Staged electrostatic thruster

Abstract

An electrostatic thruster for generating thrust by charging gas particles and / or liquid particles with a high voltage potential, the electrostatic thruster comprising at least two thruster units, wherein each thruster unit comprises: - at least one emitter, - at least one collector, wherein the at least one collector is spaced apart from the at least one emitter from a thruster unit gap, wherein the electrostatic thruster further comprises a power source electrically connected to the at least one emitter and at least one collector of each thruster unit, wherein the power source is configured to apply a voltage between the at least one emitter and at least one collector of each thruster unit, wherein the at least two thruster units are positioned in parallel to form a thruster unit array, wherein the thruster unit array further comprises an intermediate electrode powered by a current source that generates a substantially constant current.

Description

Technical Field

[0001] The present invention relates to an electrostatic thruster configured to generate thrust using a high voltage potential. Background Technology

[0002] Over the years, it has been demonstrated that force or thrust can be generated by an "asymmetric capacitor," which consists of very fine electrode wires and a larger second electrode. When a high voltage is applied to the fine electrode wires, a force is generated along the direction of those wires.

[0003] In 1921, T.T. Brown discovered a force on a Coolidge (X-ray) tube that he could not explain. This force was observed when a high voltage was applied to the tube. This discovery led to the first asymmetric capacitor with a very thin anode and a very large cathode, which generated a force in the anode direction when a high voltage was applied to the anode. GB300311A (hereinafter: D1) is T.T. Brown's first patent, which discloses a method and apparatus for generating motion. This document proposes an electric generating unit consisting of alternating insulating thick plates and conductive plates. The document also discloses a device for generating rotational motion in which the thick plates and plates are arranged radially.

[0004] EP1619123A2 (hereinafter referred to as D2) discloses an ion drive system for generating thrust or propulsion. The ion drive system includes at least one stage having an emitter 10 and an attractor 12, wherein the attractor is spaced apart from the emitter by a gap D. The ion drive system also includes a propellant source and a power source 14 for introducing propellant near the emitter. The power source creates a high-intensity field near the emitter to ionize the dielectric and creates a diffusion field near the attractor to accelerate ions away from the emitter. The attractor also accelerates ions toward the high-intensity field near the emitter. These combined accelerations create thrust.

[0005] In a preferred embodiment of D2, the ion-driven system comprises multiple stages. Additional stages are isolated to prevent reverse flow of particles with opposite charges. These additional stages are isolated because adjacent emitter-attractor pairs have opposite polarities, and by positioning subsequent emitters downstream of the diffusion-attractor field of the previous stage. One disadvantage of this device is that it requires a propellant source to generate sufficient propulsive thrust.

[0006] Another example of an implementation of an electrostatic thruster is disclosed in US2009159754A1 (D3 in this document). D3 proposes a rotor system that generates a directional ion field to propel fluid along a rotor, thereby controlling at least one boundary layer feature. The propeller system 10 includes a plurality of propeller blades or rotors 14. Each rotor includes an emitter-collector pair electrically connected to a high-voltage source. The emitter-collector pair is positioned on the upper and lower sides of each rotor. Each emitter 18 operates as an ion source, and each attractor 20 operates as an ion collector, such that the emitter / attractor network can be used to create a directional ion field to generate thrust.

[0007] The drawback of the D3's electrostatic thruster is that the emitter-collector pair on the underside of the rotor generates thrust perpendicular to the underside surface of the rotor. This thrust is diverted away from the rotor and thus counteracts the rotational movement of the propeller system.

[0008] WO2022086667A2 (D4 in this document) discloses a low-noise vertical takeoff and landing (VTOL) unmanned aerial vehicle (UAV). The UAV 10 of D4 includes an ion thruster 1 for providing thrust in the vertical direction and a thrust vectoring system for providing thrust in the horizontal direction. The ion thruster consists of three geometrically identical electrode pairs 50. Each electrode pair includes a top electrode 52 and a bottom electrode 54, the bottom electrode 54 having a voltage potential opposite to that of the top electrode. By applying the potential, thrust is generated in the direction of the top electrode. The UAV also includes a rotating motor with an impeller 5 to support the force generated by the ion thruster.

[0009] A drawback of the D4 UAV is that the force generated by the ion thruster is insufficient to lift the UAV from the ground. An additional rotating impeller is required to generate sufficient lifting force. This invention recognizes that the distance between electrode pairs is insufficient to prevent the layers from affecting the performance of subsequent electrode pairs. When the distance between electrode pairs is sufficiently increased, the overall size of the UAV becomes too large.

[0010] This invention solves the main problems of existing ion thrusters: performance loss when the thrusters are staged, performance loss when the thrusters are placed close together, and efficiency loss when the voltage is increased to generate greater thrust.

[0011] Purpose of the invention

[0012] The object of the present invention is to provide an improved electrostatic thruster that eliminates at least one of the disadvantages and limitations discussed above, and provides a more efficient electrostatic thruster device in general.

[0013] Another object of the present invention is to provide a relatively compact electrostatic propulsion device, and in particular, using less material and being lighter in weight. Summary of the Invention

[0014] At least one of the aforementioned objectives is achieved using an electrostatic thruster 10 for generating thrust by charging gas particles and / or liquid particles with a high voltage potential, the electrostatic thruster comprising at least two thruster units, wherein each thruster unit comprises:

[0015] -At least one emitter,

[0016] -At least one collection pole,

[0017] In this configuration, at least one collector electrode is spaced apart from at least one emitter electrode from the gap in the thruster unit.

[0018] The electrostatic thruster further includes a power source electrically connected to at least one emitter and at least one collector of each thruster unit, wherein the power source is configured to apply a voltage between at least one emitter and at least one collector of each thruster unit.

[0019] At least two thruster units are positioned in parallel to form a thruster unit array, wherein the thruster unit array further includes an intermediate electrode, wherein the intermediate electrode is positioned in the intermediate region between the emitter and collector electrodes of two adjacent thruster units in the thruster unit array, wherein the intermediate electrode is electrically connected to the collector electrode of the thruster unit array via a current source configured to generate a substantially constant current.

[0020] A liquid and / or gas surrounds at least one emitter and at least one collector. The liquid and / or gas can also be identified as a fluid, which includes gases and / or liquids. The emitter and collector are surrounded by a fluid. The fluid can be the environment (e.g., air or water) or can be dispensed by a distributor into the region surrounding at least one emitter and collector. The emitter can be understood as an electrode capable of emitting positive or negative charges, thereby positively or negatively charging particles, such as molecules, of the gas and / or liquid surrounding the emitter. The collector can be understood as an electrode capable of collecting charges from charged particles. Charged particles are generated around the emitter by applying a voltage between the emitter and collector using a power source. The charged particles and the collector attract each other, thereby creating a force in the direction of the emitter on the electrostatic thruster. The emission of charged particles by the emitter can be understood as including the emission of charged particles and / or the emission of charges that charge particles in the liquid and / or gas surrounding the emitter, thereby forming charged particles.

[0021] The term parallel can be understood as parallel to the direction of the force created, i.e., the thrust created. The term parallel can also be understood as parallel to the direction from the emitter to the corresponding collector, or vice versa. Similarly, the term series can be understood as arranged in the direction of the force created, i.e., the thrust created by the electrostatic thruster. The power source can be an electrical power source and can be configured to apply any suitable voltage between the emitter and collector. For example, the voltage between the emitter and collector can be a DC (direct current) voltage or a pulsed voltage. The voltage can be positive (e.g., the emitter is at a higher voltage than the collector during operation) or negative (e.g., the emitter is at a higher voltage than the collector during operation).

[0022] During operation, the charged particles emitted by the emitter have the same polarity as the emitter. Due to electrostatic forces, objects of similar polarity repel each other, while objects of opposite polarity attract each other. Therefore, the charged particles emitted by the emitter of the thruster unit repel each other and are repelled by the emitter. The inventors have recognized that two effects may be at play when thrust is generated by the thruster. On the one hand, the emitted charged particles can be attracted by the collector, which can cause the charged particles to accelerate toward the collector, generating a flow toward the collector. Due to the drag effect, the charged particles may tend to drag other particles, such as uncharged particles, molecules, etc., which can enhance the flow. This so-called "ion wind" can provide some displacement; however, the inventors have recognized that the thrust generated by the ion wind may be relatively low.

[0023] The inventors have recognized that additional effects, namely electrostatic forces, can be used to enhance thrust. In prior art electrostatic thrusters, the net electrostatic force is likely low, and therefore the contribution of electrostatic force to thrust is likely low. Charged particles emitted from the emitters of the thruster unit array can form a sphere of charged particles around the emitters. Some of these charged particles can be emitted in a hemisphere of the thruster unit's collector poles away from the thruster unit array, and another portion of these charged particles can be emitted in a hemisphere of the thruster unit's collector poles facing the thruster unit array. Due to the electrostatic force between the charged particles and the emitters, the charged particles emitted in the hemisphere of the thruster unit's collector poles away from the thruster unit array and the charged particles emitted in the hemisphere of the thruster unit's collector poles facing the thruster unit array may generate opposing electrostatic forces on the emitters, resulting in relatively low net force in prior art electrostatic thrusters. The emitted charged particles may be attracted to the collector poles due to electrostatic forces. In the hemisphere of the emitters facing away from the collector poles, such attraction on the charged particles is likely low due to the presence of emitters with opposite charges. Therefore, in existing electrostatic thrusters, the net effect of electrostatic force may be low.

