Ultra-low orbit space combined propulsion system

Abstract

The application provides an ultra-low orbit space combined propulsion system, which comprises a gas chamber for storing gas and providing the gas for a gas ionization unit; at least one gas inlet unit and at least one electrically-controlled solid propelling unit which are communicated with the gas chamber and provide the gas chamber with gas, wherein the gas inlet unit and the electrically-controlled solid propelling unit work simultaneously or at least one of the gas inlet unit and the electrically-controlled solid propelling unit works during propelling; the gas ionization unit is used for ionizing the gas output by the gas chamber to generate a plasma jet; and a tail nozzle is used for accelerating and spraying the plasma jet to generate thrust. The application can not only use the passive gas inlet unit to take the gas from the surrounding thin atmosphere as propellant, but also can generate gas by opening the active gas inlet unit to supplement the gas source when the flow is insufficient. Meanwhile, the gas chamber has the functions of storing gas and adjusting the gas flow in real time, so that the propelling system can have stable gas supply in the unstable working environment.

Description

Technical Field

[0001] This invention mainly relates to the field of propulsion system design technology, and in particular to an ultra-low orbit space combined propulsion system. Background Technology

[0002] Earth's ultra-low Earth orbit (ULE) offers significant advantages, including low launch costs and favorable conditions for Earth observation and communication. However, satellites operating at this altitude experience substantial aerodynamic drag, limiting their long-term operational duration. Air-breathing electric propulsion (EBP) technology utilizes specialized air intake devices to capture the thin atmosphere of orbital space. The thrust gained through ionization and acceleration of this atmosphere can compensate for the satellite's thrust during orbit, enabling long-term operation in ULE. While EBP has received considerable attention and rapid development in recent years, there is still significant interest in exploring this orbital altitude. However, the atmospheric density in this orbit varies drastically with seasons and solar activity, making it difficult to guarantee a continuous supply of sufficient gas molecules during orbit. Therefore, gas flow compensation and regulation solutions need to be considered.

[0003] Most existing air-breathing electric thrusters do not consider carrying their own gas source in addition to the air intake device, because high-pressure gas cylinders and their corresponding pipelines and valves would increase the complexity of the propulsion system. Therefore, it is necessary to design a simple and reliable gas replenishment scheme. In addition, air-breathing electric propulsion technology can only provide a small amount of thrust to compensate for the aerodynamic drag of the satellite in orbit, and does not have the ability to maneuver rapidly under specific mission conditions. Summary of the Invention

[0004] To address the aforementioned shortcomings of existing technologies, this invention proposes a combined ultra-low orbit space propulsion system. This invention not only utilizes a passive air intake unit to extract gas from the surrounding thin atmosphere as propellant, but also generates gas to supplement the gas source when the flow rate is insufficient by activating an active air intake unit. Simultaneously, the gas chamber has gas storage and real-time gas flow rate adjustment functions, ensuring a stable gas supply for the propulsion system even in unstable operating environments.

[0005] To achieve the above objectives, the technical solution adopted by the present invention is as follows:

[0006] This invention provides an ultra-low orbit space combined propulsion system, comprising:

[0007] The gas chamber is used to store gas and supply gas to the gas ionization unit.

[0008] At least one passive air intake unit and at least one active air intake unit are connected to and supply gas to the air chamber. The passive air intake unit is used to directly draw in gas from the outside, and the active air intake unit is used to generate gas itself. During propulsion, each passive air intake unit and the active air intake unit work simultaneously or at least one passive air intake unit and / or the active air intake unit work.

[0009] The gas ionization unit is used to ionize the gas output from the gas chamber to generate a plasma jet;

[0010] The tail nozzle accelerates the plasma jet and generates thrust.

[0011] Furthermore, when the ultra-low orbit space combined propulsion system is in operation, at least one passive air intake unit is in operation. If the external gas is scarce or / and the gas flow rate output from the air chamber is insufficient, at least one active air intake unit is activated to generate gas to replenish the air chamber.

[0012] Furthermore, the active air intake unit is an electronically controlled solid propulsion unit, which generates gas through combustion when energized.

[0013] Furthermore, the passive air intake unit includes an air intake duct, which has a parabolic cross-section tapering structure.

