CN110173375A - A kind of liquid-propellant rocket engine thrust regulating system and carrier rocket - Google Patents
A kind of liquid-propellant rocket engine thrust regulating system and carrier rocket Download PDFInfo
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- CN110173375A CN110173375A CN201910344327.3A CN201910344327A CN110173375A CN 110173375 A CN110173375 A CN 110173375A CN 201910344327 A CN201910344327 A CN 201910344327A CN 110173375 A CN110173375 A CN 110173375A
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- pipeline
- operating condition
- propellant
- low operating
- high operating
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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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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The invention discloses a kind of liquid-propellant rocket engine thrust regulating system and carrier rockets, include propellant tank, main-inlet pipeline, low operating condition pipeline, high operating condition pipeline, switching valve, export pipeline and multiple thrusters, the propellant receptacle lower box part connects the main-inlet pipeline, main-inlet pipeline one end respectively with the low operating condition pipeline and the high operating condition piping connection, the low operating condition pipeline and described high operating condition pipeline one end are separately connected the switching valve, described switching valve one end connects the export pipeline, described export pipeline one end is connect with the thruster, when the propellant tank supplies propellant to the multiple thruster, the switching valve is used for unlatching and closure by controlling the low operating condition pipeline and the high operating condition pipeline, realize propellant by the low operating condition pipeline supply and by the high operating condition pipe Switching between the supply of road, compared with the existing technology, which facilitates control, and structure is simple, convenient for operation, save the cost.
Description
Technical field
The present invention relates to liquid-propellant rocket engine field, in particular to a kind of liquid-propellant rocket engine thrust regulating system and
Carrier rocket.
Background technique
Aerospace craft is that mankind's exploration of the universe understands the effective means of the outer space, flies as aerospace craft
The core of posture and orbits controlling, the effect of rail control dynamical system include pitching yaw control, roll control, track keep,
Speed amendment etc..In different task section, aircraft needs dynamical system to provide different thrust, thus it is generally necessary to be configured with more
Platform has the thruster of different thrusts, and scheme is complicated, and architecture quality weight is at high cost.
More different thrust thrusters are substituted using change propulsive thruster, the complexity of dynamical system can be reduced, reduced
Thruster quantity reduces system structure quality, thus improve payload mass, enhancing maneuverability, improve accuracy at target etc..
Under normal conditions, realize that the technological approaches that liquid-propellant rocket engine thrust is adjusted is the propellant flow rate for controlling engine.It is common
Thrust regulation scheme be every thruster be all made of independent regulation scheme.In the thruster quantity that need to carry out change propulsive work
When more, system pipeline quantity, valve quantity and control loop quantity are more, inconvenient, control is cumbersome and maintenance is numerous
It is trivial, reliability is low.
Therefore it provides a kind of facilitate control, structure simply, convenient for the liquid rocket of operation, save the cost, high reliablity to send out
Motivation thrust regulating system is current problem to be solved.
Summary of the invention
The object of the present invention is to provide a kind of liquid-propellant rocket engine thrust regulating system and carrier rockets, have and facilitate control
The advantages that system, structure are simple, convenient for operation, save the cost, stable reliability.
To achieve the above object, the invention provides the following technical scheme: a kind of liquid-propellant rocket engine thrust regulating system,
Comprising propellant tank, main-inlet pipeline, low operating condition pipeline, high operating condition pipeline, switching valve, export pipeline and multiple thrusters,
Wherein, the propellant tank connects one end of the main-inlet pipeline, the other end of the main-inlet pipeline respectively with it is described
Low operating condition pipeline and the high operating condition piping connection, the low operating condition pipeline and the high operating condition pipeline are separately connected the switching
Valve, described switching valve one end connect the export pipeline, and described export pipeline one end is connect with the multiple thruster；Described
When propellant tank supplies propellant to the multiple thruster, the switching valve be used for by control the low operating condition pipeline and
The unlatching and closure of the high operating condition pipeline realize that propellant is supplied by the low operating condition pipeline supply and by the high operating condition pipeline
Switching between answering.
Preferably, the main-inlet pipeline connects the low operating condition pipeline and the high operating condition pipeline by diversion three-way,
The diversion three-way includes first entrance, first outlet and second outlet, first entrance described in the main-inlet piping connection, institute
It states high operating condition pipeline to connect with the first outlet, and the low operating condition pipeline is connect with the second outlet, due to the master
Entrance pipe lower end connection diversion three-way facilitates propellant to flow, convenient for operation.
