CN109083768A - Suitable for large-scale liquid oxygen methane Test System for Rocket Engine Test supply system and rocket - Google Patents
Suitable for large-scale liquid oxygen methane Test System for Rocket Engine Test supply system and rocket Download PDFInfo
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- CN109083768A CN109083768A CN201811180265.9A CN201811180265A CN109083768A CN 109083768 A CN109083768 A CN 109083768A CN 201811180265 A CN201811180265 A CN 201811180265A CN 109083768 A CN109083768 A CN 109083768A
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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
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
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Abstract
The invention discloses one kind to be suitable for large-scale liquid oxygen methane Test System for Rocket Engine Test supply system.Oxidant supply system repeated construction is avoided, cost is reduced；Gas methane and liquid methane can be supplied in supply system simultaneously, carries out the large rocket engine test of methane gas-liquid blending, low cost carries out re-generatively cooled engine combustion performance test；By mixer can stability and high efficiency carry out different methane injection temperatures large rocket engine test；Cryogenic pipe pre-cooling is carried out using liquid nitrogen in supply system, is had the advantages that safe and at low cost.On this basis, present invention also provides a kind of based on the rocket for being suitable for large-scale liquid oxygen methane Test System for Rocket Engine Test supply system.
Description
Technical field
The present invention relates to aerospace fields, in particular to a kind of to be suitable for large-scale liquid oxygen methane Test System for Rocket Engine Test confession
Answer system and rocket.
Background technique
1, large-scale liquid-propellant rocket engine has huge demand in aerospace field, and mankind's lunar exploration or future step on
Lu Huoxing requires the liquid-propellant rocket engine of high thrust as support, liquid oxygen/methane liquid-propellant rocket engine have high specific impulse,
Inexpensive, low carbon deposit, cooling noncoking, good environmental protection, it is reusable the advantages that, be current reusable carrier rocket
With the focus in large-scale liquid booster powerplant research field.But current liquid oxygen/methane rocket engine correlation test
Carry out less, still needs to further study.Existing pilot system individually carries out liquid oxygen/liquid methane and liquid oxygen/gas Methane, examination
Check system there are the wasting of resources, it is at high cost the problems such as.Therefore, it is necessary to design a set of to carry out liquid oxygen/liquid methane and liquid oxygen/gas
The pilot system of methane.
2, repeat the advantages of making and ultimate aim be in order to reduce vehicle it is disposable after abandon expensive rocket body,
It is wasted caused by engine and electrical equipment, production and the launch cost of vehicle is reduced by the way that share the expenses is used for multiple times,
It is the emphasis of space industry future development.Wherein, the reusable of engine becomes urgent problem, liquid oxygen/methane
As the propellant that alternate-engine is reused, there is potential powerful competitiveness.The reusable middle need of engine
Fully consider that its cooling effect, re-generatively cooled are suitable for the reusable engine of liquid oxygen/methane.Existing pilot system is directed to
Re-generatively cooled operating condition carries out test, and the engine containing cooling duct can only be used to carry out gas-liquid blending spray test, cause to try
It tests cost to increase, is not suitable for selecting suitable cooling duct parameter by carrying out a large amount of methane gas-liquid Mixed testings.Therefore, it is necessary to
Design a set of liquid oxygen/methane pilot system that can fill gas methane and liquid methane simultaneously.
3, in liquid oxygen/methane re-generatively cooled engine test, best methane injection temperature need to be sought, realizes high combustion efficiency
With combustion stablized purpose, for existing pilot system when methane temperature controls, control precision is low and is easily introduced impurity.Therefore, it needs
Design a set of liquid oxygen/methane pilot system for carrying out different methane injection temperature tests.
4, during liquid oxygen/methane engine test, methane gas dangerous property in air needs to examine in experimental enviroment
Consider concentration of methane gas, guarantee test safety.Existing pilot system needs to be pre-chilled using liquid methane in pipe-line system precooling process
Pipeline, a large amount of methane get into the air.And liquid methane and liquid oxygen relative cost are higher.It is a set of highly-safe therefore, it is necessary to design
And pipeline chilldown system at low cost.
