A test apparatus and system for dynamic deposition of condensed phase combustion products in rocket engines

Abstract

This invention provides a dynamic deposition test device and system for condensed phase combustion products of rocket engines. The device includes a main shell, with a propellant burner connection flange and a temperature measuring component mounting flange fixedly installed at its top and bottom, respectively. The space within the main shell and the temperature measuring component mounting flange serves as a deposition channel. An insulating sleeve, a calorimeter, and a thermocouple are installed within the temperature measuring component mounting flange. The temperature measuring component mounting flange is fixedly connected to a temperature measuring instrument connection flange, which contains a temperature measuring wire fixing plug, a temperature measuring wire connector, and a temperature measuring wire. A left observation window and a right observation window are provided on the main shell, with an observation plate and a heat protection plate respectively installed at each window. This dynamic deposition test device for condensed phase combustion products of rocket engines can observe the deposition evolution process of solid propellant combustion products under various propellant loading conditions, and simultaneously achieves real-time measurement of deposition heat flux and heat increment.

Description

Technical Field

[0001] This invention belongs to the field of solid rocket engine technology, and relates to the deposition characteristics of condensed phase combustion products of rocket engines, specifically to a dynamic deposition test device and system for condensed phase combustion products of rocket engines. Background Technology

[0002] Composite propellants containing metallic fuels have high energy and can effectively suppress high / medium frequency oscillating combustion, thus they are widely used as the main power source for solid rocket engines. However, composite propellants containing metallic fuels generate a large number of condensed metallic compound particles during combustion, creating a high-temperature, high-pressure two-phase flow environment in the combustion chamber and nozzle. During high-speed flight, the engine body experiences high overloads, and the high-temperature two-phase flow accumulates towards the engine insulation layer, causing severe ablation of the engine walls and insulation layer, thereby affecting the overall performance and service life of the engine.

[0003] Furthermore, modern large solid rocket motor nozzles typically employ a submerged design, with a significant portion extending into the combustion chamber or casing. This effectively shortens the engine length, reducing the aircraft's weight and meeting overall engine design requirements. On the other hand, most movable nozzles providing thrust vector control for the aircraft are also submerged. The submersion of the nozzle makes the flow at the combustion chamber tail extremely complex, with significant changes in flow patterns as the combustion surface shifts and mass is added. During combustion of composite propellants containing metallic fuels, larger solid particles cannot enter the nozzle and instead deposit in the cavity of the submerged nozzle's back wall, forming a so-called slag deposit layer. Because the slag cannot be discharged, propellant energy is lost, and the engine's negative weight increases. Slag deposition also intensifies heat transfer on the engine's inner walls. Moreover, slag deposits can reduce the strength of the engine walls, potentially leading to engine casing burn-through and engine failure.

[0004] To avoid the adverse effects of slag deposition on the engine, experiments need to be designed to study the deposition characteristics of propellant condensate combustion products. Chinese Patent CN105448177B discloses a dual-nozzle simulation device for studying the ablation phenomenon of the insulation layer inside a rocket engine. This device can simulate the ablation phenomenon of the insulation layer in a large solid rocket engine under conditions of particulate phase deposition in the concave cavity of the nozzle back wall. Later, using thickness gauges and electron microscopes, the ablation rate of the insulation layer mass and the microstructure of the carbonized layer can be obtained.

[0005] However, in practical applications, the aforementioned existing technologies lack a visual structure, making it difficult to conduct real-time tests on the deposition and evolution of condensed products generated by propellant combustion under high temperature and high pressure conditions. At the same time, it is difficult to dynamically and in real-time measure the heat transfer data of deposited products under different evolution states. Summary of the Invention

[0006] To address the shortcomings of existing technologies, the present invention aims to provide a dynamic deposition test device and system for condensed phase combustion products in rocket engines, thereby solving the technical problems of difficulty in real-time observation of the deposition phenomenon of solid propellant combustion products and real-time acquisition of heat transfer data in existing technologies.

