A satellite propulsion device and control method thereof

Abstract

The invention discloses a satellite propulsion device and a control method thereof. The satellite propulsion device comprises a shell, a drainage core, an oscillating atomization component, a heating component, a humidity monitoring component and an electric propulsion controller. A storage chamber for storing propellant is formed in the hollow of the shell; a guide channel is provided on the side wall of the storage chamber; the drainage core is arranged in the storage chamber; the end of the drainage core is inserted into the guide channel; the oscillating atomization component is connected to the shell, arranged at the port of the guide channel, and contacts the drainage core, and is used to atomize and spray the propellant on the end face of the drainage core; the heating component is connected to the shell, arranged on the outer wall of the shell, and is used to melt the propellant; the humidity monitoring component is connected to the shell, and is arranged on the path of the oscillating atomization component spraying liquid particles; the electric propulsion controller is arranged on the shell; the electric propulsion controller is electrically connected to the oscillating atomization component, the heating component, and the humidity monitoring component. Attitude adjustment is achieved by heating and atomizing the propellant, thereby reducing the operating cost of the satellite.

Description

Technical Field

[0001] The present invention relates to the field of satellite propulsion technology, and in particular to a satellite propulsion device and a control method thereof. Background Art

[0002] At present, with the continuous progress of science and technology and the continuous development of aerospace technology, satellites have become an important tool for human beings to explore the universe and serve human life. When satellites perform orbit change, orbit entry, orbit departure, steering and other actions in space, thrusters are usually used as standard configuration. Currently, commonly used thrusters include chemical thrusters, electric thrusters, ion thrusters, etc. Various thrusters are developing towards high precision and high efficiency ratio.

[0003] As the demand for satellites increases, especially as the cost of rocket launches decreases, the low cost of satellites themselves becomes more and more urgent. However, the commonly used thrusters on satellites are complex in structure and consume a lot of fuel, which increases the launch and manufacturing costs and cannot meet the production needs of low manufacturing costs for satellites. Some satellites can only rely on their own atmospheric resistance to achieve deorbit and orbit change without thrusters, but this will affect the flexibility of satellites.

[0004] Therefore, the prior art still needs to be improved and developed. Summary of the invention

[0005] In view of the above-mentioned deficiencies in the prior art, an object of the present invention is to provide a satellite propulsion device and a control method thereof, aiming to solve the problem that existing satellites cannot meet low-cost production requirements due to complex propulsion structures, high production and operating costs.

[0006] The technical solution of the present invention is as follows:

[0007] A satellite propulsion device, which includes a shell, a drainage core, an oscillating atomization component, a heating component, a humidity monitoring component and an electric propulsion controller. The shell is hollow and forms a storage chamber for storing propellant; a guide channel is provided on the side wall of the storage chamber; the drainage core is arranged in the storage chamber; the end of the drainage core is inserted into the guide channel; the oscillating atomization component is connected to the shell, arranged at the port of the guide channel, and contacts the drainage core, and is used to atomize and spray the propellant on the end surface of the drainage core; the heating component is connected to the shell, arranged on the outer wall of the shell, and is used to melt the propellant; the humidity monitoring component is connected to the shell, and is arranged on the path of the oscillating atomization component spraying liquid particles; the electric propulsion controller is arranged on the shell; the electric propulsion controller is electrically connected to the oscillating atomization component, the heating component, and the humidity monitoring component.

[0008] The satellite propulsion device, wherein the drainage core is in the shape of an elongated strip, and the shape of the radial cross section is circular; the shape of the radial cross section of the guide channel is circular; the diameter value of the radial cross section of the drainage core is smaller than the length value of the guide channel.

[0009] The satellite propulsion device described above, wherein a limiting groove is provided on a side of the storage chamber facing away from the guide channel, and the width of the limiting groove is less than or equal to the diameter of the radial cross-section of the drainage core; the drainage core is arranged in the limiting groove, and one end extends out of the limiting groove and contacts with the inner wall of the shell; the other end of the drainage core extends out of the limiting groove, is bent and inserted into the guide channel, and contacts with the oscillating atomization assembly.

[0010] The satellite propulsion device, wherein the material storage chamber includes a connecting area at a central position and a material suction area at an edge position, and the guide channel is arranged in the connecting area; one end of the drainage core is plugged into the guide channel, and the other end extends to a side of the material suction area away from the connecting area.

[0011] In the satellite propulsion device, the guide core is in the shape of a tree branch, and at least two forked sections extending to the inner wall of the shell are formed on one end of the guide core away from the guide channel.

[0012] The satellite propulsion device, wherein the oscillation atomization component includes an ultrasonic oscillation sieve plate and a protective rubber sleeve, wherein the ultrasonic oscillation sieve plate is arranged at the end of the guide channel; the central position of the ultrasonic oscillation sieve plate is aligned with and fits the end face of the drainage core, and the edge position of the ultrasonic oscillation sieve plate is sleeved with the protective rubber sleeve; the protective rubber sleeve is bonded to the shell.

[0013] The satellite propulsion device, wherein the shell is any one of a metal shell, an alloy shell, and a carbon fiber shell; the heating assembly includes a plurality of heating plates, and the plurality of heating plates are evenly distributed on the outer surface of the shell.

