Anode heat exchange structure of magnetic plasma thruster and magnetic plasma thruster

Abstract

The present invention relates to an anode heat exchange structure of a magnetic plasma thruster and a magnetic plasma thruster, belonging to the field of electric propulsion thruster design. The anode heat exchange structure of the magnetic plasma thruster includes a heat pipe and a radiation plate; the heat pipe is fixed on the anode body of the magnetic plasma thruster and contacts the anode body, and the length direction of the heat pipe is in the same direction as the central axis direction of the anode body; the radiation plate is fixedly arranged at the condensation end of the heat pipe. The heat deposition on the inner surface of the discharge chamber caused by plasma bombardment is transferred to the rear lightweight radiation plate through the heat pipe to dissipate heat to the environment, and improve the uniformity of the thruster anode temperature distribution. The radiation heat exchange structure takes away a large amount of heat deposited by the anode, prevents the anode from overheating and failure, and at the same time increases the working life, thrust and efficiency of the magnetic plasma thruster.

Description

Technical Field

[0001] The invention belongs to the field of electric propulsion thruster design and relates to an anode heat exchange structure of a magnetic plasma thruster and a magnetic plasma thruster. Background Art

[0002] Electric propulsion is a space propulsion technology that uses electrical energy to generate thrust. Unlike traditional chemical propulsion, electric propulsion does not rely on chemical combustion to generate thrust. Electric propulsion systems operate by ionizing a gaseous working fluid into plasma and then accelerating these ions through an electromagnetic field to generate thrust. The development of electric propulsion technology is of great significance to future space exploration and satellite applications, providing a more economical and efficient means of carrying out long-term space missions.

[0003] A magnetoplasma thruster (MPDT) is a device that generates thrust by accelerating plasma using magnetic and electric fields. It operates by ionizing a propellant (such as xenon or argon) into plasma. Electric and magnetic fields are then applied to accelerate the plasma and eject it from a nozzle, generating a reaction force that propels the satellite forward. Compared to other electric propulsion systems, this thruster offers advantages such as high specific impulse and high thrust, making it an ideal propulsion device for future deep space exploration missions.

[0004] After electrical energy is injected into a magnetoplasma thruster, only a portion of it is used to ionize the propellant or heat the plasma, ultimately converting it into kinetic energy for the thruster to generate thrust. The remaining energy is dissipated as heat deposited in the thruster's anode and cathode structures. Of this, 65%-80% of the energy is deposited at the anode. Currently, magnetoplasma thrusters are typically cooled with water. While water-cooling offers high cooling efficiency, it is difficult to implement in future space applications due to structural complexity and reliability issues. Therefore, it is necessary to design a thruster that utilizes a radiative heat dissipation structure to meet the needs of future space applications. Summary of the Invention

[0005] To address these issues, the present invention aims to design an anode heat exchange structure for a magnetoplasma thruster that dissipates heat through both conduction and radiation. This structure, through the arrangement of heat pipes, transfers heat from the anode to a rearward radiating plate, where it is radiated into the space environment. This ensures safe and reliable thruster operation, maximizes thruster efficiency, and minimizes impact on the thruster's main structure.

[0006] The present invention also provides a magnetic plasma thruster comprising the anode heat exchange structure of the magnetic plasma thruster.

[0007] The present invention adopts the following technical solutions:

[0008] An anode heat exchange structure for a magnetoplasma thruster, comprising a heat pipe and a radiation plate; the heat pipe is fixed to and in contact with the anode body of the magnetoplasma thruster, and the length direction of the heat pipe is in the same direction as the central axis direction of the anode body; the radiation plate is fixedly arranged at the condensation end of the heat pipe.

[0009] There are multiple heat pipes, and the multiple heat pipes are symmetrically arranged on the outer wall of the anode body.

[0010] The number of the heat pipes is 7, and the angle between two adjacent heat pipes is 45°.

[0011] Wherein, the heat exchange structure further includes a heat pipe support truss, and the heat pipe is fixed to the anode and cathode connectors of the magnetoplasma thruster through the heat pipe support truss.