[0007] To solve the above-mentioned technical problems, the present invention adopts the following technical solution:

[0008] A dynamic deposition test device for condensed phase combustion products of a rocket engine includes a main shell, an integrally formed propellant burner connection flange at the top of the main shell, and a temperature measuring component mounting flange fixedly connected to the bottom of the main shell. The space inside the main shell and the temperature measuring component mounting flange is a deposition channel.

[0009] The top of the temperature measuring component mounting flange extends into the main housing. An insulating sleeve is fixedly installed inside the top of the temperature measuring component mounting flange, and a calorimeter is installed inside the insulating sleeve. Both the insulating sleeve and the calorimeter are located at the bottom of the deposition channel. The calorimeter has multiple thermocouple mounting holes, and thermocouples are installed in the thermocouple mounting holes. The bottom of the temperature measuring component mounting flange is fixedly connected to the temperature measuring instrument connecting flange. A temperature measuring wire fixing plug and a temperature measuring wire connector are fixedly installed in the temperature measuring instrument connecting flange from top to bottom. A temperature measuring wire is installed inside the temperature measuring wire fixing plug. One end of the temperature measuring wire is connected to multiple thermocouples, and the other end of the temperature measuring wire passes through the temperature measuring wire connector and extends out of the bottom of the temperature measuring instrument connecting flange.

[0010] The main shell has a left observation window on the left side and a right observation window on the right side. The left and right observation windows are arranged opposite each other and are connected to the deposition channel. An observation plate is provided at each of the left and right observation windows. The observation plates are installed on the main shell. A heat protection plate is fixedly connected to the inner side of the observation plate. The heat protection plate is located inside the main shell above the insulation sleeve.

[0011] The present invention also has the following technical features:

[0012] The main housing has an integral mounting flange on its front side.

[0013] The multiple thermocouple mounting holes are arranged on both sides of the calorimeter, and the multiple thermocouple mounting holes on the same side are arranged at equal intervals.

[0014] The main housing surrounding the left and right observation windows has multiple observation plate mounting holes, and the observation plates have multiple observation plate fixing holes, with each observation plate mounting hole and the observation plate fixing hole corresponding to the other.

[0015] The sedimentation channel has a cubic structure with a side length of 80 mm and a height of 165 mm.

[0016] The left and right observation windows are the same size; the left observation window is 80mm long and 50mm wide.

[0017] The calorimeter is made of graphite.

[0018] The observation plate is made of aluminum, and the heat protection plate is made of graphite.

[0019] The temperature measuring wire fixing plug is made of polytetrafluoroethylene.

[0020] This invention also protects a dynamic deposition test system for condensed phase combustion products of a rocket engine, which includes the dynamic deposition test device for condensed phase combustion products of a rocket engine as described above. The dynamic deposition test device for condensed phase combustion products of a rocket engine is fixedly mounted on a support, on which a propellant burner is also fixedly mounted, with the bottom end of the propellant burner fixedly connected to a propellant burner connecting flange; a lifting platform is provided next to the support, and an X-ray emitter is movably mounted on the lifting platform, with the X-ray emitter near the left observation window and its light source directly facing the left observation window; a thermometer is provided next to the lifting platform, and the thermometer is connected to a temperature measuring wire.

[0021] Compared with the prior art, the present invention has the following technical effects:

[0022] (I) The dynamic deposition test device for condensed phase combustion products of rocket engines of the present invention can be used to study the deposition characteristics of condensed phases under different engine propellant loading conditions. By setting up an observation window and combining it with real-time X-ray diagnostic technology, the deposition evolution process of solid propellant combustion products under various propellant loading conditions can be observed. At the same time, the use of a temperature measuring component can overcome the difficulty of traditional temperature measuring devices not being able to operate for long periods under high temperature and high pressure environments, achieving the purpose of real-time measurement of deposition heat flux and heat increment, thereby providing experimental means for subsequent research on deposition ablation mechanisms.

[0023] (II) The dynamic deposition test device for condensed phase combustion products of rocket engines of the present invention has a simple structure and is easy to install and use. Attached Figure Description

[0024] Figure 1This is a schematic diagram of the overall structure of the experimental device for dynamic deposition of condensed phase combustion products in rocket engines.

