CN212250357U - Sectional pulse plasma thruster - Google Patents
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- CN212250357U CN212250357U CN202020609190.8U CN202020609190U CN212250357U CN 212250357 U CN212250357 U CN 212250357U CN 202020609190 U CN202020609190 U CN 202020609190U CN 212250357 U CN212250357 U CN 212250357U
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Abstract
The utility model discloses a sectional type pulse plasma thrustor, sectional type pulse plasma thrustor includes: a first segment electrode and a second segment electrode; the insulating piece is clamped between the first section of electrode and the second section of electrode; the two energy storage capacitors are respectively connected with the first section of electrode and the second section of electrode; and the two energy storage capacitors are used for respectively providing corresponding voltages for the first section of electrode and the second section of electrode. The utility model discloses can improve working medium utilization ratio and energy conversion efficiency, be favorable to improving the holistic efficiency with higher speed of thrustor.
Description
Technical Field
The utility model relates to a thrustor technical field, in particular to sectional type pulse plasma thrustor.
Background
With the development of modern high technologies such as microelectronic technology, microcomputer technology, novel material development technology and the like, the satellite technology develops towards large-scale on the one hand; on the other hand, microsatellites have also become a hot spot in development. Modern microsatellites are rapidly developed by paying attention from all countries in the world due to the characteristics of light weight, small volume, low price, high performance, short development period and the like, and are widely applied to the fields of communication, remote sensing, military detection and the like. Aiming at space tasks of micro satellites such as attitude control, position keeping, resistance compensation, orbit lifting and maintaining, formation flying and the like, the current satellite application system is developing towards the direction of networking, and in a functional constellation generally consisting of a plurality of or dozens of micro satellites, the orbit phase among the satellites is required to be controlled more accurately. This puts new and higher demands on the on-orbit propulsion technology of the microsatellite. The propulsion technology applied to the microsatellite is required to have the characteristics of small volume, light weight, excellent performance, low cost, easy control, small environmental pollution and the like. The traditional chemical propulsion technology is greatly limited in application to microsatellites due to low specific impulse, heavy weight, complex structure and the like. The pulsed plasma thruster (PPT for short) has the characteristics of small volume, light weight, compact structure and convenient and flexible control, and thus becomes an important development direction of the small satellite propulsion technology.
However, the efficiency of the pulse plasma thruster is not high due to the low working medium utilization rate and energy conversion efficiency of the pulse plasma thruster.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a sectional type pulse plasma thrustor aims at improving working medium utilization ratio and energy conversion efficiency to improve the holistic efficiency with higher speed of thrustor.
In order to achieve the above object, the present invention provides a sectional type pulsed plasma thruster, which comprises:
a first segment electrode and a second segment electrode;
the insulating piece is clamped between the first section of electrode and the second section of electrode;
the two energy storage capacitors are respectively connected with the first section of electrode and the second section of electrode; and the two energy storage capacitors are used for respectively providing corresponding voltages for the first section of electrode and the second section of electrode.
Optionally, the segmented pulsed plasma thruster further comprises:
the permanent magnet for increasing the element impulse is arranged on the sectional type pulse plasma thruster, and the direction of the magnetic field of the sectional type pulse plasma thruster is opposite to the direction of the self-induction magnetic field of the thruster;
and a permanent magnet for specific impulse is added and arranged on the second section of electrode, and the direction of the magnetic field of the permanent magnet is the same as the direction of the self-induction magnetic field of the thruster.
Optionally, the segmented pulsed plasma thruster further comprises:
the first positioning piece is arranged close to the first section of electrode so as to fix the impulse of the increasing element on two sides of the first section of electrode by using a permanent magnet;
and the second positioning piece is arranged close to the second section of electrode so as to fix the permanent magnet for increasing the specific impulse on two sides of the second section of electrode.
Optionally, the first segment electrode and the second segment electrode are arranged in parallel.
Optionally, the cathode plate and the anode plate of the first section of electrode are oppositely arranged;
the cathode plate and the anode plate of the second section of electrode are arranged in parallel or in an angle of divergence;
optionally, the cathode plate and the anode plate of the second segment of electrode are rectangular plates or tongue-shaped plates.
