Permanent magnet Hall thruster heat conduction support, supporting base and method for improving working temperature consistency of inner permanent magnet and outer permanent magnet

Abstract

The invention provides a permanent magnet Hall thruster heat conduction support, a supporting base and a method for improving the working temperature consistency of an inner permanent magnet and an outer permanent magnet. The heat conduction support comprises a heat conduction bottom plate, a heat conduction center column and heat conduction fins, and the heat conduction center column is vertically connected to the middle of the heat conduction bottom plate; the heat conduction fins are arranged at intervals in the circumferential direction of the heat conduction bottom plate, and the heat conduction bottom plate, the heat conduction center column and the heat conduction fins are of an integrated structure; the supporting base comprises a supporting base body and the heat conduction support nested in the supporting base body in a matched mode. The method for improving the working temperature consistency of the inner permanent magnet and the outer permanent magnet is realized by adopting the supporting base. According to the permanent magnet Hall thruster heat conduction support, the supporting base and the internal and external permanent magnet working temperature consistency improving method, the temperature difference of the internal and external permanent magnets can be effectively reduced, and the working temperature consistency of the internal and external permanent magnets is improved.

Description

Technical Field

[0001] This invention belongs to the fields of aerospace electric propulsion technology and plasma technology, and in particular relates to a method for improving the consistency of working temperature of a permanent magnet Hall thruster heat conduction bracket, support base and inner and outer permanent magnets. Background Technology

[0002] Hall thrusters are the most widely used space electric propulsion devices internationally, demonstrating outstanding performance in spacecraft attitude control, orbit maintenance, and maneuvering missions, and have achieved large-scale application, especially in the rapidly developing low-Earth orbit communication satellite network. Hall thrusters possess advantages such as simple structure, high specific impulse, and high thrust-to-power ratio, helping to reduce fuel consumption, lower launch costs, and increase payload efficiency, bringing significant social and economic benefits. Hall thrusters based on permanent magnet excitation with a high aspect ratio, thanks to their unique wide-channel, small radial dimension structure, offer significant advantages in compact and lightweight design, while also possessing the potential to achieve high discharge performance. This represents one of the most promising development directions for achieving multi-directional synchronous improvement of Hall thrusters.

[0003] However, the compact structure of high aspect ratio Hall thrusters significantly increases their power density, but also brings more severe thermal problems, seriously threatening the lifespan and reliability of Hall thrusters. The reduction in the inner and outer diameters of the discharge channel in high aspect ratio Hall thrusters leads to a significant reduction in the wall surface area, resulting in a significant increase in the average power required per unit area. In addition, the increased channel width further exacerbates the difference in surface area between the inner and outer walls, leading to a sharp increase in the thermal load on the inner wall. Furthermore, the reduction in the radial dimension of the inner channel makes the arrangement space of the inner permanent magnets extremely compact, thus obstructing the heat dissipation path and causing the temperature difference between the inner and outer sides to accumulate continuously.

[0004] Permanent magnets possess a non-negligible thermal characteristic: their coercivity decreases with increasing temperature, inevitably leading to a reduction in the magnetic field strength at their end faces. If the operating temperature difference between the inner and outer permanent magnets is too large, the magnetic field strength and distribution within the channel will deviate significantly from the cold-state design value, resulting in deterioration of discharge conditions and even the end of their lifespan.

[0005] Therefore, how to effectively solve the problem of excessive temperature difference between the inner and outer permanent magnets in order to achieve long-life stable discharge of Hall thrusters with large height-to-diameter ratio has become an urgent problem to be solved. Summary of the Invention

[0006] In view of this, the present invention provides a method for improving the temperature consistency of the heat-conducting bracket, support base and inner and outer permanent magnets of a permanent magnet Hall thruster, so as to solve the problem of excessive temperature difference between the inner and outer permanent magnets of a Hall thruster with a large height-to-diameter ratio.

[0007] The present invention provides a heat-conducting support for a permanent magnet Hall thruster, comprising: a heat-conducting base plate, a heat-conducting central column, and heat-conducting ribs, wherein the heat-conducting central column is vertically connected to the middle of the heat-conducting base plate, and the heat-conducting ribs are multiple and spaced apart along the circumference of the heat-conducting base plate. The heat-conducting base plate, the heat-conducting central column, and the heat-conducting ribs are an integrated structure, used to cooperate and be nested in the support base body of the permanent magnet Hall thruster, and to conduct the heat in the inner permanent magnet area sequentially through the heat-conducting central column, the heat-conducting base plate, and the heat-conducting ribs to the outer permanent magnet area.

[0008] Preferably, the heat-conducting base plate, the heat-conducting central column, and the heat-conducting fins are made of pure copper.

