CN111577564A - Single-stage composite double-pulse enhanced ionization type induction pulse plasma thruster - Google Patents
Single-stage composite double-pulse enhanced ionization type induction pulse plasma thruster Download PDFInfo
- Publication number
- CN111577564A CN111577564A CN202010608074.9A CN202010608074A CN111577564A CN 111577564 A CN111577564 A CN 111577564A CN 202010608074 A CN202010608074 A CN 202010608074A CN 111577564 A CN111577564 A CN 111577564A
- Authority
- CN
- China
- Prior art keywords
- pulse
- module
- induction coil
- induction
- wave modulation
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H1/00—Using plasma to produce a reactive propulsive thrust
- F03H1/0087—Electro-dynamic thrusters, e.g. pulsed plasma thrusters
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Plasma Technology (AREA)
Abstract
The invention discloses a single-stage composite double-pulse enhanced ionization type induction type pulse plasma thruster which comprises an induction coil module, a pulse discharge module, a wave modulation module and a pulse air mass excitation module. The wave modulation module is connected in parallel in the main discharge loop, so that the current gradient can be obviously improved while the electromagnetic force of the pulse current waveform is not obviously changed, the induction electric field intensity level is increased, the induction breakdown and ionization process at the initial discharge moment is enhanced, the IPPT working voltage level is effectively reduced, and the propulsion performance of the IPPT is improved; the scheme can reduce the working voltage level of the IPPT by more than 50 percent, thereby reducing the insulation protection requirement in the space application environment; only the wave modulation module is connected in parallel in the main discharge loop, no additional power supply or external magnetic field is needed to be provided, the wave modulation module is driven passively by the main discharge, and the wave modulation circuit is simple in structure, light in weight and reliable in work.
Description
Technical Field
The invention relates to the technical field of electric propulsion, in particular to a single-stage composite double-pulse enhanced ionization type induction pulse plasma thruster.
Background
Space propulsion refers to propulsion used for orbit maintenance, orbit transfer or interstellar flight after a spacecraft obtains the speed of flying around the earth, and can be divided into chemical propulsion and electric propulsion. Compared with the traditional chemical propulsion, the electric propulsion accelerates the propellant by electric energy to obtain the thrust, and the propulsion energy is from the outside of the propellant, so that higher jet speed can be obtained, and the electric propulsion has the advantage of large specific impulse. The adoption of the electric thruster can effectively reduce the consumption of the propellant, thereby increasing the effective load, shortening the task time and prolonging the service life. At present, the electric propulsion technology is widely applied to spacecrafts, and more than half of high-orbit communication satellites are equipped with electric propulsion systems and become one of the signs of advancement of satellite platforms.
The induction type pulse Plasma Thruster (IPPT) is an electrodeless and pulse electromagnetic type electric Thruster, has the new advantages of longer service life, higher power and larger thrust on the basis of keeping the characteristic of high specific impulse of the electric Thruster, and is suitable for interplanetary deep space exploration tasks represented by manned/unmanned Mars tasks. It produces thrust based on the principle of induction vortex repulsion: the method is characterized in that a strong pulse electromagnetic field with a circumferential electric field component and a radial magnetic field component is excited by pulse current in a specially designed planar spiral induction coil, wherein the circumferential electric field component establishes annular plasma vortex current, the radial magnetic field component interacts with the vortex current to generate axial Lorentz force to compress the plasma into sheets and accelerate the injection, and thus a propulsion effect is generated.
From the working principle, the propulsion performance of IPPT depends mainly on two processes of initial ionization and subsequent acceleration of plasma: (1) firstly, in order to enhance the electromagnetic coupling strength of a plasma current sheet and an induction coil, a gas working medium is required to reach higher ionization degree before or at the beginning instant of pulse discharge; (2) meanwhile, the electromagnetic action strength between the plasma current sheet and the induction coil is rapidly reduced along with the increase of the distance between the plasma current sheet and the induction coil, so that the time scale of the pulse current waveform and the plasma acceleration process is required to meet a specific dynamic matching relation in order to improve the global acceleration efficiency of the plasma. On the basis of meeting the requirements of the two points, the IPPT is also required to have the following characteristics by combining the particularity of the space application environment: (1) good insulation protection performance; (2) the structure is simple, the weight is light, and the volume is small; (3) the performance is stable and the service life is long, so as to meet the requirements of interplanetary deep space exploration. According to different initial plasma generating modes, IPPT mainly has three technical schemes of single-stage single-pulse direct ionization, radio frequency discharge preionization, direct current glow discharge preionization and the like at present.
