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

Abstract

The invention relates to an anode heat exchange structure of a magnetic plasma thruster and the magnetic plasma thruster, and belongs to the field of electric propulsion thruster design. The anode heat exchange structure of the magnetic plasma thruster comprises a heat pipe and a radiant panel; the heat pipe is fixed on an anode main body of the magnetic plasma thruster and is in contact with the anode main body, and the length direction of the heat pipe is the same as the central axis direction of the anode main body; and the radiant panel is fixedly arranged at the condensation end of the heat pipe. Thermal deposition, caused by plasma bombardment, on the inner surface of the discharge cavity is transferred to the light radiant panel at the rear end through the heat pipe to dissipate heat to the environment, and the anode temperature distribution uniformity of the thruster is improved. The radiation heat exchange structure takes away a large amount of heat of anode sedimentation, anode overheating failure is prevented, the service life of the magnetic plasma thruster is prolonged, and the thrust and efficiency of the magnetic plasma thruster are improved.

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. The working principle of the electric propulsion system is to ionize the gaseous working fluid into plasma, and then accelerate these ions through electromagnetic fields to generate thrust. The development of electric propulsion technology is of great significance to future space exploration and satellite applications. It can provide a more economical and efficient way to perform long-term space missions.

[0003] The magnetoplasma thruster (MPDT) is a device that uses magnetic and electric fields to accelerate plasma to generate thrust. Its working principle is to ionize the propellant (such as xenon, argon) into plasma, and then accelerate the plasma and eject it from the nozzle by applying electric and magnetic fields, generating a reaction force to propel the satellite forward. Compared with other electric propulsion thrusters, this thruster has the advantages of high specific impulse and high thrust, and is an ideal propulsion device for future deep space exploration missions.

[0004] After the electric energy is injected into the magnetoplasma thruster, only part of the energy is used to ionize the propellant or heat the plasma, which is finally converted into the kinetic energy of the thruster to generate thrust. The rest of the energy will be deposited in the form of heat on the anode and cathode structures of the thruster and dissipated. Among them, the anode energy deposition reaches 65%-80%. At present, the cooling method for magnetoplasma thrusters is usually a water-cooled structure. The water-cooled design has a high cooling efficiency, but it is difficult to implement in future space applications due to its complex structure and reliability defects. Therefore, it is necessary to design a thruster that utilizes a radiation heat dissipation structure to meet the needs of future space applications. Summary of the invention

[0005] In view of the above problems, the purpose of the present invention is to design an anode heat exchange structure of a magnetic plasma thruster that uses both heat conduction and radiation to dissipate heat. The anode heat exchange structure transfers the anode heat to the rear radiation plate by arranging heat pipes, and radiates it to the space environment, ensuring the safe and reliable operation of the thruster, ensuring the thruster's working efficiency, and minimizing the impact on the thruster's main structure.

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

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

[0008] An anode heat exchange structure of a magnetoplasma thruster, comprising a heat pipe and a radiation plate; the heat pipe is fixed on 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 also 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 on 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 uses 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 part is located in the discharge chamber.

[0017] Wherein, the heat pipe is fixed on the cathode and anode 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 setting up 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 the concentration of thermal stress 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 working life, thrust and efficiency of the magnetic plasma thruster.

[0020] (2) The present invention uses propylene as a heat exchange medium. The melting point of propylene is -185°C. In space applications, there is generally no freezing problem and no need to provide compensatory heating, thereby improving 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 a 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 between the rear end of the anode body and the heat pipe to fix the heat pipe while minimizing 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 coatings are applied on both sides of the radiation plates to maximize the heat dissipation area. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 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 It is 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 supporting truss, 204-cathode and anode connector, 205-threaded hole, 301-cathode and anode insulating parts, 302-propellant inlet, 303-propellant channel, 304-hollow cathode, 305-cathode fixing part, 307-nut. DETAILED DESCRIPTION

[0027] In order to make the purpose, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain 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 can be combined with each other as long as they do not conflict with each other.

[0028] The specific implementation of the present invention is described in detail below through specific examples in conjunction with the accompanying drawings.

[0029] See also Figure 1, an anode heat exchange structure of a magnetic plasma thruster, the anode heat exchange structure comprising a heat pipe 202 and a radiation plate 201; the heat pipe 202 is fixed on the anode body 2 of the magnetic plasma thruster and contacts the anode body 2, and the length direction of the heat pipe 202 is in the same direction as the central axis direction of the anode body 2; the radiation plate 201 is fixedly arranged at the condensation end of the heat pipe 202. The length direction of the heat pipe 202 is in the same direction as the central axis direction of the anode body 2, which can ensure that the contact area between the heat pipe and the anode body is maximized, thereby achieving a better heat transfer effect. The heat pipe is fixed to the anode body by welding.

[0030] The heat pipe 202 runs through the anode body 2 and is connected to the radiation plate 201. The heat of the anode is taken away by the heat pipe phase change heat, and the radiation plate is used to radiate heat to the environment. The heat exchange medium in the heat pipe is heated at the anode end (evaporation section), and the liquid in the tube begins to evaporate, absorbing the heat of the anode power deposition, and flows to the other end of the heat pipe, i.e., the condensation section, under a small pressure difference. Condensation at the radiation plate end, the steam releases latent heat and condenses back into liquid, and this process releases heat. The condensed liquid returns to the evaporation section by the capillary action of the liquid wick, thereby completing the entire cycle and achieving efficient heat transfer. The 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 taking away the heat deposited by the anode.

