Gas propelling device

Abstract

The utility model relates to the technical field of space propulsion, in particular to a gas propulsion device. The gas propulsion device comprises a shell, a partition plate, a control assembly, a first channel, a thruster and a grid body. A filling port and a mounting assembly are arranged on one side of the shell, an outlet is formed in the other side of the shell, and an inner cavity is defined by the shell and used for storing liquid gas; the spacing plate is arranged on the inner wall of the shell and divides the inner cavity into a first cavity close to the filling port and a second cavity close to the outlet, and small through holes are fully distributed in the spacing plate; the control assembly is arranged on the mounting assembly and communicates with the first cavity, and liquid gas in the shell is gasified and then decompressed to preset pressure through the control assembly; the first channel is communicated with the control assembly and the outlet, and gas-liquid mixed fluid decompressed by the control assembly flows through the first channel. According to the highly-integrated gas propelling device, gas-liquid separation can be better achieved in a weightless environment, liquid gas is fully subjected to phase change, and the gas utilization efficiency and specific impulse of the device are improved.

Description

Technical Field

[0001] The embodiments of the present application relate to the field of space propulsion technology, and particularly to a gas propulsion device. Background Art

[0002] Space propulsion technology is a technology that converts energy such as chemical energy and electrical energy into the jet kinetic energy of propellants, and plays an important role in manned spaceflight, artificial satellites, launch vehicles, deep space probes, defense systems, etc. Space propulsion technology ensures the reliable implementation of manned spaceflight projects, enables artificial satellites to stay in orbit for a long time, ensures that launch vehicles accurately enter orbit, helps detectors navigate interstellar space, and enhances the high-efficiency maneuverability of defense systems.

[0003] Gas propulsion uses nitrogen, helium, etc. as working fluids to generate thrust by releasing the gas in the storage tank. Gas propulsion technology is mainly divided into two types: compressed gas propulsion and phase change gas propulsion. It has the advantages of simple structure, high reliability, small volume and flexible layout, and can be applied to space missions such as space attitude control and orbit adjustment of small satellites and cube satellites. Phase change gases usually have a higher specific impulse because the energy released during the phase change of the gas can increase the specific impulse and thrust; compared with compressed gas propulsion, phase change gas propulsion can utilize the energy of the propellant more effectively.

[0004] Due to its lightweight and low-cost characteristics, the gas propulsion system has become the preferred propulsion method for small satellites to adjust their orbits and attitudes. Due to the limited mass, volume, and power of small satellites, their wide application has put forward higher requirements for space power. A space power device with small thrust, high specific impulse, light weight, and small volume can better meet the power requirements of small satellites. Compared with traditional chemical propulsion and electric propulsion, the gas propulsion system has low cost, simple structure, and high safety. Although its specific impulse is lower than that of electric propulsion, it performs particularly well in precise control and is currently widely used in the orbit control tasks of small satellites. Satellites such as Tiandu-2, Magic Cube-2, and Yunyao-1 have all adopted gas propulsion technology as the orbit-changing power of the satellites. With the expansion of the satellite constellation market scale and the progress of technology, the application scope of gas propulsion technology will be further expanded, providing more possibilities for future space missions.

[0005] In the existing phase change gas propulsion device, gas-liquid mixing occurs in a weightless environment, resulting in insufficient phase change of the liquid gas, and thus low gas utilization efficiency and low specific impulse of the gas propulsion device. Summary of the Utility Model

[0006] The purpose of the embodiments of the present application is to provide a gas propulsion device that can better achieve gas-liquid separation in a weightless environment, enable the liquid gas to fully undergo phase change, and improve the gas utilization efficiency and specific impulse of the device.