[0025] Figure 2 This is a cross-sectional view of the experimental setup for dynamic deposition of condensed phase combustion products from a rocket engine.

[0026] Figure 3 This is a schematic diagram of the temperature sensing component.

[0027] Figure 4 This is a schematic diagram of thermocouple layout.

[0028] Figure 5 This is a schematic diagram of the observation board.

[0029] Figure 6 This is a schematic diagram of the overall structure of a dynamic deposition test system for condensed phase combustion products of rocket engines.

[0030] Figure 7 This is a diagram showing the evolution of sedimentary morphology observed using the experimental apparatus of the present invention.

[0031] Figure 8(A) is a graph showing the temperature response characteristics of the calorimeter at different depths measured in the first test using the test apparatus of the present invention.

[0032] Figure 8(B) is a graph showing the temperature response characteristics of the calorimeter at different depths measured in the second experiment using the test apparatus of the present invention.

[0033] The labels in the diagram represent the following: 1-Main shell, 2-Propellant burner connecting flange, 3-Temperature measuring component mounting flange, 4-Deposition channel, 5-Insulation jacket, 6-Calcimer, 7-Thermocouple mounting hole, 8-Thermocouple, 9-Temperature measuring instrument connecting flange, 10-Temperature measuring wire fixing plug, 11-Temperature measuring wire connector, 12-Temperature measuring wire, 13-Left observation window, 14-Right observation window, 15-Observation plate, 16-Heat protection plate, 17-Mounting flange, 18-Observation plate mounting hole, 19-Observation plate fixing hole, 20-Bracket, 21-Propellant burner, 22-Lifting platform, 23-X-ray emitter, 24-Temperature measuring instrument, 25-Mounting component.

[0034] The specific content of the present invention will be further explained in detail below with reference to the embodiments. Detailed Implementation

[0035] To enable dynamic and real-time measurement of heat transfer data of deposited products under different evolution states, this invention, based on a lumped capacitance design, calculates the heat flux density of the gas-liquid two-phase interaction on the surface of the heat flux measurement device by measuring the temperature response at different depths within the device and utilizing existing sequential inverse thermal conduction problem calculation methods. A temperature sensing component is designed, comprising a calorimeter 6, an insulating jacket 5, a thermocouple 8, and a temperature sensing wire fixing plug 10. The specific design concept is as follows:

[0036] First, the selection of the calorimeter substrate:

[0037] When designing a temperature sensing component, the first challenge is selecting the calorimeter material. Based on the design principle of lumped capacitance, the difference in thermal diffusivity between the calorimeter and the sensing element cannot be too large. If the sensing element has a high thermal diffusivity while the calorimeter has a low one, the sensing element will significantly interfere with heat transfer near the measuring point, introducing substantial errors into heat flow inversion calculations. Furthermore, the calorimeter must have relatively stable physicochemical properties; its physical parameters should not change significantly under high-temperature conditions, and it should not generate significant endothermic or exothermic reactions due to thermal decomposition or chemical reactions. Insulating materials are carbonized materials, which undergo thermal decomposition and carbonization upon heating. The endothermic effect of thermal decomposition significantly impacts temperature measurement; parameters such as density and thermal conductivity change drastically after carbonization, and the contact state of the sensing element also changes. Given the significant difference in thermal diffusivity between the insulating material and the sensing element, it is unsuitable as a calorimeter. Graphite, on the other hand, is a non-carbonized material with relatively stable physicochemical properties, possessing advantages such as high-temperature resistance and ablation resistance. Therefore, this invention ultimately adopts a graphite calorimeter.

[0038] Second, circumferential insulation design of the calorimeter:

[0039] The heat flow inversion method using the inverse thermal conductivity problem is based on the quasi-one-dimensional assumption, and heat transfer from the sidewalls of the calorimeter can introduce significant errors into the measurement results. This invention embeds the graphite calorimeter into a single EPDM rubber insulation material, minimizing the influence of lateral and circumferential heat transfer.

