CN109538379A - High thrust liquid rocket engine thrust chamber experimental rig and method - Google Patents
High thrust liquid rocket engine thrust chamber experimental rig and method Download PDFInfo
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- CN109538379A CN109538379A CN201910006049.0A CN201910006049A CN109538379A CN 109538379 A CN109538379 A CN 109538379A CN 201910006049 A CN201910006049 A CN 201910006049A CN 109538379 A CN109538379 A CN 109538379A
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- 239000007788 liquid Substances 0.000 title claims abstract description 64
- 238000000034 method Methods 0.000 title claims abstract description 33
- 239000000446 fuel Substances 0.000 claims abstract description 346
- 239000007800 oxidant agent Substances 0.000 claims abstract description 255
- 230000001590 oxidative effect Effects 0.000 claims abstract description 184
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims abstract description 119
- 239000001301 oxygen Substances 0.000 claims abstract description 119
- 229910052760 oxygen Inorganic materials 0.000 claims abstract description 119
- 238000006243 chemical reaction Methods 0.000 claims abstract description 10
- 238000010998 test method Methods 0.000 claims description 25
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 14
- 239000007789 gas Substances 0.000 claims description 13
- 238000002485 combustion reaction Methods 0.000 claims description 12
- 239000003795 chemical substances by application Substances 0.000 claims description 9
- 229910052757 nitrogen Inorganic materials 0.000 claims description 7
- 239000012535 impurity Substances 0.000 claims description 6
- 230000003647 oxidation Effects 0.000 claims description 4
- 238000007254 oxidation reaction Methods 0.000 claims description 4
- 238000007664 blowing Methods 0.000 claims description 3
- 238000001914 filtration Methods 0.000 claims 2
- 238000012360 testing method Methods 0.000 description 43
- 239000003380 propellant Substances 0.000 description 32
- 230000008569 process Effects 0.000 description 14
- 238000010586 diagram Methods 0.000 description 12
- 238000009423 ventilation Methods 0.000 description 11
- 238000013461 design Methods 0.000 description 6
- 239000000463 material Substances 0.000 description 6
- 238000002679 ablation Methods 0.000 description 5
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 5
- 239000012530 fluid Substances 0.000 description 4
- 238000010926 purge Methods 0.000 description 4
- 230000007423 decrease Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 238000002474 experimental method Methods 0.000 description 3
- 239000000945 filler Substances 0.000 description 3
- 239000000047 product Substances 0.000 description 3
- 230000007704 transition Effects 0.000 description 3
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 229920006395 saturated elastomer Polymers 0.000 description 2
- 230000000903 blocking effect Effects 0.000 description 1
- 239000000306 component Substances 0.000 description 1
- 238000009833 condensation Methods 0.000 description 1
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- 238000012790 confirmation Methods 0.000 description 1
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- 239000008358 core component Substances 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 239000003721 gunpowder Substances 0.000 description 1
- 239000010763 heavy fuel oil Substances 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 150000002431 hydrogen Chemical class 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Natural products C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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- 239000013589 supplement Substances 0.000 description 1
- 229940126680 traditional chinese medicines Drugs 0.000 description 1
Classifications
-
- 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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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Testing Of Engines (AREA)
Abstract
It includes: thrust chamber that the present invention, which provides a kind of high thrust liquid rocket engine thrust chamber experimental rig and method, device, for providing place for oxidant and fuel reaction；Igniter is arranged in thrust chamber oxidant feed end, for triggering oxidant and fuel reaction；Oxygen bypass, setting supply oxidant to thrust chamber in thrust chamber oxidant feed end, for igniter fire startup stage；Oxygen main road, setting supply oxidant to the thrust chamber together with oxygen bypass after running well for thrust chamber in thrust chamber oxidant feed end；Fuel bypass, setting supply fuel to thrust chamber in the thrust chamber fuel feed end, for igniter fire startup stage；Fuel main road, setting supply fuel to thrust chamber together with fuel bypass after running well for thrust chamber in thrust chamber fuel feed end.The present invention can reduce thrust chamber and start risk, really, accurately obtains the performance data of thrust chamber, shortens thrust chamber and reseach of engine period.
Description
Technical field
It is specific next the present invention relates to liquid-propellant rocket engine field, especially liquid rocket engine thrust chamber test method
Say exactly a kind of high thrust liquid rocket (more than 10 tonnes (containing)) motor power room experimental rig and method.
Background technique
Core component one of of the thrust chamber as liquid-propellant rocket engine, performance and reliability greatly influence engine
The flight safety of complete machine and vehicle, therefore, the design and test of thrust chamber are that liquid-propellant rocket engine is developed in countries in the world
Important link.
In the prior art, liquid rocket engine thrust chamber test is generally carried out using squeeze test scheme, into thrust
The oxidant and fuel of room are single channel supply, and propellant flow rate is mainly controlled by controlling inlet pressure and the temperature of cavitation venturi
System.This method is mainly used in the test run of low thrust magnitude liquid rocket engine thrust chamber at present, and (test run refers to test specimen
The test running carried out before coming into operation or producing, it is therefore an objective to examine whether the indexs such as its precision, performance, reliability reach technology
Performance requirement).For high thrust liquid-propellant rocket engine, both at home and abroad there are mainly two types of current test methods, one is progress
The squeeze test of reduced scale part；Another kind is to carry out squeeze test using full-scale part.The principle of both test methods with it is existing
Low thrust magnitude thrust chamber is identical.
Country's current version high thrust liquid rocket engine thrust chamber is all made of reduced scale part and is tested at present, that is, uses
The reduced scale part that one or several nozzles (basic unit that nozzle is thrust chamber ejector filler) are constituted is tested, which can
Preferably to verify the performance of thrust chamber nozzle, but large number of nozzle arrangement and distribution form cannot be accurately reflected to pushing away
The influence of power room ejector filler overall performance；Simultaneously because reduced scale part and actual product the structure difference in terms of size and heat exchange area
Huge, the test of reduced scale part can not accurately reflect whether the design of thrust chamber cooling structure is able to satisfy requirement, therefore thrust
Room using this test method early stage seldom exposure Rocket Engine Combustion Chamber Design in there may be the problem of, only when thrust chamber deliver send out
Relevant issues can just be exposed when motivation carries out complete machine test run, this virtually extends the engine complete machine development time.