The single-stage single-pulse direct ionization is the earliest adopted power device of IPPT (international power station) and is also the technical scheme which is widely applied at present. According to the scheme, a gas working medium is punctured through a circumferential induction electric field at the initial stage of pulse discharge to generate initial plasma, all processes such as working medium ionization, eddy current establishment and plasma acceleration are completed only by means of a single current pulse generated by a single-stage pulse driving circuit, and the plasma generating device has the advantage of simple system structure. In order to achieve rapid and sufficient ionization of gas, the solution needs to increase the electric field strength on the surface of the induction coil, and accordingly needs to increase the gradient of pulse current at the initial moment of discharge, so that the operating voltage is relatively high, generally more than tens of kilovolts. High voltage is applied in a space environment, and extremely high requirements are put forward on insulation protection; meanwhile, the volume and the weight of the high-voltage capacitor are relatively large. Although the structure of the scheme is simpler, the scheme has no advantages in the aspects of volume, weight, reliability and the like.
In order to reduce the operating voltage of IPPT, a multi-stage IPPT scheme represented by a radio frequency assisted discharge faraday thruster (RF-FARAD) has recently appeared. According to the scheme, neutral gas is ionized through a radio frequency (helical wave) antenna, then plasma is guided to the surface of an induction coil through an external magnetic field, and finally the plasma is further ionized and accelerated through pulse induction discharge. The scheme effectively reduces the requirement on the gradient of the pulse current at the initial discharge moment, is convenient for optimizing the pulse current waveform aiming at the subsequent acceleration process, and reduces the requirement on insulation protection. However, the scheme needs to add an additional radio frequency antenna, a radio frequency power supply and an additional magnetic field coil, so that the complexity, the volume and the weight of the system are greatly increased; the radio frequency discharge has an ionization stabilization process, is difficult to be matched with the pulse working characteristics of the main discharge, and may cause negative effects on the performance of the thruster.
According to the direct current glow discharge preionization scheme, metal electrodes are arranged on the lip of the gas injector and the outer edge of the induction coil, high-voltage direct current is applied to two ends of each electrode, the current is restrained through a current-limiting resistor, a weakly ionized glow discharge area is established above the induction coil, preionization of gas working media is achieved, and the preionization working media are further ionized and accelerated through pulse discharge of the induction coil. The scheme can also reduce the working voltage level of IPPT, an external magnetic field is not required to be applied, and the structure and mass increment brought by the glow discharge electrode and the direct-current high-voltage power supply are relatively small. The IPPT has the great advantage of electrodeless working characteristics, and because the problem of electrode ablation does not exist, the IPPT can load hundreds of kilowatts and even megawatt high power, and the service life of the IPPT is relatively long; meanwhile, due to the fact that the problem of compatibility of the propellant and the electrode does not exist, the IPPT can use various working media such as water, carbon dioxide and even Mars atmosphere, and the propellant is expected to be supplied to the ground in the future. The IPPT adopting the direct current glow discharge pre-ionization scheme adds a metal electrode structure in the discharge channel, and does not have the advantages.
Disclosure of Invention
In view of one or more of the above-mentioned deficiencies in the prior art, the present invention provides a single-stage composite double-pulse enhanced ionization type inductive pulse plasma thruster.
In order to achieve the above object, the present invention provides a single-stage composite double-pulse enhanced ionization type inductive pulse plasma thruster, which comprises an induction coil module, a pulse discharge module, a wave modulation module and a pulse air mass excitation module;
the induction coil module and the pulse discharge module are electrically connected to form a main discharge loop, so that a pulse strong current is generated in the induction coil module in the discharge process of the pulse discharge module, and a strong pulse electromagnetic field with a circumferential electric field component and a radial magnetic field component is further excited around the induction coil module;
the strong pulse electromagnetic field is positioned on a flow path of the pulse air mass excited by the pulse air mass excitation module, so that the pulse air mass is rapidly broken down and ionized under the action of the strong pulse electromagnetic field, a flat and compact plasma current sheet is established, and the plasma current sheet is further compressed, accelerated and ejected under the action of Lorentz force, thereby generating a propulsion action;
the wave modulation module is connected in parallel on the main discharge circuit to make the wave modulation module arouse one section high frequency low-amplitude pulse at the discharge process of pulse discharge module, and then improve the electric current steepness of pulse strong current in the induction coil module, thereby increase the intensity level of strong pulse electromagnetic field, strengthen the induction breakdown and the ionization process of the initial moment of discharging.
