CN117552894B - Rocket engine high-altitude simulation test method and equipment - Google Patents
Rocket engine high-altitude simulation test method and equipment Download PDFInfo
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- CN117552894B CN117552894B CN202310140141.2A CN202310140141A CN117552894B CN 117552894 B CN117552894 B CN 117552894B CN 202310140141 A CN202310140141 A CN 202310140141A CN 117552894 B CN117552894 B CN 117552894B
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- 238000004088 simulation Methods 0.000 title claims abstract description 34
- 238000010998 test method Methods 0.000 title claims abstract description 27
- 238000002347 injection Methods 0.000 claims abstract description 55
- 239000007924 injection Substances 0.000 claims abstract description 55
- 238000000034 method Methods 0.000 claims abstract description 17
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 11
- 239000001301 oxygen Substances 0.000 claims description 11
- 229910052760 oxygen Inorganic materials 0.000 claims description 11
- 238000004891 communication Methods 0.000 claims description 4
- 239000000126 substance Substances 0.000 claims description 2
- 239000000243 solution Substances 0.000 description 5
- 230000008901 benefit Effects 0.000 description 4
- 238000010276 construction Methods 0.000 description 4
- 239000000446 fuel Substances 0.000 description 3
- 239000002737 fuel gas Substances 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- 238000004364 calculation method Methods 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 230000008094 contradictory effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/96—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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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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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
The invention discloses a rocket engine high-altitude simulation test method and equipment, wherein the test method comprises the following steps: before the rocket engine is ignited, controlling to open all branch pipe valves, starting all steam generators, enabling injection working media to enter an injector and starting the injector; igniting and starting the rocket engine to enable the jet pipe of the rocket engine to flow fully; closing the steam generators of the target shutdown number, enabling the rest steam generators to continuously work, and maintaining the opening state of the branch pipe valve; and when the ignition duration reaches the target time, the rocket engine and the rest steam generators are turned off. The invention improves the process method in the high-altitude simulation process of the rocket engine, realizes that the jet pipe can flow fully after the rocket engine is ignited, optimizes the scale of the injection working medium supply system, effectively saves the injection working medium and greatly reduces the test cost.
Description
Technical Field
The invention relates to the technical field of rocket engines, in particular to a rocket engine high-altitude simulation test method and equipment.
Background
In order to examine the performance of the upper-stage rocket engine in high-altitude operation, a high-altitude simulation test needs to be carried out, and the effect to be obtained is that the jet pipe can flow fully after the rocket engine is ignited. When the area of the rocket engine spray pipe is relatively large, a driving injection mode is needed, and a large amount of injection working medium is needed to be consumed.
The existing traditional rocket engine high-altitude simulation test equipment consists of a vacuum cabin, a rocket engine, a diffuser, an ejector and the like, and when the high-altitude simulation test is carried out, the ejector is started first and then the rocket engine is started, so that the pressure of the vacuum cabin is reduced, and the jet pipe of the rocket engine is full-flow. But in the test process, the injection working medium supply pipeline is continuously supplied with larger injection working medium flow all the time, all the steam generators are opened in the whole course, a large amount of injection working medium is wasted, and the test cost is higher.
Disclosure of Invention
The invention mainly aims to provide a rocket engine high-altitude simulation test method and equipment, which aim to realize that a jet pipe can flow fully after the rocket engine is ignited, and simultaneously save injection working media so as to reduce test cost.
In order to achieve the above purpose, the invention provides a rocket engine high altitude simulation test method, which comprises the following steps:
Before the rocket engine is ignited, controlling to open all branch pipe valves, starting all steam generators, enabling injection working media to enter an injector and starting the injector;
Igniting and starting the rocket engine to enable the jet pipe of the rocket engine to flow fully;
Closing the steam generators of the target shutdown number, enabling the rest steam generators to continuously work, and maintaining the opening state of the branch pipe valve;
and when the ignition duration reaches the target time, the rocket engine and the rest steam generators are turned off.
Optionally, defining the number of the steam generators as N, the number of the target shutdown units as N, the oxygen flow of a single steam generator as m, and the oxygen flow of the rocket engine as m2;
In the step of closing the target number of the steam generators, enabling the remaining steam generators to continuously work and maintaining the opening state of the branch pipe valve, the number of the remaining steam generators is N-N, and the relation formula is satisfied: n is equal to or less than m2.