Optionally, the segmented pulsed plasma thruster further comprises:
and the spark plug is embedded in the cathode plate of the first section of electrode.
Optionally, the segmented pulsed plasma thruster further comprises:
and a plurality of output ends of the power supply processing module are respectively and electrically connected with the two energy storage capacitors and the spark plug.
Optionally, the insulator is a ceramic barrier;
the number of the ceramic isolation layers is two, and one of the two ceramic isolation layers is clamped between the cathode plates of the first section of electrode and the second section of electrode;
the other of the two ceramic isolating layers is clamped between the anode plates of the first section of electrode and the second section of electrode.
Optionally, the segmented pulsed plasma thruster further comprises:
and the constant force spring is arranged corresponding to the first section of electrode and is used for providing constant thrust for the solid propellant when the solid propellant is placed in the first section of electrode.
Optionally, the anode plate of the first segment electrode is arranged in a step.
The sectional type pulse plasma thruster electrode is segmented to form a first section electrode and a second section electrode, so that the limitation of electric arc and the improvement of local current density can be realized; the insulating part is arranged in front of the arc attachment point, so that the migration phenomenon of the arc is prevented, and the high temperature and the high current density on the surface of the propellant can be continuously maintained, thereby improving the thrust, specific impulse, ablation amount and efficiency of the thruster. Because the thruster electrode is divided into two sections, and each section of the electrode is provided with voltage by respective energy storage capacitor and different voltage, the discharge at different positions is realized, thereby separating the propellant ablation ionization process and the plasma acceleration process. Provide different energy for each section electrode, make more energy be used for plasma acceleration process, the utility model discloses can improve working medium utilization ratio and energy conversion efficiency, be favorable to improving the holistic efficiency with higher speed of thrustor.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be 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 structural diagram of an embodiment of the sectional type pulsed plasma thruster of the present invention.
The reference numbers illustrate:
| reference numerals | Name (R) | Reference numerals | Name (R) |
| 10 | |
50 | |
| 20 | |
60 | |
| 30 | |
70 | |
| 40 | Power supply processing module |
The objects, features and advantages of the present invention will be further described with reference to the accompanying drawings.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.
It should be noted that, if directional indications (such as upper, lower, left, right, front and rear … …) are involved in the embodiment of the present invention, the directional indications are only used to explain the relative position relationship between the components, the motion situation, etc. in a specific posture (as shown in the drawings), and if the specific posture is changed, the directional indications are changed accordingly.
In addition, if there is a description relating to "first", "second", etc. in the embodiments of the present invention, the description of "first", "second", etc. is for descriptive purposes only and is 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 addition, the technical solutions in the embodiments 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, the combination of the technical solutions should not be considered to exist, and is not within the protection scope of the present invention.
The term "and/or" herein is merely an association describing an associated object, meaning that three relationships may exist, e.g., a and/or B, may mean: a exists alone, A and B exist simultaneously, and B exists alone. In addition, the character "/" herein generally indicates that the former and latter related objects are in an "or" relationship.
The utility model provides a sectional type pulse plasma thrustor.
It can be understood that the pulsed plasma thruster comprises a high-voltage power supply, an ignition circuit, an energy storage capacitor, a thruster body and structure, a shield and the like. The thruster body comprises a working medium, a positive electrode, a negative electrode, a spark plug, a working medium supply device, a support isolation and other components. The thruster body is generally classified into a parallel plate type and a coaxial type. The cathode and the anode of the parallel polar plate type thruster body form a discharge chamber; the working medium (propellant) is in a block shape, a small section is positioned between the cathode and the anode, and the working medium is passively supplied by a constant force spring; the spark plug is arranged on the cathode plate and generates micro-ion to trigger electric arc; the power supply charges the energy storage capacitor, and the two ends of the energy storage capacitor are respectively connected with the cathode plate and the anode plate. According to different working medium supplies, the parallel polar plate type thruster body can be divided into a tail feeding type thruster body and a side supplying type thruster body. The tail-fed long-strip-shaped working medium is parallel to the pole plates, and is gradually pushed into the discharge chamber from one end of the discharge chamber formed by the pole plates and is ablated.
