High-integration-level liquid ammonia propelling system for satellites
Through the integrated design and internal heating liquid ammonia propulsion system, the problems of low heat transfer efficiency and poor stability of traditional liquid ammonia propulsion systems are solved, and lightweight and efficient propulsion is achieved, which is suitable for propulsion tasks of micro satellites.
Patent Information
- Application Number
- CN202422245902.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-09-13
- Publication Date
- 2025-07-29
- Estimated Expiration
- 2034-09-13
AI Technical Summary
Traditional liquid ammonia propulsion systems have problems such as low heat transfer efficiency, poor system stability, large volume and weight, and high installation complexity, which cannot meet the efficient propulsion needs of micro satellites.
It adopts an integrated design and internal heating method, and connects solenoid valves, pressure reducing valves, heaters and nozzles through plug-in structures, omitting complex pipelines, adopting a dual redundant solenoid valve design, and is equipped with pressure sensors to achieve internal heating and efficient heat transfer, and improve system stability.
It reduces the weight and volume of the system, facilitates mass production and installation, improves heat transfer efficiency, enhances the long-term stability of the system, and meets the propulsion needs of microsatellites.
Smart Images
Figure CN223161992U_ABST
Abstract
Description
Technical Field
[0001] The embodiments of the present application relate to the technical field of space propulsion, and particularly to a highly integrated liquid ammonia propulsion system for satellites. 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 is mainly applied to spacecraft orbital maneuvering position keeping, attitude control, and momentum wheel unloading, etc. Space propulsion technology plays an important role in manned spaceflight, artificial satellites, launch vehicles, deep space probes, defense systems, etc. Space propulsion ensures the reliable implementation of the manned spaceflight project, enables artificial satellites to stay in orbit for a long time, ensures that the launch vehicle accurately enters the orbit, helps the probe to navigate in the interstellar space, and space propulsion improves the high-efficiency maneuverability of the defense system.
[0003] In recent years, with the popularization of small satellites and cube satellites, the cold gas propulsion system has become the preferred propulsion method for these satellites to perform orbit adjustment and attitude control due to its lightweight and low-cost characteristics. Due to the limited own 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 mass, and small volume can better match the power requirements of small satellites. Compared with traditional chemical propulsion and electric propulsion, the cold 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 cold gas propulsion technology as the orbit-changing power of the satellite. With the expansion of the satellite constellation market scale and the progress of technology, the application scope of cold gas propulsion technology will be further expanded, providing more possibilities for future space missions.
[0004] Cold gas propulsion uses "cold gas" such as nitrogen and helium as the working medium to generate thrust by releasing the gas in the storage tank. The liquid ammonia propulsion system belongs to phase change gas propulsion. At present, the liquid ammonia propulsion system is widely used in small satellites under 100 kg, and mostly adopts the external heating method. During the application process of the liquid ammonia propulsion system, it needs to be preheated in advance to make the internal liquid ammonia reach the working temperature. The external heating method has a low heat transfer efficiency. For a liquid ammonia propulsion system with a large total impulse, the preheating time required to reach the working temperature is too long to effectively meet the working requirements of the propulsion system. Utility Model Content
[0005] The traditional liquid ammonia propulsion system connects each valve assembly through pipeline joints. Limited by the bending requirements of pipelines and the convenience of installation, debugging, and maintenance of each functional valve, a large number of pipeline joints greatly reduce the installation efficiency, increase the leakage points, and also require a large amount of space, resulting in a large volume and weight of the entire gas supply system. The heating of liquid ammonia usually adopts an external heating method, which requires additional heating devices, has low heat conduction efficiency, and poor long-term stability of the system.
[0006] To solve the above problems, an embodiment of the present application provides a highly integrated liquid ammonia propulsion system for spacecraft, which includes:
[0007] A liquid ammonia storage tank, which includes a shell and an ammonia storage cavity. An ammonia transmission passage is arranged in the shell and communicates with the ammonia storage cavity. A first insertion cavity, a second insertion cavity, a third insertion cavity, and a fourth insertion cavity that penetrate the outer surface of the shell are arranged on the shell. The first insertion cavity, the second insertion cavity, the third insertion cavity, and the fourth insertion cavity are sequentially connected through the ammonia transmission passage. An electromagnetic valve assembly is arranged in the first insertion cavity, a pressure reducing valve is arranged in the second insertion cavity, a heater is arranged in the third insertion cavity, and a nozzle is arranged in the fourth insertion cavity.
