CN110374762A - A kind of rocket engine fuel system and rocket - Google Patents
A kind of rocket engine fuel system and rocket Download PDFInfo
- Publication number
- CN110374762A CN110374762A CN201910663233.2A CN201910663233A CN110374762A CN 110374762 A CN110374762 A CN 110374762A CN 201910663233 A CN201910663233 A CN 201910663233A CN 110374762 A CN110374762 A CN 110374762A
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- China
- Prior art keywords
- propellant
- propellant tank
- fuel system
- engine fuel
- tank
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/56—Control
- F02K9/58—Propellant feed valves
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/605—Reservoirs
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
Abstract
The technical issues of this application provides a kind of rocket engine fuel system and rockets, are related to rocket engine technical field, solve core grade rocket in the prior art to a certain extent at work, and propellant is supplemented in its tank of no normal direction.Rocket engine fuel system includes: booster rocket engine fuel system and core grade rocket engine fuel system；Booster rocket engine fuel system includes the first propellant tank, core grade rocket engine fuel system includes the second propellant tank, first propellant tank is connected with the second propellant tank, is provided with control valve between the first propellant tank and the second propellant tank.The first propellant tank can convey propellant into the second propellant tank in rocket engine fuel system, prevent the consumption of propellant in core grade rocket engine fuel system from core grade rocket carrying capacity being caused to decline.
Description
Technical field
This application involves rocket engine technical fields, more particularly, to a kind of rocket engine fuel system and rocket.
Background technique
In order to increase the thrust of rocket, booster rocket usually is bundled in core grade rocket surrounding, booster rocket is core grade
Rocket provides thrust.But core grade rocket is after a period of operation, with the consumption of the propellant in its tank, core grade fire
The carrying capacity of arrow itself can be declined.In the prior art, core grade rocket at work, is supplemented in its tank of no normal direction and is promoted
Agent.
Summary of the invention
The application's is designed to provide a kind of rocket engine fuel system, to solve the prior art to a certain extent
Present in core grade rocket at work, in its tank of no normal direction supplement propellant the technical issues of.
Rocket engine fuel system provided by the present application, comprising: booster rocket engine fuel system and core grade fire
Arrow engine fuel system；
The booster rocket engine fuel system includes the first propellant tank, the core grade rocket engine fuel
System includes the second propellant tank, and first propellant tank is connected to second propellant tank, and described first pushes away
Into being provided with control valve between agent tank and second propellant tank, when the control valve is in the open state, described
Propellant in one propellant tank is flowed to second propellant tank direction.
Further, the first communication port is provided on first propellant tank, first communication port is located at described
The bottom section of the side of first propellant tank；
The second communication port is provided on second propellant tank, first propellant tank and described second promote
By pipeline connection between agent tank, one end of the pipeline is connect with first communication port, and the other end and described second connects
Port connection.
Further, the outlet of first propellant tank and the outlet of second propellant tank are provided with anti-
Revolve cross plug.
Further, the anti-rotation cross plug includes rounding stage body and cross partition；
The rounding stage body is set on the cross partition, the center of the rounding stage body and the cross partition
Center be located on the same line；
The cross partition is set to the outlet of first propellant tank or going out for second propellant tank
Mouthful.
Further, flow-disturbing hole is provided on the cross partition, the number in the flow-disturbing hole is multiple.
Further, be disposed between first propellant tank and second propellant tank Venturi tube,
Flowmeter and the first solenoid valve；
The control valve is between the Venturi tube and the flowmeter.
Further, first gas relief valve and first gas safety valve, institute are provided on first propellant tank
It states and is provided with first pressure gauge between the first propellant tank and the first gas safety valve.
Further, the booster rocket engine fuel system further includes the first high pressure gas cylinder, first high pressure
First gas fill valve and the first gas cylinder safely valve, first high pressure gas cylinder and first gas cylinder safely are provided on gas cylinder
Second pressure gauge is provided between valve；
First high pressure gas cylinder is connected to first propellant tank, and first high pressure gas cylinder is pushed away with described first
Into being disposed with second solenoid valve and the first pressure reducer between agent tank.
Further, the booster rocket engine fuel system further includes the first engine and controller, and described
One propellant tank is connect with first engine, and the controller is connect with the control valve, and the control valve is unidirectional
Valve.
