CN106742074A - Ultra lightweighting spacecraft propulsion agent tank - Google Patents
Ultra lightweighting spacecraft propulsion agent tank Download PDFInfo
- Publication number
- CN106742074A CN106742074A CN201611184105.2A CN201611184105A CN106742074A CN 106742074 A CN106742074 A CN 106742074A CN 201611184105 A CN201611184105 A CN 201611184105A CN 106742074 A CN106742074 A CN 106742074A
- Authority
- CN
- China
- Prior art keywords
- housing
- forging
- connecting seat
- agent tank
- stamping
- 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
- 238000005242 forging Methods 0.000 claims abstract description 27
- 229910000838 Al alloy Inorganic materials 0.000 claims abstract description 22
- 239000003795 chemical substances by application Substances 0.000 claims abstract description 19
- 239000000956 alloy Substances 0.000 claims abstract description 17
- 238000000034 method Methods 0.000 claims abstract description 16
- 238000010438 heat treatment Methods 0.000 claims abstract description 9
- 238000012545 processing Methods 0.000 claims abstract description 9
- 239000000463 material Substances 0.000 claims abstract description 8
- 238000002347 injection Methods 0.000 claims abstract description 6
- 239000007924 injection Substances 0.000 claims abstract description 6
- 238000007493 shaping process Methods 0.000 claims abstract description 6
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 5
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 5
- 238000005516 engineering process Methods 0.000 claims description 12
- 210000002445 nipple Anatomy 0.000 claims description 8
- 229910045601 alloy Inorganic materials 0.000 claims description 7
- 239000000314 lubricant Substances 0.000 claims description 6
- 239000007787 solid Substances 0.000 claims description 6
- 229910001297 Zn alloy Inorganic materials 0.000 claims description 3
- 238000009413 insulation Methods 0.000 claims description 3
- 239000000203 mixture Substances 0.000 claims description 3
- 239000002023 wood Substances 0.000 claims description 3
- 239000004575 stone Substances 0.000 claims 1
- 238000003756 stirring Methods 0.000 abstract description 3
- 238000003466 welding Methods 0.000 abstract description 3
- 239000003380 propellant Substances 0.000 description 18
- 239000002131 composite material Substances 0.000 description 5
- PEDCQBHIVMGVHV-UHFFFAOYSA-N Glycerine Chemical compound OCC(O)CO PEDCQBHIVMGVHV-UHFFFAOYSA-N 0.000 description 4
- 238000001514 detection method Methods 0.000 description 4
- 238000013461 design Methods 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- 229910001069 Ti alloy Inorganic materials 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 229910002804 graphite Inorganic materials 0.000 description 2
- 239000010439 graphite Substances 0.000 description 2
- 208000020442 loss of weight Diseases 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 239000000523 sample Substances 0.000 description 2
- 229910001148 Al-Li alloy Inorganic materials 0.000 description 1
- 229910000695 Aluminium-scandium alloy Inorganic materials 0.000 description 1
- 229910018569 Al—Zn—Mg—Cu Inorganic materials 0.000 description 1
- FCVHBUFELUXTLR-UHFFFAOYSA-N [Li].[AlH3] Chemical compound [Li].[AlH3] FCVHBUFELUXTLR-UHFFFAOYSA-N 0.000 description 1
- 238000005275 alloying Methods 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- -1 aluminium alloy Chemical class 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 210000001787 dendrite Anatomy 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 239000001989 lithium alloy Substances 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 238000009659 non-destructive testing Methods 0.000 description 1
- 238000005070 sampling Methods 0.000 description 1
- 238000005204 segregation Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 238000003786 synthesis reaction Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/402—Propellant tanks; Feeding propellants
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The invention discloses ultra lightweighting spacecraft propulsion agent tank, including：Injection 7055 aluminum alloy materials of shaping are made, hemispheric first housing and the second housing；There is elasticity with being plastically deformed, that pure aluminum material is made, circular diaphragm along its surface vertical direction；It is characterized in that：The diaphragm arrangement is between the first housing and the second housing, wherein diaphragm is welded on the bottom of the first housing by TIG weld technique, first housing and the second housing are welded to connect by stirring friction-welding technique, first housing and the first connecting seat are shaped by forging and stamping, heat treatment, fine-processing technique, second housing and the second connecting seat are shaped by forging and stamping same as described above, heat treatment, fine-processing technique, the present invention shapes 7055 aluminum alloy materials and realizes the thick reduction of tank body wall by the injection using superhigh intensity, to reach ultra lightweighting purpose.