[0014] Furthermore, the front end of the air intake duct is provided with an air inlet, and a series of air inlets in the air inlet are arranged in a honeycomb pattern. The rear section of the air intake duct is a straight gas compression flow channel that extends all the way to the rear end of the air intake duct. The rear end of the air intake duct is sealed and connected to the air chamber through a connecting flange.

[0015] Furthermore, the inner wall of the air intake is coated with an aluminum-plated reflective material.

[0016] Furthermore, an electromagnetic valve is provided on the flow channel between the gas chamber and the gas ionization unit to adjust the gas flow rate output from the gas chamber in real time.

[0017] Furthermore, the electronically controlled solid propellant unit includes a housing and an electronically controlled solid propellant, an electronically controlled solid propellant drive mechanism, an electrode structure, a combustion chamber, and a contraction nozzle disposed within the housing. The electronically controlled solid propellant drive mechanism is used to drive the electronically controlled solid propellant to deliver the front end of the electronically controlled solid propellant to the position where the electrode structure is located for combustion. The other side of the electrode structure is the combustion chamber, and the outlet of the combustion chamber is connected to the contraction nozzle.

[0018] Furthermore, the electrode structure includes a first electrode and a second electrode. The first electrode has a series of parallel and equidistant positive electrodes, and the second electrode has the same number of negative electrodes as the positive electrodes, which are also parallel and equidistant from each other. The first electrode and the second electrode are disposed opposite each other on the same plane, and the positive electrodes of the first electrode and the negative electrodes of the second electrode are distributed alternately.

[0019] Furthermore, the gas ionization unit is a radio frequency ionization unit, including an ionization chamber shell and an ionization cavity disposed inside the ionization chamber shell, with an electromagnetic coil wound on the cavity wall along the length direction of the ionization cavity.

[0020] Furthermore, at least one active air intake unit is connected to the flow channel between the gas ionization unit and the tail nozzle.

[0021] Furthermore, the throat of the tail nozzle is provided with a permanent magnet, which generates a coaxial magnetic field to magnetically accelerate and confine the plasma jet.

[0022] Compared with the prior art, the technical effects of the present invention are as follows:

[0023] 1. Combining the advantages of passive and active air intake technologies, the ultra-low orbit space combined propulsion system can use the passive air intake unit to extract gas from the surrounding thin atmosphere as propellant. In cases of insufficient flow or other needs (such as gas storage in the gas chamber), the active air intake unit can be activated to generate gas to supplement the propellant.

[0024] 2. The passive intake unit is designed to draw in gas from the surrounding thin atmosphere without the need for complex mechanical structures such as compressors.

[0025] 3. The active air intake unit can use various existing devices that can generate gas through chemical reactions, such as electronically controlled solid propellants. The specific structure and type of electronically controlled solid propellants are not limited. Electronically controlled solid propellants have the advantages of being able to be ignited multiple times and being easy to store.

[0026] 4. Furthermore, this invention incorporates air-breathing radio frequency plasma electric propulsion technology. The passive air intake unit can draw in the rarefied atmospheric molecules in ultra-low orbit. When the flow rate is insufficient, the electrically controlled solid thruster can be energized to burn gas to replenish the gas chamber. In addition, the gas generated by the electrically controlled solid thruster can also be aerodynamically accelerated through the tail nozzle to generate high thrust. Utilizing the electrically controlled solid thruster as a gas source, its repeated operation can be achieved by adjusting the applied voltage, while also possessing the advantages of simple and reliable solid propulsion device structure.

[0027] 5. The gas chamber has gas storage function and real-time gas flow regulation function, which can ensure a stable gas supply for the propulsion system in unstable working environments.

[0028] 6. Furthermore, one embodiment of the electrically controlled solid propellant adopts an interlaced electrode structure with a fixed electrode spacing, which will not cause combustion runaway problems due to the change in length of the propellant during consumption, and has the advantage of stable operation.

[0029] 7. This invention also uses radio frequency ionization to ionize the gas, which has the advantages of low power, high ionization rate, and no electrode corrosion.

[0030] 8. The gas generated by the combustion of the electronically controlled solid propellant can be aerodynamically accelerated through the tail nozzle, enabling the propulsion system to operate at high thrust and broadening the application scenarios of the propulsion system. Attached Figure Description

[0031] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.