[0012] Wherein, the heat pipe is fixed on the anode body through an anode connector, and the anode connector is welded to the anode body.

[0013] Wherein, the radiation plate is tangent to the surface of the anode body; and / or, the radiation plate is vertically connected to the heat pipe.

[0014] Wherein, both sides of the radiation plate are coated with a high-efficiency thermal control coating; and / or, the radiation plate is a lightweight radiation plate.

[0015] Wherein, the anode heat exchange structure adopts propylene as the heat exchange medium.

[0016] A magnetic plasma thruster comprises a discharge chamber, an anode body and the anode heat exchange structure of the magnetic plasma thruster, wherein the heat pipe portion is located in the discharge chamber.

[0017] Wherein, the heat pipe is fixed on the anode and cathode connectors of the magnetoplasma thruster.

[0018] The beneficial effects of the present invention are as follows:

[0019] (1) The present invention uses heat conduction combined with radiation for heat exchange. By providing a heat pipe, the heat deposited on the anode is transferred to the rear radiation plate, which not only effectively improves the heat dissipation efficiency, but also prevents thermal stress concentration from causing deformation of the thruster. The heat deposited on the inner surface of the discharge chamber caused by plasma bombardment is transferred to the rear radiation plate through the heat pipe to dissipate heat to the environment, and improves the uniformity of the thruster anode temperature distribution. The radiation heat exchange structure takes away a large amount of heat deposited on the anode, prevents the anode from overheating and failure, and at the same time increases the service life, thrust and efficiency of the magnetic plasma thruster.

[0020] (2) The present invention uses propylene as the heat exchange medium. The melting point of propylene is -185°C. There is generally no freezing problem in space applications, and no compensatory heating is required, which improves the low-temperature adaptability and reliability of space applications.

[0021] (3) The present invention designs a heat pipe support truss; the rear end of the heat pipe needs to be connected to the radiation plate, and there is no anode body support at the rear end. In order to meet the thermodynamic performance of the heat pipe and ensure that the heat pipe does not disintegrate during the working process, a lightweight triangular support truss is designed at the rear end of the anode body and the heat pipe to fix the heat pipe while maximally reducing the excess load.

[0022] (4) The radiation plate is connected to the heat pipe and is tangent to the surface of the anode body. The arrangement of the radiation plates reduces the angular radiation coefficient between the radiation plates and improves the radiation efficiency to the background. At the same time, high-efficiency thermal control coating is applied on both sides of the radiation plate to maximize the heat dissipation area. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 1. It is an overall schematic diagram of an embodiment of the anode heat exchange structure of the magnetic plasma thruster of the present invention;

[0024] Figure 2 A partial structural diagram of the anode heat exchange structure of the magnetic plasma thruster of the present invention;

[0025] Figure 3 It is a schematic diagram of the overall structure of the magnetic plasma thruster of the present invention.

[0026] Figure numerals: 1-discharge chamber, 2-anode body, 4-anode connector, 7-anode clamping electrode, 201-radiation plate, 202-heat pipe, 203-heat pipe support truss, 204-cathode and anode connector, 205-threaded hole, 301-cathode and anode insulation, 302-propellant inlet, 303-propellant channel, 304-hollow cathode, 305-cathode fixing member, 307-nut. DETAILED DESCRIPTION

[0027] In order to make the objectives, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only intended to illustrate the present invention and are not intended to limit the present invention. In addition, the technical features involved in the various embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.

[0028] The specific embodiments of the present invention are described in detail below with reference to specific examples and the accompanying drawings.

[0029] See also Figure 1An anode heat exchange structure for a magnetic plasma thruster includes a heat pipe 202 and a radiation plate 201. The heat pipe 202 is fixed to and in contact with the anode body 2 of the magnetic plasma thruster, and the length of the heat pipe 202 is aligned with the central axis of the anode body 2. The radiation plate 201 is fixed to the condensing end of the heat pipe 202. The length of the heat pipe 202 is aligned with the central axis of the anode body 2, ensuring maximum contact area between the heat pipe and the anode body, thereby achieving better heat transfer. The heat pipe is welded to the anode body.