[0014] The satellite propulsion device, wherein the shell is filled with a porous absorbent block for absorbing liquid, and the shape of the porous absorbent block is the same as the shape of the storage chamber; the porous absorbent block is provided with a hollow channel aligned with the guide channel, and the hollow channel is used to set the drainage core; the porous absorbent block is also provided with a temperature sensor, and the temperature sensor is communicatively connected to the electric propulsion controller for collecting temperature data of the propellant.

[0015] The satellite propulsion device is characterized in that a mounting seat is protruding from the outer surface of the shell, and the guide channel is formed at the center position of the mounting seat; the oscillating atomization component is arranged on the end surface of the mounting seat; the humidity monitoring component includes a beam tube and a humidity sensor, and the beam tube is trumpet-shaped and is sleeved on the mounting seat; the humidity sensor is arranged on the inner wall of the beam tube and is electrically connected to the electric propulsion controller.

[0016] The present application also discloses a control method for a satellite propulsion device, which is used for any of the satellite propulsion devices described above; wherein, the method comprises:

[0017] Obtaining a satellite control instruction; wherein the satellite control instruction includes any one of a propulsion instruction, a deorbit instruction, and an orbit change instruction;

[0018] Calculate the atomization oscillation period and the atomization interval duration based on the satellite control command, and generate an atomization control command;

[0019] Start the heating component to preheat, then start the oscillating atomization component, and collect real-time data from the humidity monitoring component;

[0020] If the real-time data reaches a preset humidity threshold, the oscillating atomization component is started based on the atomization control instruction.

[0021] Compared with the prior art, the embodiments of the present invention have the following advantages:

[0022] The satellite propulsion device disclosed in the present invention is assembled on the satellite main frame, and the propellant stored in the shell is solid. When the satellite in orbit receives a signal to change orbit or leave orbit, the heating component arranged on the outer surface of the shell is turned on to melt the propellant in the storage chamber. The liquid propellant has fluidity and is absorbed by the drainage core with strong adsorption performance and guided to the oscillating atomization component. The propellant is atomized and sprayed out during the vibration process, thereby generating reverse thrust.

[0023] Moreover, during the operation, the humidity on the spray path of the oscillating atomizing component is detected in real time through the humidity monitoring component. If the humidity is insufficient, it means that the propellant has not melted sufficiently. The oscillating atomizing component can be controlled to pause through the electric propulsion controller and restarted after a period of time, thereby ensuring that the mist output reaches the preset standard and avoiding affecting the propulsion efficiency.

[0024] It can be seen that the present invention melts the propellant and breaks it up into small droplets, which are then sprayed out to form a propulsion force to act on the satellite's orbit change, deorbit and other actions. It has a simple structure, low manufacturing cost, and is easy to implement. It is beneficial to reducing the launch and operation costs of the satellite while ensuring the flexibility of the satellite. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0026] Figure 1 It is a structural schematic diagram of a satellite propulsion device in one embodiment of the present invention;

[0027] Figure 2 An exploded view of the structure of a satellite propulsion device in one embodiment of the present invention;

[0028] Figure 3 It is a structural schematic diagram of a part of the structure of the housing in one embodiment of the present invention;

[0029] Figure 4 A schematic structural diagram of a partial structure of a housing in another embodiment of the present invention from another angle;

[0030] Figure 5 It is a structural schematic diagram of a satellite propulsion device in another embodiment of the present invention;

[0031] Figure 6 It is a schematic structural diagram of a drainage core body in another embodiment of the present invention;

[0032] Figure 7 is a flow chart of a control method for a satellite propulsion device in one embodiment of the present invention;

[0033] Figure 8 Figure (a) is an output power-time diagram of a satellite thruster in the prior art; Figure 8 Figure (b) is an output power-time diagram of a satellite propulsion device in one embodiment of the present invention;

[0034] Fig. 9 1 is a diagram of the orbit change control steps of a satellite propulsion device in one embodiment of the present invention.

[0035] Among them, 10, shell; 11, storage chamber; 12, guide channel; 13, limit groove; 14, mounting seat; 20, drainage core; 30, oscillation atomization component; 31, ultrasonic oscillation sieve plate; 32, protective rubber sleeve; 40, heating component; 41, heating plate; 50, humidity monitoring component; 51, beam tube; 52, humidity sensor; 60, electric propulsion controller; 70, porous liquid absorption block; 71, hollow channel; 80, temperature sensor. DETAILED DESCRIPTION

[0036] In order to enable those skilled in the art to better understand the scheme of the present invention, the technical scheme in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0037] See also Figure 1 , Figure 2 and Figure 3 In one embodiment of the present invention, a satellite propulsion device is disclosed, which includes a shell 10, a drainage core 20, an oscillating atomization component 30, a heating component 40, a humidity monitoring component 50 and an electric propulsion controller 60. The shell 10 is hollow inside and has a storage chamber 11 for storing propellant; a guide channel 12 is provided on the side wall of the storage chamber 11; the drainage core 20 is arranged in the storage chamber 11; and the end of the drainage core 20 is inserted into the guide channel 12. The oscillating atomization component 30 is connected to the shell 10, arranged at the port of the guide channel 12, and contacts the drainage core 20, and is used to atomize and spray the propellant on the end surface of the drainage core 20. The heating component 40 is connected to the shell 10, arranged on the outer wall of the shell 10, and is used to melt the propellant. The humidity monitoring component 50 is connected to the shell 10 and arranged on the path of the oscillating atomization component 30 spraying liquid particles. The electric propulsion controller 60 is disposed on the housing 10 ; the electric propulsion controller 60 is electrically connected to the oscillating atomization component 30 , the heating component 40 , and the humidity monitoring component 50 .

