CN114184642B - Solid propellant high-pressure ignition and combustion suspension test device - Google Patents
Solid propellant high-pressure ignition and combustion suspension test device Download PDFInfo
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- CN114184642B CN114184642B CN202210140376.7A CN202210140376A CN114184642B CN 114184642 B CN114184642 B CN 114184642B CN 202210140376 A CN202210140376 A CN 202210140376A CN 114184642 B CN114184642 B CN 114184642B
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Abstract
The invention relates to a solid propellant high-pressure ignition and combustion suspension test device which comprises a high-pressure combustion chamber component, a pressure-resistant power supply component, a window breaking component arranged on the side surface of the high-pressure combustion chamber component and a pressure-bearing incident light path component arranged at the top of the high-pressure combustion chamber component, wherein each component is welded and sealed with the high-pressure combustion chamber component, a thermocouple is arranged in the high-pressure combustion chamber component, and a plurality of observation windows are arranged on the periphery of the high-pressure combustion chamber component. The windows are arranged in multiple directions of the combustion chamber, so that ignition and agglomeration of metal particles and synchronous measurement of a combustion flame structure and flame temperature distribution in the ignition combustion process of the solid propellant in a high-pressure environment are realized, and the data quantity and the data types which can be obtained in a test are increased; meanwhile, high-energy laser is used as a heat source required by ignition, based on the characteristic that the solid propellant cannot maintain stable combustion under the low-pressure condition, the combustion of the solid propellant is stopped by adopting a window breaking pressure relief mode, and therefore different ignition combustion stages of the solid propellant are analyzed.
Description
Technical Field
The invention relates to a solid propellant high-pressure ignition and combustion suspension test device, and belongs to the technical field of solid propellant ignition.
Background
The laser ignition is an ignition mode with high safety, reliable performance and rapid ignition in the experimental research of the ignition and combustion of the solid propellant, the ignition energy and the energy density are flexibly and precisely adjusted, the influence of environmental factors such as the pressure intensity, the temperature and the like of the solid propellant is avoided, and the laser ignition is suitable for the experimental research of the ignition and combustion process of the solid propellant.
However, the existing solid propellant laser ignition test device cannot synchronously measure the ignition and agglomeration of metal particles and the temperature distribution of combustion flame structure and flame in the ignition and combustion process of a solid propellant in a high-pressure environment, and cannot stop the combustion process of the propellant so as to analyze different ignition and combustion stages of the solid propellant.
The laser ignition test bed with the power measurement function proposed in the chinese patent 201911041562.X can only observe a laser ignition combustion test from a single window and shoot with a high-speed camera and other devices, but can only obtain image data in a single direction, and cannot simultaneously measure the experimental process by using a thermal infrared imager, an optical fiber spectrometer and a high-speed camera.
The existing test system has a limited pressure range for realizing the combustion of the solid propellant, and cannot realize an ignition test in a higher pressure environment.
Therefore, the invention provides a test device which can synchronously measure various test data and can immediately terminate the combustion process of the propellant for analysis.
Disclosure of Invention
In order to solve the technical problems, the invention provides a solid propellant high-pressure ignition and combustion suspension test device, which has the following specific technical scheme:
a high-pressure ignition and combustion suspension test device for a solid propellant comprises a high-pressure combustion chamber component A, wherein the high-pressure combustion chamber component A comprises a cylinder body, solid fuel is arranged in the cylinder body, a plurality of pressure-resistant power supply components B are arranged on the side wall of the cylinder body close to the lower position in a penetrating manner, a plurality of observation windows are uniformly arranged on the circumference of the side wall of the cylinder body, a window breaking component C is fixedly arranged on the outer side of one of the observation windows, an upper welding flange is arranged at the top of the cylinder body, a lower bottom plate is arranged at the bottom of the cylinder body, a pressure-bearing incident light path component D is arranged at the center of the upper welding flange,
when the test is started, the laser ignites the solid fuel through the pressure-bearing incident light path component D;
when the combustion reaction needs to be stopped, the window breaking component C breaks the observation window on the side face of the high-pressure combustion chamber component A, releases high-pressure gas in the high-pressure combustion chamber component A, and destroys a high-pressure environment required by solid fuel combustion.