The full-scale thrust chamber test method of high thrust liquid-propellant rocket engine, usually thrust chamber across-the-line starting to test work
Condition, this starting method to the reliability of thrust chamber ejector filler original design, thrust chamber igniting sequential and test run valve one
The requirement of cause property is very high, and flow supply and igniting sequential control are bad, easily causes thrust chamber ablation or burn-through in starting process,
Thrust chamber explosion may occur when serious during starting ignition, empirical risk is high.
Therefore, those skilled in the art need to research and develop a kind of high thrust liquid rocket engine thrust chamber test method, drop
Low-thrust room starts risk, really, accurately obtains the performance data of thrust chamber, shortens thrust chamber and reseach of engine period.
Summary of the invention
In view of this, the technical problem to be solved in the present invention is that providing a kind of high thrust liquid rocket engine thrust chamber
Experimental rig and method, when solving high thrust liquid rocket engine thrust chamber test in the prior art, empirical risk is high, nothing
Method is true, accurately obtains the performance data of thrust chamber, the problem of thrust chamber and reseach of engine period length.
In order to solve the above-mentioned technical problem, a specific embodiment of the invention provides a kind of high thrust liquid-propellant rocket engine
Thrust chamber experimental rig, comprising: thrust chamber, for providing place for oxidant and fuel reaction；Igniter, setting are pushed away described
Power room oxidant feed end, for triggering oxidant and fuel reaction；Oxygen bypass, setting are supplied in the thrust chamber oxidant
Oxidant is supplied to the thrust chamber for the igniter fire startup stage in end；Oxygen main road is arranged in the thrust chamber oxygen
Agent feed end supplies oxidant to the thrust chamber together with oxygen bypass after running well for the thrust chamber；Combustion
Material bypass, setting are supplied for the igniter fire startup stage to the thrust chamber in the thrust chamber fuel feed end
Fuel；Fuel main road, setting is in the thrust chamber fuel feed end, after running well for the thrust chamber and by the fuel
Fuel is supplied to the thrust chamber together in road.
A specific embodiment of the invention also provides a kind of high thrust liquid rocket engine thrust chamber test method, packet
Include: the high-temperature gas that igniter generates enters thrust chamber；The second oxidizer valve is opened, oxidant begins through oxygen and bypasses into institute
State thrust chamber；The second fuel valve is opened, fuel begins through fuel bypass into the thrust chamber；The first fuel valve is opened, is fired
Expect while the thrust chamber is entered by fuel main road and the fuel bypass；The first oxidizer valve is opened, oxidant leads to simultaneously
Peroxide main road and the oxygen bypass into the thrust chamber.
Above-mentioned specific embodiment according to the present invention it is found that high thrust liquid rocket engine thrust chamber experimental rig and
Method at least has the advantages that on the basis of thrust chamber conventional extruded test run scheme, in thrust chamber oxidant and combustion
Bypass and main road is respectively set in material supply road；The cavitation venturi for controlling flow is provided in bypass and main road；In main road
One is each provided between bypass for controlling the shut-off valve of main road flow supply.Work is in primary when thrust chamber starting ignition
Operating condition, at this time only bypass；Main road oxidant and fuel supply are opened after the completion of starting, thrust chamber is transferred to master by primary operating condition
Grade operating condition, under main work condition state, bypass and main road are worked at the same time.
The empirical risk of thrust chamber can be greatly reduced using step start scheme；Using oxygen-enriched ignition timing and igniter stream
Measure accounting, it can be ensured that thrust chamber is reliable, steadily lights a fire；Thrust chamber is in starting ignition process without obvious impact；Using turning grade timing,
It can ensure that thrust chamber from primary operating condition to main operating condition quick and stable transition；Using shutdown timing, it can be ensured that thrust chamber is safe, flat
Steady shutdown, while avoiding ablation in shutdown process.In addition, thrust chamber starting ignition timing in this programme, turning grade timing and pass
Machine timing etc. can be directly used for liquid-propellant rocket engine complete machine test run.
It is to be understood that above-mentioned general description and following specific embodiments are merely illustrative and illustrative, not
The range of the invention to be advocated can be limited.
Detailed description of the invention
Following appended attached drawing is part of specification of the invention, depicts example embodiments of the present invention, institute
Attached drawing is used to illustrate the principle of the present invention together with the description of specification.
Fig. 1 is a kind of high thrust liquid rocket engine thrust chamber experimental rig that the specific embodiment of the invention provides
The structural schematic diagram of embodiment one.
Fig. 2 is a kind of high thrust liquid rocket engine thrust chamber experimental rig that the specific embodiment of the invention provides
The structural schematic diagram of embodiment two.
Fig. 3 is the structural schematic diagram that a kind of oxidant high pressure that the specific embodiment of the invention provides releases pipeline.
Fig. 4 is the structural schematic diagram that a kind of fuel high pressure that the specific embodiment of the invention provides releases pipeline.
Fig. 5 is a kind of high thrust liquid rocket engine thrust chamber experimental rig that the specific embodiment of the invention provides
The structural schematic diagram of embodiment three.
Fig. 6 is a kind of high thrust liquid rocket engine thrust chamber experimental rig that the specific embodiment of the invention provides
The structural schematic diagram of example IV.
Fig. 7 is a kind of high thrust liquid rocket engine thrust chamber test method that the specific embodiment of the invention provides
The flow chart of embodiment one.
Fig. 8 is a kind of high thrust liquid rocket engine thrust chamber test method that the specific embodiment of the invention provides
The flow chart of embodiment two.
Fig. 9 is a kind of high thrust liquid rocket engine thrust chamber test method that the specific embodiment of the invention provides
The flow chart of embodiment three.
Figure 10 is a kind of high thrust liquid rocket engine thrust chamber test method that the specific embodiment of the invention provides
Example IV flow chart.
Description of symbols:
1 thrust chamber, 2 igniter
3 oxygen bypass 4 oxygen main roads
5 fuel bypass, 6 fuel main road
7 oxidants release 701 oxidant of pipeline and release valve
8 oxidants blow down 9 fuel of check valve and release pipeline
901 fuel release 10 fuel of valve and blow down check valve
23 oxidant high pressures release 2301 oxidant high pressure of pipeline and release valve
2302 oxidant high pressures release 24 fuel high pressure of throttle and release pipeline
2401 fuel high pressures release 2402 fuel high pressure of valve and release throttle
11 first oxidizer valve, 12 first fuel valve
13 second oxidizer valve, 14 second fuel valve
15 oxidant supply line, 16 oxidizer filter
17 fuel supply conduit, 18 fuel filter
19 oxygen bypass 20 oxygen main road cavitation venturi of cavitation venturi
21 fuel bypass cavitation venturi, 22 fuel main road cavitation venturi
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.