[0008] The purpose of the embodiment of the present application is to provide a highly integrated liquid ammonia propulsion system for spacecraft. Through an integrated design and an insertion structure, the intricate pipeline layout structure is omitted, the weight and volume of the overall system are reduced, it is convenient for mass production and installation, the process complexity is reduced, the cost is reduced, an internal heating method is adopted to reduce heat loss and improve heat transfer efficiency, a dual-redundancy electromagnetic valve design is adopted, and a pressure sensor is configured for monitoring to improve the long-term stability of the overall system.
[0009] In some embodiments, the electromagnetic valve assembly includes a first electromagnetic valve and a second electromagnetic valve, which are used to control the connection and disconnection of the ammonia transmission passage.
[0010] In some embodiments, when both the first electromagnetic valve and the second electromagnetic valve are in the open state, the ammonia transmission passage is in the connected state; when at least one of the first electromagnetic valve and the second electromagnetic valve is in the closed state, the ammonia transmission passage is in the blocked state.
[0011] In some embodiments, the pressure reducing valve includes a pressure reducing valve core and a pressure reducing valve spring. The pressure reducing valve spring is sleeved on the pressure reducing valve core, and the ammonia transmission passage passes through the pressure reducing valve core.
[0012] In some embodiments, the heater includes a heating component, and the heating component extends into the ammonia transmission passage through the third insertion cavity.
[0013] In some embodiments, a spiral groove is arranged on the outer surface of the heating component, and the gap between the spiral groove and the inner wall of the ammonia transmission passage forms a heating passage.
[0014] In some embodiments, a fifth insertion cavity and a sixth insertion cavity are further provided on the housing. The fifth insertion cavity communicates with the ammonia storage cavity, and the sixth insertion cavity communicates with the ammonia transmission passage between the pressure reducing valve and the heater.
[0015] In some embodiments, a first sensor is provided in the fifth insertion cavity for monitoring the pressure in the ammonia storage cavity; a second sensor is provided in the sixth insertion cavity for monitoring the pressure in the ammonia transmission passage between the pressure reducing valve and the heater.
[0016] In some embodiments, a seventh insertion cavity is further provided on the housing. One end of the seventh insertion cavity communicates with the ammonia storage cavity, and the other end penetrates through the outer surface of the housing.
[0017] In some embodiments, a filling valve is provided in the seventh insertion cavity. The filling valve is used to fill liquid ammonia into the ammonia storage cavity.
[0018] In some embodiments, a plurality of mounting holes are provided on the outer surface of the housing. The plurality of mounting holes are used for external fixation of the housing. BRIEF DESCRIPTION OF THE DRAWINGS
[0019] One or more embodiments are exemplarily illustrated by the pictures in the corresponding drawings. These exemplary illustrations do not constitute limitations on the embodiments. Elements with the same reference numerals in the drawings are represented as similar elements, unless otherwise stated, and the figures in the drawings do not constitute a scale limitation.
[0020] Figure 1 is the overall structure diagram of the liquid ammonia propulsion system provided by some embodiments of the present application;
[0021] Figure 2 is the overall front view of the liquid ammonia propulsion system provided by some embodiments of the present application;
[0022] Figure 3 is the overall cross-sectional view of the liquid ammonia propulsion system provided by some embodiments of the present application;
[0023] Figure 4 is the structural view of the liquid ammonia storage tank provided by some embodiments of the present application;
[0024] Figure 5 is the partial enlarged view of the first insertion cavity provided by some embodiments of the present application;
[0025] Figure 6 is the cross-sectional view of the structure of the first insertion cavity provided by some embodiments of the present application;
[0026] Figure 7 is the cross-sectional view of the structures of the second insertion cavity, the third insertion cavity, and the fourth insertion cavity provided by some embodiments of the present application;
[0027] Figure 8It is a cross-sectional view of the seventh insertion cavity structure provided by some embodiments of the present application;
[0028] Figure 9 It is a schematic diagram of the liquid ammonia propulsion system provided by some embodiments of the present application.
[0029] Description of the drawings: 11. Liquid ammonia storage tank; 111. Shell; 112. Ammonia storage cavity; 113. Ammonia transmission passage; 114. First insertion cavity; 1141. First installation hole; 1142. Second installation hole; 115. Second insertion cavity; 116. Third insertion cavity; 117. Fourth insertion cavity; 118. Fifth insertion cavity; 119. Sixth insertion cavity; 1110. Seventh insertion cavity; 12. Solenoid valve assembly; 121. First solenoid valve; 122. Second solenoid valve; 13. Pressure reducing valve; 131. Pressure reducing valve spool; 132. Pressure reducing valve spring; 14. Heater; 141. Heating assembly; 142. Spiral groove; 143. Heating passage; 15. Nozzle; 16. First sensor; 17. Second sensor; 18. Filling valve; 19. Installation hole. Detailed implementation manners
[0030] 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 with reference to 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 proposed to help readers 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 implemented. The division of the following embodiments is for convenience of description and should not constitute any limitation on the specific implementation manner of the present application. The various embodiments can be combined and cross-referenced with each other on the premise of not being contradictory.
