A microwave detonation dual-mode space thruster

Abstract

The present invention discloses a microwave detonation dual-mode space thruster, which includes a propellant supply system, a large-thrust propulsion module and a micro-thrust propulsion module coaxially arranged from the inside to the outside in sequence; the large-thrust propulsion module includes an injector, a plasma ignition combustor, a detonation chamber, a tail nozzle, etc. The micro-thrust propulsion module includes a microwave supply system, magnetic poles, a gas collection chamber, a discharge chamber and a grid; the microwave supply system includes a microwave connector and an antenna; the antenna is a cylindrical antenna, and a cyclotron cavity is formed between the antenna and the magnetic poles; the outer electrons in the working medium molecules located in the cyclotron cavity perform cyclotron motion in the cyclotron cavity, and resonance occurs when the cyclotron angular frequency is equal to the microwave frequency. The present invention combines microwave discharge technology, plasma combustion assistance technology and pulse detonation combustion technology, and realizes efficient and convenient switching of working modes through circuit regulation, enabling the thruster to meet the stringent requirements of large thrust, high specific impulse, long life, etc., and can be applied to diverse space missions.

Description

Technical Field

[0001] The present invention relates to the technical field of spacecraft space propulsion, and in particular to a microwave detonation dual-mode space thruster. Background Technique

[0002] With the rapid development of China's space industry, diverse space missions pose higher and more complex requirements for the propulsion system. Currently, space thrusters are mainly divided into two categories: chemical high-thrust propulsion and ionization high-specific-impulse propulsion, which are difficult to meet the diverse space mission requirements such as high thrust and high specific impulse. Microwave ion electric propulsion technology uses microwave energy to break down gas to generate plasma, and then an electrostatic field accelerates ions to generate thrust. It has the characteristics of a wide thrust range, strong controllability, high specific impulse, and can use various gases as working media, and has significant advantages in service life and precise thrust control. However, limited by its small thrust, it is currently mainly applied to tasks such as spacecraft orbit and attitude maintenance and deep space exploration, and does not meet the requirements of rapid spacecraft maneuvering. In contrast, pulse detonation chemical propulsion technology is a new type of propulsion method that uses high-temperature and high-pressure gases generated by pulsed detonation waves to provide thrust. Its prominent features are simple structure, low cost, high thrust-to-weight ratio, and high thermal cycle efficiency. For spacecraft with large mass and the need for rapid maneuvering, pulse detonation engines are an ideal choice. However, limited by the chemical energy of the propellant and the wall temperature, the specific impulse of pulse detonation engines is relatively low, and the requirement of continuous variable thrust cannot be achieved. Plasma ignition and combustion assistance is a new type of ignition and combustion assistance technology that uses the high-temperature effect, chemical effect, and aerodynamic effect of plasma to improve the ignition ability and combustion efficiency, which can enhance ignition, increase the flame propagation speed and stability ability, broaden the extinction limit, and thus achieve efficient combustion under higher pressure, lower flame temperature, and leaner fuel conditions.

[0003] The present invention combines microwave discharge technology, plasma combustion assistance technology, and pulse detonation combustion technology, and realizes efficient and convenient switching of working modes through circuit regulation, enabling the thruster to meet the harsh requirements of high thrust, high specific impulse, and long service life, and being applicable to diverse space missions. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to provide a microwave detonation dual-mode space thruster in view of the deficiencies of the above-mentioned prior art. The microwave detonation dual-mode space thruster combines microwave discharge technology, plasma combustion assistance technology, and pulse detonation combustion technology, effectively solves the problem of long detonation initiation distance of pulse detonation, thereby reducing the size of the thruster and improving the ignition and detonation performance. At the same time, through circuit regulation, efficient and convenient switching of working modes is realized, enabling the thruster to meet the harsh requirements of high thrust, high specific impulse, and long service life, and being applicable to diverse space missions.

[0005] To solve the above technical problems, the technical solution adopted by the present invention is:

[0006] A microwave detonation dual-mode space thruster, comprising a propellant supply system, a large-thrust propulsion module and a micro-thrust propulsion module coaxially arranged from inside to outside in sequence.