When the pulse plasma thruster works, firstly, the energy storage capacitor is charged to a working voltage (usually 1000-2000V), and the voltage is simultaneously acted on an electrode directly connected with the energy storage capacitor; under the action of the ignition circuit, the spark plug is ignited, and the generated trace ions are discharged to conduct the polar plate, so that the energy storage capacitor is discharged; the high-temperature electric arc formed along the surface of the working medium by discharging ablates a thin layer on the surface of the working medium block and ionizes the thin layer to form plasma; the alternating electric field which is rapidly changed on the transmission line of the thruster and between the polar plates forms a self-induction magnetic field, the magnetic field is vertical to the speed direction of the electric field and the charged particles, and Lorentz force to the charged particles is generated under the combined action of the electromagnetic field; meanwhile, the gas working medium in the discharge channel is also subjected to the action of pneumatic heat; under the combined action of Lorentz force and pneumatic heat, the plasma is mixed with other ablation products and is ejected out of the thruster together to generate a thrust pulse; and after the energy storage capacitor discharges, the thruster enters the next pulse cycle or stops working.
The efficiency of the pulse plasma thruster is not high, and the pulse plasma thruster mainly represents two aspects: firstly, the utilization rate of working medium of the pulse plasma thruster is not high, and the ionization rate of the working medium is only about 10 percent; secondly, the energy conversion efficiency is not high, most of input electric energy is converted into jet heat energy and heat loss of electronic devices, the maximum energy conversion efficiency reported at present is not more than 20%, and the energy efficiency of a thruster with discharge energy of several joules is below 10%.
In order to solve the above problem, referring to fig. 1, in an embodiment of the present invention, the segmented pulsed plasma thruster includes:
a first segment electrode 10 and a second segment electrode 20;
an insulating member 30 sandwiched between the first segment electrode 10 and the second segment electrode 20;
two energy storage capacitors C1, C2 connected to the first segment electrode 10 and the second segment electrode 20 respectively; two storage capacitors C1, C2 for providing corresponding voltages to the first segment electrode 10 and the second segment electrode 20, respectively.
In an embodiment, the segmented pulsed plasma thruster further comprises:
and the spark plug 60 is embedded in the cathode plate 12 of the first section electrode 10, and the spark plug 60 is embedded in the cathode plate 12 of the first section electrode 10.
In this embodiment, the first segment electrode 10 and the second segment electrode 20 include the cathode plate 12 of the first segment electrode 10 and the anode plate 11 of the first segment electrode 10, and the second segment electrode 20 includes the cathode plate 22 of the second segment electrode 20 and the anode plate 21 of the second segment electrode 20. The two electrodes have different functions, the first electrode 10 is used for ablating working medium, generating plasma, igniting at the spark plug 60, generating a small amount of particles comprising electrons, protons, neutral particles and particle clusters, and the particles collide with the surface of the propellant and burn a certain amount of particles from the surface of the propellant. The charged particles are accelerated in two poles under the action of strong electric field and collide with the surface of propellant and among particles to ablate the surface of propellant, and then are decomposed and ionized. As the charged particles increase, plasma is gradually formed between the two electrodes. At this time, the capacitor, the plate and the plasma region form a closed circuit, and an induction magnetic field is generated. The plasma is then accelerated by the Lorentz force to be ejected outwardly, creating a thrust pulse. After the plasma is generated, the plasma enters a discharge channel formed by a cathode plate and an anode plate of the second section of electrode 20 through the insulating part 30 to initiate the discharge of the cathode and the anode of the second section of electrode, and the propellant is fully utilized. Since the second discharge current is relatively far from the propellant surface, no subsequent ablation occurs. The discharge current flows from the anode plate of the second segment electrode 20 to the cathode plate of the second segment electrode 20. This process again forms a plasma, generating a thrust towards the outlet. The entire discharge process is completed.