As a further improvement of the above technical solution, the pulse discharge module includes a pulse switch and a high-voltage capacitor, the pulse switch, the high-voltage capacitor and the induction coil module are connected in series to form a main discharge loop, and the wave modulation module is connected in parallel to two ends of the high-voltage capacitor or the induction coil module.
As a further improvement of the above technical solution, the wave modulating module is formed by connecting a wave modulating resistor, a wave modulating capacitor and a wave modulating inductor in series;
the capacitance value of the wave-modulating capacitor is 5-15 per mill of the total capacitance value of the high-voltage capacitor;
the inductance value of the wave-modulating inductor is 5-15 per mill of the inductance value of the induction coil module.
As a further improvement of the above technical solution, the pulse discharge module includes a pulse switch and a plurality of high-voltage capacitors, the induction coil module is formed by symmetrically overlapping a plurality of spiral induction coils, and the high-voltage capacitors, the induction coils and the wave modulation module are in one-to-one correspondence;
any high-voltage capacitor, the corresponding induction coil and the pulse switch form a main discharge loop, and the wave modulation module is connected in parallel at two ends of the corresponding high-voltage capacitor or the corresponding induction coil.
As a further improvement of the above technical solution, the spiral line type portion of each induction coil is encapsulated in the coil panel to realize the positioning of each induction coil, and simultaneously, each induction coil is prevented from directly contacting with the plasma.
As a further improvement of the technical scheme, the pulse air mass excitation module is arranged on the coil panel, so that the pulse air mass excited by the pulse air mass excitation module is uniformly dispersed on the surface of the coil panel under the action of a strong pulse electromagnetic field and is compressed to form a plasma current sheet.
As a further improvement of the above technical solution, a gas dam of an annular structure is disposed on one surface of the coil panel corresponding to the pulse bolus excitation module, so as to restrict radial dissipation of the pulse bolus on the coil panel.
The invention provides a single-stage composite double-pulse enhanced ionization type induction pulse plasma thruster.A wave modulation module is connected in parallel in a main discharge loop, and the current gradient can be obviously improved while the electromagnetic force of a pulse current waveform is not obviously changed, so that the induction electric field intensity level is increased, the induction breakdown and ionization processes at the initial discharge moment are enhanced, the IPPT working voltage level is effectively reduced, and the propulsion performance of the IPPT is improved; the scheme can reduce the working voltage level of the IPPT by more than 50 percent, thereby reducing the insulation protection requirement in the space application environment; only the wave modulation module is connected in parallel in the main discharge loop, no additional power supply or external magnetic field is needed to be provided, the wave modulation module is driven passively by the main discharge, and the wave modulation circuit is simple in structure, light in weight and reliable in work.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
FIG. 1 is a schematic circuit diagram of a single-stage composite double-pulse enhanced ionization type inductive pulse plasma thruster according to one embodiment of the present invention;
FIG. 2 is a schematic diagram illustrating a comparison of current waveforms before and after adding a waveform adjusting module according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of a waveform pair of current steepness before and after adding the wave modulating module according to an embodiment of the present invention;
FIG. 4 is a positive axial view of a single-stage composite double-pulse enhanced ionization type inductive pulse plasma thruster in accordance with a second embodiment of the present invention;
fig. 5 is a diagram of a backward axis of the single-stage composite double-pulse enhanced ionization type inductive pulse plasma thruster in the second embodiment of the present invention.
The reference numbers illustrate:
the first embodiment is as follows: an induction coil module 101, a pulse discharge module 102, a wave modulation module 103 and a pulse air mass excitation module 104;
example two: the gas injection device comprises a coil panel 1, a gas box dam 2, an injection tower 3, an injector 4, an induction coil 5, a common ground plate 6, a high-voltage capacitor 7, a wave modulation module 8, a wave modulation resistor 9, a wave modulation capacitor 10, a wave modulation inductor 11 and a pulse switch 12.
