CN209008892U - A kind of aerospace propellant tank - Google Patents
A kind of aerospace propellant tank Download PDFInfo
- Publication number
- CN209008892U CN209008892U CN201821452156.3U CN201821452156U CN209008892U CN 209008892 U CN209008892 U CN 209008892U CN 201821452156 U CN201821452156 U CN 201821452156U CN 209008892 U CN209008892 U CN 209008892U
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- diaphragm
- main body
- primary diaphragm
- propellant tank
- space
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Abstract
The utility model is suitable for aerospace field, provides a kind of aerospace propellant tank, comprising: tank shell；The inner wall of primary diaphragm, primary diaphragm and tank shell forms first receiving space；The inner wall of secondary diaphragm, secondary diaphragm and tank shell forms the second accommodation space, and secondary diaphragm and primary diaphragm form closed gas compression space；The first fluid path being connected to first receiving space connects mouth；The second fluid path being connected to the second accommodation space connects mouth；And the gas circuit being connected to gas compression space connects mouth, and when gas circuit connects mouth and is passed through compressed gas to gas compression space, primary diaphragm and secondary diaphragm can deformation occurs and compresses first receiving space and the second accommodation space respectively.Fuel and oxidant can be stored in the same propellant tank by the aerospace propellant tank of the utility model simultaneously, can be effectively reduced the occupancy volume of propellant tank, be reduced the overall volume and quality of spacecraft, reduce manufacturing cost.
Description
Technical field
The utility model belongs to field of aerospace technology more particularly to a kind of aerospace propellant tank.
Background technique
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 service life of spacecraft propulsion system.Recently as section
The progress of technology and the needs of Space environment detection, spacecraft initially enter the completely new development epoch.
In the prior art, single diaphragm, diaphragm and tank shell is usually only arranged in the propellant tank of aerospace
Inner wall only forms single for accommodating the cavity of fuel or oxidant, it is therefore desirable to two mutually independent propellant tank difference
Storing fuel and oxidant keep the total quality of spacecraft and volume larger, are not easy to so that propellant tank occupied space is big
The lightness of spacecraft, and manufacturing cost is high.
Utility model content
The utility model provides a kind of aerospace propellant tank, it is intended to solve the propellant tank of the prior art only
The single storing fuel of energy or oxidant need two mutually independent propellant tanks difference storing fuels and oxidant, promote
Agent tank occupied space is big, to keep the total quality of spacecraft and volume larger, and the problem that manufacturing cost is high.
The utility model is realized in this way a kind of aerospace propellant tank, comprising:
Tank shell；
Primary diaphragm, the primary diaphragm are set in the tank shell and form first with the inner wall of the tank shell
Accommodation space；
Secondary diaphragm, the secondary diaphragm are set in the tank shell and form second with the inner wall of the tank shell
Accommodation space, the secondary diaphragm and the primary diaphragm form closed gas compression space；
The first fluid path being connected to the first receiving space connects mouth；
The second fluid path being connected to second accommodation space connects mouth；And
The gas circuit being connected to the gas compression space connects mouth, and the gas circuit connects mouth and is passed through pressure to the gas compression space
When contracting gas, the primary diaphragm and the secondary diaphragm can deformation occurs and compresses first receiving space and described second respectively
Accommodation space.
Preferably, the primary diaphragm and the secondary diaphragm are made of polytetrafluoroethylene (PTFE).
Preferably, the primary diaphragm includes the primary diaphragm main body in hemisphere face structure and is connected to first film
The inner wall of the first connecting portion of piece main body side, the first connecting portion and the tank shell is tightly connected.
Preferably, the secondary diaphragm includes the secondary diaphragm main body in hemisphere face structure and is connected to second film
The inner wall of the second connecting portion of piece main body side, the second connecting portion and the tank shell is tightly connected.
Preferably, the thickness of the first connecting portion is less than the thickness of the primary diaphragm main body, the second connecting portion
Thickness be less than the secondary diaphragm main body thickness.
Preferably, the thickness of the primary diaphragm main body is gradually increased in heart direction thereto from its edge；Second film
The thickness of piece main body is gradually increased in heart direction thereto from its edge.
Preferably, the secondary diaphragm main body is contained in the primary diaphragm main body and can be with the primary diaphragm main body
Fitting.
Preferably, the primary diaphragm and the secondary diaphragm with a thickness of 0.1~3mm.
Preferably, the tank shell is in chondritic.
Aerospace provided by the utility model with propellant tank by setting two diaphragms, two diaphragms respectively with storage
Tank shell forms first receiving space and the second accommodation space for storing fuel or oxidant, so that fuel and oxidant can
It is stored in the same tank shell simultaneously, it, can be effective without two propellant tank difference storing fuels and oxidant
The occupancy volume for reducing propellant tank reduces manufacturing cost to reduce the overall volume and quality of spacecraft；And fuel
It is infused in the same propellant tank, is easy to use simultaneously with oxidant.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of aerospace propellant tank provided by the utility model；
Fig. 2 is the structural schematic diagram of primary diaphragm in aerospace propellant tank provided by the utility model；
Fig. 3 is the structural schematic diagram of secondary diaphragm in aerospace propellant tank provided by the utility model.
Specific embodiment
In order to make the purpose of the utility model, technical solutions and advantages more clearly understood, below in conjunction with attached drawing and implementation
Example, the present invention will be further described in detail.It should be appreciated that specific embodiment described herein is only used to explain
The utility model is not used to limit the utility model.
Aerospace provided by the utility model with propellant tank by setting two diaphragms, two diaphragms respectively with storage
Tank shell forms first receiving space and the second accommodation space for storing fuel or oxidant, so that fuel and oxidant can
It is stored in the same tank shell simultaneously, it, can be effective without two propellant tank difference storing fuels and oxidant
The occupancy volume for reducing propellant tank reduces manufacturing cost to reduce the overall volume and quality of spacecraft；And fuel
It is infused in the same propellant tank, is easy to use simultaneously with oxidant.
Fig. 1 is please referred to, Fig. 1 is the structural schematic diagram of aerospace propellant tank provided by the utility model.The boat
Empty space flight propellant tank includes: tank shell 1；Primary diaphragm 2, primary diaphragm 2 be set to tank shell 1 in and with tank shell
The inner wall of body 1 forms first receiving space 3；Secondary diaphragm 4, secondary diaphragm 4 be set to tank shell 1 in and with tank shell 1
Inner wall forms the second accommodation space 5, and secondary diaphragm 4 and primary diaphragm 2 form closed gas compression space 6；It is accommodated with first
The first fluid path that space 3 is connected to connects mouth 7；The second fluid path being connected to the second accommodation space 5 connects mouth 8；And it is empty with gas compression
Between the gas circuits of 6 connections connect mouth 9, when gas circuit connects mouth 9 and is passed through compressed gas to gas compression space 6, primary diaphragm 2 and secondary diaphragm
4 can deformation occurs and compresses first receiving space 3 and the second accommodation space 5 respectively.
In the utility model embodiment, first receiving space 3 and the second accommodation space 5 can be respectively used to storing fuel or oxygen
Agent, wherein one storing fuel in first receiving space 3 and the second accommodation space 5, another one stores oxidant, to fire
Material and oxidant can be stored in simultaneously in the same propellant tank, without two propellant tanks difference storing fuels and
Oxidant, can effectively reduce the occupancy volume of propellant tank, to reduce the overall volume and quality of spacecraft, reduce system
Cause this；And fuel and oxidant are infused in the same propellant tank simultaneously, are easy to use.
In the utility model embodiment, the first fluid path connects mouth 7 and the second fluid path connects mouth 8 and is oppositely arranged.Pass through the first fluid path
It connects mouth 7 and injects fuel or oxidant into first receiving space 3, mouth 8 is connect into the second accommodation space 5 by the second fluid path and is injected
Fuel or oxidant.It is empty with gas compression is entered when connecing mouth 9 by gas circuit and being passed through compressed gas to gas compression space 6
Between 6 gas pressure increase, primary diaphragm 2 and secondary diaphragm 4 are gradually compressed up to deformation, wherein in Fig. 1 shown in arrow
Direction is primary diaphragm 2 and the deformation direction that 4 compressed gas of secondary diaphragm squeezes.Primary diaphragm 2 squeezes first receiving space
3, secondary diaphragm 4 squeezes the second accommodation space 5, so that the fuel or oxidant that are placed on first receiving space 3 are by the first fluid path
The discharge of mouth 7 is connect, the fuel or oxidant being placed in the second accommodation space 5 connect mouth 8 by the second fluid path and is discharged, when 2 He of primary diaphragm
Secondary diaphragm 4 close to tank shell 1 inner wall when, complete the discharge of propellant.When needs are to the aerospace propellant receptacle
Case is secondary to be opened in use, gas circuit is connect mouth 9, makes to restore in gas compression space 6 to normal atmospheric pressure, thus primary diaphragm
2 and secondary diaphragm 4 again deformation and restore be in original state.