Preferably, the low operating condition pipeline be equipped with regulating valve and switching pipeline, the regulating valve include the 4th entrance and
4th outlet, the low operating condition pipeline are connect with the 4th entrance, one end and the 4th outlet phase of the switching pipeline
Even and the other end connects the switching valve and facilitates the adjusting of propellant flow rate due to the presence of regulating valve, convenient for control.
Preferably, the switching valve is two-position three-way valve, including the outlet of second entrance, third entrance, third and first
Electrical interface；The wherein second entrance and the switching piping connection, the third entrance and the high operating condition piping connection, institute
It states switching valve to be electrically connected by first electrical interface and controller, the controller is for controlling the second entrance and institute
The unlatching and closure for stating third entrance, since the switching valve is connected with controller, described first is electrically connected interface and the control
The connection of device electric lead, on the one hand convenient for the opening and closing of control switching valve, while facilitating control, convenient for operation.
Preferably, according to actual needs, the propellant tank includes fuel tank and oxidant storage tank.
Preferably, the export pipeline surface is equipped with ripple struction, since the export pipeline surface is equipped with ripple struction,
Facilitate export pipeline to be bent, helps that export pipeline is installed and is safeguarded.
Preferably, the thruster surface is equipped with flame-retardant layer, and the flame-retardant layer is mutually close to the thruster surface, and
It is connected by binder viscosity, due to the presence of flame-retardant layer, thruster is avoided to be destroyed by fire, extend the service life of thruster,
It since the two is mutually close to, is connected by binder viscosity, and then guarantees that flame-retardant layer is completely embedded with thruster, securely, avoided
Flame-retardant layer generates obscission.
Preferably, the low operating condition pipeline, the high operating condition pipeline and the switching pipeline cross-sectional shape are circular configuration,
And it is internal be equipped with through-hole, the low operating condition pipeline, the high operating condition pipeline and the switching pipeline be bendable structure simultaneously
Since the cross-sectional shape of three's structure is circular configuration, on the one hand increase internal capacity, while operator being avoided to install
It is scratched in journey, effective protection personal safety, and due to the low operating condition pipeline, the high operating condition pipeline and the switching pipeline
It is bendable structure, facilitates installation, it is convenient for safeguarding.
Preferably, the low operating condition pipeline, the high operating condition pipeline and the switching pipeline inner surface be equipped with smooth layer, three
Person connect with the smooth layer viscosity, due to the presence of smooth layer, reduces oxidant or fuel is contacted with pipeline inner wall, guarantee
Oxidant or fuel flow smoothly.
The present invention also provides a kind of carrier rockets, include the above liquid-propellant rocket engine thrust regulating system.
Compared with prior art, the beneficial effects of the present invention are: the liquid-propellant rocket engine thrust regulating system is by promoting
Agent tank, main-inlet pipeline, low operating condition pipeline, high operating condition pipeline, switching valve, export pipeline and multiple thrusters composition, promote
Agent flows to main-inlet pipeline by propellant tank, enters low operating condition pipeline and high operating condition pipeline later, in low operating condition pipeline and
High operating condition pipeline enters multiple thrusters by export pipeline by switching valve, switching valve one end connection outlet pipeline, propellant
Interior, when the propellant tank supplies propellant to the multiple thruster, the switching valve is used for described low by controlling
The unlatching and closure of operating condition pipeline and the high operating condition pipeline realize propellant by the low operating condition pipeline supply and by the height
Switching between the supply of operating condition pipeline, whole operation process solve every thruster and are all made of independent thrust regulation scheme
Existing system pipeline quantity is more, valve quantity is more and control loop quantity more than problem, facilitate control, facilitate operation,
Reduce pipeline quantity, valve quantity and control loop quantity simultaneously, save the cost improves reliability.
Detailed description of the invention
Fig. 1 is fluid present invention rocket engine thrust regulating system schematic diagram；
Fig. 2 is that oxidant of the present invention and fuel fabrication control to adjust structural schematic diagram；
Fig. 3 is the structural schematic diagram of the low operating condition pipeline of the present invention；
Fig. 4 is the structural schematic diagram of export pipeline of the present invention；
Fig. 5 is thruster of the present invention and flame-retardant layer schematic cross-section.