Furthermore, a threaded sleeve is arranged in the center of the lower base plate, a propellant placing screw is arranged in the threaded sleeve, pressure-bearing optical glass is embedded in each observation window, a glass sealing welding seat is arranged on the periphery of each observation window, a plurality of threaded holes which are uniformly distributed in the circumferential direction are formed in the lower position of the cylinder, and the pressure-resistant power supply assembly B is arranged in the threaded holes in a threaded connection mode.
Further, the barrel still connects and is equipped with intake pipe, blast pipe, evacuation pipe and digital display manometer, all connects through the screw hole and establishes.
Furthermore, a plurality of thermocouple installation seats are arranged on a lower bottom plate of the high-pressure combustion chamber component A, the thermocouple installation seats are connected to the low-resistance conductive threaded rods through wires, and each thermocouple installation seat is provided with a thermocouple.
Further, withstand voltage power supply unit B includes the bolt body and sets up two low resistance conductive threaded rods at the internal portion of bolt, be provided with insulating cover between the bolt body and the low resistance conductive threaded rod, the bolt body pass through lock nut with insulating cover fixed, insulating cover includes from the lower insulating cover that upwards sets gradually, well insulating cover and last insulating cover down, it surpasss bolt body aperture to go up insulating cover edge, low resistance conductive threaded rod upper end surpasss the bolt body, and the lower extreme is internal at the bolt.
Furthermore, the window breaking assembly C comprises a sliding sleeve, one end of the sliding sleeve is fixed with a mounting seat, a stopping sliding sleeve and a window breaking firing pin are arranged in the sliding sleeve, one end of the window breaking firing pin faces the mounting seat, the other end of the window breaking firing pin is fixed on the stopping sliding sleeve, a window breaking hole is formed in the position, opposite to the window breaking firing pin, of the mounting seat, an energy storage spring is arranged on one side, far away from the mounting seat, of the stopping sliding sleeve, and a stopping device is arranged on one side of the sliding sleeve.
Furthermore, an inner thread groove is formed in the center of the stop sliding sleeve, an outer thread is arranged at one end, far away from the mounting seat, of the broken window firing pin, and the stop sliding sleeve and the broken window firing pin are fixed in a spiral mode through the inner thread and the outer thread.
Furthermore, the window breaking component C is fixed on a glass sealing welding seat of the high-pressure combustion chamber component A through a mounting seat, one side of the sliding sleeve is provided with a stop hole, the stop sliding sleeve is provided with a stop groove on the same side with the stop hole, the sliding sleeve is fixedly provided with a stop device through the stop hole,
the stopping device comprises an L-shaped limiting fixing piece and a traction magnet mounting seat, one side of the L-shaped limiting fixing piece is fixed on the traction magnet mounting seat, the other side of the L-shaped limiting fixing piece is provided with a through hole, the traction magnet mounting seat is provided with a traction magnet along the radial direction of the sliding sleeve, one end of the traction magnet, which faces to the stopping hole, is fixed with a fork-shaped limiting rod,
when the energy storage spring is in the maximum contraction state, the stop groove is opposite to the stop hole, and when the window breaking assembly C is in the stop state, the fork-shaped limiting rod is embedded in the stop groove through the through hole.
Further, the pressure-bearing incident light path component D comprises a pressure-bearing water-cooling cover, the pressure-bearing water-cooling cover is provided with a one-stage step-shaped through hole, pressure-bearing laser glass is embedded in the one-stage step-shaped through hole, a cooling water inlet pipe and a cooling water outlet pipe are respectively arranged on two sides of the aperture direction of the one-stage step-shaped through hole, a cooling ring cavity is arranged in the pressure-bearing incident light path component D, the cooling ring cavity is communicated with the cooling water inlet pipe and the cooling water outlet pipe, and the upper end face and the lower end face of the pressure-bearing laser glass are both provided with sealing buffer gaskets.
