High-integration-level single-component propulsion system for satellites

Abstract

The embodiment of the utility model relates to the technical field of space propulsion, and discloses a satellite high-integration-level single-component propulsion system which comprises a storage box and an integration part arranged on the storage box, a conveying pipeline is arranged in the integration part, one end of the conveying pipeline communicates with an inner cavity of the storage box, and the other end of the conveying pipeline extends to the outer surface of the integration part. A first containing cavity, a second containing cavity and a third containing cavity are sequentially formed in the integration part along the output path of the conveying pipeline, one end of each containing cavity communicates with the conveying pipeline, the other end of each containing cavity extends out of the integration part, a first adding and discharging valve is arranged in the first containing cavity, a first switch valve is arranged in the second containing cavity, and a second switch valve is arranged in the third containing cavity. The storage box is further provided with a fourth containing cavity penetrating through the box wall of the storage box, and a second adding and discharging valve is arranged in the fourth containing cavity. Through the high-integration design, the structural layout of the storage tank is optimized, the traditional connection mode of an external pipeline is replaced, the overall structure is simplified, and the utilization rate of an envelope space and the stability of the system are improved.

Description

Technical Field

[0001] The embodiments of the present application relate to the field of space propulsion technology, and in particular to a highly integrated single-propellant propulsion system for satellites. Background Art

[0002] A monopropellant propulsion system is a relatively simple type of rocket engine that does not require separate fuel and oxidizers, but instead relies on a single chemical substance to generate thrust. This chemical substance acts as both a fuel and an oxidizer, and when exposed to a catalyst or heated, it decomposes and releases gases. These gases are accelerated through a nozzle to generate thrust. For example, hydrazine decomposes when it comes into contact with a catalyst (such as platinum or iridium) to produce ammonia, nitrogen, and water vapor, which are passed through the nozzle to generate thrust. This process not only simplifies system design, but also controls the amount of thrust by controlling the size of the thrust chamber throat diameter, achieving precise spacecraft attitude control. The advantages of monopropellants also include: green and high energy, non-toxic, non-corrosive, and easy to preserve for a long time.

[0003] With the advancement of small satellite technology, especially CubeSat technology, the demand for compact, low-cost propulsion systems has surged. Compared to cold gas propulsion and electric propulsion, chemical propulsion offers superior overall performance, with a specific impulse only slightly lower than electric propulsion, yet offering superior maneuverability. Monopropellant propulsion systems, with their simplicity and high level of integration, are well-suited for such applications. Modern monopropellant system designs increasingly emphasize modularity and standardization, facilitating rapid integration across diverse satellite platforms. As technology matures and new propellants are developed, monopropellant propulsion systems will continue to play a vital role in future space exploration.

[0004] For example, Chinese patent document CN 117446214 A discloses a green monopropellant propulsion system, which includes a propellant tank, a liquid barrier valve, a solenoid valve, a monopropellant thrust chamber, a pressure sensor, and connecting piping. Except for the monopropellant thrust chamber and the connecting piping, the main part of the propulsion system is within a 1U (10cm×10cm×10cm) envelope and can be expanded to 2U, 4U, 6U, or even larger. The installation position of the propulsion system and the number and arrangement of thrusters are determined according to the functions and layout requirements of the entire satellite. The total impulse of the green monopropellant propulsion system is not less than 1100N·s. In the implementation case provided in the patent document, only the tank part is within the 1U size, and the envelope size of its cubic satellite frame, thrust chamber and other components exceeds 4U or even 6U, resulting in poor envelope space utilization. Other propulsion systems with the same volume have higher total impulse.

[0005] The above-mentioned green monopropellant propulsion system inevitably requires bending of pipelines to adapt to various space and structural limitations. This design complexity increases the difficulty of pre-packaging, and the pipelines increase the system pressure drop and water-machine effect, reducing the stability of the system and the pre-packaging and batch production efficiency of the product, and also increasing costs. Utility Model Content

[0006] The current monopropellant propulsion system has poor envelope space utilization, and the pipelines inevitably need to be bent to adapt to various space and structural limitations, which increases the difficulty of pre-packaging. The pipelines also increase the system pressure drop and water-machine effect, reducing the stability of the system.

[0007] In order to solve the above problems, the purpose of the embodiment of the present application is to provide a highly integrated single-propellant propulsion system for satellites, which includes a tank and an integrated part arranged thereon, a delivery pipeline is arranged in the integrated part, one end of the delivery pipeline is connected to the inner cavity of the tank, and the other end extends to the outer surface of the integrated part, and a first placement chamber, a second placement chamber and a third placement chamber are arranged in sequence along the output path of the delivery pipeline, one end of which is connected to the delivery pipeline and the other end extends to the outside of the integrated part, a first placement chamber and a third placement chamber are arranged in sequence along the output path of the delivery pipeline, a first addition and discharge valve is arranged in the first placement chamber, a first switch valve is arranged in the second placement chamber, and a second switch valve is arranged in the third placement chamber, and a fourth placement chamber that passes through the tank wall is also provided on the tank, and a second addition and discharge valve is provided in the fourth placement chamber.