[0024] The inventors have devised a method to enhance the thrust generated by electrostatic force because charged particles emitted from the emitters of the thruster unit array are drawn into the gap, i.e., the space between the emitters and collectors of the thruster unit array. In other words, charged particles emitted into the hemispheres away from and towards the collectors can be drawn into, for example, the hemisphere towards the collector, such as the space between the emitters and collectors of the thruster unit. By drawing the charged particles emitted from the emitters into the region between the emitters and collectors of the thruster unit, the charged particles may be subjected to a net electrostatic force: on the one hand, the charged particles may exert a repulsive force on the emitters, thus pushing the emitters away; on the other hand, the charged particles may exert an attractive force on the collectors, thus attracting the collectors. The repulsive force on the emitters and the attractive force on the collectors can be in the same direction and can contribute to the electrostatic force.

[0025] The inventors have designed a mechanism in which charged particles emitted from the emitter can be drawn through an intermediate electrode toward the space between the emitter and collector of a thruster unit. The intermediate electrode is electrically connected to the collector of the thruster unit via a current source configured to generate a substantially constant current. The current source can provide a substantially constant discharge of charged particles to the intermediate electrode. Therefore, the amount of discharge of charged particles at the intermediate electrode can be well controlled. The voltage (potential) of the intermediate electrode can be self-adjusted based on the substantially constant current from the current source. The substantially constant current generated by the current source and drawn at the intermediate electrode can effectively draw charged particles emitted from the emitter into the space between the emitter and collector of the thruster unit, thus attracting the charged particles into this space where they can contribute to the electrostatic forces on the emitter and collector of the thruster unit array. On the other hand, the substantially constant current generated by the current source can limit the discharge of charged particles at the intermediate electrode, and the voltage at the intermediate electrode can be self-adjusting: the voltage at the intermediate electrode can be self-adjusted based on the substantially constant current to provide discharge of charged particles.

[0026] A current source can be understood, for example, as a high-impedance current control circuit, such as a current regulator circuit, a current limiting circuit, or a high series impedance circuit. The current regulator can be configured to provide a substantially constant current or to be controlled to a current proportional to the collector current. The current regulator can, for example, be configured to measure the collector current and control the substantially constant current to be proportional to the measured collector current, thereby enabling the substantially constant current to be adjusted as the thruster power of the electrostatic thruster is adjusted. As an example of high series impedance, the current source can include a high-impedance series resistor connected between the collector and intermediate electrode of the thruster unit array, or a voltage source connected in series with a high impedance to provide a substantially constant current. The current source can be directly connected to the collector of the thruster unit array, or indirectly connected to the collector of the thruster unit array, for example, via the emitter of the thruster unit array and a power supply connected between the emitter and collector of the thruster unit array.

[0027] Electrostatic propulsion systems can be incorporated into aircraft or ships. Therefore, the gas and / or liquid in which the electrostatic propulsion system operates may change, for example, due to changes in pressure or water or moisture content. Consequently, the dielectric properties of the gas and / or liquid in which the electrostatic propulsion system operates may vary drastically. By supplying power to the intermediate electrode by a current source configured to generate a substantially constant current, the voltage across the intermediate electrode can be adjusted according to the dielectric conditions of the gas and / or liquid, thus providing the desired pull on the emitted charged particles to carry them towards the space between the emitter and collector electrodes of the array, thereby contributing to the electrostatic force while avoiding undesirable large discharges or breakdowns of the intermediate electrode.

[0028] Therefore, high electrostatic thruster force can be generated under various environmental conditions, particularly under various dielectric conditions of the (ambient) gas and / or liquid in which the thruster operates. As mentioned above, the ion wind generated by the movement of charged particles toward the collecting electrode can generate some thrust. The electrostatic force that can be generated using the electrostatic thruster according to the invention can significantly increase the effective thrust of the electrostatic thruster.

[0029] Because the intermediate electrode, driven by a current source, is configured to draw emitted charged particles from the emitter into the space between the emitter and collector, the collector can be positioned further away from the emitter, and the potential difference between the emitter and collector can be kept well below breakdown voltage. This enhances the reliability of the electrostatic thruster and its ability to operate under various dielectric conditions in gases and / or liquids. Furthermore, due to the large distance between the emitter and collector of the thruster unit array, a relatively large number of charged particles may reside in the space between the emitter and collector of the thruster unit array, i.e., in the gap between the emitter and collector of the thruster unit array. These numerous charged particles can enhance the electrostatic thrust at the collector. The power supply can be configured to set the voltage between the emitter and collector well below the breakdown voltage, for example, below 90% or 80% of the breakdown voltage, reducing the velocity of the charged particles traveling towards the collector. This allows the particles to contribute to the electrostatic thrust for a longer period before being collected by the collector. The decreasing velocity of charged particles increases the total charge of charged particles between the emitter and collector at a given time, which can help enhance electrostatic thrust. Electrostatic thrust can pull the collector towards the charged particles between the emitter and collector; therefore, the direction of electrostatic thrust can be from the collector to the emitter. The increased distance between the emitter and collector, combined with the intermediate electrode driven by the current source and the relatively low electric field strength between the emitter and collector, can significantly increase the electrostatic thrust. Furthermore, the increase in charged particles between the emitter and collector caused by the intermediate electrode pulling charged particles emitted from the emitter towards the gap between the emitter and collector can further contribute to the increase in thrust due to ion wind.

[0030] The inventors have designed an electrostatic thruster according to the invention that can generate thrust primarily caused by electrostatic force, which can be greater than the force caused by ion wind. For example, while prior art electrostatic devices mainly rely on the generation of ion wind to generate thrust, the thruster according to the invention can generate electrostatic thrust, which contributes approximately 70% to 90% to the total thrust, while the contribution of ion wind can be approximately 10% to 30%.

[0031] The intermediate electrodes are configured to distort the electric field around each emitter by pulling more charged particles from outside the thruster array inward rather than repelling them. By doing so, the emitters can be positioned more closely together before performance degradation occurs. Increasing the number of emitters per unit area increases the generation of charged particles per unit area. This improves the performance of the electrostatic thruster.

[0032] The intermediate electrode is also configured to create a stronger electrostatic pull on the emitter of the thruster unit array while maintaining a larger thruster unit gap. The benefit of this is optimized and controlled generation of charged particles, while the thruster unit gap size does not need to be on the edge of gas / liquid dielectric breakdown, thus creating a more reliable electrostatic thruster. Secondly, the increased thruster unit gap size allows more charged particles to enter the region, creating more electrostatic pull on the collector and increasing system efficiency. Alternatively, the use of an intermediate electrode allows thrusters with relatively low voltages to become more efficient.

[0033] The intermediate electrode is electrically connected to the collector electrode of the thruster unit array via a current source configured to generate a substantially constant current.

[0034] The current source regulates the voltage on the intermediate electrode, which is charged by charged particles surrounding the emitter. By having a current source instead of an external fixed voltage, the current source generates a fixed "pull" on the emitter.

[0035] When the emitter is charged by a power source, the voltage across the intermediate electrode can be 0 V. This allows for direct dielectric breakdown without a strong arc discharge because the current through the intermediate electrode is finite and essentially constant. The voltage across the intermediate electrode can be raised to a potential as high as the voltage potential that a charged particle from the emitter can achieve by charging it. The current source limits the voltage potential of the intermediate electrode. Therefore, the voltage potential across the intermediate electrode stabilizes at a level as high as the potential that a charged particle can achieve by charging it.

[0036] By increasing the (nearly constant) current of the current source, the number of generated charged particles can be increased because the intermediate electrode pulls the charged particles away from the emitter, resulting in a lower density of charged particles around the emitter. This promotes the emission of charged particles from the emitter. Because the charged particles flow towards the intermediate electrode, if the current is increased too much, the voltage on the intermediate electrode may drop back to the potential of the collector, where the generation of charged particles is at its maximum. This could lead to persistent dielectric breakdown between the emitter and the intermediate electrode. Therefore, the current source can control the generation of charged particles at the emitter.

[0037] In some implementations, the substantially constant current can be at least an order of magnitude lower than the collector current of the operating thruster unit array. The term "order of magnitude" can be understood as a factor of 10. The collector current of the thruster unit array can be understood as the electric collector current generated due to the absorption of charged particles at the collector of the thruster unit array. The efficiency loss of the electrostatic thruster can be kept low because the discharge of charged particles at the intermediate electrode can be kept at least an order of magnitude lower than the discharge of charged particles at the collector of the thruster unit array.

[0038] In some implementations, the substantially constant current can be less than 3% of the collector current of the thruster unit array in operation, preferably between 1% and 3%. A substantially constant current less than 3% of the collector current of the thruster unit array can further enhance efficiency. A substantially constant current between 1% and 3% of the collector current of the thruster unit array can provide sufficient pull on the emitted particles to enhance electrostatic force, while maintaining high thruster efficiency and high efficiency of the emitted charged particles.

[0039] The emitter, collector, and intermediate electrodes of the thruster unit array can have a longitudinal shape, for example, extending parallel to each other in a longitudinal direction substantially perpendicular to the direction from the emitter to the collector of the thruster unit array, i.e., perpendicular to the direction of the electrostatic thruster force. This parallel arrangement and longitudinal shape allows for a high density of emitters and collectors, which in turn promotes a high density of electrostatic force.

[0040] In some implementations, the power supply can be configured to apply a voltage of the same polarity between at least one emitter and at least one collector of each thruster unit in the thruster unit array.

[0041] In some embodiments, the first distance between the emitter and the intermediate electrode may be smaller than the second distance between the collector and the intermediate electrode.

[0042] By positioning the intermediate electrode closer to the emitter than the collector electrode, it is possible to distort the electric field around the emitter while maintaining a larger size for the thruster unit gap.

[0043] In some implementations, viewed along the thrust direction, i.e., from the collector in the direction of the emitter of the thruster unit array, the intermediate electrode can be offset relative to the corresponding straight line between the emitter and collector of the thruster unit array. Due to this offset, the intermediate electrode can, on the one hand, enhance the pull of charged particles emitted from the emitter in the hemisphere away from the collector, which increases the amount of charged particles between the emitter and collector, contributing to thrust generation, while reducing the amount of charged particles retained in the hemisphere of the thruster unit array away from the collector. Furthermore, the distance between the emitter and the intermediate electrode can be increased due to the offset, which can further prevent arcing. The intermediate electrode can be offset by half a pitch between adjacent emitters of the thruster unit array, thereby providing pull for charged particles emitted simultaneously by two adjacent emitters, thus promoting a compact arrangement where the emitters can be placed relatively close together. The high density of emitters and thus collectors enables an increase in effective electrostatic thrust.