Description
Technical field
The invention belongs to propellant tank technical field, and in particular to ultra lightweighting spacecraft propulsion agent tank.
Background technology
It, for spacecraft liquid propelling system is stored and the pressure vessel of supply propellant, is propulsion system that propellant tank is
Important component, performance, reliability and life-span to spacecraft propulsion system have very important influence.Recently as section
The need for the progress of technology and Space environment detection, spacecraft initially enters the brand-new development epoch.China exists《In 2011
The space flight of state》Point out to start the step task of moon exploration the 3rd for implementing to be returned as target with moon surface sample, 2017 years in white paper
No. 5 detectors of the goddess in the moon will be launched, started as moon exploration when China Aerospace cause founded for 60 anniversaries within 2016
Mars exploration plan, circular detection, landing and the tour detection and sampling that mars exploration will also complete Mars is returned.For new
Type spacecraft, especially deep space probe, the requirement to weight are very harsh, no matter and propellant tank from sole mass or
All occupy significant proportion for shared space, therefore tank lightweight turns into the key factor of spacecraft loss of weight.Tank is current
The material for using mainly has the light metals such as aluminium alloy, titanium alloy, also begin in the world develop composite tank, but propellant
The technical bottlenecks such as compatibility, leakproof with composite are also to be solved.The country is in composite technology, structure design skill
All to there is key technology in the aspect such as art, technology, Non-Destructive Testing and health monitoring technique, experimental test technology difficult in various degree
Topic, therefore the large-scale application of composite tank is difficult to realize in a short time.Can only be by using specific strength light metal higher
Material realizes tank lightweight meeting new spacecraft lightweight demand.
The conventional material of present propellant tank mainly has a titanium alloy, 2000 be with 5000 line aluminium alloys (such as 5A06,
2A12,2219), aluminium lithium alloy (such as 2195), aluminium-scandium alloy (such as 5B70).And these materials are relatively low due to specific strength,
Can not meet that tank quality is lighter, bear the stronger design requirement of internal pressure capability.7000 to be that alloy is referred to as superhigh intensity hard
Aluminium (LC), is Al-Zn-Mg-Cu alloy.Its development experience 19th century beginning of the fifties, the beginning of the seventies and the junior three nineties weight
Node is wanted, most representational 7075 (registering for 1954), 7050 (registering for 1971) and 7055 (registering for 1991) are occurred in that
Three trades mark, wherein 7055 is intensity highest alloy in wrought aluminium alloy so far, are commonly called as " trump aluminium alloy ", are also beautiful
The best ultrahigh-strength aluminum alloy of combination property of state's registration, the yield strength of 7055 aluminium alloys surpasses under T73 conditions of heat treatment
Cross more than 5A06 surrender three times, construction weight can be greatly reduced according to 7055 aluminium alloys production propellant tank, realize deep
The lightweight of sky detection spacecraft.
However, being 7055 or other 7000 line aluminium alloys, major part contributes to aerospace structure part, rarely has report
Its application on propellant tank of road.Topmost reason is that 7000 line aluminium alloy alloying element contents are higher, and tradition partly connects
There are certain tissue defects in the alloy ingot blank of continuous foundry engieering production, such as serious gross segregation, flourishing dendrite tissue,
Grain form and size are uneven, organize thick, microporosity etc., cause forging and other pressure processing forming difficulties,
Especially for thin-wall part as tank, its blank forged piece deflection is big, forging crack, and forging performance list easily occurs
Part and lot stability are poor.So rarely useful 7000 line aluminium alloy production tank, limits more high specific strength aluminium alloy in boat
Application in its device lightweight.
The content of the invention
It is an object of the invention to overcome above-mentioned the deficiencies in the prior art, there is provided ultra lightweighting spacecraft propulsion agent tank.