Optionally, before the step of igniting the rocket engine, controlling to open all branch pipe valves, starting all steam generators, enabling injection working medium to enter the injector and starting the injector, and simultaneously, further comprising:
Detecting a first air pressure value of a vacuum bulkhead surface where the rocket engine is located, detecting a second air pressure value of an inlet plane of the secondary throat of the ejector, and detecting a third air pressure value of an outlet plane of the secondary throat of the ejector.
Optionally, before the step of igniting the rocket engine, controlling to open all branch pipe valves, starting all steam generators, enabling injection working medium to enter an injector and starting the injector, wherein the second air pressure value is smaller than the third air pressure value;
After the step of igniting and starting the rocket engine and fully flowing the jet pipe of the rocket engine is executed, the first air pressure value is smaller than the second air pressure value, and the first air pressure value are both smaller than the third air pressure value.
In order to achieve the above purpose, the invention provides a rocket engine high altitude simulation test method, which comprises the following steps:
before the rocket engine is ignited, controlling to open all branch pipe valves, starting all steam generators, and enabling injection working media to enter an injector, wherein the injector is in a non-starting state;
starting the rocket engine by ignition, and simultaneously starting the ejectors so as to enable the jet pipe of the rocket engine to flow fully;
And when the ignition duration reaches the target time, the rocket engine and the steam generator are turned off.
Optionally, defining the number of the steam generators as N-N, wherein the oxygen flow rate of each steam generator is m, and the oxygen flow rate of the rocket engine is m2;
The value method of N is as follows: before the rocket engine is ignited and N steam generators work, the ejector starts to work; when N-1 steam generators work before the rocket engine is ignited, the ejector cannot be started;
The value method of n is as follows: n is equal to or less than m2.
Optionally, before the step of igniting the rocket engine, controlling to open all branch pipe valves, starting all steam generators, so that injection working medium enters the injector and the injector is in a non-starting state, and simultaneously, the method further comprises the following steps:
Detecting a first air pressure value of a vacuum bulkhead surface where the rocket engine is located, detecting a second air pressure value of an inlet plane of the secondary throat of the ejector, and detecting a third air pressure value of an outlet plane of the secondary throat of the ejector.
Optionally, before the step of igniting the rocket engine, controlling to open all branch pipe valves, starting all steam generators, and enabling injection working medium to enter an injector and enabling the injector to be in a non-starting state, wherein the second air pressure value is larger than the third air pressure value, and the first air pressure value is suitable for being smaller than a local atmospheric pressure value;
after the step of igniting and starting the rocket engine and the ejector are simultaneously started so as to enable the jet pipe of the rocket engine to flow fully, the first air pressure value is smaller than the second air pressure value, and the first air pressure value and the second air pressure value are both smaller than the third air pressure value.
In order to achieve the above object, the present invention further provides a rocket engine high-altitude simulation test device, when in test, implementing the test method as described above, the test device comprises:
The rocket engine is arranged in the vacuum cabin;
a diffuser in communication with the vacuum chamber;
the ejector is communicated with the diffuser;
the injection working medium supply pipeline comprises a supply main pipe and a plurality of supply branch pipes which are arranged on the supply main pipe in parallel, the supply main pipe is communicated with an injection working medium inlet of the injector, and each supply branch pipe is provided with a branch pipe valve; and
And a plurality of steam generators are arranged on the air inlet ends of the plurality of the supply branch pipes in a one-to-one mode.
Optionally, the test device further comprises:
A first pressure sensor mounted at the vacuum bulkhead face for detecting a first pressure value of the vacuum bulkhead face;
The second pressure sensor is arranged at the inlet plane of the secondary throat of the ejector and is used for detecting a second air pressure value of the inlet plane of the secondary throat of the ejector; and
And the third pressure sensor is arranged at the outlet plane of the secondary throat of the ejector and is used for detecting a third air pressure value of the outlet plane of the secondary throat of the ejector.
In one technical scheme of the invention, the rocket engine high altitude simulation test method comprises the following steps: before the rocket engine is ignited, controlling to open all branch pipe valves, starting all steam generators, enabling injection working media to enter an injector and starting the injector; igniting and starting the rocket engine to enable the jet pipe of the rocket engine to flow fully; closing the steam generators of the target shutdown number, enabling the rest steam generators to continuously work, and maintaining the opening state of the branch pipe valve; and when the ignition duration reaches the target time, the rocket engine and the rest steam generators are turned off. Therefore, the jet pipe of the rocket engine can flow fully after ignition, and meanwhile, the continuous supply of the injection working medium supply pipeline with the maximum injection working medium flow is avoided, a large amount of injection working mediums are saved, and the test cost is greatly reduced.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to the structures shown in these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic view of an embodiment of a rocket engine high altitude simulation test device according to the present invention;
FIG. 2 is a schematic flow chart of a first embodiment of a rocket engine high altitude simulation test method of the present invention;
FIG. 3 is a schematic flow chart of a second embodiment of a rocket engine high altitude simulation test method according to the present invention.