[0031] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by those of ordinary skill 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 description of the drawings are intended to cover non-exclusive inclusion.
[0032] 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 indicating the quantity, specific order, or primary-secondary relationship of the indicated technical features. In the description of the embodiments of the present application, "a plurality of" means two or more unless otherwise specifically defined.
[0033] In the description of the embodiments of the present application, unless otherwise clearly specified and limited, technical terms such as "installation", "connection", and "coupling" shall be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral body; it may also be a mechanical connection or an electrical connection; it can be directly connected, or indirectly connected through an intermediate medium, and it can be the communication inside two components or the interaction relationship between two components. 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 circumstances.
[0034] Referring to Figures 1 to 9 , the embodiments of the present application provide the following technical solutions:
[0035] As Figures 1 to 4 shown, the liquid ammonia storage tank 11 includes a housing 111. A liquid ammonia storage cavity 112 is arranged inside the housing 111. An ammonia transmission passage 113 is arranged on the inner wall of the housing 111. The ammonia transmission passage 113 is arranged longitudinally along the inner wall of the housing 111. The lower port of the ammonia transmission passage 113 is communicated with the liquid ammonia storage cavity 112. Along the path direction of the ammonia transmission passage 113, a first insertion cavity 114, a second insertion cavity 115, a third insertion cavity 116, and a fourth insertion cavity 117 are sequentially arranged on the housing 111. One ends of the first insertion cavity 114, the second insertion cavity 115, and the third insertion cavity 116 are all communicated with the ammonia transmission passage 113, and the other ends all extend out of the outer surface of the housing 111. The upper port of the ammonia transmission passage 113 is communicated with the outside of the housing 111 through the fourth insertion cavity 117. A fifth insertion cavity 118 and a sixth insertion cavity 119 are respectively arranged on the left and right sides of the third insertion cavity 116. The fifth insertion cavity 118 is communicated with the liquid ammonia storage cavity 112 through a through hole on the housing 111. The sixth insertion cavity 119 is communicated with the ammonia transmission passage 113 through a through hole on the housing 111. A seventh insertion cavity 1110 is further arranged on the top of the housing 111. One end of the seventh insertion cavity 1110 is communicated with the liquid ammonia storage cavity 112, and the other end extends out of the outer surface of the housing 111. Four mounting holes 19 are circumferentially arranged at the lower end of the outer surface of the housing 111.
[0036] As Figure 5 and Figure 6 shown, the solenoid valve assembly 12 includes a first solenoid valve 121 and a second solenoid valve 122. The first insertion cavity 114 includes a first mounting hole 1141 and a second mounting hole 1142. The first solenoid valve 121 is arranged in the first mounting hole 1141, and the second solenoid valve 122 is arranged in the second mounting hole 1142.
[0037] As Figure 7As shown in the figure, the pressure reducing valve 13 is arranged in the second cartridge chamber 115, and the pressure reducing valve core 131 is arranged in the ammonia transmission passage 113 through the second cartridge chamber 115. The pressure reducing valve spring 132 is sleeved on the pressure reducing valve core 131. One end of the pressure reducing valve spring 132 is connected to the pressure reducing valve core 131, and the other end is connected to the inner wall of the second cartridge chamber 115.
[0038] As Figure 7 shown in the figure, the heater 14 is arranged in the third cartridge chamber 116, and the heating component 141 is arranged in the ammonia transmission passage 113 through the third cartridge chamber 116. A spiral groove 142 is arranged on the outer surface of the heating component 141, and a heating passage 143 is formed by the gap between the spiral groove 142 and the inner wall of the ammonia transmission passage 113 where the heating component 141 is located.
[0039] As Figure 7 shown in the figure, a nozzle 15 is arranged in the fourth cartridge chamber 117.
[0040] As Figure 2 shown in the figure, the first sensor 16 is arranged in the fifth cartridge chamber 118, and the second sensor 17 is arranged in the sixth cartridge chamber 119.
[0041] As Figure 8 shown in the figure, a filling valve 18 is arranged in the seventh cartridge chamber 1110.