[0009] In a further preferred embodiment, the heat-conducting base plate is provided with multiple hollow areas larger than the anode bottom component of the permanent magnet Hall thruster.

[0010] In a further preferred embodiment, the heat-conducting fins are uniformly arranged along the circumference of the heat-conducting base plate.

[0011] The present invention also provides a permanent magnet Hall thruster support base, comprising: a support base body and the aforementioned heat-conducting bracket, wherein the heat-conducting bracket is nested within the support base body for discharging heat from the inner permanent magnet region to the outer permanent magnet region.

[0012] Preferably, the support base body includes an inner permanent magnet mounting area and an outer permanent magnet mounting area, the heat-conducting central column of the heat-conducting bracket extends to the vicinity of the inner permanent magnet mounting area, and the heat-conducting ribs of the heat-conducting bracket extend to the vicinity of the outer permanent magnet mounting area.

[0013] The present invention also provides a method for improving the working temperature consistency of the inner and outer permanent magnets of a permanent magnet Hall thruster. The method uses the aforementioned permanent magnet Hall thruster support base to conduct heat from the inner permanent magnet area to the outer permanent magnet area, thereby reducing the working temperature difference between the inner and outer permanent magnets and improving the working temperature consistency of the inner and outer permanent magnets.

[0014] The permanent magnet Hall thruster heat conduction bracket provided by this invention is an integrated heat conduction structure that can be nested in the support base of the permanent magnet Hall thruster to achieve efficient heat dissipation and improve the consistency of the working temperature of the permanent magnets inside and outside the thruster.

[0015] The permanent magnet Hall thruster support base provided by this invention embeds an integrated heat-conducting bracket into the support base body without affecting the magnetic circuit structure of the thruster. This can effectively conduct heat from the inner permanent magnet area to the outer permanent magnet area, improving the consistency of the working temperature of the inner and outer permanent magnets of the thruster.

[0016] The method for improving the working temperature consistency of the inner and outer permanent magnets of a permanent magnet Hall thruster provided by the present invention can effectively improve the working temperature consistency of the inner and outer permanent magnets by adopting the aforementioned permanent magnet Hall thruster support base. Attached Figure Description

[0017] The present invention will be further described below with reference to the accompanying drawings: Figure 1 A schematic diagram of the structure of the permanent magnet Hall thruster heat conduction bracket provided by the present invention; Figure 2 This is a schematic diagram of the structure of the permanent magnet Hall thruster support base provided by the present invention; Figure 3 This is a schematic diagram of a local thermal simulation of a permanent magnet Hall thruster using a support base without a heat-conducting bracket. Figure 4 This is a schematic diagram of a local thermal simulation of a permanent magnet Hall thruster using a support base with a heat-conducting bracket installed according to the present invention. Detailed Implementation

[0018] The present invention will be further described below with reference to specific embodiments.

[0019] Excessive temperature difference between the inside and outside of a permanent magnet Hall thruster with a large height-to-diameter ratio will lead to instability of the magnetic field configuration, which in turn will cause deterioration of the discharge conditions or even the end of its life.

[0020] To address the aforementioned issues, this invention provides a heat-conducting bracket and support base for a permanent magnet Hall thruster. By nesting the heat-conducting bracket within the support base, heat from the inner permanent magnet region can be efficiently transferred to the outer permanent magnet region, effectively solving the problem of heat deposition in the inner permanent magnet region of the permanent magnet Hall thruster and significantly improving the consistency of the operating temperature of the inner and outer permanent magnets of the thruster.

[0021] like Figure 1 As shown, the present invention provides a heat-conducting bracket for a permanent magnet Hall thruster, comprising: a heat-conducting base plate 1, a heat-conducting central column 2, and heat-conducting ribs 3, wherein the heat-conducting central column 2 is vertically connected to the middle of the heat-conducting base plate 1, and the heat-conducting ribs 3 are multiple and spaced apart along the circumference of the heat-conducting base plate 1. The heat-conducting base plate 1, the heat-conducting central column 2, and the heat-conducting ribs 3 are an integrated structure, used to cooperate and be nested within the support base body 5 of the permanent magnet Hall thruster, and to conduct the heat in the inner permanent magnet area sequentially through the heat-conducting central column 2, the heat-conducting base plate 1, and the heat-conducting ribs 3 to the outer permanent magnet area.

[0022] The permanent magnet Hall thruster heat conduction bracket is an integrated heat conduction structure that can be nested within the support base of the permanent magnet Hall thruster to achieve efficient heat dissipation and improve the consistency of the working temperature of the permanent magnets inside and outside the thruster. The integrated structural design can eliminate the thermal resistance interface in the traditional spliced ​​structure, making the heat conduction path smoother and thus effectively improving the heat conduction efficiency.

