A powder engine combustion chamber test device based on staged gas supply and laser-assisted combustion

Abstract

The present invention provides a powder engine combustion chamber test device based on staged gas supply and laser-assisted combustion, which includes an injection assembly, a length-adjustable combustion chamber, a fastening assembly, and a nozzle assembly; the length-adjustable combustion chamber is formed by connecting three cylindrical combustion chambers in a plug-in manner. The top cover of the injection assembly is embedded with an injection disk, and a plurality of primary air intake holes are radially arranged on the side wall of the top cover and are connected to the oxidizing gas delivery system. A cavity is formed between the inner wall of the top cover and the outer wall of the injection disk, which is communicated with a plurality of through holes arranged at the large end of the injection disk and the combustion chamber cavity; a central through hole is opened on the injection disk, and the two ends are respectively connected to the sulfur powder delivery system and the first combustion chamber cavity. A laser plasma igniter interface is opened on the side wall of the first combustion chamber, and a plurality of secondary air intake holes are evenly distributed on the side wall of the second combustion chamber. Both ends of the combustion chamber are fixedly connected to the injection assembly and the nozzle assembly respectively. The present invention adopts a modular design to achieve an adjustable length-to-diameter ratio of the combustion chamber, improve the test flexibility, and shorten the test cycle.

Description

Technical Field

[0001] The present invention belongs to the technical field of staged combustion of powder rocket engine combustion chambers, and particularly relates to a test device for a powder engine combustion chamber based on staged gas supply and laser-assisted combustion. Background Art

[0002] The powder rocket engine is a new type of rocket engine. Its propellant uses metal powder particles and oxidizing gases that are easy to collect, store, and transport, and has the advantages of fast response, good safety, strong anti-overload and environmental adaptability, and can achieve precise thrust adjustment and multi-pulse operation. In order to improve the combustion efficiency and combustion stability of the powder rocket engine, the staged combustion technology (the most common one is to add a secondary air intake structure on the basis of the traditional single air intake structure engine) and the laser plasma ignition and combustion assistance technology are generally adopted in the powder rocket engine combustion chamber. Staged gas supply can effectively extend the residence time of powder particles in the combustion chamber and enhance the turbulence intensity in the combustion chamber, thereby improving the combustion efficiency of the powder rocket engine; laser plasma ignition and combustion assistance can achieve precise adjustment of ignition energy and timing, and improve combustion efficiency and stability; it is found that factors such as the staged gas supply injection method, injection speed, length-diameter ratio of the pre-combustion section and afterburning section, and parameters of the laser plasma will affect the combustion characteristics of the powder engine.

[0003] Since the current research on the combustion mechanism of powder rocket engines is not yet mature, the research method is mainly based on full-scale engine test runs. The experimental cost is high and the cycle is long, which is not conducive to in-depth research on the combustion mechanism of powder engines to improve the combustion efficiency and stability of powder engines.

[0004] In addition, most of the existing powder rocket engine test devices are traditional integrated configurations with length limitations, and the control of experimental variables is limited. Especially, the adjustment of the length-diameter ratio and the staged gas supply position is restricted. It needs to be customized and purchased according to experimental requirements, and cannot be reused. The application range is small and the flexibility is poor, resulting in high experimental costs and long test cycles. Summary of the Invention

[0005] Technical problems to be solved: To solve the problem of low practicality of existing powder rocket engine test devices, the present invention provides a test device for a powder engine combustion chamber based on staged gas supply and laser-assisted combustion, which can repeatedly study the combustion characteristics of the propellant in the powder rocket engine combustion chamber, improve the combustion efficiency and combustion stability of the propellant, reduce the test cost, shorten the test cycle, and improve the flexibility of the test.

