A light-gathering jet integrated heat storage propulsion device

Abstract

The application discloses a light-gathering and jet integrated heat storage propelling device, which comprises a head shell, a body shell and a ceramic heat storage body, a ceramic metal transition cone cavity is arranged on the ceramic heat storage body, a high-temperature-resistant metal light-receiving jet pipe is arranged in the ceramic metal transition cone cavity, a light-gathering and jet channel is arranged on the high-temperature-resistant metal light-receiving jet pipe, the light-gathering and jet channel comprises a converging channel and a diverging channel, a throat is formed at the joint of the converging channel and the diverging channel, a light-gathering and jet opening is arranged on the body shell and is communicated with the diverging channel, the high-temperature-resistant metal light-receiving jet pipe realizes the light-gathering and jet functions, the front end of the diverging channel of the light-gathering and jet channel is used as a light-receiving area to receive the heat of a light spot, the design of a light-gathering cavity on the ceramic heat storage body is cancelled, the envelope size of the propelling device is reduced, more heat storage mass is provided in the limited space envelope, and the technical problem that the propelling device in the prior art cannot simultaneously have high heat storage capacity and small envelope size is solved.

Description

Technical Field

[0001] This invention belongs to the aerospace field and relates to propulsion devices, specifically a concentrated solar jet integrated thermal regenerative propulsion device. Background Technology

[0002] With the continuous expansion of space exploration missions and the booming development of commercial space activities, humanity has placed increasingly higher demands on the efficiency and economy of space transportation. Lightweight, flexible, fast-responding, and low-cost spacecraft will become the mainstay of future space activities, and more efficient space propulsion technologies will become an urgent need. Solar thermal propulsion is a new type of space propulsion technology, characterized by its small size and high specific impulse, which will provide significant performance advantages when applied to small spacecraft. A solar thermal propulsion system generally consists of a concentrator, a heat exchange core, a nozzle, and a propellant supply system. Working principle: The concentrator focuses sunlight to heat the heat exchange core at the focal point. The propellant is heated as it flows through the heat exchange core, and its expansion and acceleration through the nozzle generate thrust. Hydrogen has a low molar mass and high specific heat capacity, allowing for the highest exhaust velocity, making it an ideal propellant for this propulsion technology.

[0003] Currently, chemical propulsion is the most widely used and only propulsion technology in the aerospace field capable of generating high thrust. However, its limitation lies in its relatively low specific impulse. For small spacecraft, high-specific-impulse propulsion technologies such as electric propulsion are clearly more advantageous, but electric propulsion provides very little thrust, thus requiring a long time to meet the total impulse required for the mission. Photothermal propulsion technology, with its higher specific impulse and moderate thrust (50mN to 10N), can fill the gap between chemical and electric propulsion. It is highly suitable for orbital maneuvers, attitude control, and position holding tasks in small spacecraft, making it a promising new concept propulsion technology.

[0004] In the early stages, rhenium was used to manufacture thrust chamber prototypes. This metal has a high melting point and thermal conductivity, making it an ideal material for thrust chamber manufacturing. However, because rhenium is relatively rare, using rhenium to manufacture the entire heat exchange core would increase research and manufacturing costs significantly, making it uneconomical. On the other hand, ceramic materials, which are chemically stable, have a large specific heat capacity, and are inexpensive, suffer from the problem of thermal stress concentration after high-temperature heating, leading to ceramic breakage. Summary of the Invention

[0005] In view of the shortcomings of the existing technology, the purpose of this invention is to provide a concentrated jet integrated thermal regenerative propulsion device to solve the technical problem that the propulsion device in the prior art is difficult to balance high heat storage capacity and small envelope size.

[0006] To solve the above-mentioned technical problems, the present invention adopts the following technical solution:

[0007] A focused-jet integrated thermal regenerative propulsion device includes a head shell and a body shell. A ceramic regenerator is installed in the cavity formed by the head shell and the body shell. A slit is provided between the head shell, the body shell and the ceramic regenerator. A coaxial annular interface for the head of the ceramic regenerator is provided on one end face of the ceramic regenerator and communicates with the slit.

[0008] The other end face of the ceramic heat storage body is coaxially provided with a ceramic-metal junction frustum cavity, and a high-temperature resistant metal light-receiving nozzle is installed inside the ceramic-metal junction frustum cavity.

[0009] The high-temperature resistant metal light-receiving nozzle has a coaxially extending focused light-jetting channel.