[0040] Third, the selection of thermocouples:

[0041] The choice of temperature sensing element is crucial to the entire temperature measurement process. Analysis of the calculation principle of the thermal conduction inverse problem shows that the temperature response rate has a significant impact on the final result; therefore, the temperature sensing element must have a high temperature response rate. Furthermore, due to the high heat flux density of the gas-liquid two-phase scouring within the solid rocket motor, and the high thermal diffusivity of the calorimeter, the temperature at the measuring point closer to the calorimeter surface will be higher. This necessitates a temperature sensing element with a large measurement range. Therefore, this invention uses a thin-wire K-type thermocouple with good temperature response characteristics as the temperature sensing element, minimizing the size of the thermocouple measuring point while ensuring stable and reliable operation. During installation, high-temperature resistant heat-shrink tubing is used to prevent short circuits between thermocouple wires or between the thermocouple and the graphite calorimeter.

[0042] Fourth, the layout of measuring points:

[0043] Theoretically, the inverse problem of thermal conduction allows for the calculation of surface heat flux by placing a single measuring point within the calorimeter. However, sensitivity analysis of this inverse problem reveals that the accuracy of the calculation results is highly sensitive to experimental measurement errors. Furthermore, considering measurement errors caused by temperature measurement, heat loss, and differences in physical properties, the final calculated heat flux may contain significant errors. Therefore, researchers typically employ a design with multiple temperature measuring points. Additionally, the location of the measuring points also affects the results. If the measuring points are too far from the surface, the temperature response may be minimal during operation. Therefore, the measuring points should be placed as close as possible to the measuring surface, ensuring the temperature response does not exceed the thermocouple's range.

[0044] Fifth, thermocouple installation method

[0045] The installation method of thermocouples also has a certain impact on the measurement results. If arranged along the longitudinal heat transfer direction, the longitudinal position of the thermocouple measuring points may not be accurately guaranteed after installation, and thermocouples will also introduce heat conduction losses. Therefore, this invention adopts a transverse arrangement. This arrangement allows for a smaller diameter of the thermocouple mounting holes, which improves the accuracy of heat transfer data and avoids longitudinal position deviations caused by vibrations during engine operation. In addition, the thermocouples are arranged along a direction close to the isotherm, which greatly reduces heat conduction losses.

[0046] It should be noted that all components and instruments in this invention, unless otherwise specified, are components and instruments known in the art. For example, the propellant burner 21 is a propellant burner known in the prior art, which includes a front end cap rod, a gas generator, an ignition charge, a convergent section and an adjustment ring, and the gas generator contains propellant.

[0047] The following are specific embodiments of the present invention. It should be noted that the present invention is not limited to the following specific embodiments. All equivalent modifications made based on the technical solutions of this application fall within the protection scope of the present invention.

[0048] Example 1:

[0049] This embodiment provides a test apparatus for the dynamic deposition of condensed phase combustion products in rocket engines, such as... Figures 1 to 3 As shown, it includes a main shell 1, with a propellant burner connecting flange 2 integrally provided at the top of the main shell 1, and a temperature measuring component mounting flange 3 fixedly connected to the bottom of the main shell 1. The space inside the main shell 1 and the temperature measuring component mounting flange 3 is a deposition channel 4.

[0050] The top of the temperature measuring component mounting flange 3 extends into the main housing 1. An insulation sleeve 5 is fixedly installed inside the top of the temperature measuring component mounting flange 3. A calorimeter 6 is installed inside the insulation sleeve 5. Both the insulation sleeve 5 and the calorimeter 6 are located at the bottom of the deposition channel 4. Multiple thermocouple mounting holes 7 are opened on the calorimeter 6. Thermocouples 8 are installed in the thermocouple mounting holes 7. The bottom of the temperature measuring component mounting flange 3 is fixedly connected to the temperature measuring instrument connecting flange 9. A temperature measuring wire fixing plug 10 and a temperature measuring wire connector 11 are fixedly installed in the temperature measuring instrument connecting flange 9 from top to bottom. A temperature measuring wire 12 is installed in the temperature measuring wire fixing plug 10. One end of the temperature measuring wire 12 is connected to multiple thermocouples 8. The other end of the temperature measuring wire 12 passes through the temperature measuring wire connector 11 and extends out of the bottom of the temperature measuring instrument connecting flange 9.