Furthermore, the upper welding flange and the window breaking assembly C are fixedly connected with the high-pressure combustion chamber assembly A through hexagon bolts, the pressure-bearing incident light path assembly D is provided with a plurality of unthreaded holes, the pressure-bearing incident light path assembly D penetrates through the unthreaded holes through the hexagon bolts to be fixedly connected with the high-pressure combustion chamber assembly A, and a red copper gasket is arranged between the upper welding flange and the hexagon bolts.
The beneficial effects of the invention are: the windows are arranged in multiple directions of the combustion chamber, so that ignition and agglomeration of metal particles and synchronous measurement of a combustion flame structure and flame temperature distribution in the ignition combustion process of the solid propellant in a high-pressure environment are realized, and the data quantity and the data types which can be obtained in a test are increased; meanwhile, high-energy laser is used as a heat source required by ignition, based on the characteristic that the solid propellant cannot maintain stable combustion under the low-pressure condition, the combustion of the solid propellant is stopped by adopting a window breaking pressure relief mode, so that different ignition combustion stages of the solid propellant are analyzed; the testing device can realize the experimental research of the ignition combustion process of the solid propellant in the pressure range of 0-10MPa, and has wider application range.
Drawings
Figure 1 is a schematic view of the present invention from one perspective,
figure 2 is a side view of the present invention,
figure 3 is a schematic view of the N-N cross section of the present invention,
figure 4 is a bottom view of the present invention,
figure 5 is a schematic view of a high pressure fuel chamber assembly a of the present invention,
figure 6 is a schematic view of a voltage-withstanding power supply assembly B of the present invention,
figure 7 is a schematic view of a breaking assembly C according to the present invention,
figure 8 is a schematic cross-sectional view of a breaking assembly C of the present invention,
figure 9 is a schematic cross-sectional view of a pressure-bearing incident optical path component D of the present invention,
figure 10 is a bottom view of the pressure bearing incident optical path assembly D of the present invention,
in the figure: 1-a threaded sleeve, 2-an upper welding flange, 3-a lower bottom plate, 4-a barrel, 5-a glass sealing welding seat, 6-a multipurpose threaded hole, 7-a low-resistance conductive threaded rod, 8-a lower insulating sleeve, 9-a middle insulating sleeve, 10-a locking nut, 11-a plug body, 12-an upper insulating sleeve, 13-a window breaking firing pin, 14-a stop sliding sleeve, 15-a fork-shaped limiting rod, 16-an elastic energy accumulator, 17-a sliding sleeve, 18-a mounting seat, 20-an L-shaped limit fixing part, 21-a traction magnet mounting seat, 24-pressure-bearing laser glass, 25-a pressure-bearing water cooling cover, 26-a cooling water outlet pipe, 27-a light hole, 28-a sealing buffer gasket, 29-a cooling water inlet pipe, 32-a red copper gasket, 36-a propellant placing threaded rod, 37-a thermocouple mounting seat, 38-a traction magnet, 39-an observation window, 40-a stop groove, 41-a stop hole, 42-a through hole, 43-a cooling ring cavity, 44-an air inlet pipe, 45-an exhaust pipe, 46-an evacuation pipe and 47-a digital display pressure gauge.
Detailed Description
The present invention is further illustrated by the following figures and specific examples, which are to be understood as illustrative only and not as limiting the scope of the invention, which is to be given the full breadth of the appended claims and any and all equivalent modifications thereof which may occur to those skilled in the art upon reading the present specification.
