阅读说明：本技术 一种磁聚焦场致发射微电推进装置 (Micro-electric propulsion device for magnetic focusing field emission ) 是由 罗杨 高辉 王东魏 季朦 王忠晶 许诺 于 2021-06-11 设计创作，主要内容包括：本申请揭示了一种磁聚焦场致发射微电推进装置,包括推进剂存储腔、支撑连接结构、绝缘基底、发射极、绝缘支撑结构、栅极和环形磁铁,支撑连接结构安装于推进剂存储腔的输出端,发射极通过绝缘基底安装于支撑连接结构上,支撑连接结构、绝缘基底的通孔与推进剂存储腔的输出孔贯通；栅极通过绝缘支撑结构安装于支撑连接结构上方,绝缘支撑结构的高度高于栅极和绝缘基底的高度之和,栅极和发射极间隔设置,发射极位于绝缘支撑结构、栅极以及绝缘基板之间形成的空间内；环形磁铁套设于绝缘支撑结构上。本申请在装置电极附近增加电磁场,对产生的离子束流约束,驱使离子束流沿轴向方向喷出形成推力,有效降低羽流发散程度,减小羽流发散带来的推力损失。(The application discloses a magnetic focusing field emission micro-electric propulsion device which comprises a propellant storage cavity, a supporting and connecting structure, an insulating substrate, an emitter, an insulating supporting structure, a grid and a ring magnet, wherein the supporting and connecting structure is installed at the output end of the propellant storage cavity; the grid is arranged above the supporting and connecting structure through an insulating supporting structure, the height of the insulating supporting structure is higher than the sum of the heights of the grid and the insulating substrate, the grid and the emitter are arranged at intervals, and the emitter is positioned in a space formed among the insulating supporting structure, the grid and the insulating substrate; the annular magnet is sleeved on the insulating support structure. The electromagnetic field is added near the electrode of the device, the generated ion beam current is constrained, the ion beam current is driven to be sprayed out along the axial direction to form thrust, the plume divergence degree is effectively reduced, and the thrust loss caused by plume divergence is reduced.)

1. A magnetically focused field emission micro-electric propulsion device comprising a propellant storage chamber, a support connection structure, an insulating base, an emitter electrode, an insulating support structure, a grid electrode and a ring magnet, wherein:

the support connecting structure is arranged at the output end of the propellant storage cavity, the emitter is arranged on the support connecting structure through the insulating substrate, through holes are formed in the support connecting structure and the insulating substrate, and the through holes L in the support connecting structure and the insulating substrate are communicated with the output hole of the propellant storage cavity and are coaxially arranged;

the grid electrode is arranged above the supporting and connecting structure through the insulating supporting structure, the height of the insulating supporting structure is higher than the sum of the heights of the grid electrode and the insulating substrate after being overlapped, the grid electrode and the emitter electrode are oppositely arranged at intervals, and the emitter electrode is positioned in a space formed among the insulating supporting structure, the grid electrode and the insulating substrate;

the annular magnet is sleeved on the insulating support structure.

2. A magnetically focused field emission micro-electric propulsion device according to claim 1, characterized in that the outer diameter of the ring magnet is the same as the outer diameter of the support connection structure and the ring magnet is mounted coaxially with the support connection structure.

3. A magnetic focusing field emission micro-electric propulsion device according to claim 1, wherein the insulating support structure comprises a support portion and a carrying portion for carrying the grid, the carrying portion and the support portion have the same inner diameter and are coaxially arranged, and the outer diameter of the carrying portion is larger than the outer diameter of the support portion;

an annular space is formed among the bearing part, the outer diameter wall of the supporting part and the supporting and connecting structure, and the annular magnet is contained in the annular space.

4. A magnetically focused field emission micro-electric propulsion device according to claim 1, characterised in that the end of the ring magnet remote from the grid is mounted on the support connection structure.

5. A magnetic focusing field emission micro electric propulsion device according to claim 1, wherein the inner diameter of the ring magnet matches the outer diameter of the insulating support structure, and the inner diameter wall of the ring magnet fits snugly against the outer diameter wall of the insulating support structure.