The implementation, functional features and advantages of the objects of the present invention will be further explained with reference to the accompanying drawings.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that all the directional indicators (such as up, down, left, right, front, and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the movement situation, etc. in a specific posture (as shown in the drawing), and if the specific posture is changed, the directional indicator is changed accordingly.
In addition, the descriptions related to "first", "second", etc. in the present invention are only for descriptive purposes and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "connected," "secured," and the like are to be construed broadly, and for example, "secured" may be a fixed connection, a removable connection, or an integral part; the connection can be mechanical connection, electrical connection, physical connection or wireless communication connection; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In addition, the technical solutions in the embodiments of the present invention may be combined with each other, but it must be based on the realization of those skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination of technical solutions should not be considered to exist, and is not within the protection scope of the present invention.
The embodiment discloses a single-stage composite double-pulse enhanced ionization type induction pulse plasma thruster, which adopts the same main discharge loop and pulse gas injector configuration as a single-stage single-pulse IPPT (ionized plasma process protector), and is characterized in that a wave modulation module is connected in parallel in the main discharge loop. The wave modulation module can realize that one section high frequency low-amplitude pulse is overlapped in the pulse current waveform of main discharge to multiply discharge initial current gradient size on the basis of not changing the general trend of both electromagnetic force of pulse current, and then show the induced electric field intensity level that improves the induction coil surface, thereby strengthen gaseous induction breakdown and ionization process, finally effectively reduce IPPT operating voltage level, promote its propulsion performance. Meanwhile, the thruster only needs to be connected with the wave modulation module in parallel in the main discharge loop, no additional power supply or external magnetic field needs to be provided, the wave modulation module is driven passively by the main discharge, and the thruster is simple in structure, light in weight and reliable in work.
Example one
The single-stage composite double-pulse enhanced ionization type inductive pulse plasma thruster comprises an induction coil module 101, a pulse discharge module 102, a wave modulation module 103 and a pulse air mass excitation module 104, wherein the induction coil module 101 is used for exciting an electromagnetic field, the pulse discharge module 102 is used for generating pulse current, and the pulse air mass excitation module 104 is used for generating a pulse air mass. Specifically, the method comprises the following steps:
the induction coil module 101 and the pulse discharge module 102 are electrically connected to form a main discharge loop, so that a pulse strong current is generated in the induction coil module 101 in the discharge process of the pulse discharge module 102, and a strong pulse electromagnetic field with a circumferential electric field component and a radial magnetic field component is further excited around the induction coil module 101; the strong pulse electromagnetic field is positioned on the flow path of the pulse air mass excited by the pulse air mass excitation module 104, so that the pulse air mass is rapidly broken down and ionized under the action of the strong pulse electromagnetic field, and a flat and compact plasma current sheet is established, and the plasma current sheet is further compressed, accelerated and ejected under the action of Lorentz force, thereby generating a propulsion action; the wave modulation module 103 is connected in parallel to the main discharge circuit, so that the wave modulation module 103 excites a section of high-frequency low-amplitude pulse in the discharge process of the pulse discharge module 102, and further the current gradient of the pulse strong current in the induction coil module 101 is improved, thereby increasing the intensity level of the strong pulse electromagnetic field and enhancing the induction breakdown and ionization process at the initial discharge moment.
In this embodiment, the pulse discharging module 102 includes a pulse switch and a high-voltage capacitor, the pulse switch, the high-voltage capacitor and the induction coil module 101 are connected in series to form a main discharging loop, and the wave modulating module 103 is connected in parallel to two ends of the high-voltage capacitor or the induction coil module 101. The wave modulation module 103 is formed by serially connecting a wave modulation resistor, a wave modulation capacitor and a wave modulation inductor; the capacitance value of the wave-modulating capacitor is 5-15 per mill of the total capacitance value of the high-voltage capacitor; the inductance value of the wave-modulating inductor is 5-15 per mill of the inductance value of the induction coil module 101.
