阅读说明：本技术 一种同轴稳态烧蚀固体推进剂脉冲等离子体推力器 (Coaxial steady state ablation solid propellant pulse plasma thruster ) 是由 孙国瑞 呼文韬 张丹红 李钏 于智航 丁大龙 于 2021-07-21 设计创作，主要内容包括：一种同轴稳态烧蚀固体推进剂脉冲等离子体推力器,包括：电磁铁环、绝缘层、中心电极、绝缘介质层、点火电极、推进剂、外电极、恒力弹簧、点火电源、主放电电源、主放电电容器和电磁铁环电源。本发明提供的一种同轴稳态烧蚀固体推进剂脉冲等离子体推力器的有益效果如下：(1)通过电磁铁环的电磁场使等离子体在推进剂表面呈螺旋态行进,可有效降低径向电流密度差异性,提升推力器的推进性能一致性和工作可靠性；(2)外电极和内电极均为带锯齿状或三角状齿牙电极,根据尖端放电原理,可有效降低启动所需条件,增强了推力器的可应用性。(A coaxial steady state ablative solid propellant pulsed plasma thruster, comprising: the ignition device comprises an electromagnet ring, an insulating layer, a central electrode, an insulating medium layer, an ignition electrode, a propellant, an outer electrode, a constant force spring, an ignition power supply, a main discharge capacitor and an electromagnet ring power supply. The coaxial steady-state ablation solid propellant pulse plasma thruster provided by the invention has the following beneficial effects: (1) plasma advances spirally on the surface of the propellant through an electromagnetic field of the electromagnet ring, so that the difference of radial current density can be effectively reduced, and the propulsion performance consistency and the working reliability of the thruster are improved; (2) the outer electrode and the inner electrode are both provided with sawtooth-shaped or triangular tooth electrodes, the conditions required by starting can be effectively reduced according to the tip discharge principle, and the applicability of the thruster is enhanced.)

1. A coaxial steady state ablative solid propellant pulsed plasma thruster, comprising: an electromagnet ring (1), an insulating layer (2), a central electrode (31), an insulating medium layer (32), an ignition electrode (33), a propellant (4), an outer electrode (5), a constant force spring (6), an ignition power supply (7), a main discharge power supply (8), a main discharge capacitor (9) and an electromagnet ring power supply (10), wherein the electromagnet ring (1), the insulating layer (2), the outer electrode (5), the propellant (4), the central electrode (31), the insulating medium layer (32) and the ignition electrode (33) are arranged in the same axial direction from outside to inside, the outer electrode (5) is respectively connected with a first end of the main discharge capacitor (9) and a positive electrode of the main discharge power supply (8), the central electrode (31) is respectively connected with a second end of the main discharge capacitor (9) and a negative electrode of the main discharge power supply (8), center electrode (31) are connected the positive pole of ignition power supply (7), ignition electrode (33) are connected the negative pole of ignition power supply (7), the both ends of electromagnetism magnet ring (1) respectively with the positive negative pole of electromagnetism magnet ring power supply (10) is connected, the first end of constant force spring (6) is connected propellant (4) and the second end is connected outer electrode (5).

2. The coaxial steady-state ablative solid propellant pulsed plasma thruster of claim 1, characterized in that the electromagnetic field direction of the electromagnet ring (1) is perpendicular to the cross section of the outer electrode (5).

3. The coaxial steady-state ablative solid propellant pulsed plasma thruster of claim 2, characterized in that the magnetic field strength of the electromagnet ring (1) ranges from 0.5T to 3.0T.

4. The coaxial steady-state ablation solid propellant pulsed plasma thruster as claimed in claim 1, characterized in that the thickness of the insulating layer (2) ranges from 5 to 20mm and the material is PTFE or polyimide.

5. The coaxial steady-state ablation solid propellant pulsed plasma thruster of claim 1, characterized in that the outer electrode (5) is a circular ring with crenellated teeth or triangular teeth.

6. The coaxial steady-state ablation solid propellant pulsed plasma thruster of claim 5, characterized in that the material of the outer electrode (5) is copper or aluminum.

7. The coaxial steady-state ablative solid propellant pulsed plasma thruster of claim 1, characterized in that the central electrode (31) is a cylinder with crenellated or trigonal teeth on the head.

8. The coaxial steady-state ablative solid propellant pulsed plasma thruster of claim 7, characterized in that the material of the central electrode (31) is copper or aluminum.

