Composite propulsion device based on electron cyclotron resonance effect

Abstract

The invention provides a composite propulsion device based on an electron cyclotron resonance effect. The composite propulsion device comprises an ionization cavity, a magnet, a microwave source and a storage box, the ionization cavity ionizes and / or heats the working medium and then sprays out the working medium to generate thrust; the magnet generates a divergent magnetic field, so that heating and / or ionization in the ionization cavity can be enhanced; the microwave source inputs microwave energy to the ionization cavity and can ionize and / or heat a working medium; the storage box stores a working medium and supplies the working medium to the ionization cavity. The propelling device provided by the invention is simple in structure, free of a cathode and easy to miniaturize.

Description

Technical Field

[0001] The present invention relates to the field of electric propulsion technology, and in particular to a composite propulsion device based on electron cyclotron resonance effect, and in particular to a propulsion device that utilizes microwaves to ionize or heat gas and then ejects it to generate thrust. Background Art

[0002] According to the difference in the working fluid acceleration principle, space propulsion methods can be divided into gas propulsion and electric propulsion. Gas propulsion uses the internal energy of the working fluid itself or the heat energy supplied externally to make the working fluid gas expand and accelerate after being heated, and then eject in a directional manner to generate thrust; electric propulsion uses electrical energy to ionize the working fluid to generate charged particles, and then uses the electromagnetic field to accelerate the charged particles in a directional manner to generate thrust. The gas propulsion device starts quickly and has a large thrust, which is suitable for the thrust requirements of time-sensitive mission scenarios such as spacecraft orbit change and rapid maneuvering, but the gas propulsion device has a low specific impulse and needs to carry a large amount of propellant for long-term use. The electric propulsion device has a small thrust and a high specific impulse, which is suitable for the thrust requirements of fine control mission scenarios such as attitude control and orbit maintenance of spacecraft or large total impulse missions, but the electric propulsion device is more complex than the gas propulsion system and has many usage restrictions. Due to the difference in working principles, at present, gas propulsion devices and electric propulsion devices are usually two independent systems. Spacecraft either use one of them to meet the main mission requirements; or sacrifice the system weight and use both propulsion devices at the same time to take into account the thrust requirements in different scenarios. Summary of the invention

[0003] In view of the defects in the prior art, an object of the present invention is to provide a composite propulsion device based on the electron cyclotron resonance effect.

[0004] A composite propulsion device based on electron cyclotron resonance effect provided by the present invention comprises: an ionization chamber, a magnet, a microwave source and a tank;

[0005] The ionization chamber ionizes and / or heats the working fluid and then ejects it to generate thrust;

[0006] The magnet generates a divergent magnetic field capable of enhancing heating and / or ionization within the ionization chamber;

[0007] The microwave source inputs microwave energy into the ionization cavity, which can ionize and / or heat the working medium;

[0008] The tank stores the working fluid and supplies the working fluid to the ionization chamber.

[0009] Preferably, the ionization chamber comprises: an inner conductor and an outer conductor;

[0010] The inner conductor and the outer conductor are coaxially matched to form a microwave transmission channel;

[0011] One end of the ionization chamber is closed and connected to the microwave source through a microwave transmission cable and connected to the storage tank through a working fluid supply pipeline;

[0012] The other end of the ionization chamber is open to allow the ionized and / or heated working fluid to be ejected to generate thrust.

[0013] Preferably, the closed end of the ionization chamber is closed using a wave-transmitting medium plate;

[0014] The inner conductor is mounted on the wave-transmitting dielectric plate, and the wave-transmitting dielectric plate can achieve electrical insulation between the inner conductor and the outer conductor.

[0015] Preferably, a working fluid pipeline is provided at the center of the inner conductor;

[0016] The working fluid pipeline passes through the wave-transmitting medium plate and is connected to the working fluid supply pipeline, so as to supply working fluid into the ionization chamber.

[0017] Preferably, the microwave source is a solid-state microwave source that converts input electrical energy into microwaves of a specified frequency.

[0018] Preferably, a voltage isolation waveguide is provided on the microwave transmission cable, and the voltage isolation waveguide can isolate direct current transmission when transmitting microwave energy.