[0007] In order to solve the above technical problems, the embodiment of the present application provides a gas propulsion device, which includes a shell, a partition plate, a control component, a first channel, a thruster and a grid body. A filling port and a mounting component are provided on one side of the shell, and an outlet is provided on the other side. The shell encloses an inner cavity and is used to store liquid gas; the partition plate is provided on the inner wall of the shell, and the inner cavity is divided into a first cavity near the filling port and a second cavity near the outlet, and the partition plate is covered with small holes that penetrate through; the control component is provided on the mounting component and is connected to the first cavity, and the liquid gas in the shell is gasified and decompressed to a predetermined pressure through the control component; the first channel connects the control component with the outlet, and the gas-liquid mixed fluid after the control component is decompressed flows through the first channel and is completely gasified after heating and flows out from the outlet; the thruster is installed at the outlet, and the completely gasified gas is ejected from the thruster to provide a driving force for the gas propulsion device; the grid body is provided in the second cavity, and is formed by a plurality of connecting rods crisscrossed and connected, and is used to absorb liquid and store gas in the first cavity, so that the gas and liquid in the shell are separated.

[0008] The embodiment of the present application provides a gas propulsion device, which is provided with a shell, a control component, a first channel and a thruster. After the liquid gas in the shell is gasified, it is decompressed through the control component. After the gasification and decompression, the gas-liquid mixed fluid flows through the first channel and is completely gasified and flows out from the thruster at the outlet, providing power to the propulsion device. By providing a partition plate covered with small holes, the inner cavity of the shell is divided into a first cavity near the filling port and a second cavity near the outlet. The first cavity is connected to the control component, and the second cavity is provided with a grid body formed by a plurality of connecting rods connected in a criss-cross manner. Since a large number of connecting rods are connected to each other in the grid body, each connection forms an inner angle. Due to the surface tension of the liquid gas, the liquid is easily stored at these inner angles, and the gas will overflow, so that the gas and liquid are separated. By providing a first channel to connect the control component and the outlet, and heating the fluid in the first channel, the gas-liquid mixed fluid after the control component is decompressed is completely gasified after the first channel. The propulsion device provided in this embodiment separates gas and liquid through a grid body, and the first channel completely vaporizes the liquid, thereby enabling better gas-liquid separation in a weightless environment, allowing the liquid gas to fully undergo a phase change, and improving the gas utilization efficiency and specific impulse of the device.

[0009] In some embodiments, both ends of all the connecting rods are fixed on the inner wall of the second cavity; or, both ends of a part of the connecting rods are fixed on the inner wall of the second cavity, and the other part of the connecting rods are arranged around the cavity wall of the inner cavity.

[0010] In some embodiments, the spacer is funnel-shaped.

[0011] In some embodiments, the mounting assembly includes a first mounting hole and a second mounting hole that communicate with each other. The control assembly includes a solenoid valve and a pressure reducing valve. The solenoid valve is disposed in the first mounting hole, and the pressure reducing valve is disposed in the second mounting hole.

[0012] In some embodiments, the housing is further provided with multiple sections of second channels. The multiple sections of second channels sequentially introduce the vaporized liquid gas from the first cavity into the solenoid valve and the pressure reducing valve, and then flow out from the first channel.

[0013] In some embodiments, the first channel is disposed to surround the inner wall of the housing. One end of the first channel communicates with the pressure reducing valve, and the other end communicates with the outlet.

[0014] In some embodiments, the housing is further provided with a cleaning hole, and a plug is installed in the cleaning hole.

[0015] In some embodiments, a filling valve is provided at the filling port.

[0016] In some embodiments, there are three or four outlets, and a thruster is installed at each outlet.

[0017] In some embodiments, the housing, the spacer, the first channel, and the grid body are integrally formed. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] One or more embodiments are illustrated by way of example in the accompanying drawings, which do not constitute a limitation on the embodiments. Elements with the same reference numerals in the drawings are represented as similar elements, unless otherwise stated, and the drawings in the figures do not constitute a scale limitation.