Ultra lightweighting spacecraft propulsion agent tank, including：
Injection 7055 aluminum alloy materials of shaping are made, hemispheric first housing and the second housing；
There is elasticity with being plastically deformed, that pure aluminum material is made, circular diaphragm along its surface vertical direction；
It is characterized in that：Between the first housing and the second housing, wherein diaphragm passes through TIG weld work to the diaphragm arrangement
Skill is welded on the bottom of the first housing, and the first housing and the second housing are welded to connect by stirring friction-welding technique, first shell
Body top is provided with the first connecting seat of cylinder, and the bottom of the second housing is provided with cylindrical second connecting seat, the first connecting seat
Center is provided with manhole, and through hole top is provided with internal thread, and the center of the second connecting seat is provided with manhole, under through hole
Portion is provided with internal thread, and the first housing and the first connecting seat are shaped by forging and stamping, heat treatment, fine-processing technique, the second housing and the
Two connecting seats are shaped by forging and stamping same as described above, heat treatment, fine-processing technique.
Preferably, the through hole of the first connecting seat center is communicated by the first nipple with vent valves.
Preferably, second connecting seat is communicated by the second nipple with air intake valve.
Preferably, the content of Zn alloys is 7.6~8.4% in 7055 aluminum alloy materials, and the total content of alloy is
12.08~14.15%.
Preferably, the Forging Technology is divided into repeatedly forging and stamping, needs to melt down insulation before forging and stamping every time, every time the deflection of forging and stamping
Be 30~40%, last time forge and press, fill solid lubricant between punch-pin and blank part, after Forging Technology the first housing and
Second shell chaeta blank wall thickness is 30~40mm；It is further preferred that the solid lubricant is the mixture of graphite and wood chip.
Preferably, the wall thickness of first housing and the second housing is 0.5~3mm.
Preferably, the volume of diameter of Spherical Volume is 30~110L between first housing and the second housing.
Compared with prior art, beneficial effects of the present invention：
The present invention shapes 7055 aluminum alloy materials and realizes the thick reduction of tank body wall by the injection using superhigh intensity, with
Reach ultra lightweighting purpose；0.5~3mm of wall thickness can be produced, all kinds of propellant tanks within volume covering 110L are bearing
In the case of equal pressure, than traditional aluminum alloy materials and the additional composite of aluminium alloy cavity tank synthesis loss of weight 40% with
On；The actual burst pressure of tank can reach 8.6MPa.
Brief description of the drawings
Fig. 1 is the structural representation of ultra lightweighting spacecraft propulsion agent tank of the present invention.
Fig. 2 is schematic diagram of the ultra lightweighting spacecraft propulsion agent tank of the present invention in the case where propellant state is emptied.
Fig. 3 is schematic diagram of the ultra lightweighting spacecraft propulsion agent tank of the present invention in the case where propellant state is filled.
In figure, 1, vent valves, the 2, first nipple, the 3, first connecting seat, the 4, first housing, 5, diaphragm, 6, second shell
Body, the 7, second connecting seat, the 8, second nipple, 9, air intake valve.
Specific embodiment
Referring to Fig. 1, Fig. 2, Fig. 3, ultra lightweighting spacecraft propulsion agent tank, including：
Injection 7055 aluminum alloy materials of shaping the are made, housing 6 of hemispheric first housing 4 and second；
There is elasticity with being plastically deformed, that pure aluminum material is made, circular diaphragm 5 along its surface vertical direction；
It is characterized in that：The diaphragm 5 is arranged between the first housing 4 and the second housing 6, and wherein diaphragm 5 is welded by TIG
The bottom that technique is welded on the first housing 4 is connect, the first housing 4 and the second housing 6 are welded to connect by stirring friction-welding technique,
The top of first housing 4 is provided with the first connecting seat 3 of cylinder, and the bottom of the second housing 6 is provided with cylindrical second connecting seat 7, the
The center of a connecting seat 3 is provided with manhole, and through hole top is provided with internal thread, and the center of the second connecting seat 7 is provided with circle
Through hole, the bottom of through hole is provided with internal thread, the first housing 4 and the first connecting seat 3 by forging and stamping, heat treatment, fine-processing technique into
Shape, the second housing 6 and the second connecting seat 7 are shaped by forging and stamping same as described above, heat treatment, fine-processing technique.
The discharge of propellant for convenience, in one embodiment provided in an embodiment of the present invention, first connecting seat 3
The through hole of center is communicated by the first nipple 2 with vent valves 1.
