CN107116340A - Space flight large size, thin walled liner and its manufacture method - Google Patents
Space flight large size, thin walled liner and its manufacture method Download PDFInfo
- Publication number
- CN107116340A CN107116340A CN201710354265.5A CN201710354265A CN107116340A CN 107116340 A CN107116340 A CN 107116340A CN 201710354265 A CN201710354265 A CN 201710354265A CN 107116340 A CN107116340 A CN 107116340A
- Authority
- CN
- China
- Prior art keywords
- liner
- mouth
- large size
- thin walled
- upper cover
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Pressure Welding/Diffusion-Bonding (AREA)
- Forging (AREA)
Abstract
The invention provides a kind of space flight large size, thin walled liner and its manufacture method, the liner includes liner body, upper cover, low head, gas circuit connects mouth and fluid path connects mouth, the upper cover and low head are fixedly arranged on the top and bottom of liner body respectively, the gas circuit connects the top that mouth is fixedly arranged on upper cover, and the fluid path connects the bottom that mouth is fixedly arranged on low head.The preparation method comprises the following steps：Manufacture that liner body, upper cover, low head, gas circuit connect mouth and fluid path connects mouth respectively；Liner body, upper cover, low head, gas circuit are connect into mouth and fluid path connects mouth and welded, liner semi-finished product are obtained；The liner semi-finished product are heat-treated at 100~280 DEG C, the large size, thin walled liner is obtained.The present invention has following beneficial effect：The problem of solving the shaping of large-sized composite material winding tank metal inner lining, welding hardly possible.
Description
Technical field
The present invention relates to a kind of space flight large size, thin walled liner and its manufacture method, belong to space equipment manufacturing technology neck
Domain.
Background technology
Propellant tank is one of significant components of Propellant System, with the development of space technology, and tank is towards great Rong
Product, lighting direction are developed.Manufacture is with tank the features such as volume is big, lightweight, reliability is high to the effective load of system increase
Lotus, guarantee emission security etc. are significant.
Filament-Winding Vessel has the advantages that structure efficiency is high, reliability is high, failure mode is safe and is navigating because of it
Its pressure vessel field.Due to it is large size, thin walled the characteristics of, be faced with huge difficulty, it is necessary to solve in structure design and shaping
Many key technology difficulties such as shaping, processing and welding.
The content of the invention
Will for defect of the prior art and the big volume of missile propellant tank, lighting, the design of high reliability
Ask, it is an object of the invention to provide a kind of space flight large size, thin walled liner and its manufacture method.
The present invention is achieved by the following technical solutions：
In a first aspect, the invention provides a kind of large size, thin walled liner of space flight, it include liner body, upper cover,
Low head, gas circuit connect mouth and fluid path connects mouth, and the upper cover and low head are fixedly arranged on the top and bottom of liner body, institute respectively
State gas circuit and connect the top that mouth is fixedly arranged on upper cover, the fluid path connects the bottom that mouth is fixedly arranged on low head.
Preferably, the outer mold surface of the upper cover and low head is spheroid shape face, the spheroid shape face it is short
The length ratio of axle and major axis is (0.6~0.7)：1.
Preferably, the wall thickness of the liner body is 1.2~2.5mm, a diameter of 1200~1350mm, is highly
1900~2200, a diameter of 300~380mm of fluid path outlet.
Preferably, the material of the liner body be aluminium alloy or titanium alloy, the upper cover and low head
Material is identical with the material of liner body, and the gas circuit connects mouth and fluid path connects the material phase of the material of mouth also with liner body
Together.
Preferably, the aluminium alloy include 5A06 aluminium alloys, the titanium alloy be selected from TA0, TA1, TA2, TA3,
One kind in TA4, TA5, TA6, TA7, TA8, TA9, TA10 and TC4.
Second aspect, present invention also offers a kind of manufacture method of the large size, thin walled liner of space flight as the aforementioned, its
Comprise the following steps：
Manufacture that liner body, upper cover, low head, gas circuit connect mouth and fluid path connects mouth respectively；
Liner body, upper cover, low head, gas circuit are connect into mouth and fluid path connects mouth and welded, liner semi-finished product are obtained；
The liner semi-finished product are heat-treated at 100~280 DEG C, the large size, thin walled liner is obtained.
Preferably, the method for production of the liner body is solid forging shaping, the shaping of half barrel soldering or forged
Part rotary press modelling.
Preferably, the method for the forging rotary press modelling is：By tubular forging on core, at 350~700 DEG C
Lower carry out spinning, it is 400~700rpm to control spinning speed, and the depth of cut is 0.2~0.5mm/r.
