solder flux, and treats diffusion join domain
1-3 carries out sanding and polishing.Outside plate 1-1 and inner panel 1-2 surrounding are subjected to periphery soldering and sealing in addition to super modeling air channel, form hermetic type
Chamber, and antioxidant coating is coated in covering hermetic type chamber outer surface.
S3, design covering forming upper mold 3 and forming lower die 4, as shown in Figures 4 and 5, wherein the die face of forming upper mold 3
For plane, the die face of forming lower die 4 is the shaping dies with type chamber.By covering outside plate 1-1 and inner panel 1-2 superplastic forming
In the various chamber junction of forming lower die 4, ventilate groove width 3-5mm, depth 0.3-0.6mm, guarantees for air channel setting with diffusion connection
At least there are two air channels to connect for each type chamber, which can shape the symmetrical covering of two pieces simultaneously.It is moulded into according to plate super
Gas vent 4-1, gas vent is arranged in the last mold position of the intracavitary plate of each type in the sequencing rule that mold has during shape
Diameter 1-3mm.Three external air inlet 4-3 are arranged to every covering on forming lower die 4.
S4, covering, forming upper mold 3 and forming lower die 4 are subjected to positioning molding by positioning pin 5, are put into heat forming equipment
It heats up with furnace, in temperature-rise period, the outside plate 1-1 and inner panel 1-2 hermetic type chamber formed is persistently vacuumized, vacuum degree
No more than 0.001Pa.Reach 935 DEG C to temperature, apply proliferation welding molding pressure tonnage, guarantees mechanical pressurization compressive load per unit area
5-8MPa, the mechanical pressurization diffusion welding (DW) time is about 150-200min.
S5, cool down after completing diffusion welding (DW) connection, kept the temperature when temperature is down to 850 DEG C, be passed through argon gas progress
Superplastic forming, forming pressure are carried out by step-loaded curve, form a ladder by increment of every 0.5MPa, each stage adds
The load time is 10min, pressure maintaining 15min, until being loaded onto 2.0-2.5MPa.After completing maximum pressure pressure maintaining, pressure is depressured
To 0.01MPa-0.03MPa, and pressure maintaining is carried out until covering pickup.Covering is cooled to 300 DEG C with furnace, and carries out unloading load gas
Pressure.High temperature pickup is carried out after the completion of pressure release, and is put into next missile wing covering and is diffused connection and superplasticforming.
S6, will covering that high temperature takes out it is cooling after carry out pickling alkali and collapse, remove surface scale.
S7, the covering after laser cutting pickling alkali collapses is carried out according to covering theoretical model, cut out the illiteracy for meeting matching requirements
Skin shape, and the laser cutting burr on periphery of polishing.
S8, the technological compensa tion face formed during superplastic forming is removed into process allowance by wire cutting, forms part envelope
Upright reinforcing rib 1-5 is closed, guarantees the height of reinforcing rib 1-5 in 4-6mm.After completing wire cutting, similar diffusion bonding pad is realized
The skin thickness of domain 1-3 is the sum of outside plate 1-1 and inner panel 1-2 thickness, and the skin thickness of similar superplastic forming region 1-4 is then
The thickness of outside plate 1-1.
S9, the bending position according to covering theoretical model in covering corresponding region are crossed, and true by folding test
Determine bending springback compensation value, realizes the accurate bending of covering.For abutting the bending in the region upright reinforcing rib 1-5, doubling is needed
Tulwar carries out partial operation and forms groove to avoid upright reinforcing rib 1-5.
S10, fluorescence detection is carried out to bending line region 1-6, is confirmed whether that, there are micro-crack, there is no then complete to hand over inspection.
The above is only a preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, without departing from the technical principles of the invention, several improvement and deformations can also be made, these improvement and deformations
Also it should be regarded as protection scope of the present invention.