Reference numerals illustrate:
10. A rocket engine; 20. a vacuum chamber; 30. a diffuser; 40. an ejector; 50. a supply header; 60. a supply branch pipe; 70. a branch pipe valve; 80. a steam generator; 41. injecting a working medium inlet; 42. a secondary throat; 91. a first pressure sensor; 92. a second pressure sensor; 93. and a third pressure sensor.
The achievement of the objects, functional features and advantages of the present invention will be further described with reference to the accompanying drawings, in conjunction with the embodiments.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are only some, but not all embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
It should be noted that, if directional indications (such as up, down, left, right, front, and rear … …) are included in the embodiments of the present invention, the directional indications are merely used to explain the relative positional relationship, movement conditions, etc. between the components in a specific posture (as shown in the drawings), and if the specific posture is changed, the directional indications are correspondingly changed.
In addition, if there is a description of "first", "second", etc. in the embodiments of the present invention, the description of "first", "second", etc. is for descriptive purposes only and is not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In addition, if the meaning of "and/or" is presented throughout this document, it is intended to include three schemes in parallel, taking "a and/or B" as an example, including a scheme, or B scheme, or a scheme where a and B meet simultaneously. In addition, the technical solutions of the embodiments may be combined with each other, but it is necessary to base that the technical solutions can be realized by those skilled in the art, and when the technical solutions are contradictory or cannot be realized, the combination of the technical solutions should be considered to be absent and not within the scope of protection claimed in the present invention.
The invention provides a rocket engine high-altitude simulation test device.
Referring to FIG. 1, in one embodiment of the present invention, the rocket engine altitude simulation test device comprises a rocket engine 10, a vacuum chamber 20, a diffuser 30, an ejector 40, an ejector working substance supply line, and a plurality of steam generators 80; rocket motor 10 is disposed in vacuum chamber 20; the diffuser 30 is in communication with the vacuum chamber 20; the ejector 40 communicates with the diffuser 30; the injection working medium supply pipeline comprises a supply main pipe 50 and a plurality of supply branch pipes 60 which are arranged on the supply main pipe 50 in parallel, the supply main pipe 50 is communicated with the injection working medium inlet 41 of the injector 40, and each supply branch pipe 60 is provided with a branch pipe valve 70; a plurality of steam generators 80 are provided one-to-one on the intake ends of the plurality of supply branch pipes 60.
The steam generator 80 is a device that burns fuel and oxygen and mixes them to generate steam of a certain pressure.
In this embodiment, the rocket engine high-altitude simulation test device may further include a first pressure sensor 91, a second pressure sensor 92, and a third pressure sensor 93; the first pressure sensor 91 is installed at a wall surface of the vacuum chamber 20 for detecting a first air pressure value of the wall surface of the vacuum chamber 20; the second pressure sensor 92 is installed at the inlet plane of the secondary throat 42 of the ejector 40, and is used for detecting a second air pressure value of the inlet plane of the secondary throat 42 of the ejector 40; the third pressure sensor 93 is mounted at the outlet plane of the secondary throat 42 of the ejector 40 for detecting a third air pressure value at the outlet plane of the secondary throat 42 of the ejector 40. In this manner, a pilot may be aided in determining whether injector 40 is activated and whether the nozzles of rocket engine 10 are full.
It can be understood that by arranging a plurality of steam generators 80 in parallel connection, the invention realizes continuous supply of a proper amount of injection working medium into the injector 40, so that the inside of the injector 40 forms closed supersonic flow to start the injector 40, the pressure in the vacuum cabin 20 is greatly reduced, and the full flow of the jet pipe after the rocket engine 10 is ignited is realized. Meanwhile, as the steam generators 80 are arranged in parallel, the number of working tables of the steam generators 80 can be reduced in time in the test process, a proper amount of injection working medium is supplied, the injection working medium is effectively saved, and the test cost is greatly controlled.