[0038] The satellite propulsion device disclosed in this embodiment is assembled on the satellite main frame and launched into space with a carrier rocket. The propellant stored in the shell 10 is a solid material to improve stability and facilitate high-speed transportation. In the space environment, the satellite operates outside the atmosphere without the protection of the earth's atmosphere, and the working ambient temperature is ± 150 degrees Celsius (the temperature difference range between the direct sun surface and the shadow surface), or a wider range. During on-orbit operation, the propellant remains in a solid state. When the on-orbit satellite receives a change of orbit or a de-orbit signal, the heating component 40 arranged on the outer surface of the shell 10 is turned on to melt the propellant in the storage chamber 11. The liquid propellant has fluidity and is absorbed by the drainage core 20 with strong adsorption performance, and is guided to the oscillating atomization component 30. The propellant is atomized and ejected during the vibration process, thereby generating a reverse thrust.

[0039] For example, water is used as a propellant, cooled into ice on the ground, and filled into the storage chamber 11 and sealed for storage; after the satellite is launched into a low-Earth orbit, if it is necessary to change the orbit, the ice is melted into water by the heating component 40, which can be absorbed by the drainage core 20, atomized by the oscillating atomization component 30 and then sprayed out to generate thrust.

[0040] It should be noted that this embodiment is only an example of the type of propellant. In actual applications, according to the influence of environmental factors, atomization influencing factors, etc., a mixed solution can be configured and the liquefaction point of the mixed solution can be adjusted. Similarly, a work process of storing in a solid state and then melting in the use state can be adopted. In other words, the type of propellant is not limited in this embodiment. As long as the technical effect disclosed in this application can be achieved, as an equivalent replacement of the concept of the present invention, other propellants except water should also be within the scope of protection of this application.

[0041] Specifically, Figure 1 As shown, in this embodiment, the shell 10 is in a cubic shape as a whole, a heating component 40 is arranged on the outside of the shell 10, and the propellant is stored in the shell 10. The heating component 40 directly heats the shell 10 and transfers heat to the propellant through the shell 10 to melt it.

[0042] The shell 10 disclosed in this embodiment is made of heat-conducting material to improve thermal conductivity, quickly melt the propellant when changing orbit, and increase the fluidity of the propellant. For example, a metal shell 10, an alloy shell 10 or a carbon fiber shell 10 can be used. In addition, materials with good thermal conductivity are also conducive to heat dispersion. When the heating component 40 is working, the temperature distribution on the shell 10 is more uniform, which is conducive to uniform heat conduction to the storage chamber 11, thereby uniformly melting the propellant at various positions of the storage chamber 11, avoiding the problem of local unmelted propellant forming obstacles and affecting the flow of liquid propellant. In particular, when the carbon fiber shell 10 is used as the shell 10 in this embodiment, in addition to storing propellant, it can also reduce weight and increase the strength of the shell 10, thereby optimizing the satellite structure.

[0043] like Figure 2 As shown, as another implementation of the present embodiment, the oscillation atomization assembly 30 is disclosed to include an ultrasonic oscillation sieve sheet 31 and a protective rubber sleeve 32, wherein the ultrasonic oscillation sieve sheet 31 is arranged at the end of the guide channel 12; the central position of the ultrasonic oscillation sieve sheet 31 is aligned with and fits the end surface of the drainage core 20, and the edge position of the ultrasonic oscillation sieve sheet 31 is sleeved with the protective rubber sleeve 32; the protective rubber sleeve 32 is bonded to the shell 10.

[0044] This embodiment draws on the working mode of the commonly used atomizer and adopts ultrasonic vibration to perform atomization. Specifically, the ultrasonic oscillation sieve plate 31 includes a piezoelectric ceramic plate and a metal sieve plate with multiple funnel holes. When the piezoelectric ceramic plate is energized, ultrasonic vibration is generated. An oscillation wave of about 100-130KHz can be selected to vibrate the metal sieve plate. The metal sieve plate is attached to the end surface of the drainage core 20, thereby squeezing the liquid from the drainage core 20 and passing through the funnel holes, and dispersed into fine liquid particles to achieve the atomization effect.

[0045] Specifically, the ultrasonic oscillation sieve sheet 31 is arranged opposite to the guide channel 12, and a protective rubber sleeve 32 is sleeved on the edge. The protective rubber sleeve 32 includes but is not limited to a silicone sleeve or a latex sleeve, which plays a role in protecting the ultrasonic oscillation sieve sheet 31, while isolating vibrations to reduce the shaking of the satellite propulsion device and improve the stability of the overall structure.