Preferably, the method for production of the upper cover and low head is：Plate stamping or spinning.
Preferably, the gas circuit connects mouth and fluid path connects the method for production of mouth and is：Forging process is molded.
Compared with prior art, the present invention has following beneficial effect：
1st, the problem of present invention solves the shaping of large-sized composite material winding tank metal inner lining, welding is difficult；
With very high reliability and security when the 2, being applied in spacecraft；
3rd, the large size, thin walled welding liner manufactured using the method for the invention can be used for spacecraft propulsion system field,
Its architecture quality can be effectively reduced, reliability is improved.
Brief description of the drawings
By reading the detailed description made with reference to the following drawings to non-limiting example, further feature of the invention,
Objects and advantages will become more apparent upon：
Fig. 1 is large size, thin walled welding inner lining structure schematic diagram of the invention.
Embodiment
With reference to specific embodiment, the present invention is described in detail.Following examples will be helpful to the technology of this area
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that to the ordinary skill of this area
For personnel, without departing from the inventive concept of the premise, various modifications and improvements can be made.These belong to the present invention
Protection domain.
The structure of large size, thin walled welding liner in the present invention is as shown in figure 1, by liner body 1, upper cover 2, lower envelope
First 3, gas circuit connects mouth 4 and fluid path connects mouth 5 and constituted.
Embodiment 1
A kind of method for the large size, thin walled welding liner of manufacture that the present embodiment is provided, specifically includes following steps：
Step one：The material for preparing metal inner lining is aluminium alloy 5A06, constitute the liner body of metal inner lining, upper cover,
Low head, gas circuit connect mouth and fluid path connects mouth and connected by welding manner.
Step 2：The upper cover and low head of liner are molded by punching press or spinning process.Whole aluminum alloy plate materials are put
Punching press is carried out on mould, punching press number of times is 4~6 times, and press depth is successively decreased successively, 40~220mm of press depth scope；Or will
Whole aluminum alloy plate materials, which are placed on core, carries out spinning, 400~700r/min of spinning speed, and the depth of cut is 0.2~0.5mm/r,
By the way of spinning process is heated while in spinning, its local heating temperature is 350~700 DEG C.
Step 3：Pass through aluminium alloy solid forging shaping, the shaping of half barrel soldering or aluminum alloy forge piece rotary press modelling liner
Body.Half barrel soldering selects stirring friction-welding technique；Aluminium alloy cylinder forging is placed on core and carried out by forging spinning process
Spinning, 400~700r/min of spinning speed, the depth of cut is 0.2~0.5mm/r, and spinning process uses the side heated in spinning
Formula, its local heating temperature is 350~700 DEG C, is spun to a diameter of 1200~1350mm cylindrical section.
Step 4：Liner body, upper cover, low head, gas circuit are connect by mouth by argon arc welding technique and fluid path connects mouth and welded
Together, welding current size be 100~150A, be passed through purity be not less than 99.99% argon gas protection gas, speed of supplying gas 7~
10L/min, wire feed rate is 180~300mm/min.
Step 5：Postwelding liner carries out annealing heat-treats.Its heat treatment temperature is 100~280 DEG C, heat treatment time 2~
4h。
Embodiment 2
A kind of method for the large size, thin walled welding liner of manufacture that the present embodiment is provided, specifically includes following steps：
Step one：Prepare the material of metal inner lining for titanium alloy T A0, TA1, TA2, TA3, TA4, TA5, TA6, TA7, TA8,
TA9, TA10 and TC4, the liner body of composition metal inner lining, upper cover, low head, gas circuit connect mouth and fluid path connects mouth and passes through welding
Mode is connected.
Step 2：Pass through punching press or the upper cover and low head of super modeling technological forming liner.Whole aluminum alloy plate materials are put
Punching press is carried out on mould, punching press number of times is 6~8 times, and press depth is successively decreased successively, 40~120mm of press depth scope；Or will
Whole aluminum alloy plate materials, which are placed on core, carries out super modeling, and superplastic formation temperature is 800~1000 DEG C.
Step 3：Pass through titanium alloy solid forging shaping, the shaping of half barrel soldering or powder metallurgy forming cylindrical section.Half
Vacuum electron beam welding technique is selected in body welding.
Step 4：Cylindrical section, upper cover, low head, gas circuit are connect by mouth by electron-bombardment welding technique and fluid path connects mouth
Weld together.
Step 5：Postwelding liner carries out annealing heat-treats.Its heat treatment temperature is 550~750 DEG C, heat treatment time 2~
3h。
The specific embodiment of the present invention is described above.It is to be appreciated that the invention is not limited in above-mentioned
Particular implementation, those skilled in the art can make various deformations or amendments within the scope of the claims, this not shadow
Ring the substantive content of the present invention.