[0019] Preferably, a heating device is arranged outside the storage tank;

[0020] The heating device can heat the tank and control the pressure inside the tank.

[0021] Preferably, an insulating pipeline is provided on the working fluid supply pipeline, and the insulating pipeline is used to isolate the voltage between the ionization chamber and the tank;

[0022] The working medium supply pipeline is provided with a throttle valve, and the throttle valve can control the flow rate of the working medium in the pipeline.

[0023] Preferably, a heat exchanger is provided between the storage tank and the microwave source;

[0024] Waste heat generated by the microwave source can be transferred to the storage tank through the heat exchanger.

[0025] Preferably, the composite propulsion device can be switched between the electric propulsion mode and the gas propulsion mode by changing the gas supply flow rate and the microwave power in the ionization chamber;

[0026] When the gas supply flow rate is low and the microwave power is high, the composite propulsion device operates in an electric propulsion mode;

[0027] When the gas supply flow rate is high, the compound propulsion device operates in the gas propulsion mode.

[0028] Compared with the prior art, the present invention has the following beneficial effects:

[0029] 1. The propulsion device proposed in the present invention has a simple structure, no cathode, and is easy to miniaturize; a high specific impulse mode and a large thrust mode can be realized on the same propulsion device, combining the high specific impulse advantage of the electric propulsion device with the relatively large thrust advantage of the gas propulsion device; the device has a wide range of propellant selections, and can select working fluids that are easy to store at a high density, without the propellant type restrictions caused by cathode contamination sensitivity in ion electric propulsion and Hall electric propulsion.

[0030] 2. The present invention utilizes the electron cyclotron resonance effect and the magnetic nozzle effect to realize the electric propulsion mode with high specific impulse and the gas propulsion mode with large thruster on a single propulsion device. The propulsion device can flexibly switch between the two modes by adjusting the microwave power and the gas flow rate. In the electric propulsion mode, the gas flow rate is small and the microwave power is high. After the gas is ionized, it is ejected at high speed through the magnetic nozzle to achieve a high specific impulse; in the gas propulsion mode, the gas flow rate is large, and the microwave energy is insufficient to provide ionization energy, and the gas is mainly heated to generate a large thrust.

[0031] 3. The propulsion device proposed in the present invention can be implemented as a space propulsion system with different thrust and power levels by adapting the discharge cavity size, microwave source frequency, power, and tank volume. In a specific propulsion device, the microwave power and gas flow rate can be adjusted to switch the working mode to meet the propulsion needs of spacecraft in different working scenarios: the propulsion device can work in a high-thrust mode with lower power consumption to achieve rapid maneuvering of the spacecraft; in small-thrust tasks such as long-term orbit maintenance and attitude control, the propulsion device works in a high-specific impulse electric propulsion mode to save propellant dosage. By switching between different working modes, the maneuverability and life of the spacecraft can be significantly improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0033] Figure 1 The present invention mainly embodies a thruster composition schematic diagram of a chemical-electric hybrid propulsion device based on the electron cyclotron resonance effect;

[0034] Figure 2 The present invention mainly embodies a permanent magnet and magnetic field schematic diagram of a chemical-electric hybrid propulsion device based on the electron cyclotron resonance effect;

[0035] Figure 3The present invention mainly embodies the structural schematic diagram of an ionization chamber of a chemical-electric hybrid propulsion device based on the electron cyclotron resonance effect.

[0036] The figure shows:

[0037] Ionization chamber 1 Storage tank 4

[0038] Magnet 2 Wave-transmitting medium plate 5

[0039] Microwave source 3 Heat exchanger 6 DETAILED DESCRIPTION

[0040] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0041] Embodiment 1:

[0042] As shown in 1-3, this embodiment is a composite propulsion device based on the electron cyclotron resonance effect, comprising: an ionization chamber 1, a magnet 2, a microwave source 3 and a tank 4; the ionization chamber 1 ionizes and / or heats the working fluid and then ejects it to generate thrust; the magnet 2 generates a divergent magnetic field, which can enhance the heating and / or ionization in the ionization chamber 1; the microwave source 3 inputs microwave energy into the ionization chamber 1, which can ionize and / or heat the working fluid; the tank 4 stores the working fluid and supplies the working fluid to the ionization chamber 1.