[0006] The technical solution of the present invention is: a powder engine combustion chamber test device based on staged gas supply and laser-assisted combustion, including a jet injection assembly, a length-adjustable combustion chamber, a fastening assembly, and a nozzle assembly; the length-adjustable combustion chamber is of a sleeve structure, including a first combustion chamber 3, a second combustion chamber 4, and a third combustion chamber 5, and the three combustion chambers are sequentially matched by means of plug connection; radial holes are provided on the side wall of the first combustion chamber 3 and are connected to a laser plasma igniter, and a plurality of secondary air intake holes 11 are evenly distributed on the side wall of the second combustion chamber 4 and near one end;

[0007] The jet injection assembly includes a top cover 1, a jet injection disk 2, and a secondary air intake device. The jet injection disk 2 is coaxially installed in the top cover. The top cover 1 is fixedly connected to the first combustion chamber 3. A plurality of primary air intake holes 10 are radially provided on the side wall of the top cover and are connected to an oxidation gas delivery system. A cavity is formed between the inner wall of the top cover and the outer wall of the middle part of the jet injection disk 2. A plurality of through holes are arranged on the large end of the jet injection disk and are communicated with the cavity, the primary air intake holes 10, and the chamber of the first combustion chamber 3 to form an oxidation gas inlet channel; a central through hole is axially provided on the jet injection disk 2. One end of the central through hole is connected to a sulfur powder delivery system, and the other end is communicated with the chamber of the first combustion chamber 3; a plurality of secondary air intake devices 16 are installed at the positions of the secondary air intake holes 11, and the air intake channels on the secondary air intake devices are communicated with the secondary air intake holes 11;

[0008] The nozzle assembly includes a nozzle 6 and a throat liner 7; one end of the nozzle 6 is fixedly connected to the third combustion chamber 5, and the other end is fixed on a test platform; the throat liner 7 is installed at the throat of the nozzle 6 to prevent the throat of the nozzle from being eroded by high-temperature combustion gas;

[0009] Both ends of the second combustion chamber 4 are respectively connected to the top cover 1 and the nozzle 6 through a fastening assembly.

[0010] Further, the secondary air intake holes 11 are conical holes, one end of the secondary air intake device 16 is a conical structure matching the secondary air intake holes 11, and the other end is a plate-like structure for fixing the secondary air intake device on the side wall of the second combustion chamber 4. A columnar convex block is provided on the plate-like structure, and an air intake channel is provided along the center line of the convex block.

[0011] Further, the jet injection disk 2 is a three-stage rotary body structure. A convex block is provided on the outer wall of the small-diameter section and is embedded in a card slot provided on the inner wall of the small-diameter hole of the top cover 1. The extended part of the small-diameter section of the jet injection disk is fixedly connected to the test platform; one end of the central through hole of the jet injection disk 2 that is communicated with the chamber of the first combustion chamber 3 is conical, so that the sulfur powder is sprayed into the first combustion chamber in a conical diffusion manner.

[0012] Further, the fastening assembly is a long bolt and nut assembly. The flange plates at both ends of the second combustion chamber 4 are respectively connected to the flange plates of the top cover 1 and the third combustion chamber 5 through a plurality of bolt and nut assemblies.

[0013] Furthermore, it also includes a snap ring 8 which is installed on the outer walls of the first combustion chamber 3 and the third combustion chamber 5 and contacts with both ends of the second combustion chamber respectively, for fastening the second combustion chamber 4 to prevent axial displacement of the second combustion chamber during the test; the snap ring 8 is composed of two stepped semi-rings hinged together, with lugs provided at both ends of the two semi-rings and having through holes, and the snap ring is fixed to the first combustion chamber or the third combustion chamber by bolts; an annular groove is provided on the inner stepped surface of the snap ring for installing an O-ring for gas sealing.

[0014] Furthermore, the inner walls of the length-adjustable combustion chamber and the nozzle are attached with a heat insulation layer to prevent the high-temperature gas from causing the loss of strength of the combustion chamber or nozzle shell due to excessive temperature.

[0015] Advantages of the Invention

[0016] In the present invention, the combustion chamber of the powder rocket engine is designed modularly, realizing the reuse of each component, improving the test flexibility and shortening the test cycle; when the test device is damaged, only the damaged components need to be replaced, reducing the test cost.

[0017] Compared with the prior art, the specific advantages of the present invention are as follows:

[0018] (1) In the present invention, the combustion chamber adopts a three-stage structure, and the three combustion chambers are matched by a sleeving method. By adjusting the matching length between the three combustion chambers, the length-diameter ratio of the pre-combustion section and the afterburning section of the combustion chamber can be adjusted, and the operation is simple.

[0019] (2) In the present invention, a secondary air intake device is installed on the outer wall of the second combustion chamber and near one end, and the installation position of the secondary air intake is adjusted by reversing the installation direction of the second combustion chamber, increasing the range of the length-diameter ratio of the pre-combustion section and the afterburning section of the combustion chamber, and the secondary air intake angle and flow rate can be adjusted by replacing different secondary air intake devices, improving the test flexibility.