In order to further facilitate the discharge of propellant, in one embodiment provided in an embodiment of the present invention, described second
Connecting seat 7 is communicated by the second nipple 8 with air intake valve 9.
In order to improve the intensity of tank, reduce the wall thickness of tank, in one embodiment provided in an embodiment of the present invention, institute
It is 7.6~8.4% to state the content of Zn alloys in 7055 aluminum alloy materials, and the total content of alloy is 12.08~14.15%.
In order to further improve the intensity of tank, reduce the wall thickness of tank, in one provided in an embodiment of the present invention implementation
Example in, the Forging Technology be divided into repeatedly forging and stamping, every time forging and stamping before need to melt down insulation, every time forging and stamping deflection be 30~
40%, last time is forged and pressed, and fills solid lubricant between punch-pin and blank part, the first housing 4 and second after Forging Technology
The blank wall thickness of housing 6 is 30~40mm；
Punch-pin is separated with blank part for convenience, and the solid lubricant is the mixture of graphite and wood chip.
In order to reduce the wall thickness of tank, in one embodiment provided in an embodiment of the present invention, first housing 4 and
The wall thickness of two housings 6 is 0.5~3mm.
In order to meet the application of tank, in one embodiment provided in an embodiment of the present invention, first housing 4 and
The volume of diameter of Spherical Volume is 30~110L between two housings 6.
Ultra lightweighting spacecraft propulsion agent tank of the present invention, is worked by such a way：
When filling propellant is needed, unlatching vent valves 1, the hemispherical space that propellant is injected in the first housing 4, together
When diaphragm be bent downwardly, until diaphragm completes to push away close to (propellant takes diameter of Spherical Volume 90%) during the second 6 lower inner wall of housing
Enter the filling of agent；
When lower outer offer propellant is needed, vent valves 1 and air intake valve 9 are opened, to the inwall of the second housing 6 and diaphragm
Between space in inject filling gas, until diaphragm close to the first 4 upper inside wall of housing when (filling gas take diameter of Spherical Volume
90%) discharge of propellant, is completed.
Technical solution of the present invention is exemplarily described above in conjunction with accompanying drawing to invention, it is clear that the present invention is implemented
It is not subject to the restrictions described above, as long as employ the various unsubstantialities that the method for the present invention is conceived and technical scheme is carried out changing
Enter, or it is not improved the design of invention and technical scheme are directly applied into other occasions, in protection scope of the present invention
Within.
Claims (8)
1. ultra lightweighting spacecraft propulsion agent tank, including：
Injection 7055 aluminum alloy materials of shaping are made, hemispheric first housing (4) and the second housing (6)；
There is elasticity with being plastically deformed, that pure aluminum material is made, circular diaphragm (5) along its surface vertical direction；
It is characterized in that：The diaphragm (5) is arranged between the first housing (4) and the second housing (6), and wherein diaphragm (5) passes through
TIG weld technique is welded on the bottom of the first housing (4), and the first housing (4) and the second housing (6) weld work by agitating friction
Skill is welded to connect, and the first housing (4) top is provided with first connecting seat (3) of cylinder, and the bottom of the second housing (6) is provided with cylinder
The connecting seat of shape second (7), the center of the first connecting seat (3) is provided with manhole, and through hole top is provided with internal thread, the second connection
The center of seat (7) is provided with manhole, and the bottom of through hole is provided with internal thread, and the first housing (4) passes through with the first connecting seat (3)
Forging and stamping, heat treatment, fine-processing technique shaping, the second housing (6) is with the second connecting seat (7) by forging and stamping same as described above, heat
Treatment, fine-processing technique shaping.
2. ultra lightweighting spacecraft propulsion agent tank as claimed in claim 1, it is characterised in that：First connecting seat (3)
The through hole of center is communicated by the first nipple (2) with vent valves (1).
3. ultra lightweighting spacecraft propulsion agent tank as claimed in claim 1, it is characterised in that：Second connecting seat (7)
Communicated with air intake valve (9) by the second nipple (8).
4. ultra lightweighting spacecraft propulsion agent tank as claimed in claim 1, it is characterised in that：7055 aluminum alloy materials
The content of middle Zn alloys is 7.6~8.4%, and the total content of alloy is 12.08~14.15%.