[0043] By changing the gas supply flow rate and microwave power in the ionization chamber 1, the composite propulsion device can switch between the electric propulsion mode and the gas propulsion mode; when the gas supply flow rate is low and the microwave power is high, the composite propulsion device works in the electric propulsion mode; when the gas supply flow rate is high, the composite propulsion device works in the gas propulsion mode.

[0044] The ionization chamber 1 comprises: an inner conductor 101 and an outer conductor 102; the inner conductor 101 and the outer conductor 102 are coaxially matched to form a microwave transmission channel; one end of the ionization chamber 1 is closed, connected to the microwave source 3 through a microwave transmission cable, and connected to the tank 4 through a working fluid supply pipeline; the other end of the ionization chamber 1 is open, allowing the ionized and / or heated working fluid to be ejected to generate thrust.

[0045] The ionization cavity adopts a coaxial channel to adapt to different modes of microwave transmission such as TEM, TE, and TM, which is beneficial to improving the microwave-plasma coupling efficiency.

[0046] The closed end of the ionization chamber 1 is closed by a wave-transparent dielectric plate 5; the inner conductor 101 is mounted on the wave-transparent dielectric plate 5, and the wave-transparent dielectric plate 5 can achieve electrical insulation between the inner conductor 101 and the outer conductor 102. A working fluid pipeline is provided at the center of the inner conductor 101; the working fluid pipeline passes through the wave-transparent dielectric plate 5 and is connected to the working fluid supply pipeline, and is used to supply working fluid into the ionization chamber 1. The microwave source 3 is a solid-state microwave source, which converts input electrical energy into microwaves of a specified frequency.

[0047] The microwave transmission cable is provided with a voltage isolation waveguide, which can isolate direct current transmission when transmitting microwave energy. The working fluid supply pipeline is provided with an insulating pipeline, which is used to isolate the voltage between the ionization chamber 1 and the tank 4; the working fluid supply pipeline is provided with a throttle valve, which can control the flow rate of the working fluid in the pipeline.

[0048] A heating device is arranged outside the storage tank 4; the heating device can heat the storage tank 4 and control the pressure inside the storage tank 4. A heat exchanger 6 is arranged between the storage tank 4 and the microwave source 3; the waste heat generated by the microwave source 3 can be transferred to the storage tank 4 through the heat exchanger 6.

[0049] This embodiment provides a composite propulsion device based on the electron cyclotron resonance effect, which is composed of an ionization chamber 1, a magnet 2, a microwave source 3, and a tank 4. The ionization chamber 1 is divided into a cylindrical section 103 and an expansion section 104. The cylindrical section 103 is a coaxial structure composed of an outer conductor 101 and an inner conductor 102, which is used to transmit microwave energy; the end of the cylindrical section 103 is connected to a conical expansion channel, and there is a channel in the center of the inner conductor for conveying the working medium. The magnet 2 forms a magnetic field of a specific intensity inside the ionization chamber 1 to meet the electron cyclotron resonance condition, and at the same time generates a divergent magnetic field at the cavity outlet of the cylindrical section 103 to form a magnetic nozzle. The microwave source 3 feeds microwave energy into the coaxial ionization chamber 1 through a transmission line, and the waste heat generated by the microwave source is transmitted to the tank 4 through a heat exchanger 6 to heat the propellant and increase the tank pressure. The propellant is stored in the tank, and the propellant can enter the ionization chamber through a pipeline connected to the central channel of the inner conductor 102 of the coaxial ionization chamber 1, and is heated or ionized under the action of the microwave field and the static magnetic field.

[0050] The combination of the cylindrical section 103 and the expansion section 104 can take into account both microwave transmission and plasma acceleration. The electron cyclotron resonance region is located in the cylindrical section and forms a coaxial structure with the inner conductor 101, which keeps the cross section fixed and thus keeps the microwave transmission impedance stable, which is conducive to reducing the microwave reflectivity and improving the transmission efficiency of microwaves to the resonance region. The electrons in the plasma move along the magnetic flux lines during the expansion and acceleration process. The use of an expansion wall near the exit can reduce the number of magnetic flux lines intersecting the wall, thereby reducing the adsorption of the wall on the electrons and reducing energy loss.

