CN115112376A - Gas injection and propellant coupling effect observation test device - Google Patents
Gas injection and propellant coupling effect observation test device Download PDFInfo
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- CN115112376A CN115112376A CN202210790926.XA CN202210790926A CN115112376A CN 115112376 A CN115112376 A CN 115112376A CN 202210790926 A CN202210790926 A CN 202210790926A CN 115112376 A CN115112376 A CN 115112376A
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- transparent window
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D21/00—Measuring or testing not otherwise provided for
- G01D21/02—Measuring two or more variables by means not covered by a single other subclass
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Abstract
The invention relates to a test device for observing coupling effect of fuel gas injection and propellant, which is characterized by comprising an igniter, a measuring section, a spray pipe and a machine base, wherein the measuring section is fixed on the machine base, the igniter is arranged at the front end of the measuring section, and the spray pipe is arranged at the rear end of the measuring section. The invention can observe the coupling effect of fuel gas injection and propellant, solves the problem that the flame propagation rule of the combustion chamber of the solid engine cannot be observed before, improves the accuracy and safety of temperature and pressure measurement by punching in the testing device, and is more compact and reasonable in arrangement.
Description
Technical Field
The invention relates to the technical field of engine tests, in particular to a solid rocket engine ground test bed and a test device for observing the coupling effect of gas injection and propellant.
Background
The solid rocket engine ignition transient process can be divided into three parts: the device comprises an induction section, a flame diffusion section and a fuel gas filling section. The induction period is defined as the time interval from the operation of the igniter to the first occurrence of ignition on the surface of the propellant; the flame spread is defined as the time interval from the first ignition of the propellant surface to the complete ignition of the entire propellant charge; the gas charge is defined as the time interval between the end of flame propagation and the attainment of the combustion chamber equilibrium.
With the continuous improvement of technical indexes of the solid rocket engine, how to accurately predict the ignition transient process becomes a main difficulty of the internal trajectory of the solid rocket engine. During the ignition transient process, along with the propagation of ignition flame, the gas jet of the igniter interacts with the propellant, and the force/thermal coupling rule between the gas jet and the propellant is a necessary condition for indicating the ignition transient process. The different ignition intensity can influence the flame diffusion speed undoubtedly, and the wing grooves and the explosive columns with different shapes can influence the flow of fuel gas in the wing grooves, whether the transient response can influence the normal work of the engine or not reveals that the coupling action mechanism of fuel gas injection and propellant is a key problem in the whole ignition process.
Due to the instability of the solid grain, the direct punching of the propellant to connect the sensor presents a great risk, and the pressure and the temperature inside the grain are difficult to measure; in addition, the existing engine test device is sealed by high-temperature alloy steel, so that the flame propagation rule in the combustion chamber cannot be directly observed. Therefore, the research on the coupling action mechanism of the fuel gas injection and the propellant through a test method becomes one of the problems in the field of the current solid engine.
The transparent window is arranged on the measuring section of the solid engine, and the flame propagation rule is observed through the transparent window by using the high-speed camera, so that the problems that the combustion change of the explosive column, the combustion change of the flame and the like cannot be directly observed at present are solved. Meanwhile, a pressure sensor and a temperature sensor embedded in the middle of the grain are used for measuring temperature and pressure of the burning grain, data are collected through a pressure collection system and a temperature collection system, and the problem that holes cannot be punched on the grain to measure pressure and temperature is solved.
Disclosure of Invention
Aiming at the defects of the prior art, the invention aims to provide the test device for observing the coupling effect of the gas injection and the propellant, which can observe the coupling effect of the gas injection and the propellant, solves the problem that the flame combustion change cannot be observed before, and simultaneously improves the accuracy and the safety of temperature and pressure measurement by punching in the test device, and the arrangement is more compact and reasonable.
The invention is realized by the following technical scheme.