[0046] Specifically, Figure 2 As shown, the heating assembly 40 in this embodiment includes a plurality of heating plates 41, and the plurality of heating plates 41 are evenly distributed on the outer surface of the housing 10. In this embodiment, a plurality of heating plates 41 are provided to increase the heat source, thereby accelerating the melting of the propellant.

[0047] For example, if the shell 10 is in a cube or a cuboid shape, the outer surface of the shell 10 has eight corners. In this embodiment, eight heating plates 41 can be provided, which are respectively provided at the eight corners and are simultaneously activated during operation to improve the heat transfer efficiency. The shell 10 can also be in a triangular prism shape, and six heating plates 41 can be provided according to the number of corners of the shell 10.

[0048] In summary, the number of heating plates 41 disclosed in this embodiment is adaptively set according to the shape of the shell 10. As long as the technical effect disclosed in this application can be achieved, as an equivalent replacement of the concept of the present invention, other numbers and arrangements of heating plates 41 should also be within the scope of protection of this application.

[0049] Specifically, the heating plate 41 disclosed in this embodiment is a metal heating plate 41, and each heating plate 41 is connected to a wire (not shown in the drawings) to generate heat through electric energy. Preferably, all the heating plates 41 are connected to the electric propulsion controller 60 and are uniformly controlled by the electric propulsion controller 60 to simplify the control process and facilitate operation.

[0050] Specifically, the humidity monitoring component 50 disclosed in the present embodiment detects the humidity on the spray path of the oscillating atomizing component 30 in real time. If the humidity is insufficient, it means that the propellant is not sufficiently melted. The oscillating atomizing component 30 can be controlled to pause through the electric propulsion controller 60 and restarted after a period of time, thereby ensuring that the mist output reaches the preset standard and avoiding affecting the propulsion efficiency.

[0051] The electric propulsion controller 60 disclosed in this embodiment is an integrated circuit printed version, which can be fixed on the outer surface of the housing 10 by bonding, welding or screwing, so as to be connected to the housing 10 as a whole, convenient for transportation, stable during use, and improve the stability of the electric control. The electric propulsion controller 60 mainly controls the electric propulsion related business, that is, it is electrically connected to the oscillating atomization component 30, the heating component 40, and the humidity monitoring component 50. The electric propulsion controller 60 is externally connected to the mission control board of the satellite and communicated through a communication interface such as a serial port.

[0052] In summary, this embodiment melts the propellant and breaks it into small droplets, which are then sprayed out to form propulsion force to act on the satellite's orbit change, deorbit and other actions. It has a simple structure, low manufacturing cost, and is easy to implement. While ensuring the flexibility of the satellite, it is beneficial to reduce the launch and operation costs of the satellite. Moreover, compared with traditional chemical propulsion systems, ion propulsion systems, etc., it can reduce space junk and space debris and purify the space environment.

[0053] like Figure 3 and Figure 4 As shown, as an implementation of this embodiment, it is disclosed that the guide channel 12 is provided with a plurality of guide channels 12, and the plurality of guide channels 12 are arrayed on the side wall of one side of the storage chamber 11, which may be in a circular array, a triangular array, a rectangular array, a radial array, etc. Correspondingly, a plurality of guide cores 20 and oscillating atomization assemblies 30 are provided, each guide core 20 is inserted into a guide channel 12, and a group of oscillating atomization assemblies 30 are provided on the end face of each guide channel 12. According to the propulsion requirements of the satellite, a plurality of oscillating atomization assemblies 30 are arranged at different positions on the shell 10 to provide propulsion forces of different angles and strengths, thereby increasing the flexibility of satellite control, so as to adapt to various application scenarios such as orbit change, deorbit, and steering.

[0054] Specifically, Figure 2 As shown, as another implementation of this embodiment, the drainage core 20 is disclosed to be in the shape of a long strip, and the shape of the radial cross section is circular. The drainage core 20 disclosed in this embodiment can be made of cotton fiber under high pressure, with a circular cross section, and the cotton fiber inside is evenly distributed, reducing the edge concentration or squeezing, so that the water absorption capacity of each part of the drainage core 20 is balanced, and the liquid drainage is smoother, which is conducive to improving the atomization and spraying efficiency.

[0055] Specifically, the radial cross section of the guide channel 12 is circular, and the diameter of the radial cross section of the guide core 20 is smaller than the length of the guide channel 12. In this embodiment, the cross section of the guide channel 12 matches the cross section of the guide core 20, so that the guide core 20 can be assembled smoothly and pass through the entire guide channel 12. In addition, in this embodiment, the guide channel 12 constrains the guide core 20, so that the end surface of the guide core 20 remains in contact with the oscillating atomization assembly 30 to maintain a state of efficient atomization.

[0056] Specifically, the radial cross-section of the drainage core 20 is circular, and the length thereof inserted into the guide channel 12 is larger than the diameter of the radial cross-section. That is to say, the portion of the end of the drainage core 20 inserted into the guide channel 12 is in the shape of a long strip, which is conducive to maintaining a straight extension state and reducing the bending probability of the end of the drainage core 20, thereby ensuring that the liquid can flow smoothly at the end of the drainage core 20, thereby improving the drainage efficiency and maintaining an efficient atomization and spraying state.

