Open type magnetic plasma thermoelectric conversion and kinetic energy conversion regulation and control device

Abstract

The invention provides an open type magnetic plasma thermoelectric conversion and kinetic energy conversion regulation and control device. The device is composed of a magnetic plasma channel, a front-stage regulation and control coil, a plasma probe set, a magnet array, a thermoelectric conversion channel, a magnetic baffle, an acceleration coil and a rear-stage regulation and control coil. According to the device, a dynamic magnetic field is generated through an excitation coil array to transport high-temperature magnetic plasma, plasma distribution regulation and control are carried out based on a plasma probe measurement result, magnetic plasma induced electromotive force is obtained through a horizontal magnetic field and an inclined electrode, and thermoelectric conversion with the magnetic plasma as a working medium is achieved. And meanwhile, a magnetic mirror structure is used for accelerating the high-temperature magnetic plasma, secondary conversion of heat energy of the magnetic plasma is achieved, the stroke high-speed plasma jet generates reaction thrust, and space power is provided for a spacecraft. The invention has the advantages of simple thermoelectric conversion process, no mechanical pump conveying structure, thermoelectric conversion and space propulsion device integration and the like.

Description

Technical Field

[0001] The present invention belongs to the field of space energy and plasma propulsion, and specifically relates to an open magnetic plasma thermoelectric conversion and kinetic energy conversion control device. Background Art

[0002] In space activities, efficient space energy acquisition and advanced high-performance space propulsion technology are necessary prerequisites for diversified space exploration missions. With the increasing demand for large-scale spacecraft platforms and the in-depth advancement of deep space exploration missions, the problem of space power supply that restricts space exploration needs to be solved urgently. Chemical energy power supply is suitable for spacecraft that work for a short time. Solar power supply has advantages in near-Earth space, but it is inefficient when used for deep space exploration, which will increase the scale and design difficulty of spacecraft. At present, the quality-power ratio of solar power supply is high, which is difficult to meet the demand for high-power space power supply. Therefore, space nuclear power supply based on magnetic plasma thermoelectric conversion is currently the most promising implementation plan.

[0003] In addition, space electric propulsion technology based on plasma acceleration is one of the advanced technologies that must be used in future spacecraft. Traditional chemical propulsion has low specific impulse and is difficult to provide the high total impulse required for deep space exploration. Therefore, the conversion of plasma thermal energy to kinetic energy based on magnetic plasma thermoelectric conversion technology is an ideal technical solution for future advanced spacecraft to achieve both efficient energy conversion and kinetic energy acquisition.

[0004] The existing related technologies mainly have the following defects:

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

[0006] 2. The ultra-high temperature plasma generated by nuclear heat relies on a mechanical delivery pump, and the high temperature plasma causes serious sputtering and erosion of mechanical parts.

[0007] 3. The traditional open thermoelectric conversion system directly discharges high-temperature working fluid, resulting in energy waste.

[0008] 4. The plasma propulsion device independently assembled on ordinary spacecraft needs to discharge independently to generate plasma, the system is redundant, the upper limit of plasma temperature is low, and the propulsion performance is limited. Summary of the invention

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

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

[0011] The magnetic plasma channel is provided with an axially arranged excitation coil group. The excitation coil groups are independent of each other in the axial direction, and the direction of the magnetic field generated by them is along the axial direction of the excitation coil group to prevent the radial transport of magnetic plasma from sputtering and corroding the wall of the magnetic plasma channel. The axial direction is the direction of the central symmetry axis of the coil, and the radial direction is the direction perpendicular to the central 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 the magnetic plasma to pass through. The circular cross-section channel can avoid the problem of excessive local heat load in the traditional square cross-section channel;

[0013] The magnetic plasma channel wall is made of BN ceramics, and a gap is left between the magnetic plasma channel wall and the excitation coil group;

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

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

[0016] In an alternative embodiment,

[0017] The excitation coils have 16 groups in the axial direction, each group of coils is divided into 4 turns in the radial direction, and the 16 groups of coils are connected and disconnected in sequence from left to right and circulate, generating a dynamic magnetic field moving from left to right to drive the axial transport of plasma;

[0018] There are four front-stage control coils, and the directions of the magnetic fields generated by the coils all point to the central symmetry axis of the magnetic plasma channel.