Compared with the existing technology, rocket engine fuel system described herein has the advantage that
First in the booster rocket engine fuel system of rocket engine fuel system described herein promotes
Agent tank is connected with the second propellant tank in core grade rocket engine fuel system, and the first propellant tank and second
Control valve is provided between propellant tank, when control valve is in the open state, propellant in the first propellant tank can be with
The second propellant tank is flowed into from the first propellant tank.
When the work of core grade rocket, the first propellant tank can convey propellant into the second propellant tank, prevent
The consumption of propellant causes core grade rocket carrying capacity to decline in core grade rocket engine fuel system.
The another object of the application is to propose a kind of rocket, to solve core existing in the prior art to a certain extent
Grade rocket supplements the technical issues of propellant at work, in its tank of no normal direction.
In order to achieve the above objectives, the technical solution of the application is achieved in that
A kind of rocket is equipped with rocket engine fuel system as described in the above technical scheme in the rocket.
Possessed advantage is identical compared with the existing technology with above-mentioned rocket engine fuel system for the rocket, herein not
It repeats again.
Detailed description of the invention
It, below will be to specific in order to illustrate more clearly of the application specific embodiment or technical solution in the prior art
Embodiment or attached drawing needed to be used in the description of the prior art be briefly described, it should be apparent that, it is described below
Attached drawing is some embodiments of the application, for those of ordinary skill in the art, before not making the creative labor
It puts, is also possible to obtain other drawings based on these drawings.
Fig. 1 is the overall structure diagram of rocket engine fuel system provided by the embodiments of the present application；
Fig. 2 is knot of the anti-rotation cross plug under the first visual angle in rocket engine fuel system provided by the embodiments of the present application
Structure schematic diagram；
Fig. 3 is knot of the anti-rotation cross plug under the second visual angle in rocket engine fuel system provided by the embodiments of the present application
Structure schematic diagram；
Fig. 4 is knot of the anti-rotation cross plug under third visual angle in rocket engine fuel system provided by the embodiments of the present application
Structure schematic diagram；
Fig. 5 is knot of the anti-rotation cross plug under the 4th visual angle in rocket engine fuel system provided by the embodiments of the present application
Structure schematic diagram；
Fig. 6 is that anti-rotation cross plug is located at the first propellant receptacle in rocket engine fuel system provided by the embodiments of the present application
The schematic diagram of case.
In figure: the first propellant tank of 1-；The second propellant tank of 2-；3- control valve；The anti-rotation cross plug of 4-；5- inverted round stage
Body；The cross partition of 6-；7- flow-disturbing hole；8- flowmeter；The first solenoid valve of 9-；10- first gas relief valve；11- first gas
Safety valve；12- first gas fill valve；13- the first gas cylinder safely valve；14- first pressure gauge；15- second pressure gauge；16-
Two solenoid valves；The first pressure reducer of 17-；The first engine of 18-；The first high pressure gas cylinder of 19-；The second engine of 20-.
Specific embodiment
It is clearly and completely described below in conjunction with technical solution of the attached drawing to the application, it is clear that described implementation
Example is some embodiments of the present application, instead of all the embodiments.
The component of the embodiment of the present application for usually describing and showing in attached drawing here can be with a variety of different configurations
To arrange and design.Therefore, the detailed description of the embodiments herein provided in the accompanying drawings is not intended to limit below and is wanted
The scope of the present application of protection is sought, but is merely representative of the selected embodiment of the application.
Based on the embodiment in the application, those of ordinary skill in the art are obtained without making creative work
The every other embodiment obtained, shall fall in the protection scope of this application.
In the description of the present application, it should be noted that term " center ", "upper", "lower", "left", "right", "vertical",
The orientation or positional relationship of the instructions such as "horizontal", "inner", "outside" be based on the orientation or positional relationship shown in the drawings, merely to
Convenient for describe the application and simplify description, rather than the device or element of indication or suggestion meaning must have a particular orientation,
It is constructed and operated in a specific orientation, therefore should not be understood as the limitation to the application.In addition, term " first ", " second ",
" third " is used for descriptive purposes only and cannot be understood as indicating or suggesting relative importance.
In the description of the present application, it should be noted that unless otherwise clearly defined and limited, term " installation ", " phase
Even ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or be integrally connected；It can
To be mechanical connection, it is also possible to be electrically connected；It can be directly connected, can also can be indirectly connected through an intermediary
Connection inside two elements.For the ordinary skill in the art, above-mentioned term can be understood at this with concrete condition
Concrete meaning in application.