[0044] In some embodiments, the electrostatic thruster may include at least two tandemly positioned adjacent thruster unit arrays, wherein the distance between the collector of the first (upstream) thruster unit array and the emitter of the second (downstream) thruster unit array is less than the distance between the collectors of the first and second thruster unit arrays. For example, the distance between the collectors of the first and second thruster unit arrays may be less than 50%, more preferably less than 25%, of the distance between the collectors of the first and second thruster unit arrays. The collector of the first thruster unit array may be used accordingly to push charged particles emitted by the emitter of the second thruster unit array toward the gap between the emitter and collector of the second thruster unit array, as described in more detail below. Alternatively or additionally, the emitter of the second thruster unit array may collect or repel charged particles emitted by the emitter of the first thruster unit array, thus enhancing the overall efficiency of the tandemly positioned thruster unit arrays.

[0045] In some implementations, including at least two thruster units connected in series, the power supply can be configured to apply voltages of opposite polarities between at least one emitter and at least one collector of the first thruster unit in the two adjacent thruster units connected in series and between at least one emitter and at least one collector of the second thruster unit in the two adjacent thruster units connected in series.

[0046] In this way, the polarity of the collector electrode of the first thruster unit array can be equal to the polarity of the emitter electrode of the second thruster unit array. This prevents charged particles generated by the emitter electrode of the second thruster unit array from being attracted by the collector electrode of the first thruster unit array. Instead, the collector electrode of the first thruster unit array is configured to repel charged particles generated by the emitter electrode of the second thruster unit array. The second thruster unit array will benefit from the repulsive properties of the collector electrode of the first thruster unit array to enhance the generation of electrostatic thrust as described above. The pull of the intermediate electrode on charged particles emitted by the emitter of the second thruster unit array can therefore be supplemented by the repulsive force of the collector of the first thruster unit array, especially when the distance between the collector of the first thruster unit array and the emitter of the second thruster unit array is less than 50%, more preferably less than 25%, and even more preferably less than 10%, because the relatively nearby collector of the first thruster unit array will push the charged particles emitted by the emitter of the second thruster unit array toward the gap between the emitter and collector of the second thruster unit array, thus contributing to the generation of electrostatic thrust. Charged particles emitted by the emitter of the first thruster unit array and which may have passed the collector of the first thruster unit array can be attracted by the emitter of the second thruster unit array to discharge, which can prevent these particles from weakening the electrostatic force in the second thruster unit array because their charge is opposite to that of the charged particles emitted by the second thruster unit array. Therefore, according to this method, two adjacent thruster unit arrays can generate more than twice the thrust of a single thruster unit array. The collecting pole of the first thruster unit array may include a blunt edge facing the emitting pole of the second thruster unit array, such that the collecting pole of the first thruster unit array can reflect charged particles emitted by the emitting pole of the second thruster unit array and reduce or suppress the emission of charged particles by the collecting pole of the first thruster unit array.

[0047] Adjacent thruster unit arrays with equal polarity need to be spaced far enough apart to prevent attraction between the collecting pole of the first thruster unit array and the emitting pole of the second thruster unit array. Opposite polarities allow for a reduction in the distance between two adjacent thruster unit arrays. This provides the possibility of reducing the overall size and weight of electrostatic thrusters or increasing the number of thruster units in a given volume.

[0048] In some implementations, each collector electrode may have a blunt leading edge pointing toward the emitter electrode of the corresponding thruster unit.

[0049] The blunt leading edge prevents the generation of charged particles around the collector. These charged particles will attract the emitter, thus generating thrust in the opposite direction.

[0050] In some implementations, each collecting electrode may have a blunt trailing edge.

[0051] In some implementations, the collector electrode may have a sharp trailing edge, wherein the sharp trailing edge is configured to generate charged particles, and wherein the sharp trailing edge of the collector electrode is the emitter of an adjacent thruster unit array.

[0052] Charged particles generated around the sharp trailing edge of the collecting electrode attract the collecting electrodes of adjacent thruster unit arrays to generate the required thrust. This eliminates the need for separate emitting electrodes for adjacent thruster unit arrays, thereby reducing the number of components required for electrostatic thrusters.

[0053] In some implementations, the positive or negative high voltage potential applied to the collector electrode may be at least 30 kV, and more particularly at least 40 kV, so that the collector electrode repels the next thruster unit array.

[0054] In some implementations, at least two tandem thruster unit arrays are included, wherein the distance between the emitters of the first thruster unit array may be greater than the distance between the emitters of each subsequent thruster unit array.

[0055] A greater distance between the emitters of the first thruster unit array reduces the strength of the electric field lines surrounding the thruster unit array. Strong electric field lines cause a relatively large proportion of charged particles to be repelled away from the thruster in the opposite direction, generating a reaction force opposite to the expected force of an electrostatic thruster, and thus reducing its efficiency. The strength of the electric field lines surrounding the thruster unit array is reduced by the collecting electrodes, which act as repulsive reflectors for charged particles, thus reducing the portion of charged particles repelled away from the thruster unit array. This improves the performance of the electrostatic thruster.

[0056] The above-described embodiments can also be used in other electrostatic thrusters. For example, according to a second aspect of the invention, an electrostatic thruster 10 is provided for generating thrust by charging gas particles and / or liquid particles using a high voltage potential. This electrostatic thruster includes at least two thruster units, wherein each thruster unit includes:

[0057] -At least one emitter,

[0058] -At least one collection pole,

[0059] In this configuration, at least one collector electrode is spaced apart from at least one emitter electrode from the gap in the thruster unit.

[0060] The electrostatic thruster further includes a power source electrically connected to at least one emitter and at least one collector of each thruster unit, wherein the power source is configured to apply a voltage between at least one emitter and at least one collector of each thruster unit.

[0061] In this configuration, at least two thruster units are positioned in parallel to form a thruster unit array, wherein the electrostatic thruster includes at least two of the thruster unit arrays, and wherein the distance between the emitters of the first thruster unit array is greater than the distance between the emitters of each thruster unit array in the subsequent thruster unit arrays.

[0062] The technical effects mentioned above regarding the first aspect and this embodiment of the present invention also apply to the second aspect of the present invention. Further embodiments may also be combined with the second aspect of the present invention.

[0063] In some embodiments, at least one electric reflector may be positioned in front of at least one emitter of the first thruster unit array, wherein each electric reflector has a conductive surface and is smooth, wherein each electric reflector is electrically connected to a power source, and wherein the power source is configured to:

[0064] - Apply a high voltage potential to each emitter.

[0065] - Apply essentially the same high voltage potential to each nearby electric reflector.

[0066] Applying essentially the same high voltage potential to each nearby electric reflector means that the voltage does not need to be exactly the same level; however, it should at least have the same polarity to effectively repel charged particles along the direction of the collecting pole.

[0067] In some implementations, each electric reflector may have a relatively large surface area compared to the surface area of ​​each nearby emitter.

[0068] A smooth, relatively large surface area and conductive surfaces prevent any corona discharge or ion generation. Electro-reflectors allow the emitters in the first thruster unit array to be placed more closely together, while minimizing efficiency losses due to electric field lines surrounding the thruster unit array. Electro-reflectors prevent charged particles from being repelled away from the thruster unit array in the opposite direction. The ability to place the emitters more closely together provides the capability to create a relatively compact design for electrostatic thrusters.

[0069] The above-described embodiments can also be used in other electrostatic thrusters. For example, according to a third aspect of the invention, an electrostatic thruster 10 is provided for generating thrust by charging gas particles and / or liquid particles using a high voltage potential. This electrostatic thruster includes at least one thruster unit, wherein the thruster unit comprises:

[0070] -At least one emitter,

[0071] -At least one collection pole,

[0072] In this configuration, at least one collector electrode is spaced apart from at least one emitter electrode from the gap in the thruster unit.

[0073] The electrostatic thruster further includes a power source electrically connected to at least one emitter and at least one collector of the thruster unit, wherein the power source is configured to apply a voltage between at least one emitter and at least one collector of the thruster unit.

[0074] At least one electric reflector is positioned in front of at least one emitter of the thruster unit, wherein each electric reflector has a conductive surface that is smooth and has a relatively large surface area compared to the surface area of ​​each nearby emitter, wherein each electric reflector is electrically connected to a power source, and wherein the power source is configured to:

[0075] - Apply a high voltage potential to each emitter.

[0076] - Apply the same high voltage potential to each nearby electric reflector.

[0077] The technical effects mentioned above regarding the first aspect and this embodiment of the present invention are also applicable to the second aspect of the present invention. Other embodiments may also be combined with the second aspect of the present invention.

[0078] In some implementations, each electrical reflector may have a relatively small surface area similar to that of each nearby emitter, wherein the relatively small surface area is covered by a fine insulator.

[0079] A fine insulator is only sufficient to prevent the emission of charged particles, while providing a sufficiently strong electric field to repel nearby charged particles.

[0080] In some implementations, the emitter may include a plurality of emitter electrodes closely positioned together, wherein the plurality of emitter electrodes are configured to act as a single emitter.

[0081] Positioning multiple emitter electrodes closely together increases the particle charging characteristics of a single emitter, thereby enhancing the overall emission of charged particles. For example, multiple emitter electrodes can extend parallel to each other with a distance of less than 1 mm between them, which can promote high-charged particle emission, and in turn, enhance electrostatic thrust. When, for example, the first thruster unit array includes fewer emitters than subsequent thruster unit arrays, it may be advantageous to configure multiple emitter electrodes to act as a single emitter to generate a similar amount of charged particles in both the first and subsequent thruster unit arrays. Multiple emitter electrodes can extend parallel to each other with a distance of less than 1 mm between them, thereby enhancing the overall emission while allowing parallel emitters to act as single emitters providing high-charged particle emission.