Summary of the invention
The purpose of the present invention is to provide one kind to be suitable for large-scale liquid oxygen methane Test System for Rocket Engine Test supply system, with solution
Certainly the above-mentioned technical problems in the prior art.
It is provided by the invention to be suitable for large-scale liquid oxygen methane Test System for Rocket Engine Test supply system, it has the advantages that
Gas methane and liquid methane test share a set of liquid oxygen supply system in large rocket engine test supply system, keep away
Exempt from oxidant supply system repeated construction, reduces cost；
Gas methane and liquid methane can be supplied in supply system simultaneously, carries out the large rocket engine examination of methane gas-liquid blending
It tests, low cost carries out re-generatively cooled engine combustion performance test；
By mixer can stability and high efficiency carry out different methane injection temperatures large rocket engine test；
Cryogenic pipe pre-cooling is carried out using liquid nitrogen in supply system, is had the advantages that safe and at low cost.
In addition, present invention also provides a kind of rocket, including it is above-mentioned suitable for large-scale liquid oxygen methane Test System for Rocket Engine Test
Supply system.
Detailed description of the invention
It, below will be to specific in order to illustrate more clearly of the specific embodiment of the invention 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 present invention, 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 knot for being suitable for large-scale liquid oxygen methane Test System for Rocket Engine Test supply system that the embodiment of the present invention one provides
Structure schematic diagram.
Appended drawing reference: A01- pressure reducer；A02- hand stop valve；A03- pressure sensor；A04- hand stop valve；A05-
Pneumatic stopping valve；A06- filter；A07- orifice plate；A08- temperature sensor；A09- pressure sensor；E01- liquid oxygen storage tank；
A10- solenoid valve；A11- hand stop valve；A12- safety valve；A13- hand stop valve；B04- hand stop valve；A14- is cut manually
Only valve；A15- filter；A29- filter；A16- pneumatic stopping valve；A17- flowmeter；A18- pressure sensor；A19- temperature
Sensor；A20- venturi tube；A21- temperature sensor；A22- pressure sensor；A23- hand stop valve；A24- pneumatically ends
Valve；A26- pneumatic stopping valve；A25- orifice plate；A27- filter；A28- solenoid valve；E02- liquid nitrogen storage tank；B01- hand stop valve；
B07- safety valve；B08- hand stop valve；B09- filter；B02- hand stop valve；B03- filter；B05- filter；
B04- hand stop valve；B06- hand stop valve；C01- pressure reducer；C02- hand stop valve；C03- pressure sensor；C04- hand
Dynamic shut-off valve；C05- pneumatic stopping valve；C06- filter；C07- orifice plate；C08- temperature sensor；C09- pressure sensor；
E03- liquid methane storage tank；C10- solenoid valve；C11- hand stop valve；C12- safety valve；C13- hand stop valve；C14- is cut manually
Only valve；C16- filter；C15- filter；C17- pneumatic stopping valve；C18- flowmeter；F01- hand stop valve；C19- is manual
Shut-off valve；C20- pressure sensor；C21- temperature sensor；C22- venturi tube；C23- temperature sensor；C24- pressure sensing
Device；C25- hand stop valve；C26- pneumatic stopping valve；C28- pneumatic stopping valve；C27- orifice plate；C29- filter；C30- electromagnetism
Valve；E04- gas methane storage tank；D01- safety valve；D02- hand stop valve；D04- filter；D03- filter；D05- is pneumatically cut
Only valve；D06- pressure reducer；D07- pressure sensor；D08- flowmeter；F07- hand stop valve；D09- hand stop valve；D10-
Pressure sensor；D11- temperature sensor；D12- venturi tube；D13- temperature sensor；D14- pressure sensor；D15- electromagnetism
Valve；D16- pneumatic stopping valve；D17- filter；D18- solenoid valve；F02- pressure sensor；F03- temperature sensor；F04- is mixed
Clutch；F06- pressure sensor；F05- temperature sensor；F08- pneumatic stopping valve；F09- pressure sensor；F10- temperature sensing
Device；F11- venturi tube；F12- temperature sensor；F13- pressure sensor；F14- solenoid valve；F15- pneumatic stopping valve；F16- mistake
Filter；F17- solenoid valve；G01- pressure reducer；G03- pressure sensor；G02- pressure reducer；G04- pressure sensor.