[0010] The focusing jet channel includes a converging channel and an expanding channel that are coaxially connected. The junction of the converging channel and the expanding channel forms a throat. The length of the converging channel is shorter than the length of the expanding channel.

[0011] The outer shell body has a bottom groove on one end face of the bottom wall of the outer shell body. The bottom groove of the outer shell body is coaxially arranged with the high temperature resistant metal light-receiving nozzle. The part of the tail of the high temperature resistant metal light-receiving nozzle that extends out of the ceramic heat storage body is embedded in the bottom groove of the outer shell body.

[0012] The other end face of the bottom wall of the outer shell is also provided with a focusing nozzle, which is coaxially arranged with the groove at the bottom of the outer shell, so that the focusing nozzle is connected to the expansion channel.

[0013] The ceramic heat storage body is also provided with a main pipe that is closed at one end and open at the other end. The main pipe is coaxially arranged with the high-temperature resistant metal light-receiving nozzle. The open end of the main pipe is connected to the convergence channel. Multiple secondary pipes are also provided around the main pipe in the ceramic heat storage body. One end of the secondary pipe is connected to the side wall of the main pipe, and the other end of the secondary pipe is connected to the side wall of the ceramic heat storage body and the slit.

[0014] The present invention also has the following technical features:

[0015] The expansion channel has a cone angle of 15° and an area ratio of 81 between the expansion channel outlet and the throat.

[0016] The ceramic heat storage body is made of molten aluminum oxide, and the high-temperature resistant metal light-receiving nozzle is made of rhenium metal.

[0017] The wall thickness of the high-temperature resistant metal light-receiving nozzle is 10mm.

[0018] The length of the expansion channel extending beyond the ceramic heat storage body is 4 mm.

[0019] The heat storage body has multiple circumferentially spaced ventilation holes on one side wall of the annular interface at the head, and these ventilation holes are connected to the slit.

[0020] The outer shell head housing has an integrally formed cylindrical propellant inlet at its center. One end of the propellant inlet extends out of the outer shell head housing, and the other end extends into the annular interface of the heat storage body head.

[0021] The inner end face of the outer shell head is coaxially provided with an inner groove and an outer groove. The inner groove and the outer groove are arranged sequentially from the inside to the outside with the propellant inlet as the center. The inner groove and the other end of the annular interface of the heat storage body head are nested and fixed to form a slit between the ceramic heat storage body and the outer shell head and the outer shell body.

[0022] The outer shell body is fixed by nesting the outer shell head with the annular interface of the outer shell body.

[0023] The diameter of the slit is 2mm; the diameter of the vent hole at the interface is 1mm.

[0024] The head shell and the body shell are also fastened together by bolts and nuts.

[0025] A high-temperature resistant gasket is provided between the annular interface on the outer shell body and the inner groove on the head of the outer shell.

[0026] A high-temperature resistant gasket is provided between the expansion channel and the groove at the bottom of the outer casing.

[0027] High-temperature resistant gaskets are also provided at the locations where bolts and nuts are used to engage between the head shell and the body shell of the outer casing.

[0028] Compared with the prior art, the present invention has the following technical effects:

[0029] (I) The high-temperature resistant metal light-receiving nozzle proposed in this invention achieves both focusing and jetting functions. The front end of the expansion channel in the high-temperature resistant metal light-receiving nozzle serves as the light-receiving area to receive the heat from the focused light spot. This eliminates the need for the existing focusing cavity design on the ceramic heat storage body, reduces the envelope size of the propulsion device, and provides more heat storage mass within the limited space envelope. This solves the technical problem in the prior art that propulsion devices cannot simultaneously achieve high heat storage capacity and small envelope size.

[0030] (II) The integrated focused jet thermal propulsion device proposed in this invention combines a high-temperature resistant metal light-receiving nozzle made of high-temperature resistant rhenium metal with a ceramic thermal accumulator, which stores more heat with the same mass and saves a lot of manufacturing costs.

[0031] (III) The slit between the ceramic heat storage body and the head shell and body shell of the outer shell proposed in this invention does not allow propellant to enter during the concentrated heating process. Before the gas is introduced, the slit is in a vacuum state. In conjunction with the thermal radiation coating applied to the inner side of the head shell and body shell of the outer shell, the heat dissipation of the ceramic heat storage body to the outside in space after the temperature rise is greatly reduced, so that more heat can be used to heat the propellant to generate thrust.