6. The micro-electric propulsion device according to claim 1, wherein the ring magnet is a permanent magnet.

7. A magnetically focused field emission micro-electric propulsion device according to claim 1, characterized in that the ring magnet is an electromagnetic coil.

8. A magnetic focusing field emission micro-electric propulsion device according to claim 1, characterized in that the ring magnet is made of a rubidium iron boron magnet material.

9. A magnetically focused field emission micro-electric propulsion device according to claim 1, wherein the magnetic field formed by the ring magnet in the region between the grid and the emitter is directed upwards along the axis of the electric propulsion device and coincides with the electric field formed between the grid and the emitter.

10. The micro-electric propulsion device for magnetic focusing field emission according to claim 1, wherein the magnetic field formed by the ring magnet in the region between the grid and the emitter has a magnetic field strength of 0-0.1T.

Technical Field

The invention belongs to the technical field of space electric propulsion, and relates to a magnetic focusing field emission micro-electric propulsion device.

Background

The field emission micro-electric propulsion device has the advantages of simple structure, high efficiency, large specific impulse and the like, and is an ideal power device for a micro-nano small satellite platform in the future. During use, the propulsion device generally relies on a strong electric field between electrodes to ionize the propellant and eject the propellant under the action of the electric field force, so that the thrust is formed and acts on the satellite platform. The direction in which the propellant is ionized and ejected is determined primarily by the configuration of the electric field between the electrodes. The existing electric propulsion device design has the problems that a field divergence effect exists in a high-intensity electric field of ion beam current generated due to an electrode structure of the device, so that a plume divergence angle is overlarge, and further thrust loss, electrode ablation, propulsion efficiency reduction and the like are caused.

Disclosure of Invention

In order to solve the problems in the related art, the application provides a magnetic focusing field emission micro-electric propulsion device, which comprises the following technical scheme:

a magnetically focused field emission micro-electric propulsion device comprising a propellant storage chamber, a support connection structure, an insulating base, an emitter electrode, an insulating support structure, a grid electrode and a ring magnet, wherein:

the support connecting structure is arranged at the output end of the propellant storage cavity, the emitter is arranged on the support connecting structure through the insulating substrate, through holes are formed in the support connecting structure and the insulating substrate, and the through holes L in the support connecting structure and the insulating substrate are communicated with the output hole of the propellant storage cavity and are coaxially arranged;

the grid electrode is arranged above the supporting and connecting structure through the insulating supporting structure, the height of the insulating supporting structure is higher than the sum of the heights of the grid electrode and the insulating substrate after being overlapped, the grid electrode and the emitter electrode are oppositely arranged at intervals, and the emitter electrode is positioned in a space formed among the insulating supporting structure, the grid electrode and the insulating substrate;

the annular magnet is sleeved on the insulating support structure.

Optionally, the outer diameter of the ring magnet is the same as the outer diameter of the support connection structure, and the ring magnet and the support connection structure are coaxially mounted.

Optionally, the insulating support structure includes a support portion and a bearing portion for bearing the gate, the bearing portion and the support portion have the same inner diameter and are coaxially disposed, and an outer diameter of the bearing portion is larger than an outer diameter of the support portion; an annular space is formed among the bearing part, the outer diameter wall of the supporting part and the supporting and connecting structure, and the annular magnet is contained in the annular space.

Optionally, one end of the ring magnet, which is far away from the gate, is mounted on the support connection structure.

Optionally, the inner diameter of the ring magnet is matched with the outer diameter of the insulating support structure, and the inner diameter wall of the ring magnet is attached to the outer diameter wall of the insulating support structure.

Optionally, the ring magnet is a permanent magnet.

Optionally, the ring magnet is an electromagnetic coil.

Optionally, the ring magnet is made of a rubidium-iron-boron magnet material.

Optionally, the magnetic field formed by the ring magnet in the region between the grid and the emitter is upward along the axial direction of the electric propulsion device and is consistent with the direction of the electric field formed between the grid and the emitter.

Optionally, the magnetic field intensity of the magnetic field formed by the annular magnet in the region between the gate and the emitter is 0-0.1T.

Based on the technical scheme, the application can at least realize the following beneficial effects:

by adding the additional electromagnetic field near the electrode of the device, the generated ion beam current is restrained, the ion beam current is driven to be sprayed out along the axial direction to form thrust, the plume divergence degree is effectively reduced, and the thrust loss caused by the plume divergence is reduced; the thrust level of the field emission micro-electric propulsion device is improved, and the structure is simple and reliable.