Referring to fig. 1, a schematic circuit diagram of a single-stage composite double-pulse enhanced ionization type inductive pulse plasma thruster in this embodiment is shown, in which an induction coil module 101, a high-voltage capacitor and a pulse switch form a main discharge circuit, a wave modulation capacitor, a wave modulation inductor and a wave modulation resistor form an LRC wave modulation module 103, and the wave modulation module 103 is connected in parallel to two ends of the high-voltage capacitor or the induction coil. When the device works, a power supply is used for charging the high-voltage capacitor; then the pulse gas mass excitation module 104 injects a mass of gas to the surface of the induction coil module 101; the pulse switch is switched on to discharge the high-voltage capacitor, and meanwhile, the wave modulation module 103 generates a section of high-frequency low-amplitude pulse under the driving of the discharge of the high-voltage capacitor, and the high-frequency low-amplitude pulse signal is superposed on a pulse strong current in the induction coil module 101, so that a weak oscillation 'burr' appears in the waveform of the pulse strong current, but the basic trend of the pulse strong current does not change significantly, as shown in fig. 2; meanwhile, the current gradient of the pulse strong current is greatly improved by the high-frequency low-amplitude pulse, namely as shown in fig. 3, so that the induced electric field strength of the surface of the induction coil module 101 is improved, the induction breakdown and gas ionization processes at the initial stage of discharge are enhanced, and a magnetic-impermeable high-quality plasma current sheet is rapidly established near the induction coil; the high-frequency low-amplitude pulse is attenuated before the main pulse under the damping action of the self wave-regulating resistor, and the formed plasma current sheet is accelerated and sprayed efficiently under the action of the main pulse to complete a working pulse.
Example two
Referring to fig. 4-5, the single-stage composite double-pulse enhanced ionization type inductive pulse plasma thruster disclosed in this embodiment includes an induction coil module, a pulse discharge module, a wave modulation module, and a pulse air mass excitation module, wherein the induction coil module is configured to excite an electromagnetic field, the pulse discharge module is configured to generate a pulse current, and the pulse air mass excitation module is configured to generate a pulse air mass. Specifically, the method comprises the following steps:
the induction coil module and the pulse discharge module are electrically connected to form a main discharge loop, so that a pulse strong current is generated in the induction coil module in the discharge process of the pulse discharge module, and a strong pulse electromagnetic field with a circumferential electric field component and a radial magnetic field component is further excited around the induction coil module; the strong pulse electromagnetic field is positioned on a flow path of the pulse air mass excited by the pulse air mass excitation module, so that the pulse air mass is rapidly broken down and ionized under the action of the strong pulse electromagnetic field, and a flat and compact plasma current sheet is established, and the plasma current sheet is further compressed, accelerated and ejected under the action of Lorentz force, thereby generating a propulsion action; the wave modulation module is connected in parallel on the main discharge circuit to make the wave modulation module arouse one section high frequency low-amplitude pulse at the discharge process of pulse discharge module, and then improve the electric current steepness of pulse strong current in the induction coil module, thereby increase the intensity level of strong pulse electromagnetic field, strengthen the induction breakdown and the ionization process of the initial moment of discharging.
In this embodiment, the pulse discharging module includes a pulse switch and a plurality of high-voltage capacitors, and the induction coil module adopts six spiral line type induction coils to form according to the parallel arrangement of axisymmetric mode, and high-voltage capacitor, induction coil and wave modulation module one-to-one. The induction coil is encapsulated in the coil panel 1 by epoxy resin to achieve positioning while avoiding direct contact with the plasma. One end of each induction coil is connected with a corresponding high-voltage capacitor 7 in series so as to ensure that the magnetic field generated by the induction coil 1 has better radial uniformity; the other end of each induction coil and the high-voltage capacitor are connected in parallel with the two ends of the same pulse switch so as to ensure the discharge synchronism of the capacitors. Two ends of each group of induction coils are simultaneously connected with a group of LRC wave modulation modules 8 in parallel, each wave modulation module 8 is formed by connecting a wave modulation resistor 9, a wave modulation capacitor 10 and a wave modulation inductor 11 in series, wherein the capacitance values and inductance values of the wave modulation capacitor 10 and the wave modulation inductor 11 are respectively one percent of the total capacitance value of the high-voltage capacitor group and the inductance value of the induction coil. The pulse air mass excitation module adopts an injection tower 3, the injection tower 3 is fixed at the central position of the coil panel 1, and polyether ether ketone (PEEK) material with better insulation and high temperature resistance is adopted; the top end of the jetting tower 3 is provided with a jetting device 4, working medium gas is jetted from the top of the jetting tower 3 to the surface of the coil panel 1 in a pulse mode to form pulse air mass, and the surface of the coil panel 1 is compressed; the gas dam 2 is arranged on the periphery of the coil panel 1 to restrain the gas from escaping in the radial direction. It should be noted that a common ground plate 6 is further disposed on the single-stage composite double-pulse enhanced ionization type inductive pulse plasma thruster, and one end of each high-voltage capacitor 7 is electrically connected to the common ground plate 6 for grounding.