In the pulse plasma thruster, the discharge gap is usually 15-20mm, the discharge voltage is 1-2kV, and arc discharge along the propellant wall surface is generated in the presence of the propellant. Under the action of higher surface temperature, the electric arc can be separated from the wall surface due to thermal expansion and plasma movement to generate a migration phenomenon, and the electric arc is influenced to ionize the propellant. An insulator 30 is thus provided between the first segment electrode 10 and the second segment electrode 20 to limit the movement of the arc. For the position of the insulation 30, if the insulation is too close to the surface of the propellant, the electric arc can directly jump over the insulation 30 and migrate to the downstream anode discharge, which affects the performance of the thruster; too far from the propellant surface can result in movement of the arc away from the propellant, reducing ionization efficiency. The change trend of the electronic energy peak value is analyzed and calculated through spectrum experiment data, the position of the better insulating piece 30 is obtained, the insulating piece 30 is 4mm away from the surface of the propellant and is just designed in front of an electric arc attachment point, the migration phenomenon of the electric arc is prevented, and the high temperature and the high current density of the surface of the propellant can be continuously maintained. The insulator 30 is a micro quartz crystal ceramic having a length of 2 mm. The width of the discharge arc along the propellant wall is typically 1mm, and the width of the insulator 30 is greater than 1mm, so as to prevent the arc from jumping over the insulator 30 directly and continuing to migrate to the second electrode 20, thereby ensuring that the structure of the insulator 30 can play a role in limiting the arc. In a specific embodiment, the insulating member 30 may be implemented by using a ceramic interlayer, but in other embodiments, the insulating member 30 may also be implemented by using other insulating materials with high temperature resistance, which is not limited herein. Further, the number of the ceramic isolation layers is two, and one of the two ceramic isolation layers is clamped between the cathode plates of the first section of electrode 10 and the second section of electrode 20; the other of the two ceramic separator layers is sandwiched between the anode plates of the first segment electrode 10 and the second segment electrode 20.
The sectional type pulse plasma thruster electrode is segmented to form the first section electrode 10 and the second section electrode 20, so that the limitation of electric arc and the improvement of local current density can be realized; the insulating member 30 is disposed in front of the arc attachment point, prevents the migration phenomenon of the arc, and can continuously maintain the high temperature and the high current density on the surface of the propellant, thereby improving the thrust, specific impulse, ablation amount and efficiency of the thruster. Because the thruster electrode is divided into two sections, and each section of the electrode is provided with voltage by respective energy storage capacitors C1 and C2 and different voltages, the discharge at different positions is realized, and the propellant ablation ionization process and the plasma acceleration process are separated. Provide different energy for each section electrode, make more energy be used for plasma acceleration process, the utility model discloses can improve the holistic efficiency with higher speed of thrustor.
Referring to fig. 1, in one embodiment, the cathode plate and the anode plate of the first segment electrode 10 and the second segment electrode 20 are rectangular plates or tongue-shaped plates.
The cathode plate 12 and the anode plate 11 of the first section of electrode 10 are arranged in parallel;
the cathode plate 22 and the anode plate 21 of the second segment electrode 20 are arranged in an expansion angle shape.
In the embodiment, the distance between the polar plates is increased to accelerate plasma, and the cathode polar plate and the anode polar plate are arranged close to the tail end of the nozzle and are wide-mouthed, so that the effective specific impulse of the thruster can be further improved.
In this embodiment, the first segment electrode 10 and the second segment electrode 20 are disposed in parallel and connected by the insulating member 30, and both the first segment electrode 10 and the second segment electrode 20 are disposed in a parallel plate type. In this arrangement, a constant magnetic field orthogonal to the electric field can be applied, specifically, a permanent magnet for increasing the element impulse is added in the direction opposite to the self-induction magnetic field; the propellant utilization rate of the solid pulse plasma thruster can be improved by adding the specific impulse permanent magnet in the same direction of the self-induction magnetic field, and the performance of the thruster is improved by utilizing the magnetic field orthogonal to the electric field. In the above embodiment, a permanent magnet may be added to both the first segment electrode 10 and the second segment electrode 20, or a permanent magnet may be added to the second segment electrode 20, which is not limited herein. In practical application, two bar-shaped N, S magnets are used and installed on the outer side and the inner side of the copper polar plate paper to generate a constant magnetic field perpendicular to the paper surface in the discharge channel, and of course, the magnets can isolate the magnets from the plasma through the insulating plates to prevent the permanent magnets from contacting with each other.