It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the invention, as claimed.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the invention and together with the description, serve to explain the principles of the invention.

Fig. 1 is a schematic view of a magnetically focused field emission micro-electric propulsion device provided in one embodiment of the present application;

fig. 2 is a schematic diagram of the magnetic focusing principle of the magnetic focusing field emission micro-electric propulsion device provided in fig. 1.

The reference numbers are as follows:

1. a propellant storage chamber; 2. a support connection structure; 3. an insulating substrate; 4. an emitter; 5. an insulating support structure; 6. a gate electrode; 7. a ring magnet.

Detailed Description

Reference will now be made in detail to the exemplary embodiments, examples of which are illustrated in the accompanying drawings. When the following description refers to the accompanying drawings, like numbers in different drawings represent the same or similar elements unless otherwise indicated. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present invention. Rather, they are merely examples of apparatus and methods consistent with certain aspects of the invention, as detailed in the appended claims.

Fig. 1 is a schematic view of a magnetic focusing field emission micro-electric propulsion device provided in an embodiment of the present application, which includes a propellant storage chamber 1, a support connection structure 2, an insulating base 3, an emitter 4, an insulating support structure 5, a grid 6 and a ring magnet 7, wherein the installation relationship of the components is as follows:

the support connecting structure 2 is installed at the output end of the propellant storage cavity 1, the emitter 4 is installed on the support connecting structure 2 through the insulating substrate 3, through holes are formed in the support connecting structure 2 and the insulating substrate 3, and the through holes L in the support connecting structure 2 and the insulating substrate 3 are communicated with the output hole of the propellant storage cavity 1 and are coaxially arranged. The propellant in the storage chamber 1 can pass through the outlet opening directly into the pores of the porous material of the emitter electrode 4. Propellant is continuously emitted by ionization at the emitter electrode 4 and propellant in the storage chamber 1 is continuously replenished into the emitter electrode 4.

The grid 6 is arranged above the supporting and connecting structure 2 through the insulating supporting structure 5, the height of the insulating supporting structure 5 is higher than the sum of the heights of the grid 6 and the insulating substrate 3 after being superposed, the grid 6 and the emitter 4 are oppositely arranged at intervals, the emitter 4 is positioned in a space formed among the insulating supporting structure 5, the grid 6 and the insulating substrate, an emitter cone is arranged on the emitter 4, and the grid 6 is ensured not to be contacted with the tip of the emitter cone through the superposed height difference of the insulating supporting structure 5, the grid 6 and the insulating substrate 3. The propellant is ionized at the tip of the emitter cone and is accelerated by the electric field between the grid 6 and the emitter 4. The emitter 4 is a porous metal material with a pore diameter of only a few micrometers, so that the liquid propellant can move to the top of the emission cone of the emitter 4 under the action of the capillary force of the porous material and then be ionized under the action of a strong electric field.

The annular magnet 7 is sleeved on the insulating support structure 5.

In a possible implementation, the ring magnet 7 may be a permanent magnet. In another possible implementation, the ring magnet 7 may be an electromagnetic coil. In yet another possible implementation, the ring magnet 7 may also be made of a rubidium-iron-boron magnet material.

In practical implementation, in order to ensure that the outer diameter surface of the ring magnet 7 and the outer diameter surface of the support connection structure 2 are on the same circumferential surface, the outer diameter of the ring magnet 7 is the same as the outer diameter of the support connection structure 2, and the ring magnet 7 and the support connection structure 2 are coaxially mounted. The ring magnet is so set up can be when simplifying the structure, through the magnetic field that ring magnet formed, plays the constraint effect to the ion that produces between emitter and the grid, weakens the phenomenon of dispersing of electric field, and then makes the ion after the ionization can gather together more penetrate out.

Optionally, the insulating support structure 5 may include a support portion and a bearing portion for bearing the gate 6, the bearing portion and the support portion have the same inner diameter and are coaxially disposed, and an outer diameter of the bearing portion is larger than an outer diameter of the support portion; an annular space is formed among the bearing part, the outer diameter wall of the supporting part and the supporting and connecting structure 2, and the annular magnet 7 is accommodated in the annular space.

