Energetic ionic liquid electrospray thruster for strengthening regulation and control of dual-mode propulsion system

Abstract

The invention discloses an energetic ionic liquid electrospray thruster capable of strengthening regulation and control of a dual-mode propulsion system, which comprises a shell, a plurality of electric spray nozzles and a plurality of electric spray nozzles, a plurality of emitting electrodes, each emitting electrode is provided with a plurality of emitting electrode cones, the emitting electrodes and the emitting electrode cones are alpha alumina porous ceramic material pieces, the aperture of the emitting electrodes and the emitting electrode cones is 1-20 microns, and the porosity of the emitting electrodes and the emitting electrode cones is 20-40%; each extraction electrode is provided with a plurality of extraction electrode holes arranged in an array, and the plurality of extraction electrode holes and the plurality of emitter cones are in one-to-one correspondence axis superposition; the liquid storage block is connected with the emitting electrode; the conductive part is provided with a liquid inlet communicated with the liquid storage block, and the conductive part is electrically connected with the liquid storage block. The energetic ionic liquid electrospray thruster for strengthening regulation and control of the dual-mode propulsion system has the advantages of being high in reliability, good in stability, large in thrust, high in specific impulse, good in flexibility, high in applicability, adaptive to different liquid supply modes, capable of meeting different task requirements and the like.

Description

Technical Field

[0001] This invention relates to the field of aerospace propulsion technology, and more specifically, to an energetic ion liquid electrospray thruster that enhances the control of a dual-mode propulsion system. Background Technology

[0002] With the increasing demands of space missions, especially the rapid development of microsatellites and constellation systems, higher requirements are being placed on the maneuverability, attitude control accuracy, and long-term orbital maintenance capabilities of spacecraft.

[0003] The dual-mode propulsion system can switch between electro-spray propulsion and chemical propulsion modes, which can greatly improve the adaptability and mission flexibility of the propulsion system and cope with complex and ever-changing space missions.

[0004] Electrospray thrusters in related technologies are difficult to use directly for dual-mode propulsion. Dual-mode propulsion requires the use of specific dual-mode energetic ionic liquid propellants, but the electrospray thrusters in related technologies do not take into account their physicochemical properties such as ignition point and viscosity, resulting in limited performance. Moreover, it is difficult to switch between active and passive liquid supply modes without adding or changing the structure, which limits the flexibility and adaptability of electrospray thrusters. Summary of the Invention

[0005] This invention aims to at least solve one of the technical problems existing in the prior art. To this end, this invention proposes an energetic ionic liquid electrospray thruster with enhanced dual-mode propulsion system control. This energetic ionic liquid electrospray thruster with enhanced dual-mode propulsion system control has advantages such as high reliability, good stability, large thrust, high specific impulse, good flexibility, strong applicability, adaptability to different liquid supply modes, and meeting different mission requirements.

[0006] To achieve the above objectives, an energetic ionic liquid electrospray thruster for enhanced dual-mode propulsion system control is proposed according to an embodiment of the present invention. The energetic ionic liquid electrospray thruster for enhanced dual-mode propulsion system control includes: a housing, the housing being an insulating material component, the upper surface of the housing having multiple grooves; multiple emitters, the multiple emitters respectively fitting within the multiple grooves, each emitter having multiple arrayed emitter cones, the emitters and emitter cones being made of α-alumina porous ceramic material with a pore size of 1-20 micrometers and a porosity of 20%-40%; and multiple extraction electrodes, the... The extraction electrodes are made of metal and are respectively fitted into multiple grooves and located above the emitter. Each extraction electrode has multiple arrayed extraction electrode holes, and the axes of the multiple extraction electrode holes and the multiple emitter cones are aligned one-to-one. A liquid storage block, which is a porous metal material, is disposed within the housing and located below the emitter, and is connected to the emitter. A conductive element has a liquid inlet communicating with the liquid storage block, is disposed within the housing and located below the liquid storage block, and is electrically connected to the liquid storage block.