It include " two " and " two or more " about " multiple " herein；It include " two groups " about " multiple groups " herein
And " more than two ".
About term used herein " substantially ", " about " etc., to modify it is any can 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.
Fig. 1 is a kind of high thrust liquid rocket engine thrust chamber experimental rig that the specific embodiment of the invention provides
The structural schematic diagram of embodiment one, as shown in Figure 1, lighting a fire in the setting oxygen bypass of thrust chamber oxidant feed end and oxygen main road
Startup stage (primary operating condition), only aerobic bypass to thrust chamber supplied oxidant, in thrust chamber normal operation (main operating condition or volume
Determine operating condition) after, oxygen bypass and oxygen main road supply oxidant to thrust chamber simultaneously；In thrust chamber fuel feed end, fuel bypass is set
With fuel main road, only has fuel bypass in igniting startup stage (primary operating condition) and supply fuel to thrust chamber, it is normal in thrust chamber
After operating (main operating condition), fuel bypass and fuel main road supply fuel to thrust chamber simultaneously.
In the specific embodiment shown in the drawings, high thrust liquid rocket engine thrust chamber experimental rig includes: to push away
Power room 1, igniter 2, oxygen bypass 3, oxygen main road 4, fuel bypass 5 and fuel main road 6.Wherein, thrust chamber 1 be used for for oxidant with
Fuel reaction provides place；The setting of igniter 2 in the 1 oxidant feed end of thrust chamber, igniter 2 for trigger oxidant with
Fuel reaction, when igniter 2 is according to pyrophoric ignition or torch ignition, igniting gas flow is 1 metered flow of thrust chamber
0.1%~1.5%, it can be ensured that thrust chamber 1 is reliable, steadily lights a fire, and thrust chamber 1 is in starting ignition process without obvious impact；By oxygen
For the setting of road 3 in the 1 oxidant feed end of thrust chamber, oxygen bypass 3 is used for the igniter 2 igniting startup stage to the thrust
Oxidant is supplied in room 1；For the setting of oxygen main road 4 in the 1 oxidant feed end of thrust chamber, oxygen main road 4 is normal for the thrust chamber 1
Oxidant is supplied to the thrust chamber 1 together with oxygen bypass 3 after operating；Fuel bypass 5 is arranged in 1 fuel of thrust chamber
Feed end, fuel bypass 5 supply fuel to the thrust chamber 1 for the igniter 2 igniting startup stage；Fuel main road 6 is set
It sets in the 1 fuel feed end of thrust chamber, fuel main road 6 is used for after the thrust chamber 1 runs well and the fuel bypass 5 one
It rises to the thrust chamber 1 and supplies fuel.Preferably, the flow of the oxidant or fuel of primary operating condition is the oxidant of declared working condition
Or the flow 10%~65% of fuel.Pyrophoric ignition, torch ignition and plasma ignition etc. can be used in igniter 2, when using fire
When snack made with traditional Chinese medicines fire and torch ignition scheme, 2 flow of igniter should control thrust chamber declared working condition propellant flow rate 0.1%~
1.5%, to ensure 1 reliable ignition of thrust chamber, while guaranteeing that the work of thrust chamber 1 is flat when igniter 2 and thrust chamber 1 work together
Surely.
Referring to fig. 2, (10 tonnes or more) of high thrust liquid rocket engine thrust chamber tests are realized, stepped starting can drop
Low-thrust room 1 starts risk, and performance data that is true, accurately obtaining thrust chamber 1 shortens thrust chamber 1 and reseach of engine week
Phase.
Fig. 2 is a kind of high thrust liquid rocket engine thrust chamber experimental rig that the specific embodiment of the invention provides
The structural schematic diagram of embodiment two, as shown in Fig. 2, releasing pipeline and oxidant in thrust chamber oxidant feed end setting oxidant
Check valve is blown down, remaining oxidant in the bypass of blow-line purging's oxygen and oxygen main road is released by oxidant；It is supplied in thrust chamber fuel
Setting fuel should be held to release pipeline and fuel blowing check valve, released in blow-line purging's fuel bypass and fuel main road by fuel
Remaining fuel.
In the specific embodiment shown in the drawings, high thrust liquid rocket engine thrust chamber experimental rig further include:
Oxidant releases pipeline 7, oxidant blows down check valve 8, fuel releases pipeline 9 and fuel blows down check valve 10.Wherein, oxidant
It releases pipeline 7 to be arranged in the 1 oxidant feed end of thrust chamber, oxidant releases pipeline 7 for releasing the oxygen bypass 3 and institute
State remaining oxidant in oxygen main road 4, wherein the oxidant, which releases, to be provided with oxidant and release valve 701 on pipeline 7；Oxidation
Agent blows down the setting of check valve 8 in the 1 oxidant feed end of thrust chamber, and oxidant blows down check valve 8 and is used to the oxygen bypassing 3
Pipeline 7 is released by the oxidant with remaining oxidant in the oxygen main road 4 to blow down；Fuel releases pipeline 9 and is arranged in institute
1 fuel feed end of thrust chamber is stated, it is remaining in the fuel bypass 5 and the fuel main road 6 for releasing that fuel releases pipeline 9
Fuel, wherein the fuel, which releases, to be provided with fuel and release valve 901 on pipeline 9；Fuel blows down the setting of check valve 10 and pushes away described
1 fuel feed end of power room, fuel blow down check valve 10 and are used for remaining combustion in the fuel bypass 5 and the fuel main road 6
Material releases pipeline 9 by the fuel and blows down.Preferably for cryogenic propellant, oxidant blows down check valve 8 and fuel is blown down
Check valve 10 can also prevent from propellant (oxidant and fuel) precooling process aqueous vapor instead to soak icing causing valve clamping stagnation and spray
Mouth blocking.
Referring to fig. 2, after the completion of test run experiment, 1 oxidant feed end of thrust chamber stops supply oxidant (such as oxygen etc.),
Remaining oxidant in the bypass of blow-line purging's oxygen and oxygen main road is released by oxidant, reducing oxygen road water hammer (is having pressure pipe
In road, there is a phenomenon where the pressure caused by change dramatically to fluctuate widely referred to as water attack for fluid flow rate)；1 fuel of thrust chamber supplies
Stopping supply fuel should be held, remaining fuel in blow-line purging's fuel bypass and fuel main road is released by fuel, reduces fuel
Road water hammer, it can be ensured that thrust chamber safety, steady shutdown, while avoiding ablation in shutdown process.