[0007] The propellant supply system includes a propellant tank, a detonation branch pipeline and an ionization branch pipeline respectively connected to the propellant tank; wherein, the detonation branch pipeline can supply fuel and oxidant to the large-thrust propulsion module; the ionization branch pipeline can supply electro-propellant to the micro-thrust propulsion module.

[0008] The micro-thrust propulsion module includes a microwave supply system, a magnetic pole, a gas collection chamber, a discharge chamber and a grid.

[0009] The gas collection chamber, the discharge chamber and the grid are coaxially arranged in sequence from front to back.

[0010] The magnetic pole is a magnetic ring, coaxially arranged at the head of the discharge chamber adjacent to the gas collection chamber.

[0011] The microwave supply system includes a microwave connector and an antenna.

[0012] The antenna is a cylindrical antenna, coaxially inserted on the inner wall of the discharge chamber located inside the magnetic pole; a cyclotron cavity is formed between the antenna and the magnetic pole; the cyclotron cavity is respectively communicated with the gas collection chamber and the discharge chamber.

[0013] The microwave connector is used to feed microwave into the antenna.

[0014] After the electro-propellant provided by the ionization branch pipeline passes through the gas collection chamber, it enters the cyclotron cavity; at this time, the outer electrons in the electro-propellant molecules will perform cyclotron motion in the cyclotron cavity, and resonance occurs when the cyclotron angular frequency ω e is equal to the microwave frequency f; wherein, the cyclotron angular frequency ω e has a matching relationship with the magnetic field intensity B of the magnetic pole.

[0015] The cyclotron angular frequency ω e The calculation formula of is:

[0016]

[0017] In the formula, e and m e are respectively the charge and mass of the outer electrons in the electro-propellant molecules.

[0018] The magnetic pole is an electromagnet, and by changing the excitation current of the magnetic pole, the adjustment of the magnetic field intensity B is realized, so as to match with the microwave frequency f; when the microwave frequency f is 2.45 GHz, the magnetic field intensity B is adjusted to 0.875 T; when the microwave frequency f is 4.2 GHz, the magnetic field intensity B is adjusted to 1.5 T.

[0019] The outer shell of the high-thrust propulsion module serves as the inner shell of the discharge chamber in the micro-thrust propulsion module; the material of the outer shell of the high-thrust propulsion module is a high-temperature resistant insulating material.

[0020] The high-thrust propulsion module includes an injector, a plasma ignition and combustion assistor, a detonation chamber, and a tail nozzle; among them, the injector, the detonation chamber, and the tail nozzle are arranged coaxially in sequence from front to back; the plasma ignition and combustion assistor is arranged on the front side wall of the detonation chamber.

[0021] A DDT enhancement device is arranged in the detonation chamber.

[0022] A check valve is arranged on the detonation branch pipeline; when the pressure in the detonation chamber is lower than the injection pressure, the check valve opens, otherwise, the check valve closes.

[0023] The axial length of the antenna is greater than the axial length of the magnetic pole, and the antenna and the magnetic pole are flush with the end face of the discharge chamber.

[0024] When the spacecraft needs to perform a rapid maneuvering mission for space orbit transfer, the high-thrust propulsion module works independently to achieve high thrust; when the spacecraft needs to perform space missions such as orbit maintenance and attitude adjustment, the micro-thrust propulsion module works independently to achieve high specific impulse.

[0025] When the micro-thrust propulsion module works independently, by applying a periodically changing voltage to the grid, ions and electrons are alternately extracted to achieve self-neutralization; among them, the application frequency of the grid voltage is greater than the minimum extraction frequency of the grid.

[0026] The present invention has the following beneficial effects:

[0027] 1. The present invention makes full use of the advantages of microwave ionization technology, plasma combustion assist technology, and detonation combustion technology, and designs a microwave detonation dual-mode space thruster. This thruster can work in two different modes of high thrust and micro thrust, and can combine the advantages of high specific impulse of microwave ion electric propulsion technology and high thrust of pulse detonation chemical propulsion technology, so that its performance coverage range is wider and the application of space missions is more flexible.

