Cubesat with micro propelling device

Abstract

The utility model provides a cubesat with a miniature propelling device, which comprises a body, a first mounting position, a second mounting position and a power device, and is characterized in that at least one side of the body is provided with a first mounting position; the micro propelling device is arranged at the first mounting position and is used for applying thrust to the body; the miniature propelling device comprises a shell, a first driving device and a second driving device, the liquid storage part is arranged in the shell; the driving part is arranged in the shell and located on the side, away from the first mounting position, of the liquid storage part; wherein the working liquid stored in the liquid storage part is transmitted to the driving part, the driving part decomposes the working liquid, and thrust acting on the body is generated. The technical problem to be solved by the utility model is that the cubesat mostly adopts an attitude determination and control system (ADCS) to carry out conventional attitude adjustment in the prior art, but although the ADCS can cope with daily attitude control tasks, if an emergency occurs, the ADCS is slow in response speed, and the cubesat cannot rapidly avoid.

Description

Technical Field

[0001] The utility model relates to the technical field of cubic satellites, and in particular to a cubic satellite with a micro propulsion device. Background Art

[0002] As the number of satellites in orbit continues to grow, the risk of on-orbit collisions is increasing, and the space debris produced after the collision may further aggravate the "Kessler syndrome", a chain reaction of collisions of space debris.

[0003] However, there is at least one of the following problems in the related art: CubeSats in the related art mostly use an attitude determination and control system (ADCS) for routine attitude adjustments. Although the ADCS system can handle daily attitude control tasks, if an emergency occurs, the response speed of the ADCS system is too slow, which can easily cause the CubeSat to be unable to quickly avoid an emergency. Utility Model Content

[0004] The technical problem solved by the present invention is that most CubeSats in related technologies use an attitude detection and control system (ADCS) for routine attitude adjustments. Although the ADCS system can handle daily attitude control tasks, if an emergency occurs, the response speed of the ADCS system is too slow, which can easily make it impossible for the CubeSat to quickly avoid an emergency.

[0005] To solve the above problems, the present invention provides a CubeSat with a micro-propulsion device, comprising: a main body, at least one side of the main body being provided with a first mounting position; a micro-propulsion device, the micro-propulsion device being arranged at the first mounting position and being used to apply thrust to the main body; the micro-propulsion device comprising: a shell, the shell being provided at the first mounting position; a liquid storage portion, the liquid storage portion being provided in the shell; a drive portion, the drive portion being provided in the shell and being located on a side of the liquid storage portion away from the first mounting position; wherein the working fluid stored in the liquid storage portion is transferred to the drive portion, the drive portion decomposes the working fluid and generates thrust acting on the main body.

[0006] Compared with the existing technology, the technical effect achieved by adopting this technical solution is as follows: the CubeSats in the related technology mostly adopt the ADCS system to adjust their operating posture, but the ADCS system can only cope with daily posture adjustments. If an emergency situation occurs, such as the CubeSat is about to have an orbital collision, the response speed of the ADCS system is too slow to make a quick avoidance. Therefore, the present invention installs a micro-propulsion device for changing the attitude of the CubeSat on the CubeSat. By installing the micro-propulsion device on the first mounting position of the CubeSat body, the driving part of the micro-propulsion device decomposes the working liquid stored in the liquid storage part of the micro-propulsion device into tiny droplets, and sprays them at high speed in any direction away from the mounting position to generate thrust, thereby pushing the CubeSat body to change its operating orbit, thereby avoiding the CubeSat from colliding with other micro-satellites on orbit.

[0007] In one example of the present invention, the liquid storage portion includes: a first storage box; a second installation position, the second installation is arranged on a side of the first storage box close to the first installation position; a first liquid storage, the first liquid storage is located in the second installation position and has self-absorption.

[0008] Compared with the existing technology, the technical effect achieved by adopting this technical solution is: the first storage box is used to store the working liquid, and the first liquid storage is used to absorb the working liquid; the first liquid storage is installed in the second installation position of the first storage box, providing a reliable working liquid storage method for the micro propulsion device.

[0009] In one example of the present invention, the micro-propulsion device also includes: a first sealing portion, the first sealing portion is located on a side of the first storage box close to the first installation position; a second sealing portion is located on a side of the first storage box away from the first installation position; the first sealing portion and the second sealing portion are both connected to the first storage box.

[0010] Compared with the existing technology, the technical effect achieved by adopting this technical solution is: a first sealing part and a second sealing part are provided, and leakage of the working liquid in the liquid storage part is prevented by clamping the two sides in the middle, and the overall volume of the micro propulsion device is further reduced.