Fig. 1 is the overall structure diagram of rocket engine fuel system provided by the embodiments of the present application；Fig. 2 is the application
Structural schematic diagram of the anti-rotation cross plug under the first visual angle in the rocket engine fuel system that embodiment provides；Fig. 3 is this Shen
It please anti-structural schematic diagram of the rotation cross plug under the second visual angle in the rocket engine fuel system that provides of embodiment；Fig. 4 is this
Structural schematic diagram of the anti-rotation cross plug under third visual angle in the rocket engine fuel system of embodiment offer is provided；Fig. 5 is
Structural schematic diagram of the anti-rotation cross plug under the 4th visual angle in rocket engine fuel system provided by the embodiments of the present application；Fig. 6
It is located at the schematic diagram of the first propellant tank for rotation cross plug anti-in rocket engine fuel system provided by the embodiments of the present application.
Embodiment one:
As shown in figs 1 to 6, rocket engine fuel system provided by the embodiments of the present application, comprising: booster rocket hair
Motivation fuel system and core grade rocket engine fuel system；Booster rocket engine fuel system includes the first propellant receptacle
Case 1, core grade rocket engine fuel system include the second propellant tank 2, the first propellant tank 1 and the second propellant tank
2 connections, are provided with control valve 3, control valve 3 is in the open state between the first propellant tank 1 and the second propellant tank 2
When, the propellant in the first propellant tank 1 is flowed to 2 direction of the second propellant tank.
Specifically, the booster rocket engine fuel system of rocket engine fuel system provided by the embodiments of the present application
In the first propellant tank 1 be connected to the second propellant tank 2 in core grade rocket engine fuel system, and first promote
Be provided with control valve 3 between agent tank 1 and the second propellant tank 2, allow propellant in the first propellant tank 1 from
First propellant tank 1 is flowed into the second propellant tank 2.
When the work of core grade rocket, the first propellant tank 1 can convey propellant into the second propellant tank 2, prevent
Only the consumption of propellant causes core grade rocket carrying capacity to decline in core grade rocket engine fuel system, protects to a certain extent
The carrying capacity of core grade rocket is demonstrate,proved.
Further, the pressure in the first propellant tank 1 is greater than the pressure in the second propellant tank 2, works as control valve
When unlatching, the propellant in the first propellant tank 1 can be flowed into the second propellant tank 2.
In the present embodiment, the first communication port is provided on the first propellant tank 1, the first communication port is located at the first propellant
The bottom section of the side of tank 1；The second communication port, the first propellant tank 1 and second are provided on second propellant tank 2
By pipeline connection between propellant tank 2, one end of pipeline is connect with the first communication port, and the other end and the second communication port connect
It connects.
Preferably, it after booster rocket engine fuel system completes work within the set time, first pushes away at this time
Propellant still has a residue in into agent tank 1, opening controlling valve 3, and remaining propellant passes through control valve in the first propellant tank 1
3 enter in the second propellant tank 2 in core grade rocket engine fuel system, i.e. residue in the first propellant tank 1
Propellant can be conveyed into the second propellant tank 2, can not only prevent from promoting in core grade rocket engine fuel system
The consumption of agent causes core grade rocket carrying capacity to decline, and ensure that the carrying capacity of core grade rocket, and also reduce first and push away
The waste of propellant, economizes on resources in into agent tank 1, and also avoids the remaining propellant pair in the first propellant tank 1
Rocket part bearing capacity causes certain waste.
Specifically, after booster rocket engine fuel system completes work within the set time, in order to enable the
Remaining propellant can largely be flowed into the second propellant tank 2 out of first propellant tank 1 in one propellant tank 1
It is interior, it is preferable that the first communication port is located at the bottom section of the side of the first propellant tank 1.
In the present embodiment, booster rocket engine fuel system further includes the first engine 18, the first propellant tank 1
It is connect with the first engine 18.
Specifically, in order to enable the propellant in the first propellant tank 1 can smoothly flow to the first engine very much
In 18, the bottom of the first propellant tank 1 is provided with outlet, and the outlet of the first propellant tank 1 is known as first outlet, and first pushes away
First engine 18 is flowed to by first outlet into the propellant in agent tank 1.