The device for observing and testing the coupling effect of the fuel gas injection and the propellant is characterized by comprising an igniter, a measuring section, a spray pipe and a machine base, wherein the measuring section is fixed on the machine base;
the measuring section comprises a combustion chamber, a transparent window clamping plate, a transparent window, a temperature sensor, a pressure sensor, a grain and a high-speed camera, the combustion chamber is fixed on the base through bolts, the transparent window clamping plate is matched with the combustion chamber to detachably install the transparent window above the combustion chamber, the high-speed camera is arranged above the transparent window, a plurality of grooves for installing the grain are formed in the combustion chamber at intervals, a plurality of through holes are formed in the combustion chamber between every two adjacent grooves, the through holes are used for arranging the temperature sensor and the pressure sensor, and data collected by the temperature sensor and the pressure sensor enter a data analysis system terminal.
Further, the measuring section still includes preceding blanking cover, preceding blanking cover passes through the bolt and installs the front end at combustion chamber and transparent window cardboard, some firearm are installed in the front on the blanking cover.
Furthermore, the rear end of the spray pipe is provided with a rear plugging cover.
Furthermore, the measuring section is divided into an upper semicircle part and a lower semicircle part, the upper semicircle part is the transparent window clamping plate and the transparent window, and the lower semicircle part is the combustion chamber.
Further, the temperature sensors and the pressure sensors are alternately distributed around the semi-cylinder at intervals of 30 degrees.
Compared with the prior art, the invention has the advantages that: the invention utilizes the high-speed camera to observe the flame combustion change through the transparent window, and solves the problems that the combustion change of the explosive column, the flame combustion change and the like cannot be directly observed at present. The pressure sensor and the temperature sensor embedded in the middle of the grain carry out temperature and pressure measurement on the burning grain, and data acquisition is carried out through the pressure acquisition system and the temperature acquisition system, so that the problem that the grain cannot be punched to measure the pressure and the temperature is solved. The combustion chamber is connected with the spray pipe through the bolt, the spray pipe with different parameters can be conveniently replaced, the structure is simple, and the working efficiency is high. The whole test device has higher safety factor and reliability, and can meet the requirement of repeated use.
Drawings
FIG. 1 is a front view of the present invention;
FIG. 2 is a left side view of the present invention (high speed camera not shown);
FIG. 3 is a top view of the present invention (high speed camera not shown);
FIG. 4 is a standard isometric view of the present invention (high speed camera not shown);
FIG. 5 is an exploded view of the present invention (high speed camera not shown);
FIG. 6 is a schematic view of the installation position of the temperature/pressure sensor of the apparatus of the present invention;
FIG. 7 is a schematic view of the sensor location distribution of the present invention;
FIG. 8 is a flow chart of the present invention;
in the figure: 1. an igniter; 2. a bolt; 3. the transparent window clamping plate; 4. a transparent window; 5. a nozzle; 6. a rear blanking cover; 7. a combustion chamber; 8. a machine base; 9. a front blanking cover; 10. a temperature sensor; 11. a pressure sensor; 12. carrying out grain treatment; 13. high-speed camera 701, recess.
Detailed Description
The invention is further described with reference to the following drawings and specific examples, which are not intended to be limiting.
As shown in fig. 1 to 7, the observation test device for coupling effect of gas injection and propellant is characterized by comprising an igniter 1, a measuring section, a spray pipe 5 and a base 8, wherein the measuring section is fixed on the base 8, the igniter 1 is arranged at the front end of the measuring section, and the spray pipe 5 is arranged at the rear end of the measuring section;
the measuring section includes combustion chamber 7, transparent window cardboard 3, transparent window 4, temperature sensor 10, pressure sensor 11, powder column 12, high-speed camera 13, combustion chamber 7 passes through the bolt fastening on frame 8, transparent window cardboard 3 cooperates with combustion chamber 7 with transparent window 4 demountable installation in combustion chamber 7 top, high-speed camera 13 sets up the top of transparent window 4, 7 intervals in combustion chamber set up a plurality of installations that are used for of powder column 12 the last adjacent two of combustion chamber 7 be provided with a plurality of through-holes between the recess, the through-hole is used for setting up temperature sensor 10 and pressure sensor 11, the data that temperature sensor 10 and pressure sensor 11 gathered get into data analysis system terminal.