[0028] 2. In the present invention, the micro-thrust propulsion module and the high-thrust propulsion module can share the propellant, and the selection of the propellant includes but is not limited to fuels and oxidants such as methane, kerosene, ammonia, oxygen, nitrous oxide, hydrogen peroxide, etc., reducing the mass and volume ratio of the storage tank and the corresponding supporting pipelines, and saving space resources such as mass and volume for the spacecraft.

[0029] 3. The present invention adopts a modular design, and the micro-thrust propulsion module and the high-thrust propulsion module can work independently. At the same time, the high temperature on the wall surface during the working mode switching can provide favorable conditions for the start of another working mode. The coaxial nested space structure of this thruster is convenient for replacing other types of propulsion units for re-combination as needed when applied to different scenarios in the future.

[0030] 4. The present invention optimizes the structure design of the micro-thrust propulsion module, proposes a coaxial annular discharge chamber configuration, and adopts a cylindrical antenna and a circular grid system. Compared with the cylindrical configuration design, it has a larger coupling area ratio and a higher coupling degree of microwaves and electromagnetic fields, can effectively enhance the ionization and acceleration extraction process of propellant molecules, and realizes performance optimizations such as fast startup, high specific impulse, and high adjustment accuracy.

[0031] 5. The present invention realizes the self-neutralization effect by periodically changing the grid voltage to alternately extract ions and electrons, without an external neutralizer, simplifies the thruster structure, can avoid the restriction of particle contamination of the hot cathode material of the traditional neutralizer, reduces the failure rate, extends the thruster life, and reduces the launch cost.

[0032] 6. For the large-thrust propulsion module, the present invention indirectly initiates detonation by means of deflagration-to-detonation transition (DDT) and sets a DDT enhancement device to accelerate the formation of detonation waves; a check valve is used to realize the adaptive control of the pulse detonation cycle process, without additional control devices, reducing the complexity of the system.

[0033] 7. The present invention applies plasma-assisted combustion technology to pulse detonation chemical propulsion, adopts a plasma ignition and combustion assistor, which can be a DBD plasma ignition and combustion assistor, an arc plasma ignition and combustion assistor, a microwave plasma ignition and combustion assistor, etc. Preferably, a microwave plasma ignition and combustion assistor is adopted, which can share the microwave excitation source and power supply. While the structure is simplified, it promotes combustion detonation and realizes the mutual coupling of ignition and combustion assistance. At the same time, according to actual application needs, the present invention proposes to set 2n (n = 1, 2,...) pairs to achieve uniform ignition and generate a large number of active particles to promote stable combustion. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 Shows a three-dimensional perspective view of a microwave detonation dual-mode space thruster of the present invention.

[0035] Figure 2 Shows a three-dimensional sectional view of a microwave detonation dual-mode space thruster of the present invention.

[0036] Figure 3 Shows an explosion schematic diagram of a microwave detonation dual-mode space thruster of the present invention.

[0037] Figure 4 Shows a three-dimensional sectional view of the large-thrust propulsion module in the present invention.

[0038] Figure 5 Shows a three-dimensional sectional view of the micro-thrust propulsion module in the present invention.

[0039] Figure 6Shows the adaptive working cycle flowchart of the high-thrust propulsion module in the present invention.

[0040] Among them are:

[0041] 10. Propellant supply system;

[0042] 11. Propellant tank; 12. Ionization branch pipeline; 13. Detonation branch pipeline; 14. Check valve;

[0043] 20. Micro-thrust propulsion module;

[0044] 21. Microwave supply system; 211. Microwave connector; 212. Antenna;

[0045] 22. Magnetic pole; 23. Gas collection chamber; 231. Distribution hole; 24. Discharge chamber; 25. Grid; 26. Shielding shell; 27. Discharge chamber shell;

[0046] 30. High-thrust propulsion module;

[0047] 31. Injector; 32. Plasma ignition and combustion assistor; 33. Detonation chamber; 34. Tail nozzle; 35. DDT enhancement device. Specific embodiments

[0048] The present invention will be further described in detail below in conjunction with the accompanying drawings and specific preferred embodiments.

[0049] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by terms such as "left side", "right side", "upper part", "lower part", etc. is based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. "First", "second", etc. do not represent the importance of components, so they cannot be understood as limitations to the present invention. The specific dimensions adopted in this embodiment are only for illustrating the technical solution and do not limit the protection scope of the present invention.