[0011] In one embodiment of the present invention, the first sealing portion includes: a first sealing member, which is provided on a side of the second installation position close to the first installation position; and a first cover, which is provided on a side of the first sealing member close to the first installation position.

[0012] Compared with the existing technology, the technical effect achieved by adopting this technical solution is: through the close cooperation between the first cover body and the first seal arranged on the same side, it is ensured that the working liquid will not leak from the side where the liquid storage part is connected to the installation position, thereby ensuring the sealing of the overall structure of the cubic satellite.

[0013] In one embodiment of the present invention, the second sealing portion includes: at least one second sealing member located on a side of the first storage box away from the second installation position; and a second cover located on a side of the second sealing member away from the first storage box.

[0014] Compared with the existing technology, the technical effect achieved by adopting this technical solution is: it is clarified that at least one second seal and a second cover are provided on the side of the liquid storage part away from the installation position, further preventing the working liquid from leaking from the side of the liquid storage part away from the installation position, thereby ensuring the sealing of the overall structure of the cubic satellite.

[0015] In one example of the present invention, a third mounting position is provided on a side of the first storage box away from the first mounting position; the driving part includes: an atomizer, which is located between the second sealing member and the second cover body; wherein, by applying an extrusion force to the second cover body, the atomizer is pressed into the third mounting position and sealed.

[0016] Compared with the existing technology, the technical effect achieved by adopting this technical solution is: by applying extrusion pressure to the second cover body, the atomizer is fixed in the third installation position of the first storage box, the atomizer is sealed, and the working liquid is prevented from leaking, and it can be ensured that the working liquid can be effectively atomized and generate thrust, thereby improving the performance of the micro-propulsion device. On the other hand, by applying extrusion pressure to the atomizer by the second cover body to fix it in the third installation position, the overall volume of the micro-propulsion device can be further reduced.

[0017] In one embodiment of the present invention, the first storage box is provided with a first through hole; the second sealing member is provided with a second through hole; wherein the working liquid in the first liquid storage box flows through the first through hole and the second through hole to the atomizer.

[0018] Compared with the existing technology, the technical effect achieved by adopting this technical solution is: by setting the first through hole and the second through hole, a circulation channel is provided for the working liquid to flow from the first liquid storage to the atomizer, ensuring that the micro propulsion device can generate continuous thrust.

[0019] In an embodiment of the present invention, the first storage box is provided with a limiting groove; the atomizer is provided with a matching piece, and the matching piece is located in the limiting groove.

[0020] Compared with the existing technology, the technical effect achieved by adopting this technical solution is: by setting a limit groove that cooperates with the atomizer matching part, the atomizer is fixed in the limit groove, which can prevent the atomizer from moving, ensuring the stability and reliability of the micro-propulsion device, and preventing the occurrence of unstable thrust of the micro-propulsion device due to movement of the atomizer.

[0021] In an example of the present invention, the first cover, the second cover, the first storage box and the first sealing member are connected by bolts.

[0022] In one embodiment of the present invention, the CubeSat further includes a control circuit board connected to the atomizer.

[0023] Compared with the existing technology, the technical effect achieved by adopting this technical solution is as follows: Since the atomizer requires a high-frequency driving signal to work, a control circuit board is set on the CubeSat. By controlling the control circuit board, a high-frequency driving signal is provided according to the actual situation of the CubeSat to ensure the efficient operation of the atomizer and realize precise control of the micro-propulsion device, so that the CubeSat can accurately adjust its attitude according to the actual situation, thereby improving the autonomous control capability of the CubeSat.

[0024] After adopting the technical solution of the utility model, the following technical effects can be achieved:

[0025] (1) The present invention installs a micro-propulsion device on a CubeSat for changing the attitude of the CubeSat. By installing the micro-propulsion device on the installation position of the CubeSat, the driving part of the micro-propulsion device decomposes the working liquid stored in the liquid storage part of the micro-propulsion device into tiny droplets, and sprays them in any direction away from the installation position at high speed to generate thrust, thereby changing the orbit of the CubeSat and avoiding collision between the CubeSat and other micro-droplets on orbit.

[0026] (2) By providing the first sealing portion and the second sealing portion, leakage of the working fluid in the liquid storage portion is prevented by clamping the two sides inward, and the overall volume of the propulsion device is further reduced;

[0027] (3) By applying a squeezing force to the second cover body, the atomizer is fixed in the third mounting position of the first storage box, so that the atomizer is sealed to prevent leakage of the working liquid, and can ensure that the working liquid can be effectively atomized and generate thrust, thereby improving the performance of the propulsion device. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following briefly introduces the drawings to be used in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. Those skilled in the art can also derive other drawings based on these drawings without inventive efforts.