[0020] (3) In the present invention, a heat insulation layer or a heat-resistant and ablative component is sleeved inside the combustion chamber, the front part of the nozzle and the throat liner, for isolating the high-temperature gas to reduce the heat transfer effect on the external shell. During multiple experiments, only the heat insulation layer or the heat-resistant and ablative component needs to be replaced, realizing the reuse of the combustion chamber shell and the nozzle shell.

[0021] (4) In the present invention, each component is connected and fixed by a bolt assembly and sealed with an O-ring, with simple operation and fast disassembly and assembly.

[0022] (5) In the present invention, a laser-induced plasma igniter interface is provided on the outer wall of the first combustion chamber, which can not only realize the ignition function but also the combustion assistance function, effectively improving the combustion efficiency and stability of the engine propellant. Description of the Drawings

[0023] Figure 1It is the overall assembly drawing of the present invention;

[0024] Figure 2 is Figure 1 the left view structure drawing of

[0025] Figure 3 is Figure 2 the sectional view taken along the line A - A of

[0026] Figure 4 is Figure 1 the three - view drawing of the injection disk structure in

[0027] Figure 5 is Figure 3 the partial enlarged view at position B of

[0028] Figure 6 is Figure 1 the half - sectional view of the secondary air intake device in

[0029] In the figure: 1 - top cover, 2 - injection disk, 3 - first combustion chamber, 4 - second combustion chamber, 5 - third combustion chamber, 6 - nozzle, 7 - throat liner, 8 - snap ring, 9 - sulfurized powder injection hole, 10 - primary air intake hole, 11 - secondary air intake hole, 12 - laser plasma igniter interface, 13 - O - ring seal, 14 - thermal insulation layer, 15 - nozzle thermal insulation layer, 16 - secondary air intake device. Specific embodiments

[0030] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by terms such as "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present invention.

[0031] In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Therefore, the features defined with "first" and "second" may explicitly or implicitly include one or more of such features. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.

[0032] Refer to Figures 1-6; This embodiment proposes a powder engine combustion chamber test device based on staged gas supply and laser-assisted combustion. In order to achieve the flexibility of powder rocket engine tests and improve test efficiency, the engine test device includes an injection assembly, an adjustable combustion chamber, a nozzle assembly, and a fastening assembly. The two ends of the adjustable combustion chamber are respectively connected to the injection assembly and the nozzle assembly through the fastening assembly, and the internal cavities are connected;

[0033] The adjustable combustion chamber includes a first combustion chamber, a second combustion chamber, and a third combustion chamber. The three combustion chambers are sequentially inserted and matched. The side wall of the first combustion chamber is provided with radial holes, which are connected to the laser plasma igniter. Multiple secondary air intake holes 11 are radially opened at one end of the side wall of the second combustion chamber;

[0034] The injection assembly includes a top cover 1, an injection disk 2, and a secondary air intake device. The injection disk 2 is coaxially installed in the top cover. Multiple primary air intake holes 10 are radially arranged on the side wall of the top cover and are connected to the external oxidizing gas delivery system. A gap is formed between the inner wall of the top cover and the outer wall of the middle part of the injection disk 2. Multiple through holes are axially opened on the large end of the injection disk. Both ends of the through holes are connected to the gap and the cavity of the first combustion chamber to form an oxidizing gas inlet channel; A central through hole is axially opened on the end face of the injection disk 2. One end of the central through hole is connected to the sulfur powder delivery system, and the other end is connected to the cavity of the first combustion chamber 3; The secondary air intake device is installed at the position of the secondary air intake holes. During the test, by adjusting the matching length between the three combustion chambers, or by reversing the installation direction of the second combustion chamber to adjust the position of the secondary air intake device, the aspect ratio of the pre-combustion section and the combustion assistance section of the combustion chamber can be adjusted, improving the flexibility of powder rocket engine tests.

