CN114233524B - Research system for coupling of longitudinal unstable combustion and structural vibration of rocket engine - Google Patents
Research system for coupling of longitudinal unstable combustion and structural vibration of rocket engine Download PDFInfo
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- CN114233524B CN114233524B CN202111269253.5A CN202111269253A CN114233524B CN 114233524 B CN114233524 B CN 114233524B CN 202111269253 A CN202111269253 A CN 202111269253A CN 114233524 B CN114233524 B CN 114233524B
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 82
- 230000008878 coupling Effects 0.000 title claims abstract description 24
- 238000010168 coupling process Methods 0.000 title claims abstract description 24
- 238000005859 coupling reaction Methods 0.000 title claims abstract description 24
- 238000011160 research Methods 0.000 title claims description 25
- 238000013016 damping Methods 0.000 claims abstract description 12
- 238000012360 testing method Methods 0.000 claims abstract description 6
- 230000001133 acceleration Effects 0.000 claims description 13
- 238000002347 injection Methods 0.000 claims description 13
- 239000007924 injection Substances 0.000 claims description 13
- 230000010355 oscillation Effects 0.000 claims description 12
- 238000006073 displacement reaction Methods 0.000 claims description 6
- 230000005484 gravity Effects 0.000 claims description 3
- 230000008602 contraction Effects 0.000 claims 2
- 238000000034 method Methods 0.000 abstract description 4
- 230000008569 process Effects 0.000 abstract description 3
- 238000005259 measurement Methods 0.000 description 11
- 239000007788 liquid Substances 0.000 description 4
- 239000003380 propellant Substances 0.000 description 3
- 239000000306 component Substances 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 239000007800 oxidant agent Substances 0.000 description 2
- 230000001590 oxidative effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000001066 destructive effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 230000000452 restraining effect Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/96—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 system for researching longitudinal unstable combustion and structural vibration coupling of a rocket engine, which comprises a spring damping module, a measuring module and an engine module, wherein the spring damping module is used for measuring the longitudinal unstable combustion of the rocket engine; the spring damping component comprises a fixed plate, a movable plate, a spring component and a guide rod; the spring assembly is arranged between the fixed plate and the movable plate and can longitudinally extend and retract along the rocket engine; the guide rod can guide the longitudinal extension of the spring assembly; the measuring module is embedded in the movable plate and can monitor the longitudinal expansion data of the movable plate in real time; the engine module is coaxially arranged on the back of the movable plate; the engine module comprises a jetting section, a combustion chamber and a tail nozzle which are coaxially arranged along the longitudinal direction; wherein, be provided with pressure sensor in the combustion chamber for monitor combustion chamber pressure. According to the invention, by measuring the axial vibration data of the engine, data support is provided for summarizing the coupling relationship between combustion and vibration, and the problem of coupling of longitudinal combustion instability of an internal flow field and structure axial vibration in the ignition test process of the rocket engine can be conveniently researched.
Description
Technical Field
The invention relates to the field of liquid rocket engine research, in particular to a rocket engine longitudinal unstable combustion and structural vibration coupling research system.
Background
The core component of the liquid rocket, namely the liquid rocket engine, actually works in the extreme environment of high temperature and high pressure, and the structural stability and reliability of the engine are seriously tested. Particularly, when the combustion of the internal propellant is unstable, the combustion chamber has large pressure oscillation inside, when the flow field pressure oscillation frequency is close to the natural frequency of the engine structure, the structural resonance can be caused, a local position bears large load, the structural fatigue damage is easy to occur, and finally the destructive damage of the whole combustion chamber, the whole engine and even the whole rocket is caused.
For the coupled analysis of pressure oscillation and structural vibration caused by unstable combustion, the emphasis is currently focused on the acoustic characteristics, structural modal characteristics, and acoustic structure coupled response of the combustion chamber. The test measurement scheme is that the top of the combustion chamber is fixed, then measurement points are arranged on the wall surface of the combustion chamber along the axial direction or the circumferential direction, and a triaxial or uniaxial acceleration sensor is mounted on each measurement point. Through the analysis of the data returned by the vibration sensor under the two conditions of stable combustion and unstable combustion, the relation of combustion and vibration coupling is found out, and a method for eliminating the coupling is provided.
The prior art is biased to measure the mode of engine vibration, and the engine end face is always fixedly restrained during measurement, so that the measurement result includes the influence of a restraining structure. Considering that combustion instability in the combustion chamber is divided into a transverse type and a longitudinal type, different combustion states have great influence on structural vibration, so that decoupling research needs to be carried out on combustion and vibration, namely the freedom degree of an engine is limited, and the combustion state is consistent with the vibration direction.