As shown in figure 1, the solid propellant high-pressure ignition and combustion suspension test device comprises a high-pressure combustion chamber component A, a pressure-resistant power supply component B, a broken window component C arranged on the side surface of the high-pressure combustion chamber component A and a pressure-bearing incident light path component D arranged at the top of the high-pressure combustion chamber component A,
as shown in fig. 5, the high pressure combustion chamber assembly a comprises a cylinder 4, an upper welding flange 2 is welded on the top of the cylinder 4, a lower bottom plate 3 is welded on the bottom, a threaded sleeve 1 is arranged in the center of the lower bottom plate 3, a plurality of thermocouple installation seats 37 are arranged on the lower bottom plate 3 around the threaded sleeve 1, each thermocouple installation seat 37 is provided with a thermocouple, as shown in fig. 3, a propellant placing screw 36 is arranged in the threaded sleeve 1, as shown in fig. 2, four observation windows 39 are uniformly arranged on the side wall of the cylinder 4, pressure-bearing laser glass 24 is embedded in the observation windows 39, a glass sealing welding seat 5 is arranged around each observation window 39, as shown in fig. 4, a plurality of threaded holes 6 are uniformly distributed in the circumferential direction at the lower position of the cylinder 4, and the cylinder 4 is further connected with an air inlet pipe 44, an air outlet pipe 45, an evacuation pipe 46 and a digital pressure gauge 47 which are all connected to the cylinder 4 through the threaded holes 6;
as shown in fig. 6, the voltage-resistant power supply assembly B is disposed in the threaded hole 6 by a threaded connection manner, the voltage-resistant power supply assembly B includes a bolt body 11, two low-resistance conductive threaded rods 7 are disposed in the bolt body 11, an insulating sleeve is disposed between the bolt body 11 and the low-resistance conductive threaded rods 7, the low-resistance conductive threaded rods 6, the bolt body 11 and the insulating sleeve are fixed by a lock nut 10, the insulating sleeve includes a lower insulating sleeve 8, a middle insulating sleeve 9 and an upper insulating sleeve 12, which are sequentially disposed from bottom to top, an edge of the upper insulating sleeve 12 exceeds an aperture of the bolt body 11, an upper end of the low-resistance conductive threaded rod 7 exceeds the bolt body 11, a lower end of the low-resistance conductive threaded rod 7 is in the bolt body 11, and a thermocouple mounting seat 37 is connected to the low-resistance conductive threaded rod 7 by a wire;
as shown in fig. 7, the window breaking assembly C includes a sliding sleeve 17, one end of the sliding sleeve 17 is fixed with a mounting seat 18, as shown in fig. 8, a stopping sliding sleeve 14 and a window breaking firing pin 13 facing the mounting seat 18 are arranged in the sliding sleeve 17, the window breaking firing pin 13 is fixed in the stopping sliding sleeve 14 through internal and external threads, one side of the stopping sliding sleeve 14, which is far away from the mounting seat 18, is provided with an energy storage spring 16, the window breaking assembly C is fixed on the glass sealing welding seat 5 of the high pressure combustion chamber assembly a through the mounting seat 18, one side of the sliding sleeve 17 is provided with a stopping hole 41, and the sliding sleeve 17 is fixedly provided with a stopping device through the stopping hole 41;
the stopping device comprises an L-shaped limiting fixing piece 20 and a traction magnet mounting seat 21, one side of the L-shaped limiting fixing piece 20 is fixed on the traction magnet mounting seat 21, the other side of the L-shaped limiting fixing piece 20 is provided with a through hole 42, the traction magnet mounting seat 21 is radially provided with a traction magnet 38 along a sliding sleeve 17, one end of the traction magnet 38, which faces to a stopping hole 41, is fixed with a forked limiting rod 15, the same side of the stopping sliding sleeve 14 and the stopping hole 41 is provided with a stopping groove 40, when the energy storage spring 16 is in a maximum contraction state, the stopping groove 40 is over against the stopping hole 41, and when the window breaking assembly C is in a stopping state, the forked limiting rod 15 is embedded in the stopping groove 40 through the through hole 42;
as shown in fig. 9, the pressure-bearing incident optical path component D includes a pressure-bearing water-cooling cover 25, a pressure-bearing laser glass 24 is embedded in the pressure-bearing water-cooling cover 25, the pressure-bearing water-cooling cover 25 is provided with a one-stage step-shaped through hole, two sides of the aperture direction of the one-stage step-shaped through hole are respectively provided with a cooling water inlet pipe 29 and a cooling water outlet pipe 26, as shown in fig. 10, a cooling ring cavity 43 is provided between the cooling water inlet pipe 29 and the cooling water outlet pipe 26 in the pressure-bearing incident optical path component D, and both the upper end surface and the lower end surface of the pressure-bearing laser glass 24 are provided with a sealing buffer gasket 28.