[0032] Figure 1 This is a schematic diagram of a structure according to an embodiment of the present invention;

[0033] Figure 2 This is a schematic diagram of the structure of a passive intake unit according to an embodiment of the present invention;

[0034] Figure 3 This is a schematic diagram of the structure of an active air intake unit in one embodiment of the present invention;

[0035] Figure 4 This is a schematic diagram of the electrode structure in one embodiment of the present invention;

[0036] Figure 5 This is a schematic diagram of the structure of a gas ionization unit in one embodiment of the present invention;

[0037] Explanation of the labels in the diagram:

[0038] 1. Passive intake unit; 101. Inlet; 102. Inlet duct; 103. Gas compression flow path;

[0039] 2. Active air intake unit; 201. Base plate; 202. Spring; 203. Housing; 204. Electronically controlled solid propellant; 205. Electrode interface; 206. First electrode; 207. Second electrode; 208. Combustion chamber; 209. Contracting nozzle; 210. Electrode insulating sleeve;

[0040] 3. Air chamber;

[0041] 4. Solenoid valve;

[0042] 5. Gas ionization unit; 501. Ionization chamber; 502. Ionization chamber outer shell; 503. Electromagnetic coil;

[0043] 6. Permanent magnet;

[0044] 7. Tail nozzle. Detailed Implementation

[0045] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the spirit of the disclosed content will be clearly explained below with reference to the accompanying drawings and detailed description. Any person skilled in the art, after understanding the embodiments of the present invention, can make changes and modifications based on the techniques taught in the present invention without departing from the spirit and scope of the present invention. The illustrative embodiments and descriptions of the present invention are used to explain the present invention, but are not intended to limit the present invention.

[0046] Reference Figure 1 In one embodiment, an ultra-low orbit space combined propulsion system is provided, comprising:

[0047] Gas chamber 3 is used to store gas and supply gas to the gas ionization unit;

[0048] At least one passive air intake unit 1 and at least one active air intake unit 2 are connected to and supply gas to the air chamber 3. The passive air intake unit 1 is used to directly draw in gas from the outside, and the active air intake unit 2 is used to generate gas itself. During propulsion, each passive air intake unit 1 and active air intake unit 2 works simultaneously or at least one passive air intake unit 1 and / or active air intake unit 2 works.

[0049] The gas ionization unit 5 is used to ionize the gas output from the gas chamber 3 to generate a plasma jet;

[0050] The tail nozzle 7 accelerates the plasma jet and generates thrust.

[0051] In the above embodiment, a passive air intake unit is used to extract gas molecules from the orbit. When there is excess gas flow, it can be stored in gas chamber 3. When the gas flow is insufficient, an active air intake unit can be activated to generate gas through a chemical reaction. In addition, the gas in the gas chamber can be aerodynamically accelerated through the nozzle to generate high thrust, enabling the satellite to have rapid maneuvering capabilities.

[0052] Passive intake units typically extract gas from the surrounding thin atmosphere through the design of the intake duct, without requiring complex mechanical structures such as compressors. Currently, there are many publicly available structural designs for passive intake units, and those skilled in the art can choose appropriately based on actual needs. Since the number of passive intake units is not limited in the above embodiments, those skilled in the art can design and adjust the number, installation position, installation angle, and distribution of passive intake units based on actual application requirements to achieve better gas extraction from the surrounding thin atmosphere. Similarly, there are many publicly available types and structural designs for active intake units that generate gas through chemical reactions, and those skilled in the art can choose appropriately based on actual needs; this invention does not impose specific limitations. Since the number of active intake units is not limited in the above embodiments, those skilled in the art can design and adjust the number, installation position, installation angle, and distribution of active intake units based on actual application requirements.

[0053] In one embodiment, based on the above-mentioned ultra-low orbit space combined propulsion system, an air intake scheme is proposed: at least one passive air intake unit 1 is in operation, and if the external gas is thin or / and the gas flow rate output from the air chamber is insufficient, at least one active air intake unit 2 is activated to generate gas to supplement the gas chamber 3.