[0082] The above-described embodiments can also be used in other electrostatic thrusters. For example, according to a fourth aspect of the invention, an electrostatic thruster 10 is provided for generating thrust by charging gas particles and / or liquid particles using a high voltage potential. This electrostatic thruster includes at least one thruster unit, wherein each thruster unit includes:

[0083] -At least one emitter,

[0084] -At least one collection pole,

[0085] In this configuration, at least one collector electrode is spaced apart from at least one emitter electrode from the gap in the thruster unit.

[0086] The electrostatic thruster further includes a power source electrically connected to at least one emitter and at least one collector of the thruster unit, wherein the power source is configured to apply a voltage between at least one emitter and at least one collector of the thruster unit.

[0087] The emitter includes multiple emitter electrodes closely positioned together, wherein the multiple emitter electrodes are configured to act as a single emitter.

[0088] The technical effects mentioned above regarding the first aspect and this embodiment of the present invention are also applicable to the second aspect of the present invention. Other embodiments may also be combined with the second aspect of the present invention.

[0089] In some implementations, the power supply is configured to apply a pulsed voltage to each emitter so that the voltage alternates between two or more adjacent emitters.

[0090] Alternating voltage between two adjacent emitters can be understood as applying a voltage to the first emitter of the adjacent emitters during the first portion of the pulse repetition time, and applying zero, low, or no voltage to the second emitter of the adjacent emitters during the first portion of the pulse repetition time. The power supply is configured to apply a voltage to the second emitter of the adjacent emitters during the second portion of the pulse repetition time, i.e., the remainder, and to apply zero, low, or no voltage to the first emitter of the adjacent emitters. This can be extended with different activation schemes to apply voltage to the emitters of two or more adjacent emitters during different time periods.

[0091] By providing low duty cycle pulses, a similar number of particles can be charged when a higher current flows through the dielectric fluid (air). On average, the power consumption is similar.

[0092] Another benefit of applying pulses to the emitters is the reduction of repulsive force, as it is no longer a continuous field. When multiple emitters are positioned close to each other, alternating pulses between emitters ensures that the electric fields of nearby emitters hardly interfere with each other, and also causes more charged particles to move toward the collector in the desired direction. This creates a more efficient electrostatic propulsion system that uses less material and is lighter.

[0093] The above-described embodiments can also be used in other electrostatic thrusters. For example, according to a fifth aspect of the invention, an electrostatic thruster 10 is provided for generating thrust by charging gas particles and / or liquid particles using a high voltage potential. This electrostatic thruster includes at least two thruster units, wherein each thruster unit includes:

[0094] -At least one emitter,

[0095] -At least one collection pole,

[0096] In this configuration, at least one collector electrode is spaced apart from at least one emitter electrode from the gap in the thruster unit.

[0097] The electrostatic thruster also includes a power source electrically connected to at least one emitter and at least one collector electrode of each thruster unit, wherein the power source is configured to apply a voltage between at least one emitter and at least one collector electrode of each thruster unit.

[0098] In this configuration, at least two thruster units are positioned in parallel to form a thruster unit array, wherein a power source is configured to apply a pulsed voltage to each emitter.

[0099] The technical effects mentioned above regarding the first aspect and this embodiment of the present invention are also applicable to the second aspect of the present invention. Further embodiments may also be combined with the second aspect of the present invention.

[0100] In some implementations, each emitter and each collector may be elongated, and the emitter may include a longitudinal axis.

[0101] In some implementations, the size of the thruster unit gap can vary along the longitudinal axis of the emitter. For example, the emitter can have a serrated edge facing the collector, the serrated edge extending along the longitudinal axis of the emitter. As another example, the emitter can be zig-shaped.

[0102] For example, by alternating the size of the thruster unit gap along the longitudinal axis of the emitter due to the zigzag shape or serrated edges of the emitter, the effective length of the emitter can be increased without increasing the length of the collector. Because of this alternating distance and the increased emitter length, charged particles are generated over a larger area and, on average, at a greater distance from the collector. As a result, more charged particles are located on the intended side of the collector for a longer period, leading to increased thrust. Simultaneously, for the same amount of thrust, this configuration results in lower input power, thus significantly improving efficiency. Furthermore, the zigzag shape or serrated edges of the emitters of the thruster unit array (facing the collector of the thruster unit array) can increase the effective distance between the emitter and collector, particularly at the recesses of the zigzag shape within the serrations of the serrated edges. The zigzag shape or serrations can result in the maximum gap size being 50% to 100% larger than the minimum gap size.

[0103] The above-described embodiments can also be used in other electrostatic thrusters. For example, according to a sixth aspect of the invention, an electrostatic thruster 10 is provided for generating thrust by charging gas particles and / or liquid particles using a high voltage potential. This electrostatic thruster includes at least one thruster unit, wherein the thruster unit comprises:

[0104] -At least one emitter,

[0105] -At least one collection pole,

[0106] In this configuration, at least one collector electrode is spaced apart from at least one emitter electrode from the gap in the thruster unit.

[0107] The electrostatic thruster further includes a power source electrically connected to at least one emitter and at least one collector of the thruster unit, wherein the power source is configured to apply a voltage between at least one emitter and at least one collector of the thruster unit.

[0108] Each emitter and each collector may be elongated, and the emitter includes a longitudinal axis, and the size of the thruster unit gap may vary in the direction of the longitudinal axis of the emitter.

[0109] The technical effects described above in the first aspect and this embodiment of the present invention are also applicable to the second aspect of the present invention. Other embodiments may also be combined with the second aspect of the present invention.

[0110] In some embodiments, a barrier made of non-conductive material may be positioned on the opposite side of the emitter, and wherein the barrier conforms to the shape of the emitter.

[0111] The negative impact of altered emitter shape is that, due to the presence of more emitters nearby, charged particles generated outside the thruster are more strongly repelled in the wrong direction. To mitigate this negative effect, a deflector made of a non-conductive material should be positioned on the opposite side of the emitter, closely conforming to its shape. The deflector repels charged particles moving in the opposite direction and redirects them towards the intended direction of the collector.

[0112] In some embodiments, the first side of the collecting electrode may include a non-conductive material pointing toward a second side of the collecting electrode of an adjacent thruster unit that does not contain a non-conductive material, wherein the second side is configured to attract charged particles, and wherein the first side is not configured to attract charged particles.

[0113] When charged particles move between two collectors with equal conductivity, the charged particles at the center are attracted equally by both collectors and continue along a straight path. Because of this, they may pass the collectors before losing their charge, creating a backward pull on the collectors and thus reducing the efficiency of the propulsion system. If each collector has a non-conductive material on one side, the charged particles are pulled towards the conductive side of the adjacent collector. This reduces the amount of charged particles passing through the collectors.

[0114] The above-described embodiments can also be used in other electrostatic thrusters. For example, according to a seventh aspect of the invention, an electrostatic thruster 10 is provided for generating thrust by charging gas particles and / or liquid particles using a high voltage potential. This electrostatic thruster includes at least two thruster units, wherein each thruster unit includes:

[0115] -At least one emitter,

[0116] -At least one collection pole,

[0117] In this configuration, at least one collector electrode is spaced apart from at least one emitter electrode from the gap in the thruster unit.

[0118] The electrostatic thruster further includes a power source electrically connected to at least one emitter and at least one collector of each thruster unit, wherein the power source is configured to apply a voltage between at least one emitter and at least one collector of each thruster unit.

[0119] In this configuration, at least two thruster units are positioned in parallel to form a thruster unit array, wherein a first side of each collector electrode comprises a non-conductive material and a second side of each collector electrode does not comprise a non-conductive material, wherein the first side of the collector electrode of a thruster unit points to the second side of the collector electrode of an adjacent thruster unit, wherein the second side is configured to attract charged particles, and wherein the first side is not configured to attract charged particles.

[0120] The technical effects mentioned above in the first aspect and this embodiment of the present invention are also applicable to the second aspect of the present invention. Other embodiments may also be combined with the second aspect of the present invention.

[0121] In some embodiments, the thruster unit may include a first collector electrode and a second collector electrode having the same voltage potential as the first collector electrode, wherein the first collector electrode and the second collector electrode are spaced apart by a collector electrode gap, and wherein the first collector electrode is positioned between at least one emitter electrode and the second collector electrode.

[0122] In some implementations, the second collector is mechanically disconnected from the first collector.

[0123] Because the second collector shares the same potential as the first collector, any opposing electric field generated by charged particles remaining charged as they pass through the first collector is canceled out by the second collector. Therefore, charged particles passing through the first collector cannot resist the intended force of the thruster. When a negative or positive voltage is applied to both the first and second collectors, the collectors will also repel each other, further increasing net force and efficiency. This is particularly beneficial in applications such as acceleration lift or sustained hovering above a fixed collector system.

[0124] The above-described embodiments can also be used in other electrostatic thrusters. For example, according to an eighth aspect of the invention, an electrostatic thruster 10 is provided for generating thrust by charging gas particles and / or liquid particles using a high voltage potential. This electrostatic thruster includes at least one thruster unit, wherein the thruster unit comprises:

[0125] -At least one emitter,

[0126] -At least one collection pole,

[0127] In this configuration, at least one collector electrode is spaced apart from at least one emitter electrode from the gap in the thruster unit.

[0128] The electrostatic thruster further includes a power source electrically connected to at least one emitter and at least one collector of the thruster unit, wherein the power source is configured to apply a voltage between at least one emitter and at least one collector of the thruster unit.