[0029] Figure 1 A schematic structural diagram of a CubeSat with a micro-propulsion device provided in an embodiment of the present utility model;

[0030] Figure 2 A schematic structural diagram of a micro propulsion device provided in an embodiment of the present utility model;

[0031] Figure 3 for Figure 2Exploded view of;

[0032] Figure 4 A schematic structural diagram of a first storage box provided in an embodiment of the present utility model;

[0033] Figure 5 This is a schematic structural diagram of the atomizer provided in an embodiment of the utility model.

[0034] Description of reference numerals:

[0035] 100. CubeSat; 10. Main body; 11. First mounting position; 12. Panel; 20. Micro propulsion device; 21. Liquid storage unit; 211. First storage box; 212. First liquid storage; 213. Second mounting position; 214. Third mounting position; 215. First through hole; 216. Limiting groove; 22. Driving unit; 221. Atomizer; 222. Fitting part; 23. First sealing unit; 231. First cover; 232. First sealing member; 24. Second sealing unit; 241. Second cover; 242. Second sealing member; 243. Second through hole; 244. Third through hole. DETAILED DESCRIPTION

[0036] The following describes in detail embodiments of the present invention. Examples of the embodiments are shown in the accompanying drawings, in which the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention and are not to be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by a person of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0037] In the description of this utility model, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood in a broad sense. For example, they may refer to fixed connection, connection, or integral connection; they may refer to mechanical connection or electrical connection; they may refer to direct connection or indirect connection through an intermediate medium; and they may refer to internal communication between two components. Those skilled in the art will be able to understand the specific meanings of the above terms in this utility model based on the specific circumstances.

[0038] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, specific embodiments of the present invention are described in detail below with reference to the accompanying drawings.

[0039] See also Figure 1 , Figure 1 A schematic structural diagram of a cubic satellite with a micro-propulsion device provided by an embodiment of the present utility model; Figures 2 to 5Specifically, a CubeSat 100 with a micro-propulsion device includes: a main body 10 and a micro-propulsion device 20; wherein, a first mounting position 11 is provided on at least one side of the main body 10; the micro-propulsion device 20 is arranged at the first mounting position 11, and is used to apply thrust to the main body 10; the micro-propulsion device 20 includes: a shell, a liquid storage portion 21 and a driving portion 22; the shell is provided at the first mounting position 11; the liquid storage portion 21 is provided in the shell; the driving portion 22 is provided in the shell and is located on a side of the liquid storage portion 21 away from the first mounting position 11; wherein, the working liquid stored in the liquid storage portion 21 is transferred to the driving portion 22, and the driving portion 22 decomposes the working liquid and generates thrust acting on the main body 10.

[0040] Preferably, the working liquid is a liquid that needs to have multiple suitable properties, such as high evaporation temperature, low viscosity, low vapor pressure, etc.

[0041] Preferably, the working liquid includes high viscosity silicone oil, propylene carbonate, ether, etc.

[0042] Furthermore, the body 10 is composed of a frame and a plurality of panels 12; the first installation position 11 is located on at least one side of the frame.

[0043] Preferably, the number of micro propulsion devices 20 is the same as the number of first installation positions 11 .

[0044] Preferably, each panel 12 is provided with at least one first installation position 11 .

[0045] Preferably, the number of first installation positions 11 is 4 or 8.

[0046] When there are eight first mounting positions 11, preferably one is provided for each panel 12, and one is provided at the connection between any two adjacent panels 12. By providing multiple first mounting positions 11 and micro-propulsion devices corresponding to the first mounting positions 11, the posture of the cube satellite 100 can be adjusted more accurately.

[0047] Furthermore, the liquid storage portion 21 includes: a first storage box 211 , a second installation position 213 and a first liquid storage 212 ; the second installation position 213 is provided on a side of the first storage box 211 close to the first installation position 11 ; the first liquid storage 212 is located in the second installation position 213 .

[0048] Preferably, the first liquid storage 212 has self-absorbent properties.

[0049] Preferably, the first liquid storage 212 is a porous carbon sponge; the porous carbon sponge is composed of a large number of tiny pores, which are interconnected to form a complex three-dimensional network structure. This structure gives the porous carbon sponge excellent adsorption properties, enabling it to store a large amount of working liquid; on the other hand, in the space environment, the CubeSat 100 will be subject to various vibrations and impacts, and the elastic deformation characteristics of the porous carbon sponge can play a buffering role, protecting the working liquid from external impacts, and also overcome the problem of complex pumping equipment required to transport the working liquid in traditional propulsion systems, and realize passive transmission through capillary action, thereby simplifying the overall structure of the CubeSat 100.