[0008] The purpose of the implementation method of the present application is to provide a highly integrated single-propellant propulsion system for satellites. Through the high-integration design concept, the tank structure layout is optimized, the various valve components are integrated together, and the traditional external pipeline connection method is replaced by an internal delivery pipeline, thereby simplifying the overall structure, improving the envelope space utilization and system stability, reducing costs, and shortening delivery time.

[0009] In some embodiments, a catalytic bed is provided at one end of the delivery pipeline away from the inner cavity, and the delivery pipeline is connected to the thrust device through the catalytic bed.

[0010] In some embodiments, the first add / discharge valve is a liquid add / discharge valve, and the second add / discharge valve is a gas add / discharge valve.

[0011] In some embodiments, the first on-off valve and the second on-off valve are used to control the connection or blockage of the delivery pipeline.

[0012] In some embodiments, the first switch valve is a solenoid valve, a self-locking valve, or an electric explosion valve.

[0013] In some embodiments, the second switching valve is a solenoid valve.

[0014] In some embodiments, the tank is further provided with a pressure sensor, which is used to detect the pressure in the inner cavity of the tank.

[0015] In some embodiments, an armored heater is provided on the catalytic bed.

[0016] In some embodiments, the invention further comprises a first temperature sensor and a second temperature sensor, wherein the first temperature sensor is disposed on the catalytic bed, and the second temperature sensor is disposed on the storage tank.

[0017] In some embodiments, a plurality of mounting components are provided on the outer surface of the tank, and the mounting components are used for external fixation of the tank. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] One or more embodiments are exemplarily illustrated by pictures in the corresponding drawings. These exemplifications do not constitute limitations on the embodiments. Elements with the same reference numerals in the drawings are represented as similar elements. Unless otherwise stated, the figures in the drawings do not constitute proportional limitations.

[0019] Figure 1 This is a front view of a highly integrated monopropellant propulsion system for satellites provided in some embodiments of the present application;

[0020] Figure 2 This is a left view of a highly integrated monopropellant propulsion system for satellites provided in some embodiments of the present application;

[0021] Figure 3 This is a top view of a highly integrated monopropellant propulsion system for satellites provided in some embodiments of the present application;

[0022] Figure 4 This is a cross-sectional view of a highly integrated monopropellant propulsion system for satellites provided in some embodiments of the present application;

[0023] Figure 5 This is a cross-sectional view of the AA plane of a highly integrated monopropellant propulsion system for satellites provided in some embodiments of the present application;

[0024] Figure 6 This is a partially enlarged cross-sectional view of a highly integrated monopropellant propulsion system for satellites provided in some embodiments of the present application;

[0025] Figure 7 This is a schematic diagram of a highly integrated monopropellant propulsion system for satellites provided in some embodiments of the present application.

[0026] Description of the drawings: 11. Storage tank; 111. Inner cavity; 112. Integrated part; 113. Transport passage; 114. First placement cavity; 115. Second placement cavity; 116. Third placement cavity; 117. Fourth placement cavity; 12. First addition and discharge valve; 13. First switch valve; 14. Second switch valve; 15. Catalytic bed; 16. Thrust device; 17. Pressure sensor; 18. Second addition and discharge valve; 19. Armored heater; 20. First temperature sensor; 21. Second temperature sensor; 22. Installation assembly. DETAILED DESCRIPTION

[0027] In order to make the purpose, technical solutions and advantages of the embodiments of the present application clearer, each embodiment of the present application will be described in detail below with reference to the accompanying drawings. However, it will be understood by those skilled in the art that in each embodiment of the present application, many technical details are proposed in order to enable the reader to better understand the present application. However, even without these technical details and various changes and modifications based on the following embodiments, the technical solutions claimed in the present application can be implemented. The division of the following embodiments is for convenience of description and should not constitute any limitation on the specific implementation of the present application. The various embodiments can be combined with each other and referenced to each other under the premise of no contradiction.

[0028] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by those skilled in the art to which this application belongs; the terms used herein are for the purpose of describing specific embodiments only 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-mentioned figure descriptions are intended to cover non-exclusive inclusions.

[0029] In the description of the embodiments of this application, the technical terms "first" and "second" are used only to distinguish different objects and should not be understood to indicate or imply relative importance or implicitly specify the quantity, specific order, or primary and secondary relationship of the indicated technical features. In the description of the embodiments of this application, the meaning of "plurality" is more than two, unless otherwise clearly and specifically defined.

