A closed asymmetric capacitor plasma acceleration propulsion module

Abstract

The present invention provides a closed asymmetric capacitor plasma acceleration propulsion module, which relates to the technical field of plasma thrusters and comprises an array shell and a high-voltage power supply. An insulating pressure-resistant shell is arranged on one side of the array shell, and a flow-guiding connection hose is arranged at the end of the array shell. In actual use, multiple modules can be connected in series by arranging the array shell and the high-voltage power supply, thereby improving the ion injection speed at the final output end. An aerospace vehicle equipped with such an ion thruster module can permanently sail on orbit without worrying about the exhaustion of propellant. At the same time, the enhancement and improvement of its thrust make it powerful. The high-voltage electrodes are arranged inside the engine, which increases the working safety and makes the Biefeld-Brown effect have practical engineering application value. The module can be used as a full-electric propulsion engine without carrying working fluid for spacecraft attitude adjustment, orbit change, orbit enhancement, etc.

Description

Technical Field

[0001] The present invention relates to the technical field of plasma thrusters, and in particular to a closed asymmetric capacitor plasma acceleration propulsion module. Background Art

[0002] Ion thrusters based on the Befeld-Brown effect are mostly open forms, such as simple levitation machines, MIT's ion-propelled aircraft, and the unlimited-fuel satellite low-altitude flight electric thrusters developed by the European Space Agency. The common advantages of these thrusters are: they do not need to consume traditional chemical propellants, and as long as there is electricity (from solar energy or nuclear power), they can generate thrust permanently, that is, they have a long endurance time, but their disadvantages are: due to their small thrust and low efficiency, they are not suitable for large-scale engineering applications.

[0003] Their common feature is that their most basic thruster modules are asymmetric capacitors based on the Befeld-Brown effect, which ionize and accelerate ambient gases or particles to generate thrust. This is because ordinary simple levitation machines and MIT's ion-propelled aircraft all use asymmetric capacitor layouts in open environments, resulting in low propulsion efficiency. Although the unlimited fuel satellite low-altitude flight electric thruster developed by the European Space Agency has a closed shell that allows ions to be accelerated in a fluid channel, the space around its small electrode is large, which is prone to backflow and pressure relief. The forward positive pressure in the large thrust generating area closest to the small electrode is not fully utilized due to its structural design. Summary of the invention

[0004] The purpose of the present invention is to solve the shortcomings of the prior art and to propose a closed asymmetric capacitor plasma acceleration propulsion module.

[0005] In order to achieve the above-mentioned purpose, the present invention adopts the following technical scheme: a closed asymmetric capacitor plasma acceleration propulsion module, including an array shell and a high-voltage power supply, an insulating pressure-resistant shell is arranged on one side of the array shell, a flow-conducting connecting hose is arranged at the end of the array shell, a hollow small-hole discharge pipe is arranged between the insulating pressure-resistant shells, a discharge front end is arranged at one end of the hollow small-hole discharge pipe, an array electrode is arranged inside the array shell, the output end of the high-voltage power supply is electrically connected to the input end of the safety discharge resistor and the voltage-stabilizing and current-limiting capacitor, and a grounding wire is arranged on the surface of the insulating pressure-resistant shell.

[0006] In order to achieve different effects, the present invention has improvements in that the array electrode is divided into a spherical array electrode or an ellipsoidal array electrode, and the spherical array electrode is a honeycomb surface array, and the ellipsoidal array electrode is composed of a plurality of concentric conical surface arrays and supporting ribs.

[0007] In order to achieve different effects, the present invention has been improved in that the discharge front end of the hollow small hole type discharge pipe is divided into a sawtooth shape, and the front end of the sawtooth shape is a sharp corner 11, and the root of the sawtooth shape is a rounded groove 12.

[0008] In order to improve the quality of the insulating pressure-resistant shell, the present invention has the following improvements: the insulating pressure-resistant shell needs to be made of materials that have high pressure resistance and high temperature resistance, and can withstand plasma corrosion and the impact of high-speed plasma flow in the channel.