Specific embodiment
Technical solution of the present invention is clearly and completely described below in conjunction with attached drawing, it is clear that described implementation
Example is a part of the embodiment of the present invention, instead of all the embodiments.Based on the embodiments of the present invention, ordinary skill
Personnel's every other embodiment obtained without making creative work, shall fall within the protection scope of the present invention.
In the description of the present invention, 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 description the present invention 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 is not considered as limiting the invention.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 invention, 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 as the case may be
Concrete meaning in the present invention.
Embodiment one:
Fig. 1 is the knot for being suitable for large-scale liquid oxygen methane Test System for Rocket Engine Test supply system that the embodiment of the present invention one provides
Structure schematic diagram；As shown in Figure 1, the large-scale liquid oxygen methane Test System for Rocket Engine Test supply that is suitable for that the embodiment of the present invention one provides is
System, pressurization nitrogen are connected by pressure reducer A01 with hand stop valve A02, pressure sensor A03 and hand stop valve A04, institute
Pneumatic stopping valve A05, filter A06, orifice plate A07, temperature sensor A08, pressure biography are sequentially connected with after stating hand stop valve A04
Sensor A09 and liquid oxygen storage tank E01, the liquid oxygen storage tank E01 and solenoid valve A10, hand stop valve A11, safety valve A12 and manually
Shut-off valve A13 is connected, and divides four-way after the hand stop valve A13, is separately connected hand stop valve B04, hand stop valve A14
And filter A15, the hand stop valve A14 are followed by filter A29, are sequentially connected with pneumatic cut-off after the filter A15
Valve A16, flowmeter A17, pressure sensor A18, temperature sensor A19, venturi tube A20, temperature sensor A21 and pressure sensing
Device A22, the pressure sensor A22 are connected with hand stop valve A23, pneumatic stopping valve A24 and pneumatic stopping valve A26, institute
State pneumatic stopping valve A24 and be followed by orifice plate A25, divide threeway after the pneumatic stopping valve A26, one end be sequentially connected with filter A27 and
Solenoid valve A28, the other end connect engine；
Liquid nitrogen storage tank E02 is connected with hand stop valve B01, safety valve B07 and hand stop valve B08, described to cut manually
Only valve B08 is followed by filter B 09, divides four-way after the hand stop valve B01, is separately connected hand stop valve B02, filter
B03 and filter B 05, the filter B 03 are followed by hand stop valve B04, and the filter B 05 is followed by hand stop valve B06；
Pressurization nitrogen is connected by pressure reducer C01 with hand stop valve C02, pressure sensor C03 and hand stop valve C04
Connect, be sequentially connected with after the hand stop valve C04 pneumatic stopping valve C05, filter C06, orifice plate C07, temperature sensor C08,
Pressure sensor C09 and liquid methane storage tank E03, the liquid methane storage tank E03 and solenoid valve C10, hand stop valve C11, safety
Valve C12 is connected with hand stop valve C13, divides four-way after the hand stop valve C13, is separately connected hand stop valve B06, hand
Dynamic shutoff valve C 14 and filter C16, the hand stop valve C14 are followed by filter C15, sequentially connect after the filter C16
Threeway one end is divided to connect hand stop valve F01 after meeting pneumatic stopping valve C17, flowmeter C18, the flowmeter C18, the other end connects
Dynamic shutoff valve C 19 is taken over, is sequentially connected with pressure sensor C20, temperature sensor C21, venturi tube after the hand stop valve C19
C22, temperature sensor C23 and pressure sensor C24, the pressure sensor C24 and hand stop valve C25, pneumatic stopping valve
C26 is connected with pneumatic shutoff valve C 28, and the pneumatic stopping valve C26 is followed by orifice plate C27, divides three after the pneumatic stopping valve C28