Further, the measuring section still includes preceding blanking cover 9, preceding blanking cover 9 passes through the bolt and installs the front end at combustion chamber 7 and transparent window cardboard 3, some firearm 1 is installed on preceding blanking cover 9.
Further, the rear end of the spray pipe 5 is provided with a rear plugging cover 6.
Further, the measuring section is divided into an upper semicircular part and a lower semicircular part, the upper semicircular part is the transparent window clamping plate 3 and the transparent window 4, and the lower semicircular part is the combustion chamber 7.
Further, the temperature sensors 10 and the pressure sensors 11 are alternately distributed around the semi-cylinder at intervals of 30 °.
The transparent window passes through transparent window cardboard and the laminating of combustion chamber, simultaneously through the bolt fastening. Because the solid propellant can generate black metal particles to be attached to the surface of the transparent window when being burnt, the invention adopts the structure of the replaceable transparent window, the clamping plate is opened after the test is finished each time, and the transparent window is replaced, thereby being convenient for high-speed photography and shooting. High-speed photographic appearance is installed in the engine top, can directly clap ignition transient state process and flame propagation process through the transparent window to solve test device and can't pass through observation difficulty problems such as direct observation powder column burning change, flame burning state change. In order to measure the pressure intensity and the temperature distribution of different parts, a pressure sensor and a temperature sensor are embedded in the middle of the grain to measure the temperature and the pressure of the burning grain, and data acquisition is carried out through a pressure acquisition system and a temperature acquisition system. The problem that experimental data such as pressure intensity, temperature and the like in the ignition transient process are difficult to collect due to the fact that a traditional experimental instrument cannot punch a hole in a explosive column can be solved. The measuring section and the spraying pipe section are connected through bolts, and the spraying pipe assembly with the structure has the advantages that spraying pipes with the same overall dimension but different design Mach numbers can be replaced at any time, so that the experiment for researching the coupling of gas spraying and propellant under different design Mach numbers under different nozzles is met.
Meanwhile, the whole test device has higher safety factor and reliability, and can meet the requirement of repeated use for many times. The metal force-bearing parts of the test device are mostly of a thick-wall structure, the safety coefficient is very high and generally above 10, and meanwhile, the characteristic of large heat capacity of thick-wall metal is utilized to prevent high-temperature gas from damaging the test device; the safety coefficient of the main non-metal component and the transparent window is more than 6, and meanwhile, the used fuel adopts low-combustion-temperature propellant, and the combustion temperature is 2100K. The safety margin of the test device is guaranteed to meet the experiment requirement.
While the invention has been described with reference to a preferred embodiment, it will be understood by those skilled in the art that various changes in form and detail may be made therein without departing from the spirit and scope of the invention.
Claims (5)
1. The test device for observing the coupling effect of the fuel gas injection and the propellant is characterized by comprising an igniter (1), a measuring section, a spray pipe (5) and a base (8), wherein the measuring section is fixed on the base (8), the igniter (1) is arranged at the front end of the measuring section, and the spray pipe (5) is arranged at the rear end of the measuring section;
the measuring section comprises a combustion chamber (7), a transparent window clamping plate (3), a transparent window (4), a temperature sensor (10), a pressure sensor (11), a grain (12) and a high-speed camera (13), the combustion chamber (7) is fixed on the machine base (8) through bolts, the transparent window clamping plate (3) is matched with the combustion chamber (7) to detachably install the transparent window (4) above the combustion chamber (7), the high-speed camera (13) is arranged above the transparent window (4), a plurality of grooves (701) for installing the explosive columns (12) are arranged at intervals in the combustion chamber (7), a plurality of through holes are arranged between two adjacent grooves on the combustion chamber (7), the through hole is used for arranging the temperature sensor (10) and the pressure sensor (11), and data acquired by the temperature sensor (10) and the pressure sensor (11) enter a data analysis system terminal.
2. Observation test device for coupling effect of gas injection and propellant according to claim 1, characterized in that said measuring section further comprises a front cover (9), said front cover (9) is mounted on the front end of the combustion chamber (7) and the transparent window clamping plate (3) by bolts, said igniter (1) is mounted on the front cover (9).
3. Observation test device for coupling effect of gas injection and propellant according to claim 1, characterized in that the rear end of the nozzle (5) is provided with a rear closure (6).