[0019] Figure 1 is a three-dimensional structural schematic diagram of the housing in the top view direction of the gas propulsion device provided by some embodiments of the present application;

[0020] Figure 2 is a three-dimensional structural schematic diagram of the housing in the bottom view direction of the gas propulsion device provided by some embodiments of the present application;

[0021] Figure 3 is a three-dimensional structural schematic diagram of the gas propulsion device in the top view direction provided by some embodiments of the present application;

[0022] Figure 4 is a three-dimensional structural schematic diagram of the gas propulsion device in the bottom view direction provided by some embodiments of the present application;

[0023] Figure 5 is a top view of the gas propulsion device provided by some embodiments of the present application;

[0024] Figure 6 is the gas propulsion device provided by some embodiments of the present application Figure 5Schematic cross-sectional structure diagram at A-A' in [the figure];

[0025] Figure 7 It is a gas propulsion device provided by some embodiments of the present application Figure 5 Schematic cross-sectional structure diagram at B-B' in [the figure];

[0026] Figure 8 It is a gas propulsion device provided by some embodiments of the present application Figure 6 Partial enlarged view at C in [the figure];

[0027] Figure 9 It is a schematic diagram of the principle of the gas propulsion device provided by some embodiments of the present application.

[0028] Explanation of reference numerals: 11 - housing; 111 - filling port; 112 - mounting assembly; 1121 - first mounting hole; 1122 - second mounting hole; 113 - outlet; 114 - inner cavity; 1141 - first cavity; 1142 - second cavity; 115 - second channel; 116 - cleaning hole; 12 - spacer; 121 - small hole; 13 - control assembly; 131 - solenoid valve; 132 - pressure reducing valve; 14 - first channel; 15 - thruster; 16 - grid body; 161 - connecting rod; 17 - plug; 18 - filling valve. Detailed implementation manners

[0029] To make the objectives, technical solutions, and advantages of the embodiments of the present application clearer, the following will elaborate on each implementation manner of the present application in conjunction with the accompanying drawings. However, those of ordinary skill in the art can understand that in each implementation manner of the present application, many technical details are provided for readers to better understand the present application. However, even without these technical details and various changes and modifications based on the following implementation manners, the technical solutions claimed in the present application can still be achieved. The following division of each embodiment is for convenience of description and should not constitute any limitation to the specific implementation manner of the present application. Each embodiment can be combined and cross-referenced with each other on the premise of no contradiction.

[0030] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by those skilled in the technical field to which this application belongs; the terms used herein are only for the purpose of describing specific embodiments and are not intended to limit this application; the terms "including" and "having" and any variations thereof in the specification and claims of this application and the above accompanying drawing descriptions are intended to cover non-exclusive inclusion.

[0031] In the description of the embodiments of the present application, technical terms such as "first" and "second" are only used to distinguish different objects, and cannot be understood as indicating or implying relative importance or implicitly specifying the quantity, specific order or primary-secondary relationship of the indicated technical features. In the description of the embodiments of the present application, the meaning of "a plurality" is more than two, unless otherwise specifically defined.

[0032] In the description of the embodiments of the present application, unless otherwise clearly specified and limited, technical terms such as "install", "connect", and "couple" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or integrated; it can also be a mechanical connection or an electrical connection; it can be directly connected, or indirectly connected through an intermediate medium, and can be the communication inside two elements or the interaction relationship between two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the embodiments of the present application can be understood according to specific situations.

[0033] Space propulsion technology is a technology that converts energy such as chemical energy and electrical energy into the jet kinetic energy of propellants, and plays an important role in aspects such as manned spaceflight, artificial satellites, launch vehicles, deep space detectors, and defense systems. Space propulsion ensures the reliable implementation of the manned spaceflight project, enables artificial satellites to stay in orbit for a long time, ensures the accurate orbital injection of launch vehicles, helps detectors to navigate interstellar space, and enhances the high-efficiency maneuverability of defense systems.

[0034] Gas propulsion uses nitrogen, helium, etc. as working fluids to generate thrust by releasing the gas in the storage tank. Gas propulsion technology is mainly divided into two types: compressed gas propulsion and phase change gas propulsion. It has the advantages of simple structure, high reliability, small volume and flexible layout, and can be applied to space missions such as space attitude control and orbit adjustment of small satellites and cube satellites. Phase change gases usually have a higher specific impulse because the energy released during the phase change of the gas can increase the specific impulse and thrust; compared with compressed gas propulsion, phase change gas propulsion can use the energy of the propellant more effectively.