Disclosure of Invention
The invention aims to solve the technical problem of the prior art and provides a research system for coupling the longitudinal unstable combustion and the structural vibration of a rocket engine.
In order to solve the technical problems, the invention adopts the technical scheme that:
a system for researching longitudinal unstable combustion and structural vibration coupling of a rocket engine comprises a spring damping module, a measuring module and an engine module.
The spring damping module comprises a fixed plate, a movable plate, a spring assembly and a guide rod.
The longitudinal position of the fixed plate is fixed.
The movable plate and the fixed plate are arranged in parallel and coaxially.
The spring assembly is arranged between the fixed plate and the movable plate, and two ends of the spring assembly are respectively connected with the fixed plate and the movable plate; the spring assembly is capable of longitudinal extension and retraction along the rocket motor.
The guide rods are arranged on the fixed plate and the movable plate and are distributed along the longitudinal direction of the rocket engine, and the guide rods can guide the longitudinal extension of the spring assembly.
The measuring module is embedded in the movable plate and can monitor the longitudinal telescopic data of the movable plate or the spring assembly in real time.
The engine module is coaxially mounted on the movable plate on a side facing away from the stationary plate.
The engine module comprises a jetting section, a combustion chamber and a tail nozzle which are coaxially arranged along the longitudinal direction; wherein, be provided with pressure sensor in the combustion chamber, pressure sensor can monitor combustion chamber pressure.
The longitudinal expansion data includes one or a combination of a longitudinal expansion acceleration and a longitudinal displacement amount.
A boss is arranged on one side of the movable plate, which faces the spring assembly, and a plurality of spring mounting holes are uniformly distributed on the boss and used for mounting springs in the spring assembly; one side of the movable plate, which is far away from the spring assembly, is provided with a circular groove for arranging the measuring modules.
The guide rods are uniformly distributed on the periphery of the fixed plate and the movable plate, and the telescopic length of each guide rod can be adjusted.
One end of each guide rod is provided with a threaded part, a fixing nut is sleeved on the threaded part, and the telescopic length of each guide rod can be adjusted by adjusting the longitudinal position of the fixing nut on the guide rod.
The injection section comprises an injection pipe, and a movable plate mounting flange and a combustion chamber mounting flange which are respectively arranged at two ends of the injection pipe; the combustion chamber mounting flange is used for being connected with a combustion chamber; the movable plate mounting flange is used for being connected with the movable plate, and guide rod avoiding grooves with the same number as the guide rods are distributed on the periphery of the movable plate mounting flange.
The mounting flange of the movable plate is also provided with a threading hole for leading out a wire of a sensor in the measuring module.
The spring assembly comprises a plurality of springs which are arranged in parallel along the longitudinal direction.
When the longitudinal direction of the rocket engine is vertical, the vibration model of the research system is as follows:
ma=-kx-f-mg+F(t)
wherein,mmass of the engine module and the moving plate;athe longitudinal stretching acceleration of the movable plate is obtained by the measuring module;kin order to be the stiffness coefficient of the spring assembly,xobtaining the displacement of the movable plate for the measuring module;fthe sliding resistance of the guide rod is measured through a sliding test;gis the acceleration of gravity;F(t)thrust is the product of combustion chamber pressure and throat area.
By changing the stiffness coefficient of the springs and the number of the springs, the longitudinal vibration frequency of the research system can be changed, and the coupling relation of the structural vibration and the pressure oscillation on the frequency can be researched by combining the frequency of the pressure oscillation in the combustion chamber; the frequency of the pressure oscillation in the combustion chamber is obtained through FFT according to the measured data of the pressure sensor in the combustion chamber, and the structural vibration is obtained through FFT according to the measured data of the acceleration sensor.
The invention has the following beneficial effects:
1. the invention is based on the model engine structure, measures the axial vibration data of the engine, provides data support for summarizing the coupling relation between combustion and vibration, can conveniently research the coupling problem of the longitudinal combustion instability of an internal flow field and the axial vibration of the structure in the ignition test process of the rocket engine, and further can solve the actual problem of larger axial (longitudinal) vibration load when the liquid rocket engine is tested.
2. The invention replaces the prior fixed constraint through the constraint of the spring and the guide rail, and eliminates the interference of a constraint structure on a measurement result to a certain degree.
3. The invention simplifies the vibration of the engine into the forced vibration of the spring vibrator, completes the vibration decoupling, and only studies the coupling relation of combustion and vibration in the axial direction (longitudinal direction).
4. The system is simple in composition, each component is easy to process, the whole assembly is simple, and the subsequent replacement and transformation are facilitated.
