Pocket-size cubesat micro-propulsion system

Abstract

The utility model provides a pocket-size cubesat micro-propulsion system. The pocket-size cubesat micro-propulsion system comprises a shell; the propellant box is arranged in the shell, and a working solution is stored in the propellant box; the guide pipe is in contact with the propellant box; the conduit is located between the flow regulator and the propellant box, and the flow regulator is provided with a plurality of flow regulation holes. According to the flow regulator, the flow can be regulated by customizing the size of the flow regulating hole, and only the flow regulator needs to be replaced when the flow needs to be regulated, so that the overall cost is reduced.

Description

Technical Field

[0001] The utility model relates to the technical field of air conditioning, and in particular to a pocket-sized cubic satellite micro-propulsion system. Background Art

[0002] With the development of the times, microsatellites, especially cubic satellites, are increasingly used in the field of modern aerospace. These small spacecraft are favored for their lightness, low cost and rapid deployment. However, the design of micro-propulsion systems for cubic satellites faces special challenges, especially in the selection and storage of propellants, propulsion efficiency and system integration. Traditional chemical propellants not only have safety hazards in storage and transportation, but also may have a negative impact on the environment. Therefore, the development of a micro-propulsion system that is both environmentally friendly and efficient is crucial to the advancement of cubic satellite technology. The concept of green working fluid evaporation came into being, which uses environmentally friendly working fluids such as water or alcohols as propellants to generate thrust by heating and evaporation. This propulsion method is not only environmentally friendly, but also has significant advantages in safety and storage efficiency. Nevertheless, in order to realize this concept and ensure its applicability to cubic satellites, several key technical issues need to be solved, including how to efficiently control the flow rate of the working fluid, how to effectively convert thermal energy into propulsion energy, and how to integrate all necessary components in a limited space.

[0003] However, one of the drawbacks of the related art is that the equipment needs to be significantly adjusted when adjusting the injection flow rate, resulting in high costs. Utility Model Content

[0004] The utility model aims to solve at least one of the above technical problems.

[0005] In order to solve the above problems, the first purpose of the utility model is to provide a pocket-sized cubic satellite micro-propulsion system.

[0006] To achieve the first purpose of the utility model, an embodiment of the utility model provides a pocket-sized cubic satellite micro-propulsion system, which includes: a shell; a propellant tank, which is arranged in the shell and stores working fluid in the propellant tank; a conduit, which is in contact with the propellant tank; a flow regulator, which is located between the flow regulator and the propellant tank, and the flow regulator is provided with a plurality of flow regulating holes.

[0007] The system uses green working fluid as propellant and does not use traditional harmful fuels, so it has lower environmental pollution and higher environmental friendliness. The system uses the heat energy of the evaporation of the working fluid to propel the micro-propulsion system, and no additional energy input is required. Through the combination of micro-heaters and evaporators, thermal energy can be effectively utilized to improve propulsion efficiency. The pocket cubic satellite micro-propulsion system is compactly designed with a small size and weight. This makes it very suitable for use in space applications such as small satellites or space probes to provide tiny but effective propulsion. The flow regulator in the system has multiple flow adjustment holes, and its porosity can be customized as needed to adjust the flow rate, and the flow rate can be precisely adjusted and controlled. This enables the system to perform flexible propulsion control according to different needs, and when the flow rate needs to be adjusted, only the flow regulator needs to be replaced, which greatly reduces the cost.

[0008] In the above technical solution, the pocket cubic satellite micro-propulsion system also includes: a micro-heater, which is located on the side of the flow regulator away from the catheter.

[0009] The microheater can provide heat to heat the working fluid. Through the heating effect of the microheater, the working fluid can be evaporated quickly, thereby generating propulsion. The heating function of the microheater can effectively control the evaporation rate of the working fluid and the generation of propulsion, providing precise control of the propulsion performance of the system. The microheater can provide a rapid heating effect, so that the working fluid can evaporate quickly, thereby quickly generating propulsion. This fast response characteristic is very beneficial for tasks that require propulsion in a short time. The heating power of the microheater can be precisely adjusted to control the evaporation rate of the working fluid and the magnitude of the propulsion. This precise control capability enables the system to perform flexible and precise propulsion control according to different mission requirements. The microheater only provides heating power when needed, avoiding energy waste. By precisely controlling the heating power and evaporation rate, the system can achieve efficient use of energy and improve overall energy efficiency.

[0010] In any of the above technical solutions, the pocket cubic satellite micro-propulsion system also includes: an evaporator, which is located between the micro-heater and the flow regulator.

