CN213392530U - Inductively coupled two-stage plasma thruster - Google Patents
Inductively coupled two-stage plasma thruster Download PDFInfo
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- CN213392530U CN213392530U CN202022576526.8U CN202022576526U CN213392530U CN 213392530 U CN213392530 U CN 213392530U CN 202022576526 U CN202022576526 U CN 202022576526U CN 213392530 U CN213392530 U CN 213392530U
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Abstract
The utility model relates to the technical field of spacecraft propulsion, and discloses an inductive coupling two-stage plasma thruster, which comprises an inner wall and an aluminum oxide outer wall, wherein the inner wall is a cylindrical pyrex heat-resistant glass tube with one closed end, a radio frequency source is arranged in the inner wall, and the radio frequency source comprises a bare copper wire coil, a ferrite column, two ferrite disks and two permanent magnet rings; the front part of the outer wall is a cylindrical channel, and the rear part of the outer wall is a conical cylinder with a small front part and a big rear part; an anode is arranged in the rear part of the outer wall, and two permanent magnet blocks which are arranged in an axisymmetric manner are respectively arranged at the outer side of the front part of the outer wall and the tail part of the outer side of the rear part of the outer wall; a cathode is arranged on one side in front of the outer wall; the frequency of the radio frequency source is 4 MHZ. The beneficial effect of this application does: high thrust or high specific impulse operation can be achieved as required.
Description
Technical Field
The utility model relates to a spacecraft impels technical field, especially relates to an inductive coupling doublestage plasma thrustor.
Background
With the development of the aerospace technology, the demands of space tasks on a spacecraft propulsion system are more diversified, and the tasks such as deep space exploration, orbit transfer of a communication satellite, position keeping and the like have the requirements on the space propulsion technology, such as high specific impulse, high efficiency, long service life and the like. Traditional chemical propulsion is limited by chemical energy and wall temperature, and has low specific impulse. The electric propulsion increases the air injection speed to a higher order by means of electric energy, and can save a large amount of propellant, thereby effectively improving the effective load of the satellite, reducing the emission quality, and achieving the purposes of prolonging the service life and reducing the cost. And the electric propulsion system also has the characteristics of high control precision, high safety and the like. The method can meet the requirements of different tasks of spacecraft attitude control, position maintenance, resistance compensation, orbit transfer, deep space exploration and the like, and therefore, the method has wide application.
In the traditional steady-state plasma thruster, an axial electric field is formed between an anode and a cathode, a radial magnetic field is formed between an inner magnetic pole and an outer magnetic pole, electrons emitted by the cathode drift to a discharge chamber under the combined action of the orthogonal axial electric field and the radial magnetic field, neutral propellant atoms from the anode collide with the neutral propellant atoms and are ionized, and the neutral propellant atoms are ejected at a high speed under the action of the axial electric field to generate thrust. The electric field of the thruster is used for ionization and acceleration of the working medium, so that the thrust force and the specific impulse are not separated from each other. The plasma thruster can only realize high thrust or high specific impulse for a specific space flight task and specific power. The aerospace requirement of a multi-attitude adjusting task cannot be met.
SUMMERY OF THE UTILITY MODEL
To the deficiency that exists on the prior art, the utility model provides an inductive coupling doublestage plasma thrustor.
In order to achieve the above purpose, the present invention is realized by the following technical solution:
an inductive coupling two-stage plasma thruster comprises an inner wall, an outer wall and a propellant conveying pipe, wherein the inner wall is a cylindrical pyrex heat-resistant glass pipe with one closed end, a radio frequency source is arranged in an inner cavity of the inner wall and comprises a coil, a cylindrical hollow insulating carrier, a ferrite cylinder, two ferrite disks and two permanent magnet rings, the coil is wound on the insulating carrier, the ferrite cylinder is coaxially arranged in the center of the insulating carrier, the two ferrite disks are respectively and fixedly arranged at two ends of the ferrite cylinder, the two permanent magnet rings are respectively and fixedly arranged on the circumferential edge of one ferrite disk, magnetic poles of the two permanent magnet rings are transversely distributed, and the directions of magnetic fields of the two permanent magnet rings are opposite;
the outer wall is arranged on the outer side of the inner wall and is coaxial with the inner wall, the front part of the outer wall is a cylindrical channel, the rear part of the outer wall is in a cone shape with a small front part and a big rear part, and the rear end face of the outer wall is fixedly connected with the rear end of the inner wall through a closed end face; an anode is arranged in the rear part of the outer wall, two permanent magnet blocks which are arranged in an axisymmetric manner are respectively arranged at the outer side of the front part of the outer wall and the tail part of the outer side of the rear part of the outer wall, and the two permanent magnet blocks on the same side are fixed through an L-shaped soft iron sheet; two permanent magnet blocks that are located the front portion are the same with the samarium cobalt magnet ring magnetic field direction that is located ferrite drum front end, and two permanent magnet blocks that are located the front and back portion are the same with the samarium cobalt magnet ring magnetic field direction that is located ferrite drum rear end, outer wall place ahead one side is equipped with the negative pole, positive pole and negative pole respectively with propellant duct connection.