[0042] It should be noted that: As Figure 3 and Figure 8 shown in the figure, before the high-integration liquid ammonia propulsion system for satellite works, the filling valve 18 is opened and connected to the ammonia source device. The liquid ammonia in the ammonia source device enters the ammonia storage chamber 112 of the liquid ammonia storage tank 11 through the filling valve 18. After the liquid ammonia filling is completed, the connection between the filling valve 18 and the ammonia source device is disconnected, and the filling valve 18 is closed.
[0043] It should be noted that: When filling liquid ammonia into the ammonia storage chamber 112, a cavity with a volume of 10% of the volume of the ammonia storage chamber 112 will be left. After the filling is completed, part of the liquid ammonia in the ammonia storage chamber 112 will turn into gaseous ammonia, and at this time, the ammonia storage chamber 112 contains a gas-liquid mixed ammonia working medium.
[0044] It should be noted that: When the high-integration liquid ammonia propulsion system for satellite works, the heater 14 is first turned on, and the heating component 141 starts to heat, so that the heating passage 143 starts to heat up and reaches the heating temperature. The spiral groove 142 increases the heating area of the heating passage 143.
[0045] It should be noted that: When the high-integration liquid ammonia propulsion system for satellite works, it is first heated through the thermal control system, which is provided by the satellite overall. The liquid ammonia in the ammonia storage chamber 112 is heated to reach the initial temperature, increasing the latent heat of vaporization of the liquid ammonia working medium and improving the conversion rate of gaseous ammonia.
[0046] It should be noted that: the ammonia storage cavity 112 is equipped with a gas-liquid separation device. When the high-integration liquid ammonia propulsion system for satellite works, the gas-liquid separation device plays a role in separating gaseous ammonia and liquid ammonia.
[0047] It should be noted that: the first solenoid valve 121 and the second solenoid valve 122 are used to control the connection and disconnection of the ammonia transmission path;
[0048] When both the first solenoid valve 121 and the second solenoid valve 122 are in the open state, the ammonia transmission path 113 is in the connected state;
[0049] When at least one of the first solenoid valve 121 and the second solenoid valve 122 is in the closed state, the ammonia transmission path 113 is in the blocked state.
[0050] It should be noted that: as Figure 3 and Figure 9 shown, when the high-integration liquid ammonia propulsion system for satellite works, the first solenoid valve 121 and the second solenoid valve 122 are opened simultaneously. The gas-liquid mixed ammonia working medium in the ammonia storage cavity 112 enters the ammonia transmission path 113 from the lower port of the ammonia transmission path 113. Subsequently, the gas-liquid mixed ammonia working medium passes through the first solenoid valve 121 and the second solenoid valve 122 in sequence. Then, the gas-liquid mixed ammonia working medium passes along the ammonia transmission path 113 through the pressure reducing valve core 131. The gas-liquid mixed ammonia working medium reaches a constant pressure through the combined pressure reducing action of the pressure reducing valve core 131 and the pressure reducing valve spring 132. The gas-liquid mixed ammonia working medium after being pressure-reduced by the pressure reducing valve core 131 enters the heating path 143. Through the further heating of the heating path 143, the gas-liquid mixed ammonia working medium is completely changed into gaseous ammonia working medium to improve the specific impulse of the working medium, and then is ejected through the nozzle 15.
[0051] It should be noted that: both the first sensor 16 and the second sensor 17 are pressure sensors. The fifth insertion cavity 118 is communicated with the ammonia storage cavity 112 through the holes on the housing 111. When the high-integration liquid ammonia propulsion system for satellite works, the pressure in the fifth insertion cavity 118 is the same as the pressure in the ammonia storage cavity 112;
[0052] The sixth insertion cavity 119 is communicated with the ammonia transmission path 113 between the pressure reducing valve core 131 and the heating component 141 through the holes on the housing 111. When the high-integration liquid ammonia propulsion system for satellite works, the pressure in the sixth insertion cavity 119 is the same as the pressure in the ammonia transmission path 113 between the pressure reducing valve core 131 and the heating component 141.
[0053] It should be noted that: the temperature resistance range of all components of the high-integration liquid ammonia propulsion system for satellite is -20°C - 50°C, and the system working temperature is 20°C - 40°C.
[0054] It should be noted that: The material of the liquid ammonia storage tank 11 includes but is not limited to titanium alloy, and the heater 14 is a double-circuit armored heater.
[0055] It should be noted that: The sealing methods of the high-integration liquid ammonia propulsion system for the satellite include but are not limited to rubber ring sealing and thread sealing.