When the coil panel works, the injector 4 firstly releases a pulse air mass with specific mass to the surface of the coil panel 1; when the air mass is uniformly dispersed on the surface of the coil panel 1 and is compressed to a large extent, the pulse switch 12 is controlled to be switched on, and the high-voltage capacitor 7 quickly establishes pulse current of dozens to hundreds of kiloamperes in the induction coil 5; the LCR wave modulation module is driven by the main discharge current, generates high-frequency low-amplitude pulse current and is superposed on the main discharge current, and the strength level of an induced electric field at the initial stage of discharge is greatly improved; the gas working medium is quickly broken down and ionized under the action of the induction electric field, and a flat and compact plasma current sheet is established; the plasma current sheet is further compressed, accelerated and sprayed under the action of Lorentz force, so that a propulsion action is generated, and a working pulse is completed; the thruster operates in a pulsed manner, providing a continuous thrust action by continuously repeating the above process.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (7)
1. A single-stage composite double-pulse enhanced ionization type induction pulse plasma thruster is characterized by comprising an induction coil module, a pulse discharge module, a wave modulation module and a pulse air mass excitation module;
the induction coil module and the pulse discharge module are electrically connected to form a main discharge loop, so that a pulse strong current is generated in the induction coil module in the discharge process of the pulse discharge module, and a strong pulse electromagnetic field with a circumferential electric field component and a radial magnetic field component is further excited around the induction coil module;
the strong pulse electromagnetic field is positioned on a flow path of the pulse air mass excited by the pulse air mass excitation module, so that the pulse air mass is rapidly broken down and ionized under the action of the strong pulse electromagnetic field, a flat and compact plasma current sheet is established, and the plasma current sheet is further compressed, accelerated and ejected under the action of Lorentz force, thereby generating a propulsion action;
the wave modulation module is connected in parallel on the main discharge circuit to make the wave modulation module arouse one section high frequency low-amplitude pulse at the discharge process of pulse discharge module, and then improve the electric current steepness of pulse strong current in the induction coil module, thereby increase the intensity level of strong pulse electromagnetic field, strengthen the induction breakdown and the ionization process of the initial moment of discharging.
2. The single-stage composite double-pulse enhanced ionization type induction pulse plasma thruster of claim 1, wherein the pulse discharge module comprises a pulse switch and a high-voltage capacitor, the pulse switch, the high-voltage capacitor and the induction coil module are connected in series to form a main discharge loop, and the wave modulation module is connected in parallel at two ends of the high-voltage capacitor or the induction coil module.
3. The single-stage composite double-pulse enhanced ionization type induction pulse plasma thruster of claim 2, wherein the wave modulation module is formed by serially connecting a wave modulation resistor, a wave modulation capacitor and a wave modulation inductor;
the capacitance value of the wave-modulating capacitor is 5-15 per mill of the total capacitance value of the high-voltage capacitor;
the inductance value of the wave-modulating inductor is 5-15 per mill of the inductance value of the induction coil module.
4. The single-stage composite double-pulse enhanced ionization type induction pulse plasma thruster according to claim 2 or 3, wherein the pulse discharge module comprises a pulse switch and a plurality of high-voltage capacitors, the induction coil module is formed by symmetrically overlapping a plurality of spiral induction coils, and the high-voltage capacitors, the induction coils and the wave modulation module are in one-to-one correspondence;
any high-voltage capacitor, the corresponding induction coil and the pulse switch form a main discharge loop, and the wave modulation module is connected in parallel at two ends of the corresponding high-voltage capacitor or the corresponding induction coil.
5. The single-stage composite double-pulse enhanced ionization type induction pulse plasma thruster of claim 4, wherein the spiral line type part of each induction coil is encapsulated in the coil panel to realize the positioning of each induction coil, and simultaneously, each induction coil is prevented from being in direct contact with plasma.
6. The single-stage composite double-pulse enhanced ionization type induction pulse plasma thruster of claim 5, wherein the pulse air mass excitation module is arranged on the coil panel, so that the pulse air mass excited by the pulse air mass excitation module is uniformly dispersed and compressed on the surface of the coil panel under the action of a strong pulse electromagnetic field to form a plasma current sheet.