Preferably, the frequency of the radio frequency source is 4MHZ, which can reduce capacitive coupling and central ferrite loss compared with 13.56MHZ in the prior art, and the coupling efficiency of the radio frequency source is improved as a whole.
Preferably, the coil is a bare copper wire coil, the insulating carrier material is epoxy polymer, and the permanent magnet ring is a samarium cobalt magnet ring.
It should be noted that: the anode and cathode of the present application are prior arts, such as the anode disclosed in chinese patent 201610599709.7 or 201910243684.0, and the hollow cathode structure disclosed in a hollow cathode for electric propulsion without heater (author: zhangyan, conway, qiaocai, etc.) published in rocket propulsion (vol. 4/40/2014, vol. 2), can be used in the technical solution of the present application.
The working principle of this application does: the positions of the outer wall and the four permanent magnet blocks are combined to form an ionization chamber with four magnetic tips and magnetic field lines parallel to the wall surface of the outer wall, so that the wall-attached loss of ions can be reduced, and the plasma density can be improved.
The bare copper wire coil and the ferrite column at the center of the bare copper wire coil can generate high-density plasma, electrons can be distributed around the coil in a ring surface mode, the electrons can move back and forth along an axial magnetic field and are heated by an angular electric field induced by the coil, the magnetic induction lines of the two permanent magnet rings penetrate through the ferrite column and the ferrite disk, the magnetic field is enabled to have a component parallel to the inner wall, magnetic meeting exists in the ionization chamber, the plasma can be restrained, and the adherent loss of charged particles can be limited. And the ferrite post and the ferrite disk that set up can prevent to appear the vortex in the magnetic circuit on the one hand to reduce the power loss of radio frequency source, on the other hand has a better coupling with radio frequency source inductance power.
The beneficial effect of this application does: and the radio frequency source is used as an ionization source, is positioned in the thruster and can be singly ionized to generate plasma. The anode and cathode are separately applied with a voltage for acceleration of ions in the plasma. Therefore, the generation and acceleration of the plasma are independent of each other; thereby realizing the mutually independent thrust and specific impulse control of the thruster.
Drawings
The present invention will be described in detail with reference to the accompanying drawings and specific embodiments.
Fig. 1 is a schematic structural diagram of an inductively coupled two-stage plasma thruster according to embodiment 1 of the present invention.
Fig. 2 is a magnetic field distribution diagram of the permanent magnet ring and the permanent magnet blocks in fig. 1.
Detailed Description
In order to make the technical means, creation features, achievement purposes and functions of the present invention easy to understand, the present invention is further described below with reference to the following embodiments.
Example 1
As shown in fig. 1-2, an inductively coupled two-stage plasma thruster includes an inner wall 1, an outer alumina wall 2 and a propellant delivery pipe 3, wherein the inner wall is a cylindrical pyrex heat-resistant glass pipe with one end closed, the inner diameter of the heat-resistant glass pipe is 26mm, an inner cavity of the inner wall is provided with a radio frequency source, the radio frequency source includes a bare copper wire coil 4 with a length of 25mm and an inner diameter of 20mm, a cylindrical hollow epoxy polymer insulating carrier 5, a ferrite cylinder 6, two ferrite disks 7 with an outer diameter of 22mm, and two permanent magnet rings 8 with an inner diameter of 22mm and a wall thickness of 1mm, the coil is wound on the insulating carrier, the ferrite cylinder is coaxially disposed in the center of the insulating carrier, the two ferrite disks are respectively and fixedly disposed at two ends of the ferrite cylinder, the two permanent magnet rings are respectively and fixedly disposed on the circumferential edges of one ferrite disk, the magnetic poles of the two permanent magnet rings are transversely distributed and the directions of the magnetic fields of the two permanent magnet rings are opposite;
the outer wall 2 is arranged on the outer side of the inner wall and is coaxial with the inner wall, the front part 201 of the outer wall is a cylindrical channel with the inner diameter of 46mm and the length of 10mm, the rear part 202 of the outer wall is in a conical cylinder shape with a small front part and a large rear part, the inner diameter of the large end of the rear part of the outer wall is 92mm, and the rear end face 203 of the outer wall is fixedly connected with the rear end of the inner; an anode 9 is arranged in the rear part of the outer wall, two permanent magnet blocks 10 which are arranged in an axisymmetric manner are respectively arranged at the outer side of the front part of the outer wall and the tail part of the outer side of the rear part of the outer wall, and the two permanent magnet blocks on the same side are fixed through an L-shaped soft iron sheet 11; as shown in fig. 2, two permanent magnet blocks positioned at the front part of the outer wall are the same as the magnetic field direction of the samarium cobalt magnet ring positioned at the front end of the ferrite cylinder, two permanent magnet blocks positioned at the front and the rear parts are the same as the magnetic field direction of the samarium cobalt magnet ring positioned at the rear end of the ferrite cylinder, a cathode 12 is arranged on one side in front of the outer wall, and the anode and the cathode are respectively connected with the propellant conveying pipe.