[0050] Furthermore, the storage of the working liquid in the porous carbon sponge is achieved through capillary action, that is, the phenomenon of the liquid automatically rising in tiny pores; in the porous carbon sponge, since the size of the voids is very small, the adhesion between the liquid and the pores is greater than the cohesive force of the liquid itself, allowing the working liquid to be adsorbed and stored in the pores. This passive transmission method does not require external power.

[0051] In combination with the actual use of the present invention, preferably, the porous carbon sponge can accommodate 5-8 ml of working liquid, providing a larger working liquid storage capacity for the micro-propulsion device 20, ensuring that the CubeSat 100 can have enough liquid to generate thrust when needed, thereby extending the working time of the micro-propulsion device 20.

[0052] Furthermore, the micro-propulsion device 20 also includes: a first sealing portion 23 and a second sealing portion 24; the first sealing portion 23 is located on the side of the first storage box 211 close to the first installation position 11; the second sealing portion 24 is located on the side of the first storage box 211 away from the first installation position 11; the first sealing portion 23 and the second sealing portion 24 are both connected to the first storage box 211.

[0053] Specifically, the first sealing portion 23 includes a first sealing member 232 and a first cover 231. The first sealing member 232 is located on the side of the second mounting position 213 that is closer to the first mounting position 11. The first cover 231 is located on the side of the first sealing member 232 that is closer to the first mounting position 11. The second sealing portion 24 includes at least one second sealing member 242 and a second cover 241. The second sealing member 242 is located on the side of the first storage box 211 that is away from the second mounting position 213. The second cover 241 is located on the side of the second sealing member 242 that is away from the first storage box 211.

[0054] Furthermore, a third mounting position 214 is provided on a side of the first storage box 211 away from the first mounting position 11; the driving part 22 includes: an atomizer 221, and the atomizer 221 is located between the second sealing member 242 and the second cover body 241; wherein, by applying an extrusion force to the second cover body 241, the atomizer 221 is pressed into the third mounting position 214 and sealed to prevent leakage of the working liquid.

[0055] Preferably, in order to ensure the sealing of the micro-propulsion device 20 in a vacuum environment, the first cover body 231 is a stainless steel plate, and the first seal 232 and the second seal 242 are both ePTFE sealing gaskets. ePTFE has good chemical stability, elastic deformation properties and high temperature resistance. Combined with its specific usage, the ePTFE sealing gasket, due to its special microstructure and material properties, can make the ePTFE gasket fit tightly to the sealing surface when under pressure, forming a reliable seal.

[0056] Preferably, the atomizer 221 is a vibrating mesh atomizer.

[0057] Preferably, at least one second seal 242 is provided on both the side of the atomizer 221 close to the first storage box 211 and the side away from the first storage box 211, which can ensure that the working liquid does not leak when the atomizer 221 is pressed onto the first storage box 211 and covered.

[0058] Furthermore, the first storage box 211 is provided with a first through hole 215, the second sealing member 242 is provided with a second through hole 243, and the second cover body 241 is provided with a third through hole 244; wherein, the working liquid in the first liquid storage 212 flows through the first through hole 215 and the second through hole 243 to the atomizer 221, so that the working liquid can be smoothly transported from the first storage box 211 to the atomizer 221. After the working liquid is decomposed by the atomizer 221, it is ejected from the third through hole 244 of the second cover body 241 to form thrust.

[0059] Preferably, a limiting groove 216 is provided on the second installation position 213 of the first storage box 211; the atomizer 221 is provided with a matching piece 222, and the matching piece 222 is located in the limiting groove 216, which is used to limit the movement of the atomizer 221 to ensure the stability of the micro propulsion device.

[0060] Preferably, the first cover 231 , the second cover 241 , the first storage box 211 and the first sealing member 232 are connected by bolts.

[0061] Furthermore, the CubeSat 100 also includes: a control circuit board, which is connected to the atomizer 221. The control circuit board sends a high-frequency driving signal to the atomizer 221 to ensure that the atomizer 221 works efficiently and can achieve precise control of the micro-propulsion device, so that the CubeSat 100 can accurately adjust its posture according to actual conditions.