[0035] Gas propulsion systems have become the preferred propulsion method for microsatellites to adjust their orbits and control their attitudes due to their light weight and low cost. Due to their limited mass, volume, and power, the widespread use of microsatellites places higher demands on space power. Space power devices with low thrust, high specific impulse, light mass, and small volume can better match the power needs of microsatellites. Compared with traditional chemical propulsion and electric propulsion, gas propulsion systems have low cost, simple structure, and high safety. Although their specific impulse is lower than that of electric propulsion, they are particularly outstanding in terms of precise control. Currently, they are widely used in orbit control missions for microsatellites. Satellites such as Tiandu-2, Magic Cube-2, and Yunyao-1 all use gas propulsion technology as the power for satellite orbit changes. With the expansion of the satellite constellation market and technological advancement, the application scope of gas propulsion technology will be further expanded, providing more possibilities for future space missions.

[0036] In existing phase-change gas propulsion devices, gas and liquid mix in a weightless environment, resulting in the inability of the liquid gas to fully undergo a phase change, resulting in low gas utilization efficiency and low specific impulse of the gas propulsion device.

[0037] Therefore, in order to enable the gas propulsion device to better achieve gas-liquid separation in a weightless environment, the liquid gas is fully phase-changed to improve the gas utilization efficiency and specific impulse of the device. Some embodiments of the present application provide a gas propulsion device, by setting a shell, a control component, a first channel and a thruster, the liquid gas in the shell is gasified and then decompressed through the control component, the gas-liquid mixed fluid after gasification and decompression flows through the first channel and is completely gasified and flows out from the thruster at the outlet, providing power to the propulsion device. By setting a partition plate covered with small holes, the inner cavity of the shell is divided into a first cavity near the filling port and a second cavity near the outlet, the first cavity is connected to the control component, and the second cavity is provided with a grid body formed by a plurality of connecting rods connected in a criss-cross manner. Due to the large number of connecting rods connected to each other in the grid body, each connection forms an inner angle. Due to the surface tension of the liquid gas, the liquid is easily stored at these inner angles, and the gas will overflow, so that the gas-liquid separation. By setting the first channel to connect the control component and the outlet, and heating the fluid in the first channel, the gas-liquid mixed fluid after the control component is decompressed is completely gasified after the first channel. The propulsion device provided in this embodiment separates gas and liquid through a grid body, and the first channel completely vaporizes the liquid, thereby enabling better gas-liquid separation in a weightless environment, allowing the liquid gas to fully undergo a phase change, and improving the gas utilization efficiency and specific impulse of the device.

[0038] Combine the following Figures 1 to 9 A gas propulsion device provided in some embodiments of the present application is described.

[0039] like Figures 1 to 4 as well as Figure 6As shown, a gas propulsion device provided by some embodiments of the present application includes a shell 11, a partition plate 12, a control component 13, a first channel 14, a thruster 15 and a grid body 16. A filling port 111 and a mounting component 112 are provided on one side of the shell 11, and an outlet 113 is provided on the other side. The shell 11 encloses an inner cavity 114 and is used to store liquid gas; the partition plate 12 is provided on the inner wall of the shell 11, and divides the inner cavity 114 into a first cavity 1141 close to the filling port 111 and a second cavity 1142 close to the outlet 113. The partition plate 12 is covered with small holes 121 that penetrate through it; the control component 13 is provided on the mounting component 112, and is connected to the first cavity 1141. After the liquid gas in the shell 11 is gasified, it is decompressed to A predetermined pressure is provided; the first channel 14 connects the control component 13 with the outlet 113, and the gas-liquid mixed fluid after the pressure reduction of the control component 13 flows through the first channel 14 and is completely vaporized after being heated and flows out from the outlet 113; the thruster 15 is installed at the outlet 113, and the completely vaporized gas is ejected from the thruster 15 to provide a driving force for the gas propulsion device; the grid body 16 is arranged in the second cavity 1142, and is formed by a plurality of connecting rods 161 criss-crossed and connected, and is used to absorb the liquid and store the gas in the first cavity 1141, so that the gas and liquid in the shell 11 are separated.