[0057] Specifically, the diameter of the radial cross section of the guide channel 12 disclosed in this embodiment is slightly larger than, or equal to, the diameter of the radial cross section of the drainage core 20. In this embodiment, the diameter of the guide channel 12 is set to be slightly larger than, or equal to, the diameter of the drainage core 20, so that the drainage core 20 can be smoothly inserted into the guide channel 12, reducing assembly resistance, and at the same time, the drainage core 20 is constrained by the side wall of the guide channel 12, maintaining good stability and avoiding slipping.

[0058] like Figure 3 As shown, as another implementation of the present embodiment, a limiting groove 13 is disclosed on the side of the storage chamber 11 away from the guide channel 12, and the width value of the limiting groove 13 is less than or equal to the diameter value of the radial cross-section of the drainage core 20; the drainage core 20 is arranged in the limiting groove 13, one end extends out of the limiting groove 13 and contacts with the inner wall of the shell 10; the other end of the drainage core 20 extends out of the limiting groove 13, is bent and inserted into the guide channel 12, and contacts with the oscillating atomization assembly 30.

[0059] In this embodiment, the guide channel 12 is connected to the material storage chamber 11, and must form a certain angle with the side wall of the material storage chamber 11, so the drainage core 20 needs to be bent when extending from the limiting groove 13 to the guide channel 12. By arranging the limiting groove 13 and the guide channel 12 on both sides of the material storage chamber 11, respectively, the extension path of the drainage core 20 spans the material storage chamber 11, so the bending angle is small, avoiding the occurrence of partial transition folding of the drainage core 20, and preventing the water diversion waterway inside the drainage core 20 from being blocked.

[0060] Specifically, in this embodiment, the limiting groove 13 can be formed by digging a hole on the inner wall of the shell 10, or by protruding a baffle on the inner wall of the shell 10. The diameter of the radial cross section of the drainage core 20 is greater than the width of the limiting groove 13, so the drainage core 20 is stuck in the limiting groove 13 by interference fit and can remain stable.

[0061] Specifically, the end of the drainage core 20 extends until it contacts the inner wall of the shell 10 , so that the propellant at the edge of the storage chamber 11 can be absorbed, thereby increasing the utilization rate of the propellant.

[0062] like Figure 6 As shown, as another implementation of this embodiment, the shape of the drainage core 20 is disclosed to be a tree branch shape, and at least two forked sections extending to the inner wall of the shell 10 are formed on the end of the drainage core 20 away from the guide channel 12.

[0063] Since there is no gravity in the space environment, the propellant in the shell 10 is randomly distributed in the storage chamber 11 after melting. In this embodiment, by setting the end of the drainage core 20 to be tree-shaped and increasing the port area, the propellant at multiple positions can be absorbed, thereby improving the absorption efficiency, reducing the deposition waste of the propellant, and increasing the utilization rate.

[0064] It should be noted that the shape of the drainage core 20 is only exemplified in this embodiment, but the protection scope of the present invention is not limited to this. As long as the drainage core 20 of other shapes can achieve the technical effects disclosed in this application, they should also be within the scope of protection of this application as an equivalent replacement of the concept of the present invention.

[0065] Specifically, as another implementation of this embodiment, the material storage chamber 11 is disclosed to include a connection area at a central position and a suction area at an edge position, and the guide channel 12 is arranged in the connection area; one end of the drainage core 20 is plugged into the guide channel 12, and the other end extends to the side of the suction area away from the connection area.

[0066] In this embodiment, the guide channel 12 is arranged in the connection area, located in the center of the storage chamber 11, so that no matter in which direction the drainage core 20 extends, the distance to the suction area can be shortened, so as to reduce the drainage distance of the drainage core 20, improve the suction efficiency, shorten the length of a single drainage core 20, reduce the residual amount of propellant in the drainage core 20, and increase the utilization ratio of the propellant in the storage chamber 11.

[0067] Specifically, in this embodiment, the end of the drainage core 20 extends to the farthest position of the suction area away from the connection area, so as to absorb the propellant to the edge as much as possible to reduce residual waste. In addition, the heating component 40 is arranged on the outer surface of the shell 10, and the heat is transferred from the outside to the inside, so the propellant at the edge of the storage chamber 11 melts first. The end of the drainage core 20 is arranged in the suction area at the edge, which can quickly absorb the melted propellant and guide the propellant to the oscillating atomization component 30 for atomization as soon as possible, so as to quickly respond to the track change instruction and speed up the atomization process.

[0068] For example Figure 5 As shown, as another implementation of this embodiment, the shell 10 is filled with a porous absorbent block 70 for absorbing liquid, and the shape of the porous absorbent block 70 is the same as the shape of the storage chamber 11; the porous absorbent block 70 is provided with a hollow channel 71 aligned with the guide channel 12, and the hollow channel 71 is used to set the drainage core 20; the porous absorbent block 70 is also provided with a temperature sensor 80, and the temperature sensor 80 is communicatively connected with the electric propulsion controller 60 for collecting temperature data of the propellant.

