Open magnetic plasma thermoelectric conversion and kinetic energy conversion regulation device

Abstract

The application provides an open magnetic plasma thermoelectric conversion and kinetic energy conversion regulation device, which is composed of a magnetic plasma channel, a front-stage regulation coil, a plasma probe group, a magnet array, a thermoelectric conversion channel, a magnetic shield plate, an acceleration coil and a rear-stage regulation coil. The device generates a dynamic magnetic field to transport high-temperature magnetic plasma through an excitation coil array, carries out plasma distribution regulation based on the measurement results of the plasma probe, obtains a magnetic plasma induced electromotive force by using a horizontal magnetic field and a tilted electrode, and realizes thermoelectric conversion with the magnetic plasma as a working medium. Meanwhile, the high-temperature magnetic plasma is accelerated by using a magnetic mirror structure to realize secondary conversion of the magnetic plasma heat energy, and a high-speed plasma jet flow is generated to produce a reaction thrust, thereby providing space power for a spacecraft. The application has the advantages of simple thermoelectric conversion process, no mechanical pump conveying structure and integration of the thermoelectric conversion and the space propulsion device.

Description

Technical Field

[0001] This invention belongs to the field of space energy and plasma propulsion, specifically relating to an open magnetic plasma thermoelectric conversion and kinetic energy conversion control device. Background Technology

[0002] In space activities, efficient space energy acquisition and advanced high-performance space propulsion technologies are essential prerequisites for diverse space exploration missions. With the increasing demand for large-scale spacecraft platforms and the deepening of deep space exploration missions, the problem of space power supply, which constrains space exploration, urgently needs to be solved. Chemical energy sources are suitable for spacecraft operating for short periods. Solar energy sources have advantages in near-Earth space, but their efficiency is low when used for deep space exploration, increasing the size and design complexity of spacecraft. Currently, solar energy sources have a high power-to-weight ratio, making it difficult to meet the demands of high-power space power. Therefore, space nuclear energy sources based on magnetic plasma thermoelectric conversion are currently the most promising implementation solution.

[0003] Furthermore, space electric propulsion technology based on plasma acceleration is one of the essential advanced technologies for future spacecraft. Traditional chemical propulsion has a low specific impulse, making it difficult to provide the high total impulse required for deep space exploration. Therefore, realizing the conversion of plasma thermal energy into kinetic energy based on magneto-plasma thermoelectric conversion technology is an ideal technical solution for future advanced spacecraft that combines efficient energy conversion and kinetic energy harvesting.

[0004] The existing related technologies have the following main drawbacks:

[0005] 1. The conversion process from nuclear heat to electrical energy is complex, and multiple heat exchange processes reduce the thermoelectric conversion efficiency.

[0006] 2. The ultra-high temperature plasma generated by nuclear thermal energy relies on mechanical delivery pumps, and the high temperature plasma causes severe sputtering and erosion of mechanical components.

[0007] 3. Traditional open-loop thermoelectric conversion systems directly discharge high-temperature working fluids, resulting in energy waste.

[0008] 4. The plasma propulsion device that is independently assembled in ordinary spacecraft needs to generate plasma by independent discharge, which results in system redundancy, low upper limit of plasma temperature, and limited propulsion performance. Summary of the Invention

[0009] The purpose of this invention is to provide an open magnetic plasma thermoelectric conversion and kinetic energy conversion control device, providing a device scheme for space energy acquisition and propulsion kinetic energy generation for future deep space exploration activities of spacecraft.

[0010] In a first aspect, the space energy acquisition and propulsion kinetic energy generation device provided by the present invention includes: a magnetic plasma channel, a pre-stage control coil, and a plasma probe group;

[0011] The magnetic plasma channel is equipped with axially arranged excitation coil groups. The excitation coil groups are axially independent of each other, and the magnetic field they generate is in the axial direction along the excitation coil group to prevent radial transport of magnetic plasma from sputtering and corroding the magnetic plasma channel wall. The axial direction is the direction of the coil center axis of symmetry, and the radial direction is the direction perpendicular to the center axis.

[0012] The magnetic plasma channel is provided with a ceramic channel wall wrapped around the outside of the excitation coil group, and forms a central circular cross-section channel for magnetic plasma to pass through. The circular cross-section channel can avoid the problem of excessive local heat load that exists in the traditional square cross-section channel.

