Microwave detonation dual-mode space thruster

Abstract

The invention discloses a microwave detonation dual-mode space thruster. The microwave detonation dual-mode space thruster comprises a propellant supply system, a high-thrust propelling module and a micro-thrust propelling module, wherein the high-thrust propelling module and the micro-thrust propelling module are sequentially and coaxially arranged from inside to outside; the high-thrust propelling module comprises an injector, a plasma ignition combustion-supporting device, a detonation chamber, an exhaust nozzle and the like. The micro-thrust propulsion module comprises a microwave supply system, a magnetic pole, a gas collection cavity, a discharge chamber and a grid electrode; the microwave supply system comprises a microwave connector and an antenna; the antenna is a cylindrical antenna, and a convolution cavity is formed between the antenna and the magnetic pole; outer-layer electrons in electrical substance molecules in the convolution cavity do convolution motion in the convolution cavity, and when the convolution angular frequency is equal to the microwave frequency, resonance occurs. The microwave discharge technology, the plasma combustion-supporting technology and the pulse detonation combustion technology are fused, efficient and convenient switching of working modes is achieved through circuit regulation and control, the thruster can meet the strict requirements of large thrust, high specific impulse, long service life and the like, and the thruster can be applied to diversified space tasks.

Description

Technical Field

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

[0002] With the rapid development of my country's aerospace industry, diversified space missions have put forward higher and more complex requirements for propulsion systems. At present, space thrusters are mainly divided into two categories: chemical high-thrust propulsion and ionization high-specific impulse propulsion. It is difficult to take into account the diversified 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 accelerates ions with electrostatic fields to generate thrust. It has the characteristics of wide thrust range, strong controllability, high specific impulse, and can use a variety of gases as working fluids. It has significant advantages in service life and precise thrust control, but is limited by its small thrust. It is currently mainly used in spacecraft orbit, attitude maintenance and deep space exploration tasks, and does not meet the requirements of rapid maneuverability of spacecraft. In comparison, pulse detonation chemical propulsion technology is a new type of propulsion method that uses high-temperature and high-pressure gas generated by pulsed detonation waves to provide thrust. Its outstanding features are simple structure, low cost, high thrust-to-weight ratio, and high thermal cycle efficiency. For spacecraft with large mass and rapid maneuvering, pulse detonation engines are an ideal choice, but limited by the chemical energy of the propellant and the wall temperature, pulse detonation engines have low specific impulse and cannot meet the requirements of continuously variable thrust. Plasma ignition and combustion support is a new type of ignition and combustion support technology that uses the high temperature effect, chemical effect, and aerodynamic effect of plasma to improve ignition ability and combustion efficiency. It can enhance ignition, increase flame propagation speed and stability, and broaden the flameout limit, thereby achieving efficient combustion under higher pressure, lower flame temperature, and leaner oil conditions.

[0003] The present invention integrates microwave discharge technology, plasma combustion-assisted technology and pulse detonation combustion technology, and realizes efficient and convenient switching of working modes through circuit control, so that the thruster can take into account stringent requirements such as high thrust, high specific impulse and long life, and can be applied to various 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 response to the deficiencies of the above-mentioned prior art. The microwave detonation dual-mode space thruster integrates microwave discharge technology, plasma combustion-assisted technology and pulse detonation combustion technology, effectively solving the problem of long pulse detonation initiation distance, thereby reducing the size of the thruster and improving the ignition and initiation performance. At the same time, through circuit control, efficient and convenient switching of working modes can be achieved, so that the thruster can take into account stringent requirements such as high thrust, high specific impulse and long life, and can be applied to a variety of space missions.

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

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

[0007] The propellant supply system includes a propellant tank, and 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 high-thrust propulsion module; and the ionization branch pipeline can supply electrical fluid to the micro-thrust propulsion module.

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

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

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

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

[0012] The antenna is a cylindrical antenna, which is 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; and the cyclotron cavity is respectively connected with the gas collecting cavity and the discharge chamber.

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

[0014] The electric medium provided by the ionization branch pipeline passes through the gas collecting cavity and enters the cyclotron cavity. At this time, the outer electrons in the electric medium molecules will perform cyclotron motion in the cyclotron cavity, and when the cyclotron angular frequency ω e Resonance occurs when it is equal to the microwave frequency f; among them, the cyclotron angular frequency ω e There is a matching relationship with the magnetic field strength B of the magnetic pole.