Fig. 3 is the structural schematic diagram that a kind of oxidant high pressure that the specific embodiment of the invention provides releases pipeline；Fig. 4 is
The structural schematic diagram that a kind of fuel high pressure that the specific embodiment of the invention provides releases pipeline works as thrust as shown in Figure 3, Figure 4
When propellant used in room (oxidant and fuel) is cryogenic propellant (such as liquid oxygen liquid hydrogen, liquid oxygen methane cryogenic propellant),
Existing low pressure releases on the basis of pipeline that a high pressure in parallel releases pipeline again, prevents the decline of propellant tank liquid level very fast, shadow
Ring thrust chamber test period.
In the specific embodiment shown in the drawings, high thrust liquid rocket engine thrust chamber experimental rig further includes oxygen
Agent high pressure releases pipeline 23 and fuel high pressure releases pipeline 24.Wherein, oxidant high pressure releases pipeline 23 and the oxidant
It releases pipeline 7 to be connected in parallel, oxidant high pressure releases pipeline 23 for releasing the oxygen in the oxygen bypass 3 and the oxygen main road 4
Agent, wherein the oxidant high pressure, which is released, is provided with that oxidant high pressure releases valve 2301 and oxidant high pressure is let out on pipeline 23
Throttle 2302 out；Fuel high pressure, which releases pipeline 24 and releases pipeline 9 with the fuel, to be connected in parallel, and fuel high pressure releases pipeline 24
For releasing the fuel in the fuel bypass 5 and the fuel main road 6, wherein the fuel high pressure releases to be set on pipeline 24
It is equipped with that fuel high pressure releases valve 2401 and fuel high pressure releases throttle 2402.Before test run, only opens oxidant high pressure and let out
Valve 2301 and fuel high pressure release valve 2401 out, and oxidant high pressure releases the flow that releases that throttle 2302 controls oxidant, combustion
Material high pressure, which releases throttle 2402 and controls fuel, releases flow.
Referring to fig. 4, during pressurization and high pressure are stood, temperature can increase cryogenic propellant, when to guarantee test run
Cavitation venturi inlet temperature conditions can be again turned on propellant at this time and release valve, reduce cavitation venturi inlet temperature by overcurrent.If only
Setting low pressure releases pipeline, and since cavitation venturi inlet pressure is higher before test run, low pressure releases pipeline without restricting element, and low pressure is released
After valve is opened, flow is released equal to cavitation venturi flow, it is big that propellant releases flow, and cause the decline of propellant tank liquid level very fast,
Influence thrust chamber test period；When liquid level decline is excessive, the operation such as propellant supplement is also carried out again, seriously affects test
Efficiency simultaneously increases experimentation cost.And on the basis of low pressure releases pipeline, increasing high pressure releases pipeline, only opens before test run high
Pressure releases valve, and the flow that releases of propellant is mainly controlled by throttle at this time, releases flow and lets out much smaller than the low pressure without throttle
Thus pipeline out achievees the purpose that extend thrust chamber time installation and improves test efficiency.
Fig. 5 is a kind of high thrust liquid rocket engine thrust chamber experimental rig that the specific embodiment of the invention provides
The structural schematic diagram of embodiment three, as shown in figure 5, the first oxidizer valve and the first fuel valve control thrust chamber from primary operating condition to
Main operating condition turns grade, or turns grade from main operating condition to primary operating condition；Second oxidizer valve and the second fuel valve control propellant
Whether thrust chamber is entered.
In the specific embodiment shown in the drawings, high thrust liquid rocket engine thrust chamber experimental rig further includes
One oxidizer valve 11, the first fuel valve 12, the second oxidizer valve 13 and the second fuel valve 14.Wherein, the first oxidizer valve 11 is set
It sets between oxygen bypass 3 and the oxygen main road 4, the first oxidizer valve 11 is for controlling the oxygen main road 4 to the thrust
Oxidant is supplied in room 1；First fuel valve 12 is arranged between the fuel bypass 5 and the fuel main road 6, the first fuel valve 12
Fuel is supplied to the thrust chamber 1 for controlling the fuel main road 6；The setting of second oxidizer valve 13 bypasses 3 Hes in the oxygen
Between the thrust chamber 1, the second oxidizer valve 13 is supplied for controlling the oxygen bypass 3 and the oxygen main road 4 to the thrust chamber 1
Answer oxidant, wherein the oxygen bypass 3 is connected at the 1 oxidant feed end of thrust chamber with the oxygen main road 4；Second combustion
Expect valve 14 be arranged between the fuel main road 6 and the thrust chamber 1, the second fuel valve 14 for control the fuel bypass and
The fuel main road supplies fuel to the thrust chamber, wherein the fuel bypass 5 and the fuel main road 6 are in the thrust
It is connected at 1 fuel feed end of room.
Further, thrust chamber test is when turning grade to main operating condition from primary operating condition, 12 opening time of the first fuel valve compared with
Early 0.02~the 1s of first oxidizer valve, 11 opening time；When thrust chamber test turns grade to primary operating condition from main operating condition, the first combustion
Expect 12 shut-in time of valve compared with the first oxidizer valve 11 evening shut-in time, 0.02~1s；When thrust chamber test shutdown, the second oxidant
0.05~the 1s early compared with 14 shut-in time of the second fuel valve of valve 13.
For the thrust chamber 1 (i.e. the ratio between oxidant and fuel mass flow rates are lower than stoichiometric ratio) of oxygen-enriched combusting, turn grade
Process and shutdown process valve event timing are on the contrary, when i.e. thrust chamber turns grade to main operating condition from primary operating condition, the first fuel valve
12 compared with 11 opening time 0.02~1s of evening of the first oxidizer valve；When turning grade to primary operating condition from main operating condition, the first fuel valve 12
0.02~1s early compared with 11 shut-in time of the first oxidizer valve；When shutdown, when the second fuel valve 14 shuts down compared with the second oxidizer valve 13
Between early 0.05~1s.Oxygen-enriched ignition timing and igniter flow accounting, it can be ensured that thrust chamber 1 is reliable, steadily lights a fire；Thrust chamber 1
In starting ignition process without obvious impact.