[0035] Taking the Mg / CO2 rocket engine test with the aspect ratio of the pre-combustion section as the control variable as an example in this embodiment, where Mg is metal powder particles and CO2 is the oxidizing gas. The combustion reaction of magnesium powder and carbon dioxide produces a two-phase combustion product with components of magnesium oxide, condensed carbon, and CO, and releases a large amount of heat. According to the experimental design pressure and cost, the top cover 1, the injection disk 2, the combustion chamber shell, the snap ring 8, and the nozzle 6 shell are all machined from 345 steel material.

[0036] Refer to Figure 1; The combustion chamber test device includes a top cover 1, an injection plate 2, a first combustion chamber 3, a second combustion chamber 4, a third combustion chamber 5, a nozzle 6, a throat liner 7, a snap ring 8, a long bolt assembly, and a secondary air intake device 16. The first combustion chamber 3, the second combustion chamber 4, and the third combustion chamber 5 are of a sleeve structure, and the three combustion chambers are sleeved and matched in sequence to achieve adjustable combustion chamber length; the injection plate 2 is coaxially installed in the top cover, the top cover 1 is fixedly connected to the first combustion chamber 3, and the end face of the injection plate is hermetically matched with the end of the first combustion chamber; the nozzle 6 is fixedly connected to the third combustion chamber 5; both ends of the second combustion chamber 4 are detachably connected to the top cover and the third combustion chamber 5 through the long bolt assembly; the throat liner 7 is installed at the throat of the nozzle to prevent damage to the nozzle caused by high-temperature combustion gas; heat insulation layers are also attached to the inner walls of the combustion chamber and the nozzle to prevent the high-temperature combustion gas from transferring heat to the combustion chamber or the nozzle housing and causing the housing to lose strength; snap rings 8 are also installed on the outer walls of the first combustion chamber 3 and the third combustion chamber 5 at the end of the second combustion chamber to fix both ends of the second combustion chamber and prevent axial movement.

[0037] Refer to Figure 2 and Figure 3 ; The top cover 1 is in the shape of a rotating body, with a flange on the end face. A plurality of mounting holes are circumferentially opened on the flange for fixedly connecting the top cover and the flange of the first combustion chamber through the long bolt assembly; a multi-step hole is axially opened in the middle of the top cover. The small-diameter hole section is matched with the outer wall of the small-diameter section of the injection plate 2, and a clamping groove for matching with the protrusion on the outer wall of the small-diameter section of the injection plate 2 is opened on the inner wall; a plurality of columnar protrusions are circumferentially arranged on the outer wall of the top cover. In this embodiment, 4 are evenly arranged. Through holes are axially opened on the columnar protrusions as primary air intake holes 10, which are connected to the carbon dioxide delivery system. A chamber is formed between the inner wall of the top cover and the outer wall of the injection plate 2, and the primary air intake holes 10 communicate with the chamber. An annular groove is also arranged on the stepped surface of the inner cavity of the top cover for installing an O-ring 13.

[0038] Refer to Figure 4 ; The injection plate 2 is integrally of a three-step shape, with protrusions on the outer wall of the small-diameter section, which are embedded in the clamping grooves in the small-diameter holes of the top cover 1. The small protruding part of the injection plate is fixedly connected to the test platform through a sleeved manner. A through hole is axially opened in the middle of the injection plate 2 as a sulfur powder injection hole 9. One end of the sulfur powder injection hole 9 is connected to the magnesium sulfide powder delivery system, and the other end communicates with the inner cavity of the first combustion chamber 3. A chamber is formed between the outer wall of the middle part of the injection plate and the inner wall of the large section of the top cover 1. A plurality of through holes are axially arranged on the large end of the injection plate, which communicate with the first combustion chamber. A plurality of primary air intake holes 10 opened on the side wall of the top cover communicate with the chamber and the through holes to form a carbon dioxide entry channel. Annular grooves are opened on the stepped surface in the middle of the injection plate and on both end faces of the large end for installing O-rings.