[0062] In combination with actual usage, this example uses a cube satellite 100 equipped with four micro propulsion devices 20 as an example for explanation. The cube satellite 100 of the utility model has a size of 18mm*18mm*10mm and weighs only 8 grams. The main component of the cube satellite 100 is a 13.5 mm vibrating mesh atomizer with an operating frequency of 160KHz. An ePTEF sealing gasket is installed on each side of the vibrating mesh atomizer. When the vibrating mesh atomizer is pressed onto the first storage box 211 and covered, it can ensure that the working liquid will not leak; when thrust is needed to change the direction or orbit of the main body 10, combined with the porous carbon sponge storing the working liquid in the first storage box 211, a high-frequency driving signal is provided to the vibrating mesh atomizer through the control circuit board, and the working liquid is passively drawn out by capillary action. The porous carbon sponge transmits the working liquid to the vibrating mesh atomizer through the first through hole 215 and the second through hole 243. The vibrating mesh atomizer decomposes the working liquid into tiny droplets. These tiny droplets can quickly evaporate or burn to generate instantaneous high-speed injection to form a thrust for propelling the main body 10. Each micro-propulsion device 20 consumes about 0.7W of power and can work continuously for about one minute, generating a thrust of about 350 micronewtons until the working liquid is completely consumed, thereby changing the current attitude or current driving orbit of the CubeSat 100, thereby avoiding its collision with other satellites.

[0063] Although the present invention is disclosed as above, it is not limited thereto. Any person skilled in the art may make various changes and modifications without departing from the spirit and scope of the present invention. Therefore, the scope of protection of the present invention shall be subject to the scope defined by the claims.

Claims

1. A CubeSat with a micro-propulsion device, characterized in that: include: A body (10), wherein at least one side of the body (10) is provided with a first mounting position (11); a micro-propulsion device (20), the micro-propulsion device (20) being arranged at the first installation position (11) and being used to apply thrust to the body (10); The micro propulsion device (20) comprises: a housing, the housing being arranged at the first mounting position (11); a liquid storage portion (21), the liquid storage portion (21) being disposed in the housing; a driving portion (22), the driving portion (22) being disposed in the housing and located on a side of the liquid storage portion (21) away from the first installation position (11); The working liquid stored in the liquid storage portion (21) is transferred to the driving portion (22), and the driving portion (22) decomposes the working liquid to generate the thrust acting on the body (10).

2. The CubeSat according to claim 1, wherein: The liquid storage part (21) includes: a first storage box (211); a second installation position (213), the second installation being provided on a side of the first storage box (211) close to the first installation position (11); A first liquid storage (212), wherein the first liquid storage (212) is located in the second installation position (213) and has self-water absorption.

3. The CubeSat according to claim 2, wherein: The micro propulsion device (20) further includes: a first sealing portion (23), the first sealing portion (23) being located on a side of the first storage box (211) close to the first installation position (11); a second sealing portion (24), the second sealing portion (24) being located on a side of the first storage box (211) away from the first installation position (11); The first sealing portion (23) and the second sealing portion (24) are both connected to the first storage box (211).

4. The CubeSat according to claim 3, wherein: The first sealing portion (23) comprises: a first sealing member (232), the first sealing member (232) being arranged on a side of the second installation position (213) close to the first installation position (11); A first cover body (231), the first cover body (231) is arranged on a side of the first sealing member (232) close to the first installation position (11).

5. The CubeSat according to claim 4, wherein: The second sealing portion (24) comprises: at least one second sealing member (242), the second sealing member (242) being located on a side of the first storage box (211) away from the second installation position (213); A second cover (241), the second cover (241) is located on a side of the second sealing member (242) away from the first storage box (211).

6. The CubeSat according to claim 5, wherein: A third installation position (214) is provided on a side of the first storage box (211) away from the first installation position (11); The driving unit (22) includes: an atomizer (221), the atomizer (221) being located between the second sealing member (242) and the second cover (241); Wherein, by applying a squeezing force to the second cover (241), the atomizer (221) is pressed into the third installation position (214) and sealed.

7. The CubeSat according to claim 6, wherein: The first storage box (211) is provided with a first through hole (215); The second sealing member (242) is provided with a second through hole (243); The working liquid in the first liquid storage (212) flows through the first through hole (215) and the second through hole (243) to the atomizer (221).

8. The CubeSat according to claim 6 or 7, characterized in that: The first storage box (211) is provided with a limiting groove (216); The atomizer (221) is provided with a matching piece (222), and the matching piece (222) is located in the limiting groove (216).

9. The CubeSat according to claim 8, wherein: The first cover body (231), the second cover body (241), the first storage box (211) and the first sealing member (232) are connected via bolts.

10. The CubeSat according to claim 6, wherein: The CubeSat also includes: A control circuit board is connected to the atomizer (221).

Images