[0051] like Figure 2 As shown, A is the outline inside the ionization chamber, B is the resonance area, and C is the permanent magnet.

[0052] Existing propulsion devices generally use radio frequency (frequency range 1MHz ~ 100MHz) and microwave (frequency greater than 1GHz) to ionize gas, with radio frequency power coupled from an external antenna and microwave power coupled from an internal antenna. This embodiment only uses microwave power input through an internal antenna. Compared with existing propulsion devices, this embodiment simplifies the energy feeding path of the ionization chamber, reduces the complexity of the discharge chamber structure, and improves the electromagnetic wave-plasma energy coupling efficiency.

[0053] Existing propulsion devices generally use a grid to accelerate ions. The size of the ion current (thrust size) is limited by the space charge effect, and a high-voltage DC power supply is required. At the same time, a neutralizer is required to emit electrons to neutralize the ions ejected from the discharge chamber. This embodiment uses an expansion magnetic field (magnetic nozzle) to accelerate electrons and ions at the same time, and there is no space charge effect limitation during the acceleration process. Compared with existing propulsion devices, the acceleration method used in this embodiment does not require additional power supply, has a high thrust limit, does not require a neutralizer, has a simple device structure, and has high reliability.

[0054] Embodiment 2:

[0055] Those skilled in the art may understand this embodiment as a more specific description of Embodiment 1.

[0056] This embodiment provides a composite propulsion device based on the electron cyclotron resonance effect, which is composed of an ionization chamber 1, a magnet 2, a microwave source 3, and a tank 4. The ionization chamber 1 ionizes or heats the working fluid and ejects it to generate thrust. The magnet 2 generates a divergent magnetic field to enhance the heating, ionization and acceleration effects in the ionization chamber. The microwave source 3 inputs microwave energy into the ionization chamber 1 to ionize or heat the working fluid. The tank 4 stores the working fluid and supplies the working fluid to the ionization chamber 1.

[0057] The ionization chamber 1 is composed of an inner conductor and an outer conductor, which are coaxially matched to form a cylindrical microwave transmission channel. One end of the ionization chamber 1 is closed and connected to the microwave transmission cable and the working medium supply pipeline; the other end is open to allow the accelerated working medium to be ejected to generate thrust.

[0058] The closed end of the ionization chamber 1 is closed by a wave-transmitting dielectric plate, and the inner and outer conductors constituting the ionization chamber 1 are electrically insulated.

[0059] A pipe is provided at the center of the inner conductor of the ionization chamber 1, passing through the wave-transmitting medium plate, for supplying working fluid into the ionization chamber.

[0060] The magnet 2 is composed of an electromagnet, a permanent magnet or a combination of the two. The magnetic field distribution near the ionization chamber 1 can be changed by changing the shape, position, combination and excitation current of the magnet.

[0061] The microwave source 3 is a solid-state microwave source that converts input electrical energy into microwaves of a specified frequency.

[0062] The microwave transmission line is provided with a voltage isolation waveguide to isolate direct current transmission while transmitting microwave energy.

[0063] The storage tank 4 can store liquid, gas or solid working medium.

[0064] A heating device is arranged outside the storage tank 4 to heat the storage tank, thereby controlling the internal pressure of the storage tank.

[0065] The storage tank 4 is connected to the channel at the center of the inner conductor of the ionization chamber 1 through a pipeline. An insulating pipeline is arranged on the connecting pipeline to isolate the voltage between the discharge chamber and the storage tank. A throttle valve is arranged on the connecting pipeline to control the flow in the pipeline.

[0066] A heat exchanger is provided between the storage tank 4 and the microwave source 3 , and waste heat generated by the microwave source 3 can be transferred to the storage tank 4 through the heat exchanger.