5. ultra lightweighting spacecraft propulsion agent tank as claimed in claim 1, it is characterised in that：The Forging Technology is divided into many
Secondary forging and stamping, need to melt down insulation before forging and stamping every time, and the deflection of forging and stamping is 30~40% every time, last time forging and stamping, punch-pin and hair
Solid lubricant is filled between blank, after Forging Technology the first housing (4) and the second housing (6) blank wall thickness be 30~
40mm。
6. ultra lightweighting spacecraft propulsion agent tank as claimed in claim 5, it is characterised in that：The solid lubricant is stone
The mixture of ink and wood chip.
7. ultra lightweighting spacecraft propulsion agent tank as claimed in claim 1, it is characterised in that：First housing (4) and
The wall thickness of the second housing (6) is 0.5~3mm.
8. ultra lightweighting spacecraft propulsion agent tank as claimed in claim 1, it is characterised in that：First housing (4) and
The volume of diameter of Spherical Volume is 30~110L between second housing (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611184105.2A CN106742074A (en) | 2016-12-20 | 2016-12-20 | Ultra lightweighting spacecraft propulsion agent tank |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611184105.2A CN106742074A (en) | 2016-12-20 | 2016-12-20 | Ultra lightweighting spacecraft propulsion agent tank |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106742074A true CN106742074A (en) | 2017-05-31 |
Family
ID=58894279
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611184105.2A Pending CN106742074A (en) | 2016-12-20 | 2016-12-20 | Ultra lightweighting spacecraft propulsion agent tank |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106742074A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107167292A (en) * | 2017-07-03 | 2017-09-15 | 贵州航天朝阳科技有限责任公司 | A kind of vibration testing device of spacecraft propulsion agent tank metallic membrane |
| CN107323695A (en) * | 2017-06-14 | 2017-11-07 | 贵州航天朝阳科技有限责任公司 | A kind of attachment structure of tank diaphragm and tank housing |
| CN108708801A (en) * | 2018-06-01 | 2018-10-26 | 上海空间推进研究所 | The novel Propellant Management scheme of space propulsion system |
| CN110341989A (en) * | 2019-06-14 | 2019-10-18 | 上海宇航系统工程研究所 | A kind of connection method and the tank of tank and aluminium alloy post |
| CN112389682A (en) * | 2020-11-11 | 2021-02-23 | 上海空间推进研究所 | Diaphragm storage box |
| CN114922744A (en) * | 2022-03-31 | 2022-08-19 | 北京控制工程研究所 | Force-bearing type low-temperature common-bottom storage tank for spacecraft |
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| CN101695753A (en) * | 2009-10-23 | 2010-04-21 | 江苏豪然喷射成形合金有限公司 | Method for manufacturing high-strength 7055 aluminum alloy forge piece formed by spraying |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107323695A (en) * | 2017-06-14 | 2017-11-07 | 贵州航天朝阳科技有限责任公司 | A kind of attachment structure of tank diaphragm and tank housing |
| CN107167292A (en) * | 2017-07-03 | 2017-09-15 | 贵州航天朝阳科技有限责任公司 | A kind of vibration testing device of spacecraft propulsion agent tank metallic membrane |
| CN108708801A (en) * | 2018-06-01 | 2018-10-26 | 上海空间推进研究所 | The novel Propellant Management scheme of space propulsion system |
| CN110341989A (en) * | 2019-06-14 | 2019-10-18 | 上海宇航系统工程研究所 | A kind of connection method and the tank of tank and aluminium alloy post |
| CN110341989B (en) * | 2019-06-14 | 2023-02-24 | 上海宇航系统工程研究所 | Connecting method of storage tank and aluminum alloy bracket and storage tank |
| CN112389682A (en) * | 2020-11-11 | 2021-02-23 | 上海空间推进研究所 | Diaphragm storage box |
| CN112389682B (en) * | 2020-11-11 | 2022-04-01 | 上海空间推进研究所 | Diaphragm storage box |
| CN114922744A (en) * | 2022-03-31 | 2022-08-19 | 北京控制工程研究所 | Force-bearing type low-temperature common-bottom storage tank for spacecraft |
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Application publication date: 20170531 |
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