7. The single-stage composite double-pulse enhanced ionization type inductive pulse plasma thruster of claim 6, wherein a gas dam with an annular structure is arranged on one surface of the coil panel corresponding to the pulse air mass excitation module, so as to restrain radial dissipation of the pulse air mass on the coil panel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010608074.9A CN111577564A (en) | 2020-06-30 | 2020-06-30 | Single-stage composite double-pulse enhanced ionization type induction pulse plasma thruster |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010608074.9A CN111577564A (en) | 2020-06-30 | 2020-06-30 | Single-stage composite double-pulse enhanced ionization type induction pulse plasma thruster |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111577564A true CN111577564A (en) | 2020-08-25 |
Family
ID=72118156
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010608074.9A Pending CN111577564A (en) | 2020-06-30 | 2020-06-30 | Single-stage composite double-pulse enhanced ionization type induction pulse plasma thruster |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111577564A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112613245A (en) * | 2020-12-18 | 2021-04-06 | 中国人民解放军91550部队 | Design method of laser preionization induction plasma thruster |
Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5207760A (en) * | 1991-07-23 | 1993-05-04 | Trw Inc. | Multi-megawatt pulsed inductive thruster |
| US5605039A (en) * | 1993-07-15 | 1997-02-25 | Olin Corporation | Parallel arcjet starter system |
| CN101260873A (en) * | 2008-01-10 | 2008-09-10 | 上海交通大学 | Pulsed plasma thruster with ceramic air spout electrode |
| US20090058303A1 (en) * | 2007-08-02 | 2009-03-05 | Astrium Gmbh | High Frequency Generator for Ion and Electron Sources |
| CN103278694A (en) * | 2013-04-16 | 2013-09-04 | 广东电网公司佛山供电局 | Impulse current generating device |
| CN103596348A (en) * | 2013-11-22 | 2014-02-19 | 哈尔滨工业大学 | Low-frequency oscillation suppression outer loop of plasma Hall effect thruster |
| CN103675375A (en) * | 2013-12-31 | 2014-03-26 | 上海交通大学 | Inductive discharge high-gradient impact current generator |
| JP2015145650A (en) * | 2014-02-04 | 2015-08-13 | 公立大学法人首都大学東京 | Electric propulsion system |
| CN106014899A (en) * | 2016-05-10 | 2016-10-12 | 中国人民解放军国防科学技术大学 | Helicon plasma induction thruster |
| CN205645478U (en) * | 2016-05-03 | 2016-10-12 | 武汉智瑞捷电气技术有限公司 | Pulse inductance structure |
| CN106033059A (en) * | 2015-03-11 | 2016-10-19 | 中国科学院苏州纳米技术与纳米仿生研究所 | An electric field enhancing structure |
| CN106050593A (en) * | 2016-08-02 | 2016-10-26 | 中国科学院电工研究所 | Plasma synthesis jet flow serial connection discharge device based on Marx generator |
| CN107143475A (en) * | 2017-07-11 | 2017-09-08 | 中国人民解放军国防科学技术大学 | The multistage discharge circuit for the magnetic plasma propeller supported for laser |
| CN110391798A (en) * | 2019-08-19 | 2019-10-29 | 武汉智瑞捷电气技术有限公司 | The method for improving high-voltage charging device and pulse forming network system EMC |
| CN110671287A (en) * | 2019-09-25 | 2020-01-10 | 中国人民解放军国防科技大学 | Induction type plasma accelerating device and method |
-
2020
- 2020-06-30 CN CN202010608074.9A patent/CN111577564A/en active Pending
Patent Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5207760A (en) * | 1991-07-23 | 1993-05-04 | Trw Inc. | Multi-megawatt pulsed inductive thruster |
| US5605039A (en) * | 1993-07-15 | 1997-02-25 | Olin Corporation | Parallel arcjet starter system |
| US20090058303A1 (en) * | 2007-08-02 | 2009-03-05 | Astrium Gmbh | High Frequency Generator for Ion and Electron Sources |
| CN101260873A (en) * | 2008-01-10 | 2008-09-10 | 上海交通大学 | Pulsed plasma thruster with ceramic air spout electrode |
| CN103278694A (en) * | 2013-04-16 | 2013-09-04 | 广东电网公司佛山供电局 | Impulse current generating device |