[0007] The energetic ion liquid electrospray thruster with enhanced dual-mode propulsion system control according to embodiments of the present invention has the advantages of high reliability, good stability, large thrust, high specific impulse, good flexibility, strong applicability, adaptability to different liquid supply modes, and meeting different mission requirements.

[0008] In addition, the energetic ion liquid electrospray thruster with enhanced dual-mode propulsion system control according to the above embodiments of the present invention may also have the following additional technical features: According to one embodiment of the present invention, there are 9 grooves arranged in a 3x3 array on the housing, 9 emitters that are fitted into the 9 grooves in a one-to-one correspondence, and 9 extractors that are fitted into the 9 grooves in a one-to-one correspondence.

[0009] According to one embodiment of the present invention, a plurality of emitter cones on each emitter are arranged in a 24-row, 24-column array, the distance between two adjacent emitter cones on each emitter is 0.4 mm, the height of the emitter cone is 0.5 mm, the diameter of the cone base of the emitter cone is 0.2 mm, and the radius of curvature of the cone tip of the emitter cone is 25-35 micrometers.

[0010] According to one embodiment of the present invention, an annular insulating pad is provided between the edge of the upper surface of the emitter and the edge of the lower surface of the extractor in each groove.

[0011] According to one embodiment of the present invention, the upper surface of the liquid storage block is provided with a plurality of protrusions, and the plurality of protrusions are tightly attached to the plurality of emitters through oil-permeable filter paper.

[0012] According to one embodiment of the present invention, an annular first waterproof gasket is provided between the edge of the lower surface of the emitter and the groove.

[0013] According to one embodiment of the present invention, the conductive element is provided with a positioning groove, the edge of the positioning groove is provided with an annular boss, the liquid storage block is fitted in the positioning groove and supported on the annular boss, a spring is compressed between the liquid storage block and the bottom wall of the positioning groove, and the liquid storage block and the conductive element are electrically connected through the spring.

[0014] According to one embodiment of the present invention, an annular second anti-seepage gasket is provided between the lower surface of the liquid storage block and the upper surface of the annular boss.

[0015] According to an embodiment of the present invention, the energetic ion liquid electrospray thruster for enhanced dual-mode propulsion system control further includes a pressure plate. The pressure plate is installed on the upper surface of the housing by threaded fasteners and presses the plurality of emitters and the plurality of extractors into the groove. The pressure plate is provided with a plurality of clearance ports, which correspond one-to-one with the plurality of extractors and avoid the extractor holes of the corresponding extractors. The pressure plate is electrically grounded.

[0016] According to one embodiment of the present invention, the energetic ion liquid electrospray thruster controlled by the enhanced dual-mode propulsion system further includes a bottom cover, which is mounted on the housing by threaded fasteners.

[0017] Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. Attached Figure Description

[0018] The above and / or additional aspects and advantages of the present invention will become apparent and readily understood from the description of the embodiments taken in conjunction with the following drawings, in which: Figure 1 This is a schematic diagram of the structure of an energetic ion liquid electrospray thruster for enhanced dual-mode propulsion system control according to an embodiment of the present invention.

[0019] Figure 2 This is a cross-sectional view of an energetic ion liquid electrospray thruster with enhanced dual-mode propulsion system control according to an embodiment of the present invention.

[0020] Figure 3 This is a schematic diagram of the emitter of an energetic ionic liquid electrospray thruster with enhanced dual-mode propulsion system control according to an embodiment of the present invention.

[0021] Figure 4 This is a schematic diagram of the extraction electrode of an energetic ionic liquid electrospray thruster for enhanced dual-mode propulsion system control according to an embodiment of the present invention.

[0022] Figure 5 This is a schematic diagram of the liquid storage block of an energetic ionic liquid electrospray thruster for enhanced dual-mode propulsion system control according to an embodiment of the present invention.