[0023] The heat-conducting base plate 1, heat-conducting central column 2, and heat-conducting fins 3 are all made of pure copper, possessing high thermal conductivity and non-magnetic properties. At room temperature, the thermal conductivity of pure copper is approximately 400 W / (m·K), while that of austenitic stainless steel (1Cr18Ni9Ti) commonly used in aerospace is approximately 17 W / (m·K). While both thermal conductivity coefficients change slightly with increasing temperature, it is expected that the pure copper heat-conducting support can more effectively transfer heat from the inner permanent magnet region to the outer permanent magnet region, thereby preventing localized overheating. In practical applications, the thickness of the heat-conducting base plate, the height and diameter of the heat-conducting central column, and the width and thickness of the heat-conducting fins can be determined based on the specific structural dimensions of the Hall thruster, aiming to maximize the heat-conducting area while ensuring structural strength meets requirements. The number of heat-conducting fins is k (k≥3), aiming to enhance heat exchange efficiency by increasing the heat-conducting surface area. The heat-conducting central column and the heat-conducting base plate form a through-type heat conduction path, ensuring efficient and rapid heat removal.

[0024] Considering that the anodic heat deposition will be conducted to the heat-conducting base plate, thus affecting the efficiency of heat dissipation from the internal permanent magnet to the outside, as an improvement to the technical solution, such as Figure 1 As shown, the heat-conducting base plate 1 is provided with multiple hollow areas 4 that are larger than the anode bottom components (including anode columns, gas distributor columns, anode fastening bolts, etc.) of the permanent magnet Hall thruster. The hollow areas 4 prevent the heat-conducting base plate from directly contacting the anode base plate components, which can effectively reduce the impact of the anode on the heat dissipation effect of the inner permanent magnet area.

[0025] As an improvement to the technical solution, such as Figure 1 As shown, the heat-conducting ribs 3 are uniformly arranged along the circumference of the heat-conducting base plate 1.

[0026] like Figure 2 As shown, the present invention also provides a permanent magnet Hall thruster support base, comprising: a support base body 5 and the aforementioned heat-conducting bracket, wherein the heat-conducting bracket is nested within the support base body 5 to conduct heat from the inner permanent magnet region to the outer permanent magnet region, and the support base body 5 is used to fix the heat-conducting bracket and other magnetic circuit structure components. Preferably, the support base body 5 is made of stainless steel or high-strength non-magnetic material to ensure the strength and stability of the structure.

[0027] This permanent magnet Hall thruster support base integrates a heat-conducting bracket into the support base body without affecting the thruster's magnetic circuit structure. This effectively transfers heat from the inner permanent magnet area to the outer permanent magnet area, improving the consistency of the operating temperature of the inner and outer permanent magnets of the thruster. The support base balances structural strength and heat conduction requirements. The support base body mainly provides vibration and deformation resistance, while the heat-conducting bracket focuses on thermal management. The non-magnetic properties of both work together to ensure that the magnetic field distribution of the thruster is not affected. In addition, the integrated heat-conducting bracket also offers high ease of installation.

[0028] As an improvement to the technical solution, such as Figure 2 As shown, the support base body 5 includes an inner permanent magnet mounting area 51 and an outer permanent magnet mounting area 52. The heat-conducting central column 2 of the heat-conducting bracket extends to the vicinity of the inner permanent magnet mounting area 51, and the heat-conducting ribs 3 of the heat-conducting bracket extend to the vicinity of the outer permanent magnet mounting area 52. Due to the high thermal conductivity of pure copper, most of the heat in the inner permanent magnet area will be conducted to the bottom of the thruster through the heat-conducting central column. When the heat reaches the heat-conducting base plate, it is radiated outward through the base plate itself and effectively dissipated through the heat-conducting ribs integrally connected to the heat-conducting base plate. These heat-conducting ribs greatly enhance heat dissipation and strengthen the conduction of temperature from the inner permanent magnet area to the outer permanent magnet area. This heat dissipation method of inner permanent magnet area – heat-conducting central column – heat-conducting base plate – heat-conducting ribs – outer permanent magnet area ensures that the heat in the inner permanent magnet area can be efficiently dissipated, avoiding magnetic field distortion and deterioration of discharge conditions caused by local overheating in the inner permanent magnet area.

[0029] This invention also discloses a method for improving the working temperature consistency of the inner and outer permanent magnets of a permanent magnet Hall thruster. The method utilizes the aforementioned permanent magnet Hall thruster support base to conduct heat from the inner permanent magnet area to the outer permanent magnet area, thereby reducing the working temperature difference between the inner and outer permanent magnets and improving the working temperature consistency of the inner and outer permanent magnets.