Claims (10)
1. the large size, thin walled liner of a kind of space flight, it is characterised in that connect mouth including liner body, upper cover, low head, gas circuit
Mouth is connect with fluid path, the upper cover and low head are fixedly arranged on the top and bottom of liner body respectively, and it is fixed that the gas circuit connects mouth
In the top of upper cover, the fluid path connects the bottom that mouth is fixedly arranged on low head.
2. the large size, thin walled liner of space flight as claimed in claim 1, it is characterised in that outside the upper cover and low head
Type face is spheroid shape face, and the short axle in the spheroid shape face and the length ratio of major axis are (0.6~0.7)：1.
3. the large size, thin walled liner of space flight as claimed in claim 1, it is characterised in that the wall thickness of the liner body is
1.2~2.5mm, a diameter of 1200~1350mm, are highly 1900~2200mm, a diameter of 300~380mm of fluid path outlet.
4. the large size, thin walled liner of space flight as claimed in claim 1, it is characterised in that the material of the liner body is aluminium
Alloy or titanium alloy, the material of the upper cover and low head are identical with the material of liner body, and the gas circuit connects mouth and liquid
The material that road connects mouth is also identical with the material of liner body.
5. the large size, thin walled liner of space flight as claimed in claim 4, it is characterised in that the aluminium alloy is closed including 5A06 aluminium
Gold, the one kind of the titanium alloy in TA0, TA1, TA2, TA3, TA4, TA5, TA6, TA7, TA8, TA9, TA10 and TC4.
6. a kind of space flight as described in any one in Claims 1 to 5 manufacture method of large size, thin walled liner, its feature
It is, comprises the following steps：
Manufacture that liner body, upper cover, low head, gas circuit connect mouth and fluid path connects mouth respectively；
Liner body, upper cover, low head, gas circuit are connect into mouth and fluid path connects mouth and welded, liner semi-finished product are obtained；
The liner semi-finished product are heat-treated at 100~280 DEG C, the large size, thin walled liner is obtained.
7. the manufacture method of the large size, thin walled liner of space flight as claimed in claim 6, it is characterised in that the liner body
Method for production for solid forging shaping, half barrel soldering shaping or forging rotary press modelling.
8. the space flight as claimed in claim 7 manufacture method of large size, thin walled liner, it is characterised in that the forging spinning
The method of shaping is：By tubular forging on core, spinning is carried out at 350~700 DEG C, control spinning speed for 400~
700rpm, the depth of cut is 0.2~0.5mm/r.
9. the space flight as claimed in claim 6 manufacture method of large size, thin walled liner, it is characterised in that the upper cover and
The method for production of low head is：Plate stamping or spinning.
10. the space flight as claimed in claim 6 manufacture method of large size, thin walled liner, it is characterised in that the gas circuit connects
The method for production that mouth and fluid path connect mouth is：Forging process is molded.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710354265.5A CN107116340A (en) | 2017-05-18 | 2017-05-18 | Space flight large size, thin walled liner and its manufacture method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710354265.5A CN107116340A (en) | 2017-05-18 | 2017-05-18 | Space flight large size, thin walled liner and its manufacture method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107116340A true CN107116340A (en) | 2017-09-01 |
Family
ID=59727677
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710354265.5A Pending CN107116340A (en) | 2017-05-18 | 2017-05-18 | Space flight large size, thin walled liner and its manufacture method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107116340A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111876706A (en) * | 2020-06-30 | 2020-11-03 | 成都飞机工业（集团）有限责任公司 | Heat treatment method of thin-wall damage tolerance type TC4-DT titanium alloy part |
| CN114505688A (en) * | 2022-03-04 | 2022-05-17 | 西安零壹空间科技有限公司 | Thin-wall special-shaped combustion chamber shell and machining method thereof |
| CN114871557A (en) * | 2022-06-21 | 2022-08-09 | 南京晨光集团有限责任公司 | Vacuum electron beam manufacturing method for spacecraft thin-wall cylindrical storage tank |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1715729A (en) * | 2005-07-04 | 2006-01-04 | 哈尔滨工业大学 | Composite material pressure container with large size, super thin metal inner lining and its producing method |