[0023] Figure 6 This is a schematic diagram of the conductive component of an energetic ionic liquid electrospray thruster for enhanced dual-mode propulsion system control according to an embodiment of the present invention.

[0024] Figure 7 This is a schematic diagram of the housing of an energetic ion liquid electrospray thruster for enhanced dual-mode propulsion system control according to an embodiment of the present invention.

[0025] Figure 8 This is a schematic diagram of the bottom cover of an energetic ion liquid electrospray thruster for enhanced dual-mode propulsion system control according to an embodiment of the present invention.

[0026] Reference numerals: Energetic ionic liquid electrospray thruster with enhanced dual-mode propulsion system control 1, housing 10, groove 11, emitter 20, emitter cone 21, extraction electrode 30, extraction electrode hole 31, liquid storage block 40, boss 41, upper spring groove 42, conductive component 50, liquid inlet 51, positioning groove 52, annular boss 53, lower spring groove 54, wiring terminal 55, insulating gasket 60, first anti-seepage rubber gasket 71, second anti-seepage rubber gasket 72, pressure plate 80, clearance opening 81, bottom cover 90, flange 91. Detailed Implementation

[0027] This application is based on the findings and understanding of the following facts and issues: Electrospray thrusters in related technologies are difficult to use directly for dual-mode propulsion. Dual-mode propulsion requires the use of specific dual-mode energetic ionic liquid propellants, but the electrospray thrusters in related technologies do not take into account their physicochemical properties such as ignition point and viscosity, resulting in limited performance. Moreover, it is difficult to switch between active and passive liquid supply modes without adding or changing the structure, which limits the flexibility and adaptability of electrospray thrusters.

[0028] Specifically, the energetic ionic liquid propellant used for dual-mode propulsion, such as EP-36, is composed of ethyl 1-ethyl-3-methylimidazolium sulfate (EMIM-EtSO4), hydroxylamine nitrate (HAN), and water, and has a viscosity of 35.0 mPa·s at room temperature. Compared with the propellants used in electrospray propulsion systems of non-dual-mode propulsion systems in related technologies, it has a lower viscosity and ignition point.

[0029] The lower viscosity makes it difficult for electrospray thrusters in related technologies to deliver propellant smoothly to the launch pole under suitable flow resistance, affecting its hydrodynamic stability. The higher ignition point makes the propellant easy to ignite due to temperature rise during launch.

[0030] Embodiments of the present invention are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention.

[0031] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential," etc., indicating orientation or positional relationships, are based on the orientation or positional relationships shown in the accompanying drawings and are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. Furthermore, features defined with "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, unless otherwise stated, "a plurality of" means two or more. In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0032] The energetic ion liquid electrospray thruster 1, which enhances the regulation of a dual-mode propulsion system according to an embodiment of the present invention, is described below with reference to the accompanying drawings.

[0033] like Figures 1-8 As shown, the energetic ionic liquid electrospray thruster 1 with enhanced dual-mode propulsion system control according to an embodiment of the present invention includes a housing 10, multiple emitters 20, multiple extractors 30, a liquid storage block 40, and a conductive element 50.

[0034] The housing 10 is made of insulating material, and its upper surface has multiple grooves 11 (the vertical direction is shown by the arrows in the figure and is only for ease of description, not a limitation on the actual installation direction). Multiple emitters 20 are respectively fitted into the multiple grooves 11, and each emitter 20 has multiple arrayed emitter cones 21. Both the emitters 20 and emitter cones 21 are made of porous alumina ceramic material with a pore size of 1-20 micrometers and a porosity of 20%-40%. Extraction electrodes 30 are made of metal material, and multiple extraction electrodes 30 are respectively fitted into the multiple grooves 11 and located above the emitters 20. Each extraction electrode 30 has multiple arrayed extraction electrode holes 31, and the axes of the extraction electrode holes 31 and the multiple emitter cones 21 are aligned one-to-one. A liquid storage block 40 is made of porous metal material, located inside the housing 10 and below the emitters 20, and is connected to the emitters 20. The conductive element 50 is provided with a liquid inlet that communicates with the liquid storage block 40. The conductive element 50 is located inside the housing 10 and below the liquid storage block 40. The conductive element 50 is electrically connected to the liquid storage block 40.