[0013] The walls of the magnetic plasma channel are made of BN ceramic and have a gap between them and the excitation coil assembly;

[0014] The plasma probe group is located on the inner wall of the magnetic plasma channel to measure the magnetic plasma density, assess the degree of non-uniformity of plasma distribution, and provide feedback parameters for the pre-stage control coil.

[0015] The pre-stage control coil is configured as a coaxial multi-turn coil, and the central axis of symmetry of the pre-stage control coil is perpendicular to the central axis of symmetry of the magnetic plasma channel. The pre-stage control coil constrains the plasma in the magnetic plasma channel and controls the uniformity by relying on the measurement results of the plasma probe group.

[0016] In an optional implementation,

[0017] The excitation coil has 16 groups in the axial direction, and each group of coils is divided into 4 turns in the radial direction. The 16 groups of coils are connected and disconnected in sequence from left to right and cycle to generate a dynamic magnetic field that moves from left to right, driving the axial transport of plasma.

[0018] There are four pre-stage control coils, and the magnetic field generated by the coils all points towards the central axis of symmetry of the magnetic plasma channel.

[0019] The plasma probe group has four probes, which are located downstream of the pre-stage control coil and are arranged in a symmetrical structure, pointing towards the central axis of symmetry of the magnetic plasma channel.

[0020] Secondly, the space energy acquisition and propulsion kinetic energy generation device provided by the present invention includes: a magnet array and a thermoelectric conversion channel;

[0021] The thermoelectric conversion channel has a circular cross-section, and the section through the central axis of symmetry is an arc-shaped expansion section to conform to the radial diffusion trend of high-temperature magnetic plasma and reduce the sputtering corrosion of the thermoelectric conversion channel by plasma.

[0022] The thermoelectric conversion channel is provided with an inclined annular tungsten metal electrode, and an annular ceramic insulating gasket is provided between the electrodes.

[0023] The magnet array is configured as rectangular permanent magnet poles placed opposite each other on both sides of the thermoelectric conversion channel. The magnet array is placed along the wall of the expanded thermoelectric conversion channel and a gap is provided between it and the thermoelectric conversion channel. The height of the magnet array gradually increases along the central axis of symmetry of the thermoelectric conversion channel to completely cover the height of the thermoelectric conversion channel, so that the magnetic plasma in the thermoelectric conversion channel is always in a magnetic field.

[0024] In an optional implementation,

[0025] The ring-shaped tungsten metal electrode is provided with 18 electrodes, the ceramic insulating pad is provided with 17 electrodes, and the tilt angle is set to 35°.

[0026] The magnet array is arranged in a pattern of (1+2+2+3+3+3)*2=28 blocks;

[0027] Thirdly, the space energy acquisition and propulsion kinetic energy generation device provided by the present invention includes: a magnetic baffle plate, an acceleration coil, and a subsequent control coil;

[0028] The accelerating coil is provided with a coaxial multi-turn coil and is covered with a ceramic shell.

[0029] The magnetic baffle is configured as an L-shaped cross-section ring, with its lower edge embedded inside the accelerating coil and a gap provided between it and the outer wall of the accelerating coil.

[0030] The subsequent control coil is configured as an arc-shaped variable cross-section multi-turn coil, and the central axis of symmetry of its arc surface coincides with the central axis of symmetry of the acceleration coil.

[0031] In an optional implementation,

[0032] The post-stage control coil is set up with four symmetrically placed coils. When each coil is energized, the magnetic field points to the central axis of symmetry of the acceleration coil.

[0033] Fourthly, the space energy acquisition and propulsion kinetic energy generation device provided by the present invention includes: a thermoelectric conversion circuit, a front-stage transport circuit, and a rear-stage acceleration circuit;

[0034] The working steps of the thermoelectric conversion circuit are as follows:

[0035] The magnetic plasma enters the thermoelectric conversion channel from the inlet. Under the magnetic field of the magnet array, it is driven by the Lorentz force to generate an induced potential on the tungsten metal electrode. The potentials of the inlet and outlet electrodes of the thermoelectric conversion channel are extracted respectively, serving as the positive and negative poles of the thermoelectric conversion circuit, providing a potential difference for the load R, thereby realizing the conversion of the thermal energy of the magnetic plasma into electrical energy.