| EP1818596B1 (en) * | 2006-02-09 | 2009-04-15 | Gräfenthaler Kunststofftechnik GmbH | Pressure vessel made of plastic and method for its manufacture |
| CN101676595A (en) * | 2008-09-15 | 2010-03-24 | 本特勒Sgl有限责任两合公司 | Method for producing a gas container, in particular for motor vehicles |
| CN102991729A (en) * | 2012-11-30 | 2013-03-27 | 北京控制工程研究所 | Light mesh-type surface tension storage tank |
| CN105674041A (en) * | 2016-01-28 | 2016-06-15 | 上海空间推进研究所 | Spherical composite gas cylinder for spaceflight |
-
2017
- 2017-05-18 CN CN201710354265.5A patent/CN107116340A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1715729A (en) * | 2005-07-04 | 2006-01-04 | 哈尔滨工业大学 | Composite material pressure container with large size, super thin metal inner lining and its producing method |
| EP1818596B1 (en) * | 2006-02-09 | 2009-04-15 | Gräfenthaler Kunststofftechnik GmbH | Pressure vessel made of plastic and method for its manufacture |
| CN101676595A (en) * | 2008-09-15 | 2010-03-24 | 本特勒Sgl有限责任两合公司 | Method for producing a gas container, in particular for motor vehicles |
| CN102991729A (en) * | 2012-11-30 | 2013-03-27 | 北京控制工程研究所 | Light mesh-type surface tension storage tank |
| CN105674041A (en) * | 2016-01-28 | 2016-06-15 | 上海空间推进研究所 | Spherical composite gas cylinder for spaceflight |
Non-Patent Citations (1)
| Title |
|---|
| 张天平等: "一种卫星推进系统复合材料氦气瓶设计及验证", 《上海航天》 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111876706A (en) * | 2020-06-30 | 2020-11-03 | 成都飞机工业（集团）有限责任公司 | Heat treatment method of thin-wall damage tolerance type TC4-DT titanium alloy part |
| CN114505688A (en) * | 2022-03-04 | 2022-05-17 | 西安零壹空间科技有限公司 | Thin-wall special-shaped combustion chamber shell and machining method thereof |
| CN114871557A (en) * | 2022-06-21 | 2022-08-09 | 南京晨光集团有限责任公司 | Vacuum electron beam manufacturing method for spacecraft thin-wall cylindrical storage tank |
| CN114871557B (en) * | 2022-06-21 | 2024-05-07 | 南京晨光集团有限责任公司 | Vacuum electron beam manufacturing method for spacecraft thin-wall cylindrical storage tank |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP4896032B2 (en) | Tubular target | |
| US6203752B1 (en) | Rhenium-coated tungsten-based alloy and composite articles and method therefor | |
| US3622313A (en) | Hot isostatic pressing using a vitreous container | |
| CN107116340A (en) | Space flight large size, thin walled liner and its manufacture method | |
| US20020041819A1 (en) | Low oxygen refractory metal powder for powder metallurgy | |
| BR102015004077A2 (en) | methods for fabricating a part | |
| US20030042233A1 (en) | Production and use of welding filler metal | |
| CN104480437A (en) | Production method for integrally formed cylindrical target | |
| CZ20011740A3 (en) | Low oxygen refractory hard-to-melt metal powder for powder metallurgy, process of its production and products produced therefrom | |
| NO145330B (en) | PROCEDURE FOR THE MANUFACTURE OF STAINLESS STEEL BEETS | |
| CN108480621A (en) | A method of shaping rhenium component using spherical rhenium powder | |
| WO2006008197A1 (en) | Cylindrical target obtained by hot isostatic pressing | |
| CN108796304A (en) | A kind of γ-TiAl prealloys gas-atomized powder electrode bar and preparation method thereof | |
| EP1779946B1 (en) | Supersolvus hot isostatic pressing and ring rolling of hollow powder forms | |
| US3531848A (en) | Fabrication of integral structures | |
| SE411051B (en) | PROCEDURE FOR PREPARING A FOREMAL OF FIBER REINFORCED METAL MATERIAL | |
| EP0694754A2 (en) | Method for producing high density refractory metal warhead liners from single phase materials | |
| US20140106144A1 (en) | System and method for fabrication of 3-d parts | |
| CN106735190A (en) | A kind of preparation method of particle enhanced aluminum-based composite material large scale thick-wall tube | |
| CN117259755A (en) | Preparation method of large-size TC18 titanium alloy thin-wall part | |
| EP0358802A1 (en) | Method for fabricating titanium alloys in foil form | |
| CN109807338B (en) | Sectional preparation method of rhenium-niobium composite spray pipe | |
| CN105458265B (en) | A kind of hot isostatic pressing use control pattern core, its manufacturing method and its application of recyclable reuse | |
| US7400697B1 (en) | Clad tube for nuclear fuel | |
| US20170225261A1 (en) | Welding electrodes and methods of manufacturing same |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |