CN109763913A - Bipropellant propulsion developing agent storage and supply system and space launch vehicle - Google Patents
Bipropellant propulsion developing agent storage and supply system and space launch vehicle Download PDFInfo
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- CN109763913A CN109763913A CN201910042393.5A CN201910042393A CN109763913A CN 109763913 A CN109763913 A CN 109763913A CN 201910042393 A CN201910042393 A CN 201910042393A CN 109763913 A CN109763913 A CN 109763913A
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- fuel
- oxidant
- supply system
- developing agent
- tank shell
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- 238000003860 storage Methods 0.000 title claims abstract description 71
- 239000007800 oxidant agent Substances 0.000 claims abstract description 164
- 239000000446 fuel Substances 0.000 claims abstract description 161
- 230000001590 oxidative effect Effects 0.000 claims abstract description 128
- 239000003795 chemical substances by application Substances 0.000 claims abstract description 71
- 230000009471 action Effects 0.000 claims abstract description 6
- 239000007789 gas Substances 0.000 claims description 44
- 239000002775 capsule Substances 0.000 claims description 43
- 238000005192 partition Methods 0.000 claims description 16
- 230000003647 oxidation Effects 0.000 claims description 6
- 238000007254 oxidation reaction Methods 0.000 claims description 6
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 5
- 239000001301 oxygen Substances 0.000 claims description 5
- 229910052760 oxygen Inorganic materials 0.000 claims description 5
- 230000014759 maintenance of location Effects 0.000 claims description 3
- 238000010276 construction Methods 0.000 abstract description 4
- 239000002828 fuel tank Substances 0.000 description 11
- 239000003380 propellant Substances 0.000 description 9
- 238000010586 diagram Methods 0.000 description 8
- 239000012530 fluid Substances 0.000 description 8
- 239000000463 material Substances 0.000 description 7
- 238000003466 welding Methods 0.000 description 7
- 239000000306 component Substances 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 5
- 238000002485 combustion reaction Methods 0.000 description 4
- 239000007788 liquid Substances 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 230000008859 change Effects 0.000 description 3
- 239000007769 metal material Substances 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 239000000470 constituent Substances 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
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- Fuel Cell (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
This application provides a kind of bipropellant propulsion developing agent storage and supply system and space launch vehicle, bipropellant propulsion developing agent storage and supply system include: tank shell, fuel assembly, oxidizer module and pressurizing pack；Fuel assembly and oxidizer module are oppositely arranged in tank shell, and air cavity space is formed between fuel assembly and oxidizer module；External inflation equipment is filled with pressurization working medium to air cavity space by pressurizing pack；Under the squeezing action of pressurization working medium, fuel assembly is used for thruster module discharge fuel, and oxidizer module is used for thruster module exhaust oxidant.The application can significantly reduce the envelope size and construction weight of system, the integrated level of raising system, it helps to realize bipropellant propulsion developing agent storage and supply system is integrated, target of miniaturization and lightweight, the performance of aerospace craft rail control engine system can be significantly improved.
Description
Technical field
The application belongs to rail control technical field of engines, and in particular to a kind of bipropellant propulsion developing agent storage and supply system
And space launch vehicle.
Background technique
Rail control engine system is the core component of aerospace craft, and propellant storage and supply system occupy appearance
Precise tracking system overwhelming majority space and weight are the important determinants for influencing its performance.Existing bipropellant
Storage and supply system mainly by fuel tank, oxidant tank, high pressure gas cylinder, gas circuit isolating valve, pressure regulator, fluid path every
It is formed from valve, gas-liquid road pipeline and mounting structure etc., wherein under lesser spatial dimension and lighter architecture quality, as far as possible
More loading propellants simultaneously realizes that the Propellant Supply of not gas enclosure is the key technology of propellant storage and supply system.
As illustrated in fig. 1 and 2, existing bipropellant propulsion developing agent storage and supply system include: two kinds of cloth of series and parallel type
Office's mode.Present inventor has found in R&D process: that there are space utilization rates is low for above two conventional layout style, packet
The problems such as network size is bigger than normal, mounting structure is complicated and construction weight is bigger than normal.With the development of space technology with the liter of application demand
Grade, spacecraft miniaturization, integrated, light-weighted demand is increasingly prominent, and bipropellant propulsion developing agent storage and supply system is normal
Rule layout type has been unable to satisfy current application demand, limits the application of rail control engine.
Summary of the invention
To be overcome the problems, such as present in the relevant technologies at least to a certain extent, this application provides a kind of bipropellant propulsions
Developing agent storage and supply system and space launch vehicle.
According to the embodiment of the present application in a first aspect, this application provides a kind of bipropellant propulsion developing agent storages and supply system
System comprising:
Tank shell, fuel assembly, oxidizer module and pressurizing pack；
The fuel assembly and oxidizer module are oppositely arranged in the tank shell, and the fuel assembly and oxidation
Air cavity space is formed between agent component；
External inflation equipment is used to be filled with pressurization working medium to the air cavity space by the pressurizing pack；
Under the squeezing action of the pressurization working medium, the fuel assembly is used for thruster module discharge fuel, described
Oxidizer module is used for thruster module exhaust oxidant.
Bipropellant propulsion developing agent storage and supply system, the fuel assembly as described above include fuel capsule stack and combustion
Expect end socket；The oxidizer module includes oxidant capsule stack and oxidant end socket；
The fuel capsule stack and oxidant capsule stack are oppositely arranged in the tank shell；The air cavity space
It is formed between the fuel capsule stack and oxidant capsule stack；
Side of the fuel capsule stack far from the oxidant capsule stack, the combustion is arranged in the fuel end socket
It is provided with fuel road isolating valve on material end socket and adds valve, the fuel assembly passes through fuel road isolating valve and fuel conduit and institute
State the connection of thruster module；
Side of the oxidant capsule stack far from the fuel capsule stack is arranged in the oxidant end socket, described
It is provided with oxidant road isolating valve on oxidant end socket and adds valve, the oxidizer module passes through oxidant road isolating valve and oxygen
Agent pipeline is connect with the thruster module.
Bipropellant propulsion developing agent storage and supply system, the fuel capsule stack as described above include fuel bellows and combustion
Expect top cover；The oxidant capsule stack includes oxidant bellows and oxidant top cover；
In the tank shell, the fuel bellows is arranged along the length direction of the tank shell in the tank shell
The other side of the tank shell is arranged in along the length direction of the tank shell for the side of body, the oxidant bellows；
The fuel bellows is fixedly connected close to the side of the oxidant bellows with the fuel top cover, opposite side with
The fuel end socket is fixedly connected；
The oxidant bellows is fixedly connected close to the side of the fuel bellows with the oxidant top cover, opposite side
It is fixedly connected with the oxidant end socket.
Bipropellant propulsion developing agent storage as described above and supply system, the fuel top cover is to the fuel bellows inner-concave
It is recessed inside into, the oxidant top cover to the oxidant bellows；Air cavity between the fuel top cover and oxidant top cover
Space is an elliposoidal or diameter of Spherical Volume.
Bipropellant propulsion developing agent storage as described above and supply system, the shape of the fuel end socket and the shape of fuel top cover
Shape matching setting, outer projection from the fuel end socket to the fuel bellows, the direction of the fuel end socket protrusion with it is described
The recessed direction of fuel top cover is consistent；
The shape of the oxidant end socket matches setting with the shape of oxidant top cover, and the oxidant end socket is to the oxygen
The direction of the outer projection of agent bellows, the oxidant end socket protrusion is consistent with the direction that the oxidant top cover is recessed.
Bipropellant propulsion developing agent storage as described above and supply system, be located at the fuel assembly and oxidizer module it
Between, charge valve is provided on the tank shell, the pressurizing pack is connect with charge valve.
Bipropellant propulsion developing agent storage as described above and supply system, the pressurizing pack include high pressure gas cylinder, gas circuit every
From valve and air-flow distributor；The entrance of the high pressure gas cylinder is connect with the charge valve, and outlet passes through the gas circuit isolating valve
It is connect with air-flow distributor.
Bipropellant propulsion developing agent storage and supply system, the pressurizing pack as described above further include pressure regulator, institute
It states pressure regulator to be arranged between gas circuit isolating valve and air-flow distributor, and connects with the gas circuit isolating valve and air-flow distributor
It connects.
Bipropellant propulsion developing agent storage as described above and supply system are additionally provided with safety valve on the tank shell.
Bipropellant propulsion developing agent storage as described above and supply system, are located in the tank shell, in the fuel stack
Subdivision partition plate is set at the air cavity space formed between part and oxidizer module.
Further, the subdivision partition plate is arranged on the central axes of the width direction of the tank shell, the subdivision
The both ends of partition are fixedly connected with the tank shell.
According to the second aspect of the embodiment of the present application, present invention also provides a kind of space launch vehicles comprising above-mentioned
Bipropellant propulsion developing agent storage and supply system described in one.
According to the above-mentioned specific embodiment of the application it is found that at least having the advantages that the application double elements pushes away
Into developing agent storage and supply system by the way that fuel assembly and oxidizer module is oppositely arranged in same tank shell, can save
One fuel end socket and an oxidant end socket save the mounting structure between fuel assembly and oxidizer module, can be significant
Reduce the envelope size and construction weight of bipropellant propulsion developing agent storage and supply system.In addition, by the way that pressurizing pack setting is existed
In the air cavity space formed between fuel assembly and oxidizer module, bipropellant propulsion developing agent storage and supply can be further increased
The integrated level of system lowers its envelope size.
It is to be understood that above-mentioned general description and following specific embodiments are merely illustrative and illustrative, not
The range to be advocated of the application can be limited.
Detailed description of the invention
Following appended attached drawing is a part of the description of the present application, appended attached it illustrates embodiments herein
The principle for describing to be used to illustrate the application together of figure and specification.
Fig. 1 is the structural schematic diagram of existing tandem bipropellant propulsion developing agent storage and supply system.
Fig. 2 is the structural schematic diagram of existing parallel bipropellant propulsion developing agent storage and supply system.
Fig. 3 is a kind of bipropellant propulsion developing agent storage that the embodiment of the present application one provides and supply system and thruster module
Attachment structure schematic diagram.
Fig. 4 is a kind of bipropellant propulsion developing agent storage that the embodiment of the present application two provides and supply system and thruster module
Attachment structure schematic diagram.
Description of symbols:
1, tank shell；11, charge valve；12, safety valve；13, subdivision partition plate；
2, fuel assembly；21, fuel capsule stack；211, fuel bellows；212, fuel top cover；22, fuel end socket；23,
Fuel road isolating valve and plus valve；24, fuel conduit；
3, oxidizer module；31, oxidant capsule stack；311, oxidant bellows；312, oxidant top cover；32, it aoxidizes
Agent end socket；33, oxidant road isolating valve and plus valve；34, oxidant pipeline；
4, pressurizing pack；41, high pressure gas cylinder；42, gas circuit isolating valve；43, air-flow distributor；44, pressure regulator；
5, thruster module；
10, fuel tank；20, oxidant tank；30, fluid path isolating valve.
Specific embodiment
For the purposes, technical schemes and advantages of the embodiment of the present application are more clearly understood, below will with attached drawing and in detail
Narration clearly illustrates the spirit of content disclosed herein, and any skilled artisan is understanding teachings herein
After embodiment, when the technology that can be taught by teachings herein, it is changed and modifies, without departing from the essence of teachings herein
Mind and range.
Illustrative embodiments of the present application and the description thereof are used to explain the present application, but is not intended as the restriction to the application.
In addition, in the drawings and embodiments the use of element/component of same or like label is for representing same or like portion
Point.
About " first " used herein, " second " ... etc., not especially censure the meaning of order or cis-position,
It is non-to limit the application, only for distinguish with same technique term description element or operation.
About direction term used herein, such as: upper and lower, left and right, front or rear etc. are only the sides with reference to attached drawing
To.Therefore, the direction term used is intended to be illustrative and not intended to limit this creation.
It is open term, i.e., about "comprising" used herein, " comprising ", " having ", " containing " etc.
Mean including but not limited to.
About it is used herein " and/or ", including any of the things or all combination.
It include " two " and " two or more " about " multiple " herein；It include " two groups " about " multiple groups " herein
And " more than two ".
About term used herein " substantially ", " about " etc., to modify it is any can with the quantity of slight change or
Error, but this slight variations or error can't change its essence.In general, slight change or mistake that such term is modified
The range of difference can be 20% in some embodiments, in some embodiments can be 10%, in some embodiments can for 5% or
It is other numerical value.It will be understood by those skilled in the art that the aforementioned numerical value referred to can be adjusted according to actual demand, not as
Limit.
It is certain to describe the word of the application by lower or discuss in the other places of this specification, to provide art technology
Personnel's guidance additional in relation to the description of the present application.
Fig. 1 is the structural schematic diagram of existing tandem bipropellant propulsion developing agent storage and supply system.As shown in Figure 1, existing
Tandem bipropellant propulsion developing agent storage and supply system include fuel tank 10, oxidant tank 20, high pressure gas cylinder 41, gas circuit every
From valve 42, pressure regulator 44, fluid path isolating valve 30 and thruster module 5.Fuel tank 10 and the series connection of oxidant tank 20 are set
It sets in systems.High pressure gas cylinder 41 is store with fuel tank 10 and oxidant respectively by gas circuit isolating valve 42 and pressure regulator 44
The entrance of case 20 connects, and the exit of fuel tank 10 and oxidant tank 20 is provided with fluid path isolating valve 30, two fluid path
Isolating valve 30 is connect by pipeline with thruster module 5.
Fig. 2 is the structural schematic diagram of existing parallel bipropellant propulsion developing agent storage and supply system.As shown in Fig. 2, existing
Parallel bipropellant propulsion developing agent storage and supply system include fuel tank 10, oxidant tank 20, high pressure gas cylinder 41, gas circuit every
From valve 42, pressure regulator 44, fluid path isolating valve 30 and thruster module 5.Fuel tank 10 and 20 parallel connection of oxidant tank are set
It sets in systems.High pressure gas cylinder 41 is store with fuel tank 10 and oxidant respectively by gas circuit isolating valve 42 and pressure regulator 44
The entrance of case 20 connects, and the exit of fuel tank 10 and oxidant tank 20 is provided with fluid path isolating valve 30, two fluid path
Isolating valve 30 is connect by pipeline with thruster module 5.
Bipropellant propulsion developing agent storage provided by the present application and supply system can effectively solve the problem that existing conventional layout style
Envelope size present in bipropellant propulsion developing agent storage and supply system is big, space utilization rate is low and architecture quality is asked again etc.
Topic.
The application bipropellant propulsion developing agent storage and supply system include tank shell, fuel assembly, oxidizer module and increasing
Press component.
Fuel assembly and oxidizer module are oppositely arranged in tank shell, and shape between fuel assembly and oxidizer module
At air cavity space.
Between fuel assembly and oxidizer module, charge valve is provided on tank shell.Pressurizing pack and inflation
Valve connection.External inflation equipment can be filled with pressurization working medium by charge valve into pressurizing pack.Pressurizing pack is used for air cavity
Space is filled with pressurization working medium.
Under the squeezing action of pressurization working medium, fuel assembly is used for thruster module discharge fuel, and oxidizer module is used
In to thruster module exhaust oxidant.
The application bipropellant propulsion developing agent storage and supply system first fill combustion before or before delivering into fuel assembly
Material, oxidant is filled into oxidizer module, is sealed and stored later.Fuel assembly and oxidizer module, which respectively correspond, plays sealing
The effect of fuel and oxidant is isolated.
It is filled with pressurization working medium into pressurizing pack, is sealed and stored later.Wherein, pressurization working medium is specially pressurization gas work
Matter.
When the application bipropellant propulsion developing agent storage and supply system work, pressurizing pack is to fuel assembly and oxidizer module
Between be filled with pressurization working medium in the air cavity space that is formed.In this case, fuel assembly and oxidizer module can make fuel and
Both propellants of oxidant are isolated with pressurization gas working medium, to guarantee that propellant is liquid without entrained gas.
Under the squeezing action of pressurization gas working medium, fuel assembly to thruster module discharge fuel, oxidizer module to
Thruster module exhaust oxidant.
The application bipropellant propulsion developing agent storage and supply system can effectively solve the problem that existing bipropellant propulsion developing agent storage and confession
The problem that envelope size existing for system convention layout type is big, space utilization rate is low, architecture quality is heavy is answered, is helped to realize double
Constituent element propellant storage and supply system is integrated, target of miniaturization and lightweight, can significantly improve aerospace craft appearance
The performance of precise tracking system.
Embodiment one
Fig. 3 is a kind of bipropellant propulsion developing agent storage that the embodiment of the present application one provides and supply system and thruster module
Attachment structure schematic diagram.As shown in figure 3, bipropellant propulsion developing agent storage and supply system include tank shell 1, fuel assembly 2, oxygen
Agent component 3 and pressurizing pack 4.
Wherein, fuel assembly 2 includes fuel capsule stack 21 and fuel end socket 22.Oxidizer module 3 includes oxidant film
Case assembly 31 and oxidant end socket 32.
Fuel capsule stack 21 and oxidant capsule stack 31 are oppositely arranged in tank shell 1.Fuel capsule stack 21
Air cavity space is formed between oxidant capsule stack 31.
Side of the fuel capsule stack 21 far from oxidant capsule stack 31, fuel capsule stack is arranged in fuel end socket 22
21 form a closing cavity with fuel end socket 22, which is fuel cavity.Fuel road is provided on fuel end socket 22
Isolating valve and plus valve 23.Fuel cavity is connect by fuel road isolating valve and fuel conduit 24 with thruster module 5；By adding
Valve fills into fuel cavity or releases fuel liquid.
Side of the oxidant capsule stack 31 far from fuel capsule stack 21, oxidant bellows is arranged in oxidant end socket 32
Component 31 and oxidant end socket 32 form another closing cavity, which is oxidant cavity.On oxidant end socket 32
It is provided with oxidant road isolating valve and adds valve 33.Oxidant cavity passes through oxidant road isolating valve and oxidant pipeline 34 and pushes away
Power device module 5 connects.By adding valve that oxidant liquid is filled or released into oxidant cavity.
Specifically, tank shell 1, fuel end socket 22 and oxidant end socket 32 are all made of metal material and are made.Tank shell 1
Material it is compatible with the fuel of storage or oxidant level-one.The material of fuel end socket 22 is compatible with the fuel level-one of storage.Oxidation
The material of agent end socket 32 is compatible with the oxidant level-one of storage.
It is attached between tank shell 1 and fuel end socket 22 using welding or flange connection.Tank shell 1 and oxygen
It is attached between agent end socket 32 using welding or flange connection.
Fuel road isolating valve and add valve 23 be fixed on fuel end socket 22 by welding manner.The isolation of oxidant road
Valve and add valve 33 be fixed on oxidant end socket 32 by welding manner.
Further, fuel capsule stack 21 includes fuel bellows 211 and fuel top cover 212.Oxidant capsule stack 31
Including oxidant bellows 311 and oxidant top cover 312.
In tank shell 1, the side of tank shell 1 is arranged in along the length direction of tank shell 1 for fuel bellows 211,
The other side of tank shell 1 is arranged in along the length direction of tank shell 1 for oxidant bellows 311.Fuel bellows 211 is close to oxidation
The side of agent bellows 311 is fixedly connected with fuel top cover 212, and opposite side is fixedly connected with fuel end socket 22.Oxidant bellows
311 are fixedly connected close to the side of fuel bellows 211 with oxidant top cover 312, opposite side and the fixed company of oxidant end socket 32
It connects.
Specifically, fuel bellows 211 and oxidant bellows 311 are all made of metal material and are made.The material of fuel bellows 211
It is compatible with the fuel level-one of storage.The material of oxidant bellows 311 is compatible with the oxidant level-one of storage.
Specifically, it can be attached using welding manner between fuel bellows 211 and fuel top cover 212.Oxidant film
It can be attached using welding manner between box 311 and oxidant top cover 312.
Preferably, fuel top cover 212 is recessed to inside fuel bellows 211, and oxidant top cover 312 is to oxidant bellows 311
Inside is recessed.Air cavity space between fuel top cover 212 and oxidant top cover 312 is specially an elliposoidal or diameter of Spherical Volume.
Pressurizing pack 4 can be arranged in the elliposoidal or diameter of Spherical Volume, further increase the integrated level of system, reduce
The envelope size of system.
In addition, the shape of fuel end socket 22 matches setting with the shape of fuel top cover 212, fuel end socket 22 is to fuel bellows
The direction of 211 outer projections, 22 protrusion of fuel end socket is consistent with the direction that fuel top cover 212 is recessed.
The shape of oxidant end socket 32 matches setting with the shape of oxidant top cover 312, and oxidant end socket 32 is to oxidant
The direction of 311 outer projection of bellows, 32 protrusion of oxidant end socket is consistent with the direction that oxidant top cover 312 is recessed.
Pressurizing pack 4 includes high pressure gas cylinder 41, gas circuit isolating valve 42 and air-flow distributor 43.The entrance of high pressure gas cylinder 41 with
Charge valve 11 connects, and outlet is connect by gas circuit isolating valve 42 with air-flow distributor 43.Specifically, pressurizing pack 4 can lead to
Mounting bracket is crossed to be fixedly connected on inside or outside tank shell 1.
Between fuel assembly 2 and oxidizer module 3, charge valve 11 is provided on tank shell 1.Pressurizing pack 4
It is connect with charge valve 11.External inflation equipment can be filled with pressurization working medium by charge valve 11 into pressurizing pack 4.Specifically,
External inflation equipment is filled with pressurization gas working medium into high pressure gas cylinder 41 by charge valve 11.
When the application bipropellant propulsion developing agent storage and supply system work, gas circuit isolating valve 42 is beaten according to external control instruction
It opens, the high pressure gas stored in high pressure gas cylinder 41 uniformly sprays into fuel assembly 2 by gas circuit isolating valve 42 and air-flow distributor 43
In the air cavity space formed between oxidizer module 3.
In discharge opeing process, fuel capsule stack 21 and oxidant capsule stack 31 are gradually moved to the two sides of tank shell 1,
Until propellant drains or the control valve of downstream thruster module 5 is closed；When propellant drains, fuel top cover 212 and fuel are sealed
First 22 fitting, oxidant top cover 312 are bonded with oxidant end socket 32.
In addition, pressurizing pack 4 further includes pressure regulator 44, pressure regulator 44 is arranged in gas circuit isolating valve 42 and air-flow
Between distributor 43, and it is connect with gas circuit isolating valve 42 and air-flow distributor 43.Pressure regulator 44 is used for high pressure gas cylinder 41
The high pressure gas of output is adjusted to the gas of system demand pressure.
When being not provided with pressure regulator 44, the application bipropellant propulsion developing agent storage and supply system work are falling pressure work
Mode.
It in the present embodiment, is the safety for guaranteeing bipropellant propulsion developing agent storage and supply system work, on tank shell 1
It is additionally provided with safety valve 12.
Specifically, charge valve 11 and safety valve 12 are fixed on tank shell 1 by welding manner.