Logical, one end is sequentially connected with filter C29 and solenoid valve C30, and the other end connects engine；
Gas methane storage tank E04 is connected with safety valve D01, hand stop valve D02 and filter D04, the manual shutoff
Valve D02 is followed by filter D03, and pneumatic stopping valve D05, pressure reducer D06, pressure sensor are sequentially connected with after the filter D04
Divide threeway after D07 and flowmeter D08, the flowmeter D08, one end connects hand stop valve F07, and the other end connects manual shutoff
Pressure sensor D10, temperature sensor D11, venturi tube D12, temperature is sequentially connected with after valve D09, the hand stop valve D09 to pass
Divide threeway after sensor D13 and pressure sensor D14, the pressure sensor D14, is separately connected solenoid valve D15 and pneumatic cut-off
Divide threeway after valve D16, the pneumatic stopping valve D16, one end is sequentially connected with filter D17 and solenoid valve D18, other end connection hair
Motivation；
Pressure sensor F02, temperature sensor F03 and mixer F04, institute are sequentially connected with after the hand stop valve F01
Pressure sensor F06, temperature sensor F05 and mixer F04, the mixer F04 are sequentially connected with after stating hand stop valve F07
After be sequentially connected with pneumatic stopping valve F08, pressure sensor F09, temperature sensor F10, venturi tube F11, temperature sensor F12 and
Divide threeway after pressure sensor F13, the pressure sensor F13, is separately connected solenoid valve F14 and pneumatic stopping valve F15, it is described
Divide threeway after pneumatic stopping valve F15, one end is sequentially connected with filter F 16 and solenoid valve F17, and the other end connects engine；
The pneumatic stopping valve A05, pneumatic stopping valve A16, pneumatic stopping valve A24, pneumatic stopping valve A26, pneumatic cut-off
Valve C05, pneumatic stopping valve C17, pneumatic stopping valve C26, pneumatic stopping valve C28, pneumatic stopping valve D05, pneumatic stopping valve D16,
Pneumatic stopping valve F08 and pneumatic stopping valve F15 is connect by pressure sensor G03 with pressure reducer G01；
The solenoid valve D18, solenoid valve F17, solenoid valve C30 and solenoid valve A28 pass through pressure sensor G04 and pressure reducer
G02 connection.
It is the manipulation gas for adjusting all pneumatic stopping valves first that the present invention, which carries out thrust chamber independent experiment main working process,
Body pressure, that is, air pressure adjustment guarantees that each pneumatic stopping valve drives required pressure to design value after adjusting pressure reducer G01.Then it adjusts
Fuel and oxidizer pressurizing system are saved, by the air pressure adjustment after pressure reducer A01 to design value, gives liquid oxygen storage tank E01 output medium
Pressure provides guarantee, and the air pressure adjustment after pressure reducer C01 to design value is provided to liquid methane storage tank E03 output medium pressure
Guarantee.The blowoff pressure for finally adjusting test is normal value, the i.e. output pressure of pressure reducer G02.It is also provided in system to liquid
Oxygen storage tank E01 and liquid methane storage tank E03 carries out the pipeline of propellant filling, is directly filled by tank car to it.Specifically
Operating process is as follows:
It before carrying out nitrogen supercharging operation, needs to be filled fuel and oxidant, main mode utilizes tank car
It is filled.For oxidizer systems, hand stop valve A13 is opened, opens hand stop valve A14, liquid oxygen storage tank E01 is carried out
Hand stop valve A13 is closed in filling after filling, close hand stop valve A14 after deflating to residual liquid in pipeline,
So far oxidant storage tank filling finishes.For fuel system, hand stop valve C13 is opened, hand stop valve C14 is opened, to liquid
Methane storage tank E03 is filled, and hand stop valve C13 is closed after filling, is closed after deflating to residual liquid in pipeline
Close hand stop valve C14.In addition gas methane storage tank E04 stowing operation directly open hand stop valve D02 progress, after close
Hand stop valve D02 is so far finished for fuel system filling.In addition liquid nitrogen storage tank E02 stowing operation is directly opened cuts manually
Only valve B08 carry out, after close hand stop valve B08.