[0067] By changing the gas supply flow rate and microwave power in the discharge chamber, the device can be switched between electric propulsion mode and gas propulsion mode. When the flow rate is low and the microwave power is high, the device can work in the electric propulsion mode. When the flow rate is high, the device can work in the gas propulsion mode.

[0068] Embodiment 3:

[0069] Those skilled in the art may understand this embodiment as a more specific description of Embodiment 1.

[0070] In view of the defects in the prior art, the purpose of the present invention is to provide a chemical-electric hybrid propulsion device based on the electron cyclotron resonance effect, so that a single propulsion device has a high specific impulse electric propulsion mode and a large thrust gas propulsion mode, and can flexibly switch between the two working modes according to mission requirements.

[0071] According to the present invention, a chemical-electric hybrid propulsion device based on the electron cyclotron resonance effect is provided, comprising: an ionization chamber, a magnet, a microwave source, and a tank. The ionization chamber ionizes or heats the working fluid and then ejects it to generate thrust. The magnet generates a divergent magnetic field to enhance the heating, ionization and acceleration effects in the ionization chamber. The microwave source inputs microwave energy into the ionization chamber to ionize or heat the working fluid. The tank stores the working fluid and supplies the working fluid to the ionization chamber.

[0072] Furthermore, the ionization chamber is composed of an inner conductor and an outer conductor, which are coaxially matched to form a cylindrical microwave transmission channel, so that electromagnetic waves are transmitted therein in TE mode.

[0073] Furthermore, the left end of the ionization chamber is closed, and a microwave connector and a gas pipe connector are installed on the left side of the closed end, which are used to connect the microwave transmission line and the working fluid supply pipeline respectively.

[0074] Furthermore, the right end of the ionization chamber is open, and the working fluid can be ejected from the open end to generate thrust after being accelerated.

[0075] Furthermore, the closed end of the ionization chamber is sealed with a wave-transmitting dielectric plate to achieve electrical insulation between the inner and outer conductors of the ionization chamber.

[0076] Furthermore, the magnet is composed of an electromagnet, a permanent magnet or a combination of the two. By changing the shape, position, combination and excitation current of the magnet, the magnetic field distribution near the ionization chamber can be changed to regulate the heating and acceleration process of the charged particles.

[0077] Furthermore, a voltage isolation waveguide is provided on the microwave transmission line, which can isolate direct current transmission while transmitting microwave energy.

[0078] Furthermore, heating devices may be arranged inside and outside the tank, and the working medium may be heated by the heating devices inside or outside the tank to increase the temperature of the gaseous working medium, or to gasify the liquid or solid working medium, thereby controlling the internal pressure of the tank.

[0079] Furthermore, the tank is connected to the ionization chamber via a pipeline, an insulating pipeline is provided on the connecting pipeline to isolate the voltage between the ionization chamber and the tank; a throttle valve is provided on the connecting pipeline to control the flow in the pipeline.

[0080] Furthermore, a heat exchanger is provided between the storage tank and the microwave source, and waste heat generated by the microwave source can be transferred to the storage tank through the heat exchanger.

[0081] Furthermore, the composite propulsion device based on the electron cyclotron resonance effect can switch between the electric propulsion mode and the gas propulsion mode by changing the gas supply flow rate in the discharge chamber. In the small thrust working scenarios such as fine-tuning of the spacecraft attitude and unloading of the momentum wheel, the small thrust and high specific impulse mode is adopted; in the mission scenarios with strong timeliness such as changing orbits and collision avoidance, the high thrust working mode is adopted. Electrons obtain energy from the microwave field through the electron cyclotron resonance effect. When the flow rate is low, the gas density is low (the air pressure is less than 1Pa), the electron free path is large, and the collision frequency is low. The electron energy can be accumulated to a high level, exceeding the ionization energy of the gas atoms, and the ionized gas generates plasma. The plasma is ejected at a high speed through the magnetic nozzle to generate thrust, and the device works in the electric propulsion mode; when the flow rate is high, the gas density is high (the air pressure is greater than 100Pa), the electron free path is small, and the electron-atom collision is frequent. The electron energy is difficult to exceed the gas ionization energy, but the working gas can be heated by frequent collisions, and the gas is accelerated and ejected to generate thrust, and the device works in the gas propulsion mode.

