Light condensation and injection integrated heat storage propelling device

Abstract

The invention discloses a light gathering and spraying integrated heat storage propelling device which comprises a shell head shell, a shell body shell and a ceramic heat storage body, a ceramic metal connection frustum cavity is formed in the ceramic heat storage body, and a high-temperature-resistant metal light receiving spraying pipe is installed in the ceramic metal connection frustum cavity; the high-temperature-resistant metal light receiving spray pipe is provided with a light gathering spray channel. The light-gathering injection channel comprises a convergence channel and an expansion channel, and a throat is formed at the joint of the convergence channel and the expansion channel; the shell of the shell body part is provided with a light-gathering jet orifice, and the light-gathering jet orifice is communicated with the expansion channel; according to the high-temperature-resistant metal light receiving spray pipe, the light gathering function and the spraying function are achieved, the front end of an expansion channel of a light gathering spraying channel serves as a light receiving area to receive heat of light gathering light spots, the design of a light gathering cavity in a ceramic heat storage body is omitted, the envelope size of the propelling device is reduced, more heat storage mass is provided in a limited space envelope, and the energy consumption is reduced. The technical problem that a propelling device in the prior art is difficult to give consideration to high heat storage capacity and small envelope size is solved.

Description

Technical Field

[0001] The present invention belongs to the field of aerospace, relates to a propulsion device, and particularly relates to a combined concentrating and jetting regenerative thermal propulsion device. Background Art

[0002] With the continuous expansion of space exploration missions and the booming development of commercial space activities, humans have put forward higher and higher requirements for space transportation efficiency and economy. Lightweight, flexible, fast-responsive, and low-cost spacecraft will become the main force in future space activities, and more efficient space propulsion technologies will also become an urgent need. Solar thermal propulsion is a new type of space propulsion technology, which has the characteristics of small volume and high specific impulse, and will gain great 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, and the propellant is heated when flowing through the heat exchange core, and thrust is generated through the expansion and acceleration of the nozzle. Hydrogen has a small molar mass and a high specific heat capacity, and can obtain the highest exhaust velocity, making it an ideal propellant for this propulsion technology.

[0003] At present, chemical propulsion technology is the most widely used in the field of aerospace and is also the only propulsion technology that can generate large thrust. However, its limitation lies in its relatively low specific impulse. On small spacecraft, high-specific-impulse propulsion technologies such as electric propulsion are obviously more advantageous, but the thrust that electric propulsion can provide is very small, so it takes a long time to meet the total impulse required for the mission. Solar thermal propulsion technology has a relatively high specific impulse and moderate thrust, and can provide a thrust of 50 mN to 10 N, which can fill the gap between chemical propulsion and electric propulsion, and is very suitable for tasks such as orbital maneuvering, attitude control, and position holding of small spacecraft. It is a new concept propulsion technology with great development potential.

[0004] In the space propulsion technology development plan of NASA in the United States, solar thermal propulsion technology is also listed as a project for priority development and realization in the near future. Rockwell Corporation in the United States early used rhenium metal to manufacture a thrust chamber test piece. This metal has a high melting point and thermal conductivity, and is an ideal material for manufacturing the thrust chamber. However, due to the rarity of rhenium metal, using rhenium metal to manufacture the entire heat exchange core body will increase a large amount of research and development and manufacturing costs, and is not economical; while ceramic materials with stable chemical properties, large specific heat capacity, and low cost have the problem that thermal stress concentration occurs after high-temperature heating, resulting in ceramic fragmentation. Summary of the Invention

[0005] Aiming at the deficiencies of the existing technology, the purpose of the present invention is to provide a combined concentrating and jetting regenerative thermal propulsion device to solve the technical problem that it is difficult for the existing propulsion devices to balance high heat storage capacity and small envelope size.