Referring to Fig. 5, turn grade timing, it can be ensured that thrust chamber 1 is from primary operating condition to main operating condition quick and stable transition；When shutdown
Sequence, it can be ensured that 1 safety of thrust chamber, steady shutdown, while avoiding ablation in shutdown process；And 1 starting ignition timing of thrust chamber,
Turning grade timing and shutdown timing etc. can be directly used for liquid-propellant rocket engine complete machine test run.
Fig. 6 is a kind of high thrust liquid rocket engine thrust chamber experimental rig that the specific embodiment of the invention provides
The structural schematic diagram of example IV, as shown in fig. 6, oxidizer filter is filtered through in the oxidant of oxidant supply line
Impurity, fuel filter are filtered through the impurity in the fuel of fuel supply conduit.Cavitation venturi controls propellant (oxidant and combustion
Material) flow.
In the specific embodiment shown in the drawings, high thrust liquid rocket engine thrust chamber experimental rig further include:
Oxidant supply line 15, oxidizer filter 16, fuel supply conduit 17, fuel filter 18, oxygen bypass cavitation venturi 19, oxygen
Main road cavitation venturi 20, fuel bypass cavitation venturi 21 and fuel main road cavitation venturi 22.Wherein, oxidant supply line 15 and the oxygen
3 connection of bypass, oxidant supply line 15 are used to give oxygen bypass 3 supply oxidant；Oxidizer filter 16 is arranged in institute
It states on oxidant supply line 15, oxidizer filter 16 is used to filter the impurity in oxidant；Fuel supply conduit 17 and institute
The connection of fuel bypass 5 is stated, fuel supply conduit 17 is used to supply fuel to the fuel bypass 5；The setting of fuel filter 18 exists
In the fuel supply conduit 17, fuel filter 18 is used to filter the impurity in fuel；Oxygen bypasses cavitation venturi 19 and is arranged in institute
It states in oxygen bypass 3, oxygen bypass cavitation venturi 19 is used to control the flow of oxidant in the oxygen bypass 3；Oxygen main road cavitation venturi 20 is set
It sets on the oxygen main road 4, oxygen main road cavitation venturi 20 is used to control the flow of oxidant in the oxygen main road 4；Fuel bypass gas
It loses pipe 21 to be arranged on the fuel bypass 5, fuel bypass cavitation venturi 21 is used to control the stream of fuel in the fuel bypass 5
Amount；Fuel main road cavitation venturi 22 is arranged on the fuel main road 6, and fuel main road cavitation venturi 22 is for controlling the fuel main road
The flow of fuel in 6.The primary operating condition propellant flow rate of thrust chamber 1 is the 10%~65% of declared working condition propellant flow rate, thrust
Bigger, primary operating condition flow accounting is smaller；Thrust is smaller, and flow accounting is bigger.
Further, oxidizer filter 16 and fuel filter 18 are all made of 70 μm and filter screen filtration below, prevent
Only the fifth wheel in propellant causes valve clamping stagnation or other failures.Oxygen bypasses cavitation venturi 19, oxygen main road cavitation venturi 20, by fuel
Road cavitation venturi 21 and the processing of 22 inner mold face of fuel main road cavitation venturi and test can refer to aerospace standard QJ1783A-96 " liquid fire
Arrow engine cavitation Venturi tube general specification " it executes.
Preferably, oxidant or fuel flow rate can be by formulaIt is calculated.Wherein, public
In formulaFor liquid mass flow；CdIt for cavitation venturi discharge coefficient, is obtained by cavitation venturi liquid flow test, d is discharge first
Letter；A is cavitation venturi throat circulation area；ρ is fluid density；piFor cavitation venturi inlet fluid pressures, the head that i is inlet is first
Letter；psFor the saturated with fluid vapour pressure under corresponding temperature, s is the initial of saturated.
Referring to Fig. 6, step start scheme can be greatly reduced the empirical risk of thrust chamber 1,1 starting ignition timing of thrust chamber,
Turning grade timing and shutdown timing etc. can be directly used for liquid-propellant rocket engine complete machine test run.
Fig. 7 is a kind of high thrust liquid rocket engine thrust chamber test method that the specific embodiment of the invention provides
The flow chart of embodiment one, method as shown in Figure 7 can be applied in device shown in FIG. 1 to FIG. 6, and igniter is powered, high
Wet body enters thrust chamber, opens the second oxidizer valve and the second fuel valve, oxidant and fuel are bypassed to thrust chamber；
Open the first fuel valve and the first oxidizer valve, oxidant and fuel enter thrust chamber by bypass and main road, and thrust chamber is by first
Grade operating condition goes to main operating condition.
In the specific embodiment shown in the drawings, high thrust liquid rocket engine thrust chamber test method includes:
S101: the high-temperature gas that igniter generates enters thrust chamber.In the embodiment of the present invention, gunpowder is can be used in igniter
Igniting, torch ignition and plasma ignition etc., when using pyrophoric ignition and torch ignition scheme, igniter flow should be controlled
The 0.1%~1.5% of thrust chamber declared working condition propellant flow rate, to ensure thrust chamber reliable ignition, while guarantee igniter and
Thrust chamber stable working when thrust chamber works together.
S102: opening the second oxidizer valve, and oxidant begins through oxygen and bypasses into the thrust chamber.Implementation of the invention
In example, the second oxidizer valve is opened in C1 mouthfuls of ventilations, and oxidant begins through oxygen and bypasses into thrust chamber.
S103: opening the second fuel valve, and fuel begins through fuel bypass into the thrust chamber.The embodiment of the present invention
In, the second fuel valve is opened in C2 mouthfuls of ventilations, and fuel begins through fuel bypass and enters thrust chamber.Open the second fuel valve when
Between than open the second oxidizer valve time it is 0.05S~0.5S late.If the thrust chamber is oxygen-enriched combusting thrust chamber, institute is opened
The time for stating the second fuel valve is 0.02S~1S more late than the time for opening second oxidizer valve.
S104: the first fuel valve is opened, fuel passes through fuel main road simultaneously and the fuel bypass enters the thrust chamber.
In the embodiment of the present invention, the first fuel valve is opened in C4 mouthfuls of ventilations, and fuel passes through fuel main road simultaneously and fuel bypass entrance pushes away
Power room.
S105: the first oxidizer valve is opened, oxidant passes through oxygen main road simultaneously and the oxygen bypasses into the thrust chamber.