Go up welded flange 2 and broken window subassembly C and all be connected fixedly through hexagon bolt and high pressure combustion chamber subassembly A, a plurality of unthreaded holes 27 have been seted up to pressure-bearing incident light path subassembly D, and pressure-bearing incident light path subassembly D passes unthreaded hole 27 through hexagon bolt and is connected fixedly with high pressure combustion chamber subassembly A, goes up and is provided with red copper gasket 32 between welded flange 2 and the hexagon bolt.
And all the components are welded and sealed with the high-pressure combustion chamber component A and are fixed by penetrating hexagon bolts.
The high-pressure combustion chamber assembly A and the upper welding flange 2 are fixed through the hexagon bolts, the red copper gasket 32 is arranged between the high-pressure combustion chamber assembly A and the upper welding flange 2, and gas in the high-pressure combustion chamber assembly A is prevented from leaking through a gap between the high-pressure combustion chamber assembly A and the upper welding flange 2 through deformation of the red copper gasket 32.
In operation, the exhaust pipe 43 controls the exhaust process through a high-pressure normally closed solenoid valve. The air inlet pipe 42 is connected with a high-pressure air bottle with a pressure reducing valve, and the pressure of the high-pressure air bottle is adjusted by the pressure reducing valve according to the pressure in the test equipment displayed by the digital display pressure gauge 47, so that the pressure required by the test is achieved. The gas type in the test environment can be realized by replacing the gas source in the high-pressure gas cylinder. The vacuum pumping pipe 46 is connected with a vacuum pump to pump out impurity gases in the test equipment.
The propellant is conveyed to a test position by screwing a propellant placing screw rod 36 into a threaded sleeve 1 in a high-pressure combustion chamber component A required by claim 1, the solid propellant is ignited by adopting laser ignition, a high-speed camera and a spectrum analyzer are used for synchronously measuring the ignition of metal particles, the agglomeration combustion flame structure and the flame temperature distribution through an observation window 39, and the two-dimensional flame temperature distribution obtained by the infrared thermal imager through window shooting is checked and corrected to further obtain the accurately measured flame temperature distribution of the solid propellant.
The thermocouple measures the temperature distribution of the flame in the axial direction during the combustion of the propellant.
When the combustion reaction needs to be stopped, the traction magnet 38 is controlled to drive the fork-shaped limiting fixing piece 15 to be drawn out of the stopping groove of the stopping sliding sleeve 14, so that the clamping fixation of the stopping sliding sleeve 14 is cancelled, the window breaking firing pin 13 is driven to rapidly move towards the direction of the observation window 39 under the action of the elastic energy accumulator 16, the observation window 39 is impacted and broken, gas in the high-pressure combustion chamber component A is discharged, the high-pressure environment condition of a reaction space is damaged, the solid propellant can only be combusted under the high-pressure condition, and the combustion reaction is stopped in time, so that the combustion intermediate state of the propellant can be observed.
In light of the foregoing description of the preferred embodiment of the present invention, many modifications and variations will be apparent to those skilled in the art without departing from the spirit and scope of the invention. The technical scope of the present invention is not limited to the content of the specification, and must be determined according to the scope of the claims.