Description of symbols:
1 propellant tank, 11 oxidant storage tank
12 fuel tank, 2 main-inlet pipeline
3 diversion three-way, 31 first entrance
32 first outlet, 33 second outlet
The 4 high operating condition pipelines of low operating condition pipeline 5
The 4th entrance of 6 regulating valve 61
62 the 4th outlet, 7 switching pipeline
8 switching valve, 81 second entrance
The outlet of 82 third entrance, 83 third
84 first electrical interface, 9 export pipeline
10 thrusters
Specific embodiment
Understand in order to make the object, technical scheme and advantages of the embodiment of the invention clearer, below will with attached drawing and in detail
Narration clearly illustrates the spirit of disclosed content, and any skilled artisan is understanding the content of present invention
After embodiment, when the technology that can be taught by the content of present invention, it is changed and modifies, without departing from the essence of the content of present invention
Mind and range.
The illustrative embodiments of the present invention and their descriptions are used to explain the present invention, but not as a limitation of the invention.
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 present invention, 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.
About term used herein " substantially ", " about " etc., to modify it is any can be with the quantity or mistake of microvariations
Difference, but this slight variations or error can't change its essence.In general, microvariations that such term is modified or error
Range in some embodiments can be 20%, in some embodiments can be 10%, can be in some embodiments 5% or its
His 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, it is not limited thereto.
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.
Please refer to Fig. 1-5, the embodiment provides a kind of liquid-propellant rocket engine thrust regulating system, comprising into
Agent tank 1, main-inlet pipeline 2, low operating condition pipeline 4, high operating condition pipeline 5, switching valve 8, export pipeline 9 and multiple thrusters 10,
Wherein, propellant tank 1 connect main-inlet pipeline 2 one end, the other end of main-inlet pipeline 2 respectively with low operating condition pipeline 4 and
High operating condition pipeline 5 connects, and low operating condition pipeline 4 and high operating condition pipeline 5 are separately connected switching valve 8,8 one end connection outlet pipe of switching valve
Road 9,9 one end of export pipeline are connect with multiple thrusters 10, when propellant tank 1 supplies propellant to multiple thrusters 10,
Switching valve 8 is used for unlatching and closure by controlling low operating condition pipeline 4 and high operating condition pipeline 5, realizes propellant by low operating condition pipe
Road 4 is supplied and by the switching between the supply of high operating condition pipeline 5.
Specifically: the liquid-propellant rocket engine thrust regulating system is by propellant tank 1, main-inlet pipeline 2, low operating condition
Pipeline 4, high operating condition pipeline 5, switching valve 8, export pipeline 9 and multiple thrusters 10 form, and whole process, propellant passes through propulsion
Agent tank stream 1 enters low operating condition pipeline 44 and high operating condition pipeline 5, in low operating condition pipeline and high operating condition to main-inlet pipeline 2 later
Pipeline 5 enters multiple thrusters 10 by export pipeline 9 by switching valve 8,8 one end connection outlet pipeline 9 of switching valve, propellant
Interior, when propellant tank 1 supplies propellant to multiple thrusters 10, switching valve 8 is used for by controlling low operating condition pipeline 4 and height
The unlatching and closure of operating condition pipeline 5 realize that propellant is supplied by low operating condition pipeline 4 and by cutting between the supply of high operating condition pipeline 5
It changes, to control the supply of propellant, whole operation process solves every thruster 10 and is all made of independent thrust regulation scheme
Existing system pipeline quantity is more, valve quantity is more and control loop quantity more than problem, facilitate control, facilitate operation,
Reduce pipeline quantity, valve quantity and control loop quantity simultaneously, save the cost improves reliability.
Propellant tank 1 includes oxidant storage tank 11 and fuel tank 12, and above-mentioned thrust adjustment structure can both cooperate oxygen
Agent storage tank 11 uses, and to enter the amount of thrust chamber by adjusting oxidant, adjusts motor power；Combustion can also be independently matched with
Expect that storage tank 12 uses, to enter the amount of thrust chamber by adjusting fuel, adjusts motor power, or be set to oxidant simultaneously
Storage tank 11 and fuel tank 12 flow into the flow of thrust chamber to pass through while adjust oxidant storage tank 11 and fuel tank 12, adjust
Save motor power, it should be noted that thruster includes thrust chamber, and thrust chamber is used to provide field for oxidant and fuel reaction
Institute.
