阅读说明：本技术 单级复合双脉冲增强电离型感应式脉冲等离子体推力器 (Single-stage composite double-pulse enhanced ionization type induction pulse plasma thruster ) 是由 车碧轩 李小康 程谋森 王墨戈 郭大伟 于 2020-06-30 设计创作，主要内容包括：本发明公开了一种单级复合双脉冲增强电离型感应式脉冲等离子体推力器,包括感应线圈模组、脉冲放电模组、调波模组与脉冲气团激发模组。在主放电回路中并联调波模组,可在不显著改变脉冲电流波形既电磁力大小的同时,显著提高电流陡度,从而增大感应电场强度水平,增强放电初始时刻的感应击穿与电离过程,最终有效降低IPPT工作电压水平、提升其推进性能；本方案可将IPPT的工作电压水平降低50％以上,从而减小空间应用环境中的绝缘防护要求；仅需在主放电回路中并联调波模组,无需提供额外电源或外部磁场,调波模组由主放电被动驱动,结构简单、重量较轻、工作可靠。(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.)

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.

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;