[0129] The thruster unit includes a first collector and a second collector, wherein a power source is configured to apply the same voltage potential to the first collector and the second collector of the thruster unit, wherein the first collector and the second collector of the thruster unit are spaced apart by a collector gap, and wherein in the thruster unit, the first collector is positioned between at least one emitter and the second collector.

[0130] The technical effects mentioned above regarding the first aspect and this embodiment of the present invention are also applicable to the second aspect of the present invention. Other embodiments may also be combined with the second aspect of the present invention.

[0131] In some embodiments, the power supply may be configured to apply a voltage difference between each emitter of the first thruster unit array and each collector of the second thruster unit array, and wherein the electrostatic thruster includes at least one electric reflector configured to bend the electric field of adjacent thruster unit arrays, wherein the electric reflector is positioned between the thruster unit arrays, and wherein the distance between the second thruster unit array and the electric reflector is less than the distance between the first thruster unit array and the electric reflector.

[0132] In some implementations, the power supply can be configured to apply the same voltage potential to both the emitter and the corresponding electric reflector.

[0133] In some implementations, each electrical reflector may be insulated to reduce the generation of charged particles.

[0134] In some implementations, the surface area of ​​the electric reflector can be larger than the surface area of ​​the emitter.

[0135] The above-described embodiments can also be used in other electrostatic thrusters. For example, according to a ninth aspect of the invention, an electrostatic thruster 10 is provided for generating thrust by charging gas particles and / or liquid particles using a high voltage potential. This electrostatic thruster includes at least two thruster units, wherein each thruster unit includes:

[0136] -At least one emitter,

[0137] -At least one collection pole,

[0138] In this configuration, at least one collector electrode is spaced apart from at least one emitter electrode from the gap in the thruster unit.

[0139] The electrostatic thruster further includes a power source electrically connected to at least one emitter and at least one collector of each thruster unit, wherein the power source is configured to apply a voltage between at least one emitter and at least one collector of each thruster unit.

[0140] In this configuration, at least two thruster units are positioned in parallel to form a thruster unit array, wherein electrostatic thrusters comprise at least two of the thruster unit arrays, wherein a power source is configured to apply a voltage difference between each emitter of a first thruster unit array and each collector of a second thruster unit array, and wherein the electrostatic thruster includes at least one electric reflector configured to bend the electric field of adjacent thruster unit arrays, wherein the electric reflector is positioned between the thruster unit arrays, and wherein the distance between the second thruster unit array and the electric reflector is less than the distance between the first thruster unit array and the electric reflector.

[0141] The technical effects mentioned above regarding the first aspect and this embodiment of the present invention are also applicable to the second aspect of the present invention. Other embodiments may also be combined with the second aspect of the present invention.

[0142] The present invention also relates to aircraft, particularly airplanes or unmanned aircraft, including the electrostatic propulsion system described in any one of the preceding claims.

[0143] The present invention also relates to spacecraft, particularly small satellites, including the electrostatic thruster of any one of the preceding claims.

[0144] The advantages of the features mentioned above also apply to aircraft, unmanned aerial vehicles, or small satellites. Aircraft or spacecraft with smaller, lighter, and more efficient electrostatic propulsion will significantly increase their operational freedom. This will increase their operational range, their maximum permissible payload, and their future sustainability.

[0145] The present invention also relates to an electrostatic wing thruster (100) for providing thrust to a wing configured for moving through a fluid, wherein the electrostatic wing thruster comprises:

[0146] - The wing, which includes:

[0147] The front portion, wherein the front portion includes at least one front emitter,

[0148] The upper part, which includes at least one collecting electrode positioned on the upper surface of the wing,

[0149] The lower part, wherein the lower part includes at least one lower reflector positioned on the lower surface of the wing,

[0150] - A power supply electrically connected to at least one emitter, at least one reflector, and at least one collector, wherein the power supply is configured to:

[0151] A high voltage potential is applied to each front emitter and each reflector.

[0152] Apply an opposite high voltage potential or a neutral voltage potential to each collector electrode.

[0153] Each emitter is configured to generate charged particles, each reflector is configured to repel charged particles, and each collector is configured to attract charged particles.

[0154] Fluid (air) flow causes charged particles to move along the underside of the wing. As the charged particles pass at least one reflector of the same polarity, the reflector repels the wing upwards and the charged particles downwards, thus creating a high voltage beneath the wing. Charged particles moving along the top of the wing (through fluid flow and electrostatic forces) are attracted to at least one collector at the top, while the collector and the wing are drawn upwards towards the charged particles, creating a low voltage above the wing. This provides the ability to control the upward or downward movement of the wing.

[0155] In some implementations, each front emitter may be spaced apart from the front surface of the wing by a front gap.

[0156] In some embodiments, the lower portion of the wing may include at least one lower emitter spaced apart from the lower surface of the wing by a lower gap, wherein each lower emitter is electrically connected to a power source, and wherein the power source is configured to apply a high voltage potential to each lower emitter.

[0157] The present invention also relates to aircraft, particularly airplanes or unmanned aircraft, including the electrostatic wing propulsion of any one of claims 26 to 28.

[0158] The present invention also relates to vessels, particularly submarines or hydrofoils, including the electrostatic wing propulsion system of any one of claims 26 to 28.

[0159] The advantages of the features mentioned above also apply to aircraft or ships that include the electrostatic wing thruster 100. The electrostatic wing thruster 100 will significantly improve the controllability of the equipment. Attached Figure Description

[0160] Figures 1a to 1b An isometric view of an embodiment of an electrostatic thruster with a central electrode is shown.

[0161] Figure 2 A schematic diagram of a thruster unit array with an intermediate electrode is shown.

[0162] Figures 3a to 3bA schematic diagram of two thruster units connected in series is shown.

[0163] Figure 4 An isometric view of the thruster unit is shown.

[0164] Figures 5a to 5b An isometric view of an electrostatic thruster is shown.

[0165] Figure 6a A schematic diagram of the thruster unit array is shown.

[0166] Figure 6b A schematic diagram of two thruster unit arrays connected in series is shown.

[0167] Figures 7a to 7b An isometric view of an electrostatic thruster with an electric reflector is shown.

[0168] Figure 8 A schematic diagram of two thruster unit arrays with electric reflectors is shown.

[0169] Figure 9 An isometric view of a thruster unit array with multiple emitter electrodes is shown.

[0170] Figure 10 A schematic diagram of a thruster unit array with a pulsed voltage source is shown.

[0171] Figure 11 A side view of the thruster unit is shown.

[0172] Figures 12a to 12b A schematic diagram of the collector poles of the thruster unit array is shown.

[0173] Figure 13 An isometric view of an electrostatic thruster is shown.

[0174] Figure 14 An isometric view of a thruster unit with an additional collecting pole is shown.

[0175] Figure 15 A schematic diagram of two thruster units with electric reflectors is shown.

[0176] Figures 16a to 16b A cross-sectional view of an electrostatic wing propulsion system is shown. Detailed Implementation

[0177] Go to Figures 1a to 1b and Figure 4An electrostatic thruster 10 is shown that generates thrust by charging gas particles and / or liquid particles using a high voltage potential. The electrostatic thruster 10 uses Coulomb force and accelerates the gas particles and / or liquid particles in the direction of the electric field. The electrostatic thruster 10 includes at least two thruster units 20. Each thruster unit 20 includes at least one emitter 22 and at least one collector 24. The at least two thruster units 20 are positioned in parallel to form a thruster unit array 40. The parallel thruster units may be arranged along a direction perpendicular to the direction of the electric field between the emitter and collector. The parallel thruster units may also be arranged in different, non-parallel configurations, such as triangular, square, or hexagonal configurations.

[0178] The electrostatic thruster 10 also includes a power supply 30 electrically connected to at least one emitter 22 and at least one collector 24. The power supply 30 is configured to apply a direct current (DC) voltage between at least one emitter 22 and at least one collector 24 in each thruster unit 20. By applying the voltage between the emitter 22 and collector 24, charged particles 5 are generated around the emitter 22. The charged particles 5 and the collector 24 attract each other, thereby creating a force on the electrostatic thruster 10 in the direction of the emitter 22. Assuming the force generated by the electrostatic thruster acts in the vertical direction, i.e., pushing the thruster upwards, the emitter of the thruster unit can be perpendicularly above the collector of the thruster unit.

[0179] The emitter 22 has a relatively small surface area compared to the collector 24. This smaller surface area allows for the ionization of the fluid, such as the gas and / or liquid surrounding the emitter 22. This is known as corona discharge. The collector 24 has a relatively large surface area to prevent any ionization that would otherwise result in particles 5 with opposite charges. These oppositely charged particles 5 are attracted to the emitter 22 of the corresponding thruster unit 20, thereby generating thrust in opposite directions. The power source is configured to generate a sufficiently high voltage to induce ionization in the ambient fluid surrounding the emitter, for example, at least 5 kV in air, preferably 20 kV to 40 kV. In other gases or liquids, the voltage may vary considerably, depending on the dielectric strength of the gas / liquid. The emitter and collector may be formed of conductive structures, such as metallic structures, that can be at least partially in direct contact with the ambient fluid to charge particles in the ambient fluid, for example, at the emitter, and to discharge charged particles in the ambient fluid, for example, at the collector.

[0180] This force comprises two main components. The first component is caused by the attraction of the collecting electrode 24 in the direction of the charged particles 5 surrounding the emitting electrode 22. The other component is caused by the charged particles 5, which move in the direction of the collecting electrode 24 and thereby push gas particles and / or liquid particles in the surrounding medium to create a thrust in the direction of the emitting electrode.