During carrying out thrust chamber routine tests, it is necessary first to carry out test preparation, confirmation system is all to cut manually
Only valve and pneumatic stopping valve are in close state, pressure requirements needed for adjusting pressure reducer G01 outlet pressure to pneumatic stopping valve, root
It is indicated according to pressure sensor G03, gas source needed for so far all pneumatic stopping valves is guaranteed.Adjust pressure reducer G02
Indicate that so far pilot system swept-off gases adjust and finish to required blowoff pressure's value according to pressure sensor G04.Then adjust
Pressure reducer A01 makes the required pressure size of output pressure, is indicated by pressure sensor A03, if adjusting wrong output pressure
Deflation pressure release is carried out by opening hand stop valve A02, opens hand stop valve A04 and pneumatic stopping valve A05 later, so far
Oxidizer pressurizing system adjusting finishes.Pressure reducer C01 output pressure is then adjusted to design value, by pressure sensor C03 come
Instruction carries out deflation pressure release by opening hand stop valve C02 if adjusting wrong output pressure, finally opens hand stop valve
C04 and pneumatic shutoff valve C 05, so far low temp fuel pressure charging system adjusting finish, nitrogen partial end of operation.It then turns on pneumatic
Shut-off valve D05, adjusting pressure reducer D06 makes the required pressure size of output pressure, is indicated by pressure sensor D07, until
The adjusting of this gas methane system pressure finishes.The thrust chamber test preparation stage finishes.
During the independent formal test of thrust chamber, precooling process is carried out to pipeline first and is beaten for oxidant transport system
Hand stop valve B01 is opened, hand stop valve B04 is opened, opens pneumatic stopping valve A16, during pre-cooling, needs to open manually
Shut-off valve A23 and pneumatic stopping valve A24, empties the gas generated in precooling process.It is complete to entire pipeline Liquid nitrogen precooler
After finishing, hand stop valve B01 is closed, closes hand stop valve B04, hand stop valve B02 is opened, carries out extra liquid nitrogen deflation
Operation after deflation, closes hand stop valve B02.It closes and opens hand stop valve A13, finish it to liquid oxygen pre-cooling pipeline
Afterwards, hand stop valve A13 is closed, pneumatic stopping valve A16 is closed, closes hand stop valve A23, pneumatic stopping valve A24 is closed, beats
Hand stop valve A14 is opened, surplus liquid bleed air operation is carried out, after deflation, closes hand stop valve A14, so far oxidant
Pre-cooling finishes in pipeline.For low temp fuel transport system, hand stop valve B01 is opened, opens hand stop valve B06, is opened
Pneumatic stopping valve C17 during pre-cooling, needs to open hand stop valve C25 and pneumatic shutoff valve C 26, in precooling process
The gas of generation is emptied.After finishing to entire pipeline Liquid nitrogen precooler, hand stop valve B01 is closed, closes manual shutoff
Valve B06 opens hand stop valve B02, carries out extra liquid nitrogen bleed air operation, after deflation, closes hand stop valve B02.It closes
It closes and opens hand stop valve C13, after being finished to liquid oxygen pre-cooling pipeline, close hand stop valve C13, close pneumatic stopping valve
C17 closes hand stop valve C25, closes pneumatic stopping valve C26, opens hand stop valve C14, carries out surplus liquid deflation behaviour
Make, after deflation, closes hand stop valve C14, be so far pre-chilled and finish in low temp fuel pipeline.In the operation being pre-chilled
In, it needs timely to be monitored the liquid in pipeline according to equipment such as temperature sensor, the pressure sensors at scene.So far
Preparation is finished before thrust chamber is tested.During formal test, the pilot system used according to actual tests is led to
Sequential operation is crossed, pneumatic stopping valve A16, pneumatic stopping valve A26, pneumatic stopping valve C17, pneumatic stopping valve are opened or close
C28, pneumatic stopping valve D05, pneumatic stopping valve D16, pneumatic stopping valve F08 and pneumatic stopping valve F15, the behaviour of this eight valves
Work sequence is controlled by computer timing.After end to be tested, to pipe-line system carry out shutoff operation, be first shut off fuel and
Oxidant transport system, the pilot system used according to actual tests close pneumatic stopping valve A16, pneumatic stopping valve A26, gas
Dynamic shutoff valve C 17, pneumatic stopping valve C28, pneumatic stopping valve D05, pneumatic stopping valve D16, pneumatic stopping valve F08 and pneumatic section
Only valve F15.Opening solenoid valve A28, solenoid valve C30, solenoid valve D18 and solenoid valve F17 carry out nitrogen in pipeline and engine and blow
It removes.It opens pneumatic stopping valve A24, pneumatic stopping valve C26, solenoid valve D15 and solenoid valve F14 and carries out bleed air operation in pipeline, pipe
After liquid cleans out in road, above-mentioned pneumatic stopping valve A24, pneumatic stopping valve C26, solenoid valve D15 and solenoid valve F14 are closed.