[0030] In the description of the embodiments of the present application, unless otherwise expressly specified or limited, technical terms such as "installed," "connected," and "connected" should be understood in a broad sense. For example, they can refer to fixed connections, detachable connections, or integration; mechanical connections, or electrical connections; direct connections, or indirect connections through an intermediate medium; and can refer to internal connectivity between two components or interaction between two components. Those skilled in the art can understand the specific meanings of the above terms in the embodiments of the present application based on specific circumstances.

[0031] Reference Figures 1 to 6, the embodiments of this application provide the following technical solutions:

[0032] like Figure 1 and Figure 2 As shown, an integrated portion 112 is provided below the tank 11, a catalytic bed 15 is connected below the integrated portion 112, a thrust device 16 is connected below the catalytic bed 15, a first adding and discharging valve 12, a first switching valve 13 and a second switching valve 14 are circumferentially provided on the integrated portion 112, an armored heater 19 is provided on the catalytic bed 15, a pressure sensor 17 is also provided below the tank 11, a first temperature sensor 20 is welded to the outer surface of the catalytic bed 15, and a second temperature sensor 21 is bonded and covered on the outer surface of the tank 11.

[0033] like Figure 3 As shown, four mounting components 22 are circumferentially arranged on the upper portion of the outer surface of the storage tank 11. Each mounting component 22 is provided with a threaded hole for external fixation of the storage tank 11. The size of the threaded hole is determined according to the actual installation environment.

[0034] like Figures 4 to 6 As shown, the storage tank 11 is provided with an inner cavity 111, and the integrated part 112 is provided with a conveying passage 113. The upper end of the conveying passage 113 is connected to the inner cavity 111, and the lower end is connected to the catalytic bed 15. The integrated part 112 is provided with a first placement cavity 114, a second placement cavity 115 and a third placement cavity 116 along the path of the conveying passage 113 from the upper end to the lower end of the conveying passage 113. One end of the first placement cavity 114, the second placement cavity 115 and the third placement cavity 116 are all connected to the conveying passage, and the other end extends to the outer surface of the integrated part 112. The first adding and discharging valve 12 is fixedly connected to the first placement cavity 114 by means of threads, the first switching valve 13 is fixedly connected to the second placement cavity 115 by means of a flange, the second switching valve 14 is fixedly connected to the third placement cavity 116 by means of a flange, and a fourth placement cavity 117 penetrating the wall of the storage tank 11 is further provided at the lower part of the wall of the storage tank 11. The pressure sensor 17 is fixedly connected to the fourth placement cavity 117 by means of threads, and a passage connecting the inner cavity 111 and the outside of the storage tank 11 is further provided at the top of the wall of the storage tank 11, in which the second adding and discharging valve 18 is fixedly connected by means of threads.

[0035] It should be noted that the first adding and discharging valve 12 is a liquid adding and discharging valve, and the second adding and discharging valve 18 is a gas adding and discharging valve.

[0036] It should be noted that the catalytic bed 15 is fixedly connected to the integrated portion 112 of the tank 11 via a flange, and the thrust device 16 is fixedly connected to the catalytic bed 15 via a flange.

[0037] It should be noted that the first switch valve 13 and the second switch valve 14 are used to control the connection or blocking of the delivery pipeline 113;

[0038] When the first switch valve 13 and the second switch valve 14 are both solenoid valves, when both solenoid valves are in the open state, the delivery pipeline 113 is in the connected state;

[0039] When at least one solenoid valve is in a closed state, the delivery pipeline 113 is in a blocked state.

[0040] like Figure 7 As shown, before use, the system is evacuated from the inner cavity 111 of the tank 11 via the second add-discharge valve 18. A rated amount of propellant is then added to the inner cavity 111 of the tank 11 via the first add-discharge valve 12. The propellant then enters the inner cavity 111 via the first add-discharge valve 12 and a portion of the delivery passage 113. The inner cavity 111 of the tank 11 is then filled with pressurized gas for rated operation via the second add-discharge valve 18. The internal pressure of the inner cavity 111 of the tank 11 is constantly monitored via the pressure sensor 17. Completion of the above steps completes the filling process.

[0041] When the system is in use, a heating instruction is first sent to the armored heater 19, and the armored heater 19 heats the catalyst bed 15 to the temperature required for the system to work. The first temperature sensor 20 monitors whether the temperature of the catalyst bed 15 reaches the required value;

[0042] Then, a working instruction is sent to the two solenoid valves to control the two solenoid valves to open simultaneously and set the opening time of the two solenoid valves;

[0043] After the two solenoid valves are opened simultaneously, the delivery passage 113 is in a connected state. The propellant in the inner cavity 111 enters the upper port of the delivery passage 113 and then flows along the path of the delivery passage 113 through the two solenoid valves in sequence and enters the catalyst bed 15 from the lower port of the delivery passage 113. The propellant undergoes a chemical reaction in the catalyst bed 15 to produce high-temperature and high-pressure gas, which flows into the thrust device 16 and is finally ejected from the lower port of the thrust device 16 to generate propulsion.

