CN105889006B - A kind of hall thruster ceramic heat-dissipating holder - Google Patents

Abstract

The invention discloses a Hall thruster ceramic heat dissipation bracket, which relates to the field of Hall thruster ceramic heat dissipation. The problem that the existing Hall thruster has poor heat dissipation and reduces the performance and working stability of the thruster is solved. It includes a barrel-shaped structure, the upper port of the barrel-shaped structure is provided with an outer convex edge, and an inner sleeve is arranged on the inner bottom surface of the barrel of the barrel-shaped structure, the inner sleeve is coaxial with the barrel-shaped structure, and the inner sleeve The barrel runs through the bottom surface of the barrel-shaped structure, the height of the inner sleeve is lower than that of the barrel-shaped structure, and a plurality of circular or rectangular hollow structures are evenly arranged along the circumferential direction of the barrel-shaped structure barrel wall. It is mainly used to dissipate heat from the Hall thruster.

Description

A Hall thruster ceramic cooling bracket

technical field

The invention relates to the field of Hall thruster ceramic heat dissipation.

Background technique

The Hall thruster is an electric propulsion device widely used at present. Compared with the traditional chemical propulsion device, it has the advantages of high efficiency, high specific impulse and long life. Its working principle is: there are mutually orthogonal radial magnetic fields and axial electric fields in the channel of the Hall thruster. The electrons emitted from the cathode into the channel drift to the anode under the action of the magnetic field and electric field, and are ejected from the gas distributor. The working medium gas undergoes impact ionization, and the ionized electrons are confined in the channel by the radial magnetic field due to their small mass, while the ion mass is large, and the magnetic field basically has no effect on it. out, thereby generating thrust.

The heat source of the Hall thruster in the working process is mainly composed of two parts. One part is that the ions are not ejected out of the channel during the process of accelerating towards the outlet under the action of the electric field force, but are sputtered onto the wall surface, and the ion energy is converted. The other part is the heat generated when the electrons drift to the anode under the action of the electric field and magnetic field, and the electrons recombine with the anode.

These two parts of heat make the wall temperature of the ceramic channel higher, and conduct heat conduction and heat radiation to the magnetic circuit and coil at the same time, resulting in high temperature of the magnetic circuit and coil, and high coil temperature will accelerate the aging of the coil insulation or even burn out Phenomenon, the high temperature of the magnetic circuit will cause the magnetic permeability to drop rapidly, and the combined action of the two will change the magnetic field position and magnetic field intensity of the thruster, thereby reducing the performance and working stability of the thruster.

Contents of the invention

The purpose of the present invention is to solve the poor heat dissipation performance of the existing Hall thruster, which reduces the performance and working stability of the thruster, and provides a ceramic heat dissipation bracket for the Hall thruster.

A Hall thruster ceramic cooling bracket, which includes a barrel-shaped structure, the upper port of the barrel-shaped structure is provided with a convex edge,

An inner sleeve is provided on the inner bottom surface of the drum-shaped structure, the inner sleeve is coaxial with the drum-shaped structure, and the inner sleeve runs through the bottom surface of the drum-shaped structure,

the height of the inner sleeve is lower than the height of the barrel-shaped structure,

A plurality of circular or rectangular hollow structures are evenly arranged along the circumferential direction of the barrel wall of the barrel-shaped structure.

The thermal bracket is implemented in copper.

The outer wall of the barrel-shaped structure is painted.

The protruding edge is uniformly provided with 4 installation through holes along the circumferential direction of the barrel-shaped structure.

During the working process of the Hall thruster, the bombardment of ions on the wall surface and the recombination of electrons and anodes will cause a large amount of heat deposition in the ceramic channel, making the temperature of the ceramic channel higher, and this part of the heat will transfer the heat on the inner wall of the channel through thermal radiation. The heat is transferred to the coil, and the heat is transferred to the outer magnetic pole and the bottom plate through heat conduction, so that the temperature of the magnetic circuit structure increases, thereby reducing the magnetic permeability of the magnetic circuit, and even reaching a state of magnetic saturation, which seriously reduces the performance of the thruster. At the same time Coil temperature is too high will reduce the service life of the insulation, or even burn out. Therefore, the present invention alleviates the thermal environment of the ceramic channel through two ways of heat conduction and heat radiation, and improves the performance and working stability of the thruster.

The beneficial effect brought by the present invention is that, by adopting the hollowed-out ceramic cooling bracket, it not only plays the role of installing the ceramic channel, but makes the outer surface of the ceramic channel directly radiate to the space environment, and at the same time, the cooling bracket selects materials with high thermal conductivity and performs surface treatment , increase the heat dissipation capacity of the ceramic channel, minimize the contact area between the heat dissipation bracket and the outer magnetic pole, and reduce the heat transfer from the ceramic channel to the coil and magnetic circuit, thereby playing a protective role, reducing the temperature of the coil and magnetic circuit, and improving Thruster life and working stability.