Preferably, core grade rocket engine fuel system further includes the second engine 20, the second propellant tank 2 and second
Engine 20 connects.The outlet of second propellant tank 2 is located at the bottom of the second propellant tank 2, the second propellant tank 2
Outlet is known as second outlet, and the propellant in the second propellant tank 2 flows to the second engine 20 by second outlet.
After booster rocket engine fuel system completes work within the set time, the first engine 18 is closed at this time
It closes, control valve 3 is opened, and remaining propellant enters the combustion of core grade rocket engine by control valve 3 in the first propellant tank 1
In the second propellant tank 2 in material system, to guarantee the carrying capacity of core grade rocket.
When the propellant of the first propellant tank 1 flows to the first engine 18 by first outlet, or works as second and push away
When flowing to the second engine 20 by second outlet into the propellant of agent tank 2, the first propellant tank 1, the second propellant receptacle
Whirlpool energy can be generated in case 2.In a kind of preferred embodiment of the present embodiment, in order to disperse and weaken the first propellant receptacle
The whirlpool energy that propellant in the propellant of case 1 and the second propellant tank 2 generates, the outlet of the first propellant tank 1 and
The outlet of second propellant tank 2 is provided with anti-rotation cross plug 4.
Specifically, anti-rotation cross plug 4 includes rounding stage body 5 and cross partition 6；Rounding stage body 5 be set to it is cross every
On plate 6, the center of rounding stage body 5 and the center of cross partition 6 are located on the same line；Cross partition 6 is set to
The outlet of one propellant tank 1 or the outlet of the second propellant tank 2.
As shown in Figure 2 and Figure 5, rounding stage body 5 is set on cross partition 6, and cross partition 6 is welded in the first propulsion
In the outlet of agent tank 1 or the outlet of the second propellant tank 2.When the propellant in the first propellant tank 1 goes out from first
When propellant when mouth outflow or in the second propellant tank 2 is flowed out from second outlet, in the first propellant tank of part 1
Propellant or the second propellant tank of part 2 in propellant first along the side wall of rounding stage body 5 flow to cross partition
6, what rounding stage body 5 can generate the propellant of propellant or the second propellant tank 2 in the first propellant tank 1
Whirlpool energy carries out preliminary decrease and dispersion.
Cross partition 6 includes first partition and second partition, and as shown in Figure 4 and Figure 5, first partition is vertically inserted in
Second partition, first partition is equal with the height of second partition, first partition and the second partition place of intersecting vertically for it is cross every
The center of plate 6.In Fig. 4, first partition and second partition form four quadrant areas, are referred to as first quartile region, second
Quadrant area, third quadrant region and fourth quadrant region.Propellant or the second propellant receptacle in first propellant tank 1
Propellant in case 2 is by flowing in each quadrant area of cross partition 6, and then can push away to first after rounding stage body 5
The whirlpool energy generated into the propellant of propellant or the second propellant tank 2 in agent tank 1 is further weakened
And disperse.The propellant in propellant or the second propellant tank 2 in first propellant tank 1 passes through cross partition 6
Flow out the first propellant tank 1 or the second propellant tank 2.
In a kind of preferred embodiment of the present embodiment, flow-disturbing hole 7, in flow-disturbing hole 7 are provided on cross partition 6
Number is multiple.
Preferably, first partition includes A plate and C plate, and second partition includes B plate and D plate, and A plate is generally aligned in the same plane with C plate
On, B plate and D plate are in the same plane.Angle between A plate and B plate, angle, C plate between B plate and C plate and between A plate
Angle be right angle.Angle region between A plate and B plate is first quartile region, and the angle region between B plate and C plate is
Second quadrant area, angle region between C plate and D plate are third quadrant region, and the angle region between D plate and A plate is the
Four-quadrant region.It is provided with flow-disturbing hole 7 on A plate, B plate, C plate and D plate, when the propellant of the first propellant tank 1 or
When the propellant of two propellant tanks 2 is flowed into each quadrant area by rounding stage body 5, in one of quadrant area
Part propellant (propellant in propellant or the second propellant tank of part 2 in the first propellant tank of part 1) can
To be flowed into adjacent quadrant area by flow-disturbing hole 7, second-disturbing flow is formed, further disperses and weakens the first propulsion
The whirlpool energy that propellant in the propellant of agent tank 1 and the second propellant tank 2 generates.