[0011] The working fluid is conducted to the evaporator, and the microheater heats the evaporator. When the temperature of the evaporator is high enough, the working fluid evaporates into hot gas and is ejected due to the pressure difference generated. Through the evaporator, the liquid propellant in the working fluid can be heated and converted into gaseous propellant to generate thrust. By evaporating the working fluid, the system can use thermal energy more efficiently and convert it into thrust. This can improve propulsion efficiency and enable the system to produce greater thrust output with a given amount of working fluid. The introduction of the evaporator can simplify the system structure because it allows the evaporation process of the working fluid to be directly used to generate thrust without the use of other complex propulsion mechanisms or components.

[0012] In any of the above technical solutions, a first gasket is provided between the evaporator and the flow regulator.

[0013] The first gasket is arranged between the evaporator and the flow regulator, which can provide a certain physical spacing and support to prevent direct contact or collision between the evaporator and the flow regulator, and can provide additional support and isolation to ensure a stable spacing between the evaporator and the flow regulator, thereby protecting their structural integrity. The gasket may also help reduce heat conduction or transfer to ensure that the heat of the microheater mainly acts on the evaporator and the working fluid without excessive dissipation.

[0014] In any of the above technical solutions, the evaporator is provided with a plurality of micro nozzles.

[0015] Micronozzles can release the working fluid in a small and concentrated manner, which can make more efficient use of propellants compared to uniform spraying. By controlling the number of micronozzles and the spray pattern, it is possible to save the use of propellants, extend the working time of the system or reduce the load of the propellant. The spraying method of micronozzles can produce higher speeds and momentum transfer, thereby improving propulsion efficiency. This is particularly important for micro-scale propulsion systems, because the high-speed spraying of microjets can generate enough thrust to overcome the microgravity environment or air resistance and achieve a more effective micro-propulsion effect.

[0016] In any of the above technical solutions, the pocket cubic satellite micro-propulsion system also includes: a sealing plate, which is located between the flow regulator and the propellant tank.

[0017] The sealing plate acts as a seal in the system and can effectively prevent the leakage of working fluid or gas. The setting of the sealing plate can ensure the normal operation of the propulsion system and reduce the loss of energy and material. As a component of the system, the sealing plate can provide structural support and stability. It can increase the overall rigidity of the system, making the system more solid and stable during operation. The sealing plate can isolate the space between the flow regulator and the propellant tank to prevent mutual interference between the two. This helps to ensure that each component in the system can work independently and improve the reliability and stability of the system. Therefore, the setting of the sealing plate can provide good sealing performance, structural support and component isolation, thereby ensuring the reliability, stability and normal operation of the system.

[0018] In any of the above technical solutions, the sealing plate is provided with a first through hole, and the conduit passes through the first through hole.

[0019] Through the first through hole on the sealing plate, the conduit can pass through the sealing plate, so that the conduit can be connected to other parts of the system and realize fluid transmission. At the same time, the sealing plate can provide effective sealing at the position where the conduit passes through the through hole, ensuring the sealing performance of the system and preventing the working fluid or other substances from leaking or entering areas that should not be entered. Such a design can ensure the normal operation and reliability of the system, ensure the flow of the working fluid and the normal operation of the propulsion system.

[0020] In any of the above technical solutions, the pocket cubic satellite micro-propulsion system also includes: a pad, which is arranged between the sealing plate and the propellant tank.

[0021] The pad is located between the sealing plate and the propellant tank. Its function is to fill the gap, enhance the structural stability and provide support. By adding the pad, the overall rigidity and stability of the system can be enhanced, the tight connection between the components can be ensured, and the vibration and looseness during operation can be reduced. This helps the reliability and performance stability of the system, and also helps to reduce the risk of damage or leakage caused by external environmental factors. The pad can also avoid direct collision between the sealing plate and the propellant tank, and prevent the propellant tank from leaking the internal working fluid due to collision, thereby improving the overall safety of the system.

[0022] In any of the above technical solutions, the backing plate is provided with a second through hole, and the conduit passes through the second through hole.

[0023] Through the second through hole on the pad, the conduit can pass through the pad and connect to other components of the system. This connection can ensure the stability and sealing of the conduit so as to effectively transmit the working fluid or other fluids. At the same time, the presence of the pad can also provide support and structural support for the conduit, enhancing the stability and reliability of the system.

[0024] In any of the above technical solutions, a liquid storage device is provided in the propellant tank.

[0025] The liquid storage device can be used to store working fluid for use by the system. This ensures that the system can provide sufficient propellant when needed to ensure the normal operation and propulsion effect of the system. The existence of the liquid storage device can improve the reliability and stability of the system, allowing the pocket cubic satellite micro-propulsion system to continuously carry out propulsion tasks. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the technical solutions of the embodiments of the utility model, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0027] Figure 1 Schematic diagram of a pocket-sized cubic satellite micro-propulsion system according to some embodiments of the present invention;

[0028] Figure 2 Schematic diagram of flow regulators of some embodiments provided by the utility model;

[0029] Figure 3 Schematic diagram of micro heaters according to some embodiments of the present invention.