[0036] The working steps of the front-end transport circuit are as follows:

[0037] The positive and negative terminals of the power supply are led out from the thermoelectric conversion circuit and connected to four sets of pre-stage control coils and the magnetic plasma channel, respectively. The four sets of pre-stage control coils work independently to achieve magnetic plasma uniformity adjustment. The 16 sets of coils in the magnetic plasma channel work independently and cyclically in sequence to achieve radial constraint and axial transport of magnetic plasma.

[0038] The working steps of the subsequent acceleration circuit are as follows:

[0039] The positive and negative terminals of the power supply are led out from the thermoelectric conversion circuit and connected to the acceleration coil and four sets of post-stage control coils, respectively. The acceleration coil uses a single magnetic mirror and magnetic nozzle to achieve axial acceleration of the high-temperature magnetic plasma and generate kinetic thrust. The four sets of post-stage control coils work independently to achieve radial constraint of the accelerated magnetic plasma jet and control the direction of the generated kinetic thrust.

[0040] By combining the above processes, this device can realize the conversion of high-temperature magnetic plasma thermal energy into electrical energy and kinetic thrust.

[0041] The beneficial effects of this invention compared to the prior art are as follows:

[0042] 1. The conversion process from nuclear heat to electricity is simple, which improves the thermoelectric conversion efficiency.

[0043] 2. High-temperature magnetic plasma is driven by the circulating magnetic field within the magnetic plasma channel, replacing the traditional mechanical delivery pump and avoiding the sputtering erosion of mechanical components by the high-temperature plasma.

[0044] 3. To enable the reuse of high-temperature working fluid in open thermoelectric conversion systems, generating kinetic energy to provide space propulsion for spacecraft and avoid energy waste.

[0045] 4. This invention integrates the magnetic plasma thermoelectric conversion device with the spacecraft plasma propulsion device, avoiding energy waste and system redundancy caused by the re-discharge process of a separately set plasma propulsion device. At the same time, compared with a separately set plasma propulsion device, the magnetic plasma in this invention has a higher temperature and higher propulsion performance. Attached Figure Description

[0046] Figure 1 An exploded view of the structure of the open magnetic plasma thermoelectric conversion and kinetic energy conversion control device provided in an embodiment of the present invention.

[0047] Figure 2 This is a cross-sectional view of the open magnetic plasma thermoelectric conversion and kinetic energy conversion control device provided in an embodiment of the present invention.

[0048] Figure 3 The schematic diagram of the magnetic plasma channel structure and excitation coil drive circuit in the open magnetic plasma thermoelectric conversion and kinetic energy conversion control device provided in the embodiment of the present invention.

[0049] Figure 4 The thermoelectric conversion channel structure and thermoelectric conversion principle diagram in the open magnetic plasma thermoelectric conversion and kinetic energy conversion control device provided in the embodiments of the present invention.

[0050] Figure 5 The diagram shows the structure of the magnetic baffle and accelerating coil in the open magnetic plasma thermoelectric conversion and kinetic energy conversion control device provided in the embodiment of the present invention.

[0051] Figure 6 The circuit diagram of the open magnetic plasma thermoelectric conversion and kinetic energy conversion control device provided in the embodiment of the present invention.

[0052] The labels in the diagram are explained as follows:

[0053] 1. Magnetic plasma channel; 2. Pre-stage control coil; 3. Plasma probe assembly; 4. Magnet array.

[0054] 5. Thermoelectric conversion channel; 6. Magnetic baffle; 7. Accelerating coil; 8. Post-stage control coil.

[0055] 101-119, Excitation Coil 501, Tungsten Electrode 502, Ceramic Insulating Gasket Detailed Implementation

[0056] This invention proposes an open-type magnetic plasma thermoelectric conversion and kinetic energy conversion control device. The technical solution of this invention will be clearly and completely described below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are for illustration and explanation only and are not intended to limit the invention.

[0057] In the description of this invention, it should be noted that the terms "upstream", "downstream", "left side", "right side", "vertical", "horizontal", "inner", "outer", etc., which indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, are only for the convenience of describing this invention, and are not intended to indicate or imply a specific orientation that the device or structure referred to must have, and therefore should not be construed as a limitation of this invention.

[0058] like Figure 1 As shown, the open magnetic plasma thermoelectric conversion and kinetic energy conversion control device provided in this embodiment includes, from upstream to downstream: magnetic plasma channel 1, pre-stage control coil 2, plasma probe group 3, magnet array 4, thermoelectric conversion channel 5, magnetic baffle plate 6, acceleration coil 7, and post-stage control coil 8.