For example, the propellant of the propellant of the first propellant tank 1 or the second propellant tank 2 is used in this section
Propellant indicates.When part propellant flows into first quartile region by rounding stage body 5, the part in first quartile region is pushed away
It can be flowed into fourth quadrant region by the flow-disturbing hole 7 on A plate into agent, the part propellant in first quartile can also lead to
The flow-disturbing hole 7 crossed on B plate enters in the second quadrant area.
That is, the part propellant in first quartile region can be entered by the flow-disturbing hole 7 on B plate second as
It limits region and fourth quadrant region is entered by the flow-disturbing hole 7 on A plate.Part propellant in second quadrant area can lead to
The flow-disturbing hole 7 crossed on B plate enters first quartile region and enters third quadrant region by the flow-disturbing hole 7 on C plate.The
Part propellant in three quadrant region can enter the second quadrant area by the flow-disturbing hole 7 on C plate and by D plate
Flow-disturbing hole 7 enter fourth quadrant region.Part propellant in fourth quadrant region can pass through the flow-disturbing hole 7 on D plate
It enters third quadrant region and first quartile region is entered by the flow-disturbing hole 7 on A plate.
2 flow-disturbing holes 7 in 1 flow-disturbing hole 7 or setting etc. can be set on A plate, B plate, C plate and D plate, do not do herein specific
It limits, can specifically set according to the actual situation.
In the present embodiment, Venturi tube, flow are disposed between the first propellant tank 1 and the second propellant tank 2
Meter 8 and the first solenoid valve 9；Control valve 3 is between Venturi tube and flowmeter 8, and Venturi tube is for controlling the first propellant tank 1
Interior propellant flows into the flow of the second propellant tank 2.
When control valve 3 is opened, the propellant in the first propellant tank 1 is flowed into the second propellant tank 2, at this time
First solenoid valve 9 is open state, and can flow into second by the propellant of the first propellant tank 1 known to flowmeter 8 and push away
Into the specific flow of agent tank 2.When control valve 3 is closed, the propellant in the first propellant tank 1 stops to the second propellant
Flowing in tank 2, the first solenoid valve 9 is in off state at this time.
Booster rocket engine fuel system is being set in rocket engine fuel system provided by the embodiments of the present application
Time in complete work after, and after remaining propellant is flowed into the second propellant tank 2 in the first propellant tank 1, help
Push away grade rocket and core grade Separation.After booster rocket and core grade Separation, the first solenoid valve 9 is closed, and prevents second to push away
It is flowed out from the second propellant tank 2 into the propellant in agent tank 2.
Preferably, it is provided with first gas relief valve 10 and first gas safety valve 11 on the first propellant tank 1, first
Air venting valve 10 is for releasing to the gas in the first propellant tank 1, and first gas safety valve 11 is for guaranteeing the
Pressure in one propellant tank 1 is in safe range.It is arranged between first propellant tank 1 and first gas safety valve 11
There is first pressure gauge 14.
In the present embodiment, booster rocket engine fuel system further includes the first high pressure gas cylinder 19, the first high pressure gas cylinder
First gas fill valve 12 and the first gas cylinder safely valve 13, the first high pressure gas cylinder 19 and the first gas cylinder safely valve 13 are provided on 19
Between be provided with second pressure gauge 15；First high pressure gas cylinder 19 is connected to the first propellant tank 1, the first high pressure gas cylinder 19 and
Second solenoid valve 16 and the first pressure reducer 17 are disposed between one propellant tank 1.
Specifically, when needing to be passed through high pressure gas to the first high pressure gas cylinder 19, open first gas fill valve 12, i.e., it is logical
It crosses first gas fill valve 12 and is passed through high pressure gas into high pressure gas cylinder.First gas cylinder safely valve 13 can guarantee the first high pressure gas
Pressure in bottle 19 is in certain safe range.After high pressure gas passes through 17 pressure regulation of the first pressure reducer, enters back into first and push away
Into in agent tank 1.Second solenoid valve 16 is between the first pressure reducer 17 and the first high pressure gas cylinder 19, for opening or disconnecting
Supply of the high pressure gas to the first propellant tank 1 in first high pressure gas cylinder 19.
Preferably, rocket engine fuel system provided by the embodiments of the present application further includes controller, controller and control
Valve 3 connects.