Below by taking thrust regulating system is arranged in oxidant storage tank as an example, the present invention is described in detail.Specifically, should
Kind liquid-propellant rocket engine thrust regulating system includes oxidant storage tank 11, main-inlet pipeline 2, low operating condition pipeline 4, high operating condition
Pipeline 5, switching valve 8, export pipeline 9 and multiple thrusters 10, wherein 1 lower part of propellant tank connects main-inlet pipeline 2, main
2 one end of entrance pipe is connect with low operating condition pipeline 4 and high operating condition pipeline 5 respectively, low operating condition pipeline 4 and high 5 one end of operating condition pipeline
It is separately connected switching valve 8,8 one end connection outlet pipeline 9 of switching valve, 9 one end of export pipeline is connect with thruster 10.
Specifically, the liquid-propellant rocket engine thrust regulating system is by oxidant storage tank 11, main-inlet pipeline 2, low work
Condition pipeline 4, high operating condition pipeline 5, switching valve 8, export pipeline 9 and multiple thrusters 10 form, and pass through main-inlet by propellant
Pipeline 2 flows into low operating condition pipeline 4 and high operating condition pipeline 5, flows into export pipeline 9 after propellant, is entered by export pipeline 9 more
A thruster 10, whole process, propellant, to main-inlet pipeline 2, enter low operating condition pipeline 44 by propellant tank stream 1 later
With high operating condition pipeline 5, in low operating condition pipeline and high operating condition pipeline 5 by switching valve 8,8 one end connection outlet pipeline 9 of switching valve,
Propellant is entered in multiple thrusters 10 by export pipeline 9, supplies propellant to multiple thrusters 10 in oxidant storage tank 11
When, switching valve 8 is used for unlatching and closure by controlling low operating condition pipeline 4 and high operating condition pipeline 5, realizes propellant by low operating condition
Pipeline 4 is supplied and by the switching between the supply of high operating condition pipeline 5, to control the supply of propellant, whole operation process is solved
Every thruster 10 is all made of that system pipeline quantity present in independent thrust regulation scheme is more, valve quantity is more and control
Problem more than the quantity of circuit facilitates control, facilitates operation, while reducing pipeline quantity, valve quantity and control loop quantity,
Save the cost improves reliability.
In the present embodiment, main-inlet pipeline 2 connects low operating condition pipeline 4 and high operating condition pipeline 5 by diversion three-way 3,
The diversion three-way includes first entrance 31, first outlet 32 and second outlet 33, and main-inlet pipeline 2 connects first entrance 31,
High operating condition pipeline 5 is connect with first outlet 32, and low operating condition pipeline 4 is connect with second outlet 33, due to 2 lower end of main-inlet pipeline
Diversion three-way 3 is connected, propellant is facilitated to flow, convenient for operation.
It should be noted that low operating condition pipeline 4 is equipped with regulating valve 6 and switching pipeline 7, regulating valve 6 includes the 4th entrance
61 and the 4th export 62, and low operating condition pipeline 4 is connect with the 4th entrance 61, and the one end for pipeline 7 of transferring is connected another with the 4th outlet 62
One end connects switching valve 8 and facilitates the adjusting of propellant flow rate due to the presence of regulating valve 6, convenient for control.
It is noted that switching valve 8 is two-position three-way valve, including second entrance 81, third entrance 82, third outlet 83
And first electrical interface 84, second entrance 81 connects with switching pipeline 7, third entrance 82 and high operating condition pipeline 5 connect, switching valve
8 are electrically connected by the first electrical interface 84 with controller, and controller is used to control the unlatching of second entrance 81 and third entrance 82
And closure, since switching valve 8 is connected with controller, first interface 84 that is electrically connected is connect with controller electric lead, is on the one hand convenient for
The opening and closing of switching valve is controlled, while facilitating control, convenient for operation.
It should be noted that the installation of export pipeline 9 for convenience, can be arranged ripple struction on 9 surface of export pipeline,
To facilitate export pipeline 9 to be bent, help that export pipeline 9 is installed and is safeguarded.
Particularly, in order to extend 10 service life of thruster, flame-retardant layer, flame-retardant layer and thrust are equipped on 10 surface of thruster
10 surface of device is mutually close to, and is connected by binder viscosity, due to the presence of flame-retardant layer, thruster 10 is avoided to be destroyed by fire,
Extend the service life of thruster 10.Further, since the two is mutually close to, connected, and then guaranteed fire-retardant by binder viscosity
Layer with thruster 10 be completely embedded, securely, avoid flame-retardant layer generate obscission.