9. The coaxial steady-state ablative solid propellant pulsed plasma thruster of claim 1, characterized in that the ignition electrode (33) is in the form of an elongated filament made of copper, tungsten or carbon nanotubes.

10. The coaxial steady-state ablation solid propellant pulsed plasma thruster of claim 1, characterized in that the propellant (4) is annular and is made of PTFE, ETFE or solid sulfur.

Technical Field

The invention belongs to the technical field of micro-satellite propulsion, and particularly relates to a coaxial steady ablation solid propellant pulse plasma thruster.

Background

The coaxial solid propellant pulse plasma thruster is an electric thruster without a movable part and with high specific impulse, and has wide application value on microsatellites represented by cuboids. The radial ablation rate of the ablation surface of the solid propellant is inconsistent due to the inconsistency of the radial current density and the field intensity gradient in the working process of the thruster, and after the working times exceed a certain value, the phenomena of high ablation rate at the center of the thruster and low ablation rate at the outer diameter are shown, so that the consistency of the propelling performance of the thruster is poor, the reliability of ignition starting is poor, and the applicability of the coaxial solid propellant pulse plasma thruster is greatly limited.

Disclosure of Invention

In order to solve the above problems, the present invention provides a coaxial steady-state ablation solid propellant pulse plasma thruster, comprising: an electromagnet ring, an insulating layer, a central electrode, an insulating medium layer, an ignition electrode, a propellant, an outer electrode, a constant force spring, an ignition power supply, a main discharge capacitor and an electromagnet ring power supply, wherein the electromagnet ring, the insulating layer, the outer electrode, the propellant, the center electrode, the insulating medium layer and the ignition electrode are arranged in the same axial direction from outside to inside, the outer electrodes are respectively connected with the first end of the main discharge capacitor and the positive electrode of the main discharge power supply, the central electrodes are respectively connected with the second end of the main discharge capacitor and the negative electrode of the main discharge power supply, the central electrode is connected with the positive electrode of the ignition power supply, the ignition electrode is connected with the negative electrode of the ignition power supply, the two ends of the electromagnet ring are respectively connected with the positive electrode and the negative electrode of the electromagnet ring power supply, the first end of the constant force spring is connected with the propellant, and the second end of the constant force spring is connected with the outer electrode.

Preferably, the electromagnetic field direction of the electromagnet ring is perpendicular to the section of the outer electrode.

Preferably, the magnetic field strength of the electromagnet ring ranges from 0.5T to 3.0T.

Preferably, the thickness of the insulating layer ranges from 5 mm to 20mm, and the material is PTFE or polyimide.

Preferably, the outer electrode is a circular ring with serrated teeth or triangular teeth.

Preferably, the material of the external electrode is copper or aluminum.

Preferably, the center electrode is a cylinder with serrated teeth or triangular teeth on the head

Preferably, the material of the central electrode is copper or aluminum.

Preferably, the ignition electrode is in the shape of an elongated wire and is made of copper, tungsten or carbon nanotubes.

Preferably, the propellant is annular and is made of PTFE, ETFE or solid sulfur.

The coaxial steady-state ablation solid propellant pulse plasma thruster provided by the invention has the following beneficial effects:

(1) plasma advances spirally on the surface of the propellant through an electromagnetic field of the electromagnet ring, so that the difference of radial current density can be effectively reduced, and the propulsion performance consistency and the working reliability of the thruster are improved.

(2) The outer electrode and the inner electrode are both provided with sawtooth-shaped or triangular tooth electrodes, the conditions required by starting can be effectively reduced according to the tip discharge principle, and the applicability of the thruster is enhanced.

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, and 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 these drawings without creative efforts.

FIG. 1 is a schematic diagram of a coaxial steady-state ablative solid propellant pulsed plasma thruster provided by the invention;

FIG. 2 is a schematic structural diagram of a main body of a coaxial steady-state ablative solid propellant pulsed plasma thruster provided by the invention;

FIG. 3 is a schematic diagram of an outer electrode structure of a coaxial steady-state ablative solid propellant pulsed plasma thruster provided by the invention;

FIG. 4 is a schematic structural diagram of a central electrode of a coaxial steady-state ablative solid propellant pulsed plasma thruster provided by the invention;

description of the symbols: 1-electromagnet ring, 2-insulating layer, 31-center electrode, 32-insulating medium layer, 33-ignition electrode, 4-propellant, 5-outer electrode, 6-constant force spring, 7-ignition power supply, 8-main discharge power supply, 9-main discharge capacitor and 10-electromagnet ring power supply.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail with reference to the accompanying drawings in conjunction with the following detailed description. It should be understood that the description is intended to be exemplary only, and is not intended to limit the scope of the present invention. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present invention.