Control valve 3 is opened, and the remaining propellant in the first propellant tank 1 is flowed to the second propellant tank 2, when the
After remaining propellant is flowed into the second propellant tank 2 in one propellant tank 1, controller controls control valve 3 and closes.
The propellant in the second propellant tank 2 flows into the first propellant tank 1 in order to prevent, it is preferable that control valve 3
For check valve.
Core grade rocket engine fuel system provided by the embodiments of the present application further includes the second high pressure gas cylinder, the second high pressure gas
It is provided with second gas fill valve and the second gas cylinder safely valve on bottle, is arranged between the second gas cylinder safely valve and the second high pressure gas cylinder
There is third pressure gauge.Second high pressure gas cylinder is connected to the second propellant tank 2, the second high pressure gas cylinder and the second propellant tank 2
Between be disposed with third solenoid valve and the second pressure reducer.Be provided on second propellant tank 2 second gas relief valve and
Second gas safety valve is provided with the 4th pressure gauge between second gas safety valve and the second propellant tank 2.
Rocket engine fuel system provided by the embodiments of the present application includes multiple booster rocket engine fuel systems,
First propellant tank 1 of each booster rocket engine fuel system with core grade rocket engine fuel system second
Propellant tank 2 is connected to, and is provided with control valve 3 between each first propellant tank 1 and the second propellant tank 2, each to control
When valve 3 is opened, the propellant in each first propellant tank 1 can be flowed to the direction of the second propellant tank 2.
Embodiment two:
A kind of rocket is provided in this implementation, the rocket engine fuel system provided including above-described embodiment one.
In the present embodiment, since rocket includes the rocket engine fuel system that above-described embodiment one provides, thus have
There are whole beneficial effects that above-mentioned rocket engine fuel system has, this is no longer going to repeat them.
Finally, it should be noted that the above various embodiments is only to illustrate the technical solution of the application, rather than its limitations；To the greatest extent
Pipe is described in detail the application referring to foregoing embodiments, those skilled in the art should understand that: its according to
So be possible to modify the technical solutions described in the foregoing embodiments, or to some or all of the technical features into
Row equivalent replacement；And these are modified or replaceed, each embodiment technology of the application that it does not separate the essence of the corresponding technical solution
The range of scheme.
Claims (10)
1. a kind of rocket engine fuel system characterized by comprising booster rocket engine fuel system and core grade fire
Arrow engine fuel system；
The booster rocket engine fuel system includes the first propellant tank, the core grade rocket engine fuel system
Including the second propellant tank, first propellant tank is connected to second propellant tank, first propellant
It is provided with control valve between tank and second propellant tank, when the control valve is in the open state, described first is pushed away
It is flowed into the propellant in agent tank to second propellant tank direction.
2. rocket engine fuel system according to claim 1, which is characterized in that set on first propellant tank
It is equipped with the first communication port, first communication port is located at the bottom section of the side of first propellant tank；
The second communication port, first propellant tank and second propellant receptacle are provided on second propellant tank
By pipeline connection between case, one end of the pipeline is connect with first communication port, the other end and second communication port
Connection.
3. rocket engine fuel system according to claim 1, which is characterized in that first propellant tank goes out
The outlet of mouth and second propellant tank is provided with anti-rotation cross plug.
4. rocket engine fuel system according to claim 3, which is characterized in that the anti-rotation cross plug includes rounding
Stage body and cross partition；
The rounding stage body is set on the cross partition, in the center of the rounding stage body and the cross partition
The heart is located on the same line；
The cross partition is set to the outlet of first propellant tank or the outlet of second propellant tank.
5. rocket engine fuel system according to claim 4, which is characterized in that be provided on the cross partition
Flow-disturbing hole, the number in the flow-disturbing hole are multiple.
6. rocket engine fuel system according to claim 1, which is characterized in that first propellant tank and institute
It states and is disposed with Venturi tube, flowmeter and the first solenoid valve between the second propellant tank；
The control valve is between the Venturi tube and the flowmeter.
7. rocket engine fuel system according to claim 1, which is characterized in that set on first propellant tank
It is equipped with first gas relief valve and first gas safety valve, between first propellant tank and the first gas safety valve
It is provided with first pressure gauge.