Drawings
FIG. 1 is a schematic structural diagram of a rocket engine longitudinal unstable combustion and structural vibration coupling research system.
Fig. 2 shows a schematic top view of the movable plate according to the present invention.
Fig. 3 shows a schematic view of the bottom structure of the movable plate of the present invention.
Fig. 4 shows a schematic view of the structure of the injection section of the present invention.
Among them are:
10. a spring damping module;
11. fixing a plate;
12. a movable plate; 121. a spring mounting hole; 122. a circular groove; 123. a guide rod hole; 124. a bolt mounting hole; 125. a boss;
13. a spring assembly;
14. a guide bar; 141. a limiting head; 144. fixing a nut;
20. a measurement module;
30. an engine module;
31. an injection section;
311. mounting a flange on the movable plate; 311a guide bar escape slot; 311b, a threading hole;
312. a combustion chamber mounting flange;
313. an injector tube; 313a propellant filling port; 313b. A nozzle;
32. a combustion chamber; 33. a tail nozzle.
Detailed Description
The present invention will be described in further detail with reference to the drawings and specific preferred embodiments.
In the description of the present invention, it is to be understood that the terms "left side", "right side", "upper part", "lower part", etc., indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and that "first", "second", etc., do not represent an important degree of the component parts, and thus are not to be construed as limiting the present invention. The specific dimensions used in the present example are only for illustrating the technical solution and do not limit the scope of protection of the present invention.
As shown in FIG. 1, the research system for coupling the longitudinally unstable combustion of the rocket engine with the structural vibration comprises a spring damping module 10, a measurement module 20 and an engine module 30.
The spring damping module includes a stationary plate 11, a movable plate 12, a spring assembly 13, and guide rods 14.
The fixed plate is fixed in the longitudinal position, such as a top plate of the frame through bolts.
The movable plate and the fixed plate are arranged in parallel and coaxially, and a plurality of circular guide grooves, preferably four guide grooves, are uniformly distributed around the movable plate and the fixed plate; and a guide rod is arranged in each circular guide groove.
The guide rod is arranged along the longitudinal direction of the rocket engine and can guide the longitudinal extension of the spring assembly.
Each guide rod is preferably in the form of a bolt, including a stop head 141, a smooth rod portion and a threaded portion. Wherein, spacing head 141 is located the movable plate below, and smooth pole portion passes the circular guide slot of movable plate and the circular guide slot of deciding the board in proper order. Then, the fixing nut 144 is fitted over the threaded portion, and the length of each guide bar can be adjusted by adjusting the longitudinal position of the fixing nut on the threaded portion of the guide bar.
As shown in fig. 2 and 3, a boss 125 is disposed on one side of the movable plate facing the spring assembly, and a plurality of spring mounting holes 121 are uniformly distributed on the boss for mounting springs in the spring assembly; the side of the moving plate facing away from the spring assembly is provided with a circular recess 122 for the arrangement of the measurement modules.
The spring assembly is arranged between the fixed plate and the movable plate, and two ends of the spring assembly are respectively connected with the fixed plate and the movable plate; the spring assembly comprises a plurality of springs which are arranged in parallel along the longitudinal direction and can extend and retract along the longitudinal direction of the rocket engine.
The measuring module is embedded in the movable plate and can monitor the longitudinal telescopic data of the movable plate or the spring assembly in real time. The longitudinal expansion data includes one or a combination of a longitudinal expansion acceleration and a longitudinal displacement amount.
The engine module is coaxially mounted on the movable plate on a side facing away from the stationary plate.
The engine module comprises an injection section 31, a combustion chamber 32 and a tail nozzle 33 which are coaxially arranged along the longitudinal direction; wherein, be provided with pressure sensor in the combustion chamber, pressure sensor can monitor combustion chamber pressure.
As shown in fig. 4, the injection segment comprises an injection pipe 313, a movable plate mounting flange 311 and a combustion chamber mounting flange 312 which are respectively arranged at two ends of the injection pipe; the combustion chamber mounting flange is used for being connected with the combustion chamber; the movable plate mounting flange is used for being connected with the movable plate, and guide rod avoiding grooves 311a with the same number as the guide rods are distributed on the periphery of the movable plate mounting flange.
Furthermore, the movable plate mounting flange is also provided with a threading hole 311b for leading out a sensor in the measuring module. The threading holes are designed to be large holes and can also be lightening holes, so that the whole weight is lightened.
The injection tube is provided with a propellant filling port 313a and a nozzle 313b. The fuel and the oxidant are sprayed out through the nozzle and then are combusted in the combustion chamber section, and finally the fuel and the oxidant are sprayed out through the spray pipe section to form thrust.