[0059] The specific working steps are as follows:

[0060] Step 1: High-temperature magnetic plasma with a temperature above 4000K enters magnetic plasma channel 1 from the left; as... Figure 2 and Figure 3 As shown, the 16 sets of excitation coils 101-116 inside the magnetic plasma channel 1 are sequentially switched on and off from the left side, forming a loop. Each set of coils generates an axial magnetic field to drive the high-temperature magnetic plasma entering the magnetic plasma channel 1 to move to the right, realizing the axial transport of the high-temperature plasma; at the same time, the axial magnetic field constrains the radial movement of the high-temperature magnetic plasma, avoiding the interaction between the high-temperature magnetic plasma and the inner wall of the magnetic plasma channel 1, and reducing the corrosion failure of the transport channel components;

[0061] Step 2: High-temperature magnetic plasma is transported by magnetic plasma channel 1 to the pre-stage control coil 2. The plasma probe group 3 arranged inside the transport channel measures the plasma density and obtains the non-uniformity of the high-temperature magnetic plasma density distribution in the channel. The pre-stage control coil 2 is energized sequentially according to the non-uniformity of the plasma density distribution measured by the plasma probe group to radially constrain the high-temperature magnetic plasma in the channel. At the same time, the diagnostic results of the plasma probe group 3 are used again as feedback parameters to regulate the uniformity of the high-temperature magnetic plasma density in the channel, ensuring the uniformity of the high-temperature magnetic plasma jet at the inlet of the downstream thermoelectric conversion channel 5.

[0062] Step 3: The uniformly distributed high-temperature magnetic plasma enters the thermoelectric conversion channel 5 and is subjected to the Lorentz force in the horizontal magnetic field formed by the vertically placed magnet array 4, which induces an electromotive force between the tungsten electrodes 501. The electrode potential is then led out to the load end, thereby realizing the conversion of magnetic plasma thermal energy into electrical energy.

[0063] Step 4: The temperature of the magnetic plasma decreases after passing through the thermoelectric conversion channel 5, but remains higher than that of ordinary low-temperature plasma. After exiting the thermoelectric conversion channel 5, the magnetic plasma enters the accelerating coil 7 equipped with a magnetic baffle plate 6. The magnetic baffle plate 6 is embedded upstream of the accelerating coil 7, guiding the magnetic field lines on the left side of the accelerating coil 7 radially outward, preventing the formation of a reverse magnetic mirror magnetic field on the left side of the accelerating coil 7 from hindering the upstream magnetic plasma flow. After passing through the magnetic baffle plate 6, the magnetic plasma enters the single magnetic mirror structure magnetic field on the right side of the accelerating coil 7. Accelerated by the magnetic mirror structure, its thermal energy is further converted into plasma kinetic energy, achieving plasma acceleration and generating a reaction thrust.

[0064] Step 5: The subsequent control coil 8 radially controls the plasma jet, controlling the direction of the plasma jet reaction thrust, and providing space power for autonomous directional control of the spacecraft.

[0065] The high-temperature magnetic plasma should be generated by a nuclear reactor or electric heater, pre-ionization device, etc. The high-temperature magnetic plasma generating device should be placed upstream of the magnetic plasma channel, but the high-temperature magnetic plasma generating device is not the subject of this invention.