[0056] For the high-integration liquid ammonia propulsion system for the satellite, through the integrated design of the liquid ammonia storage tank 11, the first insertion cavity 114, the second insertion cavity 115, the third insertion cavity 116 and the fourth insertion cavity 117 are sequentially connected through the ammonia transmission path 113. The first solenoid valve 121, the second solenoid valve 122, the pressure reducing valve 13, the heater 14 and the nozzle 15 are respectively inserted into the first mounting hole 1141, the second mounting hole 1142, the second insertion cavity 115, the third insertion cavity 116 and the fourth insertion cavity 117, omitting the traditional intricate pipeline layout structure, reducing the occupied space volume. The plug-in structure is convenient for mass production and installation, reduces the process complexity, and effectively saves costs at the same time; the heater 14 is a double-circuit armored heater, which adopts the internal heating method, and increases the heating area through the spiral groove 141, reduces the heat loss, improves the heat transfer efficiency, reduces the preheating time of the liquid ammonia propulsion system, and improves the gasification effect; the double-redundancy solenoid valve design is realized through the first solenoid valve 121 and the second solenoid valve 122, improving the long-term stability of the system.
[0057] Those of ordinary skill in the art can understand that the above embodiments are specific embodiments for implementing the present application, and in actual applications, various changes can be made in form and details without departing from the spirit and scope of the present application.
Claims
1. A high-integration liquid ammonia propulsion system for satellites, characterized in that, It includes an ammonia storage tank, and the ammonia storage tank includes a housing and an ammonia storage chamber. An ammonia transmission passage is arranged in the housing and communicated with the ammonia storage chamber. A first insertion cavity, a second insertion cavity, a third insertion cavity and a fourth insertion cavity are arranged on the housing, and one end of each of them penetrates through the outer surface of the housing. The first insertion cavity, the second insertion cavity, the third insertion cavity and the fourth insertion cavity are sequentially communicated through the ammonia transmission passage. An electromagnetic valve assembly is arranged in the first insertion cavity, a pressure reducing valve is arranged in the second insertion cavity, a heater is arranged in the third insertion cavity, and a nozzle is arranged in the fourth insertion cavity.
2. The high-integration liquid ammonia propulsion system for satellite according to claim 1, wherein The electromagnetic valve assembly includes a first electromagnetic valve and a second electromagnetic valve, which are used to control the connection and disconnection of the ammonia transmission passage; When both the first electromagnetic valve and the second electromagnetic valve are in the open state, the ammonia transmission passage is in the connected state; When at least one of the first electromagnetic valve and the second electromagnetic valve is in the closed state, the ammonia transmission passage is in the blocked state.
3. A high-integration liquid ammonia propulsion system for satellites according to claim 1, characterized in that, The pressure reducing valve includes a pressure reducing valve core and a pressure reducing valve spring. The pressure reducing valve spring is sleeved on the pressure reducing valve core, and the ammonia transmission passage passes through the pressure reducing valve core.
4. A high-integration liquid ammonia propulsion system for satellites according to claim 1, characterized in that, The heater includes a heating component, and the heating component extends into the ammonia transmission passage through the third insertion cavity.
5. The high-integration liquid ammonia propulsion system for satellite according to claim 4, characterized in that A spiral groove is arranged on the outer surface of the heating component, and the gap between the spiral groove and the inner wall of the ammonia transmission passage forms a heating passage.
6. The high-integration liquid ammonia propulsion system for satellite according to claim 1, characterized in that, A fifth insertion cavity and a sixth insertion cavity are also arranged on the housing. The fifth insertion cavity is communicated with the ammonia storage chamber, and the sixth insertion cavity is communicated with the ammonia transmission passage between the pressure reducing valve and the heater.
7. The high-integration liquid ammonia propulsion system for satellite according to claim 6, characterized in that, A first sensor is arranged in the fifth insertion cavity, which is used to monitor the pressure in the ammonia storage chamber; A second sensor is arranged in the sixth insertion cavity, which is used to monitor the pressure in the ammonia transmission passage between the pressure reducing valve and the heater.
8. A high-integration liquid ammonia propulsion system for satellites according to claim 1, characterized in that A seventh insertion cavity is also arranged on the housing. One end of the seventh insertion cavity is communicated with the ammonia storage chamber, and the other end penetrates through the outer surface of the housing.
9. A high-integration liquid ammonia propulsion system for satellites according to claim 8, characterized in that, A filling valve is arranged in the seventh insertion cavity, and the filling valve is used to fill liquid ammonia into the ammonia storage chamber.
10. A high-integration liquid ammonia propulsion system for satellites according to claim 1, characterized in that, A plurality of mounting holes are arranged on the outer surface of the housing, and the plurality of mounting holes are used for external fixation of the housing.