[0035] Specifically, the pore size of the α-alumina porous ceramic material of emitter 20 and emitter cone 21 is preferably 5-10 micrometers. The porous alumina ceramic can be subjected to hydrophilic modification treatment, such as plasma treatment or sol-gel hydrophilic coating treatment after sintering, to improve its wettability with propellant.

[0036] The housing 10 can be made of polyetheretherketone (PEEK) material to improve structural strength while ensuring insulation and to facilitate the assembly and disassembly of other structures.

[0037] The extraction electrode 30 can be made of 304 stainless steel. It uses chemical etching to process thin metal sheets, so as to ensure overall flatness and processing accuracy at a lower processing cost.

[0038] The liquid storage block 40 can be made of porous sponge titanium to ensure that the pore size is small enough to provide capillary force while also having good conductivity and ductility.

[0039] The conductive component 50 may be provided with a terminal 55 for connecting to a high-voltage power supply, and the terminal 55 may extend out from the housing 10.

[0040] Extraction electrode 30 can be electrically grounded.

[0041] The inlet 51 can be connected to a propellant supply device to supply propellant.

[0042] The dual-mode energetic ionic liquid propellant is wetted into the emitter 20 through either passive or active supply mode. By connecting a high-voltage power supply, a certain potential difference is formed between the emitter 20 and the extraction electrode 30. Under the action of the electric field, the dual-mode energetic ionic liquid is stretched at the tip of the emitter cone 21 to form a Taylor cone and further emits ions or droplets to generate thrust.

[0043] In the active supply mode, the propellant is actively injected into the back of the reservoir block 40 through the inlet 51 of the conductive component 50 at a certain flow rate under controlled conditions, and uniformly penetrates and wets the emitter 20 under capillary force. In the passive supply mode, the propellant directly wets the emitter 20 without the need for a supply device.

[0044] When energized, the following circuit can be formed: high voltage power supply—conductive component 50—liquid storage block 40—emitter 20; extraction electrode 30—grounding, to form a potential difference.

[0045] According to an embodiment of the present invention, the energetic ionic liquid electrospray thruster 1 with enhanced dual-mode propulsion system control uses both the emitter 20 and the emitter cone 21 as porous α-alumina ceramic materials. Since α-phase alumina has extremely high stability and high temperature resistance compared to other phases, compared with electrospray thrusters in related technologies, the energetic ionic liquid electrospray thruster 1 with enhanced dual-mode propulsion system control can better maintain the tip shape of the emitter cone 21 during electrospray launch, and can avoid the propellant ignition due to temperature rise during electrospray launch, reduce the risk of propellant ignition, and ensure the stability and reliability of the launch process.

[0046] Furthermore, by making the aperture of the emitter 20 and the emitter cone 21 1-20 micrometers and the porosity 20%-40%, compared with the electrospray thrusters in related technologies, the propellant can be stably transported in the high-density array of the emitter 20. This ensures that the propellant is smoothly delivered to the tip of the emitter cone 21 under appropriate flow resistance and minimizes droplet emission, increases the emission ratio of cationic monomers / dimers in the spray plume, suppresses excessive emission of large anion clusters, improves macroscopic specific impulse and efficiency, avoids the problem of propellant hydrodynamic instability, and ensures the stability and reliability of the energetic ion liquid electrospray thruster 1 with enhanced dual-mode propulsion system control in electrospray mode.