[0040] It should be noted that if Figures 1 - 4As shown, the shell 11 is an irregularly shaped shell formed in one piece, the upper half can be cylindrical or other shapes, the upper end surface can be arc-shaped, the upper end surface is provided with a mounting assembly 112 and a filling port 111, and the lower end surface is provided with an outlet 113. The shell 11 can be made of titanium alloy or other metal materials. The inner cavity 114 surrounded by the shell 11 is divided into a first cavity 1141 near the filling port 111 and a second cavity 1142 near the outlet 113 by a partition plate 12. The partition plate 12 is covered with small holes 121 that penetrate to facilitate the flow of liquid in the inner cavity 114. The control assembly 13 can be arranged on the mounting assembly 112 by plug-in. The control assembly 13 can be a valve assembly composed of a combination valve, which has the functions of decompression and switching. The control assembly 13 is connected to the first cavity 1141. The initial liquid gas in the first cavity 1141 is heated by an external thermal control platform to reach the initial working temperature and partially gasify. After gasification, the gas is decompressed to a predetermined pressure through the control component 13 and flows from the first channel 14 to the outlet 113. Before the device works, the liquid in the shell 11 is heated to a preset temperature. The shell 11 is made of high-strength material to meet the safe storage of liquid at high temperature and pressure. The first channel 14 is arranged on the inner wall of the shell 11, and the outer wall of the first channel 14 is in contact with the liquid in the shell 11. The small amount of liquid in the first channel 14 that may not be completely gasified is heated to be completely gasified and flows out from the outlet 113; the thruster 15 can be an existing small thrust device, which is installed at the outlet 113 by plug-in. The gas that is completely gasified and has a certain pressure is ejected from the thruster 15 to provide a driving force for the device; the entire second cavity 1142 is filled with a grid body 16, and a large number of connecting rods 161 are crisscrossed and connected to form, similar to the full-house scaffolding on the construction site, and the connection of the connecting rods 161 forms an inner angle of a certain angle, and a large number of inner angles become places for liquid adsorption. Since liquid has surface tension, it is easy to be adsorbed on the surface of an object. The inner corner is the intersection of multiple surfaces and can be used to adsorb and store liquid. The more connecting rods 161 there are in the grid body 16, the denser the connection points, and the more inner corners there are, the stronger the liquid adsorption capacity is, and the more conducive to the separation of gas and liquid in the shell 11.

[0041] The liquid gas can be ammonia, nitrogen, helium, argon or krypton. If it is ammonia, its storage temperature is: -20°C - 40°C, the working temperature is 20°C - 40°C, not exceeding 50°C at the highest, and the maximum pressure is 2 MPa. Before the device is launched, liquid is filled through the filling port 111. During orbit, the grid body 16 adsorbs the liquid in the gas-liquid mixture in the weightless state into the second cavity 1142, and the gas is located in the first cavity 1141 and flows towards the outlet 113. During the non-working period of the device, the gas is sealed in the housing 11 through the control component 13. After the partially vaporized gas in the housing 11 flows to the control component 13, the pressure in the housing 11 decreases. When it is lower than the saturated vapor pressure value at the current temperature, the liquid further vaporizes, and the heat of vaporization comes from the heat released by the cooling of the liquid in the storage tank. Since boiling occurs when the liquid gas vaporizes and evaporates during the operation of the propulsion device, a small amount of liquid (this phenomenon will gradually disappear as the liquid in the housing 11 decreases) will flow from the outlet 113 to the control component 13. The small amount of liquid after pressure reduction enters the first channel 14 and is vaporized by heat exchange, thereby increasing the specific impulse.