When the longitudinal direction of the rocket engine is vertical, the vibration model of the research system is as follows:
ma=-kx-f-mg+F(t)
wherein,mmass of the engine module and the moving plate;athe longitudinal stretching acceleration of the movable plate is obtained by the measuring module;kin order to be the stiffness coefficient of the spring assembly,xobtaining the displacement of the movable plate for the measuring module;fthe sliding resistance of the guide rod is measured through a sliding test;gis the acceleration of gravity;F(t)thrust is the product of combustion chamber pressure and throat area.
When longitudinal combustion is unstable, the pressure in the combustion chamber oscillates greatly, so that the thrust also oscillates, the whole engine module and the movable plate vibrate, and the motion of the movable part can be simplified into forced vibration of the spring vibrator due to the guide rail constraint and the spring damping effect on the spring damping module. By changing the stiffness coefficient of the spring and the number of the springs, the longitudinal vibration frequency of the research system can be changed, and the coupling relation of the structural vibration and the pressure oscillation on the frequency can be researched by combining the frequency of the pressure oscillation in the combustion chamber; the frequency of the pressure oscillation in the combustion chamber is obtained by FFT through the measurement data of the pressure sensor in the combustion chamber, and the structural vibration is obtained by FFT through the measurement data of the acceleration sensor.
Based on the vibration model, the coupling relation between the longitudinal combustion instability and the structural vibration can be further researched by combining the vibration acceleration data and the combustion chamber pressure data.
The invention mainly researches the coupling relation between the longitudinal combustion instability and the structural vibration, and the assembled engine is in a vertical state. Considering that the overall mechanism is too high after the subsequent combustion chamber is lengthened, the design of the guide rod can be changed, and the overall system is changed into a horizontal structure.
The decoupling idea of the invention can also be used for analyzing the vibration of other structures, such as airplanes, ships and the like, and the experimental system can also be used for analyzing the single degree of freedom of the vibration of other structures.
Although the preferred embodiments of the present invention have been described in detail, the present invention is not limited to the details of the embodiments, and various equivalent changes may be made within the technical spirit of the present invention, and the technical scope of the present invention is also covered by the present invention.
Claims (10)
1. A system for researching longitudinal unstable combustion and structural vibration coupling of a rocket engine is characterized in that: the device comprises a spring damping module, a measuring module and an engine module;
the spring damping module comprises a fixed plate, a movable plate, a spring assembly and a guide rod;
fixing the longitudinal position of the fixed plate;
the movable plate and the fixed plate are arranged in parallel and coaxially;
the spring assembly is arranged between the fixed plate and the movable plate, and two ends of the spring assembly are respectively connected with the fixed plate and the movable plate; the spring assembly can longitudinally extend and retract along the rocket engine;
the guide rods are arranged on the fixed plate and the movable plate and are distributed along the longitudinal direction of the rocket engine, and can guide the longitudinal extension of the spring assembly;
the measuring module is embedded in the movable plate and can monitor the longitudinal expansion data of the movable plate or the spring assembly in real time;
the engine module is coaxially arranged on one side of the movable plate, which is far away from the fixed plate;
the engine module comprises a jetting section, a combustion chamber and a tail nozzle which are coaxially arranged along the longitudinal direction; wherein, be provided with pressure sensor in the combustion chamber, pressure sensor can monitor combustion chamber pressure.
2. A rocket engine longitudinally unstable combustion and structural vibration coupled research system as recited in claim 1, wherein: the longitudinal expansion and contraction data of the movable plate includes one or a combination of longitudinal expansion and contraction acceleration and longitudinal displacement.
3. A rocket engine longitudinally unstable combustion and structural vibration coupled research system as recited in claim 1, wherein: a boss is arranged on one side of the movable plate facing the spring assembly, and a plurality of spring mounting holes are uniformly distributed on the boss and used for mounting springs in the spring assembly; one side of the movable plate, which is far away from the spring assembly, is provided with a circular groove for arranging the measuring modules.
4. A rocket engine longitudinally unstable combustion and structural vibration coupled research system as recited in claim 1, wherein: the guide rods are uniformly distributed on the periphery of the fixed plate and the movable plate, and the telescopic length of each guide rod can be adjusted.
5. A rocket engine longitudinally unstable combustion and structural vibration coupling research system as recited in claim 4, wherein: one end of each guide rod is provided with a threaded part, a fixing nut is sleeved on the threaded part, and the telescopic length of each guide rod can be adjusted by adjusting the longitudinal position of the fixing nut on the guide rod.