[0054] When the ultra-low orbit space propulsion system in the above embodiments is operating, different positions, numbers, and types of air intake units can be rationally selected to operate in order to replenish the gas in the air chamber. For example, if only all passive air intake units operate, gas can be drawn from the surrounding thin atmosphere to replenish the air chamber. Alternatively, passive air intake units can be used simultaneously, while a certain number of active air intake units operate together to replenish the gas in the air chamber. The design and adjustment of the above air intake scheme are determined based on current actual needs.

[0055] like Figure 1 As shown, furthermore, a solenoid valve 4 is installed on the flow channel between the gas chamber 3 and the gas ionization unit 5 to adjust the gas flow rate output from the gas chamber 3 in real time. Excess gas collected or generated by the passive intake unit 1 and the active intake unit 2, which are connected to and supply gas to the gas chamber 3, can be stored in the gas chamber. The solenoid valve can adjust the flow rate in real time according to the required thrust to compensate for the constantly changing aerodynamic resistance. The specific structure of the gas chamber 3 is not limited. Figure 1 The shape shown is spherical. In practical applications, those skilled in the art can design it into different regular or irregular shapes according to their needs.

[0056] In one embodiment, a passive air intake unit is proposed based on the aforementioned ultra-low orbit space combined propulsion system. (Refer to...) Figure 2The passive air intake unit 1 includes an air intake duct 102, which has a parabolic, tapering cross-section. The inner wall of the air intake duct 102 is coated with an aluminum-plated reflective material. An air inlet 101 is located at the front end of the air intake duct 102, and a series of air inlets in the air inlet 101 are arranged in a honeycomb pattern. The rear section of the air intake duct 102 is a gas compression channel 103. The cross-section of the gas compression channel 103 at any point is smaller than the cross-section of the upstream air intake duct 102. The gas compression channel 103 is used to compress and accelerate the gas from the air intake duct 102. The cross-section design of the gas compression channel 103 is not limited; it can be a straight gas compression channel with a uniform cross-section, or a gas compression channel with a cross-section that gradually decreases along the gas flow direction. The gas compression channel 103 extends to the rear end of the air intake duct, which is sealed to the gas chamber 3 via a connecting flange. The design of the air intake in this embodiment can balance good gas collection efficiency and compression ratio.

[0057] In one embodiment, based on the aforementioned ultra-low orbit space combined propulsion system, the active air intake unit 2 is proposed to employ an electrically controlled solid propulsion unit. This unit generates gas through combustion when energized. When the flow rate is insufficient, the electrically controlled solid propulsion unit can be energized to replenish the gas chamber. Using the electrically controlled solid propulsion unit as a gas source allows for repeated operation by adjusting the applied voltage, while also possessing the advantages of a simple and reliable solid propulsion device structure.

[0058] In one embodiment, based on the aforementioned ultra-low orbit space combined propulsion system, an electrically controlled solid propulsion unit is proposed. (Refer to...) Figure 3The electrically controlled solid propellant unit includes a housing and, within the housing, an electrically controlled solid propellant 204, an electrically controlled solid propellant drive mechanism, an electrode structure, a combustion chamber 208, and a contraction nozzle 209. For ease of assembly and maintenance, the housing includes a shell 203 and a base plate 201. The front end of the shell 203 is provided with the contraction nozzle 209, and the bottom of the shell 203 is sealed by the base plate 201. The electrically controlled solid propellant drive mechanism drives the electrically controlled solid propellant 204, delivering its front end to the location of the electrode structure for combustion. In this embodiment, the electrically controlled solid propellant drive mechanism is a spring 202. One end of the spring 202 is connected to the base plate 201 of the housing, and the other end of the spring 202 is connected to (or may abut against) the rear end of the electrically controlled solid propellant 204. Initially, spring 202 is compressed. As the electrically controlled solid propellant 204 burns continuously, spring 202 deforms, continuously propelling the front end of the electrically controlled solid propellant 204 to the electrode structure to supply the propellant. The other side of the electrode structure is a combustion chamber 208, the outlet of which is connected to a converging nozzle 209. (Refer to...) Figure 4 One embodiment presents a novel electrode structure. The electrode structure includes a first electrode 206 and a second electrode 207. The first electrode 206 has a series of parallel, equidistantly arranged positive electrodes, and the second electrode 207 has the same number of negative electrodes as the positive electrodes, also arranged parallel and equidistantly. The first electrode 206 and the second electrode 207 are disposed opposite each other on the same plane, with the positive electrodes of the first electrode 206 and the negative electrodes of the second electrode 207 interleaved. An electrode interface 205 for mounting the electrode structure is provided at a corresponding position in the housing 203. An electrode insulating sleeve 210 is fitted on the outside of the electrode structure, meaning the first electrode 206 and the second electrode 207 are installed inside the electrode insulating sleeve 210. The electrode structure is mounted at the electrode interface 205 in the housing 203 via a snap-fit ​​structure on the electrode insulating sleeve 210. Using the fixed electrode structure provided in the above embodiment, the positive and negative electrodes are alternately distributed on the front end face of the electrically controlled solid propellant 204. A spring is used to supply the electrically controlled solid propellant. Since the electrode spacing is fixed, the device has the advantage of stable and reliable operation.