[0082] The propulsion device proposed in this embodiment has a simple structure, no cathode, and is easy to miniaturize; high specific impulse mode and high thrust mode can be achieved on the same propulsion device, combining the high specific impulse advantage of the electric propulsion device with the relatively high thrust advantage of the gas propulsion device; the device has a wide range of propellant selections, and can select working fluids that are easy to store at a high density, and there is no restriction on the type of propellant caused by cathode contamination sensitivity in ion electric propulsion and Hall electric propulsion.

[0083] Embodiment 4:

[0084] Those skilled in the art may understand this embodiment as a more specific description of Embodiment 1.

[0085] like Figure 1-3 As shown, this embodiment provides a chemical-electric hybrid propulsion device based on the electron cyclotron resonance effect, including: an ionization chamber, a magnet, a microwave source, and a tank. The ionization chamber is not coaxial, and the magnet is installed near the ionization chamber to generate a magnetic field that meets the electron cyclotron resonance condition at a specific position in the ionization chamber; the microwave source inputs microwave energy to the ionization chamber through a microwave transmission line; and the tank inputs gas to the ionization chamber through a gas supply pipeline.

[0086] At present, space propulsion devices include gas propulsion devices and electric propulsion devices. Gas propulsion devices are simple in structure, with large thrust but low specific impulse; electric propulsion devices have high specific impulse and low thrust. When selecting a propulsion system for a spacecraft, there are limitations on weight, power and system complexity, and it is difficult to balance specific impulse and thrust.

[0087] This embodiment uses the electron cyclotron resonance effect and the magnetic nozzle effect to realize the electric propulsion mode with high specific impulse and the gas propulsion mode with large thruster on a single propulsion device. By adjusting the microwave power and gas flow rate, the propulsion device can flexibly switch between the two modes. In the electric propulsion mode, the gas flow rate is small and the microwave power is high. After the gas is ionized, it is ejected at high speed through the magnetic nozzle to achieve a high specific impulse; in the gas propulsion mode, the gas flow rate is large, and the microwave energy is insufficient to provide ionization energy, and the gas is mainly heated to generate a large thrust.

[0088] The discharge cavity is a coaxial structure, and the left end is closed by a dielectric material. The dielectric material can be selected from alumina ceramics, boron nitride ceramics or quartz glass. The left side of the dielectric material is a coaxial transition structure, which converts the discharge cavity into a standard coaxial microwave connector. The connector forms include N-type connectors, SMA-type connectors, etc. Through the structural design of the transition structure, wave impedance matching in the transition area can be achieved; the standard microwave connector can be further directly or indirectly connected to the microwave source. The indirect connection methods include: coaxial cable, waveguide-coaxial cable converter, etc.

[0089] The magnet can be a permanent magnet, an electromagnet or a combination of the two. By designing the shape and magnetization strength of the magnet, a magnetic field that meets the electron cyclotron resonance condition is generated in the space above the magnetic pole, and this area is the resonance zone. The discharge cavity is placed above the magnetic pole, and the discharge cavity is open upward, so that the resonance zone is located between the end face of the dielectric window of the discharge cavity and the open end, and it is ensured that the magnetic flux lines generated by the magnet are divergent along the dielectric window to the open end.

[0090] When the working fluid is gas, such as xenon, krypton, argon, etc., titanium alloy cylinders or carbon fiber composite cylinders are used; when the working fluid is liquid or solid, such as liquid ammonia, water, iodine, etc., the tank and transmission pipeline are equipped with heaters and insulation layers to vaporize the working fluid and ensure that the working fluid remains in a gaseous state during transportation. The tank and microwave source are stacked up and down through the transfer structure, so that the microwave source can transfer heat to the tank.