Then off nitrogen pressurization system closes pneumatic stopping valve A05, opens hand stop valve A02, solenoid valve A10 and cuts manually
Only valve A11 is pressurized nitrogen pipeline and tank body to oxygen road and carries out pressure release, gas is released finish after, close hand stop valve A02,
Hand stop valve A04, solenoid valve A10 and hand stop valve A11.In addition pneumatic stopping valve C05 is closed, hand stop valve is opened
C02, solenoid valve C10 and hand stop valve C11 carry out pressure release to fuel tank body and fuel nitrogen pressure piping, after pressure release,
Hand stop valve C02, hand stop valve C04, solenoid valve C10 and hand stop valve C11 are closed, so far pressure charging system has been closed
At.To the supply system end of operation of thrust chamber test process.
It is provided by the invention to be suitable for large-scale liquid oxygen methane Test System for Rocket Engine Test supply system, it has the advantages that
Gas methane and liquid methane test share a set of liquid oxygen supply system in large rocket engine test supply system, keep away
Exempt from oxidant supply system repeated construction, reduces cost；
Gas methane and liquid methane can be supplied in supply system simultaneously, carries out the large rocket engine examination of methane gas-liquid blending
It tests, low cost carries out re-generatively cooled engine combustion performance test；
By mixer can stability and high efficiency carry out different methane injection temperatures large rocket engine test；
Cryogenic pipe pre-cooling is carried out using liquid nitrogen in supply system, is had the advantages that safe and at low cost.
Specifically, the liquid oxygen storage tank E01 is high pressure liquid oxygen storage tank.
Specifically, the liquid methane storage tank E03 is high pressure liquid methane storage tank.
Specifically, the gas methane storage tank E04 is high pressure gas methane storage tank.
Specifically, the liquid nitrogen storage tank E02 is low pressure liquid nitrogen storage tank.
Specifically, the pressure of the liquid oxygen storage tank E01 is 10MPa.
Specifically, the pressure of the liquid methane storage tank E03 is 15MPa.
Specifically, the pressure of the gas methane storage tank E04 is 15MPa.
Specifically, the pressure of the liquid nitrogen storage tank E02 is 0.8MPa.
Embodiment two:
Present invention also provides a kind of rockets, including the above-mentioned large size liquid oxygen methane Test System for Rocket Engine Test that is suitable for supply system
System.
Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the present invention., rather than its limitations；To the greatest extent
Pipe present invention has been described in detail with reference to the aforementioned 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, various embodiments of the present invention technology that it does not separate the essence of the corresponding technical solution
The range of scheme.