[0042] A gas propulsion device provided by an embodiment of the present application, by setting the housing 11, the control component 13, the first channel 14 and the thruster 15, the liquid gas in the housing 11 is vaporized and then passes through the control component 13 and is depressurized. The gas-liquid mixed fluid after vaporization and depressurization (subsequently, as the liquid in the housing 11 decreases, it is completely gas later) flows through the first channel 14 and is completely vaporized after heating and flows out from the thruster 15 at the outlet 113, providing power for the propulsion device. By setting the spacer 12 with small holes 121, the inner cavity 114 of the housing 11 is divided into a first cavity 1141 close to the filling port 111 and a second cavity 1142 close to the outlet 113. The first cavity 1141 is connected to the control component 13, and the second cavity 1142 is provided with a grid body 16 formed by a plurality of connecting rods 161 connected in a crisscross manner. Due to the numerous connecting rods 161 in the grid body 16 being connected to each other, an inner angle is formed at each connection. Due to the surface tension of the liquid gas, the liquid is easily stored at these inner angles, and the gas will overflow, resulting in gas-liquid separation. By setting the first channel 14 to connect the control component 13 and the outlet 113 and heating the fluid in the first channel 14, the gas-liquid mixed fluid after depressurization by the control component 13 is completely vaporized after passing through the first channel 14. The propulsion device provided by this embodiment separates gas and liquid through the grid body 16, and the first channel 14 completely vaporizes the liquid, so as to better achieve gas-liquid separation in a weightless environment, enable the liquid gas to fully undergo a phase change, and improve the gas utilization efficiency and specific impulse of the device.

[0043] In some embodiments of the present application, both ends of all the connecting rods 161 are fixed on the inner wall of the second cavity 1142; alternatively, both ends of a part of the connecting rods 161 are fixed on the inner wall of the second cavity 1142, and the other part of the connecting rods 161 is arranged around the cavity wall of the inner cavity 114.

[0044] It should be noted that, as Figure 6 and Figure 8 shown, a large number of connecting rods 161 are connected in a criss-cross manner to form a grid body 16 that fills the entire second cavity 1142. The connecting rods 161 can be divided into two categories. The first category of connecting rods 161 is directly connected to the inner wall of the second cavity 1142, and the second category of connecting rods 161 is arranged around the cavity wall of the inner cavity 114. The second category of connecting rods 161 is connected to the first category in an interlaced manner, and the first category of connecting rods 161 can also be connected to each other in an interlaced manner. The connecting rods 161 can be square rods, cylindrical rods, or other suitable shapes. The arrangement of the connecting rods 161 needs to be determined according to the shape of the housing 11, the shape and position of the spacer 12. The grid body 16 can be composed of the first category of connecting rods 161 alone, or formed by the interlaced connection of the first category of connecting rods 161 and the second category of connecting rods 161.

[0045] In some embodiments of the present application, the spacer 12 is funnel-shaped.

[0046] It should be noted that the spacer 12 can be parallel to the cross-section of the housing 11, or in the shape of a funnel formed from the upper end to the lower end of the housing 11. The upper cavity of the funnel forms the first cavity 1141 with the housing 11, and the outer wall of the funnel forms the second cavity 1142 with the housing 11. The funnel-shaped spacer 12, on the one hand, connects the upper and lower parts of the housing 11 integrally to play an internal support role, and on the other hand, is convenient for three-dimensional printing of the overall housing 11. In addition, the area of the funnel-shaped spacer 12 is relatively large, which is convenient for liquid to be stored and aggregated from top to bottom.

[0047] In some embodiments of the present application, the mounting assembly 112 includes a first mounting hole 1121 and a second mounting hole 1122 that communicate with each other. The control assembly 13 includes a solenoid valve 131 and a pressure reducing valve 132. The solenoid valve 131 is arranged in the first mounting hole 1121, and the pressure reducing valve 132 is arranged in the second mounting hole 1122.

[0048] It should be noted that both the solenoid valve 131 and the pressure reducing valve 132 are existing devices. The liquid gas flows from the first cavity to the solenoid valve 131, then to the pressure reducing valve 132, and after being decompressed and vaporized in the pressure reducing valve 132, it flows to the first channel 14. During operation, the solenoid valve 131 is opened through the master control platform and serves as the on-off valve of the device. The pressure reducing valve 132 reduces the high-pressure vaporized gas to low-pressure gas, playing a role in throttling and stabilizing the pressure, and finally sprays out from the outlet 113 to generate a driving force. The solenoid valve 131 and the pressure reducing valve 132 are hermetically installed on the mounting assembly 112 in a cartridge structure, which is convenient for replacement.