In order to save injection working medium and reduce test cost, referring to fig. 1 to 3, the invention also provides two rocket engine high-altitude simulation test methods, which are both based on the test equipment. Defining the number of steam generators 80 as N, the following target shutdown number as N, the oxygen flow rate of a single steam generator 80 as m, the fuel flow rate as x m, the water flow rate as y m, and the injection working medium flow rate supplied by the single steam generator 80 as (1+x+y) m; oxygen flow of rocket engine 10 is defined as m2, and fuel flow is defined as x2 x m2; the ignition time of rocket engine 10 is defined as t.
1) Referring to fig. 1 and 2, the first rocket engine altitude simulation test method comprises the following steps:
s11, before the rocket engine 10 is ignited, all branch pipe valves 70 are controlled to be opened, all steam generators 80 are started, injection working media are enabled to enter the injector 40, and the injector 40 is started.
After the test starts, the first pressure sensor 91 detects a first air pressure value of the wall surface of the vacuum cabin 20 where the rocket engine 10 is located in real time, the second pressure sensor 92 detects a second air pressure value of the inlet plane of the secondary throat 42 of the ejector 40 in real time, and the third pressure sensor 93 detects a third air pressure value of the outlet plane of the secondary throat 42 of the ejector 40 in real time.
In this step, before the rocket engine 10 ignites, the N branch pipe valves 70 are opened, the N steam generators 80 are started, the injection working medium reaches the injection working medium inlet 41 through the injection working medium supply header pipe 50, and enters the injector 40, the inside of the injector 40 forms closed supersonic flow, the pressure in the vacuum cabin 20 is greatly reduced, and at this time, the injector 40 is in a starting state. The judgment basis is that the second air pressure value displayed by the second pressure sensor 92 is smaller than the third air pressure value displayed by the third pressure sensor 93.
And S12, igniting and starting the rocket engine 10, so that the jet pipe of the rocket engine 10 flows fully.
In this step, rocket engine 10 is ignited and started, rocket engine 10 fuel gas accelerates in diffuser 30, closed supersonic flow is formed, and the jet pipe realizes full flow. The determination method is that the first air pressure value displayed by the first pressure sensor 91 is smaller than the second air pressure value displayed by the second pressure sensor 92, and the first air pressure value and the second air pressure value are both smaller than the third air pressure value displayed by the third pressure sensor 93.
And S13, closing the steam generators 80 of the target shutdown number, enabling the rest steam generators 80 to continuously work, and maintaining the opening state of the branch pipe valve 70.
In this step, after rocket engine 10 is started by ignition, n steam generators 80 are turned off so that n×m is close to m2, but n×m is equal to or smaller than m2. Thus, the first air pressure value detected by the first pressure sensor 91 on the vacuum chamber 20 does not change, that is, the ignition ambient pressure of the rocket engine 10 does not change, and the full flow does not change.
The mechanism is that the kinetic energy provided by the self-combustion gas replaces the kinetic energy provided by part of injection working medium after the rocket engine 10 is started.
Throughout the process, the remaining N-N manifold valves 70 remain open and the N-N steam generators 80 continue to operate.
S14, when the ignition duration reaches the target time, the rocket engine 10 and the rest of the steam generators 80 are turned off.
In this step, when the ignition duration satisfies the requirement, the rocket engine 10 is turned off, the N-N steam generators 80 are turned off, and the test is ended.
It can be understood that the first process can actually save the injection working medium supply amount n (1+x+y) m t, has objective economic benefit, and can save the medium cost by 30 ten thousand yuan according to one test t=1000 s, n=2, (1+x+y) m=25 kg/s and injection working medium unit price 6 yuan/kg calculation.
Obviously, the invention optimizes the high-altitude simulation test method of the rocket engine, not only realizes that the jet pipe can flow fully after the rocket engine 10 is ignited, but also effectively saves injection working medium, greatly reduces test cost and brings great economic benefit.
2) Referring to fig. 1 and 3, the second rocket engine altitude simulation test method comprises the following steps:
S21, before the rocket engine 10 is ignited, all branch pipe valves 70 are controlled to be opened, all steam generators 80 are started, injection working media are enabled to enter the injector 40, and the injector 40 is in a non-starting state.
In this step, the rocket engine 10 is not ignited, the N-N branch pipe valve 70 is opened, the N-N steam generators 80 are started, the injection working medium reaches the injection working medium inlet 41 through the injection working medium supply header pipe 50 and enters the injector 40, the inside of the injector 40 cannot form closed supersonic flow, the pressure in the vacuum chamber 20 is reduced, but the injector 40 is in a non-starting state at this time. The second air pressure value displayed by the second pressure sensor 92 is larger than the third air pressure value displayed by the third pressure sensor 93, and the first air pressure value displayed by the first pressure sensor 91 is suitable for being smaller than the local atmospheric pressure.