Claims (10)
1. one kind is suitable for large-scale liquid oxygen methane Test System for Rocket Engine Test supply system, which is characterized in that pressurization nitrogen is by subtracting
Depressor (A01) is connected with hand stop valve (A02), pressure sensor (A03) and hand stop valve (A04), described to cut manually
Pneumatic stopping valve (A05), filter (A06), orifice plate (A07), temperature sensor (A08), pressure are only sequentially connected with after valve (A04)
Sensor (A09) and liquid oxygen storage tank (E01), the liquid oxygen storage tank (E01) and solenoid valve (A10), hand stop valve (A11), peace
Full valve (A12) is connected with hand stop valve (A13), divides four-way after the hand stop valve (A13), is separately connected manual shutoff
Valve (B04), hand stop valve (A14) and filter (A15), the hand stop valve (A14) are followed by filter (A29), institute
Pneumatic stopping valve (A16), flowmeter (A17), pressure sensor (A18), temperature sensor are sequentially connected with after stating filter (A15)
(A19), venturi tube (A20), temperature sensor (A21) and pressure sensor (A22), the pressure sensor (A22) and manually
Shut-off valve (A23), pneumatic stopping valve (A24) are connected with pneumatic stopping valve (A26), and the pneumatic stopping valve (A24) is followed by hole
Plate (A25) divides threeway after the pneumatic stopping valve (A26), and one end is sequentially connected with filter (A27) and solenoid valve (A28), another
End connection engine；
Liquid nitrogen storage tank (E02) is connected with hand stop valve (B01), safety valve (B07) and hand stop valve (B08), the hand
Dynamic shut-off valve (B08) is followed by filter (B09), is divided four-way after the hand stop valve (B01), is separately connected hand stop valve
(B02), filter (B03) and filter (B05), the filter (B03) are followed by hand stop valve (B04), the filter
(B05) it is followed by hand stop valve (B06)；
It is pressurized nitrogen and passes through pressure reducer (C01) and hand stop valve (C02), pressure sensor (C03) and hand stop valve (C04)
It is connected, pneumatic stopping valve (C05), filter (C06), orifice plate (C07), temperature is sequentially connected with after the hand stop valve (C04)
Spend sensor (C08), pressure sensor (C09) and liquid methane storage tank (E03), the liquid methane storage tank (E03) and solenoid valve
(C10), hand stop valve (C11), safety valve (C12) are connected with hand stop valve (C13), the hand stop valve (C13)
After divide four-way, be separately connected hand stop valve (B06), hand stop valve (C14) and filter (C16), the manual shutoff
Valve (C14) is followed by filter (C15), and pneumatic stopping valve (C17), flowmeter (C18) are sequentially connected with after the filter (C16),
Threeway one end is divided to connect hand stop valve (F01) after the flowmeter (C18), the other end connects hand stop valve (C19), described
Pressure sensor (C20), temperature sensor (C21), venturi tube (C22), temperature sensing are sequentially connected with after hand stop valve (C19)
Device (C23) and pressure sensor (C24), the pressure sensor (C24) and hand stop valve (C25), pneumatic stopping valve (C26)
It is connected with pneumatic stopping valve (C28), the pneumatic stopping valve (C26) is followed by orifice plate (C27), the pneumatic stopping valve (C28)
After divide threeway, one end is sequentially connected with filter (C29) and solenoid valve (C30), and the other end connects engine；
Gas methane storage tank (E04) is connected with safety valve (D01), hand stop valve (D02) and filter (D04), described manual
Shut-off valve (D02) is followed by filter (D03), is sequentially connected with pneumatic stopping valve (D05), pressure reducer after the filter (D04)
(D06), pressure sensor (D07) and flowmeter (D08), threeway is divided after the flowmeter (D08), and one end connects hand stop valve
(F07), other end connection hand stop valve (D09), be sequentially connected with after the hand stop valve (D09) pressure sensor (D10),
Temperature sensor (D11), venturi tube (D12), temperature sensor (D13) and pressure sensor (D14), the pressure sensor
(D14) divide threeway after, be separately connected solenoid valve (D15) and pneumatic stopping valve (D16), the pneumatic stopping valve (D16) divides three afterwards
Logical, one end is sequentially connected with filter (D17) and solenoid valve (D18), and the other end connects engine；
Pressure sensor (F02), temperature sensor (F03) and mixer are sequentially connected with after the hand stop valve (F01)
(F04), pressure sensor (F06), temperature sensor (F05) and mixer are sequentially connected with after the hand stop valve (F07)
(F04), pneumatic stopping valve (F08), pressure sensor (F09), temperature sensor are sequentially connected with after the mixer (F04)
(F10), venturi tube (F11), temperature sensor (F12) and pressure sensor (F13), the pressure sensor (F13) divide three afterwards
It is logical, it is separately connected solenoid valve (F14) and pneumatic stopping valve (F15), divides threeway after the pneumatic stopping valve (F15), one end is sequentially
Filter (F16) and solenoid valve (F17) are connected, the other end connects engine；
It is the pneumatic stopping valve (A05), pneumatic stopping valve (A16), pneumatic stopping valve (A24), pneumatic stopping valve (A26), pneumatic
Shut-off valve (C05), pneumatic stopping valve (C17), pneumatic stopping valve (C26), pneumatic stopping valve (C28), pneumatic stopping valve (D05),
Pneumatic stopping valve (D16), pneumatic stopping valve (F08) and pneumatic stopping valve (F15) pass through pressure sensor (G03) and pressure reducer
(G01) it connects；
The solenoid valve (D18), solenoid valve (F17), solenoid valve (C30) and solenoid valve (A28) by pressure sensor (G04) with
Pressure reducer (G02) connection.