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

[0016]

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

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

[0019] 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.

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

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

[0022] A one-way valve is arranged on the detonation branch pipeline; when the pressure in the detonation chamber is lower than the injection pressure, the one-way valve opens, otherwise, the one-way 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 at the rear end surface of the discharge chamber.

[0024] When the spacecraft needs to perform rapid maneuvering missions such as changing orbits in space, 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, a periodically changing voltage is applied to the gate to alternately extract ions and electrons to achieve self-neutralization; wherein the frequency of applying the gate voltage is greater than the minimum extraction frequency of the gate.

[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 technology, and detonation combustion technology to design a microwave detonation dual-mode space thruster. The thruster can operate in two different modes, 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 is wider and the application of space missions is more flexible.

[0028] 2. In the present invention, the micro-thrust propulsion module and the large-thrust propulsion module can share propellants. The choice of propellants includes but is not limited to methane, kerosene, ammonia, oxygen, nitrous oxide, hydrogen peroxide and other fuels and oxidizers, which reduces the mass volume ratio of the tank and the corresponding supporting pipelines, and can save space resources such as mass and volume for the spacecraft.

[0029] 3. The present invention adopts modular design, and the micro-thrust propulsion module and the large-thrust propulsion module can work independently. At the same time, when the working mode is switched, the high temperature of the wall surface can provide favorable conditions for the start of another working mode. The coaxial nested space structure of the thruster is set up to facilitate the replacement of other types of propulsion units as needed when applied to different scenarios in the future.

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

[0031] 5. The present invention achieves the effect of self-neutralization by alternately introducing ions and electrons through periodic changes in the gate voltage. No external neutralizer is required, the thruster structure is simplified, and the restriction of particle contamination of the hot cathode material of the traditional neutralizer can be avoided, the failure rate can be reduced, the life of the thruster can be extended, and the launch cost can be reduced.

[0032] 6. For the high-thrust propulsion module, the present invention adopts the slow combustion to detonation transition (DDT) method for indirect detonation, and sets a DDT enhancement device to accelerate the formation of detonation waves; a one-way valve is used to achieve adaptive control of the pulse detonation cycle process, without the need for additional control devices, reducing the complexity of the system.

[0033] 7. The present invention applies plasma combustion-supporting technology to pulse detonation chemical propulsion, and adopts plasma ignition combustion-supporting device, which can adopt DBD plasma ignition combustion-supporting device, arc plasma ignition combustion-supporting device, microwave plasma ignition combustion-supporting device, etc. Preferably, microwave plasma ignition combustion-supporting device is adopted, which can share microwave excitation source and power supply, and promote combustion and detonation while simplifying the structure, so as to realize mutual coupling between ignition and combustion-supporting. At the same time, according to the actual application needs, the present invention proposes to set 2n (n=1,2,...) pairs in pairs to realize uniform ignition and generate a large number of active particles to promote stable combustion. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 A three-dimensional stereogram of a microwave detonation dual-mode space thruster of the present invention is shown.

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

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

[0037] Figure 4 A three-dimensional cross-sectional view of a high-thrust propulsion module according to the present invention is shown.

[0038] Figure 5 A three-dimensional cross-sectional view of the micro-thrust propulsion module of the present invention is shown.

[0039] Figure 6A flow chart of the adaptive working cycle of the high thrust propulsion module in the present invention is shown.

[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 collecting cavity; 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 booster; 33. Detonation chamber; 34. Tail nozzle; 35. DDT enhancement device. DETAILED DESCRIPTION

[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 terms "left side", "right side", "upper part", "lower part" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, which is only for the convenience of describing the present invention and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. "First", "second" and the like do not indicate the importance of the components, and therefore cannot be understood as limiting the present invention. The specific dimensions used in this embodiment are only for illustrating the technical solution, and do not limit the scope of protection of the present invention.

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

[0051] like Figure 2 As shown, the propellant supply system includes a propellant tank 11, and a detonation branch line 13 and an ionization branch line 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 effectively save mass resources while making full use of the volume space resources of the spacecraft. 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 detonation branch pipeline can supply fuel and oxidant to the high-thrust propulsion module, and a one-way valve 14 is preferably provided on the detonation branch pipeline.

[0054] The above-mentioned ionization branch pipeline can supply electric medium to the micro-thrust propulsion module. The electric medium is preferably one or a combination of fuel and oxidant. Further, the ionization branch pipeline is preferably provided with a cracking gasification device.