[0049] In some embodiments of the present application, the housing 11 is further provided with multiple sections of second channels 115. The multiple sections of second channels 115 sequentially introduce the vaporized liquid gas from the first cavity 1141 into the solenoid valve 131 and the pressure reducing valve 132, and then flow out from the first channel 14.

[0050] As Figure 6 shown, the multiple sections of second channels 115 are arranged in the mounting assembly 112 and mainly include three sections: the first section is the communication channel from the first cavity 1141 to the first mounting hole 1121, the second section is the communication channel from the first mounting hole 1121 to the second mounting hole 1122, and the third section is the communication channel from the second mounting hole 1122 to the first channel 14.

[0051] In some embodiments of the present application, the first channel 14 is arranged to surround the inner wall of the housing 11. One end of the first channel 14 is connected to the pressure reducing valve 132, and the other end is connected to the outlet 113.

[0052] As Figure 6 and Figure 7 shown, the first channel 14 starts from the second channel 115 between the pressure reducing valve 132 and the inner cavity 114 of the housing 11, and then surrounds the inner wall of the housing 11 for one or several circles before ending at the outlet 113. A heating sheet (not shown in the figure) is provided on the outer side wall of the housing 11 at the position of the first channel, and the heating sheet is generally overall responsible by the control system. The first channel 14 arranged in this way can be fully heated by the heating sheet outside the housing 11, so as to be completely vaporized. In order to show the arrangement of the first channel 14, Figure 7 the grid body 16 arranged in the second cavity 1142 is removed.

[0053] In some embodiments of the present application, the housing 11 is further provided with a cleaning hole 116, and a plug 17 is installed in the cleaning hole 116.

[0054] It should be noted that during the three-dimensional printing process of manufacturing the housing 11, powder will remain inside the housing 11, and debris will also be generated during the machining process. Therefore, cleaning is required. After cleaning, a cleanliness inspection test can be carried out. After passing the test, the plug 17 is installed and will not be disassembled subsequently. As Figures 1 - 4As shown, a cleaning hole 116 and a corresponding plug 17 can be provided respectively above and below the housing 11 for easy cleaning.

[0055] In some embodiments of the present application, a filling valve 18 is provided at the filling port 111.

[0056] It should be noted that providing the filling valve 18 at the filling port 111 facilitates injecting liquid gas into the housing 11. The filling valve 18 is a separate functional component and is hermetically installed in the filling port 111 by an insertion structure.

[0057] In some embodiments of the present application, there are three or four outlets 113 ( Figure 4 only one of which is shown in [ID=], and the specific number can be increased according to requirements), and a thruster 15 is installed at each outlet 113.

[0058] It should be noted that when there are three outlets 113, they can form an equilateral triangle, and when there are four outlets 113, they can form a regular quadrilateral. The three or four thrusters 15 can provide thrust in different directions, enabling the device to change direction. At this time, the first channel 14 needs to be divided into multiple branches and connected to the corresponding outlets 113.

[0059] In some embodiments of the present application, the housing 11, the spacer 12, the first channel 14, and the grid body 16 are integrally formed.

[0060] It should be noted that the overall structure of the housing 11, the spacer 12, the first channel 14, and the grid body 16 is a multi-channel box body formed integrally. There are multiple connected second channels 115 inside, which can be made by die casting or 3D printing. 3D printing is a preferred manufacturing method. Based on the designed 3D model file of the overall structure, using titanium alloy (TC4), the overall structure is constructed by layer-by-layer printing. Under the premise of meeting the propellant volume requirements, a rational design is carried out, arranging the installation positions of various valves in the optimal direction, adopting an insertion installation method, further reducing the complexity of the system. At the same time, the valve components are all independent functional parts, which not only reduces the process complexity but also improves the feasibility of mass production; the flow pipelines between the valves are arranged internally and are all formed in one piece by 3D printing, without the need for post-processing and installation, improving the later production efficiency. The overall structure envelope size is within 165 mm (millimeters) × 165 mm × 130 mm, and the overall weight is within 1.6 kilograms (the original weight was about 2 kilograms), greatly reducing the volume and weight of the gas supply system and improving the production efficiency. Each component is installed on the housing 11 using a sealing structure to prevent gas leakage. This highly integrated design reduces the volume and weight of the propulsion device, improves the compatibility of the high-pressure storage tank, and at the same time enables mass production and reduces costs.