Compared with traditional bipropellant propulsion developing agent storage and the conventional layout style of supply system, the application bipropellant
Storage and supply system share the structure type of a tank shell 1 by fuel assembly 2 and oxidizer module 3, can save
One fuel end socket 22 and an oxidant end socket 32 save the mounting structure between fuel tank and oxidant tank, can
Significantly reduce the envelope size and construction weight of bipropellant propulsion developing agent storage and supply system.In addition, by the way that pressurizing pack 4 is set
It sets in air cavity space, the integrated level of bipropellant propulsion developing agent storage and supply system can be further increased, lower its envelope ruler
It is very little.
Embodiment two
Fig. 4 is a kind of bipropellant propulsion developing agent storage that the embodiment of the present application two provides and supply system and thruster module
Attachment structure schematic diagram.The basic structure of bipropellant propulsion developing agent storage provided in this embodiment and supply system and one phase of embodiment
Together, it no longer elaborates herein.The difference is that: subdivision partition plate 13 is added in tank shell 1.
As shown in figure 4, being located in tank shell 1, the air cavity space formed between fuel assembly 2 and oxidizer module 3
Place's setting subdivision partition plate 13.Subdivision partition plate 13 is vertical with the axis of 1 length direction of tank shell.Subdivision partition plate 13 is as to fuel
Capsule stack 21 and oxidant capsule stack 31 play the redundancy structure of sealing and buffer action, in fuel capsule stack 21 and oxidation
Agent capsule stack 31 breaks down in the case where leakage, and fuel and oxidant are isolated, and both makes will not to occur blending, anti-
It answers, to improve the intrinsic safety and reliability of system.
Correspondingly, it there are two the settings of air-flow distributor 43, respectively corresponds and is arranged in subdivision partition plate 13 and 212 shape of fuel top cover
At the air cavity space that is formed of air cavity space and subdivision partition plate 13 and oxidant top cover 312 in.Safety valve 12 is also equipped with two
It is a, it is separately positioned on the tank shell 1 of 13 two sides of subdivision partition plate.
Preferably, subdivision partition plate 13 is arranged on the central axes of 1 width direction of tank shell, and the both ends of subdivision partition plate 13 are equal
It is fixedly connected with tank shell 1, subdivision partition plate 13 divides air cavity space equally.
Embodiment three
The embodiment of the present application three additionally provides a kind of space launch vehicle comprising any in embodiment one and embodiment two
Bipropellant propulsion developing agent storage and supply system.
The foregoing is merely the schematical specific embodiments of the application, before not departing from the conceptions and principles of the application
It puts, the equivalent changes and modifications that any those skilled in the art is made, should belong to the range of the application protection.
Claims (12)
1. a kind of bipropellant propulsion developing agent storage and supply system characterized by comprising
Tank shell, fuel assembly, oxidizer module and pressurizing pack；
The fuel assembly and oxidizer module are oppositely arranged in the tank shell, and the fuel assembly and oxidant group
Air cavity space is formed between part；
External inflation equipment is used to be filled with pressurization working medium to the air cavity space by the pressurizing pack；
Under the squeezing action of the pressurization working medium, the fuel assembly is used for thruster module discharge fuel, the oxidation
Agent component is used for thruster module exhaust oxidant.
2. bipropellant propulsion developing agent storage according to claim 1 and supply system, which is characterized in that the fuel assembly packet
Include fuel capsule stack and fuel end socket；The oxidizer module includes oxidant capsule stack and oxidant end socket；
The fuel capsule stack and oxidant capsule stack are oppositely arranged in the tank shell；The air cavity space is formed
Between the fuel capsule stack and oxidant capsule stack；
Side of the fuel capsule stack far from the oxidant capsule stack, the fuel envelope is arranged in the fuel end socket
It is provided with fuel road isolating valve on head and adds valve, the fuel assembly is pushed away by fuel road isolating valve and fuel conduit with described
The connection of power device module；
Side of the oxidant capsule stack far from the fuel capsule stack, the oxidation is arranged in the oxidant end socket
It is provided with oxidant road isolating valve on agent end socket and adds valve, the oxidizer module passes through oxidant road isolating valve and oxidant
Pipeline is connect with the thruster module.