[0055] like Figure 2 , Figure 3 and Figure 5 As 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 collecting cavity 23, a discharge chamber 24, a grid 25, a shielding shell 26 and a discharge chamber shell 27.

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

[0057] The magnetic pole is a magnetic ring, which is coaxially arranged at the head of the discharge chamber adjacent to the gas collecting cavity.

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

[0059] 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. Furthermore, the length of the antenna extending into the discharge chamber is preferably 1 / 2-2 / 3 of the discharge chamber, which is 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 tail end surface of the discharge chamber.

[0060] like Figure 5 As shown, the tail end face of the gas collecting cavity is provided with a circle of evenly distributed distribution holes 231, and the gas collecting cavity is connected to the cyclotron cavity through the distribution holes, and the cyclotron cavity is directly connected to the discharge chamber. The electrical medium enters the gas collecting cavity and the residence time is prolonged due to the resistance, and the gas is evenly distributed through the distribution holes and enters the discharge chamber.

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

[0062] The magnetic pole is preferably an electromagnet, and the magnetic field strength B is adjusted by changing the excitation current of the magnetic pole to match the microwave frequency f; when the microwave frequency f is 2.45GHz, the magnetic field strength B is adjusted to 0.875T; when the microwave frequency f is 4.2GHz, the magnetic field strength B is adjusted to 1.5T.

[0063] A shield case 26 is preferably provided on the outer periphery of the discharge chamber housing 27 .

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

[0065] The injector, detonation chamber and tail nozzle are coaxially arranged from front to back; among them, the injector is preferably a coaxial injector, which can promote the mixing and detonation process of the fuel and oxidizer.

[0066] The above-mentioned igniter is arranged on the front side wall of the detonation chamber. The igniter adopts a plasma ignition combustion aid, which can adopt a DBD plasma ignition combustion aid device, an arc plasma ignition combustion aid device, a microwave plasma ignition combustion aid device, etc. The present invention preferably adopts a microwave plasma ignition combustion aid device, which shares a microwave excitation source and power supply with the micro-thrust propulsion module to achieve structural reuse and simplification. According to the actual application needs, the plasma ignition combustion aid is 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 detonation adopts the indirect detonation method of transition from slow combustion to detonation (DDT). A DDT enhancement device 35 is installed in the detonation tube to accelerate the transition from slow combustion to detonation. Shchelkin spiral wire, semi-disc-shaped protrusion, plugging plate, orifice plate, etc. can be used.

[0068] Further one-way valve arrangement can be used to achieve Figure 6 The self-adaptive control of the detonation cycle process shown in the figure is completely controlled by the self-adaptive control of the working process of the detonation cycle, and does not require a special control device such as a solenoid valve. When the pressure in the detonation chamber is lower than the injection pressure, the one-way valve opens, otherwise, the one-way valve closes.

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

[0070] Combined with the actual application of the invention, the temperature of the propulsion module will rise sharply when it is working, and the wall material needs to be optimized. For the shell of the micro-thrust propulsion module, high-temperature resistant materials such as titanium alloy can be selected, and for the shell of the large-thrust propulsion module, insulating materials with good high-temperature resistance such as silicon-based ceramics and carbon-carbon composite materials can be selected. While being suitable for the high-temperature environment of chemical large-thrust combustion, it can also meet the conditions for maintaining the generation 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 fluid of the other module, creating favorable conditions for switching and starting the thruster working mode.

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

[0072] 1. High-thrust propulsion

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

[0074] (1) Propellant filling: Turn on the fuel and oxidizer switches and open the one-way valve to 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 the form of deflagration, first generating a slow combustion wave in the detonation tube. After DDT, the slow combustion wave turns into 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 propagates toward the outlet and is finally further expanded and discharged through the tail nozzle, generating a large thrust.

[0078] (5) Expansion wave transmission: An expansion wave is generated at the pipe mouth and transmitted into the detonation chamber, exhausting the burned gas, and the gas parameters in the detonation chamber gradually reach equilibrium.

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

[0080] 2. 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 microwave source to generate a magnetic field, and feed microwaves into the discharge chamber through the antenna.

[0083] (2) Propellant introduction: Open the propellant storage and supply system and introduce the propellant.

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

[0085]

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

[0087] When e When the frequency is equal to that of the externally applied microwaves, the electrons resonate with the microwaves, and the microwave energy is continuously coupled to the electrons, raising the electron temperature and energy level, transforming them into high-energy electrons, and eventually breaking free from the constraints of the atomic nucleus and flying out to achieve ionization.