[0044] During the operation of the system, the pressure sensor 17 monitors the pressure change in the inner cavity 111 in real time, and the second temperature sensor 21 monitors the temperature change in the inner cavity 111 in real time.

[0045] It should be noted that the satellite's highly integrated monopropellant propulsion system is equipped with a control system for monitoring and controlling the working status of the tank 11, the first switch valve 13, the second switch valve 14, the pressure sensor 17 and the armored heater 19.

[0046] It should be noted that when the storage tank 11 is used for long-term storage, the first switch valve 13 can be set as a self-locking valve or an electric explosion valve to meet the long-term storage requirements of different pre-packages, improve system reliability, and reduce leakage rate.

[0047] It should be noted that the envelope size of the satellite's highly integrated monopropellant propulsion system is 3U (300mm×100mm×100mm), and the total impulse of the system is ≥2200N·s.

[0048] This satellite-based highly integrated single-propellant propulsion system has an integrated portion 112 provided at the lower portion of the tank 11, and a conveying passage 113 provided in the integrated portion 112. The first placement cavity 114, the second placement cavity 115 and the third placement cavity 116 provided on the integrated portion 112 are connected through the conveying passage 113. The first addition and discharge valve 12, the first switch valve 13 and the second switch valve 14 are respectively inserted into the first placement cavity 114, the second placement cavity 115 and the third placement cavity 116. One end of the conveying passage 113 is connected to the inner cavity 111, and the other end is connected to the thrust device 16 through the catalytic bed 15, forming a complete thrust generation path. The second addition and discharge valve 18 and the pressure sensor 17 are both provided on the tank 11, which optimizes the structure of the tank 11 and replaces the traditional external pipe connection method, realizing an integrated design, reducing the leakage rate of the system, and improving the envelope space utilization and stability.

[0049] Those skilled in the art will appreciate that the above-mentioned embodiments are specific examples for implementing the present application, and that in actual applications, various changes may be made thereto in form and detail without departing from the spirit and scope of the present application.

Claims

1. A highly integrated monopropellant propulsion system for satellites, characterized in that: It includes a storage tank and an integrated part arranged thereon, a delivery pipeline is arranged in the integrated part, one end of the delivery pipeline is connected to the inner cavity of the storage tank, and the other end extends to the outer surface of the integrated part, and a first placement cavity, a second placement cavity and a third placement cavity are arranged in sequence on the integrated part along the output path of the delivery pipeline, one end of which is connected to the delivery pipeline and the other end extends to the outside of the integrated part, a first addition and discharge valve is arranged in the first placement cavity, a first switch valve is arranged in the second placement cavity, and a second switch valve is arranged in the third placement cavity, and a fourth placement cavity is further provided on the storage tank, which passes through the tank wall, and a second addition and discharge valve is provided in the fourth placement cavity.

2. A highly integrated monopropellant propulsion system for satellites according to claim 1, characterized in that: A catalytic bed is provided at one end of the delivery pipeline away from the inner cavity, and the delivery pipeline is communicated with the thrust device through the catalytic bed.

3. A highly integrated monopropellant propulsion system for satellites according to claim 2, characterized in that: The first adding and discharging valve is a liquid adding and discharging valve, and the second adding and discharging valve is a gas adding and discharging valve.

4. A highly integrated monopropellant propulsion system for satellites according to claim 3, characterized in that: The first switch valve and the second switch valve are used to control the connection or blocking of the delivery pipeline.

5. The highly integrated monopropellant propulsion system for satellites according to claim 4, characterized in that: The first switch valve is a solenoid valve, a self-locking valve or an electric explosion valve.

6. A highly integrated monopropellant propulsion system for satellites according to claim 5, characterized in that: The second switch valve is a solenoid valve.

7. A highly integrated monopropellant propulsion system for satellites according to claim 6, characterized in that: The tank is also provided with a pressure sensor, which is used to detect the pressure in the inner cavity of the tank.

8. The highly integrated monopropellant propulsion system for satellites according to claim 7, characterized in that: An armored heater is provided on the catalytic bed.

9. The highly integrated monopropellant propulsion system for satellites according to claim 8, characterized in that: The invention also includes a first temperature sensor and a second temperature sensor, wherein the first temperature sensor is arranged on the catalytic bed, and the second temperature sensor is arranged on the storage tank.

10. A highly integrated monopropellant propulsion system for satellites according to claim 9, characterized in that: A plurality of mounting components are provided on the outer surface of the tank, and the mounting components are used for external fixing of the tank.

Images