[0061] Such asFigure 9 As shown, for the gas propulsion device provided by the embodiment of the present application, high-pressure liquefied gas is filled into the housing 11 through the filling valve 18. The housing 11 is preheated, and partial vaporization of the liquid occurs inside the housing 11. After a part of the vaporized gas flows to the solenoid valve 131, the pressure inside the housing 11 decreases. When it is lower than the saturated vapor pressure value at the current temperature, further vaporization of the liquid occurs. Since boiling will occur during the vaporization and evaporation of the liquid during the preheating of the housing 11, a small amount of liquid will flow from the outlet 113 to the solenoid valve 131 and the pressure regulating valve. The mixture of the decompressed gas and the small amount of liquid enters the first channel 14 and is heated. After the liquid is completely vaporized, it is ejected from the thruster 15 to generate thrust.

[0062] Those of ordinary skill in the art can understand that the above embodiments are specific embodiments for implementing the present application. In actual applications, various changes can be made to them in form and details without departing from the spirit and scope of the present application.

Claims

1. A gas propulsion device, characterized in that, include: A shell, one side of the shell is provided with a filling port and a mounting assembly, and the other side is provided with an outlet, and the shell encloses an inner cavity and is used to store liquid gas; A partition plate is arranged on the inner wall of the shell, dividing the inner cavity into a first cavity near the filling port and a second cavity near the outlet, and the partition plate is covered with small holes; A control assembly, which is arranged on the mounting assembly and communicated with the first cavity, and the liquid gas in the shell is decompressed to a predetermined pressure through the control assembly after being gasified; a first channel, connecting the control component with the outlet, wherein the gas-liquid mixed fluid after the pressure reduction of the control component flows through the first channel and is completely gasified after being heated and flows out from the outlet; A thruster is installed at the outlet, and the completely gasified gas is ejected from the thruster to provide a driving force for the gas propulsion device; The grid body is arranged in the second cavity and is formed by a plurality of connecting rods connected in a crisscross manner. The grid body is used to absorb liquid and store gas in the first cavity, so that the gas and liquid in the shell are separated.

2. The gas propulsion device according to claim 1, characterized in that, Both ends of all the connecting rods are fixed on the inner wall of the second cavity; or, Two ends of a portion of the connecting rods are fixed on the inner wall of the second cavity, and another portion of the connecting rods is arranged around the cavity wall of the inner cavity.

3. A gas propulsion device according to claim 1, characterized in that, The partition plate is funnel-shaped.

4. A gas propulsion device according to claim 1, characterized in that, The mounting assembly includes a first mounting hole and a second mounting hole that are interconnected. The control assembly includes a solenoid valve and a pressure reducing valve. The solenoid valve is arranged in the first mounting hole, and the pressure reducing valve is arranged in the second mounting hole.

5. A gas propulsion device according to claim 4, characterized in that, The shell is further provided with a plurality of second channels, which guide the gasified liquid gas from the first cavity into the solenoid valve and the pressure reducing valve in sequence and then flow out from the first channel.

6. A gas propulsion device according to claim 4, characterized in that, The first channel is disposed around the inner wall of the shell, one end of the first channel is connected to the pressure reducing valve, and the other end of the first channel is connected to the outlet.

7. A gas propulsion device according to claim 1, characterized in that, The shell is also provided with a cleaning hole, and a plug is installed in the cleaning hole.

8. A gas propulsion device according to claim 1, characterized in that, The filling port is provided with a filling valve.

9. A gas propulsion device according to claim 1, characterized in that, There are three or four outlets, and each outlet is equipped with the thruster.

10. A gas propulsion device according to claim 1, characterized in that, The shell, the partition plate, the first channel and the grid body are integrally formed.

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