Referring to fig. 1, in an embodiment, the segmented pulsed plasma thruster further includes:
a permanent magnet (not shown) for increasing the element impulse is arranged on the first section electrode of the segmented pulse plasma thruster, and the direction of the magnetic field of the permanent magnet is opposite to the direction of the self-induction magnetic field of the thruster
A permanent magnet (not shown) for increasing specific impulse, arranged on the second section electrode of the thruster, and having a magnetic field direction the same as the self-induction magnetic field direction of the thruster
In this embodiment, the spark plug 60 starts to ignite, and emits a small amount of particles, which include electrons, ions, and neutral particles, after the particles collide with the surface of the solid propellant, the surface of the propellant emits a large amount of particles due to secondary electron phenomenon, wherein the charged particles are accelerated under the action of the strong electric field of the cathode plate and the anode plate, and continue to collide with the surface of the solid propellant and the emitted particles, so that the surface of the propellant emits more particles, and then the ablated gas molecules are decomposed and ionized into charged particles, when the plasmoid is large enough, the energy storage capacitors C1 and C2 corresponding to the two electrodes, the cathode plate of the two electrodes, the anode plate, and the plasmoid form a current loop of the RLC, and generate a self-induced magnetic field. The plasma group is ejected under the action of electromagnetic force generated by the self-induction magnetic field and the external magnetic field together, and required thrust is generated. Because the increasing unit impulse is fixed near the first section of electrode 10 by the permanent magnet, the direction of the magnetic field is opposite to the direction of the self-induction magnetic field of the plasmoid, the speed of the plasmoid can be effectively reduced, the advancing speed of the neutral gas is reduced, the collision probability of charged particles and the neutral gas can be increased by the magnetic force action of the magnet and the gas storage cavity, and the ionization rate of the solid propellant is improved. Because the current in the later discharge period of the RLC circuit is attenuated, the thrust requirement cannot be met only by the acceleration specific impulse of the plasma self-induction magnetic field, and the specific impulse increasing permanent magnet is added in the same direction of the self-induction magnetic field generated by the plasma cluster, so that the advancing speed of the plasma is increased to meet the specific impulse requirement of the thruster.
In the above embodiment, the two permanent magnets are fixedly disposed by a positioning element, specifically, the first positioning element is disposed near the first segment anode, so as to fix the increase element impulse on two sides of the first segment electrode 10 by the permanent magnets;
and the second positioning piece is arranged close to the second section of electrode 20 so as to fix the permanent magnet for increasing the specific impulse on two sides of the second section of electrode 20.
Referring to fig. 1, in an embodiment, the segmented pulsed plasma thruster further includes:
and a power supply processing module 40, wherein a plurality of output ends of the power supply processing module 40 are respectively electrically connected with the two energy storage capacitors C1 and C2 and the spark plug 60.
In this embodiment, the power processing module 40 may be implemented by using components such as a DC-DC converter, an inductor, a capacitor, and a resistor. The power processing module 40 is connected to the satellite-borne dc bus to convert the satellite-borne power output by the satellite-borne dc bus into the charging voltage of the two energy storage capacitors C1 and C2 and into the power supply of the spark plug 60. Further, the segmented pulsed plasma thruster further includes an ignition circuit 70 configured by a circuit configuration such as an ignition power supply circuit, an ignition start circuit, and an ignition control circuit. The ignition circuit 70 is connected to the power processing module 40 at one end and to the spark plug 60 at the other end to drive the spark plug 60 to operate. It is understood that those skilled in the art can implement the functions of the ignition power supply circuit, the ignition start circuit and the ignition control circuit according to the existing circuit structure, and the detailed description is omitted here. For example, the ignition power supply circuit may be implemented using a pulse transformer or a boost inductor, a PWM controller, or the like. The ignition control circuit can be realized by adopting an integrated chip, such as an MCU, a singlechip and the like. The ignition starting circuit can be realized by adopting elements such as a current-limiting resistor, an energy storage element, an ignition switch, a bleeder resistor and the like.