[0030] The heat pipe 202 runs through the anode body 2 and connects to the radiant plate 201. It uses phase change heat to carry away heat deposited from the anode and then radiates heat to the surrounding environment via the radiant plate. The heat exchange medium in the heat pipe is heated at the anode end (evaporation section), causing the liquid inside the tube to evaporate, absorbing the heat deposited by the anode power. Under a slight pressure differential, it flows to the other end of the heat pipe, the condensation section. Condensing at the radiant plate, the vapor releases latent heat and condenses back into liquid, releasing heat in the process. The condensed liquid returns to the evaporation section via the capillary action of the wick, completing the cycle and achieving efficient heat transfer. This heat pipe is an internal circulation heat pipe.

[0031] Preferably, there are multiple heat pipes, and the multiple heat pipes are symmetrically arranged on the outer wall of the anode body. The symmetrical arrangement of multiple heat pipes is more conducive to removing the heat deposited by the anode.

[0032] Better yet, see Figure 1 The number of heat pipes 202 is 7, and the angle between two adjacent heat pipes is 45°. The heat pipes 202 are arranged symmetrically around the anode body 2. Except for the anode clamping electrode 7, the other heat pipes are arranged at an angle of 45°, for a total of 7 heat pipes.

[0033] Better, see Figure 1 The length of the heat pipe is greater than that of the anode body, and the projection of the radiation plate is located on the anode body. This arrangement can achieve a better radiation effect.

[0034] See also Figure 1 and Figure 2 The heat exchange structure also includes a heat pipe support truss 203, through which the heat pipe 202 is secured to the anode and cathode connectors 204 of the magnetoplasma thruster. The heat pipe support truss 203 is positioned at the rear end of the anode to form a triangular support structure with the heat pipe. The support truss is welded to form a secure connection with the anode and cathode connectors and the heat pipe. Preferably, there are seven heat pipe support trusses in total. The rear end of the heat pipe 202 is welded to the radiation plate 201 and the heat pipe support truss 203.

[0035] Among them, see Figure 1 The heat pipe 202 is fixed to the anode body 2 through the anode connector 4 , and the anode connector 4 is welded to the anode body 2 .

[0036] Better, see Figure 1 and Figure 2 The radiation plate is tangent to the surface of the anode body; and / or the radiation plate is perpendicularly connected to the heat pipe. This arrangement reduces the angular radiation coefficient between the radiation plates and improves the radiation efficiency to the background.

[0037] Furthermore, both sides of the radiation plate are coated with a high-efficiency thermal control coating, which can maximize the heat dissipation area.

[0038] Furthermore, the radiation plate is a lightweight radiation plate, which can reduce the load of the heat pipe.

[0039] The anode heat exchange structure uses propylene as the heat exchange medium. Propylene has a melting point of -185°C and generally does not freeze in space applications, eliminating the need for compensatory heating. This improves low-temperature adaptability and reliability in space applications.

[0040] See also Figure 1 and Figure 3 The present invention further provides a magnetic plasma thruster, comprising a discharge chamber 1, an anode body 2, and the anode heat exchange structure of the magnetic plasma thruster described above, wherein the heat pipe 202 is partially located in the discharge chamber 1. In other words, the heat pipe runs through the discharge chamber and the anode body.

[0041] Furthermore, the magnetoplasma thruster also includes an anode intermediate connector 4, anode and cathode connectors 204, cathode and cathode insulators 301, a propellant inlet 302, a propellant channel 303, a hollow cathode 304, and a cathode fixing member 305. The heat pipe 202 is further fixed to the cathode and cathode connectors 204; the cathode and cathode connectors 204 are fixed to the anode body 2, cathode and cathode insulators 301, and propellant channel 303 via threaded holes 205, bolts, and nuts 307.