8. rocket engine fuel system according to claim 1, which is characterized in that the booster rocket engine combustion
Material system further includes the first high pressure gas cylinder, is provided with first gas fill valve and the first gas cylinder safely on first high pressure gas cylinder
Valve is provided with second pressure gauge between first high pressure gas cylinder and the first gas cylinder safely valve；
First high pressure gas cylinder is connected to first propellant tank, first high pressure gas cylinder and first propellant
Second solenoid valve and the first pressure reducer are disposed between tank.
9. rocket engine fuel system according to claim 8, which is characterized in that the booster rocket engine combustion
Material system further includes the first engine and controller, and first propellant tank is connect with first engine, the control
Device processed is connect with the control valve, and the control valve is check valve.
10. a kind of rocket, which is characterized in that including rocket engine fuel system as claimed in any one of claims 1-9 wherein
System.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910663233.2A CN110374762B (en) | 2019-07-22 | 2019-07-22 | Rocket engine fuel system and rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910663233.2A CN110374762B (en) | 2019-07-22 | 2019-07-22 | Rocket engine fuel system and rocket |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110374762A true CN110374762A (en) | 2019-10-25 |
| CN110374762B CN110374762B (en) | 2020-12-25 |
Family
ID=68254868
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910663233.2A Active CN110374762B (en) | 2019-07-22 | 2019-07-22 | Rocket engine fuel system and rocket |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111207008A (en) * | 2020-02-21 | 2020-05-29 | 中国科学院理化技术研究所 | Device and method for discharging residual propellants in propellant cross conveying pipeline |
| CN112459925A (en) * | 2020-11-02 | 2021-03-09 | 中国运载火箭技术研究院 | Built-in baffle type storage box |
| CN113404619A (en) * | 2021-07-30 | 2021-09-17 | 西安交通大学 | Cut-energy vibration-damping liquid rocket propellant intercircuit cross conveying system |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2623774B1 (en) * | 1987-11-27 | 1990-03-16 | Aerospatiale | DEVICE FOR TRANSFERRING FUEL BETWEEN TANKS OF AN AIRCRAFT |
| US6488237B1 (en) * | 2001-09-28 | 2002-12-03 | The Boeing Company | Propellant cross-feed system and method |
| US20030056838A1 (en) * | 2001-09-21 | 2003-03-27 | Grayson Gary D. | Variable-gravity anti-vortex and vapor-ingestion-suppression device |
| CN103670800A (en) * | 2013-11-18 | 2014-03-26 | 北京宇航系统工程研究所 | Propellant pipe cross conveying system |
| CN105065898A (en) * | 2015-07-24 | 2015-11-18 | 北京控制工程研究所 | Through-type on-orbit refueling system of satellite propulsion system |
| CN107327355A (en) * | 2017-07-28 | 2017-11-07 | 北京宇航系统工程研究所 | A kind of spacecraft propulsion agent management method |
-
2019
- 2019-07-22 CN CN201910663233.2A patent/CN110374762B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2623774B1 (en) * | 1987-11-27 | 1990-03-16 | Aerospatiale | DEVICE FOR TRANSFERRING FUEL BETWEEN TANKS OF AN AIRCRAFT |
| US20030056838A1 (en) * | 2001-09-21 | 2003-03-27 | Grayson Gary D. | Variable-gravity anti-vortex and vapor-ingestion-suppression device |
| US6488237B1 (en) * | 2001-09-28 | 2002-12-03 | The Boeing Company | Propellant cross-feed system and method |
| CN103670800A (en) * | 2013-11-18 | 2014-03-26 | 北京宇航系统工程研究所 | Propellant pipe cross conveying system |
| CN105065898A (en) * | 2015-07-24 | 2015-11-18 | 北京控制工程研究所 | Through-type on-orbit refueling system of satellite propulsion system |
| CN107327355A (en) * | 2017-07-28 | 2017-11-07 | 北京宇航系统工程研究所 | A kind of spacecraft propulsion agent management method |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111207008A (en) * | 2020-02-21 | 2020-05-29 | 中国科学院理化技术研究所 | Device and method for discharging residual propellants in propellant cross conveying pipeline |
| CN112459925A (en) * | 2020-11-02 | 2021-03-09 | 中国运载火箭技术研究院 | Built-in baffle type storage box |
| CN113404619A (en) * | 2021-07-30 | 2021-09-17 | 西安交通大学 | Cut-energy vibration-damping liquid rocket propellant intercircuit cross conveying system |
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| Publication number | Publication date |
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| CN110374762B (en) | 2020-12-25 |
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