3. bipropellant propulsion developing agent storage according to claim 2 and supply system, which is characterized in that the fuel bellows group
Part includes fuel bellows and fuel top cover；The oxidant capsule stack includes oxidant bellows and oxidant top cover；
In the tank shell, the tank shell is arranged in along the length direction of the tank shell in the fuel bellows
The other side of the tank shell is arranged in along the length direction of the tank shell for side, the oxidant bellows；
The fuel bellows is fixedly connected close to the side of the oxidant bellows with the fuel top cover, opposite side with it is described
Fuel end socket is fixedly connected；
The oxidant bellows is fixedly connected close to the side of the fuel bellows with the oxidant top cover, opposite side and institute
Oxidant end socket is stated to be fixedly connected.
4. bipropellant propulsion developing agent storage according to claim 3 and supply system, which is characterized in that the fuel top cover to
The fuel bellows inner-concave into, the oxidant top cover to the oxidant bellows inside be recessed；The fuel top cover and oxygen
Air cavity space between agent top cover is an elliposoidal or diameter of Spherical Volume.
5. bipropellant propulsion developing agent storage according to claim 4 and supply system, which is characterized in that the fuel end socket
Shape matches setting, outer projection of the fuel end socket to the fuel bellows, the fuel envelope with the shape of fuel top cover
The direction of head protrusion is consistent with the direction that the fuel top cover is recessed；
The shape of the oxidant end socket matches setting with the shape of oxidant top cover, and the oxidant end socket is to the oxidant
The direction of the outer projection of bellows, the oxidant end socket protrusion is consistent with the direction that the oxidant top cover is recessed.
6. bipropellant propulsion developing agent storage according to claim 1 and supply system, which is characterized in that be located at the fuel stack
Between part and oxidizer module, charge valve is provided on the tank shell, the pressurizing pack is connect with charge valve.
7. bipropellant propulsion developing agent storage according to claim 6 and supply system, which is characterized in that the pressurizing pack packet
Include high pressure gas cylinder, gas circuit isolating valve and air-flow distributor；The entrance of the high pressure gas cylinder is connect with the charge valve, and outlet is logical
The gas circuit isolating valve is crossed to connect with air-flow distributor.
8. bipropellant propulsion developing agent storage according to claim 7 and supply system, which is characterized in that the pressurizing pack is also
Including pressure regulator, the pressure regulator is arranged between gas circuit isolating valve and air-flow distributor, and with the gas circuit every
It is connected from valve with air-flow distributor.
9. described in any item bipropellant propulsion developing agent storages and supply system according to claim 1~8, which is characterized in that described
Safety valve is additionally provided on tank shell.
10. described in any item bipropellant propulsion developing agent storages and supply system according to claim 1~8, which is characterized in that be located at
In the tank shell, at the air cavity space that is formed between the fuel assembly and oxidizer module setting subdivision every
Plate.
11. bipropellant propulsion developing agent storage according to claim 10 and supply system, which is characterized in that the subdivision partition plate
It is arranged on the central axes of the width direction of the tank shell, the both ends of the subdivision partition plate are fixed with the tank shell
Connection.
12. a kind of space launch vehicle, which is characterized in that including bipropellant as claimed in any one of claims 1 to 11
Storage and supply system.
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| CN111924138A (en) * | 2020-09-21 | 2020-11-13 | 蓝箭航天空间科技股份有限公司 | Special diaphragm box inflation and pressure measurement device for low-temperature aerospace carrier |
| CN112211750A (en) * | 2020-10-19 | 2021-01-12 | 北京天兵科技有限公司 | Rocket engine ignition agent storage and supply device |
| CN114233520A (en) * | 2021-12-10 | 2022-03-25 | 北京航空航天大学 | Electric pump pressurized attitude and orbit control integrated propulsion system and spacecraft |
| CN114607527A (en) * | 2022-03-23 | 2022-06-10 | 北京航天雷特机电工程有限公司 | Temperature control conveying system for propellant of space engine |
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