S22, igniting and starting the rocket engine 10, and simultaneously starting the ejectors 40 to enable the jet pipes of the rocket engine 10 to flow fully.
In this step, rocket motor 10 is ignited and started, so that injector 40 and rocket motor 10 are simultaneously started, and the jet pipe of rocket motor 10 is fully flowed. The determination method is that the first air pressure value displayed by the first pressure sensor 91 is smaller than the second air pressure value displayed by the second pressure sensor 92, and the first air pressure value and the second air pressure value are both smaller than the third air pressure value displayed by the third pressure sensor 93.
The mechanism is that the injector 40 is not started before the rocket engine 10 is ignited, and the kinetic energy provided by the self fuel gas replaces the kinetic energy provided by partial injection working medium after the rocket engine 10 is ignited.
S23, when the ignition duration reaches the target time, the rocket engine 10 and the steam generator 80 are turned off.
In this step, when the ignition duration satisfies the requirement, rocket engine 10 is turned off, steam generator 80 is turned off, and the test is ended.
It should be noted that, for the high-altitude simulation test method of the second rocket engine 10, the injection working medium supply system is only provided with the N-N paths of steam generators 80, the injection working medium supply branch pipes 60 and the branch pipe valves 70 during construction. That is, in this embodiment, the total number of steam generators 80, the number of injection fluid supply branch pipes 60 and branch pipe valves 70 is N-N. The value of N is obtained by ensuring that the injector 40 can be started when the rocket engine 10 is not ignited, and that N-1 cannot be started when the injector is operated alone. That is, before the rocket engine 10 is ignited and when the N steam generators 80 are operated, the ejector 40 is started; when N-1 steam generators 80 are operated before rocket motor 10 is ignited, injector 40 cannot be started. The value of n is that n is close to m2, but n is less than or equal to m2.
It can be appreciated that by adopting the second process, devices such as the steam generator 80, the injection working medium supply branch pipe 60, the branch pipe valve 70 and the like are reduced in the test equipment construction process, and the injection working medium supply quantity can be saved in the test process by more than n (1+x+y) m t. According to one test t=1000s, n=2, (1+x+y) m=25 kg/s, the system construction cost can be saved by about 400 ten thousand yuan, and the medium cost is saved by 30 ten thousand yuan for each test.
Obviously, the invention optimizes the high-altitude simulation test method of the rocket engine, not only realizes that the spray pipe can flow fully after the rocket engine 10 is ignited, but also effectively reduces the construction cost of equipment, saves injection working medium, greatly reduces the test cost and brings great economic benefit.
The foregoing description is only of the optional embodiments of the present invention, and is not intended to limit the scope of the invention, and all the equivalent structural changes made by the description of the present invention and the accompanying drawings or the direct/indirect application in other related technical fields are included in the scope of the invention.
Claims (7)
1. The rocket engine high-altitude simulation test method is applied to rocket engine high-altitude simulation test equipment and is characterized in that the test equipment comprises:
The rocket engine is arranged in the vacuum cabin;
a diffuser in communication with the vacuum chamber;
the ejector is communicated with the diffuser;
the injection working medium supply pipeline comprises a supply main pipe and a plurality of supply branch pipes which are arranged on the supply main pipe in parallel, the supply main pipe is communicated with an injection working medium inlet of the injector, and each supply branch pipe is provided with a branch pipe valve; and
A plurality of steam generators arranged one-to-one on the air inlet ends of the plurality of supply branch pipes;
The test method comprises the following steps:
Before the rocket engine is ignited, controlling to open all branch pipe valves, starting all steam generators, enabling injection working media to enter an injector and starting the injector;
Igniting and starting the rocket engine to enable the jet pipe of the rocket engine to flow fully;
Closing the steam generators of the target shutdown number, enabling the rest steam generators to continuously work, and maintaining the opening state of the branch pipe valve;
When the ignition duration reaches the target time, closing the rocket engine and the rest steam generators;
defining the number of the steam generators as N, the target shutdown number as N, the oxygen flow of a single steam generator as m, and the oxygen flow of the rocket engine as m2;
In the step of closing the target number of the steam generators, enabling the remaining steam generators to continuously work and maintaining the opening state of the branch pipe valve, the number of the remaining steam generators is N-N, and the relation formula is satisfied: n is equal to or less than m2.