In the embodiment of the present invention, C3 mouthfuls of ventilations, oxidant passes through oxygen main road simultaneously and oxygen bypasses into thrust chamber, and thrust chamber is by primary
Operating condition goes to main operating condition.The time for opening first oxidizer valve is 0.02S more late than the time for opening first fuel valve
~1S.If the thrust chamber is oxygen-enriched combusting thrust chamber, the time for opening first oxidizer valve is more described by first than opening
Morning time 0.02S~1S of fuel valve.
Referring to Fig. 7, the empirical risk of thrust chamber can be greatly reduced in step start scheme；Oxygen-enriched ignition timing and igniter stream
Measure accounting, it can be ensured that thrust chamber is reliable, steadily lights a fire；Thrust chamber is in starting ignition process without obvious impact；Turn grade timing, it can be true
Thrust chamber is protected from primary operating condition to main operating condition quick and stable transition.
Fig. 8 is a kind of high thrust liquid rocket engine thrust chamber test method that the specific embodiment of the invention provides
The flow chart of embodiment two fills oxidant as shown in figure 8, the high-temperature gas that igniter generates enters before thrust chamber
To the second oxidizer valve, and will be before filling fuels to the second fuel valve；It is ready to start to oxidant and fuel pressurization, heating.
In the specific embodiment shown in the drawings, before step S101, high thrust liquid rocket engine thrust chamber
Test method further include:
S97: opening the first oxidizer valve and oxidant releases valve, and oxidant is filled to the second oxidizer valve.This hair
In bright embodiment, C3 and C5 mouthfuls of ventilations open the first oxidizer valve and oxidant release valve, oxidant is filled to the second oxygen
Before agent valve.
S98: opening the first fuel valve and fuel releases valve, before filling fuels to the second fuel valve.Implementation of the invention
In example, C4 and C6 mouthfuls of ventilations open the first fuel valve and fuel release valve, before filling fuels to the second fuel valve.
S99: closing first oxidizer valve and the oxidant releases valve, is supplied by oxidant supply line predetermined
The oxidant of pressure and predetermined temperature.In the embodiment of the present invention, so that oxidant inlet OX1 pressure and temperature is reached design and want
It asks.
S100: closing first fuel valve and the fuel releases valve, supplies predetermined pressure by fuel supply conduit
With the fuel of predetermined temperature.In the embodiment of the present invention, fuel inlet F1 pressure and temperature is made to reach design requirement.
Referring to Fig. 8, before igniting, oxidant is filled to the second oxidizer valve, and by filling fuels to the second fuel
Before valve, after oxidant and fuel pressurization, heating, ready to start, experiment safety is high.
Fig. 9 is a kind of high thrust liquid rocket engine thrust chamber test method that the specific embodiment of the invention provides
The flow chart of embodiment three fills oxidant to second as shown in figure 9, the first oxidizer valve of opening and oxidant release valve
Before step before oxidizer valve, nitrogen conversion is carried out to oxidant and fuel supply conduit.
In the specific embodiment shown in the drawings, before step S97, the test of high thrust liquid rocket engine thrust chamber
Method further include:
S96: to oxygen bypass, oxygen main road, fuel bypass, fuel main road, oxidant supply line and fuel supply conduit into
The conversion of row nitrogen.In the embodiment of the present invention, to oxidant and fuel supply conduit (such as oxygen bypass, oxygen main road, combustion on the day of test run
Expect bypass, fuel main road, oxidant supply line and fuel supply conduit etc.) progress nitrogen displacement, prevent Propellant Supply pipe
Remaining vapor etc. is exceeded in road, causes to freeze in precooling process and cause test run failure.
Referring to Fig. 9, nitrogen displacement is carried out to oxidant and fuel supply conduit, is prevented remaining in Propellant Supply pipeline
Vapor etc. is exceeded, causes to freeze in precooling process and cause test run failure.
Figure 10 is a kind of high thrust liquid rocket engine thrust chamber test method that the specific embodiment of the invention provides
Example IV flow chart, as shown in Figure 10, after thrust chamber reaches predetermined test period, close the first oxidizer valve and first
Fuel valve is then shut off the second oxidizer valve and the second fuel valve, blows down remaining oxidant in oxidant supply line, blows down
Remaining fuel in fuel supply conduit.
In the specific embodiment shown in the drawings, after step S105, the examination of high thrust liquid rocket engine thrust chamber
Proved recipe method further include:
S106: after the predetermined time, the first oxidizer valve is closed, oxidant only passes through the oxygen and bypasses into described push away
Power room.In the embodiment of the present invention, C3 mouthfuls are removed gas, close the first oxidizer valve, and oxidant only passes through the oxygen and bypasses into institute
State thrust chamber.
S107: closing the first fuel valve, and fuel only passes through the fuel bypass into the thrust chamber.Implementation of the invention
In example, C4 mouthfuls are removed gas, close the first fuel valve, and fuel only passes through the fuel bypass into the thrust chamber.Close described
The time of one fuel valve is 0.02S~1S more late than the time for closing first oxidizer valve；If the thrust chamber is oxygen-enriched combustion
Thrust chamber is burnt, the time for closing first fuel valve is 0.02S~1S more early than the time for closing first oxidizer valve.
S108: closing the second oxidizer valve, stops supplying oxidant to the thrust chamber, opens simultaneously oxidant and blows down list
Valve is released to valve and oxidant, the oxidant is blown down and releases remaining oxidant in pipeline.In the embodiment of the present invention, C1 mouthfuls
Gas is removed, the second oxidizer valve is closed, B1 mouthfuls of ventilations open oxidant and blow down check valve, blow down the oxidant and release in pipeline
Remaining oxidant；C5 mouthfuls of ventilations simultaneously open oxidant and release valve, reduce oxidant and release pipeline water hammer.
S109: close the second fuel valve, stop give the thrust chamber supply fuel, open simultaneously fuel blow down check valve and
Fuel releases valve, blows down the fuel and releases remaining fuel in pipeline.In the embodiment of the present invention, C2 mouthfuls are removed gas, close the
Two fuel valves, B2 mouthfuls of ventilations open fuel and blow down check valve, while C6 mouthfuls of ventilations, open fuel and release valve, reduce fuel and release
Pipeline water hammer.The time for closing second fuel valve is 0.05S~1S more late than the time for closing second oxidizer valve；
If the thrust chamber is oxygen-enriched combusting thrust chamber, the time of second fuel valve is closed than closing second oxidizer valve
Morning time 0.05S~1S.