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

[0020] In a second aspect, the present invention provides a space energy acquisition and propulsion kinetic energy generation device, comprising: a magnet array and a thermoelectric conversion channel;

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

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

[0023] The magnet array is configured as rectangular permanent magnet poles placed relatively on both sides of the thermoelectric conversion channel, the magnet array is placed along the wall of the expansion type thermoelectric conversion channel, and a gap is provided between the magnet array and the thermoelectric conversion channel; the height of the magnet array gradually increases along the central symmetric axis 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 the magnetic field;

[0024] In an alternative embodiment,

[0025] There are 18 annular tungsten metal electrodes, 17 ceramic insulating pads, and the inclination angle is set to 35°;

[0026] The magnet array is arranged in an arrangement of (1+2+2+3+3+3)*2=28 pieces;

[0027] In a third aspect, the space energy acquisition and propulsion kinetic energy generation device provided by the present invention includes: a magnetic shielding plate, an acceleration coil and a rear-stage control coil;

[0028] The acceleration coil is provided with a coaxial multi-turn coil, which is covered with a ceramic shell;

[0029] The magnetic shielding plate is set as an L-shaped cross-section circular ring, the lower edge of which is embedded inside the acceleration coil, and a gap is set between the outer wall of the acceleration coil;

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

[0031] In an alternative embodiment,

[0032] The rear stage control coil is set to be 4 coils placed symmetrically, and the magnetic field of each coil points to the central symmetry axis of the acceleration coil after power is applied;

[0033] In a fourth aspect, the space energy acquisition and propulsion kinetic energy generation device provided by the present invention comprises: 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 entrance. Under the action of the magnetic field of the magnet array, the magnetic plasma is driven by the Lorentz force to generate an induced potential on the tungsten metal electrode. The potentials of the entrance electrode and the exit electrode of the thermoelectric conversion channel are respectively drawn out to serve as the positive and negative electrodes 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-stage transport circuit are as follows:

[0037] The positive and negative electrodes of the power supply are led out from the thermoelectric conversion circuit and connected to 4 groups of front-stage control coils and the magnetic plasma channel respectively; the 4 groups of front-stage control coils work independently to achieve the uniformity adjustment of the magnetic plasma; the 16 groups of coils in the magnetic plasma channel work independently and cyclically in turn to achieve radial confinement and axial transport of the magnetic plasma;

[0038] The working steps of the latter stage acceleration loop are as follows:

[0039] The positive and negative electrodes 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 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 confinement of the accelerated magnetic plasma jet and regulate the direction of the generated kinetic thrust;

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

[0041] Compared with the prior art, the present invention has the following beneficial effects:

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

[0043] 2. Rely on the circulating magnetic field in the magnetic plasma channel to drive the high-temperature magnetic plasma, replacing the traditional mechanical delivery pump to avoid the sputtering erosion of mechanical parts by high-temperature plasma.

[0044] 3. Realize the reuse of high-temperature working fluid in the open thermoelectric conversion system to generate kinetic energy to provide space power for spacecraft and avoid energy waste.

[0045] 4. The magnetic plasma thermoelectric conversion device is integrated with the spacecraft plasma propulsion device to avoid energy waste and system redundancy caused by the re-discharge process of the independently arranged plasma propulsion device; at the same time, compared with the independently arranged plasma propulsion device, the magnetic plasma in the present invention has a higher temperature and a higher propulsion performance. BRIEF DESCRIPTION OF THE DRAWINGS

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

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

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

[0050] Figure 5 A structural diagram of a magnetic shielding plate and an accelerating coil in an open magnetic plasma thermoelectric conversion and kinetic energy conversion control device provided in an embodiment of the present invention.