| CN103596348A (en) * | 2013-11-22 | 2014-02-19 | 哈尔滨工业大学 | Low-frequency oscillation suppression outer loop of plasma Hall effect thruster |
| CN103675375A (en) * | 2013-12-31 | 2014-03-26 | 上海交通大学 | Inductive discharge high-gradient impact current generator |
| JP2015145650A (en) * | 2014-02-04 | 2015-08-13 | 公立大学法人首都大学東京 | Electric propulsion system |
| CN106033059A (en) * | 2015-03-11 | 2016-10-19 | 中国科学院苏州纳米技术与纳米仿生研究所 | An electric field enhancing structure |
| CN205645478U (en) * | 2016-05-03 | 2016-10-12 | 武汉智瑞捷电气技术有限公司 | Pulse inductance structure |
| CN106014899A (en) * | 2016-05-10 | 2016-10-12 | 中国人民解放军国防科学技术大学 | Helicon plasma induction thruster |
| CN106050593A (en) * | 2016-08-02 | 2016-10-26 | 中国科学院电工研究所 | Plasma synthesis jet flow serial connection discharge device based on Marx generator |
| CN107143475A (en) * | 2017-07-11 | 2017-09-08 | 中国人民解放军国防科学技术大学 | The multistage discharge circuit for the magnetic plasma propeller supported for laser |
| CN110391798A (en) * | 2019-08-19 | 2019-10-29 | 武汉智瑞捷电气技术有限公司 | The method for improving high-voltage charging device and pulse forming network system EMC |
| CN110671287A (en) * | 2019-09-25 | 2020-01-10 | 中国人民解放军国防科技大学 | Induction type plasma accelerating device and method |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112613245A (en) * | 2020-12-18 | 2021-04-06 | 中国人民解放军91550部队 | Design method of laser preionization induction plasma thruster |
| CN112613245B (en) * | 2020-12-18 | 2024-03-12 | 中国人民解放军91550部队 | Design method of laser pre-ionization induction plasma thruster |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US6334302B1 (en) | Variable specific impulse magnetoplasma rocket engine | |
| US6492784B1 (en) | Propulsion device and method employing electric fields for producing thrust | |
| CN210106081U (en) | Solid ablation type magnetic plasma thruster | |
| CN109538432B (en) | Spiral wave plasma propulsion device without neutralizer | |
| CN110469474B (en) | Radio frequency plasma source for microsatellite | |
| US20150022031A1 (en) | Electromagnetic Propulsion System | |
| US9394889B2 (en) | Chemical-electromagnetic hybrid propeller with variable specific impulse | |
| CN109737023B (en) | Self-breakdown type pulse plasma thruster of annular cone structure anode | |
| CN111577564A (en) | Single-stage composite double-pulse enhanced ionization type induction pulse plasma thruster | |
| CN210637195U (en) | Radio frequency plasma propeller | |
| CN104405603A (en) | Helicon plasma electric propulsion device | |
| RU2741401C1 (en) | Module with multichannel plasma propulsion system for small spacecraft | |
| CN112253413A (en) | Inductively coupled two-stage plasma thruster | |
| CN107654347B (en) | A kind of high-performance solid ablative-type protective coating pulsed plasma electric propulsion device | |
| US11187213B2 (en) | Thruster device | |
| CN102879285A (en) | Device for realizing strong magnetic pressure oblique wave loading in solid materials | |
| CN110131120B (en) | Solid ablation type magnetic plasma thruster | |
| US3238413A (en) | Magnetically controlled plasma accelerator | |
| CN111997853A (en) | Near space environment air suction type radio frequency plasma propeller | |
| EP3807533B1 (en) | Fiber-fed advanced pulsed plasma thruster (fppt) | |
| AU2004273099A1 (en) | Method and device for generating alfven waves | |
| Kirtley et al. | Steady operation of an FRC thruster on Martian atmosphere and liquid water propellants | |
| CN108194293B (en) | A kind of coaxial-type induction trigger pulse plasma propeller | |
| CN110486244B (en) | Electromagnetic induction type plasma accelerating device | |
| Birx et al. | Technology of magnetically driven accelerators |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20200825 |
|
| RJ01 | Rejection of invention patent application after publication |