In an embodiment of the present application, as shown in fig. 1 to 4, the present invention provides a coaxial steady-state ablation solid propellant pulsed plasma thruster, comprising: an electromagnet ring 1, an insulating layer 2, a central electrode 31, an insulating medium layer 32, an ignition electrode 33, a propellant 4, an outer electrode 5, a constant force spring 6, an ignition power supply 7, a main discharge power supply 8, a main discharge capacitor 9 and an electromagnet ring power supply 10, wherein the electromagnet ring 1, the insulating layer 2, the outer electrode 5, the propellant 4, the central electrode 31, the insulating medium layer 32 and the ignition electrode 33 are arranged coaxially from outside to inside, the outer electrode 5 is respectively connected with a first end of the main discharge capacitor 9 and a positive electrode of the main discharge power supply 8, the central electrode 31 is respectively connected with a second end of the main discharge capacitor 9 and a negative electrode of the main discharge power supply 8, the central electrode 31 is connected with the positive electrode of the ignition power supply 7, the ignition electrode 33 is connected with the negative electrode of the ignition power supply 7, two ends of the electromagnet ring 1 are respectively connected with the positive electrode and the negative electrode of the electromagnet ring power supply 10, the constant force spring 6 is connected at a first end to the propellant 4 and at a second end to the outer electrode 5.

When the coaxial steady-state ablation solid propellant pulse plasma thruster provided by the invention works, after the ignition power supply 7 starts a signal, the ignition electrode 33 loads voltage to a certain amplitude, and the ignition electrode 33 generates a small amount of excitation electrons. And exciting electrons to generate a small amount of plasma outside the central electrode 31 under a high-voltage surface flashover mechanism, so that the ignition starting process of the thruster is completed. Under the high-voltage driving of the outer electrode 5 and the central electrode 31, a small amount of plasma generated by ignition starting presents a spiral avalanche effect on the surface of the propellant 4, and arc discharge is formed on the surface of the propellant 4. The thermal energy radiated by the arc discharge ablates the propellant 4 to produce a small amount of neutral gas. Under the action of high voltage, neutral gas is ionized into charged particles and accelerated to be sprayed out by an electromagnetic field generated by self induction.

In the embodiment of the present application, the electromagnetic field direction of the electromagnet ring 1 is perpendicular to the cross section of the outer electrode 5.

In the embodiment of the present application, the magnetic field strength of the electromagnet ring 1 ranges from 0.5T to 3.0T.

In the embodiment of the present application, the thickness of the insulating layer 2 ranges from 5 mm to 20mm, and the material is PTFE or polyimide.

In the embodiment of the present application, the outer electrode 5 is a ring with serrated teeth or triangular teeth.

In the embodiment of the present application, the material of the outer electrode 5 is copper or aluminum.

In the embodiment of the present application, the center electrode 31 is a cylinder with serrated teeth or triangular teeth on the head.

In the embodiment of the present application, the material of the central electrode 31 is copper or aluminum.

In the embodiment of the present application, the ignition electrode 33 is an elongated filament made of copper, tungsten or carbon nanotube.

In the embodiment of the present application, the propellant 4 is annular and is made of PTFE, ETFE, or solid sulfur.

The coaxial steady-state ablation solid propellant pulse plasma thruster provided by the invention has the following beneficial effects:

(1) plasma advances spirally on the surface of the propellant through an electromagnetic field of the electromagnet ring, so that the difference of radial current density can be effectively reduced, and the propulsion performance consistency and the working reliability of the thruster are improved;

(2) the outer electrode and the inner electrode are both provided with sawtooth-shaped or triangular tooth electrodes, the conditions required by starting can be effectively reduced according to the tip discharge principle, and the applicability of the thruster is enhanced.

It is to be understood that the above-described embodiments of the present invention are merely illustrative of or explaining the principles of the invention and are not to be construed as limiting the invention. Therefore, any modification, equivalent replacement, improvement and the like made without departing from the spirit and scope of the present invention should be included in the protection scope of the present invention. Further, it is intended that the appended claims cover all such variations and modifications as fall within the scope and boundaries of the appended claims or the equivalents of such scope and boundaries.