[0032] (IV) The present invention can use 3D printing technology to print the designed ceramic heat storage body and embed the machined high-temperature resistant metal nozzle into it, which reduces the difficulty of the process. Attached Figure Description

[0033] Figure 1 This is a right-side structural schematic diagram of the integrated regenerative propulsion device for concentrating light jets.

[0034] Figure 2 This is a schematic diagram of the right-side cross-sectional structure of the integrated regenerative propulsion device for concentrating light jets.

[0035] Figure 3 This is a right-side structural schematic diagram of the high-temperature resistant metal light-receiving nozzle in a concentrated light jet integrated regenerative propulsion device.

[0036] Figure 4 This is a schematic diagram of the right-side cross-sectional structure of the high-temperature resistant metal light-receiving nozzle in the integrated concentrated light jet regenerative propulsion device.

[0037] Figure 5 This is a schematic diagram of the ceramic regenerator structure in the integrated concentrated jet thermal regenerator propulsion device.

[0038] Figure 6 This is a schematic diagram of the right-side cross-sectional structure of the ceramic regenerator in the integrated concentrated jet thermal regenerator propulsion device.

[0039] Figure 7 This is a schematic diagram of the right-side structure of the outer shell of the integrated concentrated solar power propulsion device.

[0040] Figure 8 This is a schematic diagram of the right-side cross-sectional structure of the outer shell of the integrated concentrated solar power propulsion device.

[0041] Figure 9 This is a schematic diagram of the right-hand structure of the head shell of the integrated concentrated solar power propulsion device.

[0042] Figure 10 This is a schematic diagram of the right-side cross-sectional structure of the head shell of the integrated concentrated solar power propulsion device.

[0043] The meanings of the labels in the diagram are as follows: 1-Outer shell head shell, 2-Outer shell body shell, 3-Ceramic heat storage body, 4-Slit, 5-Focusing jet channel, 6-Bolt, 7-Nut, 8-High temperature resistant metal light-receiving nozzle, 9-Focusing jet nozzle.

[0044] 101 - Propellant inlet, 102 - Inner groove of the outer shell head, 103 - Outer groove of the outer shell head.

[0045] 201 - Annular interface on the outer casing; 202 - Groove at the bottom of the outer casing.

[0046] 301-Annular interface at the head of the heat storage body; 302-Ventilation hole at the interface; 303-Ceramic-metal junction cone cavity; 304-Main pipe; 305-Secondary pipe.

[0047] 501 - Convergence channel, 502 - Dilation channel, 503 - Throat.

[0048] The specific content of the present invention will be further explained in detail below with reference to the embodiments. Detailed Implementation

[0049] It should be noted that, unless otherwise specified, the equipment and materials used in this invention are all those known in the prior art.

[0050] This invention combines rhenium metal and ceramic materials. Utilizing the high-temperature resistance, high thermal conductivity, and high thermal stress limit of high-temperature resistant metals (such as rhenium and molybdenum), a high-temperature resistant metal light-receiving nozzle for an integrated focused solar propulsion device is manufactured. The focused light spot irradiates the rhenium metal surface, where it absorbs heat and rapidly transfers it to the outer ceramic heat storage body. The high specific heat capacity of the ceramic allows for the storage of more heat. Furthermore, because rhenium metal has a higher thermal conductivity than ceramic, heat is preferentially conducted to other parts of the metal, resulting in a more uniform temperature on the ceramic's heat-absorbing surface, eliminating thermal stress concentration, and preventing localized high temperatures from causing ceramic breakage.

[0051] Furthermore, to reduce heat radiation loss to the outside, this invention eliminates the conventional focusing cavity and designs the nozzle extending outward on the other side as an integrated light-receiving and jetting nozzle. The focused light spot directly irradiates inward from the outlet of the integrated light-receiving and jetting nozzle. The advantage of this design is that it reduces the envelope size of the integrated light-receiving and jetting regenerative propulsion device, combines the space occupied by the two functional areas, and has the smallest surface area for the same solid mass, i.e., the smallest area for heat radiation to the outside. The slit design allows the propellant to form a fluid insulation layer enveloping it in the slit between the ceramic heat accumulator and the head shell and body shell, regenerating and utilizing some of the dissipated heat.

[0052] Following the above technical solutions, specific embodiments of the present invention are given below. It should be noted that the present invention is not limited to the following specific embodiments, and all equivalent modifications made based on the technical solutions of this application fall within the protection scope of the present invention.