[0051] A left observation window 13 is provided on the left side of the main shell 1, and a right observation window 14 is provided on the right side of the main shell 1. The left observation window 13 and the right observation window 14 are arranged opposite to each other and are connected to the sedimentation channel 4. An observation plate 15 is provided at the left observation window 13 and the right observation window 14 respectively. The observation plate 15 is installed on the main shell 1. A heat protection plate 16 is fixedly connected to the inner side of the observation plate 15. The heat protection plate 16 is located inside the main shell 1 above the insulation sleeve 5.

[0052] In this embodiment, opening the left observation window 13 and the right observation window 14 can reduce the attenuation of X-rays due to the wall thickness of the main housing 1.

[0053] As one specific solution in this embodiment, such as Figure 1 As shown, a mounting flange 17 is integrally provided on the front side of the main housing 1, and the mounting flange 17 is used to install the experimental device of the present invention.

[0054] As one specific solution in this embodiment, such as Figure 4 As shown, multiple thermocouple mounting holes 7 are arranged on both sides of the calorimeter 6, and the multiple thermocouple mounting holes 7 on the same side are arranged at equal intervals.

[0055] In this embodiment, there are five thermocouple mounting holes 7, and one thermocouple 8 is installed in each thermocouple mounting hole 7. Using multiple thermocouples 8 can improve the accuracy of heat flow calculation results. The thermocouples are arranged at equal intervals along a direction close to the isotherm, which can greatly reduce heat conduction loss and simplify the calculation of heat flow inversion in the later stage. The gaps between the thermocouple mounting holes 7 and the thermocouples 8 are filled with graphite powder to reduce the influence of the small cavities on the heat transfer of the calorimeter and reduce the error of heat flow inversion.

[0056] As one specific solution in this embodiment, such as Figure 1 and Figure 5 As shown, multiple observation plate mounting holes 18 are provided on the main housing 1 around the left observation window 13 and the right observation window 14, and multiple observation plate fixing holes 19 are provided on the observation plate 15. The multiple observation plate mounting holes 18 and the multiple observation plate fixing holes 19 are set in a one-to-one correspondence.

[0057] As a specific embodiment, the deposition channel 4 has a cube structure, the side length of the cross-section of the deposition channel is 80mm, and the height of the deposition channel is 165mm.

[0058] In this embodiment, to avoid edge effects that may occur when testing solid fuel combustion products using X-ray real-time diagnostic technology, the deposition channel 4 is designed as a cube structure, thus avoiding imaging edge effects introduced by other three-dimensional channels such as circles. The dimensions of the deposition channel cross-section can be designed according to different combustion chamber outlet cross-sectional areas. Designers need to simulate the two-phase flow time and confirm the design through calculations.

[0059] As a specific embodiment, the left observation window 13 and the right observation window 14 are the same size; the length of the left observation window is 80mm and the width is 50mm.

[0060] In this embodiment, the lengths of the left observation window 13 and the right observation window 14 are designed based on the cross-sectional area of ​​the deposition channel 4, and the widths are designed based on the deposition layer depth required for the experiment.

[0061] As a specific embodiment, the calorimeter 6 is made of graphite. Using a graphite calorimeter 6 can improve the accuracy of temperature measurement.

[0062] As a specific embodiment, the observation plate 15 is made of aluminum, and the heat protection plate 16 is made of graphite.

[0063] In this embodiment, the thickness of the observation plate 15 is 5 mm; the thickness of the heat protection plate 16 is 5 mm. The thickness of the observation plate 15 and the heat protection plate 16 is determined based on the X-ray radiation power and the imaging clarity under the adjustment state, that is, the thickness is determined based on Beer's attenuation theorem.

[0064] As a specific embodiment, the temperature measuring wire fixing plug 10 is made of polytetrafluoroethylene.