[0181] Go to Figure 1b , Figures 2 to 3b The electrostatic thruster 10 may further include at least two adjacent thruster unit arrays 40a and 40b arranged in series. Adjacent thruster unit arrays 40 are thruster unit arrays 40 positioned adjacent to each other without any thruster unit array positioned between them. The series arrangement of the thruster unit arrays can be understood as the thruster unit arrays (each comprising at least two parallel thruster units) being arranged along the direction of the electric field, i.e., the direction of the force generated by the thruster. Figure 2 An array of single thruster units in series is shown. (Example) Figure 3a As can be seen, the distance 41a between the collecting pole 24 of the first thruster unit array 40a and the emitting pole 22 of the second thruster unit array 40b is smaller than the distance 41b between the collecting pole 24 of the first thruster unit array 40a and the collecting pole 24 of the second thruster unit array 40b. Multiple thruster unit arrays 40 can be positioned in series. This will result in... Figure 1b The arrays 40a, 40b and 40c show multiple rows of emitters 22 and collectors 24 following each other.

[0182] The power supply 30 is configured to apply a voltage of the same polarity between at least one emitter 22 and at least one collector 24 of each thruster unit 20 in the thruster unit array 40. This ensures that adjacent thruster units 20 in the thruster unit array 40 do not interfere with each other, which could lead to undesirable forces and / or dielectric breakdown in opposite directions when the distance between the thruster unit arrays is insufficient.

[0183] At least one collector electrode 24 is spaced apart from at least one emitter electrode 22 by a thruster unit gap 28. The thruster unit gap 28 is a critical factor in the efficiency of the electrostatic thruster 10. Increasing the gap ensures that charged particles 5 remain within the thruster unit gap 28 for a longer period of time, generating greater thrust when the total amount of charged particles emitted between the emitter and collector electrodes can increase. On the other hand, a larger thruster unit gap 28 will also increase the size of the device, requiring more material and resulting in a heavier electrostatic thruster 10. The thruster unit array 40 also includes an intermediate electrode 42. The intermediate electrode is configured to distort the electric field around each emitter by pulling more charged particles inward onto the outside of the thruster array, i.e., pulling them into the space between the emitter and collector electrodes, rather than repelling them. Furthermore, by doing so, the emitters can be positioned more closely together before performance loss occurs.

[0184] Intermediate electrode 42 is positioned in the intermediate region 44 between the emitter 22 and collector 24 of two adjacent thruster units 20 in the thruster unit array 40. A first distance 45 between the emitter 22 and intermediate electrode 42 is less than a second distance 46 between the collector 24 and intermediate electrode 42. For example, the first distance 45 may be 50% or less of the second distance 46. Viewed from the direction of thrust, intermediate electrode 42 can be positioned at the corresponding center between adjacent emitters of the thruster unit array, which can pull charged particles emitted from two adjacent emitters while avoiding the intermediate electrode being positioned in the main path of charged particles from the corresponding emitter to the corresponding collector, in which the intermediate electrode would attract many charged particles (which would in turn increase the voltage of the current-driven intermediate electrode, bringing it closer to the emitter voltage, thereby reducing the pull on the charged particles). Intermediate electrode 42 is electrically connected to the collector 22 of the same thruster unit array 40 via current source 32. The current source 32 is configured to apply a constant current to the intermediate electrode 42, such that a predetermined amount of charged particles generated at the emitter are collected by the intermediate electrode, thus maintaining the collected charged particles at a predetermined level. The intermediate electrode may include a conductive structure, such as a metallic structure, and may extend along the emitter and collector electrodes of the thruster unit array. The intermediate electrode 42 is offset relative to the corresponding straight line between the emitter and collector electrodes 42 of the thruster unit array by half the spacing between adjacent emitters 22 of the thruster unit array, to provide a pull force on the charged particles emitted simultaneously by two adjacent emitters 22.

[0185] Current source 32 is configured to apply a current level ranging from 1 µA to 10 µA to each intermediate electrode 42. This is approximately 1% to 3% of the total current supplied to the electrostatic thruster. The current level depends on the dielectric strength of the gas or liquid surrounding the electrostatic thruster and the position of the intermediate electrode relative to the emitter and collector electrodes of the electrostatic thruster. Ideally, the current level supplied to the intermediate electrodes should be a low percentage of the total current. A high percentage would indicate that too many charged particles are discharged before reaching the collector electrode of the thruster unit.

[0186] The intermediate electrode 42 is also configured to create a stronger electrostatic pull on the emitter 22 of the thruster unit array 40 while maintaining a larger thruster unit gap 28. The benefit of this is optimized and controlled generation of charged particles 5, while the size of the thruster unit gap 28 does not need to be on the edge of gas / liquid dielectric breakdown, thus creating a more reliable electrostatic thruster 10. Secondly, the increased size of the thruster unit gap 28 allows more charged particles 5 to enter the region, creating more electrostatic pull on the collector 24 and increasing system efficiency. Alternatively, the use of the intermediate electrode 42 allows thrusters with relatively low voltages to become more efficient.

[0187] Charged particles emitted from the emitter can be drawn through an intermediate electrode toward the space between the emitter and collector of the thruster unit. The intermediate electrode is electrically connected to the collector of the thruster unit via a current source configured to generate a substantially constant current. The current source can provide a substantially constant discharge of charged particles to the intermediate electrode. Therefore, the amount of discharge of charged particles through the intermediate electrode can be well controlled. The voltage (potential) of the intermediate electrode can be self-adjusted based on the substantially constant current from the current source. The substantially constant current generated by the current source and drawn at the intermediate electrode can effectively pull the charged particles emitted from the emitter into the space between the emitter and collector of the thruster unit, thus drawing the charged particles into this space where they can contribute to the electrostatic forces on the emitter and collector of the thruster unit array. On the other hand, the substantially constant current generated by the current source can limit the discharge of charged particles at the intermediate electrode and make the voltage at the intermediate electrode self-adjusting: the voltage at the intermediate electrode can be self-adjusted based on the substantially constant current to provide discharge of charged particles.

[0188] exist Figures 3a to 3b In the process, for two adjacent thruster units connected in series, the power supply 30 is configured to apply voltages of opposite polarities between at least one emitter 22 and at least one collector 22 of the first thruster unit 20a in the two adjacent thruster units 20 and between at least one emitter 22 and at least one collector 24 of the second thruster unit 20b in the two adjacent thruster units 20 connected in series.

[0189] In this way, the polarity of the collecting pole 24 of the first thruster unit array 40a is equal to that of the emitting pole 22 of the second thruster unit array 40b. This prevents the charged particles 5 generated by the emitting pole 22 of the second thruster unit array 40b from being attracted by the collecting pole 24 of the first thruster unit array 40a. Instead, the collecting pole 24 of the first thruster unit array 40a is configured to repel the charged particles 5 generated by the emitting pole 22 of the second thruster unit array 40b. The second thruster unit array 40b will benefit from the repulsive properties of the collecting pole 24 of the first thruster unit array 40a. Therefore, according to this method, two adjacent thruster unit arrays 40a and 40b generate more than twice the thrust of a single thruster unit array 40a.

[0190] The positive or negative high voltage potential applied to the collector electrode 24 is at least 30 kV, and more particularly at least 40 kV, so that the collector electrode 24 has a repulsive effect on the next thruster unit array 40.

[0191] Adjacent thruster unit arrays 40 with equal polarity need to be spaced far enough apart to prevent attraction between the collecting pole 24 of the first thruster unit array 40a and the emitting pole 22 of the second thruster unit array 40b. Opposite polarities allow for a reduction in the distance between two adjacent thruster unit arrays 40. This provides the possibility of reducing the overall size and weight of the electrostatic thruster 10 or increasing the number of thruster unit arrays 40a, 40b, 40c in a given volume.

[0192] Each collector electrode 24 has a blunt leading edge 25 pointing towards the corresponding emitter electrode of the thruster unit 20. The blunt leading edge 25 has a relatively large surface area compared to the surface area of ​​the emitter electrode 22. The blunt leading edge 25 also has no sharp angles. These combined features prevent the generation of charged particles 5 around the collector electrode 24. These charged particles 5 would attract the emitter electrode and thus generate thrust in the opposite direction.

[0193] Furthermore, each collector electrode 24 may have a blunt trailing edge 26 or a sharp trailing edge 27. A blunt trailing edge 27 provides the same advantages as a blunt leading edge 25. On the other hand, a sharp trailing edge 27 is configured to generate charged particles 5. Compared to a blunt leading edge 25, a sharp trailing edge 27 comprises a relatively small surface area, which allows for corona discharge when a sufficiently high voltage is applied by the power supply 30. The sharp trailing edge 27 of the collector electrode 24 serves as the emitter of the adjacent thruster unit array 40.

[0194] Charged particles 5 generated around the sharp trailing edge 27 of the collecting pole 24 attract the collecting poles 24 of adjacent thruster unit arrays 40 to generate the required thrust. This eliminates the need for separate emitting poles 22 for adjacent thruster unit arrays 40, reducing the number of components required for the electrostatic thruster 10.

[0195] Go to Figures 5a to 5b A portion of an electrostatic thruster 10 is shown, wherein the distance between the emitters 22 of the first thruster unit array 40a is greater than the distance between the emitters 22 of each subsequent thruster unit array 40. According to Figure 5a and Figure 5b The electrostatic thruster may also include at least one intermediate electrode and a current source, which are omitted in the accompanying drawings for clarity.

[0196] Go to Figures 6a to 6b This illustrates the effect of a larger distance between the emitters 22. A larger distance between the emitters 22 of the first thruster unit array 40a reduces the strength of the electric field lines surrounding the thruster unit array 40. Strong electric field lines cause a relatively large proportion of the charged particles 5 to be repelled away from the thruster in the opposite direction, generating a reaction force opposite to the intended force of the electrostatic thruster 10, and thus reducing its efficiency. See [link to relevant documentation]. Figure 6a The electric field lines surrounding the thruster unit array 40 are reduced by the collector 24, which acts as a repulsive reflector for the charged particles 5, thereby reducing the portion of the charged particles 5 that are repelled away from the thruster unit array 40, see 6b. Figure 6a and Figure 6b The electrostatic thruster may also include at least one intermediate electrode and a current source, which are omitted in the accompanying drawings for clarity.