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

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

[0090] The minimum extraction frequency f of the above gate min The calculation formula is preferably:

[0091]

[0092] in:

[0093]

[0094] Where, L eff is the effective distance of ions moving between the gates; L g is the gate spacing, t s is the screen thickness, r s is the radius of the grid hole; U s is the gate voltage, M is the mass of the ion, and e is the electron charge.

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

[0096] When the gate voltage is greater than zero, the gate extracts ions; when the gate voltage is equal to or less than zero, the gate extracts electrons. The total amount of ions and electrons extracted by the gate is equal on average in each cycle, and the beam is quasi-neutral, thus achieving the effect of self-neutralization, without the need for an external neutralizer, reducing system complexity and lowering the failure rate.

[0097] The present invention integrates microwave discharge technology, plasma combustion-supporting technology and pulse detonation combustion technology, comprehensively combines technical advantages, effectively solves the problem of long pulse detonation detonation distance, improves ignition capability and combustion efficiency, and realizes efficient and convenient switching of working modes through circuit regulation. Microwave ion electric propulsion technology has a wide thrust range, strong controllability, and high specific impulse. It can use a variety of gases as working fluids, and has significant advantages in service life and precise thrust control; pulse detonation chemical propulsion technology has a simple structure, low cost, high thrust-to-weight ratio, and high thermal cycle efficiency; plasma ignition and combustion-supporting technology can enhance ignition, improve flame propagation speed and stability, and achieve efficient combustion under higher gas pressure, lower flame temperature, and leaner oil conditions. The present invention realizes the combination of high-thrust propulsion and micro-thrust propulsion modules, and innovatively designs the components. The thruster can work in microwave ion electric propulsion mode and pulse detonation chemical propulsion mode respectively, and has the characteristics of high thrust, high specific impulse, and long life. It overcomes the limitations of the application of a single propulsion technology, can be applied to a variety of space missions, and provides new ideas for the combination of other types of propulsion units in the future.

[0098] The preferred embodiments of the present invention are 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 belong to 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 the inside to the outside; The propellant supply system includes a propellant tank, and 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 high-thrust propulsion module; and the ionization branch pipeline can supply electrical fluid to the micro-thrust propulsion module; The micro-thrust propulsion module includes a microwave supply system, magnetic poles, gas collecting cavity, discharge chamber and grid; The gas collecting cavity, the discharge chamber and the grid are coaxially arranged from front to back; The magnetic pole is a magnetic ring, which 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, 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 connected with the gas collecting cavity and the discharge chamber; The microwave connector is used to feed microwaves to the antenna; The electric medium provided by the ionization branch pipeline passes through the gas collecting cavity and enters the cyclotron cavity. At this time, the outer electrons in the electric medium molecules will perform cyclotron motion in the cyclotron cavity, and when the cyclotron angular frequency ω e Resonance occurs when the frequency f of the microwave fed into the antenna is equal to that of the microwave fed into the antenna; where the cyclotron angular frequency ω e There is 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: Cyclotron angular frequency ω e The calculation formula is: In the formula, e and m e are the charge and mass of the outer electrons in the electrical fluid molecules, respectively.

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

4. The microwave detonation dual-mode space thruster according to claim 1, characterized in that: 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: The high-thrust propulsion module includes an injector, a plasma ignition booster, a detonation chamber and a tail nozzle; wherein the injector, the detonation chamber and the tail nozzle are coaxially arranged in sequence from front to rear; the plasma ignition booster is arranged on the front side wall of the detonation chamber; when the high-thrust propulsion module is started, the plasma ignition booster discharges, 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 aid to realize the integration of microwave discharge technology, plasma combustion-aided technology and pulse detonation combustion technology. It utilizes the high temperature effect, chemical effect and aerodynamic effect of plasma to improve the ignition ability and flame stabilization ability and achieve efficient combustion.

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

8. The microwave detonation dual-mode space thruster according to claim 1, characterized in that: 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 rear 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 rapid maneuvering missions such as changing orbits in space, 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.

10. The microwave detonation dual-mode space thruster according to claim 1, characterized in that: When the micro-thrust propulsion module works independently, a periodically changing voltage is applied to the gate to alternately extract ions and electrons to achieve self-neutralization; wherein the frequency of applying the gate voltage is greater than the minimum extraction frequency of the gate.

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