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

[0052] The numbers in the figure are explained as follows:

[0053] 1. Magnetic plasma channel 2. Front stage control coil 3. Plasma probe group 4. Magnet array

[0054] 5. Thermoelectric conversion channel 6. Magnetic shielding plate 7. Acceleration coil 8. Post-stage control coil

[0055] 101-119, excitation coil 501, tungsten electrode 502, ceramic insulating pad DETAILED DESCRIPTION

[0056] The present invention proposes an open magnetic plasma thermoelectric conversion and kinetic energy conversion control device. The technical solution of the present invention is clearly and completely described below in conjunction with the accompanying drawings. It should be understood that the specific implementation methods described herein are only used to illustrate and explain the present invention, and are not used to limit the present invention.

[0057] In the description of the present invention, it should be noted that terms such as “upstream”, “downstream”, “left side”, “right side”, “vertical”, “horizontal”, “inside” and “outside” indicating directions or positional relationships are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention, rather than indicating or implying a specific direction that the device or structure referred to must have, and therefore cannot be understood as a limitation on the present invention.

[0058] like Figure 1 As shown, the present embodiment provides an open magnetic plasma thermoelectric conversion and kinetic energy conversion control device, which includes, from upstream to downstream: a magnetic plasma channel 1, a front-stage control coil 2, a plasma probe group 3, a magnet array 4, a thermoelectric conversion channel 5, a magnetic shielding plate 6, an acceleration coil 7, and a rear-stage control coil 8.

[0059] The specific working steps are:

[0060] Step 1: High-temperature magnetic plasma with a temperature higher than 4000K enters magnetic plasma channel 1 from the left; Figure 2 and Figure 3 As shown, the 16 groups of excitation coils 101-116 inside the magnetic plasma channel 1 are connected and disconnected in sequence from the left side to form a cycle. Each group 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: The high-temperature magnetic plasma is transported to the front-stage control coil 2 by the magnetic plasma channel 1. The plasma probe group 3 arranged on the inner side of the transport channel measures the plasma density to obtain the non-uniformity of the high-temperature magnetic plasma density distribution in the channel. The front-stage control coil 2 is energized in turn 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 result of the plasma probe group 3 is used as a feedback parameter again to uniformly control the high-temperature magnetic plasma density in the channel to ensure the uniformity of the high-temperature magnetic plasma jet at the entrance 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 acted upon by the Lorentz force in the horizontal magnetic field formed by the vertically placed magnet array 4, forming an induced potential between the tungsten electrodes 501, and the electrode potential is led 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 passing through the thermoelectric conversion channel 5 decreases, but is still higher than that of ordinary low-temperature plasma. After being discharged from the thermoelectric conversion channel 5, the magnetic plasma enters the acceleration coil 7 equipped with a magnetic shielding plate 6. The magnetic shielding plate 6 is embedded in the upstream of the acceleration coil 7, and the magnetic flux lines on the left side of the acceleration coil 7 are radially directed outward to avoid the formation of a reverse magnetic mirror magnetic field on the left side of the acceleration coil 7 to generate resistance to the upstream magnetic plasma flow. After passing through the magnetic shielding plate 6, the magnetic plasma enters the single magnetic mirror structure magnetic field on the right side of the acceleration coil 7, and is accelerated by the magnetic mirror structure, further converting the thermal energy into plasma kinetic energy to achieve plasma acceleration and generate reaction thrust.

[0064] Step 5: The rear-stage control coil 8 performs radial control on the plasma jet to control the direction of the reaction thrust of the plasma jet, thereby providing the spacecraft with space power with autonomous direction control.

[0065] The high temperature magnetic plasma should be generated by a nuclear reactor or an electric heater, pre-ionization or other device. The high temperature magnetic plasma generating device should be placed upstream of the magnetic plasma channel, but the high temperature magnetic plasma generating device does not belong to the content of the present invention.