[0050] As Figure 1 、 Figure 2 and Figure 3 shown, a microwave detonation dual-mode space thruster includes a propellant supply system 10, and a high-thrust propulsion module 30 and a micro-thrust propulsion module 20 arranged coaxially from inside to outside in sequence.

[0051] As Figure 2 shown, the propellant supply system includes a propellant tank 11, and a detonation branch pipeline 13 and an ionization branch pipeline 12 respectively connected to the propellant tank.

[0052] The above-mentioned propellant tank is shared by the large-thrust propulsion module 30 and the micro-thrust propulsion module 20, which can make full use of the volume space resources of the spacecraft while effectively saving the mass resources. The propellant tank preferably includes a fuel tank and an oxidizer tank. Among them, the fuel tank preferably stores methane or kerosene, etc.; the oxidizer tank preferably stores oxygen, etc.

[0053] The above-mentioned detonation branch pipeline can supply fuel and oxidizer to the large-thrust propulsion module, and a check valve 14 is preferably arranged on the detonation branch pipeline.

[0054] The above-mentioned ionization branch pipeline can supply electropropellant to the micro-thrust propulsion module. The electropropellant is preferably one or a combination of fuel and oxidizer. Further, a cracking and gasification device is preferably arranged on the ionization branch pipeline.

[0055] As Figure 2 、 Figure 3 and Figure 5 shown, the micro-thrust propulsion module adopts a coaxial annular configuration and preferably includes a microwave supply system 21, a magnetic pole 22, a gas collection chamber 23, a discharge chamber 24, a grid 25, a shielding shell 26 and a discharge chamber shell 27.

[0056] The gas collection chamber, the discharge chamber and the grid are coaxially arranged in sequence from front to back.

[0057] The magnetic pole is a magnetic ring and is coaxially arranged at the head of the discharge chamber adjacent to the gas collection chamber.

[0058] The microwave supply system includes a microwave connector and an antenna.

[0059] The antenna is a cylindrical antenna and is coaxially inserted into the inner wall of the discharge chamber located inside the magnetic pole; a gyration cavity is formed between the antenna and the magnetic pole. Further, the length range of the antenna extending into the discharge chamber is preferably 1 / 2 - 2 / 3 of the discharge chamber, slightly greater than the length of the magnetic pole. In this embodiment, the axial length of the antenna is greater than the axial length of the magnetic pole, and the antenna and the magnetic pole are flush at the end face of the discharge chamber.

[0060] As Figure 5 shown, a circle of evenly distributed distribution holes 231 is opened at the end face of the gas collection chamber, and the gas collection chamber is connected to the gyration cavity through the distribution holes. At the same time, the gyration cavity is directly connected to the discharge chamber. The electropropellant enters the gas collection chamber and the residence time is prolonged due to the resistance effect, and the gas is evenly distributed and introduced into the discharge chamber through the distribution holes.

[0061] The microwave connector is used to feed microwave into the antenna.

[0062] The magnetic poles are preferably electromagnets. By changing the excitation current of the magnetic poles, the adjustment of the magnetic field intensity B is achieved, so as to match the microwave frequency f. When the microwave frequency f is 2.45 GHz, the magnetic field intensity B is adjusted to 0.875 T. When the microwave frequency f is 4.2 GHz, the magnetic field intensity B is adjusted to 1.5 T.

[0063] Preferably, a shielding shell 26 is arranged on the outer periphery of the above-mentioned discharge chamber shell 27.

[0064] As Figure 4 shown, the large-thrust propulsion module adopts a cylindrical configuration and mainly includes an injector 31, a plasma ignition and combustion assistor 32, a detonation chamber 33, and a tail nozzle 34.

[0065] The injector, the detonation chamber, and the tail nozzle are coaxially arranged in sequence from front to back. Among them, the injector preferably adopts a coaxial injector, which can promote the mixing and detonation process of fuel and oxidant.