S110: closing that the oxidant releases valve and the fuel releases valve, by the oxidant blow down check valve and
The fuel blows down check valve and blows down remaining oxidant and fuel in the thrust chamber.In the embodiment of the present invention, B1 and B2
Mouth ventilation blows down check valve by the oxidant and the fuel blows down check valve to oxidant remaining in thrust chamber and combustion
Material is blown down.
Referring to Figure 10, timing of shutting down, it can be ensured that thrust chamber safety, steady shutdown, while ablation in shutdown process is avoided, it can
The empirical risk of thrust chamber is greatly reduced；Thrust chamber starting ignition timing turns grade timing and shutdown timing etc. can be directly used for liquid
Body rocket engine complete machine test run.
In other specific embodiments of the invention, after step silo, high thrust liquid rocket engine thrust chamber
Test method can with the following steps are included: testing ground confirmation safety after, the appearance of checkout facility equipment；If testing equipment is complete
It is good, repeated test run is such as needed, then repeatedly step S99~S110, otherwise enters and operate in next step；Before releasing the second oxidizer valve
Remaining oxidant in pipeline；Release before the second fuel valve residual fuel in pipeline；For cryogenic propellant, nitrogen or heat can be passed through
Nitrogen blows down thrust chamber and valve surface, accelerates product to rise again, it is desirable that oxygen head cavity (oxidant releases pipeline) and fuel
Head cavity (fuel releases pipeline) temperature is not less than 273K, and product surface is frostless and condensation of moisture；B1 and B2 mouthfuls is removed gas, closes thrust
Room oxygen head cavity and fuel head cavity are blown down；C5, C6 mouthfuls are removed gas, and closing oxidant releases valve and fuel releases valve；To testing equipment into
Row protection, the maintenance such as prevents sundries from entering thrust chamber inner cavity, while carrying out rain-proof dust-proof, and experiment work terminates.
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 (16)
1. a kind of high thrust liquid rocket engine thrust chamber experimental rig, which is characterized in that the device includes:
Thrust chamber (1), for providing place for oxidant and fuel reaction；
Igniter (2) is arranged in the thrust chamber (1) oxidant feed end, for triggering oxidant and fuel reaction；
Oxygen bypasses (3), setting in the thrust chamber (1) oxidant feed end, for the igniter (2) light a fire startup stage to
The thrust chamber (1) supplies oxidant；
Oxygen main road (4), setting are used for after the thrust chamber (1) runs well and institute in the thrust chamber (1) oxidant feed end
It states oxygen bypass (3) and supplies oxidant to the thrust chamber (1) together；
Fuel bypass (5), setting in the thrust chamber (1) fuel feed end, for the igniter (2) light a fire startup stage to
The thrust chamber (1) supplies fuel；And
Fuel main road (6), setting are used for after the thrust chamber (1) runs well and institute in the thrust chamber (1) fuel feed end
It states fuel bypass (5) and supplies fuel to the thrust chamber (1) together.
2. high thrust liquid rocket engine thrust chamber experimental rig according to claim 1, which is characterized in that the device
Further include:
Oxidant releases pipeline (7), setting in the thrust chamber (1) oxidant feed end, for release the oxygen bypass (3) and
Remaining oxidant in the oxygen main road (4), wherein the oxidant, which releases, to be provided with oxidant on pipeline (7) and release valve
(701)；And
Oxidant blows down check valve (8), setting in the thrust chamber (1) oxidant feed end, for by oxygen bypass (3) and
Remaining oxidant releases pipeline (7) by the oxidant and blows down in the oxygen main road (4).
3. high thrust liquid rocket engine thrust chamber experimental rig according to claim 2, which is characterized in that the device
Further include:
Fuel releases pipeline (9), is arranged in the thrust chamber (1) fuel feed end, for releasing the fuel bypass (5) and institute
State remaining fuel in fuel main road (6), wherein the fuel, which releases, to be provided with fuel and release valve (901) on pipeline (9)；With
And
Fuel blows down check valve (10), setting in the thrust chamber (1) fuel feed end, for by the fuel bypass (5) and
Remaining fuel releases pipeline (9) by the fuel and blows down in the fuel main road (6).
4. high thrust liquid rocket engine thrust chamber experimental rig according to claim 3, which is characterized in that the device
Further include:
Oxidant high pressure releases pipeline (23), releases pipeline (7) with the oxidant and is connected in parallel, for releasing the oxygen bypass
(3) and the oxidant in the oxygen main road (4), wherein the oxidant high pressure, which is released, is provided with oxidant height on pipeline (23)
Pressure releases valve (2301) and oxidant high pressure releases throttle (2302)；And
Fuel high pressure releases pipeline (24), releases pipeline (9) with the fuel and is connected in parallel, for releasing the fuel bypass
(5) and the fuel in the fuel main road (6), wherein the fuel high pressure, which releases, to be provided with fuel high pressure on pipeline (24) and let out
Valve (2401) and fuel high pressure release throttle (2402) out.
5. high thrust liquid rocket engine thrust chamber experimental rig according to claim 1, which is characterized in that the device
Further include:
First oxidizer valve (11), setting is between oxygen bypass (3) and the oxygen main road (4), for controlling the oxygen master
Road (4) Xiang Suoshu thrust chamber (1) supplies oxidant；
First fuel valve (12) is arranged between the fuel bypass (5) and the fuel main road (6), for controlling the combustion
Expect that main road (6) Xiang Suoshu thrust chamber (1) supplies fuel.
6. high thrust liquid rocket engine thrust chamber experimental rig according to claim 5, which is characterized in that the device
Further include:
Second oxidizer valve (13), setting is between oxygen bypass (3) and the thrust chamber (1), for controlling by the oxygen
Road (3) and the oxygen main road (4) Xiang Suoshu thrust chamber (1) supply oxidant, wherein the oxygen bypass (3) and the oxygen main road
(4) it is connected at the thrust chamber (1) oxidant feed end；
Second fuel valve (14) is arranged between the fuel main road (6) and the thrust chamber (1), for controlling the fuel
Bypass and the fuel main road supply fuel to the thrust chamber, wherein the fuel bypass (5) and the fuel main road (6)
It is connected at the thrust chamber (1) fuel feed end.