Referring to fig. 1, in an embodiment, the segmented pulsed plasma thruster further includes:
and the constant force spring 50 is arranged corresponding to the first section of the electrode 10 and is used for providing constant thrust for the solid propellant when the fixed propellant is placed in the first section of the electrode 10.
In this embodiment, the supply of propellant is provided by a constant force spring 50 to exert a force on the propellant to ensure that the propellant is delivered to the thruster port at the desired rate.
In one embodiment, the anode plate 11 of the first segment electrode 10 is arranged in a step.
The surface of the solid propellant is blocked by the stepped anode plate, so that the success rate of ignition can be improved, and the burnt neutral gas is prevented from diffusing without being ionized.
The above is only the optional embodiment of the present invention, and not therefore the limit of the patent scope of the present invention, all of which are in the concept of the present invention, the equivalent structure transformation of the content of the specification and the drawings is utilized, or the direct/indirect application is included in other related technical fields in the patent protection scope of the present invention.
Claims (10)
1. A segmented pulsed plasma thruster, characterized in that the segmented pulsed plasma thruster comprises:
a first segment electrode and a second segment electrode;
the insulating piece is clamped between the first section of electrode and the second section of electrode;
the two energy storage capacitors are respectively connected with the first section of electrode and the second section of electrode; and the two energy storage capacitors are used for respectively providing corresponding voltages for the first section of electrode and the second section of electrode.
2. The segmented pulsed plasma thruster of claim 1 further comprising:
the magnetic field direction of the permanent magnet for increasing the element impulse of the sectional type pulse plasma thruster is opposite to the direction of the self-induction magnetic field of the thruster;
and the specific impulse increasing permanent magnet is arranged on the second section of electrode, and the direction of the magnetic field of the specific impulse increasing permanent magnet is the same as the direction of the self-induction magnetic field of the thruster.
3. The segmented pulsed plasma thruster of claim 2 further comprising:
the first positioning piece is arranged close to the first section of electrode so as to fix the impulse of the increasing element on two sides of the first section of electrode by using a permanent magnet;
and the second positioning piece is arranged corresponding to the second section of electrode so as to fix the permanent magnet for increasing the specific impulse on two sides of the second section of electrode.
4. The segmented pulsed plasma thruster of claim 1 wherein the cathode plate and the anode plate of the second segment of electrodes are rectangular plates or tongue-shaped plates.
5. The segmented pulsed plasma thruster of claim 1 wherein the cathode plate and the anode plate of the first segment of electrodes are arranged in parallel;
the cathode plate and the anode plate of the second section of electrode can be arranged in parallel or in an expansion mode.
6. The segmented pulsed plasma thruster of claim 1 further comprising:
and the spark plug is embedded in the cathode plate of the first section of electrode.
7. The segmented pulsed plasma thruster of claim 6 further comprising:
and a plurality of output ends of the power supply processing module are respectively and electrically connected with the two energy storage capacitors and the spark plug.
8. The segmented pulsed plasma thruster of any one of claims 1 to 7 wherein said insulator is a ceramic barrier;
the number of the ceramic interlayers is two, and one of the two ceramic interlayers is clamped between the cathode plates of the first section of electrode and the second section of electrode;
the other of the two ceramic interlayers is clamped between the anode plates of the first section of electrode and the second section of electrode.
9. The segmented pulsed plasma thruster of any one of claims 1 to 7, further comprising:
and the constant force spring is arranged corresponding to the first section of electrode and is used for providing constant thrust for the solid propellant when the solid propellant is placed in the first section of electrode.
10. The segmented pulsed plasma thruster of any one of claims 1 to 7 wherein the anode plate of the first segment electrode is stepped.
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| CN111365207A (en) * | 2020-04-21 | 2020-07-03 | 何振 | Sectional pulse plasma thruster |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111365207A (en) * | 2020-04-21 | 2020-07-03 | 何振 | Sectional pulse plasma thruster |
| CN111365207B (en) * | 2020-04-21 | 2024-07-16 | 湖南鸿星科技有限公司 | Sectional pulse plasma thruster |
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