[0066] The above-mentioned igniter is arranged on the front side wall of the detonation chamber. The igniter adopts a plasma ignition and combustion assistor, which can adopt a DBD plasma ignition and combustion assist device, an arc plasma ignition and combustion assist device, a microwave plasma ignition and combustion assist device, etc. The present invention preferably adopts a microwave plasma ignition and combustion assist device, which shares the microwave excitation source and power supply with the micro-thrust propulsion module to realize the simplification of the structure reuse. According to the actual application needs, the plasma ignition and combustion assistors are arranged in pairs of 2n (n = 1, 2,...) to achieve uniform ignition and generate a large number of active particles to promote stable combustion.

[0067] The detonation is initiated by an indirect detonation method of deflagration-to-detonation transition (DDT). A DDT enhancement device 35 is arranged in the detonation tube to accelerate the transition from deflagration to detonation, and Shchelkin spiral wires, semi-circular protrusions, plug plates, orifice plates, etc. can be used.

[0068] The further setting of the check valve can be used to realize the adaptive control of the detonation cycle process as Figure 6 shown. Its opening and closing are completely adaptively controlled by the working process of the detonation cycle, and no special control equipment similar to a solenoid valve is required. When the pressure in the detonation chamber is lower than the injection pressure, the check valve opens; otherwise, the check valve closes.

[0069] The above-mentioned tail nozzle preferably adopts a convergent-divergent nozzle, which can maintain sufficient pressure in the detonation chamber to adapt to the high-vacuum environmental conditions.

[0070] Combined with the actual application of the invention, the temperature of the propulsion module will rise sharply during operation, and it is necessary to optimize the wall material. For the outer shell of the micro-thrust propulsion module, high-temperature-resistant materials such as titanium alloy can be selected. For the outer shell of the large-thrust propulsion module, insulating materials with good high-temperature resistance such as silicon-based ceramics and carbon-carbon composite materials are selected. They are suitable for the high-temperature environment of chemical large-thrust combustion and can also meet the conditions for the generation and maintenance of plasma in the outer-ring ionization micro-thrust propulsion module. When one of the modules finishes working, the wall temperature is relatively high, which can promote the ionization or combustion process of the working medium in the other module, creating favorable conditions for the switching and startup of the thruster working mode.

[0071] The present invention enables the large-thrust propulsion module and the micro-thrust propulsion module to work independently.

[0072] I. Large-thrust propulsion

[0073] When the spacecraft needs to perform rapid maneuvering tasks such as space orbit transfer, the large-thrust propulsion module works independently to achieve large thrust. The specific working cycle process is as follows:

[0074] (1) Propellant filling: Open the fuel and oxidizer switches and activate the one-way valve, and fill the detonation tube in a certain proportion.

[0075] (2) Ignition: Start the plasma ignition booster and ignite at a given frequency, while promoting auxiliary combustion.

[0076] (3) Detonation wave initiation, formation and propagation: After the gas is ignited, it burns in a deflagration form, first generating a deflagration wave in the detonation tube. After DDT, the deflagration wave becomes a high-speed and stable detonation wave, followed by an expansion wave. When the pressure in the detonation chamber is higher than the injection pressure, the one-way valve automatically closes.

[0077] (4) Detonation wave transmission: The detonation wave propagates towards the outlet end, and finally expands and discharges through the nozzle, generating a large thrust at the same time.

[0078] (5) Expansion wave entry: An expansion wave is generated at the nozzle entrance and enters the detonation chamber, exhausting the burned gas, and the gas parameters in the detonation chamber gradually reach equilibrium.

[0079] (6) Cycle repetition: When the pressure in the detonation chamber is lower than the injection pressure, the one-way valve reopens, and the above working cycle process is repeated.

[0080] II. Micro-thrust propulsion

[0081] When the spacecraft needs to perform space tasks such as orbit maintenance and attitude adjustment, the micro-thrust propulsion module works independently to achieve high specific impulse. The specific working cycle process is as follows:

[0082] (1) Magnetic field and microwave feeding: Turn on the magnetic poles and the microwave source to generate a magnetic field, and feed the microwave into the discharge chamber through the antenna.

[0083] (2) Propellant feeding: Turn on the propellant storage and supply system to feed the propellant.