7. high thrust liquid rocket engine thrust chamber experimental rig according to claim 1, which is characterized in that the device
Further include:
Oxidant supply line (15) is connected to oxygen bypass (3), for supplying oxidant to oxygen bypass (3)；
Oxidizer filter (16) is arranged on the oxidant supply line (15), for filtering the impurity in oxidant；
Fuel supply conduit (17) is connected to the fuel bypass (5), for supplying fuel to the fuel bypass (5)；And
Fuel filter (18) is arranged on the fuel supply conduit (17), for filtering the impurity in fuel.
8. high thrust liquid rocket engine thrust chamber experimental rig according to claim 1, which is characterized in that the device
Further include:
Oxygen bypasses cavitation venturi (19), and setting is in oxygen bypass (3), for controlling the stream of oxidant in the oxygen bypass (3)
Amount；
Oxygen main road cavitation venturi (20) is arranged on the oxygen main road (4), for controlling the stream of oxidant in the oxygen main road (4)
Amount.
9. high thrust liquid rocket engine thrust chamber experimental rig according to claim 1, which is characterized in that the device
Further include:
Fuel bypass cavitation venturi (21) is arranged on the fuel bypass (5), for controlling fuel in the fuel bypass (5)
Flow；
Fuel main road cavitation venturi (22) is arranged on the fuel main road (6), for controlling fuel in the fuel main road (6)
Flow.
10. a kind of high thrust liquid rocket engine thrust chamber test method, which is characterized in that this method comprises:
The high-temperature gas that igniter generates enters thrust chamber；
The second oxidizer valve is opened, oxidant begins through oxygen and bypasses into the thrust chamber；
The second fuel valve is opened, fuel begins through fuel bypass into the thrust chamber；
The first fuel valve is opened, fuel passes through fuel main road simultaneously and the fuel bypass enters the thrust chamber；
The first oxidizer valve is opened, oxidant passes through oxygen main road simultaneously and the oxygen bypasses into the thrust chamber.
11. high thrust liquid rocket engine thrust chamber test method according to claim 9, which is characterized in that igniting
Before the step of high-temperature gas that device generates enters thrust chamber, this method further include:
It opens the first oxidizer valve and oxidant releases valve, oxidant is filled to the second oxidizer valve；
It opens the first fuel valve and fuel releases valve, before filling fuels to the second fuel valve；
It closes first oxidizer valve and the oxidant releases valve, by oxidant supply line supply predetermined pressure and in advance
Determine the oxidant of temperature；
It closes first fuel valve and the fuel releases valve, supply predetermined pressure and predetermined temperature by fuel supply conduit
Fuel.
12. high thrust liquid rocket engine thrust chamber test method according to claim 11, which is characterized in that open
First oxidizer valve and oxidant release valve, oxidant are filled to before the step before the second oxidizer valve, this method is also wrapped
It includes:
Nitrogen is carried out to oxygen bypass, oxygen main road, fuel bypass, fuel main road, oxidant supply line and fuel supply conduit to turn
It changes.
13. high thrust liquid rocket engine thrust chamber test method according to claim 10, which is characterized in that open
First oxidizer valve, oxidant pass through oxygen main road simultaneously and the step of the oxygen bypasses into the thrust chamber after, this method
Further include:
After the predetermined time, the first oxidizer valve is closed, oxidant only passes through the oxygen and bypasses into the thrust chamber；
The first fuel valve is closed, fuel only passes through the fuel bypass into the thrust chamber；
The second oxidizer valve is closed, stops supplying oxidant to the thrust chamber, oxidant is opened simultaneously and blows down check valve and oxygen
Agent releases valve, blows down the oxidant and releases remaining oxidant in pipeline；
The second fuel valve is closed, stops supplying fuel to the thrust chamber, fuel blowing check valve is opened simultaneously and fuel releases
Valve blows down the fuel and releases remaining fuel in pipeline.
14. high thrust liquid rocket engine thrust chamber test method according to claim 13, which is characterized in that close
Second fuel valve stops supplying fuel to the thrust chamber, opens simultaneously fuel blowing check valve and fuel releases valve, blow down institute
After stating the step of fuel releases remaining fuel in pipeline, this method further include:
It closes that the oxidant releases valve and the fuel releases valve, check valve is blown down by the oxidant and the fuel is blown
Except check valve blows down remaining oxidant and fuel in the thrust chamber.
15. high thrust liquid rocket engine thrust chamber test method according to claim 13, which is characterized in that close
The time of first fuel valve is 0.02S~1S more late than the time for closing first oxidizer valve, closes second fuel
The time of valve is 0.05S~1S more late than the time for closing second oxidizer valve；
If the thrust chamber is oxygen-enriched combusting thrust chamber, the time of first fuel valve is closed than closing first oxidation
Morning time 0.02S~1S of agent valve, the time for closing second fuel valve are more early than the time for closing second oxidizer valve
0.05S~1S.
16. high thrust liquid rocket engine thrust chamber test method according to claim 10, which is characterized in that open
The time of second fuel valve is 0.02S~1S more late than the time for opening second oxidizer valve, opens first oxidation
The time of agent valve is 0.02S~1S more late than the time for opening first fuel valve；
If the thrust chamber is oxygen-enriched combusting thrust chamber, the time of second fuel valve is opened than opening second oxidation
Evening time 0.02S~1S of agent valve, the time for opening first oxidizer valve are more early than the time for opening first fuel valve
0.02S~1S.
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| CN110017992A (en) * | 2019-05-16 | 2019-07-16 | 九州云箭(北京)空间科技有限公司 | A kind of liquid rocket dynamical system test run method and its device |
| CN110954794A (en) * | 2019-12-11 | 2020-04-03 | 中国科学院力学研究所 | Liquid propellant constant-pressure discharge characteristic parameter measuring device |
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| CN112576414A (en) * | 2020-12-02 | 2021-03-30 | 西安航天动力研究所 | Liquid rocket engine thrust chamber filling test device and method and simulation criterion |
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| CN114458478A (en) * | 2020-12-25 | 2022-05-10 | 北京天兵科技有限公司 | Double-station test bed and test method for extrusion pump pressure type rocket engine |
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| CN114658567A (en) * | 2022-03-31 | 2022-06-24 | 沈阳航天新光集团有限公司 | Small-thrust nitrous oxide kerosene rocket engine ground test system and test method |
| CN116025488A (en) * | 2023-03-30 | 2023-04-28 | 中国人民解放军战略支援部队航天工程大学 | Engine working condition adjustment test device and adjustment method |
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