In addition, low operating condition pipeline 4, high operating condition pipeline 5 and switching 7 section of pipeline are circular configuration, and inside is equipped with through-hole,
This design can increase three's internal capacity, simultaneously because the cross-sectional shape of three is circular configuration, operator be avoided to pacify
It is scratched during dress, effective protection personal safety, it is worth mentioning at this point that, in the present embodiment, low operating condition pipeline 4, senior engineer
Condition pipeline 5 and switching pipeline 7 all can be bendable structure, facilitate installation, convenient for safeguarding, further explanation, in order to protect
It is sufficient to demonstrate,prove 1 inner fuel of propellant tank, is cylindrical structure by the shape of propellant tank 1, due to the propellant tank 1
Shape be cylindrical structure, increase volume, improve internal memory storage.
The quantity of thruster 1 is 6 in the present embodiment, and in actual application, the quantity of thruster 10 can be with
It is other quantity, in order to avoid repeating, no longer discusses herein.
In the present embodiment, connection type includes to be threadedly coupled, welding, and riveting etc. no longer illustrates herein.
Working principle: thruster 10 is in high operating condition (high thrust output), thruster when 10 inlet pressure of thruster is P1
Thruster is in low operating condition (low thrust output) when 10 inlet pressures are P2.Assuming that 1 boost pressure of propellant tank is P1, adjust
6 outlet pressure of valve is P2, and 1 flow resistance of propellant tank, 3 flow resistance of diversion three-way, 8 flow resistance of switching valve, pipe-line system flow resistance are ignored not
Meter, then thruster inlet pressure is P1 when high 5 place runner of operating condition pipeline is access, and low 4 place runner of operating condition pipeline is access
When thruster inlet pressure be P2.By controlling 8 working condition of switching valve, realize that 10 change propulsive of thruster is adjusted, specific works
Principle is as follows: default 8 state of switching valve, after the pressurization of propellant tank 1, high 5 place runner of operating condition pipeline is in channel status,
Low 4 place runner of operating condition pipeline is in close state, and 10 inlet pressure of thruster is P1 at this time, and thruster 10 is in high operating condition work
Make state.When needing thruster 10 switching to the work of low operating condition by high operating condition working condition, control system is logical to switching valve 8
Electricity, switching valve 8 work, and low 4 place runner of operating condition pipeline are placed in open state, 5 place runner of high operating condition pipeline is placed in closing
State, thruster inlet pressure is P2 at this time, and thruster 10 is in low operating condition working condition.It needs thruster 10 by low operating condition
When working condition switches to the work of high operating condition, controller 5 is powered to switching valve 8, and switching valve 8 works, will be where high operating condition pipeline
Runner is placed in open state, 4 place runner of low operating condition pipeline is placed in off, and thruster inlet pressure is adjusted to again at this time
P1, thruster 10 are in high operating condition working condition.In this way, realizing 10 change propulsive of thruster by constantly controlling 8 state of switching valve
Work.
Second embodiment of the present invention is related to a kind of liquid-propellant rocket engine thrust regulating system, and second embodiment is
It is further improved on the basis of first embodiment, as shown in Figure 1, specifically, in low operating condition pipeline 4, high operating condition
Pipeline 5 and switching 7 inner surface of pipeline are equipped with smooth layer, and connect with smooth layer viscosity, due to the presence of smooth layer, reduce oxidation
Agent or fuel are contacted with pipeline inner wall, guarantee that oxidant or fuel flow smoothly, it should be pointed out that in order to facilitate control piper
The internal diameter of low operating condition pipeline 4 is designed to facilitate the flow of control oxidant less than passing through in high operating condition pipeline 5 by flow.
In addition, regulating valve 6 is installed on low operating condition pipeline 4 in present embodiment, and in actual application, regulating valve 6
It may be mounted at the outlet of diversion three-way 3 or 8 entrance of switching valve, regulating valve 6 includes throttle valve, speed governing valve, overflow throttle valve one kind
Or it is several, it will not enumerate herein.
Controller is programmable controller.
The present invention also provides a kind of carrier rockets, include the above liquid-propellant rocket engine thrust regulating system.
The foregoing is merely the schematical specific embodiments of the present invention, before not departing from conceptions and principles of the invention
It puts, the equivalent changes and modifications that any those skilled in the art is made should belong to the scope of protection of the invention.