As one embodiment of the utility model, tank shell 1 is in chondritic.Certainly, the shape of tank shell 1 is also
Other shapes can be set into.
As one embodiment of the utility model, primary diaphragm 2 and secondary diaphragm 4 are made of polytetrafluoroethylene (PTFE).
In the present embodiment, using the mechanical property that polytetrafluoroethylene (PTFE) material is excellent, primary diaphragm 2 and secondary diaphragm 4 are becoming
It can restore after shape to initial state, consequently facilitating the recycling of the aerospace propellant tank.By by first
Diaphragm 2 and secondary diaphragm 4 are arranged to polytetrafluoroethylene material, efficiently solve existing aerospace and are utilized with propellant tank
It is difficult to restore to the original state the problem of cannot reusing after metallic membrane deformation, and due to metallic membrane heavier mass, so that
Aerospace is larger with propellant tank total quality, and the primary diaphragm 2 and secondary diaphragm 4 of the utility model are due to using poly- four
Vinyl fluoride is made, and substantially reduces the quality of diaphragm, and then reduces the total quality of aerospace propellant tank.
Referring to figure 2., Fig. 2 is that the structure of primary diaphragm in aerospace propellant tank provided by the utility model is shown
It is intended to.As one embodiment of the utility model, primary diaphragm 2 include in hemisphere face structure primary diaphragm main body 21 and
It is connected to the first connecting portion 22 of 21 side of primary diaphragm main body, the inner wall sealed connection of first connecting portion 22 and tank shell 1.
Wherein, primary diaphragm 2 and secondary diaphragm 4 and the connection type of the inner wall of tank shell 1 are unlimited.Preferably, first connecting portion 22
It is connect with the inner wall gluing of tank shell 1, sealing effect is good.
Referring to figure 3., Fig. 3 is that the structure of secondary diaphragm in aerospace propellant tank provided by the utility model is shown
It is intended to.As one embodiment of the utility model, secondary diaphragm 4 include in hemisphere face structure secondary diaphragm main body 41 and
It is connected to the second connecting portion 42 of 41 side of secondary diaphragm main body, the inner wall sealed connection of second connecting portion 42 and tank shell 1.
Preferably, second connecting portion 42 is connect with the inner wall gluing of tank shell 1.
As one embodiment of the utility model, the thickness of first connecting portion 22 is less than the thickness of primary diaphragm main body 21
Degree, the thickness of second connecting portion 42 are less than the thickness of secondary diaphragm main body 41.Since the thickness of first connecting portion 22 is less than first
The thickness of diaphragm main body 21 makes first connecting portion 22 be easy to produce deformation and the compression of primary diaphragm main body 21 first is driven to accommodate sky
Between 3.The thickness of second connecting portion 42 is less than the thickness of secondary diaphragm main body 41, so that second connecting portion 42 is easy to produce deformation and drives
Dynamic secondary diaphragm main body 41 compresses the second accommodation space 5.
As one embodiment of the utility model, the thickness T1 of primary diaphragm main body 21 is from its edge heart direction thereto
It is gradually increased；The thickness T1 of secondary diaphragm main body 41 is gradually increased in heart direction thereto from its edge, is convenient for primary diaphragm main body
21 and secondary diaphragm main body 41 overturning deformation.
As a preferred embodiment of the utility model, primary diaphragm 2 and secondary diaphragm 4 with a thickness of 0.1~3mm,
The turnable deformation for guaranteeing primary diaphragm 2 and secondary diaphragm 4 facilitates primary diaphragm 2 and secondary diaphragm 4 to compress first receiving space
3 and second accommodation space 5.
As one embodiment of the utility model, secondary diaphragm main body 41 is contained in primary diaphragm main body 21 and can be with
Primary diaphragm main body 21 is bonded.When first receiving space 3 and the second accommodation space 5 fill it up with propellant, secondary diaphragm 4 and first
Diaphragm 2 is bonded, and so that secondary diaphragm 4 and primary diaphragm 2 is not subject to the saturated vapour pressure of propellant, is effectively increased secondary diaphragm 4
With the service life of primary diaphragm 2.