[0030] in, Figures 1 to 3 The corresponding relationship between the reference numerals and the component names is as follows:

[0031] 100 - shell, 200 - propellant box, 300 - conduit, 400 - flow regulator, 410 - flow regulating hole, 500 - micro heater, 600 - evaporator, 610 - micro nozzle, 700 - sealing plate, 710 - first through hole, 800 - pad, 810 - second through hole, 900 - first gasket. DETAILED DESCRIPTION

[0032] In order to make the above-mentioned purposes, features and advantages of the utility model more obvious and easy to understand, the specific embodiments of the utility model are described in detail below in conjunction with the accompanying drawings. It should be noted that the embodiments of the present application and the features in the embodiments can be combined with each other without conflict. In the following description, many specific details are set forth to facilitate a full understanding of the utility model, but the utility model can also be implemented in other ways different from those described herein, and therefore, the scope of protection of the utility model is not limited by the specific embodiments disclosed below.

[0033] Refer to the following Figures 1 to 3 The technical solutions of some embodiments of the utility model are described.

[0034] like Figure 1 , Figure 2 As shown, an embodiment of the utility model provides a pocket-sized cubic satellite micro-propulsion system, which includes: a shell 100; a propellant tank 200, which is arranged in the shell 100, and the propellant tank 200 stores working fluid, and the propellant tank 200 is provided with a liquid storage device; a conduit 300, which is in contact with the propellant tank 200; a flow regulator 400, which is located between the flow regulator 400 and the propellant tank 200, and the flow regulator 400 is provided with a plurality of flow regulating holes 410.

[0035] In this embodiment, the propellant tank 200 has a groove, and one end of the conduit 300 is embedded in the groove. The size of the groove is consistent with the size of one end of the conduit 300. This end of the conduit 300 can fully contact the propellant tank 200, so that the working fluid in the propellant tank 200 can flow into the conduit 300. Preferably, the conduit 300 can be made of a porous glass tube material to play a filtering and blocking role. By selecting a suitable pore size, solid particles or other impurities can be prevented from entering the conduit, thereby protecting the micro-nozzle and other key components inside the system from blockage or damage, and the glass material has good corrosion resistance to ensure the overall safety and stability of the system. A liquid storage device is provided in the propellant tank 200, which is mainly used to store the working fluid. Preferably, the working fluid can use fluorocarbon liquid. This type of liquid has the unique properties of low latent heat of evaporation, high liquid density, non-flammable, and resistance to thermal decomposition and hydrolysis, which meets the requirements of the working fluid. The liquid storage device can use polyimide porous foam, which can store the working fluid and eliminate the shaking under microgravity to improve the stability and safety of the system. The working fluid in the propellant tank 200 enters the conduit 300 through capillary action, then enters the flow regulator 400, and enters the next component through the flow regulating hole 410 on the flow regulator 400. Preferably, the flow regulator 400 can use porous glass, and its porosity can be customized to achieve the effect of regulating the flow.

[0036] like Figure 1 , Figure 3 As shown, the pocket cubic satellite micro propulsion system also includes: a micro heater 500, which is located on the side of the flow regulator 400 away from the conduit 300; an evaporator 600, which is located between the micro heater 500 and the flow regulator 400, the evaporator 600 is provided with a plurality of micro nozzles 610, and a first gasket 900 is provided between the evaporator 600 and the flow regulator 400.

[0037] In this embodiment, the right side of the flow regulator 400 is in contact with the conduit 300, the left side of the flow regulator 400 is in direct contact with the first gasket 900, the other side of the first gasket 900 is in direct contact with the right side of the evaporator 600, and the other side of the evaporator 600 is in direct contact with the micro heater 500. The working fluid enters the evaporator 600 from the through hole in the middle of the first gasket 900 through the conduit 300 via the flow regulator 400, and the micro heater 500 is heated by electricity to heat the evaporator 600. The working fluid on the evaporator 600 is slightly heated to form gas, which is ejected from the micro nozzle 610 in the center circle of the evaporator 600. The micro heater 500 is annular, and the area inside the annular ring is not less than the area of ​​the micro nozzle 610 in the center circle of the evaporator 600, so as to ensure that the gas ejected from the micro nozzle 610 can pass through the ejection device of the micro heater 500 without being blocked, so as to achieve the effect of jet propulsion. Preferably, the microheater 500 can use a ceramic ring microheater, the ceramic structure has good thermal conductivity and corrosion resistance, and the microheater 500 is electrically powered for heating. Preferably, the first gasket 900 can use expanded polytetrafluoroethylene material, which has good sealing and elasticity. Preferably, the evaporator 600 can use an aluminum nitride sheet with a series of laser-drilled micronozzles. Aluminum nitride has high thermal conductivity, good chemical resistance and oxidation resistance, and the number and size of the micronozzles can be customized to generate different levels of thrust.