Claims (10)
1. a kind of liquid-propellant rocket engine thrust regulating system, it is characterised in that: comprising propellant tank, main-inlet pipeline, low
Operating condition pipeline, high operating condition pipeline, switching valve, export pipeline and multiple thrusters, wherein the propellant tank connects the master
One end of entrance pipe, the other end of the main-inlet pipeline connect with the low operating condition pipeline and the high operating condition pipeline respectively
It connects, the low operating condition pipeline and the high operating condition pipeline are separately connected the switching valve, and switching valve one end connection is described out
Mouth pipeline, described export pipeline one end is connect with the multiple thruster；In the propellant tank to the multiple thruster
When supplying propellant, the switching valve is used for the unlatching by controlling the low operating condition pipeline and the high operating condition pipeline and closes
It closes, realizes propellant by the low operating condition pipeline supply and by the switching between the high operating condition pipeline supply.
2. liquid-propellant rocket engine thrust regulating system according to claim 1, it is characterised in that: the main-inlet pipeline
The low operating condition pipeline and the high operating condition pipeline are connected by diversion three-way, the diversion three-way includes first entrance, and first
Outlet and second outlet, first entrance described in the main-inlet piping connection, the high operating condition pipeline and the first outlet connect
It connects, and the low operating condition pipeline is connect with the second outlet.
3. liquid-propellant rocket engine thrust regulating system according to claim 1, it is characterised in that: the low operating condition pipeline
Be equipped with regulating valve and switching pipeline, the regulating valve include the 4th entrance and the 4th outlet, the low operating condition pipeline with it is described
The connection of 4th entrance, one end of the switching pipeline is connected with the 4th outlet and the other end connect the switching valve.
4. liquid-propellant rocket engine thrust regulating system according to claim 3, it is characterised in that: the switching valve is two
Position three-way valve, including the outlet of second entrance, third entrance, third and the first electrical interface；Wherein the second entrance with it is described
Transfer piping connection, the third entrance and the high operating condition piping connection, the switching valve by first electrical interface with
Controller is electrically connected, and the controller is used to control the unlatching and closure of the second entrance and the third entrance.
5. liquid-propellant rocket engine thrust regulating system according to claim 1, it is characterised in that: the propellant tank
Include fuel tank and oxidant storage tank.
6. liquid-propellant rocket engine thrust regulating system according to claim 1, it is characterised in that: the export pipeline table
Face is equipped with ripple struction.
7. liquid-propellant rocket engine thrust regulating system according to claim 1, it is characterised in that: the thruster surface
Equipped with flame-retardant layer, the flame-retardant layer is mutually close to the thruster surface, and is connected by binder viscosity.
8. liquid-propellant rocket engine thrust regulating system according to claim 1 or 3, it is characterised in that: the low operating condition
Pipeline, the high operating condition pipeline and the switching pipeline cross-sectional shape are circular configuration, and internal equipped with through-hole, the low operating condition
Pipeline, the high operating condition pipeline and the switching pipeline are bendable structure.
9. liquid-propellant rocket engine thrust regulating system according to claim 8, it is characterised in that: the low operating condition pipe
Road, the high operating condition pipeline and the switching pipeline inner surface are equipped with smooth layer, and three connect with the smooth layer viscosity.
10. a kind of carrier rocket, it is characterised in that: pushed away comprising liquid-propellant rocket engine described in any one of claim 1-9
Draught control system.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910344327.3A CN110173375A (en) | 2019-04-26 | 2019-04-26 | A kind of liquid-propellant rocket engine thrust regulating system and carrier rocket |
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| CN201910344327.3A CN110173375A (en) | 2019-04-26 | 2019-04-26 | A kind of liquid-propellant rocket engine thrust regulating system and carrier rocket |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111441876A (en) * | 2020-04-01 | 2020-07-24 | 北京深蓝航天科技有限公司 | Liquid rocket fuel conveying structure for multiple engines in parallel connection |
| CN113405407A (en) * | 2019-12-27 | 2021-09-17 | 北京星际荣耀空间科技股份有限公司 | Liquid rocket thrust control system and liquid rocket |
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| CN113405407A (en) * | 2019-12-27 | 2021-09-17 | 北京星际荣耀空间科技股份有限公司 | Liquid rocket thrust control system and liquid rocket |
| CN111441876A (en) * | 2020-04-01 | 2020-07-24 | 北京深蓝航天科技有限公司 | Liquid rocket fuel conveying structure for multiple engines in parallel connection |
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Application publication date: 20190827 |