[0053] Example:

[0054] This embodiment provides a focused-jet integrated thermal regenerative propulsion device, including a head shell 1 and a body shell 2, as shown below. Figure 1 , Figure 2 , Figure 5 and Figure 6 As shown, a ceramic heat storage body 3 is installed in the cavity formed by the outer shell head shell 1 and the outer shell body shell 2. A slit 4 is provided between the outer shell head shell 1 and the outer shell body shell 2 and the ceramic heat storage body 3. A heat storage body head annular interface 301 is coaxially provided on one end face of the ceramic heat storage body 3 and communicates with the slit 4.

[0055] like Figure 1 , Figure 2 , Figure 5 and Figure 6 As shown, a ceramic-metal junction conical cavity 303 is coaxially formed on the other end face of the ceramic heat storage body 3, and a high-temperature resistant metal light-receiving nozzle 8 is installed inside the ceramic-metal junction conical cavity 303.

[0056] like Figures 1 to 4 As shown, a through-type focusing jet channel 5 is coaxially opened on the high-temperature resistant metal light-receiving nozzle 8.

[0057] like Figures 1 to 4 As shown, the focusing jet channel 5 includes a converging channel 501 and an expanding channel 502 that are coaxially connected. The junction of the converging channel 501 and the expanding channel 502 forms a throat 503. The length of the converging channel 501 is less than the length of the expanding channel 502.

[0058] like Figure 1 , Figure 2 , Figure 7 and Figure 8 As shown, a bottom groove 202 is provided on one end face of the bottom wall of the outer shell body 2. The bottom groove 202 is coaxially arranged with the high-temperature resistant metal light-receiving nozzle 8. The part of the tail of the high-temperature resistant metal light-receiving nozzle 8 that extends out of the ceramic heat storage body 3 is embedded in the bottom groove 202.

[0059] like Figure 1 , Figure 2 , Figure 7 and Figure 8 As shown, a focusing nozzle 9 is also provided on the other end face of the bottom wall of the outer shell 2. The focusing nozzle 9 is coaxially arranged with the bottom groove 202 of the outer shell, so that the focusing nozzle 9 is connected to the expansion channel 502.

[0060] like Figure 1 , Figure 2 , Figure 5 and Figure 6 As shown, a main pipe 304 with one end closed and the other end open is also provided inside the ceramic heat storage body 3. The main pipe 304 is coaxially arranged with the high-temperature resistant metal light-receiving nozzle 8. The open end of the main pipe 304 is connected to the convergence channel 501. Multiple secondary pipes 305 are also provided inside the ceramic heat storage body 3 around the main pipe 304. One end of the secondary pipe 305 is connected to the side wall of the main pipe 304, and the other end of the secondary pipe 305 leads to the side wall of the ceramic heat storage body 3 and is connected to the slit 4.

[0061] In this embodiment, the throat area at throat 503 is further calculated using the following formula:

[0062]

[0063]

[0064] In the formula:

[0065] This indicates the flow rate passing through the throat, expressed in kg / s.

[0066] This indicates the total pressure of the thrust chamber, expressed in Pa.

[0067] This represents the area of ​​the throat, in meters. 2 .

[0068] This represents the gas constant, with units of J / kg·K.

[0069] This indicates the total temperature of the thrust chamber, expressed in Kelvin (K).

[0070] This is an intermediate quantity.

[0071] k represents the specific heat ratio.

[0072] In this embodiment, the cone angle of the expansion channel 502 is 15°, and the area ratio of the outlet of the expansion channel 502 to the throat 503 is 81.

[0073] In this embodiment, the ceramic heat storage body 3 is made of molten aluminum oxide, and the high-temperature resistant metal light-receiving nozzle 8 is made of rhenium metal.

[0074] In this embodiment, the wall thickness of the high-temperature resistant metal light-receiving nozzle 8 is 10mm; the length of the tail of the expansion channel 502 extending out of the ceramic heat storage body 3 is 4mm.

[0075] like Figure 1 , Figure 2 , Figure 5 and Figure 6 As shown, multiple venting holes 302 are circumferentially equidistantly opened on one side wall of the annular interface 301 at the head of the heat storage body, and the venting holes 302 are connected to the slit 4.

[0076] like Figure 1 , Figure 2 , Figure 9 and Figure 10 As shown, a cylindrical propellant inlet 101 is integrally formed at the center of the outer shell head housing 1. One end of the propellant inlet 101 extends out of the outer shell head housing 1, and the other end of the propellant inlet 101 extends into the annular interface 301 of the heat storage body head.