Description of drawings

Fig. 1 is a schematic structural view of a Hall thruster ceramic cooling bracket according to the present invention;

Fig. 2 is a diagram of the relative position relationship between a Hall thruster ceramic cooling bracket and the Hall thruster according to the present invention; wherein, the reference numeral 6 represents the inner magnetic pole, the reference numeral 7 represents the bottom plate, and the reference numeral 8 represents The outer coil, the reference numeral 9 represents the outer iron core, the reference numeral 10 represents the outer magnetic pole, the reference numeral 11 represents the ceramic channel, the reference numeral 12 represents the magnetic shield, the reference numeral 13 represents the inner coil, and the reference numeral 14 represents the inner iron core.

Detailed ways

Specific embodiment 1: Refer to Fig. 1 to illustrate this embodiment, a Hall thruster ceramic cooling bracket described in this embodiment, it includes a barrel-shaped structure 1, and the upper port of the barrel-shaped structure 1 is provided with a convex edge 2,

An inner sleeve 3 is provided on the inner bottom surface of the barrel of the barrel-shaped structure 1, the inner sleeve 3 is coaxial with the barrel-shaped structure 1, and the inner sleeve 3 runs through the bottom surface of the barrel-shaped structure 1,

The height of the inner sleeve 3 is lower than the height of the barrel-shaped structure 1,

A plurality of circular or rectangular hollow structures are evenly arranged along the circumferential direction of the barrel wall of the barrel-shaped structure 1 .

In this embodiment, in the process of use, specifically referring to FIG. 2 , the ceramic channel 11 of the thruster is located between the inner wall of the barrel-shaped structure 1 and the outer wall of the inner sleeve 3 , and the outer magnetic pole 10 and the convex pole are connected by bolts. Make a fixed connection along 2. The ceramic channels 11 are arranged on the heat dissipation bracket, and play the role of installing ceramics. The bottom of the inner sleeve 3 is flush with the barrel outer bottom surface of the barrel-shaped structure 1 .

A plurality of circular or rectangular hollow structures are evenly arranged along the circumferential direction of the barrel wall of the cylindrical structure 1, which increases the heat radiation area of the ceramic channel, and the heat is scattered to the surrounding environment through the hollow structures, improving the thruster performance and job stability.

The ceramic heat dissipation bracket is a hollow structure, and the hollow area is increased as much as possible under the guarantee of strength, so that the ceramic channel can directly radiate heat to the space environment, improve the heat dissipation capacity of the ceramic channel, reduce the heat deposition on the channel, and then reduce The temperature of the small ceramic channel.

The design of the outer convex edge 2 makes the contact area between the ceramic cooling bracket and the outer magnetic pole small, reducing the heat from the cooling bracket to the outer magnetic pole through heat conduction to the outer magnetic pole, thereby reducing the temperature of the outer magnetic pole and the magnetic circuit, ensuring its Magnetic permeability, so as to ensure the working stability of the thruster.

Embodiment 2: The difference between this embodiment and the Hall thruster ceramic heat dissipation support described in Embodiment 1 is that the heat dissipation support is realized by copper.

In this embodiment, the ceramic cooling bracket is made of high thermal conductivity material "copper" to increase the heat conduction from the ceramic channel to the cooling bracket.

Embodiment 3: The difference between this embodiment and the Hall thruster ceramic cooling bracket described in Embodiment 1 is that the outer wall surface of the barrel-shaped structure 1 is painted.

In this embodiment, the outer wall of the cylindrical structure 1 is sprayed with paint, and the surface of the ceramic heat dissipation support is treated to increase the surface emissivity, so that the heat transmitted from the ceramic to the heat dissipation support is better radiated to the space environment, thereby reducing The temperature of the ceramic channel.

Embodiment 4: The difference between this embodiment and the Hall thruster ceramic cooling bracket described in Embodiment 1 is that the convex edge 2 is uniformly arranged along the circumferential direction of the barrel-shaped structure 1 4 mounting through holes4.

In this embodiment, when the ceramic channel 11 is placed on the cooling bracket, the bolts are passed through the through holes 4 so that the outer magnetic pole 10 is fixedly connected to the outer convex edge 2 .

Claims (4)

1. A Hall thruster ceramic cooling bracket is characterized in that it comprises a barrel-shaped structure (1), and the upper port of the barrel-shaped structure (1) is provided with an outer convex edge (2), An inner sleeve (3) is provided on the inner bottom surface of the barrel of the barrel-shaped structure (1), the inner sleeve (3) is coaxial with the barrel-shaped structure (1), and the inner sleeve (3) runs through the barrel-shaped the bottom surface of structure (1), The height of the inner sleeve (3) is lower than the height of the barrel-shaped structure (1), A plurality of circular or rectangular hollow structures are evenly arranged along the circumferential direction of the barrel wall of the barrel-shaped structure (1). 2. A Hall thruster ceramic cooling bracket according to claim 1, characterized in that the cooling bracket is made of copper. 3. A Hall thruster ceramic cooling bracket according to claim 1, characterized in that the outer wall surface of the barrel-shaped structure (1) is painted. 4. A Hall thruster ceramic cooling bracket according to claim 1, characterized in that, said convex edge (2) is evenly provided with four along the circumferential direction of the barrel-shaped structure (1) Install through holes (4).