[0069] In this embodiment, the porous liquid-absorbing block 70 includes but is not limited to materials with good water absorption performance such as sponges, water-absorbing resins, and water-absorbing fibers. Water-absorbing resins such as polyacrylamide-based water-absorbing resins and polyacrylamide adenate-based water-absorbing resins are in a gel state after absorbing moisture and have good water-retaining capacity; water-absorbing fibers such as cellulose fibers and wood fibers have water-locking capacity and low manufacturing costs, and can be manufactured into various shapes according to usage requirements, which is convenient for processing.

[0070] The porous absorbent block 70 disclosed in this embodiment first fully absorbs liquid and then solidifies into a solid state for storage. When in use, the porous absorbent block 70 fully absorbed with propellant is loaded into the storage chamber 11 and launched into space with the satellite; when the heating component 40 generates heat, the propellant in the porous absorbent block 70 melts and is evenly distributed in the porous absorbent block 70. The drainage core 20 is arranged in the hollow channel 71. Since the drainage core 20 has better liquid absorption performance, the propellant on the porous absorbent block 70 gradually flows toward the drainage core 20 and is adsorbed by the drainage core 20.

[0071] It can be seen that this embodiment further ensures the uniform distribution of the propellant by arranging a porous liquid absorption block 70 in the storage chamber 11, reduces the local deposition of the propellant, and thus makes it easier for the drainage core 20 to absorb the propellant in a zero-gravity environment, thereby achieving the effect of improving the atomization efficiency.

[0072] For example Figure 5As shown, a temperature sensor 80 is also provided in the porous liquid absorbing block 70. The data sent by the temperature sensor 80 can accurately determine the temperature in the storage chamber 11, and then the working time of the heating component 40 can be accurately controlled to ensure that the oscillating atomizing component 30 is started for atomization after the propellant melts.

[0073] like Figure 2 , Figure 3 and Figure 4 As shown, as another implementation of this embodiment, a mounting seat 14 is protrudingly provided on the outer surface of the shell 10, and the guide channel 12 is formed at the center position of the mounting seat 14; the oscillation atomization assembly 30 is arranged on the end face of the mounting seat 14; the humidity monitoring assembly 50 includes a beam tube 51 and a humidity sensor 52, and the beam tube 51 is trumpet-shaped and is sleeved on the mounting seat 14; the humidity sensor 52 is arranged on the inner wall of the beam tube 51 and is electrically connected to the electric propulsion controller 60.

[0074] The mounting seat 14 disclosed in this embodiment is integrally formed with the housing 10, and the guide channel 12 is extended to the mounting seat 14, so that the length of the guide channel 12 is increased, which is conducive to ensuring that the ends of the guide core 20 are arranged in a straight line, and improving the stability of contact with the oscillating atomization assembly 30. In addition, compared with assembling on the outer surface of the housing 10, it is more convenient to assemble the oscillating atomization assembly 30 and the beam tube 51 on the protruding mounting seat 14.

[0075] The beam tube 51 disclosed in this embodiment is sleeved on the mounting seat 14, shielding the oscillating atomization assembly 30, and the atomized droplets are constrained by the beam tube 51 to avoid splashing and better control the propulsion direction. The humidity sensor 52 on the inner wall of the beam tube 51 collects the humidity inside the beam tube 51, so as to judge the real-time atomization amount according to the preset temperature threshold, so as to achieve the purpose of judging the atomization effect.

[0076] like Figure 7 As shown, as another embodiment of the present application, a control method of a satellite propulsion device is disclosed, which is used for any of the satellite propulsion devices described above; wherein, it includes:

[0077] S100, obtaining a satellite control instruction; wherein the satellite control instruction includes any one of a propulsion instruction, a deorbit instruction, and an orbit change instruction;

[0078] S200, calculating the atomization oscillation period and the atomization interval duration based on the satellite control instruction, and generating an atomization control instruction;

[0079] S300, starting the heating component 40 for preheating, then starting the oscillating atomizing component 30, and collecting real-time data of the humidity monitoring component 50;

[0080] S400: If the real-time data reaches a preset humidity threshold, the oscillating atomization assembly 30 is started based on the atomization control instruction.

[0081] The satellite propulsion device disclosed in this embodiment is communicatively connected to the control panel of the satellite main frame. When the satellite performs actions such as changing orbit or leaving orbit, the satellite propulsion device receives the control command, then preheats, selects the atomization mode based on the control command, and then performs atomization. The whole process is simple and fast, with high atomization efficiency, which is conducive to rapid response, improves the satellite operation speed, and quickly completes the satellite position adjustment.

[0082] Specifically, in this embodiment, by setting the atomization oscillation period and the atomization interval duration, a point-spraying method is implemented, which is beneficial to saving working fluid and improving the precision of satellite orbit adjustment. Figure 8 As shown, different from Figure 8 As shown in Figure (a), the conventional atomization component performs continuous atomization at a set frequency; the oscillating atomization component 30 in this embodiment sets the atomization oscillation period to T1 and the atomization interval to T0. Figure 8 As shown in Figure (b), the inertia of the satellite's motion can be used to fine-tune the orbit.