Claims (8)
1. A solid propellant high pressure ignition and combustion suspension test device is characterized in that: the high-pressure combustion chamber component A comprises a cylinder body (4), solid fuel is arranged in the cylinder body (4), the side wall of the cylinder body (4) is close to the lower position and penetrates through and is provided with a plurality of pressure-resistant power supply components B, the circumference of the side wall of the cylinder body (4) is uniformly provided with a plurality of observation windows (39), the outer side of one of the observation windows (39) is fixedly provided with a window breaking component C, the top of the cylinder body (4) is provided with an upper welding flange (2), the bottom of the cylinder body is provided with a lower bottom plate (3), the central position of the upper welding flange (2) is provided with a pressure-bearing incident light path component D,
when the test is started, the laser ignites the solid fuel through the pressure-bearing incident light path component D;
when the combustion reaction needs to be terminated, the window breaking component C breaks an observation window (39) on the side face of the high-pressure combustion chamber component A, high-pressure gas in the high-pressure combustion chamber component A is released, and a high-pressure environment required by the combustion of the solid fuel is destroyed;
the center of the lower bottom plate (3) is provided with a threaded sleeve (1), a propellant placing screw (36) is arranged in the threaded sleeve (1), pressure-bearing laser glass (24) is embedded in each observation window (39), a glass sealing welding seat (5) is arranged on the periphery of each observation window (39), a plurality of threaded holes (6) which are uniformly distributed in the circumferential direction are formed in the lower position of the cylinder body (4), and the pressure-resisting power supply assembly B is arranged in the threaded holes (6) in a threaded connection mode;
the window breaking assembly C comprises a sliding sleeve (17), one end of the sliding sleeve (17) is fixedly provided with an installation seat (18), a stopping sliding sleeve (14) and a window breaking firing pin (13) are arranged in the sliding sleeve (17), one end of the window breaking firing pin (13) faces the installation seat (18), the other end of the window breaking firing pin is fixed on the stopping sliding sleeve (14), a window breaking hole is formed in the position, opposite to the window breaking firing pin (13), of the installation seat (18), an energy storage spring (16) is arranged on one side, far away from the installation seat (18), of the stopping sliding sleeve (14), and a stopping device is arranged on one side of the sliding sleeve (17).
2. The solid propellant high pressure ignition and burnout test apparatus of claim 1, wherein: the barrel (4) is also provided with an air inlet pipe (44), an exhaust pipe (45), a vacuum-pumping pipe (46) and a digital display pressure gauge (47) which are connected through a threaded hole (6).
3. The solid propellant high pressure ignition and combustion suspension test device of claim 1, wherein: the high-pressure combustor assembly A is characterized in that a plurality of thermocouple installation seats (37) are arranged on a lower bottom plate (3) of the high-pressure combustor assembly A, the thermocouple installation seats (37) are connected to a low-resistance conductive threaded rod (7) through wires, and each thermocouple installation seat (37) is provided with a thermocouple.
4. The solid propellant high pressure ignition and combustion suspension test device of claim 1, wherein: withstand voltage power supply unit B includes the bolt body (11) and sets up two low resistance conductive threaded rod (7) inside the bolt body (11), be provided with insulating cover between the bolt body (11) and low resistance conductive threaded rod (7), bolt body (11) and insulating cover are fixed through lock nut (10), insulating cover includes from lower insulating cover (8), well insulating cover (9) and last insulating cover (12) that upwards set gradually down, it surpasss bolt body (11) aperture to go up insulating cover (12) edge, low resistance conductive threaded rod (7) upper end surpasss bolt body (11), and the lower extreme is in bolt body (11).
5. The solid propellant high pressure ignition and burnout test apparatus of claim 1, wherein: an inner thread groove is formed in the center of the stop sliding sleeve (14), an outer thread is arranged at one end, far away from the mounting seat (18), of the broken window firing pin (13), and the stop sliding sleeve (14) and the broken window firing pin (13) are spirally fixed through the inner thread and the outer thread.