[0030] Example 1 Based on the above structural design, a copper heat-conducting bracket with k=6 is adopted, and a stainless steel support base is used as the main body. Ansys thermal simulation analysis yielded the following results: Figure 3 , Figure 4 The temperature comparison diagram shown below, in which, Figure 3 This is a schematic diagram of the local temperature without this heat-conducting bracket installed. Figure 4 This is a schematic diagram of the local temperature when the thermally conductive bracket is installed. Simulation results show that, under the same input conditions, the copper thermally conductive bracket efficiently dissipates heat from the inner permanent magnet and promotes uniform heat dissipation in the outer permanent magnet region, resulting in a decrease of 80℃~100℃ in the operating temperature difference between the inner and outer permanent magnets. This significantly improves the consistency of the operating temperature between the inner and outer permanent magnets and reduces heat deposition in the inner permanent magnet region.

[0031] This design employs an integrated structure of a pure copper thermally conductive base plate, a thermally conductive central column, and thermally conductive fins nested within a stainless steel support base. Utilizing the high thermal conductivity and non-magnetic properties of pure copper, and through a through-type heat conduction path and fin design that increases the heat dissipation surface area, heat from the inner permanent magnet region is efficiently transferred to the outer permanent magnet region. Ansys simulations have verified that after installing this thermally conductive bracket, the operating temperature difference between the inner and outer permanent magnets can be reduced by 80℃~100℃, significantly improving operating temperature consistency and preventing magnetic field distortion and deterioration of discharge conditions caused by localized overheating. This invention balances structural strength and heat dissipation efficiency, is applicable to various types of permanent magnet Hall thrusters, provides a key thermal management solution for the high-reliability heat dissipation requirements of the aerospace field, and can promote the development of lightweight, long-life Hall electric propulsion technology.

[0032] Although preferred embodiments of this application have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments as well as all changes and modifications falling within the scope of this application.

[0033] Obviously, those skilled in the art can make various modifications and variations to this application without departing from the spirit and scope of this application. Therefore, if such modifications and variations fall within the scope of the claims of this application and their equivalents, this application also intends to include such modifications and variations.

Claims

1. A heat-conducting bracket for a permanent magnet Hall thruster, characterized in that, include: The heat-conducting base plate (1), the heat-conducting central column (2), and the heat-conducting ribs (3) are provided. The heat-conducting central column (2) is vertically connected to the middle of the heat-conducting base plate (1). The heat-conducting ribs (3) are multiple and spaced apart along the circumference of the heat-conducting base plate (1). The heat-conducting base plate (1), the heat-conducting central column (2), and the heat-conducting ribs (3) are an integrated structure. They are used to fit and be nested in the support base body (5) of the permanent magnet Hall thruster, and to conduct the heat in the inner permanent magnet area to the outer permanent magnet area in sequence through the heat-conducting central column (2), the heat-conducting base plate (1), and the heat-conducting ribs (3).

2. The permanent magnet Hall thruster heat conduction bracket according to claim 1, characterized in that, The heat-conducting base plate (1), the heat-conducting central column (2), and the heat-conducting fins (3) are made of pure copper.

3. The permanent magnet Hall thruster heat conduction bracket according to claim 1, characterized in that, The heat-conducting base plate (1) is provided with multiple hollow areas (4) that are larger than the anode bottom component of the permanent magnet Hall thruster.

4. The permanent magnet Hall thruster heat conduction bracket according to claim 1, characterized in that, The heat-conducting ribs (3) are uniformly arranged along the circumference of the heat-conducting base plate (1).

5. A permanent magnet Hall thruster support base, characterized in that, include: The support base body (5) and the heat-conducting bracket according to any one of claims 1 to 4, wherein the heat-conducting bracket is nested within the support base body (5) for discharging heat from the inner permanent magnet region to the outer permanent magnet region.

6. The permanent magnet Hall thruster support base according to claim 1, characterized in that, The support base body (5) includes an inner permanent magnet mounting area (51) and an outer permanent magnet mounting area (52). The heat-conducting central column (2) of the heat-conducting bracket extends to the vicinity of the inner permanent magnet mounting area (51), and the heat-conducting ribs (3) of the heat-conducting bracket extend to the vicinity of the outer permanent magnet mounting area (52).

7. A method for improving the uniformity of working temperature of the inner and outer permanent magnets in a permanent magnet Hall thruster, characterized in that: The permanent magnet Hall thruster support base described in claim 5 or 6 is used to conduct heat from the inner permanent magnet area to the outer permanent magnet area, thereby reducing the temperature difference between the inner and outer permanent magnets and improving the consistency of the working temperature of the inner and outer permanent magnets.

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