[0083] The atomization interval duration T0 disclosed in this embodiment can be set to one tenth or one twentieth of the atomization oscillation period T1, for example, atomization is performed once every second, and then the next atomization is performed after an interval of one tenth of a second. The short interval time ensures that the satellite is always controlled by the propulsion force and does not get out of control.

[0084] In this embodiment, the atomization amount of the oscillating atomizing component 30 is determined by collecting real-time data, and then it is determined whether the oscillating atomizing component 30 is working normally. For example, the preset humidity threshold is 90-100%. If the real-time data is only 80%, the oscillating atomizing component 30 is controlled to be turned off first, and the heating component 40 continues to heat for a period of time, such as 10-20 seconds, and then the oscillating atomizing component 30 is turned on again, and real-time data is collected again. When the real-time data reaches 90%, it is determined that the satellite propulsion device has reached a normal working state, and the oscillating atomizing component 30 can be controlled to atomize according to the atomization control instruction to perform propulsion actions and complete operations such as orbit change and de-orbit.

[0085] like Fig. 9 As shown, in another implementation of this embodiment, the orbit change control process of the satellite propulsion device is as follows:

[0086] Step 1: Receive the track change instruction.

[0087] In the initial state, the satellite propulsion device remains silent, the propellant is solid, and the satellite's motion attitude is stable. The satellite service system is set on the satellite to control the attitude and perform mission planning. The satellite service system sends an orbit change command to the satellite propulsion device, and the satellite propulsion device starts the orbit change work after receiving the orbit change command.

[0088] Step 2: Calculate the propulsion direction and adjust the satellite attitude.

[0089] The satellite's propulsion direction is calculated according to the orbit change instruction, and then the overall axial direction of the satellite is adjusted to be consistent with the direction of the upcoming orbit change to facilitate propulsion and improve stability during the orbit change operation.

[0090] Step 3: Start the heating component to melt the propellant into liquid.

[0091] While adjusting the satellite's attitude, or after the attitude is adjusted, the heating component is started for preheating. The solid propellant melts into liquid and becomes fluid, which is then absorbed by the drainage core, allowing the oscillating atomization component to come into contact with the liquid propellant.

[0092] Step 4: Start the oscillating atomization component to complete high-speed oscillation, break up the liquid propellant into tiny particles, and discharge them.

[0093] Step 5: Start the humidity monitoring component to collect humidity data on the path where the oscillating atomization component sprays liquid.

[0094] Step 6: Determine whether the humidity data meets the standard.

[0095] The real-time detected humidity data is used to determine whether the mist output of the oscillating atomization component meets the standard, and then the degree of liquefaction of the propellant is inferred.

[0096] Step 7: If the humidity data does not meet the standard, it means that the mist output of the oscillating atomization component is insufficient and the propellant has not been fully liquefied. Then turn off the oscillating atomization component, delay for 10 seconds, wait for the propellant to liquefy, and then repeat step 4. Repeat the cycle until the humidity data meets the standard, and then perform the satellite orbit change work.

[0097] Step 8: If the measured humidity data is greater than 90%, it is judged that the fog output of the oscillating atomization component is sufficient, the liquefaction degree of the propellant is high, and the propulsion work can be started. Then, the atomization control instruction is calculated based on the orbit change instruction, and the oscillating atomization component is controlled to continue atomizing based on the atomization control instruction to promote the satellite to change orbit.

[0098] It should be understood that the various parts of the present application can be implemented in hardware, software, firmware or a combination thereof. In the above-mentioned embodiments, multiple steps or methods can be implemented in software or firmware stored in a memory and executed by a suitable instruction execution system. If implemented in hardware, as in another embodiment, it can be implemented by any one of the following technologies known in the art or their combination: a discrete logic circuit having a logic gate circuit for implementing a logic function on a data signal, a dedicated integrated circuit having a suitable combination of logic gate circuits, a programmable gate array, a field programmable gate array, etc.

[0099] In addition, each functional unit in each embodiment of the present application may be integrated into a processing module, or each unit may exist physically separately, or two or more units may be integrated into one module. The above-mentioned integrated module may be implemented in the form of hardware or in the form of a software functional module. If the integrated module is implemented in the form of a software functional module and sold or used as an independent product, it may also be stored in a computer-readable storage medium.

[0100] In summary, the present application discloses a satellite propulsion device, which includes a shell 10, a drainage core 20, an oscillating atomization assembly 30, a heating assembly 40, a humidity monitoring assembly 50 and an electric propulsion controller 60. The shell 10 is hollow and has a storage chamber 11 for storing propellant; a guide channel 12 is provided on the side wall of the storage chamber 11; the drainage core 20 is arranged in the storage chamber 11; the end of the drainage core 20 is inserted into the guide channel 12; the oscillating atomization assembly 30 is connected to the shell 10 and is arranged in the guide channel The port 12 is connected to the drainage core 20, and is in contact with the drainage core 20, and is used to atomize and spray out the propellant on the end surface of the drainage core 20; the heating component 40 is connected to the shell 10, and is arranged on the outer wall of the shell 10, and is used to melt the propellant; the humidity monitoring component 50 is connected to the shell 10, and is arranged on the path of the oscillating atomizing component 30 spraying liquid particles; the electric propulsion controller 60 is arranged on the shell 10; the electric propulsion controller 60 is electrically connected to the oscillating atomizing component 30, the heating component 40, and the humidity monitoring component 50. This embodiment melts the propellant and breaks it into small droplets, and then sprays it to form a propulsion force, which acts on the satellite's orbit change, deorbit and other actions. It has a simple structure, low manufacturing cost, and is easy to implement. On the basis of ensuring the flexibility of the satellite, it is beneficial to reduce the launch and operation costs of the satellite.