Claims (10)
1. a kind of manufacturing process of Varying-thickness lightweight missile wing covering, which is characterized in that the manufacturing process includes the following steps:
S1, covering include outside plate and inner panel, and the expansion plate of covering outside plate and inner panel is calculated by missile wing skin part theoretical size
Shape；
The scribing line sample of S2, the outside plate according to the reinforcing rib shape and Position Design of skin part and inner panel diffusion join domain
Solder flux is stopped in superplastic forming region and the coating of each ventilation groove location by plate, and treats diffusion join domain and carry out sanding and polishing；By institute
It states outside plate and the inner panel surrounding and carries out periphery soldering and sealing in addition to super modeling air channel, form hermetic type chamber；
S3, design covering forming upper mold and forming lower die, wherein the die face of the forming upper mold is plane, under the forming
The die face of mould is the shaping dies with type chamber；Wherein, the covering outside plate and inner panel superplastic forming and diffusion are connected
Air channel the various chamber junction of the forming lower die is set, guaranteeing each type chamber, at least there are two air channels to connect；Root
Gas vent is set in the intracavitary plate of each type last mold position according to the plate sequencing that mold has during superplastic forming；
Multiple external air inlets are arranged to covering on the forming lower die；
S4, the covering, forming upper mold and forming lower die are subjected to positioning molding, are put into heat forming equipment and heat up with furnace, to temperature
Degree reaches 935 DEG C, applies proliferation welding molding pressure tonnage, carries out mechanical pressurization diffusion welding (DW)；
S5, cool down after completing diffusion welding (DW) connection, kept the temperature when temperature is down to 850 DEG C, be passed through inert gas progress
Superplastic forming, forming pressure are carried out by step-loaded curve；After completing maximum pressure pressure maintaining, pressure is declined, and carries out
Pressure maintaining is until covering pickup；The covering cools down with furnace, and carries out unloading load air pressure；
S6, will covering that high temperature takes out it is cooling after carry out pickling alkali and collapse, remove surface scale；
S7, the covering after laser cutting pickling alkali collapses is carried out according to covering theoretical model, cut out the illiteracy for meeting matching requirements
Skin shape；
S8, the technological compensa tion face formed during superplastic forming is removed into process allowance by wire cutting, it is straight forms partial closure
Vertical reinforcing rib；
S9, the bending position according to covering theoretical model in covering corresponding region are crossed, and are determined and rolled over by folding test
Replication bullet offset realizes the accurate bending of covering.
2. manufacturing process as described in claim 1, which is characterized in that the covering outside plate and inner panel use TA15 titanium alloy,
Thickness is 0.5mm.
3. manufacturing process as described in claim 1, which is characterized in that in the step S2, in the hermetic type chamber appearance
Face coats antioxidant coating.
4. manufacturing process as described in claim 1, which is characterized in that in the step S3, the ventilation groove width 3-5mm,
Deep 0.3-0.6mm.
5. manufacturing process as described in claim 1, which is characterized in that in the step S3, the exhaust bore dia 1-
3mm。
6. manufacturing process as described in claim 1, which is characterized in that in the step S4, in temperature-rise period, to described
The hermetic type chamber that outside plate and inner panel are formed persistently is vacuumized, and the vacuum degree of the hermetic type chamber is not more than 0.001Pa.
7. manufacturing process as described in claim 1, which is characterized in that in the step S4, apply proliferation welding molding pressure
When tonnage, guarantee mechanical pressurization compressive load per unit area 5-8MPa, the mechanical pressurization diffusion welding (DW) time is about 150-200min.
8. manufacturing process as described in claim 1, which is characterized in that in the step S5, be passed through argon gas and carry out super be moulded into
Shape.
9. manufacturing process as described in claim 1, which is characterized in that in the step S5, forming pressure is added by ladder
Carry curve carry out when, using every 0.5MPa be increment formed a ladder, each load time in stage be 10min, pressure maintaining 15min,
Until being loaded onto 2.0-2.5MPa.