[0032] Better yet, see Figure 1 The number of the heat pipes 202 is 7, and the angle between two adjacent heat pipes is 45°. The heat pipes 202 are arranged symmetrically in the anode body 2, except that no heat pipe is arranged at the anode clamping electrode 7, and the angle of the remaining heat pipes is 45°, and a total of 7 heat pipes are arranged.

[0033] For better, see Figure 1 The length of the heat pipe is greater than the length of the anode body, and the projection of the radiation plate is located on the anode body. Such an 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, and the heat pipe 202 is fixed to the cathode and cathode connectors 204 of the magnetic plasma thruster through the heat pipe support truss 203. The heat pipe support truss 203 is arranged at the rear end of the anode to form a triangular support structure with the heat pipe, and the support truss is welded to form a reliable connection with the cathode and cathode connectors and the heat pipe. More preferably, there are 7 heat pipe support trusses in total. The rear end of the heat pipe 202 is connected and fixed to the radiation plate 201 and the heat pipe support truss 203 by welding.

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

[0036] For 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 vertically 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. The melting point of propylene is -185°C, and there is generally no freezing problem in space applications, so there is no need to provide compensatory heating, which improves the low-temperature adaptability and reliability of space applications.

[0040] See also Figure 1 and Figure 3 The present invention also 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, wherein the heat pipe 202 is partially located in the discharge chamber 1. That is, the heat pipe runs through the discharge chamber and the anode body.

[0041] Furthermore, the magnetoplasma thruster further comprises an anode intermediate connector 4, anode and cathode connectors 204, cathode and cathode insulating members 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 on the cathode and cathode connectors 204; the cathode and cathode connectors 204 are fixed to the anode body 2, the cathode and cathode insulating members 301, and the propellant channel 303 through threaded holes 205, bolts and nuts 307.

[0042] The purpose of the cathode and anode insulating parts 301 is to insulate the cathode and anode of the thruster to prevent the cathode and anode from directly contacting each other, resulting in a short circuit and burning the thruster. The propellant channel 303 is connected to the hollow cathode through a thread. The heat pipe 202 is partially embedded in the discharge chamber 1 and is connected to the anode body 2 through the anode intermediate connector 4 to complete radial fixation. The anode clamping electrode 7 is connected and fixed to the anode body 2 by welding. When the magnetic plasma thruster is working, the hollow cathode 304 and the anode body 2 and the discharge chamber 1 ionize the gas propellant entering from the propellant inlet 302 by applying an external high voltage, generate plasma in the discharge chamber 1, and accelerate the ejection under the action of the electromagnetic field to form 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 the anode power to settle, 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 phase change heat transfer characteristics are used to efficiently take away a large amount of heat from the anode, and the heat is dissipated to the outside through the lightweight radiation plate, so as to balance the anode temperature, reduce the ablation phenomenon, extend the service life of the magnetic plasma thruster, and increase the thrust of the thruster.

[0044] It will be easily understood by those skilled in the art that the above description is only 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 protection scope of the present invention.

[0045] The parts not described in detail in the present description belong to the known technology in the art. The above embodiments are provided only for the purpose of describing the present invention, but not to limit the scope of the present invention. The scope of the present invention is defined by the appended claims. Various equivalent substitutions and modifications made without departing from the spirit and principle of the present invention should be included in the scope of the present invention.

Claims

1. An anode heat exchange structure of 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 on the anode body of the magnetic plasma thruster and is in contact with 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.

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 for a magnetic plasma thruster according to claim 2, characterized in that: The number of the heat pipes is 7, and the angle between two adjacent heat pipes is 45°.

4. The anode heat exchange structure of the magnetoplasma thruster according to claim 1, characterized in that: The heat exchange structure also includes a heat pipe supporting truss, and the heat pipe is fixed to the anode and cathode connecting parts of the magnetoplasma thruster through the heat pipe supporting truss.

5. The anode heat exchange structure of the magnetoplasma thruster according to claim 1, characterized in that: The heat pipe is fixed to the anode body through an anode connector, and the anode connector is welded to the anode body.

6. The anode heat exchange structure of the magnetoplasma thruster according to claim 5, 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.

7. The anode heat exchange structure of the magnetoplasma thruster according to claim 5, 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.

8. The anode heat exchange structure of the magnetic plasma thruster according to any one of claims 1 to 7, characterized in that: The anode heat exchange structure uses propylene as the heat exchange medium.

9. A magnetic plasma thruster, characterized in that: The invention comprises a discharge chamber, an anode body and an anode heat exchange structure of a magnetic plasma thruster according to any one of claims 1 to 8, wherein the heat pipe portion is located in the discharge chamber.

10. The magnetoplasma thruster according to claim 9, characterized in that: The heat pipe is fixed on the cathode and anode connectors of the magnetoplasma thruster.

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