[0101] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present application may be combined with each other.

[0102] It should be noted that the present invention takes a satellite propulsion device and a control method thereof as an example to introduce the specific structure and working principle of the present invention, but the application of the present invention is not limited to a satellite propulsion device and a control method thereof, and can also be applied to the production and use of other similar workpieces.

[0103] It should be understood that the present invention is not limited to the exact construction that has been described above and shown in the drawings and that various modifications and changes may be made without departing from the scope thereof. The scope of the present invention is limited only by the appended claims.

[0104] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A satellite propulsion device, characterized in that: include: A shell, wherein the shell is hollow and has a storage chamber for storing propellant; a guide channel is provided on the side wall of the storage chamber; A drainage core is disposed in the material storage chamber; an end of the drainage core is inserted into the guide channel; An oscillating atomizing assembly connected to the housing, disposed at the port of the guide channel and in contact with the guide core, for atomizing and spraying the propellant on the end surface of the guide core; A heating component, connected to the shell and disposed on the outer wall of the shell, for melting the propellant; A humidity monitoring component, connected to the housing and disposed on a path where the oscillating atomizing component sprays liquid particles; as well as An electric propulsion controller is arranged on the housing; the electric propulsion controller is electrically connected to the oscillating atomization component, the heating component, and the humidity monitoring component; The drainage core is in the shape of an elongated strip, and the radial cross section is in the shape of a circle; the radial cross section of the guide channel is in the shape of a circle; the diameter of the radial cross section of the drainage core is smaller than the length of the guide channel; A limiting groove is provided on the side of the storage chamber away from the guide channel, and the width of the limiting groove is less than or equal to the diameter of the radial cross section of the drainage core; the drainage core is arranged in the limiting groove, and one end extends out of the limiting groove and contacts the inner wall of the shell; the other end of the drainage core extends out of the limiting groove, is bent and inserted into the guide channel, and contacts the oscillating atomization assembly.

2. The satellite propulsion device according to claim 1, characterized in that: The material storage chamber comprises a connection area at a central position and a material suction area at an edge position, and the guide channel is arranged in the connection area; One end of the drainage core is plugged into the guide channel, and the other end extends to a side of the suction area away from the connection area.

3. The satellite propulsion device according to claim 1, characterized in that: The drainage core is in the shape of a tree branch, and one end of the drainage core away from the guide channel is formed with at least two forked sections extending to the inner wall of the shell.

4. The satellite propulsion device according to claim 1, characterized in that: The oscillating atomization component includes an ultrasonic oscillation sieve sheet and a protective rubber sleeve, wherein the ultrasonic oscillation sieve sheet is arranged at the end of the guide channel; the central position of the ultrasonic oscillation sieve sheet is aligned with and fits the end surface of the drainage core, and the edge position of the ultrasonic oscillation sieve sheet is sleeved with the protective rubber sleeve; the protective rubber sleeve is bonded to the shell.

5. The satellite propulsion device according to claim 1, characterized in that: The shell is any one of a metal shell, an alloy shell, and a carbon fiber shell; The heating assembly comprises a plurality of heating plates, and the plurality of heating plates are evenly distributed on the outer surface of the shell.

6. The satellite propulsion device according to claim 1, characterized in that: The shell is filled with a porous liquid-absorbing block for absorbing liquid, and the shape of the porous liquid-absorbing block is the same as that of the storage chamber; Among them, the porous liquid absorbent block is provided with a hollow channel aligned with the guide channel, and the hollow channel is used to set the drainage core; the porous liquid absorbent block is also provided with a temperature sensor, and the temperature sensor is communicatively connected with the electric propulsion controller for collecting temperature data of the propellant.

7. The satellite propulsion device according to claim 1, characterized in that: A mounting seat is protrudingly provided on the outer surface of the shell, and the guide channel is formed at the center of the mounting seat; the oscillating atomization assembly is arranged on the end surface of the mounting seat; The humidity monitoring component comprises a beam tube and a humidity sensor. The beam tube is trumpet-shaped and sleeved on the mounting seat. The humidity sensor is arranged on the inner wall of the beam tube and is electrically connected to the electric propulsion controller.

8. A control method for a satellite propulsion device, used for the satellite propulsion device according to any one of claims 1 to 7; characterized in that: include: Obtaining a satellite control instruction; wherein the satellite control instruction includes any one of a propulsion instruction, a deorbit instruction, and an orbit change instruction; Calculate the atomization oscillation period and the atomization interval duration based on the satellite control command, and generate an atomization control command; Start the heating component to preheat, then start the oscillating atomization component, and collect real-time data from the humidity monitoring component; If the real-time data reaches a preset humidity threshold, the oscillating atomization component is started based on the atomization control instruction.

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