10. manufacturing process as described in claim 1, which is characterized in that in the step S5, complete maximum pressure pressure maintaining
Afterwards, pressure is depressurized to 0.01-0.03MPa, and carries out pressure maintaining until covering pickup；The covering is cooled to 300 DEG C with furnace, and
Carry out unloading load air pressure.
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| CN201811305983.4A CN109434380B (en) | 2018-11-05 | 2018-11-05 | Variable-thickness lightweight missile wing skin forming method |
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| CN201811305983.4A CN109434380B (en) | 2018-11-05 | 2018-11-05 | Variable-thickness lightweight missile wing skin forming method |
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| CN109434380B CN109434380B (en) | 2020-11-13 |
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| CN110203421A (en) * | 2019-05-21 | 2019-09-06 | 重庆零壹空间航天科技有限公司 | Empennage and aircraft comprising the empennage |
| CN110539138A (en) * | 2019-09-30 | 2019-12-06 | 北京星航机电装备有限公司 | Preparation method of aluminum alloy lightweight active cooling structural skin |
| CN110666457A (en) * | 2019-10-09 | 2020-01-10 | 北京星航机电装备有限公司 | Preparation method of titanium alloy thin-wall lightweight flap part |
| CN110773879A (en) * | 2019-11-06 | 2020-02-11 | 哈尔滨工业大学 | Metal hollow structure prefabricated vacancy forming device and method thereof |
| CN112975287A (en) * | 2021-02-23 | 2021-06-18 | 哈尔滨工业大学 | Superplastic deformation/diffusion connection forming technology for wavy hollow skin structure part |
| CN113857356A (en) * | 2021-11-09 | 2021-12-31 | 西安航空学院 | Forming die and method for airplane skin parts |
| CN113878361A (en) * | 2021-09-30 | 2022-01-04 | 北京航星机器制造有限公司 | Processing and manufacturing die and method for special-shaped curved surface hollow skin |
| CN113909802A (en) * | 2021-09-06 | 2022-01-11 | 中车长春轨道客车股份有限公司 | Manufacturing method and structure of aluminum alloy vehicle head |
| CN113997015A (en) * | 2021-10-29 | 2022-02-01 | 北京星航机电装备有限公司 | Variable-thickness titanium alloy skin integrated forming method |
| CN114749562A (en) * | 2022-06-14 | 2022-07-15 | 成都飞机工业（集团）有限责任公司 | Air guide system of superplastic forming/diffusion bonding die and manufacturing method thereof |
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| CN110666457A (en) * | 2019-10-09 | 2020-01-10 | 北京星航机电装备有限公司 | Preparation method of titanium alloy thin-wall lightweight flap part |
| CN110773879A (en) * | 2019-11-06 | 2020-02-11 | 哈尔滨工业大学 | Metal hollow structure prefabricated vacancy forming device and method thereof |
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| CN113878361A (en) * | 2021-09-30 | 2022-01-04 | 北京航星机器制造有限公司 | Processing and manufacturing die and method for special-shaped curved surface hollow skin |
| CN113878361B (en) * | 2021-09-30 | 2022-11-15 | 北京航星机器制造有限公司 | Processing and manufacturing die and method for special-shaped curved surface hollow skin |
| CN113997015A (en) * | 2021-10-29 | 2022-02-01 | 北京星航机电装备有限公司 | Variable-thickness titanium alloy skin integrated forming method |
| CN113857356A (en) * | 2021-11-09 | 2021-12-31 | 西安航空学院 | Forming die and method for airplane skin parts |
| CN114749562A (en) * | 2022-06-14 | 2022-07-15 | 成都飞机工业（集团）有限责任公司 | Air guide system of superplastic forming/diffusion bonding die and manufacturing method thereof |
| CN114749562B (en) * | 2022-06-14 | 2022-10-25 | 成都飞机工业（集团）有限责任公司 | Air guide system of superplastic forming/diffusion connecting die and manufacturing method thereof |
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