[0059] Reference Figure 5In one embodiment, based on the aforementioned ultra-low orbit space propulsion system, the gas ionization unit 5 is proposed to be a radio frequency ionization unit, including an ionization chamber shell 502 and an ionization cavity 501 disposed within the ionization chamber shell 502. An electromagnetic coil 503 is wound around the cavity wall along the length direction of the ionization cavity 501. Using radio frequency ionization offers the advantage of high ionization efficiency. Simultaneously, the gas in the ionization cavity 501 undergoes radio frequency ionization through the electromagnetic coil 503, thus avoiding corrosion problems caused by direct contact between the gas and the electrode structure, ensuring long-term operation of the device.

[0060] Reference Figure 1 Furthermore, in the illustrated embodiment, at least one active air intake unit is connected to the flow channel between the gas ionization unit 5 and the tail nozzle 7. Figure 1 As can be seen, two active air intake units are connected in the flow channel between the gas ionization unit 5 and the tail nozzle 7. The selection and structural design of the active air intake units can adopt the active air intake units provided in any of the above embodiments, and will not be elaborated further here.

[0061] Reference Figure 1 Furthermore, in the illustrated embodiment, a permanent magnet 6 is provided at the throat of the tail nozzle 7, and the coaxial magnetic field generated by the magnet accelerates and confines the plasma jet magnetically. Furthermore, the permanent magnet 6 is a ring-shaped permanent magnet, fitted onto the throat of the tail nozzle 7, and the coaxial magnetic field it generates can limit the divergence angle of the plasma jet.

[0062] In the above embodiments, when the gas flow rate taken in by the passive air intake unit is insufficient, the electrically controlled solid thruster can be energized to burn gas to supplement the gas chamber.

[0063] The ultra-low orbit space propulsion system has multiple operating modes, including low thrust and high specific impulse, and high thrust and low specific impulse (multiple operating modes can be obtained by activating different numbers and positions of electrically controlled solid rocket motors). Two typical operating modes are described below:

[0064] The first mode: only the gas chamber 3 provides jet gas to the tail nozzle 7. That is, the gas chamber supplies a small flow of gas under the regulation of the solenoid valve 4. After being ionized and accelerated by the gas ionization unit 5, it is ejected from the tail nozzle 7. This mode can achieve a low thrust and high specific impulse working mode. This mode is suitable for satellite on-orbit thrust compensation missions.

[0065] In the second mode, the gas chamber 3 provides jet gas to the tail nozzle 7, while the electrically controlled solid thruster (i.e., the electrically controlled solid thruster connected directly to the tail nozzle 7) is energized and combusted to produce gas, which is then supplied to the tail nozzle 7. The gas entering the tail nozzle 7 is accelerated by the tail nozzle 7 and then ejected, which can achieve a high thrust and low specific impulse working mode. This mode is suitable for the rapid maneuvering mission of the satellite.

[0066] Matters not covered in this invention are common knowledge.

[0067] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0068] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the invention patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this patent application should be determined by the appended claims.