[0047] Furthermore, by providing multiple grooves 11 on the upper surface of the housing 10, with multiple emitters 20 respectively fitted within the multiple grooves 11, and multiple extractors 30 respectively fitted within the multiple grooves 11 and located above the emitters 20, compared to electrospray thrusters in related technologies, the energetic ionic liquid electrospray thruster 1 with enhanced dual-mode propulsion system control adopts a modular design, which facilitates the rational arrangement of emitters 20 and extractors 30, improves the consistency of the emission array, and facilitates a significant increase in emission point density while ensuring controllable machining tolerances, thereby increasing the overall thrust. This ensures that the energetic ionic liquid electrospray thruster 1 with enhanced dual-mode propulsion system control can freely switch between active and passive liquid supply modes without modifying or adding to the structure in high-thrust, high-specific-impulse working modes, enhancing the controllability of propulsion parameters such as flow rate and voltage, and flexibly adapting to the needs of dual-mode propulsion systems, thus improving flexibility and applicability.

[0048] Therefore, the energetic ionic liquid electrospray thruster 1, which enhances the regulation of the dual-mode propulsion system, can be easily combined with a chemical thruster to form a dual-mode propulsion system, and facilitates control and operation under the dual-mode system.

[0049] Therefore, the energetic ion liquid electrospray thruster 1 with enhanced dual-mode propulsion system control according to the present invention has the advantages of high reliability, good stability, large thrust, high specific impulse, good flexibility, and strong applicability.

[0050] The energetic ion liquid electrospray thruster 1, which enhances the regulation of a dual-mode propulsion system according to a specific embodiment of the present invention, is described below with reference to the accompanying drawings.

[0051] In some specific embodiments of the present invention, such as Figures 1-8 As shown, the energetic ionic liquid electrospray thruster 1 with enhanced dual-mode propulsion system control according to an embodiment of the present invention includes a housing 10, multiple emitters 20, multiple extractors 30, a liquid storage block 40, and a conductive element 50.

[0052] Specifically, such as Figure 1 and Figure 7 As shown, there are nine grooves 11 arranged in a 3x3 array on the housing 10. There are nine emitters 20, each corresponding to one of the nine grooves 11, and nine extractors 30, each corresponding to one of the nine grooves 11. This not only facilitates the modular installation of the emitters 20 and extractors 30, but also facilitates the formation of arrayed thrust units, improving propulsion efficiency.

[0053] More specifically, such as Figure 3As shown, the multiple emitter cones 21 on each emitter 20 are arranged in a 24-row, 24-column array. The spacing between two adjacent emitter cones 21 on each emitter 20 is 0.4 mm, the height of each emitter cone 21 is 0.5 mm, the diameter of the cone base is 0.2 mm, and the radius of curvature of the cone tip is 25-35 micrometers. Specifically, the dimensions of the extraction electrode 30 are preferably 9 mm in length, 9 mm in width, and 1-3 mm in thickness, and the diameter of the extraction electrode orifice 31 is 0.3 mm. This can further improve the capillary transport capacity of the extraction electrode 30 and the emitter cones 21.

[0054] Advantageously, such as Figure 2 As shown, an annular insulating pad 60 is provided between the edge of the upper surface of the emitter 20 and the edge of the lower surface of the extractor 30 within each groove 11. Specifically, the insulating pad 60 can be made of zirconium oxide material, and is rectangular in shape with a resistivity greater than 10¹²Ω / cm², an outer diameter of 14.8±0.1 mm, an inner diameter of 11±0.1 mm, and a thickness of 0.1-0.5 mm. The distance between the emitter 20 and the extractor 30 can be adjusted by changing the thickness, number, and combination of the insulating pads 60. This facilitates the use of the insulating pads 60 to separate the emitter 20 and the extractor 30, forming a stable electrode spacing.

[0055] More advantageously, such as Figure 2 and Figure 5 As shown, the upper surface of the liquid storage block 40 is provided with multiple protrusions 41, which are in close contact with multiple emitters 20 through oil-permeable filter paper. In this way, the oil-permeable filter paper can serve as a liquid permeation medium layer, which not only increases the contact area between the liquid storage block 40 and the emitter 20 and reduces the local resistance, but also allows the oil-permeable filter paper to filter out some impurities.