[0077] like Figure 1 , Figure 2 , Figure 9 and Figure 10 As shown, an inner groove 102 and an outer groove 103 are coaxially formed on the inner end face of the outer shell head housing 1. The inner groove 102 and the outer groove 103 are arranged sequentially from the inside to the outside with the propellant inlet 101 as the center. The other end of the inner groove 102 and the annular interface 301 of the heat storage body head are nested and fixed so that a slit 4 is formed between the ceramic heat storage body 3 and the outer shell head housing 1 and the outer shell body housing 2.

[0078] like Figure 1 and Figure 2 As shown, the outer shell body 2 is nested and fixed to the outer groove 103 of the outer shell head through the annular interface 201 of the outer shell body.

[0079] In this embodiment, the diameter of the slit 4 is 2 mm; the diameter of the interface ventilation hole 302 is 1 mm.

[0080] like Figure 2 As shown, the head shell 1 and the body shell 2 are also fastened together by bolts 6 and nuts 7.

[0081] In this embodiment, a high-temperature resistant gasket is further provided between the annular interface 201 of the outer shell body and the inner groove 102 of the outer shell head; a high-temperature resistant gasket is provided between the expansion channel 502 and the bottom groove 202 of the outer shell body; and a high-temperature resistant gasket is also provided at the position where the bolts 6 and nuts 7 are used to cooperate between the outer shell head shell 1 and the outer shell body shell 2.

[0082] Furthermore, in this embodiment, the ceramic heat storage body 3 can be manufactured using 3D printing technology.

[0083] In this embodiment, the light spot after focusing on the right side of the integrated solar-jet regenerative propulsion device is irradiated into the high-temperature resistant metal light-receiving nozzle 8. The heat provided by the light spot is quickly conducted to the ceramic heat storage body 3 by the high-temperature resistant metal light-receiving nozzle 8. No working fluid is introduced into the slit 4 between the ceramic heat storage body 3 and the outer shell head shell 1 and the outer shell body shell 2 during the heating process. The slit 4 is in a vacuum state, which reduces the energy dissipation to the outside during the heating process. The temperature of the ceramic heat storage body 3 gradually rises. When the energy input and heat dissipation reach equilibrium, the temperature no longer changes. At this time, hydrogen is introduced through the propellant inlet 101. The hydrogen flows into the slit 4 between the ceramic heat storage body 3 and the outer shell head shell 1 and the outer shell body shell 2 through the venting hole 302 on the annular interface 301 on the head of the ceramic heat storage body 3. The hydrogen in the slit 4 absorbs some of the heat radiated by the ceramic heat storage body 3 to the outside and is preheated before entering the main pipe 304 and the secondary pipe 305 to conduct more thorough convective heat exchange with the ceramic heat storage body 3. After absorbing heat and rising in the main pipe 304 and the secondary pipe 305, the hydrogen passes through the convergence channel 501, the throat 503 and the expansion channel 502. The hydrogen is then ejected from the concentrating jet port 9 through the convergence and expansion of the concentrating jet channel 5 and generates thrust.

[0084] Furthermore, in this embodiment, a simulation model is constructed and material properties are set. When the ceramic heat storage body 3 is heated to above 1800K, 0.1g / s of hydrogen gas is introduced through the propellant inlet 101. After being heated and ejected, it can generate a thrust of more than 0.6N, which can meet the requirements of slow orbit change of the space flight device. The equivalent vacuum specific impulse of the device reaches 6000m / s, that is, the specific impulse exceeds 600s, which is far greater than the specific impulse of about 300s of conventional chemical propellants. More work can be done under the same propellant flow rate. Similarly, calculations were performed to simulate a satellite entering an orbit with the back of the Earth after the concentrated heating is completed and the light source input is turned off. The results show that after the 2kg ceramic heat storage body 3 is heated and enters the back of the Earth, it can still provide the propulsion device with Newton-level thrust for more than 1 minute.