[0038] like Figure 1 As shown, the pocket cubic satellite micro-propulsion system also includes: a sealing plate 700, which is located between the flow regulator 400 and the propellant tank 200; the sealing plate 700 is provided with a first through hole 710, and the conduit 300 passes through the first through hole 710.

[0039] In this embodiment, the conduit 300 passes through the first through hole 710, and the size of the first through hole 710 is adapted to the size of the conduit 300. The sealing plate 700 is provided with a groove, and the flow regulator 400, the first gasket 900, the evaporator 600, and the micro heater 500 are stacked in sequence and placed in the groove. The sealing plate 700 blocks and seals the propellant tank 200 and the flow regulator 400 and other devices to prevent unnecessary consumption caused by leakage of the working fluid.

[0040] like Figure 1 As shown, the pocket cubic satellite micro-propulsion system also includes: a pad 800, which is arranged between the sealing plate 700 and the propellant box 200; the pad 800 is provided with a second through hole 810, and the catheter 300 passes through the second through hole 810.

[0041] In this embodiment, the pad 800 is located between the sealing plate 700 and the propellant tank 200, and the conduit 300 passes through the second through hole 810, and the size of the second through hole 810 is adapted to the size of the conduit 300. The pad 800 is elastic and can absorb the collision and extrusion between the sealing plate 700 and the propellant tank 200, thereby improving the overall safety and stability of the system.

[0042] In the present invention, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance; the term "plurality" refers to two or more, unless otherwise clearly defined. The terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense. For example, "connected" can be a fixed connection, a detachable connection, or an integral connection; "connected" can be a direct connection or an indirect connection through an intermediate medium. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to the specific circumstances.

[0043] In the description of the present invention, it is necessary to understand that the terms "upper" and "lower" etc. indicating directions or positional relationships are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or unit referred to must have a specific direction, be constructed and operated in a specific direction. Therefore, it cannot be understood as a limitation on the present invention.

[0044] In the description of this specification, the description of the terms "one embodiment", "some embodiments", "specific embodiments", etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the utility model. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0045] Although the utility model is disclosed as above, the utility model is not limited thereto. Any person skilled in the art can make various changes and modifications without departing from the spirit and scope of the utility model. Therefore, the protection scope of the utility model shall be subject to the scope defined by the claims.

Claims

1. A pocket-sized cubic satellite micro-propulsion system, characterized in that: include: Housing (100); a propellant box (200), the propellant box (200) being arranged in the housing (100), and the propellant box (200) storing a working fluid; a conduit (300), the conduit (300) being in contact with the propellant tank (200); A flow regulator (400), the conduit (300) is located between the flow regulator (400) and the propellant tank (200), and the flow regulator (400) is provided with a plurality of flow regulating holes (410).

2. The pocket-sized cubic satellite micro-propulsion system according to claim 1, characterized in that: Also includes: A micro heater (500), wherein the micro heater (500) is located on a side of the flow regulator (400) away from the conduit (300).

3. The pocket-sized cubic satellite micro-propulsion system according to claim 2, characterized in that: Also includes: An evaporator (600), wherein the evaporator (600) is located between the micro-heater (500) and the flow regulator (400).

4. The pocket-sized cubic satellite micro-propulsion system according to claim 3, characterized in that: A first gasket (900) is provided between the evaporator (600) and the flow regulator (400).

5. The pocket-sized cubic satellite micro-propulsion system according to claim 3, characterized in that: The evaporator (600) is provided with a plurality of micro nozzles (610).

6. The pocket-sized cubic satellite micro-propulsion system according to claim 1, characterized in that: Also includes: A sealing plate (700), wherein the sealing plate (700) is located between the flow regulator (400) and the propellant tank (200).

7. The pocket-sized cubic satellite micro-propulsion system according to claim 6, characterized in that: The sealing plate (700) is provided with a first through hole (710), and the conduit (300) passes through the first through hole (710).

8. The pocket-sized cubic satellite micro-propulsion system according to claim 6, characterized in that: Also includes: A backing plate (800), wherein the backing plate (800) is arranged between the sealing plate (700) and the propellant tank (200).

9. The miniature cubic satellite micro-propulsion system according to claim 8, characterized in that: The pad (800) is provided with a second through hole (810), and the conduit (300) passes through the second through hole (810).

10. The pocket-sized cubic satellite micro-propulsion system according to claim 1, characterized in that: A liquid storage device is provided in the propellant box (200).

Images