CN206750178U - Ultra lightweighting spacecraft propulsion agent tank - Google Patents
Ultra lightweighting spacecraft propulsion agent tank Download PDFInfo
- Publication number
- CN206750178U CN206750178U CN201621399654.7U CN201621399654U CN206750178U CN 206750178 U CN206750178 U CN 206750178U CN 201621399654 U CN201621399654 U CN 201621399654U CN 206750178 U CN206750178 U CN 206750178U
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- housing
- connecting seat
- agent tank
- diaphragm
- ultra lightweighting
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Abstract
The utility model discloses ultra lightweighting spacecraft propulsion agent tank, including：Injection is shaped made of 7055 aluminum alloy materials, hemispheric first housing and the second housing；Occur along its surface vertical direction made of elasticity and plasticity deformation, pure aluminum material, circular diaphragm；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 by forging and pressing, being heat-treated, fine-processing technique shaping, second housing and the second connecting seat are shaped by forging and stamping same as described above, heat treatment, fine-processing technique, the utility model shapes 7055 aluminum alloy materials by using the injection of superhigh intensity realizes the thick reduction of tank body wall, to reach ultra lightweighting purpose.
Description
Technical field
The utility model belongs to propellant tank technical field, and in particular to ultra lightweighting spacecraft propulsion agent tank.
Background technology
Propellant tank is the pressure vessel for storing and supplying propellant for spacecraft liquid propelling system, is propulsion system
Important component, there is very important influence to the performance, reliability and life-span of spacecraft propulsion system.Recently as section
The progress of technology and the needs of Space environment detection, spacecraft initially enter the brand-new development epoch.China exists《In 2011
The space flight of state》Point out that startup is implemented to be returned as the step task of moon exploration the 3rd of target with moon surface sample in white paper, 2017 years
No. 5 detectors of the goddess in the moon will be launched, started when China Aerospace cause founded for 60 anniversaries as moon exploration within 2016
Mars exploration plan, mars exploration also by the circular detection for completing Mars, landing and make an inspection tour detection and sampling return.For new
Type spacecraft, especially deep space probe, the requirement to weight is 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 used mainly has the light metals such as aluminium alloy, titanium alloy, also begins to develop composite tank, but propellant in the world
The technical bottlenecks such as compatibility, leakproof with composite are also to be solved.The country is in composite technology, structure design skill
Key technology hardly possible in various degree all be present in art, technology, Non-Destructive Testing and health monitoring technique, experimental test technology etc.
Topic, therefore the large-scale application of composite tank is difficult to realize in a short time.Can only be by using the higher light metal of specific strength
Material realizes tank lightweight to meet new spacecraft lightweight demand.
The conventional material of present propellant tank mainly has a titanium alloy, 2000 systems and 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 because specific strength is relatively low,
It 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) occurs
Three trades mark, wherein 7055 be intensity highest alloy in wrought aluminium alloy so far, it is commonly called as " trump aluminium alloy ", Ye Shimei
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, aerospace structure part is largely contributed to, rarely has report
Its application on propellant tank of road.Most important reason is that 7000 line aluminium alloy alloying element contents are higher, and tradition partly connects
Certain tissue defects be present in the alloy ingot blank of continuous foundry engieering production, such as dendrite tissue of serious gross segregation, prosperity,
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 and is navigating
Application in its device lightweight.
Utility model content
The purpose of this utility model is to overcome above-mentioned the deficiencies in the prior art, there is provided the agent of ultra lightweighting spacecraft propulsion is store
Case.
Ultra lightweighting spacecraft propulsion agent tank, including：
Injection is shaped made of 7055 aluminum alloy materials, hemispheric first housing and the second housing；
Occur along its surface vertical direction made of elasticity and plasticity deformation, pure aluminum material, circular diaphragm；
It is characterized in that：The diaphragm arrangement is between the first housing and the second housing, and wherein diaphragm is welded on first shell
The bottom of body, the first housing and the second housing are welded to connect, and the first housing upper is provided with the first connecting seat of cylinder, second shell
The bottom of body is provided with cylindrical second connecting seat, is provided with manhole at the center of the first connecting seat, through hole top is provided with interior spiral shell
Line, manhole is provided with the center of the second connecting seat, the bottom of through hole is provided with internal thread.
Preferably, the through hole at 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 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, the beneficial effects of the utility model：
The utility model realizes tank body wall thickness by using injection 7055 aluminum alloy materials of shaping of superhigh intensity and subtracted
It is small, to reach ultra lightweighting purpose；0.5~3mm of wall thickness can be produced, volume covers all kinds of propellant tanks within 110L,
In the case where bearing equal pressure, loss of weight is integrated than the tank of traditional aluminum alloy materials and the additional composite of aluminium alloy cavity
More than 40%；The actual burst pressure of tank can reach 8.6MPa.
Brief description of the drawings
Fig. 1 is the structural representation of the utility model ultra lightweighting spacecraft propulsion agent tank.
Fig. 2 is schematic diagram of the utility model ultra lightweighting spacecraft propulsion agent tank in the case where emptying propellant state.
Fig. 3 is schematic diagram of the utility model ultra lightweighting spacecraft propulsion agent tank in the case where filling propellant state.
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.