[0009] Compared with the prior art, the advantages and positive effects of the present invention are:

[0010] In the present invention, during actual use, by providing an array shell and a high-voltage power supply, multiple modules can be connected in series, and the ion injection speed at the final output end can be increased. An aerospace vehicle equipped with such an ion thruster module can permanently sail in orbit without worrying about the exhaustion of propellant. At the same time, the increase and improvement of its thrust make it powerful. The high-voltage electrodes are arranged inside the engine, which increases the working safety, so that the Biefeld-Brown effect has practical engineering application value, and can be used as a full-electric thrust engine that does not require carrying working fluid for spacecraft attitude adjustment, orbit change, orbit enhancement, etc. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Figure 1 The present invention provides a schematic diagram of the overall structure of a closed asymmetric capacitor plasma acceleration propulsion module;

[0012] Figure 2 The present invention proposes a closed asymmetric capacitor plasma acceleration propulsion module in which the surface array electrode is composed of a plurality of concentric conical surface arrays and supporting ribs;

[0013] Figure 3 The present invention proposes a closed asymmetric capacitor plasma acceleration propulsion module with a hollow small hole discharge pipe electrode structure;

[0014] Figure 4 The present invention proposes a closed asymmetric capacitor plasma acceleration propulsion module in which the surface array electrodes are in the form of a honeycomb surface array.

[0015] Legend:

[0016] 1. Hollow small hole discharge pipe; 2. Grounding wire; 3. Array electrode; 4. Safety discharge resistor; 5. Voltage-stabilizing and current-limiting capacitor; 6. High-voltage power supply; 7. Discharge front end; 8. Diversion connecting hose; 9. Insulating and pressure-resistant shell; 10. Array shell; 11. Sharp corner; 12. Rounded groove; 13. Support rib plate; 14. Honeycomb surface array. DETAILED DESCRIPTION

[0017] In order to more clearly understand the above-mentioned purpose, features and advantages of the present invention, the present invention is further described below in conjunction with the accompanying drawings and embodiments. It should be noted that the embodiments of the present application and the features in the embodiments can be combined with each other without conflict.

[0018] In the following description, many specific details are set forth to facilitate a full understanding of the present invention. However, the present invention may also be implemented in other ways than those described herein. Therefore, the present invention is not limited to the specific embodiments of the following disclosure.

[0019] For example, see Figure 1-4 The present invention provides a technical solution: a closed asymmetric capacitor plasma acceleration propulsion module, including an array shell 10 and a high-voltage power supply 6, an insulating pressure-resistant shell 9 is arranged on one side of the array shell 10, a flow-conducting connection hose 8 is arranged at the end of the array shell 10, a hollow small-hole discharge pipe 1 is arranged between the insulating pressure-resistant shells 9, a discharge front end 7 is arranged at one end of the hollow small-hole discharge pipe 1, an array electrode 3 is arranged inside the array shell 10, the output end of the high-voltage power supply 6 is electrically connected to the input end of the safety discharge resistor 4 and the voltage-stabilizing current-limiting capacitor 5, and the insulating pressure-resistant shell 9 is provided with a discharge pipe 1. A grounding wire 2 is provided on the surface of the shell 9, the array electrode 3 is divided into a spherical array electrode 3 or an ellipsoidal array electrode 3, and the spherical array electrode 3 is a honeycomb array 14, the ellipsoidal array electrode 3 is composed of a plurality of concentric conical arrays and a supporting rib plate 13, the discharge front end 7 of the hollow small hole discharge pipe 1 is serrated, and the front end of the serrated shape is a sharp corner 11, and the root of the serrated shape is a rounded groove 12, and the insulating pressure-resistant shell 9 needs to be made of a material with high pressure resistance and high temperature resistance, and can withstand plasma corrosion, and resist the impact of high-speed plasma flow in the channel.

[0020] Attached Figure 1 The basic cross-sectional structure of the enclosed asymmetric capacitor plasma accelerator thruster module of the present invention is given. The small electrode plate of the asymmetric capacitor is composed of a hollow small hole discharge pipe 1, and the large electrode plate is composed of an array electrode 3. The discharge front end 7 of the hollow small hole discharge pipe 1 is serrated, the front end of the serrated shape is a sharp corner 11, and the root of the serrated shape is a rounded groove 12. The hollow small hole discharge pipe 1 and the large electrode plate are connected and sealed by the array electrode 3 through an insulating pressure-resistant shell 9. The array electrode 3 is installed inside the array surface shell 10, and the tail of the array surface shell 10 is connected to a guide connection hose 8. The high-voltage circuit connecting the two electrodes is composed of a high-voltage power supply 6, a voltage-stabilizing and current-limiting capacitor 5, a safety discharge resistor 4, and a grounding wire 2. The grounding wire 2 can be a virtual ground.