[0084] (3) Electron cyclotron resonance heating: Under the combined action of the microwave and the magnet, the outer electrons of the propellant molecules in the discharge chamber perform cyclotron motion, and the cyclotron angular frequency is:

[0085]

[0086] where e and m e are the charge and mass of the electron respectively, and B is the magnetic field strength.

[0087] When ω e is equal to the externally applied microwave frequency, the electrons resonate with the microwave, and the microwave energy is continuously coupled into the electrons, increasing the electron temperature and raising the electron energy level, turning into high-energy electrons, and finally flying out of the atomic nucleus binding to achieve ionization.

[0088] (4) Plasma generation: The generated high-energy electrons collide with the propellant molecules fed into the discharge chamber, causing them to ionize and generate plasma.

[0089] (5) Plasma accelerated ejection: The generated plasma is accelerated and ejected through the grid system to generate thrust. At this time, by applying a periodically varying voltage to the grid, ions and electrons are alternately extracted to achieve self-neutralization; among them, the application frequency of the grid voltage is greater than the minimum extraction frequency of the grid.

[0090] The minimum extraction frequency f min of the above grid is preferably calculated as:

[0091]

[0092] where:

[0093]

[0094] In the formula, L eff is the effective distance for the ions to move between the grids; L g is the grid spacing, t s is the thickness of the screen grid, r s is the radius of the grid hole; U s is the grid voltage, M is the mass of the ion, and e is the electron charge.

[0095] When a double-gate structure is adopted, the double-gate spacing is 0.5 mm, the screen-grid thickness is 0.4 mm, the screen-grid hole radius is 1.0 mm, the minimum extraction frequency corresponding to a gate voltage of 1200 V is 15.6073 MHz. As long as a gate voltage greater than the minimum extraction frequency is applied, the self-neutralization extraction frequency can be satisfied.

[0096] When the gate voltage is greater than zero, ions are extracted by the gate; when the gate voltage is equal to or less than zero, electrons are extracted by the gate. The total amount of ions and electrons extracted by the gate is on average equal in each cycle, and the beam current is quasi-neutral, thus enabling the effect of self-neutralization. There is no need for an external neutralizer, which can reduce the system complexity and lower the failure rate.

[0097] The present invention combines microwave discharge technology, plasma-assisted combustion technology, and pulse detonation combustion technology, integrates the technical advantages, effectively solves the problem of long pulse detonation ignition distance, improves the ignition ability and combustion efficiency, and at the same time realizes the efficient and convenient switching of working modes through circuit regulation. The microwave ion electric propulsion technology has a wide thrust range, strong controllability, and high specific impulse, and can use a variety of gases as working media, having significant advantages in service life and precise thrust control; the pulse detonation chemical propulsion technology has a simple structure, low cost, high thrust-to-weight ratio, and high thermal cycle efficiency; the plasma ignition and combustion assistance technology can enhance ignition, improve the flame propagation speed and stability ability, and achieve efficient combustion under higher pressure, lower flame temperature, and leaner fuel conditions. The present invention realizes the combination of large-thrust propulsion and micro-thrust propulsion modules, and has carried out innovative design on components. This thruster can work in microwave ion electric propulsion mode and pulse detonation chemical propulsion mode respectively, with characteristics such as large thrust, high specific impulse, and long service life, overcomes the limitations of single propulsion technology applications, can be applied to diverse space missions, and provides new ideas for future combinations of other types of propulsion units.

[0098] The preferred embodiments of the present invention have been described in detail above. However, the present invention is not limited to the specific details in the above embodiments. Within the technical concept of the present invention, various equivalent transformations can be made to the technical solutions of the present invention, and these equivalent transformations all fall within the protection scope of the present invention.