The frequency of the radio frequency source is 4MHz, compared with 13.56MHz in the prior art, the frequency can reduce capacitive coupling and central ferrite loss, and the coupling efficiency of the radio frequency source is improved integrally.
The radio frequency source of the thruster is used as an ionization source, is located inside the thruster, and singly ionizes to generate plasma. The anode and cathode are separately applied with a voltage for acceleration of ions in the plasma. Therefore, the generation and acceleration of the plasma are independent of each other, and the thrust force and the specific impulse are independent of each other. The thruster can also be used for alternative working media which are more difficult to ionize than xenon. Thrust is a function of dc voltage during the acceleration phase, and rf voltage during the ionization phase,
the thrust calculation formula of the thruster is as follows:
here, jiIs ion current density, theta is azimuth angle, R is distance from measuring probe to thruster, IiIs an ion current.
The total thrust of the thruster is
Where < v > represents the average ion velocity, which can be found from the electron distribution function.
The average cosine is given by:
wherein the mass flow rate can be calculated by:
where w is the basic elementary charge, miIs the ion mass.
Those skilled in the art should understand that the present invention is not limited by the above embodiments. The foregoing embodiments and description have been made only for the purpose of illustrating the principles of the invention. The present invention can be further modified and improved without departing from the spirit and scope of the present invention. Such changes and modifications are intended to be within the scope of the claimed invention. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (3)
1. An inductively coupled two-stage plasma thruster is characterized in that: the high-power plasma generator comprises an inner wall, an outer wall and a propellant conveying pipe, wherein the inner wall is a cylindrical pyrex heat-resistant glass pipe with one closed end, a radio frequency source is arranged in an inner cavity of the inner wall and comprises a coil, a cylindrical hollow insulating carrier, a ferrite cylinder, two ferrite disks and two permanent magnet rings, the coil is wound on the insulating carrier, the ferrite cylinder is coaxially arranged in the center of the insulating carrier, the two ferrite disks are respectively and fixedly arranged at two ends of the ferrite cylinder, the two permanent magnet rings are respectively and fixedly arranged on the circumferential edge of one ferrite disk, magnetic poles of the two permanent magnet rings are transversely distributed and the directions of magnetic fields of the two permanent magnet rings are opposite;
the outer wall is arranged on the outer side of the inner wall and is coaxial with the inner wall, the front part of the outer wall is a cylindrical channel, the rear part of the outer wall is in a cone shape with a small front part and a big rear part, and the rear end face of the outer wall is fixedly connected with the rear end of the inner wall through a closed end face; an anode is arranged in the rear part of the outer wall, two permanent magnet blocks which are arranged in an axisymmetric manner are respectively arranged at the outer side of the front part of the outer wall and the tail part of the outer side of the rear part of the outer wall, and the two permanent magnet blocks on the same side are fixed through an L-shaped soft iron sheet; two permanent magnet blocks that are located the front portion are the same with the samarium cobalt magnet ring magnetic field direction that is located ferrite drum front end, and two permanent magnet blocks that are located the front and back portion are the same with the samarium cobalt magnet ring magnetic field direction that is located ferrite drum rear end, outer wall place ahead one side is equipped with the negative pole, positive pole and negative pole respectively with propellant duct connection.
2. The inductively coupled dual-stage plasma thruster of claim 1 wherein: the frequency of the radio frequency source is 4 MHZ.
3. The inductively coupled dual-stage plasma thruster of claim 1 wherein: the coil is bare copper wire coil, the insulating carrier material is epoxy polymer, the permanent magnet ring is samarium cobalt magnet ring, the outer wall material is aluminium oxide.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202022576526.8U CN213392530U (en) | 2020-11-09 | 2020-11-09 | Inductively coupled two-stage plasma thruster |
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| CN202022576526.8U CN213392530U (en) | 2020-11-09 | 2020-11-09 | Inductively coupled two-stage plasma thruster |
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