[0021] The ion acceleration channel or ion cavity of this closed asymmetric capacitor plasma acceleration thruster module is isolated and closed from the external environment, and the external environment is isolated from the high-energy and high-speed ions inside mainly through the following components: hollow small hole discharge pipe 1 electrode, insulating pressure-resistant shell 9, array shell 10, and bendable diversion connecting hose 8.

[0022] Through the flow-guiding connecting hose 8, multiple such plasma accelerator thruster modules can be connected in series end to end, and the charged particles inside can be energized step by step to increase their internal pressure and kinetic energy, thereby increasing the pressure and speed of the ion flow ejected by the last-stage plasma accelerator thruster module. The connection of the flow-guiding connecting hose 8 allows the modules in series to be bent and their positions to be flexibly arranged, which facilitates the high-thrust electric propulsion engine system composed of multiple thruster modules and enables it to be flexibly installed and arranged on aerospace vehicles.

[0023] The place where the thrust intensity generated by the Befeld-Brown effect composed of an asymmetric capacitor is the largest is near the small face positive plate, that is, near the hollow small hole type discharge pipe 1 in this embodiment. Through the structural setting of this patent, the thrust can be completely transmitted to the nozzle and channel behind through the sealed channel without causing the ion flow pressure discharge and backflow under the traditional open environment or the overly large channel structure. The ion channel composed of the array shell 10, the hollow small hole type discharge pipe 1, and other components has an inner wall designed to be streamlined, which conforms to the minimum flow resistance principle of fluid mechanics, so that the ion flow in the channel can pass through the channel with the minimum resistance, and then through the multi-module series step-by-step acceleration measures, the ion flow rate and pressure ejected from the tail nozzle of the final acceleration module can be accumulated to the maximum, thereby generating a strong fluid ejection rate and thrust output.

[0024] Therefore, the plasma thrust module of this structure and the plasma propulsion engine composed of it have the characteristics of large thrust. In addition, when flying in the space environment at a speed above the first cosmic speed of 7.9m / s, the high-speed ramjet effect of the windward surface can greatly increase the concentration of inhaled particles, which is much higher than the particle concentration in the static space environment. Therefore, the number of particles inhaled per second is much greater, which further increases the available ionized particulate material in the propulsion process and also increases its thrust output.

[0025] This high-thrust plasma thruster composed of an asymmetric capacitor in a closed cavity has the following advantages: high thrust, no need to consume its own working fluid, and it can achieve permanent endurance by simply supplying it with electricity, without having to worry about running out of the chemical propellant it carries. Electricity can be supplied by solar panels or small nuclear power, and its range is almost infinite. Therefore, it can be said that with this high-thrust electric propulsion module that does not consume its own working fluid, the dream of permanently controlling spacecraft in orbit and interstellar navigation can be turned into reality.

[0026] Attached Figure 2 A detailed structural form of the large electrode of the closed asymmetric capacitor plasma acceleration thruster module of the present invention is given. This large electrode is composed of an ellipsoidal array electrode 3. The ellipsoidal array electrode 3 is manifested as a honeycomb surface array 14 in a three-dimensional structure. The material is metal and has good conductivity. The honeycomb surface array 14 has a large surface area, and the electric field strength near it is much smaller than that near the small electrode hollow small hole discharge pipe 1. It and the small electrode together form an asymmetric capacitor to produce the Befeld-Brown effect. The small electrode is responsible for ionizing the particles sucked in through the pipe and making them charged and turned into ions. The honeycomb-shaped large electrode 18 is responsible for generating an electric field in space, pulling the charged ions to move toward it, applying kinetic energy, and generating thrust at the same time. The energized particle flow can pass through the multiple small holes of the honeycomb and pass through the ellipsoidal surface of the large electrode at high speed, thereby generating a backward high-speed particle jet.

[0027] Attached Figure 3 A detailed structural form of the large electrode plate of the closed asymmetric capacitor plasma acceleration thruster module of the present invention is given. The large electrode plate is composed of a spherical array electrode 3. The spherical array electrode 3 is manifested as a concentric cone electrode plate and a supporting rib plate 13 in a three-dimensional structure. The concentric cone electrode plate has a large surface area, and the electric field strength near it is much smaller than that near the small electrode hollow small hole discharge pipe 1. It and the small electrode together constitute an asymmetric capacitor to produce the Befeld-Brown effect. The small electrode is responsible for ionizing the particles sucked in through the pipe and making them charged and turned into ions. The concentric cone electrode plate is responsible for generating an electric field in space, pulling the charged ions to move toward it, applying kinetic energy, and generating thrust at the same time. The energized particle flow can pass through the multiple gaps of the concentric cones and pass through the spherical surface of the large electrode plate at high speed, thereby generating a backward high-speed particle jet.