6. A rocket engine longitudinally unstable combustion and structural vibration coupling research system as recited in claim 4, wherein: the injection section comprises an injection pipe, and a movable plate mounting flange and a combustion chamber mounting flange which are respectively arranged at two ends of the injection pipe; the combustion chamber mounting flange is used for being connected with a combustion chamber; the movable plate mounting flange is used for being connected with the movable plate, and guide rod avoiding grooves with the same number as the guide rods are distributed on the periphery of the movable plate mounting flange.
7. A rocket engine longitudinally unstable combustion and structural vibration coupled research system as recited in claim 6, wherein: the mounting flange of the movable plate is also provided with a threading hole for leading out a wire of a sensor in the measuring module.
8. A rocket engine longitudinally unstable combustion and structural vibration coupled research system as recited in claim 1, wherein: the spring assembly comprises a plurality of springs which are arranged in parallel along the longitudinal direction.
9. A rocket engine longitudinally unstable combustion and structural vibration coupling research system as recited in claim 8, wherein: when the longitudinal direction of the rocket engine is vertical, the vibration model of the research system is as follows:
ma=-kx-f-mg+F(t)
wherein,mmass of the engine module and the moving plate;athe longitudinal stretching acceleration of the movable plate is obtained by the measuring module;kin order to be the stiffness coefficient of the spring assembly,xobtaining the displacement of the movable plate for the measuring module;fthe sliding resistance of the guide rod is measured through a sliding test;gis the acceleration of gravity;F(t)thrust is the product of combustion chamber pressure and throat area.
10. A rocket engine longitudinally unstable combustion and structural vibration coupled research system according to claim 8 or 9, characterized in that: by changing the stiffness coefficient of the spring and the number of the springs, the longitudinal vibration frequency of the research system can be changed, and the coupling relation of the structural vibration and the pressure oscillation in the combustion chamber on the frequency can be researched by combining the frequency of the pressure oscillation in the combustion chamber; and the frequency of the pressure oscillation in the combustion chamber is obtained by FFT (fast Fourier transform) according to the measured data of the pressure sensor in the combustion chamber.
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| CN202111269253.5A CN114233524B (en) | 2021-10-29 | 2021-10-29 | Research system for coupling of longitudinal unstable combustion and structural vibration of rocket engine |
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| CN202111269253.5A CN114233524B (en) | 2021-10-29 | 2021-10-29 | Research system for coupling of longitudinal unstable combustion and structural vibration of rocket engine |
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| CN114233524A CN114233524A (en) | 2022-03-25 |
| CN114233524B true CN114233524B (en) | 2023-03-10 |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH07301151A (en) * | 1994-05-02 | 1995-11-14 | Daicel Chem Ind Ltd | Burner for testing solid propellant vibration combustion characteristic |
| CN102072046A (en) * | 2010-12-09 | 2011-05-25 | 北京航空航天大学 | Gas-gas combustor support device for test |
| CN109488488A (en) * | 2018-12-18 | 2019-03-19 | 中国人民解放军战略支援部队航天工程大学 | Test section suitable for combustion instability optical measurement longitudinal under high temperature and high pressure environment |
| CN112432792A (en) * | 2020-11-25 | 2021-03-02 | 哈尔滨工程大学 | Solid rocket engine test frame based on magnetic suspension non-contact weak constraint |
| CN112610364A (en) * | 2020-12-29 | 2021-04-06 | 内蒙航天动力机械测试所 | Solid rocket engine elasticity weak constraint test stand |
-
2021
- 2021-10-29 CN CN202111269253.5A patent/CN114233524B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH07301151A (en) * | 1994-05-02 | 1995-11-14 | Daicel Chem Ind Ltd | Burner for testing solid propellant vibration combustion characteristic |
| CN102072046A (en) * | 2010-12-09 | 2011-05-25 | 北京航空航天大学 | Gas-gas combustor support device for test |
| CN109488488A (en) * | 2018-12-18 | 2019-03-19 | 中国人民解放军战略支援部队航天工程大学 | Test section suitable for combustion instability optical measurement longitudinal under high temperature and high pressure environment |
| CN112432792A (en) * | 2020-11-25 | 2021-03-02 | 哈尔滨工程大学 | Solid rocket engine test frame based on magnetic suspension non-contact weak constraint |
| CN112610364A (en) * | 2020-12-29 | 2021-04-06 | 内蒙航天动力机械测试所 | Solid rocket engine elasticity weak constraint test stand |
Non-Patent Citations (1)
| Title |
|---|
| 单喷嘴模型发动机纵向高频燃烧不稳定性实验分析;王迪等;《实验流体力学》;20180430;第32卷(第02期);第18-23页 * |
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