2. A rocket engine altitude simulation test method according to claim 1, wherein before said rocket engine ignition is performed, controlling to open all branch pipe valves, starting all steam generators, allowing injection working medium to enter an injector and starting said injector, and simultaneously, further comprising:
Detecting a first air pressure value of a vacuum bulkhead surface where the rocket engine is located, detecting a second air pressure value of an inlet plane of the secondary throat of the ejector, and detecting a third air pressure value of an outlet plane of the secondary throat of the ejector.
3. A rocket engine altitude simulation test method according to claim 2, wherein said second air pressure value is less than said third air pressure value after said steps of controlling and opening all branch valves, starting all steam generators, injecting working medium into an injector and starting said injector before said rocket engine ignition is performed;
After the step of starting the rocket engine with the ignition performed, the nozzle of the rocket engine is fully flowed, the first air pressure value is smaller than the second air pressure value, and both the first air pressure value and the second air pressure value are smaller than the third air pressure value.
4. The rocket engine high-altitude simulation test method is applied to rocket engine high-altitude simulation test equipment and is characterized in that the test equipment comprises:
The rocket engine is arranged in the vacuum cabin;
a diffuser in communication with the vacuum chamber;
the ejector is communicated with the diffuser;
the injection working medium supply pipeline comprises a supply main pipe and a plurality of supply branch pipes which are arranged on the supply main pipe in parallel, the supply main pipe is communicated with an injection working medium inlet of the injector, and each supply branch pipe is provided with a branch pipe valve; and
A plurality of steam generators arranged one-to-one on the air inlet ends of the plurality of supply branch pipes;
The test method comprises the following steps:
Defining the total number of the steam generators as N-N, wherein the oxygen flow of a single steam generator is m, and the oxygen flow of the rocket engine is m2;
The value method of N is as follows: just can ensure that the ejector can be started when the rocket engine is not ignited, and N-1 can not be started when the ejector works independently; n is the reducible number of the steam generators, and the value method of n is as follows: n is equal to or less than m2;
Before the rocket engine is ignited, controlling to open an N-N branch pipe valve, starting N-N steam generators, and enabling injection working media to enter an injector, wherein the injector is in a non-starting state;
starting the rocket engine by ignition, and simultaneously starting the ejectors so as to enable the jet pipe of the rocket engine to flow fully;
And when the ignition duration reaches the target time, the rocket engine and the steam generator are turned off.
5. A rocket engine altitude simulation test method according to claim 4, wherein before said rocket engine ignition is performed, controlling to open all branch pipe valves, starting all steam generators, and enabling injection working medium to enter an injector while said injector is in a non-starting state, further comprising:
Detecting a first air pressure value of a vacuum bulkhead surface where the rocket engine is located, detecting a second air pressure value of an inlet plane of the secondary throat of the ejector, and detecting a third air pressure value of an outlet plane of the secondary throat of the ejector.
6. A rocket engine altitude simulation test method according to claim 5, wherein said second air pressure value is greater than said third air pressure value and said first air pressure value is adapted to be less than a local atmospheric pressure value after said step of controlling opening all manifold valves, starting all steam generators, causing an ejector working substance to enter an ejector and said ejector is in a non-start state prior to said step of performing said igniting of a rocket engine;
after the step of igniting and starting the rocket engine and the ejector are simultaneously started so as to enable the jet pipe of the rocket engine to flow fully, the first air pressure value is smaller than the second air pressure value, and the first air pressure value and the second air pressure value are both smaller than the third air pressure value.
7. A rocket engine altitude simulation test method according to claim 1 or 4, wherein said test device further comprises:
A first pressure sensor mounted at the vacuum bulkhead face for detecting a first pressure value of the vacuum bulkhead face;
The second pressure sensor is arranged at the inlet plane of the secondary throat of the ejector and is used for detecting a second air pressure value of the inlet plane of the secondary throat of the ejector; and
And the third pressure sensor is arranged at the outlet plane of the secondary throat of the ejector and is used for detecting a third air pressure value of the outlet plane of the secondary throat of the ejector.
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| CN202310140141.2A CN117552894B (en) | 2023-02-21 | 2023-02-21 | Rocket engine high-altitude simulation test method and equipment |
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| CN202310140141.2A CN117552894B (en) | 2023-02-21 | 2023-02-21 | Rocket engine high-altitude simulation test method and equipment |
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| CN117552894B true CN117552894B (en) | 2024-05-17 |
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Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
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| KR20130077195A (en) * | 2011-12-29 | 2013-07-09 | 한국항공우주연구원 | Apparatus and method for ground-testing a rocket engine for high altitude environment |
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