[0006] To solve the above technical problems, the present invention adopts the following technical solutions to achieve:

[0007] A focusing jet integrated heat storage propulsion device comprises an outer shell head shell and an outer shell body shell, a ceramic heat storage body is installed in a cavity surrounded by the outer shell head shell and the outer shell body shell, a slit is provided between the outer shell head shell and the outer shell body shell and the ceramic heat storage body, and a heat storage body head annular interface is coaxially arranged on one end surface of the ceramic heat storage body and is connected to the slit.

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

[0009] A through-going light-focusing injection channel is coaxially provided on the high-temperature-resistant metal light-receiving nozzle.

[0010] The focusing injection channel comprises a convergent channel and an expansion channel which are coaxially connected, a throat is formed at the intersection of the convergent channel and the expansion channel, and the length of the convergent channel is shorter than that of the expansion channel.

[0011] A bottom groove of the shell body is provided on one end surface of the bottom wall of the shell body, and the bottom groove of the 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 extending out of the ceramic heat storage body is embedded in the bottom groove of the shell body.

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

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

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

[0015] The cone angle of the expansion channel is 15°, and the area ratio of the expansion channel outlet to the throat is 8:1.

[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 10 mm.

[0018] The tail of the expansion channel extends out of the ceramic heat storage body by 4 mm.

[0019] On one side wall of one end of the head annular interface of the heat storage body, a plurality of interface ventilation circular holes are circumferentially and equidistantly arranged, and the interface ventilation circular holes are communicated with the slit.

[0020] At the central position of the head shell of the outer shell, a cylindrical propellant inlet is integrally formed. One end of the propellant inlet extends outside the head shell of the outer shell, and the other end of the propellant inlet extends into the head annular interface of the heat storage body.

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

[0022] The body shell of the outer shell is nested and fixed with the outer groove of the head of the outer shell through the annular interface of the body of the outer shell.

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

[0024] The head shell of the outer shell and the body shell of the outer shell are also tightly connected by the cooperation of bolts and nuts.

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

[0026] A high-temperature resistant gasket is arranged between the expansion channel and the bottom groove of the body of the outer shell.

[0027] A high-temperature resistant gasket is also arranged at the position where the head shell of the outer shell and the body shell of the outer shell are used in cooperation with bolts and nuts.

[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 by the present invention realizes the two functions of light concentration and injection. 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 of the light-concentrated spot, cancels the design of the existing light-concentrating cavity on the ceramic heat storage body, reduces the envelope size of the propulsion device and gives more heat storage mass within the limited space envelope, and solves the technical problem that it is difficult for the propulsion device in the prior art to balance high heat storage capacity and small envelope size.

[0030] (Ⅱ) The integrated light-concentrating injection heat storage propulsion device proposed by the present invention combines a high-temperature resistant metal light-receiving nozzle made of high-temperature resistant metal rhenium with a ceramic heat storage body, stores more heat under the same mass and saves a large amount of manufacturing costs.

[0031] (III) During the process of concentrating and heating, the propellant is not introduced into the slit between the ceramic regenerator proposed by the present invention and the head shell and the body shell of the outer shell. Before ventilation, the slit is in a vacuum state. Combined with the thermal radiation coating applied on the inner sides of the head shell and the body shell of the outer shell, the heat dissipation of the ceramic regenerator to the outside world in space after heating is greatly reduced, enabling more heat to be used for heating the propellant to generate thrust.

[0032] (IV) The present invention can use 3D printing technology to print the designed ceramic regenerator and embed the machined high-temperature-resistant metal nozzle into it, reducing the process difficulty. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 It is a right-view structural schematic diagram of the overall assembly structure of the concentrating and jetting integrated regenerative propulsion device.

[0034] Figure 2 It is a right-view sectional structural schematic diagram of the overall assembly structure of the concentrating and jetting integrated regenerative propulsion device.

[0035] Figure 3 It is a right-view structural schematic diagram of the high-temperature-resistant metal light-receiving nozzle in the concentrating and jetting integrated regenerative propulsion device.