[0028] Attached Figure 4A detailed structural form of the discharge small electrode of the closed asymmetric capacitor plasma acceleration thruster module of the present invention is given. This small electrode is composed of a hollow small hole discharge pipe 1, and its discharge front end 7 is sawtooth-shaped, the sawtooth front end is a sharp corner 11, and the sawtooth root is a rounded groove 12. The sawtooth front end is a sharp corner 11, which is more conducive to plasma discharge. Since the electric field intensity near the tip is very high, it is more conducive to local discharge and corona generation, and more charges will be released into the surrounding space, which can better ionize the particulate medium sucked in. The sawtooth root is Figure 2 The rounded groove 12 is more conducive to transferring the negative pressure suction force generated near the tip to the inside of the hollow small hole discharge pipe 1, so as to absorb more particulate medium from the inside and avoid pressure reflux discharge caused by absorbing too many particles from the outside of the pipe wall.

[0029] Working principle: by setting the array shell 10 and the high-voltage power supply 6, an ion channel (cavity) sealed from the external environment is designed, so that the inhaled air (or other forms of environmental particles) are ionized at the outlet of the hollow pinhole discharge pipe 1 and become charged ions. Under the action of the high-voltage electric field, the charged ions are accelerated and pushed toward the spherical or ellipsoidal array. When the ions hit the spherical array, they exchange charge with the array surface to become neutral particles, and fly out of the bipolar plate space at high speed from the space in the array gap. With the help of the environmental gas medium and its own high speed, it is compressed and encrypted, and then sucked into the acceleration channel (cavity) of the engine thruster module, and then ejected after being accelerated by the electric field, thereby generating thrust output. At the same time, it does not consume its own limited working fluid fuel, so its range is almost infinite. Therefore, it is expected that with the help of engineering practical innovation and improvement of this thruster, the spacecraft can gradually realize permanent orbital navigation without orbital decay, and it can also give birth to future transportation tools for humans to carry out long-term and long-distance interstellar navigation.

[0030] The above description is only a preferred embodiment of the present invention and does not limit the present invention in other forms. Any technician familiar with the profession may use the technical content disclosed above to change or modify it into an equivalent embodiment with equivalent changes and apply it to other fields. However, any simple modification, equivalent change and modification made to the above embodiment based on the technical essence of the present invention without departing from the content of the technical solution of the present invention still falls within the protection scope of the technical solution of the present invention.

Claims

1. A closed asymmetric capacitor plasma acceleration propulsion module, comprising a front shell (10) and a high voltage power supply (6), characterized in that: An insulating pressure-resistant shell (9) is provided on one side of the array surface shell (10), a flow-conducting connection hose (8) is provided at the end of the array surface shell (10), a hollow small-hole discharge pipe (1) is provided between the insulating pressure-resistant shells (9), a discharge front end (7) is provided at one end of the hollow small-hole discharge pipe (1), an array electrode (3) is provided inside the array surface shell (10), the output end of the high-voltage power supply (6) is electrically connected to the input end of the safety discharge resistor (4) and the voltage-stabilizing current-limiting capacitor (5), a grounding wire (2) is provided on the surface of the insulating pressure-resistant shell (9), the array electrode (3) is divided into a spherical array electrode (3) or an ellipsoidal array electrode (3), and the spherical array electrode (3) is a honeycomb surface array (14), and the ellipsoidal array electrode (3) is composed of a plurality of concentric conical surface arrays and a supporting rib plate (13).

2. The enclosed asymmetric capacitor plasma acceleration propulsion module according to claim 1, characterized in that: The discharge front end (7) of the hollow small hole type discharge pipe (1) is sawtooth shaped, the front end of the sawtooth is a sharp corner (11), and the root of the sawtooth is a rounded groove (12).

3. The enclosed asymmetric capacitor plasma acceleration propulsion module according to claim 1, characterized in that: The insulating pressure-resistant shell (9) needs to be made of a material that has high pressure and high temperature resistance, and is able to withstand plasma corrosion and the impact of high-speed plasma flow in the channel.

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