[0042] The purpose of the anode and cathode insulators 301 is to insulate the thruster's anode and cathode, preventing direct contact between the anode and cathode, which could cause a short circuit and burn the thruster. The propellant channel 303 is connected to the hollow cathode via threads. The heat pipe 202 is partially embedded in the discharge chamber 1 and is connected to the anode body 2 via the anode intermediate connector 4 for radial fixation. The anode clamping electrode 7 is welded to the anode body 2. When the magnetic plasma thruster is in operation, the hollow cathode 304 and the anode body 2 are connected to the discharge chamber 1 by applying an external high voltage to ionize the gas propellant entering from the propellant inlet 302, generating plasma in the discharge chamber 1. The plasma is then accelerated and ejected under the action of the electromagnetic field to generate thrust. The heat pipe radiation heat dissipation structure is described separately below.

[0043] Due to plasma bombardment and sputtering, a plasma sheath is formed on the inner surface of the discharge chamber 1, causing anode power to drop and heat to accumulate in the discharge chamber 1 and the anode body 2. The heat pipe 202 runs through the discharge chamber 1 and the anode body 2 and is connected to the radiation plate 201 at the rear end. The heat pipe utilizes the phase change heat transfer characteristics of the heat pipe to efficiently remove a large amount of heat from the anode and dissipate heat to the outside through the lightweight radiation plate, thereby balancing the anode temperature, reducing ablation, extending the service life of the magnetic plasma thruster, and increasing the thrust of the thruster.

[0044] It will be easily understood by those skilled in the art that the above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

[0045] Any portions not described in detail in this specification are known in the art. The above embodiments are provided for illustrative purposes only and are not intended to limit the scope of the present invention. The scope of the present invention is defined by the appended claims. Any equivalent substitutions and modifications that do not depart from the spirit and principles of the present invention are intended to be encompassed within the scope of the present invention.

Claims

1. An anode heat exchange structure for a magnetic plasma thruster, characterized in that: The anode heat exchange structure includes a heat pipe and a radiation plate; the heat pipe is fixed to the anode body of the magnetic plasma thruster and contacts the anode body, and the length direction of the heat pipe is in the same direction as the central axis direction of the anode body; the radiation plate is fixedly arranged at the condensation end of the heat pipe; The heat exchange structure also includes a heat pipe support truss, and the heat pipe is fixed to the anode and cathode connectors of the magnetic plasma thruster through the heat pipe support truss; the heat pipe is fixed to the anode body through the anode connector, and the anode connector is welded to the anode body.

2. The anode heat exchange structure of the magnetoplasma thruster according to claim 1, characterized in that: There are multiple heat pipes, and the multiple heat pipes are symmetrically arranged on the outer wall of the anode body.

3. The anode heat exchange structure of the magnetoplasma thruster according to claim 2, characterized in that: The number of the heat pipes is 7. Except for the anode clamping electrode where no heat pipe is arranged, the angle between the other two adjacent heat pipes is 45°.

4. The anode heat exchange structure of the magnetoplasma thruster according to claim 1, characterized in that: The radiation plate is tangent to the surface of the anode body; and / or the radiation plate is vertically connected to the heat pipe.

5. The anode heat exchange structure of the magnetoplasma thruster according to claim 1, characterized in that: Both sides of the radiation plate are coated with a high-efficiency thermal control coating; and / or the radiation plate is a lightweight radiation plate.

6. The anode heat exchange structure of a magnetoplasma thruster according to any one of claims 1 to 5, characterized in that: The anode heat exchange structure uses propylene as the heat exchange medium.

7. A magnetic plasma thruster, characterized in that: The anode heat exchange structure of the magnetic plasma thruster comprises a discharge chamber, an anode body and any one of claims 1 to 6, wherein the heat pipe portion is located in the discharge chamber.

8. The magnetoplasma thruster according to claim 7, characterized in that: The heat pipe is fixed on the anode and cathode connectors of the magnetoplasma thruster.

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