[0039] Refer to Figure 3; The first combustion chamber 3, the second combustion chamber 4, and the third combustion chamber 5 are of a sleeve structure. The two ends of the second combustion chamber are respectively in close fit with the first combustion chamber 3 and the fifth combustion chamber 5 in a plug-in manner. According to the design requirements of the test length-diameter ratio, the fitting length between the three combustion chambers can be adjusted. The inner walls of the three combustion chambers are attached with an adiabatic layer 14, preferably a high-silica adiabatic layer, to isolate the heat transfer of high-temperature gas to the combustion chamber shell and ensure that the shell does not lose strength due to excessive temperature. Flange plates are provided at both ends of the second combustion chamber, and flange plates are provided at one end of the first combustion chamber and the third combustion chamber. The flange plates at both ends of the second combustion chamber 4 are respectively fixedly connected to the flange plates on the top cover 1 and the nozzle 6 through a plurality of long bolt-nut assemblies. An annular groove is provided on the combustion chamber end face for installing an O-ring 13 to ensure that the combustion chamber is in a sealed state. A columnar boss is provided on the outer wall of the first combustion chamber 3, and a through hole is opened along the axis of the columnar boss as the laser plasma igniter interface 12 for accessing the laser plasma igniter.

[0040] Refer to Figure 3 、 Figure 5 and Figure 6 ; A plurality of through holes are circumferentially distributed on the outer wall of the second combustion chamber 4 and near one end, which are secondary air inlet holes 11. A secondary air inlet device 16 is installed on the secondary air inlet holes 11. In this embodiment, the secondary air inlet holes 11 are tapered holes, and the secondary air inlet device is provided with a tapered structure matching the secondary air inlet holes. The air inlet hole on the secondary air inlet device is communicated with the secondary air inlet holes 11 and is connected to the carbon dioxide supply system. Before the secondary air inlet is the pre-combustion section of the combustion chamber, and after the secondary air inlet is the combustion-supporting section of the combustion chamber. Since the secondary air inlet holes are close to one end of the second combustion chamber, during the test, by reversing the installation of the second combustion chamber 4, the position of the secondary air inlet can be adjusted, so that the length-diameter ratios of the pre-combustion section and the combustion-supporting section of the combustion chamber can be adjusted. In addition, the setting angle or aperture of the air inlet hole on the secondary air inlet device 16 can be adjusted according to the test requirements By replacing the secondary air inlet device, the secondary air inlet angle and flow rate can be adjusted to improve the combustion efficiency and enhance the test flexibility.

[0041] A snap ring 8 is also sleeved on the outer walls of the first combustion chamber 3 and the third combustion chamber 5 and near the end face of the second combustion chamber for fastening the second combustion chamber 4 to prevent the axial movement of the second combustion chamber during the test. The snap ring 8 is composed of two stepped half-rings hinged together. The two ends of the half-ring are provided with ear pieces with through holes. The outer wall of the combustion chamber is fastened by bolts. An annular groove is provided on the inner stepped surface of the snap ring, and an O-ring 13 is placed in the groove for air sealing.

[0042] Both ends of the nozzle 6 are funnel-shaped. An earpiece is provided at one end of the nozzle and is fixedly connected to the flange of the third combustion chamber 5 by bolts. A throat liner 7 is embedded in the inner wall of the middle part of the nozzle. The throat liner 7 is made of carbon composite material or refractory metal. The other end of the nozzle is fixed to the test platform by a socket connection to ensure that no strong vibration occurs during the engine test run. The inner wall of the nozzle 6 is attached with a nozzle insulation layer 15, which is used to isolate the high-temperature gas to reduce the heat transfer to the nozzle shell. After multiple experiments, only the insulation layer or the throat liner needs to be replaced, realizing the reuse of the nozzle and saving costs.

[0043] The working process of this embodiment is as follows: The swirling carbon dioxide gas enters the chamber formed between the inner wall of the top cover 1 and the outer wall of the injection disk 2 through the primary air inlet holes 10 on the top cover 1, and then enters the combustion chamber through 8 through holes axially opened at the large end of the injection disk. The magnesium sulfide powder is sprayed into the pre-combustion section of the first combustion chamber in a conical diffusion manner through the magnesium sulfide powder injection holes 9 on the injection disk 2, and is fully mixed with the carbon dioxide gas. Under the high-temperature radiation and combustion support of the laser plasma igniter, a violent combustion reaction occurs, generating high-temperature and high-pressure two-phase gas. Then it enters the afterburning section after the secondary air intake, and the gas further reacts fully. Finally, it expands and does work through the nozzle 6 and is discharged, generating a reverse thrust.

[0044] Although the embodiments of the present invention have been shown and described above, it can be understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those of ordinary skill in the art can make changes, modifications, substitutions, and variations to the above embodiments within the scope of the present invention without departing from the principles and purposes of the present invention.