Claims

1. A microwave detonation dual-mode space thruster, characterized in that: It includes a propellant supply system, a large-thrust propulsion module and a micro-thrust propulsion module which are coaxially arranged from inside to outside in sequence. The propellant supply system includes a propellant tank, a detonation branch pipeline and an ionization branch pipeline which are respectively connected to the propellant tank; among them, the detonation branch pipeline can supply fuel and oxidant to the large-thrust propulsion module; the ionization branch pipeline can supply electropropellant to the micro-thrust propulsion module. The large-thrust propulsion module includes an injector, a plasma ignition and combustion assistor, a detonation chamber and a tail nozzle; among them, the injector, the detonation chamber and the tail nozzle are coaxially arranged from front to back in sequence; the plasma ignition and combustion assistor is arranged on the front side wall of the detonation chamber. The micro-thrust propulsion module includes a microwave supply system, a magnetic pole, a gas collecting cavity, a discharge chamber and a grid. The gas collecting cavity, the discharge chamber and the grid are coaxially arranged from front to back in sequence. The magnetic pole is a magnetic ring and is coaxially arranged at the head of the discharge chamber adjacent to the gas collecting cavity. The microwave supply system includes a microwave connector and an antenna. The antenna is a cylindrical antenna and is coaxially inserted into the inner wall of the discharge chamber located inside the magnetic pole; a cyclotron cavity is formed between the antenna and the magnetic pole; the cyclotron cavity is respectively connected to the gas collecting cavity and the discharge chamber. The microwave connector is used to feed microwave into the antenna. After the working medium provided by the ionization branch pipeline passes through the gas collecting cavity, it enters the cyclotron cavity; at this time, the outer electrons in the working medium molecules will perform cyclotron motion in the cyclotron cavity, and when the cyclotron angular frequency ω e is equal to the microwave frequency f fed into the antenna, resonance occurs; among them, the cyclotron angular frequency ω e has a matching relationship with the magnetic field strength B of the magnetic pole.

2. The microwave detonation dual-mode space thruster according to claim 1, characterized in that: Gyroscopic angular frequency ω e The calculation formula is as follows: where e and m e are the charge and mass of the outermost electrons in the dielectric molecules, respectively.

3. The microwave detonation dual-mode space thruster according to claim 1, characterized in that: The magnetic pole is an electromagnet. By changing the excitation current of the magnetic pole, the adjustment of the magnetic field intensity B is realized, so as to match the microwave frequency f; when the microwave frequency f is 2.45 GHz, the magnetic field intensity B is adjusted to 0.875 T; when the microwave frequency f is 4.2 GHz, the magnetic field intensity B is adjusted to 1.5 T.

4. The microwave detonation dual-mode space thruster according to claim 1, wherein: The outer shell of the large-thrust propulsion module is the inner shell of the discharge chamber in the micro-thrust propulsion module; the outer shell material of the large-thrust propulsion module is a high-temperature resistant insulating material.

5. The microwave detonation dual-mode space thruster according to claim 1, characterized in that: When the large-thrust propulsion module starts, the plasma ignition and combustion assistor discharges and ignites and assists combustion.

6. The microwave detonation dual-mode space thruster according to claim 5, characterized in that: The pulse detonation chamber adopts a microwave plasma ignition and combustion assistor to realize the integration of microwave discharge technology, plasma combustion assist technology and pulse detonation combustion technology, and utilizes the high-temperature effect, chemical effect and aerodynamic effect of the plasma to improve the ignition ability and flame stabilization ability and realize efficient combustion.

7. The microwave detonation dual-mode space thruster according to claim 5, characterized in that: A check valve is arranged on the detonation branch pipeline; when the pressure in the detonation chamber is lower than the injection pressure, the check valve opens, otherwise, the check valve closes.

8. The microwave detonation dual-mode space thruster according to claim 1, wherein: The axial length of the antenna is greater than the axial length of the magnetic pole, and the antenna and the magnetic pole are flush at the tail end surface of the discharge chamber.

9. The microwave detonation dual-mode space thruster according to claim 1, characterized in that: When the spacecraft needs to perform a rapid maneuver task of space orbit transfer, the large-thrust propulsion module works independently to achieve large thrust; when the spacecraft needs to perform space tasks such as orbit maintenance and attitude adjustment, the micro-thrust propulsion module works independently to achieve high specific impulse.

10. The microwave detonation dual-mode space thruster according to claim 1, characterized in that: When the micro-thrust propulsion module works independently, by applying a periodically changing voltage to the grid, ions and electrons are alternately extracted to realize self-neutralization; among them, the application frequency of the grid voltage is greater than the minimum extraction frequency of the grid.

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