[0036] Figure 4 It is a right-view sectional structural schematic diagram of the high-temperature-resistant metal light-receiving nozzle in the concentrating and jetting integrated regenerative propulsion device.

[0037] Figure 5 It is a right-view structural schematic diagram of the ceramic regenerator in the concentrating and jetting integrated regenerative propulsion device.

[0038] Figure 6 It is a right-view sectional structural schematic diagram of the ceramic regenerator in the concentrating and jetting integrated regenerative propulsion device.

[0039] Figure 7 It is a right-view structural schematic diagram of the body part of the outer shell in the concentrating and jetting integrated regenerative propulsion device.

[0040] Figure 8 It is a right-view sectional structural schematic diagram of the body part of the outer shell in the concentrating and jetting integrated regenerative propulsion device.

[0041] Figure 9 It is a right-view structural schematic diagram of the head part of the outer shell in the concentrating and jetting integrated regenerative propulsion device.

[0042] Figure 10 It is a right-view sectional structural schematic diagram of the head part of the outer shell in the concentrating and jetting integrated regenerative propulsion device.

[0043] The meanings of the labels in the figure are as follows: 1 - outer shell head housing, 2 - outer shell body housing, 3 - ceramic regenerator, 4 - slit, 5 - concentrating injection channel, 6 - bolt, 7 - nut, 8 - high-temperature resistant metal light-receiving nozzle, 9 - concentrating injection port.

[0044] 101 - propellant inlet, 102 - inner groove in the outer shell head, 103 - outer groove in the outer shell head.

[0045] 201 - annular interface of the outer shell body, 202 - bottom groove of the outer shell body.

[0046] 301 - annular interface of the regenerator head, 302 - ventilation round hole for the interface, 303 - ceramic-metal transition frustum cavity, 304 - main pipeline, 305 - secondary pipeline.

[0047] 501 - convergent channel, 502 - divergent channel, 503 - throat.

[0048] The following further elaborates on the specific content of the present invention in conjunction with embodiments. Specific Embodiment

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

[0050] The present invention selects to combine two materials, metal rhenium and ceramic. Utilizing the properties of high-temperature resistant metals (such as rhenium, molybdenum, etc.) like high temperature resistance, high thermal conductivity, and high thermal stress limit, a high-temperature resistant metal light-receiving nozzle of the concentrating injection integrated regenerative propulsion device is manufactured. The focused light spot is irradiated onto the rhenium metal surface. After the rhenium metal absorbs heat, it quickly transfers the heat to the outer ceramic regenerator. The physical property of the high specific heat capacity of the ceramic can store more heat. And because the thermal conductivity coefficient of the rhenium metal is higher than that of the ceramic, the heat will be preferentially conducted to other parts of the metal, making the temperature of the heat-absorbing surface of the ceramic more uniform, eliminating heat stress concentration, and preventing the ceramic from breaking due to local high temperature.

[0051] In addition, in order to reduce the heat radiation loss to the outside world, the present invention cancels the conventional concentrating cavity and designs the nozzle extending to the other side externally as an integrated light-receiving and injection nozzle. The focused light spot directly irradiates inward from the outlet of the integrated light-receiving and injection nozzle. The advantage of this design is that it reduces the envelope size of the concentrating injection integrated regenerative propulsion device, combines the spaces occupied by the two functional areas, and has the smallest surface area under the same solid mass, that is, the smallest area for radiating heat to the outside world. The design of the slit enables the propellant to form a wrapped fluid heat-insulating layer in the slit between the ceramic regenerator and the outer shell head housing and the outer shell body housing, and regeneratively utilizes part of the dissipated heat.

[0052] In accordance with the above technical scheme, 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 changes made on the basis of the technical scheme of this application fall within the protection scope of the present invention.

[0053] Example:

[0054] This embodiment provides a focused jet integrated thermal storage propulsion device, including a shell head shell 1 and a shell body shell 2. Figure 1 , Figure 2 , Figure 5 and Figure 6 As shown, a ceramic heat storage body 3 is installed in the cavity surrounded 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, and a heat storage body head annular interface 301 is coaxially arranged on one end face of the ceramic heat storage body 3 and is connected to the slit 4.