[0065] Example 2:

[0066] This embodiment provides a dynamic deposition test system for condensed phase combustion products of a rocket engine, which includes the dynamic deposition test device for condensed phase combustion products of a rocket engine described in Embodiment 1. For example... Figure 6 As shown, the dynamic deposition test device for condensed phase combustion products of rocket engines is fixedly installed on the support 20. A propellant burner 21 is also fixedly installed on the support 20, and the bottom end of the propellant burner 21 is fixedly connected to the propellant burner connecting flange 2. A lifting platform 22 is set next to the support 20. An X-ray emitter 23 is movably installed on the lifting platform 22. The X-ray emitter 23 is close to the left observation window 13, and the light source of the X-ray emitter 23 is directly facing the left observation window 13. A thermometer 24 is set next to the lifting platform 22 and is connected to the temperature measuring line 12.

[0067] In this embodiment, since the experiment needs to be carried out in a high temperature and high pressure environment, and the two-phase gas pollution generated by the combustion of solid propellant is serious, it is difficult to conduct experiments on the deposition evolution process inside the device using general optical observation methods. Therefore, X-ray emitter 23 is used to conduct experiments through X-ray real-time diagnostic technology.

[0068] As a specific embodiment, one end of the mounting component 25 is fixedly disposed inside the mounting flange 17, and the other end of the mounting component 25 penetrates the main housing 1 and is fixedly installed on the bracket 20. The device of the present invention is fixed by the mounting flange 17 and the mounting component 25.

[0069] The installation and operation process of this invention is as follows:

[0070] First, assemble and install the calorimeter 6, insulation sleeve 5, thermocouple 8 and temperature measuring wire fixing plug 10 in the bottom of the deposition channel 4. Then, install the observation plate 15 and heat protection plate 16 on the left observation window 13 and the right observation window 14 to complete the assembly of the test device.

[0071] Second, such as Figure 6 As shown, the assembled test device is mounted on the bracket 20 via mounting flange 17 and mounting piece 25. The test device is connected to the propellant burner 21 via propellant burner connecting flange 2. Then, the temperature measuring line 12 is connected to the temperature measuring instrument 24. Then, the X-ray emitter 23 is moved so that the emission source of the moving X-ray emitter 23 is directly facing the left observation window 13 and the right observation window 14, thus completing the installation of the test system.

[0072] Third, after the experimental system is installed, the propellant in the propellant burner 21 is ignited. Large droplets from the condensed phase products of propellant combustion will deposit on the surfaces of the insulation jacket 5 and the calorimeter 6, while small droplets will flow out. The droplets deposited on the surface of the calorimeter 6 will rapidly exchange heat with it. Due to the large temperature difference between the droplets and the calorimeter 6, heat will be transferred along its axial direction, and the temperature rise changes at different gradients will be recorded by the thermocouple 8. Simultaneously, the evolution morphology of the droplets deposited on the surfaces of the insulation jacket 5 and the calorimeter 6 will be observed by X-rays projected from the observation plate 15 and the heat protection plate 16, thus achieving the purpose of dynamically and in real-time observing the evolution of the deposition morphology.

[0073] Effect verification:

[0074] The dynamic deposition test apparatus for condensed phase combustion products of rocket engines of the present invention is used in accordance with the present invention. Figure 4 The measurement point layout shown indicates that the evolution of sedimentary morphology was observed as follows: Figure 7 As shown in Figure 8(A) and Figure 8(B), the temperature response characteristics of the calorimeter at different depths obtained by temperature measurement are shown in Figure 8(A) and Figure 8(B).