Claims

1. An open magnetic plasma thermoelectric conversion and kinetic energy conversion control device, characterized in that: The system consists of a magnetic plasma channel, a front-stage control coil, a plasma probe group, a magnet array, a thermoelectric conversion channel, a magnetic shield, an acceleration coil, and a back-stage control coil. Among them, the magnetic plasma channel is used to confine and transport high-temperature magnetic plasma; the plasma probe group is used to measure the uniformity of the magnetic plasma distribution in the magnetic plasma channel; the front-stage control coil is used to control the uniformity of the magnetic plasma distribution; the magnet array is used to form a magnetic field of a specific structure; the thermoelectric conversion channel is placed in the middle of the magnet array, which is used to convert the thermal energy of the high-temperature magnetic plasma into electrical energy; the magnetic shielding plate is used to confine the magnetic field on one side of the acceleration coil to avoid 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 and generate reaction thrust; the rear-stage control coil is used to radially constrain the magnetic plasma jet and control the thrust direction of the spacecraft.

2. An open magnetic plasma thermoelectric conversion and kinetic energy conversion control device according to claim 1, characterized in that: The magnetic plasma channel contains 16 groups of excitation coils arranged axially and independently of each other. The 16 groups of excitation coils are connected and disconnected in sequence to generate an axial dynamic magnetic field to drive the axial movement of the magnetic plasma. The excitation coil group is covered with a BN ceramic wall with gaps to form a circular cross-section channel, avoiding excessive local heat load in the traditional square cross-section and protecting the excitation coil from damage by high temperature.

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

4. The open magnetic plasma thermoelectric conversion and kinetic energy conversion control device according to claim 1, characterized in that: The cross-section of the thermoelectric conversion channel is circular, and the cut surface is an arc-shaped expansion section. The thermoelectric conversion channel electrodes are annular tungsten metal electrodes inclined at an angle of 35°, and BN ceramic insulating pads are arranged between the electrodes.

5. The open 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 permanent magnet array. The permanent magnet specifications are 250mm×100mm×30mm and 200mm×100mm×30mm, and the material is ferrite or samarium cobalt alloy.

6. The open magnetic plasma thermoelectric conversion and kinetic energy conversion control device according to claim 1, characterized in that: The magnetic shielding plate is an L-shaped cross-section circular ring structure, which is embedded in the inner side of the acceleration coil to block the magnetic field on the left side of the acceleration coil from extending upstream, thereby forming a single magnetic mirror structure on the right side of the acceleration coil.

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

8. A solution capable of realizing the functions of the open magnetic plasma thermoelectric conversion and kinetic energy conversion control device as described in claim 1, characterized in that: The steps include: Step 1: High-temperature magnetic plasma with a temperature higher than 4000K enters the magnetic plasma channel from the left, and 16 groups of excitation coils are connected and disconnected in sequence from the left, generating an axial magnetic field to drive 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 and provides input and feedback parameters for the front-stage control coil. The front-stage control coil uses this to radially constrain 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 electrical energy for the load, and also providing electrical energy for the front-stage control circuit and the rear-stage acceleration circuit. Step 4: The magnetic plasma enters the single magnetic mirror structure magnetic field generated by the acceleration coil, and is accelerated by the magnetic field to form a plasma high jet, generating a reaction thrust. Step 5: The rear-stage control coil radially controls the plasma jet according to the spacecraft's space attitude and orbit control requirements to control the direction of the plasma jet's reaction thrust.

9. An open magnetic plasma thermoelectric conversion and kinetic energy conversion control device according to claims 1 and 8, characterized in that: High-temperature magnetic plasma produced by pre-ionization devices such as nuclear reactors and electric heaters is selected as the fluid working fluid. The magnetic plasma with temperature parameters higher than 4000K passes through the magnetic plasma channel, thermoelectric conversion channel and acceleration coil successively. No secondary ionization and working fluid heat exchange are required, thus realizing the efficient conversion of high-temperature magnetic plasma thermal energy into electrical energy and kinetic energy in an open loop structure.

10. An open magnetic plasma thermoelectric conversion and kinetic energy conversion control device according to claims 1 and 8, characterized in that: The electric energy required by the first few control loops and the subsequent acceleration loop is provided by the thermoelectric conversion channel, achieving energy self-sufficiency.

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