2. according to claim 1 be suitable for large-scale liquid oxygen methane Test System for Rocket Engine Test supply system, which is characterized in that
The liquid oxygen storage tank (E01) is high pressure liquid oxygen storage tank.
3. according to claim 1 be suitable for large-scale liquid oxygen methane Test System for Rocket Engine Test supply system, which is characterized in that
The liquid methane storage tank (E03) is high pressure liquid methane storage tank.
4. according to claim 1 be suitable for large-scale liquid oxygen methane Test System for Rocket Engine Test supply system, which is characterized in that
The gas methane storage tank (E04) is high pressure gas methane storage tank.
5. according to claim 1 be suitable for large-scale liquid oxygen methane Test System for Rocket Engine Test supply system, which is characterized in that
The liquid nitrogen storage tank (E02) is low pressure liquid nitrogen storage tank.
6. according to claim 2 be suitable for large-scale liquid oxygen methane Test System for Rocket Engine Test supply system, which is characterized in that
The pressure of the liquid oxygen storage tank (E01) is 10MPa.
7. according to claim 3 be suitable for large-scale liquid oxygen methane Test System for Rocket Engine Test supply system, which is characterized in that
The pressure of the liquid methane storage tank (E03) is 15MPa.
8. according to claim 4 be suitable for large-scale liquid oxygen methane Test System for Rocket Engine Test supply system, which is characterized in that
The pressure of the gas methane storage tank (E04) is 15MPa.
9. according to claim 5 be suitable for large-scale liquid oxygen methane Test System for Rocket Engine Test supply system, which is characterized in that
The pressure of the liquid nitrogen storage tank (E02) is 0.8MPa.
10. a kind of rocket, which is characterized in that be suitable for large-scale liquid oxygen methane fire including of any of claims 1-9
Arrow engine test supply system.
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| CN201811180265.9A CN109083768B (en) | 2018-10-10 | 2018-10-10 | Supply system suitable for large-scale liquid oxygen methane rocket engine test and rocket |
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| CN109737829A (en) * | 2019-01-31 | 2019-05-10 | 北京蓝箭空间科技有限公司 | Rocket liquid tank propellant transfer system and carrier rocket |
| CN109916630A (en) * | 2019-03-27 | 2019-06-21 | 中南大学 | Engine supply system and its removable integration test platform |
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| CN112360646B (en) * | 2020-09-02 | 2023-06-23 | 航天科工火箭技术有限公司 | Low-temperature rocket engine, turbine pump and bearing cooling structure thereof |
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| CN113446133A (en) * | 2021-08-30 | 2021-09-28 | 西安航天动力研究所 | Ground screening test device and test method for oxygen-enriched methane-rich gas injection unit |
| CN113790110A (en) * | 2021-11-16 | 2021-12-14 | 西安空天引擎科技有限公司 | Integrated liquid flow test system for rocket engine |
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| CN114739055B (en) * | 2022-04-11 | 2022-12-06 | 西安交通大学 | Liquid oxygen/liquid methane comprehensive supercooling system and method based on liquid oxygen refrigeration capacity |
| CN114739055A (en) * | 2022-04-11 | 2022-07-12 | 西安交通大学 | Liquid oxygen/liquid methane comprehensive supercooling system and method based on liquid oxygen refrigeration capacity |
| CN115384818A (en) * | 2022-08-25 | 2022-11-25 | 北京航天试验技术研究所 | Mars surface methane propellant in-situ preparation environment simulation device and method thereof |
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