Claims

1. An open-type magnetic plasma thermoelectric conversion and kinetic energy conversion control device, characterized in that: The device consists of a magnetic plasma channel, a pre-stage control coil, a plasma probe group, a magnet array, a thermoelectric conversion channel, a magnetic baffle, an acceleration coil, and a post-stage control coil. The magnetic plasma channel, used to confine and transport high-temperature magnetic plasma, comprises 16 axially arranged and independent excitation coils. These coils are sequentially switched on and off, generating an axial dynamic magnetic field to drive the axial movement of the magnetic plasma. The excitation coils are encased in BN ceramic material with gaps, forming a circular cross-section channel to avoid excessive localized heat loads common in traditional square cross-sections and protect the excitation coils from high-temperature damage. A plasma probe group measures the uniformity of the magnetic plasma distribution within the channel. A pre-stage control coil regulates the uniformity of the magnetic plasma distribution. A magnet array forms a specific magnetic field structure. A thermoelectric conversion channel, located in the center of the magnet array, converts the thermal energy of the high-temperature magnetic plasma. The thermoelectric conversion channel is circular in cross-section, with an arc-shaped expanded section. The electrodes of the thermoelectric conversion channel are 35° inclined annular tungsten metal electrodes, with BN ceramic insulating pads placed between the electrodes. The magnetic baffle is an L-shaped annular structure embedded inside the acceleration coil, blocking the magnetic field on the left side of the acceleration coil from extending upstream. This forms a single magnetic mirror structure on the right side of the acceleration coil, which is used to constrain the magnetic field on one side of the acceleration coil and avoid generating transport resistance to the upstream magnetic plasma. The acceleration coil is used to generate the magnetic field of the magnetic mirror structure and accelerate the magnetic plasma to form a magnetic plasma jet, which generates reaction thrust. The subsequent control coil is used to radially constrain the magnetic plasma jet and control the direction of the spacecraft's thrust.

2. The open-type magnetic plasma thermoelectric conversion and kinetic energy conversion control device according to claim 1, characterized in that: Four sets of plasma probes are symmetrically placed on the inner wall of the magnetic plasma channel to measure the uniformity of plasma distribution. Four sets of pre-stage control coils are set downstream of the excitation coil in the magnetic plasma channel and upstream of the plasma probe sets. The magnetic field generated points towards the axis of symmetry of the magnetic plasma channel to regulate the uniformity of magnetic plasma distribution.

3. The open-type magnetic plasma thermoelectric conversion and kinetic energy conversion control device according to claim 1, characterized in that: The horizontal magnetic field of the thermoelectric conversion channel is generated by a vertically placed array of permanent magnets. The permanent magnets are 250mm×100mm×30mm and 200mm×100mm×30mm in size, and are made of ferrite or samarium cobalt alloy.

4. The open-type magnetic plasma thermoelectric conversion and kinetic energy conversion control device according to claim 1, characterized in that: The subsequent control coil is an arc-shaped variable cross-section multi-turn coil, with the arc surface placed coaxially with the acceleration coil.

5. A method for realizing the function of the open magnetic plasma thermoelectric conversion and kinetic energy conversion control device as described in claim 1, characterized in that: Includes the following steps: Step 1: High-temperature magnetic plasma with a temperature higher than 4000K enters the magnetic plasma channel from the left. 16 sets of excitation coils are turned on and off in sequence from the left to generate an axial magnetic field that drives the high-temperature magnetic plasma to move to the right and transport it to the thermoelectric conversion channel. Step 2: The plasma probe group measures the uniformity of plasma distribution, providing input and feedback parameters for the pre-stage control coil. Based on this, the pre-stage control coil radially constrains the high-temperature magnetic plasma in the channel to ensure the uniformity of the high-temperature magnetic plasma jet distribution. Step 3: The high-temperature magnetic plasma enters the thermoelectric conversion channel and is constrained by the horizontal magnetic field to form an induced potential between the tungsten electrodes, providing power to the load and simultaneously providing power to the pre-stage control circuit and the post-stage acceleration circuit. Step 4: The magnetic plasma enters the magnetic field of the single magnetic mirror structure generated by the accelerating coil, and is accelerated by the magnetic field to form a high-speed plasma jet, which generates a reaction thrust. Step 5: The subsequent control coils radially control the plasma jet according to the spacecraft's attitude and orbit control requirements, thereby controlling the direction of the plasma jet's reaction thrust.

6. The method for realizing the function of an open magnetic plasma thermoelectric conversion and kinetic energy conversion control device according to claim 5, characterized in that: High-temperature magnetic plasma generated by a nuclear reactor and an electric heater pre-ionization device is selected as the working fluid. The magnetic plasma with a temperature parameter higher than 4000K passes through the magnetic plasma channel, the thermoelectric conversion channel and the acceleration coil in sequence. No secondary ionization and working fluid heat exchange are required, so as to realize the efficient conversion of high-temperature magnetic plasma thermal energy into electrical energy and kinetic energy in an open loop structure.

7. The method for realizing the function of an open magnetic plasma thermoelectric conversion and kinetic energy conversion control device according to claim 5, characterized in that: The electrical energy required for the pre-stage control circuit and the post-stage acceleration circuit is provided by the thermoelectric conversion channel, achieving energy self-sufficiency.

Images