[0055] like Figure 1 , Figure 2 , Figure 5 and Figure 6 As shown, a ceramic-metal intersecting cone cavity 303 is coaxially opened on the other end surface of the ceramic heat storage body 3, and a high-temperature resistant metal light-receiving nozzle 8 is installed in the ceramic-metal intersecting cone cavity 303.

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

[0057] like Figures 1 to 4 As shown, the focusing injection channel 5 includes a convergent channel 501 and an expansion channel 502 which are coaxially connected. A throat 503 is formed at the intersection of the convergent channel 501 and the expansion channel 502. The length of the convergent channel 501 is less than that of the expansion channel 502.

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

[0059] like Figure 1 , Figure 2 , Figure 7 and Figure 8 As shown, the other end surface of the bottom wall of the outer shell body 2 is also provided with a focusing injection port 9 , which is coaxially arranged with the groove 202 at the bottom end of the outer shell body, so that the focusing injection port 9 is connected with the expansion channel 502 .

[0060] As Figure 1 , Figure 2 , Figure 5 and Figure 6 shown, a main pipe 304 with one end closed and one end open is further provided in the ceramic regenerator 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 communicated with the converging channel 501. A plurality of secondary pipes 305 are further provided in the ceramic regenerator 3 around the main pipe 304. One end of the secondary pipe 305 is communicated with 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 regenerator 3 and is communicated with the slit 4.

[0061] Further in this embodiment, the throat area at the throat 503 is calculated by the following formula:

[0062]

[0063] In the formula

[0064] q m represents the flow value passing through the throat, and the unit is kg / s.

[0065] represents the total pressure of the thrust chamber, and the unit is Pa.

[0066] A t represents the throat area, and the unit is m 2 .

[0067] represents the gas constant, and the unit is J / kg·K.

[0068] represents the total temperature of the thrust chamber, and the unit is K.

[0069] Г is an intermediate quantity.

[0070] k represents the specific heat ratio.

[0071] Further in this embodiment, the cone 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.

[0072] Further in this embodiment, the ceramic regenerator 3 is made of a molten aluminum oxide material, and the high-temperature resistant metal light-receiving nozzle 8 is made of rhenium metal.

[0073] Further in this embodiment, the wall thickness of the high-temperature resistant metal light-receiving nozzle 8 is 10 mm; the length of the tail of the diverging channel 502 extending out of the ceramic regenerator 3 is 4 mm.

[0074] As Figure 1 , Figure 2, Figure 5 and Figure 6 As shown in Figure 5 and Figure 6 , a plurality of interface ventilation round holes 302 are circumferentially and equidistantly opened on the side wall at one end of the heat storage body head annular interface 301, and the interface ventilation round holes 302 communicate with the slit 4.

[0075] As Figure 1 , Figure 2 , Figure 9 and Figure 10 As shown in Figure 1 , Figure 2 , Figure 9 and Figure 10 , a cylindrical propellant inlet 101 is integrally formed at the central position of the outer shell head housing 1. One end of the propellant inlet 101 extends outside the outer shell head housing 1, and the other end of the propellant inlet 101 extends into the heat storage body head annular interface 301.

[0076] As Figure 1 , Figure 2 , Figure 9 and Figure 10 As shown in Figure 1 , Figure 2 , Figure 9 and Figure 10 , an inner groove 102 and an outer groove 103 of the outer shell head are coaxially opened on the inner end face of the outer shell head housing 1. The inner groove 102 and the outer groove 103 of the outer shell head are arranged in sequence from inside to outside with the propellant inlet 101 as the center. The inner groove 102 of the outer shell head and the other end of the heat storage body head annular interface 301 are nested and fixed to form a slit 4 between the ceramic heat storage body 3, the outer shell head housing 1 and the outer shell body housing 2.