[0197] Turn Figures 7a to 8 An electrostatic thruster 10 with an electric reflector 21 is shown. At least one electric reflector 21 is positioned in front of at least one emitter 22 of a first thruster unit array 40a. Each electric reflector 21 has a conductive surface, is smooth, and has a relatively large surface area compared to the surface area of ​​each nearby emitter 22. Each electric reflector 21 is electrically connected to a power supply 30, which is configured to:

[0198] - Apply a high voltage potential to each emitter 22

[0199] - Apply the same high voltage potential to each nearby electric reflector 21.

[0200] A smooth, relatively large surface area and conductive surface prevent any corona discharge or ion generation. The electric reflector 21 allows the emitters in the first thruster unit array 40 to be placed more closely together, while minimizing efficiency losses due to the electric field lines surrounding the thruster unit array 40. The electric reflector 21 prevents charged particles 5 from being repelled away from the thruster unit array 40 in the opposite direction. Figures 7a to 8 The electrostatic thruster may also include at least one intermediate electrode and a current source, which are omitted in the accompanying drawings for clarity.

[0201] Go to Figure 9 An electrostatic thruster 10 with an emitter 22 having a plurality of emitter electrodes 23 is shown. Each emitter 22 includes a plurality of emitter electrodes 23 closely positioned together. The plurality of emitter electrodes 23 are configured to act as a single emitter 22. The plurality of emitter electrodes can extend parallel to each other with a distance of less than 1 mm between the emitter electrodes, which can facilitate the parallel emitters effectively acting as a single emitter with high emission. Figure 9 The electrostatic thruster may also include at least one intermediate electrode and a current source, which are omitted in the accompanying drawings for clarity.

[0202] Go to Figure 10The diagram illustrates an electrostatic thruster 10, whose power supply 30 is configured to apply a pulsed voltage to each emitter 22. By providing pulses with a low duty cycle, a similar number of particles can be charged while a higher current flows through the dielectric fluid (air). On average, the power consumption is similar. Another benefit of applying pulses to the emitters 22 is the reduction of repulsive force, as it is no longer a constant field. When multiple emitters 22 are positioned close to each other, alternating pulses between emitters ensures that the electric fields of nearby emitters hardly interfere, and also causes more charged particles 5 to move toward the collector 24 in the intended direction. Figure 10 The electrostatic thruster depicted may also include at least one intermediate electrode and a current source, which are omitted in the accompanying drawings for clarity.

[0203] Go to Figure 11 An electrostatic thruster 10 is shown, wherein each emitter 22 and each collector 24 is elongated. The emitter 22 includes a longitudinal axis 12. The dimensions of the thruster unit gap 28 vary in the direction of the longitudinal axis 12 of the emitter 22. In the depicted example, the emitter includes a zigzag shape. By alternating the dimensions of the thruster unit gap 28 in the direction of the longitudinal axis 12 of the emitter 22, the length of the emitter 22 can be increased without increasing the length of the collector 24. Because of this alternating distance and the increased emitter length, charged particles 5 are generated over a larger area and, on average, at a greater distance from the collector 24. As a result, more charged particles 5 are located on the intended side of the collector 24 for a longer period, leading to increased thrust. The zigzag shape of the emitter increases the effective distance between the emitter and collector, particularly at the concave portion of the zigzag shape, where the emitter is furthest from the collector, i.e., where the gap exhibits its longest length. An increased effective distance between the emitter and collector may contribute to an increase in the total number of charged particles, thereby increasing the total charge between the emitter and collector, which contributes to electrostatic thrust. Furthermore, a zigzag shape or sawtooth pattern can, for example, result in the maximum size of gap 28 being 50% to 100% larger than the minimum size of gap 28. Figure 11 The depicted electrostatic thruster may also include at least one intermediate electrode and a current source, which are omitted in the accompanying drawings for clarity.

[0204] At the same time, this configuration results in low input power for the same amount of thrust, thereby significantly improving efficiency. A non-conductive material blocking element 29 is positioned on the opposite side 14 of the emitter 22, and wherein the blocking element 29 conforms to the shape of the emitter 29.

[0205] Go to Figures 12a to 12bThe diagram shows two adjacent collecting poles 24. A first side 52 of the collecting pole 24 includes a non-conductive material 50, which points towards a second side 53 of the adjacent thruster unit 20's collecting pole 24, which lacks the non-conductive material 50. The second side 53 is configured to attract charged particles 5, while the first side 52 is not configured to attract charged particles 5.

[0206] When a charged particle 5 moves between two collectors 24 with equal conductivity, the charged particle 5 at the center is attracted equally by both collectors 24 and continues along a straight path, as shown in the image. Figure 12a As shown. Because of this, they may pass the collector 24 before losing their charge, creating a backward pull on the collector 24, and thus reducing the efficiency of the electrostatic thruster 10. In the case where one side of each collector 24 includes a non-conductive material 50, the charged particles 5 are pulled towards the conductive side of the adjacent collector 24, as shown. Figure 12b This can be seen in the image. This reduces the amount of charged particles 5 passing through the collecting pole 24.

[0207] Go to Figure 13 The diagram shows an electrostatic thruster 10 having an electric reflector 21, an intermediate electrode 42, and a collecting electrode 24 having a non-conductive material 50. Figure 13 An implementation in which the technical effects of different features are combined in a single embodiment is shown. This is a basic example of an implementation having multiple features to improve the efficiency of the electrostatic thruster 10. Various other implementations are possible, in which different features can be combined to form a single electrostatic thruster 10.

[0208] Go to Figure 14 The diagram illustrates a thruster unit 20 having a first collector electrode 24a and a second collector electrode 24b. The second collector electrode 24b has the same voltage potential as the first collector electrode 24a. The first collector electrode 24a and the second collector electrode 24b are spaced apart by a collector electrode gap 16, with the first collector electrode 24a positioned between at least one emitter electrode 22 and the second collector electrode 24b. The second collector electrode 24b is mechanically disconnected from the first collector electrode 24a.

[0209] Because the second collector 24b shares the same potential as the first collector 24a, any opposing electric field generated by the charged particle 5 remaining charged as it passes through the first collector 24a is canceled out by the second collector 24b. Therefore, the charged particle 5 passing through the first collector 24a cannot resist the intended force of the electrostatic thruster 10. When a negative or positive voltage is applied to the first collector 24a and the second collector 24b, the collectors will also repel each other, further increasing net force and efficiency. Figure 14 The depicted electrostatic thruster units may also each include at least one intermediate electrode and a current source, which are omitted in the figures for clarity.

[0210] Go to Figure 15 The diagram illustrates two thruster units 40a and 40b connected in series. A power supply 30 is configured to apply a voltage difference between each emitter 22 of the first thruster unit array 40a and each collector 24 of the second thruster unit array 40b. The electrostatic thruster 10 includes at least one electric reflector 60 configured to bend the electric field of adjacent thruster unit arrays 40. The electric reflector 60 is positioned between the thruster unit arrays 40a and 40b, and the distance between the second thruster unit array 40b and the electric reflector 60 is less than the distance between the first thruster unit array 40a and the electric reflector 60. Figure 10 The depicted thruster units may each include at least one intermediate electrode and a current source, which are omitted in the figures for clarity.

[0211] The power supply 30 is configured to apply the same voltage potential to the emitter 22 and the corresponding electric reflector 60. Each electric reflector 60 is either insulated or has a sufficiently large surface area to reduce the generation of charged particles 5. The surface area of ​​the electric reflector 60 is larger than the surface area of ​​the emitter 22.

[0212] The electrostatic thruster 10 can be implemented in aircraft, especially airplanes or unmanned aerial vehicles.

[0213] The electrostatic thruster 10 can also be implemented in spacecraft, especially small satellites, such as microsatellites, nanosatellites, picosatellites or femtosatellites.

[0214] Go to Figures 16a to 16b An electrostatic wing thruster 100 is shown for providing thrust 101 to a wing 110, which is configured to move 102 through a fluid 103. The electrostatic wing thruster 100 includes a wing 110 and a power source 130. The wing 110 includes a front portion 112, an upper portion 114, and a lower portion 116. The front portion 112 includes at least one front emitter 120. The upper portion 114 includes at least one collector 122 positioned at the upper surface 115 of the wing 110. The lower portion 116 includes at least one lower reflector 124 positioned at the lower surface 117 of the wing 110.

[0215] A power source 130 is electrically connected to at least one emitter 120, at least one reflector 124, and at least one collector 122. The power source 130 is configured to apply a high voltage potential to each emitter 120 and each reflector 124. The power source 130 is also configured to apply an opposite high voltage potential or a neutral voltage potential to each collector 122. Each emitter 120 is configured to generate charged particles 105. Each reflector 124 is configured to repel charged particles 105, and each collector 122 is configured to attract charged particles 105.

[0216] Each front emitter 120 may be spaced apart from the front surface 113 of the wing 110 by a front gap 111. The lower portion 116 of the wing 110 includes at least one lower emitter 126, which is spaced apart from the lower surface 117 of the wing 110 by a lower gap 127. Each lower emitter 126 is also electrically connected to a power source 130. The power source 130 is configured to apply a high voltage potential to each lower emitter 126.

[0217] Fluid (air) flow causes charged particles 105 to move along the lower portion 116 of the wing 110. As the charged particles 105 pass at least one reflector 124 of the same polarity, the reflector 124 repels the wing 110 upwards and the charged particles 105 downwards, thereby creating a high voltage below the wing 110. Charged particles 105 moving along the top of the wing 110 (due to fluid flow and electrostatic forces) are attracted to at least one collecting electrode 122 at the top, while the at least one collecting electrode 122 and the wing 110 are attracted upwards towards the charged particles 105, thereby creating a low voltage above the wing 110. This provides the ability to control the upward or downward movement of the wing 110.