Aerospace provided by the utility model with propellant tank by setting two diaphragms, two diaphragms respectively with storage
Tank shell forms first receiving space and the second accommodation space for storing fuel or oxidant, so that fuel and oxidant can
It is stored in the same tank shell simultaneously, it, can be effective without two propellant tank difference storing fuels and oxidant
The occupancy volume for reducing propellant tank reduces manufacturing cost to reduce the overall volume and quality of spacecraft；And fuel
It is infused in the same propellant tank, is easy to use simultaneously with oxidant.
The above is only the preferred embodiments of the present utility model only, is not intended to limit the utility model, all practical at this
Made any modifications, equivalent replacements, and improvements etc., should be included in the guarantor of the utility model within novel spirit and principle
Within the scope of shield.
Claims (9)
1. a kind of aerospace propellant tank characterized by comprising
Tank shell；
Primary diaphragm, the primary diaphragm are set in the tank shell and form first with the inner wall of the tank shell and accommodate
Space；
Secondary diaphragm, the secondary diaphragm are set in the tank shell and form second with the inner wall of the tank shell and accommodate
Space, the secondary diaphragm and the primary diaphragm form closed gas compression space；
The first fluid path being connected to the first receiving space connects mouth；
The second fluid path being connected to second accommodation space connects mouth；And
The gas circuit being connected to the gas compression space connects mouth, and the gas circuit connects mouth and is passed through compressed gas to the gas compression space
When body, the primary diaphragm and the secondary diaphragm can deformation occurs and compresses first receiving space and described second respectively accommodates
Space.
2. aerospace propellant tank according to claim 1, which is characterized in that the primary diaphragm and described
Two diaphragms are made of polytetrafluoroethylene (PTFE).
3. aerospace propellant tank according to claim 1, which is characterized in that the primary diaphragm includes in half
The primary diaphragm main body of spherical structure and the first connecting portion for being connected to primary diaphragm main body side, first connection
The inner wall of portion and the tank shell is tightly connected.
4. aerospace propellant tank according to claim 3, which is characterized in that the secondary diaphragm includes in half
The secondary diaphragm main body of spherical structure and the second connecting portion for being connected to secondary diaphragm main body side, second connection
The inner wall of portion and the tank shell is tightly connected.
5. aerospace propellant tank according to claim 4, which is characterized in that the thickness of the first connecting portion
Less than the thickness of the primary diaphragm main body, the thickness of the second connecting portion is less than the thickness of the secondary diaphragm main body.
6. aerospace propellant tank according to claim 5, which is characterized in that the thickness of the primary diaphragm main body
Degree is gradually increased in heart direction thereto from its edge；Heart direction is gradually thereto from its edge for the thickness of the secondary diaphragm main body
Increase.
7. aerospace propellant tank according to claim 4, which is characterized in that the secondary diaphragm main body receiving
In can be bonded in the primary diaphragm main body and with the primary diaphragm main body.
8. aerospace propellant tank according to claim 1, which is characterized in that the primary diaphragm and described
Two diaphragms with a thickness of 0.1~3mm.
9. aerospace propellant tank according to claim 1, which is characterized in that the tank shell is in spherical knot
Structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821452156.3U CN209008892U (en) | 2018-09-06 | 2018-09-06 | A kind of aerospace propellant tank |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821452156.3U CN209008892U (en) | 2018-09-06 | 2018-09-06 | A kind of aerospace propellant tank |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209008892U true CN209008892U (en) | 2019-06-21 |
Family
ID=66832385
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821452156.3U Active CN209008892U (en) | 2018-09-06 | 2018-09-06 | A kind of aerospace propellant tank |
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Cited By (2)
| 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 |
| WO2022098483A3 (en) * | 2020-10-16 | 2022-07-21 | Swarm Technologies, Inc. | Propulsion system for satellites |
-
2018
- 2018-09-06 CN CN201821452156.3U patent/CN209008892U/en active Active
Cited By (2)
| 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 |
| WO2022098483A3 (en) * | 2020-10-16 | 2022-07-21 | Swarm Technologies, Inc. | Propulsion system for satellites |
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