[0077] As Figure 1 and Figure 2 As shown in Figure 1 and Figure 2 , the outer shell body housing 2 is nested and fixed with the outer groove 103 of the outer shell head through the outer shell body annular interface 201.

[0078] In this embodiment, further, the diameter of the slit 4 is 2 mm; the diameter of the interface ventilation round hole 302 is 1 mm.

[0079] As Figure 2 As shown in Figure 2 , the outer shell head housing 1 and the outer shell body housing 2 are also tightly connected by the cooperation of bolts 6 and nuts 7.

[0080] In this embodiment, further, a high-temperature resistant gasket is provided between the outer shell body annular interface 201 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; a high-temperature resistant gasket is also provided at the position where the bolts 6 and nuts 7 are used in cooperation between the outer shell head housing 1 and the outer shell body housing 2.

[0081] In this embodiment, further, the ceramic heat storage body 3 can be made by 3D printing technology.

[0082] Specifically, in this embodiment, the spot after concentrating light on the right side of the integrated concentrating and jetting heat storage propulsion device irradiates into the high-temperature resistant metal light-receiving nozzle 8. The heat provided by the spot is quickly conducted by the high-temperature resistant metal light-receiving nozzle 8 to the ceramic heat storage body 3. The slit 4 between the ceramic heat storage body 3, the outer shell head shell 1 and the outer shell body shell 2 is not filled with working medium during the heating process, and the slit 4 is in a vacuum state, reducing the energy dissipation to the outside during the heating process. The temperature of the ceramic heat storage body 3 gradually rises and stops changing when the energy input and heat dissipation reach equilibrium. At this time, hydrogen is introduced through the propellant inlet 101. The hydrogen will flow into the slit 4 between the ceramic heat storage body 3, the outer shell head shell 1 and the outer shell body shell 2 through the interface ventilation round hole 302 on the heat storage body head annular interface 301 on the ceramic heat storage body 3. The hydrogen in the slit 4 absorbs part of the heat radiated by the ceramic heat storage body 3 to the outside for preheating and then enters the main pipeline 304 and the secondary pipeline 305 to conduct more sufficient convective heat exchange with the ceramic heat storage body 3. After absorbing heat and increasing in temperature in the main pipeline 304 and the secondary pipeline 305, the hydrogen passes through the convergent channel 501, the throat 503 and the divergent channel 502, and is ejected from the concentrating and jetting port 9 through the convergent-divergent of the concentrating and jetting channel 5 to generate thrust.

[0083] Furthermore, in this embodiment, the simulation model proposed in this embodiment is constructed and the material properties are set. When the ceramic heat storage body 3 is heated to above 1800K, 0.1 g / s of hydrogen is introduced through the propellant inlet 101. After being heated and ejected, a thrust of more than 0.6 N can be generated, which can meet the requirements of the slow orbit change of the space flight device. The equivalent vacuum specific impulse of the device reaches 6000 m / s, that is, the specific impulse exceeds 600 s, far exceeding the specific impulse of about 300 s of conventional chemical propellants, and more work can be done under the same propellant flow rate. Similarly, after the concentrating light heating is completed, the light source input is turned off to simulate the satellite entering the Earth's backlit orbit. The results show that after the 2-kg ceramic heat storage body 3 completes heat storage and enters the backlit surface, it can still provide a thrust of the order of N for the propulsion device for more than 1 minute.