6. The solid propellant high pressure ignition and burnout test apparatus of any one of claims 1 or 5, wherein: the window breaking assembly C is fixed on a glass sealing welding seat (5) of the high-pressure combustion chamber assembly A through a mounting seat (18), a stop hole (41) is formed in one side of the sliding sleeve (17), a stop groove (40) is formed in the side, which is the same as the stop hole (41), of the stop sliding sleeve (14), a stop device is fixedly arranged on the sliding sleeve (17) through the stop hole (41),
the stopping device comprises an L-shaped limiting fixing piece (20) and a traction magnet mounting seat (21), one side of the L-shaped limiting fixing piece (20) is fixed on the traction magnet mounting seat (21), the other side of the L-shaped limiting fixing piece (20) is provided with a through hole (42), the traction magnet mounting seat (21) is radially provided with a traction magnet (38) along a sliding sleeve (17), one end of the traction magnet (38) facing a stopping hole (41) is fixed with a fork-shaped limiting rod (15),
when the energy storage spring (16) is in the maximum contraction state, the stop groove (40) is opposite to the stop hole (41), and when the window breaking assembly C is in the stop state, the fork-shaped limiting rod (15) is embedded in the stop groove (40) through the through hole (42).
7. The solid propellant high pressure ignition and combustion suspension test device of claim 1, wherein: the pressure-bearing incident light path component D comprises a pressure-bearing water-cooling cover (25), a one-level step-shaped through hole is formed in the pressure-bearing water-cooling cover (25), pressure-bearing laser glass (24) is embedded in the one-level step-shaped through hole, a cooling water inlet pipe (29) and a cooling water outlet pipe (26) are respectively arranged on two sides of the aperture direction of the one-level step-shaped through hole, a cooling annular cavity (43) is arranged in the pressure-bearing incident light path component D, the cooling annular cavity (43) is communicated with the cooling water inlet pipe (29) and the cooling water outlet pipe (26), and sealing buffer gaskets (28) are arranged on the upper end face and the lower end face of the pressure-bearing laser glass (24).
8. The solid propellant high pressure ignition and combustion suspension test device of claim 1, wherein: go up welded flange (2) and broken window subassembly C and all be connected fixedly through hexagon bolt and high pressure combustion chamber subassembly A, a plurality of unthreaded holes (27) have been seted up to pressure-bearing incident light path subassembly D, pressure-bearing incident light path subassembly D passes unthreaded hole (27) through hexagon bolt and is connected fixedly with high pressure combustion chamber subassembly A, go up and be provided with red copper gasket (32) between welded flange (2) and the hexagon bolt.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210140376.7A CN114184642B (en) | 2022-02-16 | 2022-02-16 | Solid propellant high-pressure ignition and combustion suspension test device |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210140376.7A CN114184642B (en) | 2022-02-16 | 2022-02-16 | Solid propellant high-pressure ignition and combustion suspension test device |
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| CN114184642A CN114184642A (en) | 2022-03-15 |
| CN114184642B true CN114184642B (en) | 2022-07-26 |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101979999B (en) * | 2010-11-04 | 2011-12-28 | 西安近代化学研究所 | Solid propellant depressurizing and extinguishing device |
| CN107064410B (en) * | 2017-04-01 | 2019-04-09 | 华侨大学 | Static premix gas combustion limits extend test device under dielectric impedance plasma discharge |
| CN108548754B (en) * | 2018-05-09 | 2020-07-14 | 西北工业大学 | Device and method for quickly extinguishing solid propellant under high pressure condition |
| CN108593837B (en) * | 2018-06-08 | 2024-02-09 | 中国科学技术大学 | Solid propellant high-pressure combustion characteristic parameter measuring equipment with observation window |
| CN109596770B (en) * | 2018-11-27 | 2021-07-23 | 西安近代化学研究所 | Propellant powder explosion fragment pressure relief combustion stopping device |
| CN112147268B (en) * | 2020-09-03 | 2022-08-19 | 西安近代化学研究所 | Device and method for nondestructively preparing flameout surface of solid propellant |
| CN112666309A (en) * | 2021-02-04 | 2021-04-16 | 中国人民解放军国防科技大学 | High-pressure combustor experimental system and visual high-pressure combustor |
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