Embodiment
Referring to Fig. 1, Fig. 2, Fig. 3, ultra lightweighting spacecraft propulsion agent tank, including：
Injection is shaped made of 7055 aluminum alloy materials, the hemispheric housing 6 of first housing 4 and second；
Occur along its surface vertical direction made of elasticity and plasticity deformation, pure aluminum material, circular diaphragm 5；
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 on
The bottom of one housing 4, the first housing 4 and the second housing 6 are welded to connect, and the top of the first housing 4 is provided with the first connection of cylinder
Seat 3, the bottom of the second housing 6 are provided with cylindrical second connecting seat 7, manhole, through hole are provided with the center of the first connecting seat 3
Top is provided with internal thread, and manhole is provided with the center of the second connecting seat 7, and the bottom of through hole is provided with internal thread.
Through hole at the center of first connecting seat 3 is communicated by the first nipple 2 with vent valves 1.
Second connecting seat 7 is communicated by the second nipple 8 with air intake valve 9.
The wall thickness of the housing 6 of first housing 4 and second is 0.5~3mm.
The volume of diameter of Spherical Volume is 30~110L between the housing 6 of first housing 4 and second.
The utility model ultra lightweighting spacecraft propulsion agent tank, is worked by such a way：
When needing to fill propellant, unlatching vent valves 1, the hemispherical space that propellant is injected in the first housing 4,
Diaphragm is bent downwardly simultaneously, until diaphragm is completed close to propellant (taking diameter of Spherical Volume 90%) during the second 6 lower inner wall of housing
The filling of propellant；
When needing lower outer offer propellant, vent valves 1 and air intake valve 9 are opened, to the inwall of the second housing 6 and diaphragm
Between space in injection 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.
Utility model is exemplarily described above in conjunction with accompanying drawing for technical solutions of the utility model, it is clear that this practicality
New specific implementation is not subject to the restrictions described above, and is carried out as long as employing methodology and technical scheme of the present utility model
Various unsubstantialities improve, or it is not improved the design of utility model and technical scheme are directly applied into other occasions,
Within the scope of protection of the utility model.
Claims (5)
1. ultra lightweighting spacecraft propulsion agent tank, including：
Made of injection 7055 aluminum alloy materials of shaping, hemispheric first housing (4) and the second housing (6)；
Occur along its surface vertical direction made of elasticity and plasticity deformation, pure aluminum material, circular diaphragm (5)；
It is characterized in that：The diaphragm (5) is arranged between the first housing (4) and the second housing (6), and wherein diaphragm (5) welds
In the bottom of the first housing (4), the first housing (4) and the second housing (6) are welded to connect, and the first housing (4) top is provided with cylinder
The first connecting seat (3) of shape, the bottom of the second housing (6) are provided with cylindrical second connecting seat (7), in the first connecting seat (3)
Manhole is provided with the heart, through hole top is provided with internal thread, manhole is provided with the center of the second connecting seat (7), through hole
Bottom is provided with internal thread.
2. ultra lightweighting spacecraft propulsion agent tank as claimed in claim 1, it is characterised in that：First connecting seat (3)
Through hole at 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 by the second nipple (8) with air intake valve (9).
4. ultra lightweighting spacecraft propulsion agent tank as claimed in claim 1, it is characterised in that：First housing (4) and
The wall thickness of second housing (6) is 0.5~3mm.
5. 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 |
|---|---|---|---|
| CN201621399654.7U CN206750178U (en) | 2016-12-20 | 2016-12-20 | Ultra lightweighting spacecraft propulsion agent tank |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621399654.7U CN206750178U (en) | 2016-12-20 | 2016-12-20 | Ultra lightweighting spacecraft propulsion agent tank |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206750178U true CN206750178U (en) | 2017-12-15 |
Family
ID=60607729
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621399654.7U Active CN206750178U (en) | 2016-12-20 | 2016-12-20 | Ultra lightweighting spacecraft propulsion agent tank |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206750178U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109204887A (en) * | 2018-09-06 | 2019-01-15 | 宁波天擎航天科技有限公司 | A kind of aerospace propellant tank |
| CN109611301A (en) * | 2019-01-23 | 2019-04-12 | 北京控制工程研究所 | A kind of hydrazine Arcjet ignition system inhibiting pressure fluctuation |
| CN112705842A (en) * | 2021-01-28 | 2021-04-27 | 贵州航天天马机电科技有限公司 | Welding device for large-size variable-curvature hollow storage tank diaphragm shell |
| CN113090415A (en) * | 2021-04-13 | 2021-07-09 | 西北工业大学 | Variable flow solid-liquid mixing engine |
-
2016
- 2016-12-20 CN CN201621399654.7U patent/CN206750178U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109204887A (en) * | 2018-09-06 | 2019-01-15 | 宁波天擎航天科技有限公司 | A kind of aerospace propellant tank |
| CN109611301A (en) * | 2019-01-23 | 2019-04-12 | 北京控制工程研究所 | A kind of hydrazine Arcjet ignition system inhibiting pressure fluctuation |
| CN112705842A (en) * | 2021-01-28 | 2021-04-27 | 贵州航天天马机电科技有限公司 | Welding device for large-size variable-curvature hollow storage tank diaphragm shell |
| CN113090415A (en) * | 2021-04-13 | 2021-07-09 | 西北工业大学 | Variable flow solid-liquid mixing engine |
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