Claims

1. A focused jet integrated heat storage propulsion device, comprising an outer shell head shell (1) and an outer shell body shell (2), a ceramic heat storage body (3) is installed in a cavity surrounded 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), and a heat storage body head annular interface (301) is coaxially provided on one end surface of the ceramic heat storage body (3) and is connected to the slit (4), characterized in that: The other end surface of the ceramic heat storage body (3) is coaxially provided with a ceramic-metal intersecting frustum cavity (303), and a high-temperature resistant metal light-receiving nozzle (8) is installed in the ceramic-metal intersecting frustum cavity (303); The high temperature resistant metal light receiving nozzle (8) is coaxially provided with a through light focusing injection channel (5); The light-focusing injection channel (5) comprises a convergent channel (501) and an expansion channel (502) which are coaxially connected, a throat (503) is formed at the intersection of the convergent channel (501) and the expansion channel (502), and the length of the convergent channel (501) is shorter than the length of the expansion channel (502); The bottom wall of the outer shell body shell (2) is provided with an outer shell body bottom end groove (202), the outer shell body bottom end groove (202) is coaxially arranged with the high temperature resistant metal light receiving nozzle (8), and the tail of the high temperature resistant metal light receiving nozzle (8) extending out of the ceramic heat storage body (3) is embedded in the outer shell body bottom end groove (202); The other end surface of the bottom wall of the outer shell body shell (2) is also provided with a focusing injection port (9), and the focusing injection port (9) is coaxially arranged with the groove (202) at the bottom end of the outer shell body, so that the focusing injection port (9) is connected with the expansion channel (502); The ceramic heat storage body (3) is also provided with a main pipe (304) with one end closed and the other end open. 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). A plurality of secondary pipes (305) are also provided around the main pipe (304) in the ceramic heat storage body (3). 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).

2. The integrated thermal storage propulsion device for focusing and jetting according to claim 1, characterized in that: 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 8:

1.

3. The integrated thermal storage propulsion device for focusing and jetting according to claim 1, characterized in that: 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.

4. The integrated light-concentrating jet heat storage propulsion device according to claim 1, characterized in that: The wall thickness of the high temperature resistant metal light receiving nozzle (8) is 10 mm.

5. The integrated thermal storage propulsion device for focusing and jetting according to claim 1, characterized in that: The length of the tail of the expansion channel (502) extending outside the ceramic heat storage body (3) is 4 mm.

6. The integrated thermal storage propulsion device for focusing and jetting according to claim 1, characterized in that: A plurality of interface ventilation circular holes (302) are equidistantly arranged on the side wall of one end of the annular interface (301) at the head of the heat storage body, and the interface ventilation circular holes (302) are connected to the slit (4).

7. The integrated thermal storage propulsion device for focusing and jetting according to claim 1, characterized in that: A cylindrical propellant air inlet (101) is integrally formed at the center of the shell head shell (1), one end of the propellant air inlet (101) extends out of the shell head shell (1), and the other end of the propellant air inlet (101) extends into the annular interface (301) of the heat storage body head; An inner groove (102) and an outer groove (103) of the shell head are coaxially formed on the inner end surface of the shell head shell (1); the inner groove (102) and the outer groove (103) of the shell head are arranged in sequence from the inside to the outside with the propellant air inlet (101) as the center; the inner groove (102) of the shell head and the other end of the annular interface (301) of the heat storage body head are nested and fixed to form a slit (4) between the ceramic heat storage body (3) and the shell head shell (1) and the shell body shell (2); The shell body shell (2) is nested and fixed with the outer groove (103) of the shell head through the shell body annular interface (201).

8. The integrated thermal storage propulsion device for focusing and jetting according to claim 1, characterized in that: The diameter of the slit (4) is 2 mm; the diameter of the interface ventilation circular hole (302) is 1 mm.

9. The integrated thermal storage propulsion device for focusing and jetting according to claim 1, characterized in that: The shell head shell (1) and the shell body shell (2) are also fastened together by the coordinated use of bolts (6) and nuts (7).

10. The integrated light-concentrating jet heat storage propulsion device according to claim 1, 7 or 9, characterized in that: A high temperature resistant gasket is provided between the annular interface (201) of the shell body and the inner groove (102) of the shell head; A high temperature resistant gasket is arranged between the expansion channel (502) and the groove (202) at the bottom end of the outer shell body; A high temperature resistant gasket is also provided at the position where the bolt (6) and the nut (7) are used in cooperation between the shell head shell (1) and the shell body shell (2).

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