In other words, the ring magnet 7 is sleeved on the periphery of the supporting portion of the insulating supporting structure 5 and is fastened between the bearing portion and the supporting connecting structure 2, so as to ensure the firmness of the ring magnet 7. The magnetic field formed by the annular magnet in the area between the grid 6 and the emitter 4 is upward along the axial direction of the electric propulsion device and is consistent with the direction of the electric field formed between the grid 6 and the emitter 4, so that a magnetic field capable of stably restraining ions generated between the emitter 6 and the grid 4 is formed between the grid 6 and the emitter 4, and the ionized ions are ensured to be gathered and ejected in the restraining direction by controlling the restraining direction in which the ions are gathered and ejected.

Preferably, the magnetic field intensity of the magnetic field formed by the annular magnet in the region between the grid and the emitter is 0-0.1T, and the magnetic field is matched with a strong electric field (about 10 kV) applied between the emitter and the grid, so that the interference on other equipment can be avoided while ions are gathered.

In another possible implementation, an end of the ring magnet 7 remote from the grid 6 is mounted on the support and connection structure 2.

Optionally, the inner diameter of the ring magnet 7 is matched with the outer diameter of the insulating support structure 5, and the inner diameter wall of the ring magnet 7 is attached to the outer diameter wall of the insulating support structure 5. The size of the whole electric propulsion device can be reduced to a certain extent by the fitting and installation of the annular magnet and the insulating support structure, so that the electric propulsion device can be applied to a micro-nano small satellite platform, and the application range of the electric propulsion device is expanded.

The annular magnet 7 can be a permanent magnet, the permanent magnet can generate a magnetic field required by restricting the plume without external power supply, the permanent magnet is of an annular structure, the magnetic field formed in the region between the grid 6 and the emitter 4 can be ensured to be upward along the axial direction of the electric propulsion device, as shown in fig. 2, according to the motion theory of charged particles in the magnetic field, the magnetic field has a restriction effect on positively charged ions, the original motion track of the positively charged ions is changed, and the positively charged ions are driven to be spirally ejected along the axial direction. In the embodiment, the ring magnet can generate the magnetic field required by the electric field plume without external power supply, thereby simplifying the complexity of the circuit.

In summary, the magnetic focusing field emission micro-electric propulsion device provided by the application realizes the restraint of the generated ion beam current by adding the additional electromagnetic field near the electrode of the device, drives the ion beam current to be sprayed out along the axial direction to form thrust, effectively reduces the plume divergence degree, reduces the thrust loss caused by the plume divergence and improves the propulsion efficiency; the thrust level of the field emission micro-electric propulsion device is improved, and the structure is simple and reliable.

On the other hand, the additional magnetic field is generated by the permanent magnet, so that the beam effect is improved, and the requirement of system power supply driving is not increased.

In order to make the technical solution of the present invention more clearly understood by those skilled in the art, the working principle of the present invention is described as follows:

the magnetic focusing field emission micro-electric propulsion device provided by the invention ionizes the propellant at the top of the emitter by applying a strong electric field (about 10kV, such as 9-11kV) between the emitter and the grid, positively charged ions formed by ionization move from the emitter to the grid at high speed under the action of the strong electric field and pass through the grid hole to form ion flow to be ejected out to form thrust, an additional magnetic field simultaneously acts on the moving plasma to generate Lorentz force on the moving plasma, the radial motion of the plasma is constrained to the axial direction, the divergence of the ion flow is further constrained, the magnetic focusing effect is generated, and the plume divergence angle of the propulsion device is reduced.

Other embodiments of the invention will be apparent to those skilled in the art from consideration of the specification and practice of the invention disclosed herein. This application is intended to cover any variations, uses, or adaptations of the invention following, in general, the principles of the invention and including such departures from the present disclosure as come within known or customary practice within the art to which the invention pertains. It is intended that the specification and examples be considered as exemplary only, with a true scope and spirit of the invention being indicated by the following claims.

It will be understood that the invention is not limited to the precise arrangements described above and shown in the drawings and that various modifications and changes may be made without departing from the scope thereof. The scope of the invention is limited only by the appended claims.