4. The gas injection and propellant coupling observation test device of claim 1, wherein the measuring section is divided into an upper semicircular part and a lower semicircular part, the upper semicircular part is the transparent window clamping plate (3) and the transparent window (4), and the lower semicircular part is the combustion chamber (7).
5. Observation test device for coupling effect of gas injection and propellant according to claim 1, characterized in that said temperature sensors (10) and pressure sensors (11) are alternately distributed around a semi-cylinder at 30 ° intervals.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202210790926.XA CN115112376A (en) | 2022-07-05 | 2022-07-05 | Gas injection and propellant coupling effect observation test device |
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| CN202210790926.XA CN115112376A (en) | 2022-07-05 | 2022-07-05 | Gas injection and propellant coupling effect observation test device |
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| CN115112376A true CN115112376A (en) | 2022-09-27 |
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| CN202210790926.XA Pending CN115112376A (en) | 2022-07-05 | 2022-07-05 | Gas injection and propellant coupling effect observation test device |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116291970A (en) * | 2023-02-13 | 2023-06-23 | 南昌航空大学 | Observable solid rocket engine ignition test platform |
| CN116625694A (en) * | 2023-07-21 | 2023-08-22 | 中国空气动力研究与发展中心空天技术研究所 | Quick replacement device for optical observation glass of scramjet engine |
| CN116735386A (en) * | 2023-06-19 | 2023-09-12 | 北京理工大学 | Free-filling solid propellant ignition impact visual test device and method |
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| CN112526058A (en) * | 2020-11-04 | 2021-03-19 | 东南大学 | Small-thrust solid propellant grain combustion and propulsion performance detection test device |
| CN113417760A (en) * | 2021-06-18 | 2021-09-21 | 西北工业大学 | Solid propellant oxygen combustion split charging coupled combustion transparent window experimental device and experimental method |
| CN114047286A (en) * | 2021-11-05 | 2022-02-15 | 西北工业大学 | Modularized oxygen-enriched fuel gas rich combustion characteristic testing device |
| CN114352440A (en) * | 2022-01-07 | 2022-04-15 | 北京理工大学 | Modular solid rocket ramjet ground direct connection test device |
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| CN105651809A (en) * | 2015-12-31 | 2016-06-08 | 中国人民解放军国防科学技术大学 | Experimental device for particle combustion under high speed air flow |
| CN110596301A (en) * | 2019-10-14 | 2019-12-20 | 西安近代化学研究所 | Test engine and test method for combustion of double-base propellant in different overload directions |
| CN211524967U (en) * | 2019-11-01 | 2020-09-18 | 湖北航天化学技术研究所 | Solid rocket engine nozzle blanking cover opening pressure test tool |
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| CN113417760A (en) * | 2021-06-18 | 2021-09-21 | 西北工业大学 | Solid propellant oxygen combustion split charging coupled combustion transparent window experimental device and experimental method |
| CN114047286A (en) * | 2021-11-05 | 2022-02-15 | 西北工业大学 | Modularized oxygen-enriched fuel gas rich combustion characteristic testing device |
| CN114352440A (en) * | 2022-01-07 | 2022-04-15 | 北京理工大学 | Modular solid rocket ramjet ground direct connection test device |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116291970A (en) * | 2023-02-13 | 2023-06-23 | 南昌航空大学 | Observable solid rocket engine ignition test platform |
| CN116735386A (en) * | 2023-06-19 | 2023-09-12 | 北京理工大学 | Free-filling solid propellant ignition impact visual test device and method |
| CN116735386B (en) * | 2023-06-19 | 2024-04-19 | 北京理工大学 | Free-filling solid propellant ignition impact visual test device and method |
| CN116625694A (en) * | 2023-07-21 | 2023-08-22 | 中国空气动力研究与发展中心空天技术研究所 | Quick replacement device for optical observation glass of scramjet engine |
| CN116625694B (en) * | 2023-07-21 | 2023-10-13 | 中国空气动力研究与发展中心空天技术研究所 | Quick replacement device for optical observation glass of scramjet engine |
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