[0056] Furthermore, such as Figure 2 As shown, an annular first waterproof gasket 71 is provided between the edge of the lower surface of the emitter 20 and the groove 11. Specifically, the first waterproof gasket 71 can be a silicone part, and the first waterproof gasket 71 is rectangular and annular, with an outer diameter of 14.8 ± 0.1 mm, an inner diameter of 11 ± 0.1 mm, and a thickness of 0.1 mm, 0.2 mm, and 0.5 mm, which can be selected according to the assembly clamping force. This can improve the sealing between the edge of the lower surface of the emitter 20 and the groove 11, and the flexibility of the first waterproof gasket 71 can improve the stability of the emitter 20.

[0057] Specifically, such as Figure 2 and Figure 6As shown, the conductive component 50 is provided with a positioning groove 52, and the edge of the positioning groove 52 is provided with an annular boss 53. The liquid storage block 40 is fitted into the positioning groove 52 and supported on the annular boss 53. A spring is compressed between the liquid storage block 40 and the bottom wall of the positioning groove 52, and the liquid storage block 40 and the conductive component 50 are electrically connected through the spring. Specifically, the lower surface of the liquid storage block 40 is provided with an upper spring groove 42, and the bottom wall of the positioning groove 52 is provided with a lower spring groove 54. The spring is respectively fitted into the upper spring groove 42 and the lower spring groove 54. This facilitates the formation of a propellant storage chamber between the conductive component 50 and the liquid storage block 40, and the spring facilitates the electrical connection between the liquid storage block 40 and the conductive component 50.

[0058] Advantageously, such as Figure 2 As shown, an annular second anti-seepage gasket 72 is provided between the lower surface of the liquid storage block 40 and the upper surface of the annular boss 53. Specifically, the second anti-seepage gasket 72 is rectangular. This can improve the sealing between the liquid storage block 40 and the conductive component 50.

[0059] Furthermore, such as Figure 1 As shown, the energetic ion liquid electrospray thruster 1 with enhanced dual-mode propulsion system control also includes a pressure plate 80. The pressure plate 80 is installed on the upper surface of the housing 10 by threaded fasteners and presses multiple emitters 20 and multiple extractors 30 into the groove 11. The pressure plate 80 is provided with multiple clearance ports 81, which correspond one-to-one with multiple extractors 30 and avoid the extraction port 31 of the corresponding extractor 30. The pressure plate 80 is electrically grounded. Specifically, the lower surface of the pressure plate 80 may have protrusions around the clearance ports 81 to facilitate pressing the extractors 30 and emitters 20. This not only facilitates the positioning of the emitters 20 and extractors 30 in the groove 11, but also facilitates the simultaneous grounding of multiple extractors 30.

[0060] Furthermore, such as Figure 1 and Figure 8 As shown, the energetic ion liquid electrospray thruster 1 with enhanced dual-mode propulsion system control also includes a bottom cover 90, which is mounted on the housing 10 by threaded fasteners. Specifically, the liquid inlet 51 can extend from the bottom cover 90. This facilitates the positioning of the internal structures of the housing 10, and a flange 91 can be provided on the bottom cover 90 for connection with other structures.

[0061] Specifically, the overall assembly dimensions of the energetic ion liquid electrospray thruster 1 with enhanced dual-mode propulsion system control are 70-90 mm in length, 70-90 mm in width, and 20-40 mm in thickness, preferably 76 mm in length, 76 mm in width, and 27.5 mm in thickness.

[0062] Other configurations and operations of the energetic ion liquid electrospray thruster 1 with enhanced dual-mode propulsion system control according to embodiments of the present invention are known to those skilled in the art and will not be described in detail here.