Claims

1. A combined ultra-low orbit space propulsion system, characterized in that, include: The gas chamber is used to store gas and supply gas to the gas ionization unit. At least one passive air intake unit and at least one active air intake unit are connected to and supply gas to the air chamber. The passive air intake unit is used to directly draw in gas from the outside, and the active air intake unit is used to generate gas itself. During propulsion, each passive air intake unit and the active air intake unit work simultaneously or at least one passive air intake unit and / or at least one active air intake unit can be selected to work. The gas ionization unit is used to ionize the gas output from the gas chamber to generate a plasma jet; The tail nozzle accelerates and ejects the plasma jet to generate thrust. An electromagnetic valve is installed on the flow channel between the gas chamber and the gas ionization unit to adjust the gas flow rate output from the gas chamber in real time. At least one active air intake unit is connected to the flow channel between the gas ionization unit and the tail nozzle. The throat of the tail nozzle is equipped with a permanent magnet, which generates a coaxial magnetic field to magnetically accelerate and confine the plasma jet, thereby limiting the divergence angle of the plasma jet. The ultra-low orbit space combined propulsion system has multiple operating modes, including low thrust and high specific impulse and high thrust and low specific impulse. In the low thrust and high specific impulse operating mode, only the gas chamber provides the jet gas to the tail nozzle. The gas chamber is supplied with a small flow of gas under the regulation of the solenoid valve. After being ionized and accelerated by the gas ionization unit, the gas is ejected from the tail nozzle for on-orbit thrust compensation mission. In the high-thrust, low-specific-impulse operating mode, the air chamber provides jet gas to the tail nozzle, while the active air intake unit, which is directly connected to the tail nozzle, also provides gas to the tail nozzle. The gas entering the tail nozzle is accelerated and then ejected for rapid maneuvering missions.

2. The ultra-low orbit space combined propulsion system according to claim 1, characterized in that, When the ultra-low orbit space combined propulsion system is in operation, at least one passive air intake unit is working. If the outside gas is thin or / and the gas flow rate output from the air chamber is insufficient, at least one active air intake unit is activated to generate gas to replenish the air chamber.

3. The ultra-low orbit space combined propulsion system according to claim 1 or 2, characterized in that, The active air intake unit is an electronically controlled solid propulsion unit, which generates gas through combustion when energized.

4. The ultra-low orbit space combined propulsion system according to claim 3, characterized in that, The passive air intake unit includes an air intake duct, which has a parabolic cross-section with a tapering shape.

5. The ultra-low orbit space combined propulsion system according to claim 4, characterized in that, The front end of the air intake duct is provided with an air inlet, and a series of air inlets in the air inlet are arranged in a honeycomb pattern. The rear section of the air intake duct is a straight gas compression channel that extends all the way to the rear end of the air intake duct. The rear end of the air intake duct is sealed and connected to the air chamber through a connecting flange.

6. The ultra-low orbit space combined propulsion system according to claim 4 or 5, characterized in that, The inner wall of the air intake is coated with aluminum-plated reflective material.

7. The ultra-low orbit space combined propulsion system according to claim 3, characterized in that, The electronically controlled solid propellant unit includes a housing and an electronically controlled solid propellant, an electronically controlled solid propellant drive mechanism, an electrode structure, a combustion chamber, and a contraction nozzle disposed within the housing. The electronically controlled solid propellant drive mechanism is used to drive the electronically controlled solid propellant to deliver the front end of the electronically controlled solid propellant to the position where the electrode structure is located for combustion. The other side of the electrode structure is the combustion chamber, and the outlet of the combustion chamber is connected to the contraction nozzle.

8. The ultra-low orbit space combined propulsion system according to claim 7, characterized in that, The electrode structure includes a first electrode and a second electrode. The first electrode has a series of parallel and equidistant positive electrodes, and the second electrode has the same number of negative electrodes as the positive electrodes, which are also parallel and equidistant from each other. The first electrode and the second electrode are disposed opposite each other on the same plane, and the positive electrodes of the first electrode and the negative electrodes of the second electrode are distributed alternately.

9. The ultra-low orbit space combined propulsion system according to claim 1, 2, 4, 5, 7, or 8, characterized in that, The gas ionization unit is a radio frequency ionization unit, including an ionization chamber shell and an ionization cavity disposed inside the ionization chamber shell, with an electromagnetic coil wound on the cavity wall along the length direction of the ionization cavity.

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