[0218] Electrostatic wing propulsion can be implemented in aircraft, especially airplanes or unmanned aerial vehicles, or in ships, especially submarines or hydrofoils.

[0219] Although specific embodiments of the invention have been described above, it will be understood that the invention may be practiced in ways other than those described. The above description is intended to be illustrative and not limiting.

[0220] As used herein, the term “a” or “an” is defined as one or more. As used herein, the term “multiple” is defined as two or more. As used herein, the term “another” is defined as at least a second or more. As used herein, the terms “comprising” and / or “having” are defined as including, i.e., open language, not excluding other elements or steps.

[0221] Any reference numerals in the claims should not be construed as limiting the scope of the claims or the invention. It will be appreciated that the particular embodiments claimed may not achieve all the stated purposes.

[0222] The mere fact that certain measures are stated in mutually different dependent claims does not indicate that a combination of these measures cannot be used advantageously.

[0223] The white lines between paragraphs in the text above indicate that the technical features presented in that paragraph can be considered as technical features discussed independently of previous or subsequent paragraphs.

Claims

1. An electrostatic thruster (10) for generating thrust by charging gas particles and / or liquid particles using a high voltage potential, wherein, The electrostatic thruster includes at least two thruster units (20), each thruster unit comprising: -At least one emitter (22). -At least one collection pole (24). The at least one collecting pole is spaced apart from the at least one launching pole by the thruster unit gap (28). The electrostatic thruster further includes a power source (30) electrically connected to at least one emitter and at least one collector of each thruster unit, wherein the power source is configured to apply a voltage between the at least one emitter and at least one collector of each thruster unit. The at least two thruster units are positioned in parallel to form a thruster unit array (40), wherein the thruster unit array further includes an intermediate electrode (42), wherein the intermediate electrode is located in an intermediate region (44) between the emitter and the collector of two adjacent thruster units in the thruster unit array, wherein the intermediate electrode is electrically connected to the collector of the thruster unit array via a current source (32) configured to generate a substantially constant current.

2. The electrostatic thruster according to claim 1, wherein, The essentially constant current is at least an order of magnitude lower than the collector current of the thruster unit array during operation.

3. The electrostatic thruster according to claim 2, wherein, The substantially constant current is less than 3% of the collector current of the thruster unit array during operation, preferably between 1% and 3% of the collector current.

4. The electrostatic thruster according to the preceding claim, wherein, The power source is configured to apply the voltage with the same polarity between the at least one emitter and the at least one collector of each thruster unit in the thruster unit array.

5. The electrostatic thruster according to any one of the preceding claims, wherein, The first distance (45) between the emitter and the intermediate electrode is smaller than the second distance (46) between the collector and the intermediate electrode.

6. The electrostatic thruster according to any one of the preceding claims, wherein, The intermediate electrode is offset relative to the corresponding straight line between the emitter and collector electrodes of the thruster unit array, preferably offset by half the distance between adjacent emitters of the thruster unit array.

7. The electrostatic thruster according to any one of the preceding claims, comprising at least two adjacent thruster unit arrays (40a, 40b) arranged in series, wherein, The distance (41a) between the collecting pole of the first thruster unit array (40a) and the emitting pole of the second thruster unit array (40b) is less than the distance (41b) between the collecting pole of the first thruster unit array and the collecting pole of the second thruster unit array.

8. The electrostatic thruster according to any one of the preceding claims, comprising at least two thruster units connected in series, wherein, The power supply is configured such that, for two adjacent thruster units connected in series, the voltage is applied with opposite polarities between at least one emitter and at least one collector in the first thruster unit (20a) of the two adjacent thruster units and between at least one emitter and at least one collector in the second thruster unit (20b) of the two adjacent thruster units connected in series.

9. The electrostatic propulsion device according to any one of the preceding claims, wherein, Each collecting pole has a blunt leading edge (25) that points toward the emitter pole of the corresponding thruster unit.

10. The electrostatic thruster according to any one of the preceding claims, wherein, Each collection pole has a blunt trailing edge (26).

11. The electrostatic thruster according to any one of the preceding claims, wherein, The collecting pole has a sharp trailing edge (27), wherein the sharp trailing edge is configured to generate charged particles (5), and wherein the sharp trailing edge of the collecting pole is the emitter of an adjacent thruster unit array.

12. The electrostatic thruster according to any one of the preceding claims, wherein, The positive or negative high voltage potential applied to the collector electrode is at least 30 kV, and more particularly at least 40 kV, so that the collector electrode repels the next thruster unit array.

13. The electrostatic thruster according to any one of the preceding claims, comprising at least two thruster unit arrays connected in series, wherein, The distance between the emitters of the first thruster unit array (40a) is greater than the distance between the emitters of each subsequent thruster unit array.

14. The electrostatic thruster according to any one of the preceding claims, wherein, At least one electric reflector (21) is positioned in front of the at least one emitter of the first thruster unit array, wherein each electric reflector has a conductive surface and is smooth, wherein each electric reflector is electrically connected to the power source, and wherein the power source is configured to: - Apply a high voltage potential to each emitter - Apply essentially the same high voltage potential to each nearby electric reflector.

15. The electrostatic thruster according to any one of the preceding claims, wherein, Each electric reflector has a relatively large surface area compared to the surface area of ​​each nearby emitter.

16. The electrostatic thruster according to any one of the preceding claims, wherein, The emitter includes a plurality of emitter electrodes (23) closely positioned together, wherein the plurality of emitter electrodes are configured to act as a single emitter, wherein, preferably, the plurality of emitter electrodes extend parallel to each other and the distance between the emitter electrodes is less than 1 mm.

17. The electrostatic thruster according to any one of the preceding claims, wherein, The power supply is configured to apply a pulsed voltage to each emitter so that the voltage alternates between two adjacent emitters.

18. The electrostatic thruster according to any one of the preceding claims, wherein, Each emitter and each collector is elongated, and wherein the emitter includes a longitudinal axis (12).

19. The electrostatic thruster according to the preceding claim, wherein, The size of the gap between the propeller units varies in the direction of the longitudinal axis of the emitter pole, which preferably has a serrated edge or a zigzag shape facing the collector pole.

20. The electrostatic thruster according to any one of the preceding claims, wherein, A non-conductive material blocking element (29) is positioned on the opposite side (14) of the emitter, wherein the blocking element follows the shape of the emitter.

21. The electrostatic thruster according to any one of the preceding claims, wherein, The first side (52) of the collecting pole includes a non-conductive material (50), which points to a second side (53) of the collecting pole of an adjacent thruster unit that does not contain the non-conductive material, wherein the second side is configured to attract charged particles, and wherein the first side is not configured to attract charged particles.

22. The electrostatic thruster according to any one of the preceding claims, wherein, The thruster unit includes a first collector electrode (24a) and a second collector electrode (24b) having the same voltage potential as the first collector electrode, wherein the first collector electrode and the second collector electrode are spaced apart by a collector electrode gap (16), and wherein the first collector electrode is positioned between the at least one emitter electrode and the second collector electrode.

23. The electrostatic thruster according to the preceding claim, wherein, The second collector is mechanically disconnected from the first collector.

24. The electrostatic thruster according to any one of claims 7 to 23, wherein, The power source is configured to apply a voltage difference between each emitter of the first thruster unit array and each collector of the second thruster unit array, and wherein the electrostatic thruster includes at least one electric reflector (60) configured to bend the electric field of adjacent thruster unit arrays, wherein the electric reflector is positioned between the thruster unit arrays, and wherein the distance between the second thruster unit array and the electric reflector is less than the distance between the first thruster unit array and the electric reflector.

25. The electrostatic thruster according to the preceding claim, wherein, The power source is configured to apply the same voltage and potential to the emitter and the corresponding electric reflector.

26. The electrostatic thruster according to any one of claims 24 to 25, wherein, Each electric reflector is insulated to reduce the generation of charged particles.

27. The electrostatic thruster according to any one of claims 24 to 26, wherein, The surface area of ​​an electric reflector is larger than the surface area of ​​an emitter.

28. An aircraft (1), particularly an airplane or an unmanned aircraft, comprising an electrostatic thruster according to any one of the preceding claims.

29. A spacecraft (4), particularly a small satellite, comprising an electrostatic thruster according to any one of the preceding claims.

30. An electrostatic wing thruster (100) for providing thrust (101) to a wing (110), the wing being configured to move (102) through a fluid (103), wherein, The electrostatic wing propulsion device includes: -The wing, wherein the wing comprises: The front portion (112) includes at least one front emitter (120). The upper part (114) includes at least one collecting pole (122) located on the upper surface (115) of the wing. The lower part (116) includes at least one lower reflector (124) positioned on the lower surface (117) of the wing. - A power supply (130) electrically connected to the at least one emitter, the at least one reflector, and the at least one collector, wherein the power supply is configured to: A high voltage potential is applied to each front emitter and each reflector. Apply an opposite high voltage potential or neutral voltage potential to each collector electrode. Each emitter is configured to generate charged particles (105), and Each reflector is configured to repel the charged particles, and each collector is configured to attract the charged particles.

31. The electrostatic wing propulsion device according to the preceding claim, wherein, Each front emitter is spaced apart from the front surface (113) of the wing by a front gap (111).

32. The electrostatic wing propulsion device according to any one of claims 30 to 31, wherein, The lower portion of the wing includes at least one lower emitter (126) spaced apart from the lower surface of the wing by a lower gap (127), wherein each lower emitter is electrically connected to the power source, and wherein the power source is configured to apply the high voltage potential to each lower emitter.

33. An aircraft (2), particularly an airplane or an unmanned aircraft, comprising an electrostatic wing propulsion system according to any one of claims 30 to 32.

34. A vessel (3), particularly a submarine or hydrofoil, comprising an electrostatic wing propulsion system according to any one of claims 30 to 32.

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