[0063] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "illustrative embodiment," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0064] Although embodiments of the invention have been shown and described, those skilled in the art will understand that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.

Claims

1. An energetic ionic liquid electrospray thruster for enhanced dual-mode propulsion system control, characterized in that, include: The housing is made of insulating material, and the upper surface of the housing has multiple grooves; Multiple emitters are respectively fitted into multiple grooves. Each emitter is provided with multiple emitter cones arranged in an array. Both the emitters and the emitter cones are made of α-alumina porous ceramic material with a pore size of 1-20 micrometers and a porosity of 20%-40%. Multiple extraction electrodes, each being a metallic component, are respectively fitted into multiple grooves and located above the emitter electrode. Each extraction electrode has multiple arrayed extraction electrode holes, and the axes of the multiple extraction electrode holes and the multiple emitter cones are aligned one-to-one. A liquid storage block, which is a porous metal material component, is disposed inside the housing and located below the emitter, and is connected to the emitter; A conductive element is provided with a liquid inlet communicating with the liquid storage block. The conductive element is disposed inside the housing and located below the liquid storage block, and the conductive element is electrically connected to the liquid storage block.

2. The energetic ion liquid electrospray thruster for enhanced dual-mode propulsion system control according to claim 1, characterized in that, There are 9 grooves arranged in a 3x3 array on the housing. There are 9 transmitters, each corresponding to one of the 9 grooves. There are 9 extraction electrodes, each corresponding to one of the 9 grooves.

3. The energetic ion liquid electrospray thruster for enhanced dual-mode propulsion system control according to claim 1, characterized in that, The plurality of emitter cones on each emitter are arranged in a 24-row, 24-column array. The distance between two adjacent emitter cones on each emitter is 0.4 mm. The height of each emitter cone is 0.5 mm. The diameter of the base of each emitter cone is 0.2 mm. The radius of curvature of the tip of each emitter cone is 25-35 micrometers.

4. The energetic ion liquid electrospray thruster for enhanced dual-mode propulsion system control according to claim 1, characterized in that, An annular insulating pad is provided between the edge of the upper surface of the emitter and the edge of the lower surface of the extractor within each groove.

5. The energetic ion liquid electrospray thruster for enhanced dual-mode propulsion system control according to claim 1, characterized in that, The upper surface of the liquid storage block is provided with multiple protrusions, and the multiple protrusions are tightly attached to the multiple emitters through oil-permeable filter paper.

6. The energetic ion liquid electrospray thruster for enhanced dual-mode propulsion system control according to claim 1, characterized in that, An annular first waterproof gasket is provided between the edge of the lower surface of the emitter and the groove.

7. The energetic ion liquid electrospray thruster for enhanced dual-mode propulsion system control according to claim 1, characterized in that, The conductive component is provided with a positioning groove, and the edge of the positioning groove is provided with an annular boss. The liquid storage block is fitted in the positioning groove and supported on the annular boss. A spring is compressed between the liquid storage block and the bottom wall of the positioning groove. The liquid storage block and the conductive component are electrically connected through the spring.

8. The energetic ion liquid electrospray thruster for enhanced dual-mode propulsion system control according to claim 7, characterized in that, A second annular waterproof gasket is provided between the lower surface of the liquid storage block and the upper surface of the annular boss.

9. The energetic ion liquid electrospray thruster for enhanced dual-mode propulsion system control according to claim 1, characterized in that, It also includes a pressure plate, which is installed on the upper surface of the housing by threaded fasteners and presses the plurality of emitters and the plurality of extractors into the groove. The pressure plate is provided with a plurality of clearance openings, which correspond one-to-one with the plurality of extractors and avoid the extractor holes of the corresponding extractors. The pressure plate is electrically grounded.

10. The energetic ion liquid electrospray thruster for enhanced dual-mode propulsion system control according to claim 1, characterized in that, It also includes a bottom cover, which is mounted on the housing by threaded fasteners.

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