[0091] The propulsion device proposed in this embodiment can be implemented as a space propulsion system with different thrust and power levels by adapting the discharge cavity size, microwave source frequency, power, and tank volume. In a specific propulsion device, the microwave power and gas flow rate can be adjusted to achieve working mode switching to meet the propulsion needs of spacecraft in different working scenarios: the propulsion device can work in a high-thrust mode at a relatively low power consumption to achieve rapid maneuvering of the spacecraft; in small-thrust missions such as long-term orbit maintenance and attitude control, the propulsion device works in a high-specific impulse electric propulsion mode to save propellant dosage. By switching between different working modes, the maneuverability and life of the spacecraft can be significantly improved.

[0092] The propulsion device proposed by the present invention has a simple structure, has no cathode, and is easy to be miniaturized.

[0093] In the description of the present application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0094] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A composite propulsion device based on electron cyclotron resonance effect, characterized in that: include: An ionization chamber (1), a magnet (2), a microwave source (3) and a storage tank (4); The ionization chamber (1) ionizes and / or heats the working fluid and then ejects it to generate thrust; The magnet (2) generates a divergent magnetic field capable of enhancing heating and / or ionization in the ionization chamber (1); The microwave source (3) inputs microwave energy into the ionization chamber (1), which can ionize and / or heat the working medium; The storage tank (4) stores the working fluid and supplies the working fluid to the ionization chamber (1).

2. The composite propulsion device based on the electron cyclotron resonance effect according to claim 1, characterized in that: The ionization chamber (1) comprises: an inner conductor (101) and an outer conductor (102); The inner conductor (101) and the outer conductor (102) are coaxially matched to form a microwave transmission channel; One end of the ionization chamber (1) is closed and connected to the microwave source (3) via a microwave transmission cable, and connected to the storage tank (4) via a working fluid supply pipeline; The other end of the ionization chamber (1) is open, allowing the ionized and / or heated working fluid to be ejected to generate thrust.

3. The composite propulsion device based on the electron cyclotron resonance effect according to claim 2, characterized in that: The closed end of the ionization chamber (1) is closed using a wave-transmitting medium plate (5); The inner conductor (101) is mounted on the wave-transmitting dielectric plate (5), and the wave-transmitting dielectric plate (5) is capable of achieving electrical insulation between the inner conductor (101) and the outer conductor (102).

4. The composite propulsion device based on the electron cyclotron resonance effect according to claim 3 is characterized in that: A working fluid pipeline is arranged at the center of the inner conductor (101); The working medium pipeline passes through the wave-transmitting medium plate (5) and is connected to the working medium supply pipeline, and is used to supply working medium into the ionization chamber (1).

5. The composite propulsion device based on electron cyclotron resonance effect according to claim 1, characterized in that: The microwave source (3) is a solid-state microwave source that converts input electrical energy into microwaves of a specified frequency.

6. The composite propulsion device based on the electron cyclotron resonance effect according to claim 5, characterized in that: The microwave transmission cable is provided with a voltage isolation waveguide, and the voltage isolation waveguide can isolate direct current transmission when transmitting microwave energy.

7. The composite propulsion device based on electron cyclotron resonance effect according to claim 1, characterized in that: A heating device is arranged outside the storage tank (4); The heating device is capable of heating the storage tank (4) and controlling the pressure inside the storage tank (4).

8. The composite propulsion device based on the electron cyclotron resonance effect according to claim 2, characterized in that: An insulating pipeline is provided on the working fluid supply pipeline, and the insulating pipeline is used to isolate the voltage between the ionization chamber (1) and the storage tank (4); The working medium supply pipeline is provided with a throttle valve, and the throttle valve can control the flow rate of the working medium in the pipeline.

9. The composite propulsion device based on the electron cyclotron resonance effect according to claim 1, characterized in that: A heat exchanger (6) is provided between the storage tank (4) and the microwave source (3); The waste heat generated by the microwave source (3) can be transferred to the storage tank (4) through the heat exchanger (6).

10. The composite propulsion device based on electron cyclotron resonance effect according to claim 1, characterized in that: By changing the gas supply flow rate and microwave power in the ionization chamber (1), the composite propulsion device can be switched between an electric propulsion mode and a gas propulsion mode; When the gas supply flow rate is low and the microwave power is high, the composite propulsion device operates in an electric propulsion mode; When the gas supply flow rate is high, the compound propulsion device operates in the gas propulsion mode.

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