Claims

1. A dynamic deposition test apparatus for condensed phase combustion products of a rocket engine, characterized in that, Includes a main shell (1), with a propellant burner connecting flange (2) integrally provided at the top of the main shell (1), and a temperature measuring component mounting flange (3) fixedly connected at the bottom of the main shell (1). The space inside the main shell (1) and the temperature measuring component mounting flange (3) is a deposition channel (4). The top of the temperature measuring component mounting flange (3) extends into the main housing (1). An insulating sleeve (5) is fixedly installed inside the top of the temperature measuring component mounting flange (3). A calorimeter (6) is installed inside the insulating sleeve (5). Both the insulating sleeve (5) and the calorimeter (6) are located at the bottom of the deposition channel (4). The calorimeter (6) has multiple thermocouple mounting holes (7), and thermocouples (8) are installed inside the thermocouple mounting holes (7). (3) is fixedly connected to the bottom of the thermometer connecting flange (9). The thermometer connecting flange (9) is fixedly provided with a thermometer wire fixing plug (10) and a thermometer wire connector (11) from top to bottom. The thermometer wire fixing plug (10) is provided with a thermometer wire (12). One end of the thermometer wire (12) is connected to multiple thermocouples (8). The other end of the thermometer wire (12) passes through the thermometer wire connector (11) and extends out of the bottom of the thermometer connecting flange (9). The main shell (1) has a left observation window (13) on its left side and a right observation window (14) on its right side. The left observation window (13) and the right observation window (14) are arranged opposite to each other and are connected to the deposition channel (4). An observation plate (15) is provided at each of the left observation window (13) and the right observation window (14). The observation plate (15) is installed on the main shell (1) and a heat protection plate (16) is fixedly connected to the inner side of the observation plate (15). The heat protection plate (16) is located inside the main shell (1) above the heat insulation sleeve (5).

2. The dynamic deposition test apparatus for condensed phase combustion products of rocket engines as described in claim 1, characterized in that, The main housing (1) is integrally provided with a mounting flange (17) on the front side.

3. The dynamic deposition test apparatus for condensed phase combustion products of rocket engines as described in claim 1, characterized in that, The multiple thermocouple mounting holes (7) are arranged on both sides of the calorimeter (6), and the multiple thermocouple mounting holes (7) on the same side are arranged at equal intervals.

4. The dynamic deposition test apparatus for condensed phase combustion products of rocket engines as described in claim 1, characterized in that, The main housing (1) surrounding the left observation window (13) and the right observation window (14) is provided with a plurality of observation plate mounting holes (18), and the observation plate (15) is provided with a plurality of observation plate fixing holes (19). The plurality of observation plate mounting holes (18) and the plurality of observation plate fixing holes (19) are provided in a one-to-one correspondence.

5. The dynamic deposition test apparatus for condensed phase combustion products of rocket engines as described in claim 1, characterized in that, The sedimentation channel (4) is a cube structure with a side length of 80 mm and a height of 165 mm.

6. The dynamic deposition test apparatus for condensed phase combustion products of rocket engines as described in claim 1, characterized in that, The left observation window (13) and the right observation window (14) are the same size; the left observation window is 80mm long and 50mm wide.

7. The dynamic deposition test apparatus for condensed phase combustion products of rocket engines as described in claim 1, characterized in that, The calorimeter (6) is made of graphite.

8. The dynamic deposition test apparatus for condensed phase combustion products of rocket engines as described in claim 1, characterized in that, The observation plate (15) is made of aluminum, and the heat protection plate (16) is made of graphite.

9. The dynamic deposition test apparatus for condensed phase combustion products of rocket engines as described in claim 1, characterized in that, The temperature measuring wire fixing plug (10) is made of polytetrafluoroethylene.

10. A dynamic deposition test system for condensed phase combustion products of a rocket engine, characterized in that, The device includes a dynamic deposition test apparatus for condensed phase combustion products of a rocket engine as described in any one of claims 1 to 9; the dynamic deposition test apparatus for condensed phase combustion products of a rocket engine is fixedly installed on a support (20), and a propellant burner (21) is also fixedly installed on the support (20), with the bottom end of the propellant burner (21) fixedly connected to the propellant burner connecting flange (2); a lifting platform (22) is provided next to the support (20), and an X-ray emitter (23) is movably installed on the lifting platform (22), with the X-ray emitter (23) close to the left observation window (13), and the light source of the X-ray emitter (23) facing the left observation window (13); a thermometer (24) is provided next to the lifting platform (22), and the thermometer (24) is connected to the temperature measuring line (12).

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