Claims

1. A powder engine combustion chamber test device based on staged gas supply and laser assisted combustion, characterized in that, It includes a jet component, a length-adjustable combustion chamber, a fastening component and a nozzle component; The length-adjustable combustion chamber is of a sleeve structure, including a first combustion chamber (3), a second combustion chamber (4) and a third combustion chamber (5). The three sections of the combustion chamber are sealed and fitted in a plug-in manner in sequence. Radial holes are provided on the side wall of the first combustion chamber (3) and are connected to a laser plasma igniter. A plurality of secondary air intake holes (11) are evenly distributed on the side wall of the second combustion chamber (4) and near one end; The jet component includes a top cover (1), a jet plate (2) and a secondary air intake device (16). The jet plate (2) is coaxially installed in the top cover. The top cover (1) is fixedly connected to the first combustion chamber (3). A plurality of primary air intake holes (10) are radially provided on the side wall of the top cover and are connected to an oxidation gas delivery system. A cavity is formed between the inner wall of the top cover and the outer wall of the middle part of the jet plate (2). A plurality of through holes are arranged on the large end of the jet plate and are communicated with the cavity, the primary air intake holes (10) and the chamber of the first combustion chamber (3) to form an oxidation gas inlet channel. A central through hole is axially provided on the jet plate (2). One end of the central through hole is connected to a sulfur powder delivery system, and the other end is communicated with the chamber of the first combustion chamber (3). A plurality of secondary air intake devices (16) are installed at the positions of the secondary air intake holes (11), and the air intake channels on the secondary air intake devices are communicated with the secondary air intake holes (11); The nozzle component includes a nozzle (6) and a throat liner (7); one end of the nozzle (6) is fixedly connected to the third combustion chamber (5), and the other end is fixed on a test platform; the throat liner (7) is installed at the throat of the nozzle (6) to prevent the throat of the nozzle from being ablated by high-temperature combustion gas; Both ends of the second combustion chamber (4) are respectively connected to the top cover (1) and the nozzle (6) through a fastening component; The secondary air intake hole (11) is a tapered hole. One end of the secondary air intake device (16) is a tapered structure matching the secondary air intake hole (11), and the other end is a plate-like structure for fixing the secondary air intake device on the side wall of the second combustion chamber (4). Columnar bumps are provided on the plate-like structure, and an air intake channel is opened along the center line of the bumps.

2. The powder engine combustion chamber test device based on staged air supply and laser-assisted combustion according to claim 1, characterized in that, The jet plate (2) is a three-stage rotary body structure. A bump is provided on the outer wall of the small-diameter section and is embedded in a card slot opened on the inner wall of the small-diameter hole of the top cover (1). The protruding part of the small-diameter section of the jet plate is fixedly connected to the test platform; one end of the central through hole of the jet plate (2) that is communicated with the chamber of the first combustion chamber (3) is tapered, so that the sulfur powder is sprayed into the first combustion chamber in a tapered diffusion manner.

3. The combustion chamber test device of a powder engine based on staged gas supply and laser assisted combustion according to claim 1, characterized in that The fastening component is a long bolt and nut component. The flange plates at both ends of the second combustion chamber (4) are respectively connected to the flange plates of the top cover (1) and the third combustion chamber (5) through a plurality of bolt and nut components.

4. A powder engine combustion chamber test device based on staged gas supply and laser-assisted combustion as claimed in claim 1, characterized in that, It further includes snap rings (8), which are installed on the outer walls of the first combustion chamber (3) and the third combustion chamber (5) and are respectively in contact with both ends of the second combustion chamber (4), and are used to fasten the second combustion chamber to prevent axial movement of the second combustion chamber during the test; the snap rings (8) are formed by hinging two stepped half-rings, and lugs with through holes are provided at both ends of the two half-rings, and the snap rings are fixed to the first combustion chamber or the third combustion chamber through bolts; an annular groove is provided on the inner stepped surface of the snap ring for installing an O-ring for gas sealing.

5. The combustion chamber test device of a powder engine based on staged gas supply and laser-assisted combustion according to claim 1, characterized in that, The inner walls of the length-adjustable combustion chamber and the nozzle (6) are attached with heat insulation layers to prevent the high-temperature gas from causing the loss of strength of the combustion chamber or the nozzle housing due to excessive temperature.

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