Claims

1. A light-gathering and jet integration heat storage propulsion device, comprising a shell head shell (1) and a shell body shell (2), a ceramic heat storage body (3) is installed in the cavity surrounded by the shell head shell (1) and the shell body shell (2), a slit (4) is arranged between the shell head shell (1), the shell body shell (2) and the ceramic heat storage body (3), and a heat storage body head annular interface (301) is coaxially arranged on one end face of the ceramic heat storage body (3) and connected with the slit (4), characterized in that: a ceramic metal transition cone cavity (303) is coaxially arranged on the other end face of the ceramic heat storage body (3), and a high-temperature-resistant metal light-receiving jet pipe (8) is fitted and installed in the ceramic metal transition cone cavity (303); the high-temperature-resistant metal light-receiving jet pipe (8) is coaxially provided with a through light-gathering and jet channel (5); the light-gathering and jet channel (5) comprises a converging channel (501) and a diverging channel (502) coaxially connected in communication, a throat (503) is formed at the joint of the converging channel (501) and the diverging channel (502), and the length of the converging channel (501) is less than the length of the diverging channel (502); an end face of a bottom wall of the shell body shell (2) is provided with a shell body bottom end groove (202) coaxially arranged with the high-temperature-resistant metal light-receiving jet pipe (8), and a part of the high-temperature-resistant metal light-receiving jet pipe (8) extending out of the ceramic heat storage body (3) is embedded in the shell body bottom end groove (202); the other end face of the bottom wall of the shell body shell (2) is also provided with a light-gathering and jet port (9) coaxially arranged with the shell body bottom end groove (202), so that the light-gathering and jet port (9) is in communication with the diverging channel (502); the ceramic heat storage body (3) is also provided with a main pipeline (304) with one end closed and the other end open, the main pipeline (304) is coaxially arranged with the high-temperature-resistant metal light-receiving jet pipe (8), the open end of the main pipeline (304) is in communication with the converging channel (501), and a plurality of secondary pipelines (305) are arranged around the main pipeline (304) in the ceramic heat storage body (3), one end of each secondary pipeline (305) is in communication with the side wall of the main pipeline (304), and the other end of each secondary pipeline (305) leads to the side wall of the ceramic heat storage body (3) and is in communication with the slit (4). The taper angle of the diverging channel (502) is 15°, and the area ratio of the outlet of the diverging channel (502) to the throat (503) is 81. The ceramic heat storage body (3) is made of fused alumina, and the high-temperature-resistant metal light-receiving jet pipe (8) is made of rhenium metal. The wall thickness of the high-temperature-resistant metal light-receiving jet pipe (8) is 10 mm. The length of the tail part of the diverging channel (502) extending out of the ceramic heat storage body (3) is 4 mm. A plurality of interface air exchange round holes (302) are equidistantly arranged on the side wall of one end of the heat storage body head annular interface (301) in a circumferential direction, and the interface air exchange round holes (302) are in communication with the slit (4). ​ 2. The integrated light condensing and jet propulsion accumulator device according to claim 1, wherein ​ 3. The integrated light condensing and jet accumulating propulsion device according to claim 1, wherein ​ 4. The integrated light condensing and jet accumulating propulsion device according to claim 1, wherein ​ 5. The integrated light condensing and jet accumulating propulsion device according to claim 1, wherein ​ 6. The integrated light condensing and jet accumulating propulsion device according to claim 1, wherein ​ 7. The integrated light condensing and jet accumulating propulsion device according to claim 1, wherein The center of the shell head shell (1) is integrally provided with a cylindrical propellant inlet (101), one end of the propellant inlet (101) extends out of the shell head shell (1), the other end of the propellant inlet (101) extends into the heat accumulator head annular interface (301); The inner end face of the shell head shell (1) is coaxially provided with a shell head inner groove (102) and a shell head outer groove (103), the shell head inner groove (102) and the shell head outer groove (103) are arranged from inside to outside with the propellant inlet (101) as the center, the shell head inner groove (102) and the other end of the heat accumulator head annular interface (301) are nested and fixed, so that the ceramic heat accumulator (3) is formed between the shell head shell (1) and the shell body shell (2) The gap (4) is formed. The shell body shell (2) is nested and fixed with the shell head outer groove (103) through the shell body annular interface (201).

8. The integrated light condensing and jet accumulating propulsion device according to claim 6, wherein The diameter of the gap (4) is 2mm; the diameter of the interface ventilation round hole (302) is 1mm.

9. The integrated light condensing and jet accumulating propulsion device according to claim 1, wherein The shell head shell (1) and the shell body shell (2) are also fastened and connected by the cooperation of the bolt (6) and the nut (7).

10. The integrated light and jet accumulator propulsion device of any one of claims 1, 7 or 9, wherein, The high-temperature-resistant gasket is arranged between the shell body annular interface (201) and the shell head inner groove (102); The high-temperature-resistant gasket is arranged between the expansion channel (502) and the shell body bottom end groove (202); The high-temperature-resistant gasket is also arranged at the position where the bolt (6) and the nut (7) are cooperatively used between the shell head shell (1) and the shell body shell (2).

Images