Combined multi-modal ion gate

Abstract

The utility model discloses a combined multi-mode ion grid electrode, comprising a screen grid and an acceleration grid, the screen grid is connected with an upstream ionization chamber, the screen grid is provided with a plurality of first through holes with parallel axes, and the first through holes form a first lead-out channel for leading out cations in plasma; the acceleration grid is located at the downstream of the screen grid and is spaced from the screen grid, a plurality of second through holes are formed in the acceleration grid, the second through holes form second leading-out channels for leading out positive ions in the plasma, the number of the second through holes is consistent with that of the first through holes, each second through hole is coaxial with one first through hole in the screen grid, and the first through holes are communicated with the first through holes in the screen grid. A cavity is formed in the acceleration grid, the cavity is not communicated with the second through hole, the cavity is communicated with a cold air source through a cold air connector in the surface of the acceleration grid, and a miniature conical spray pipe penetrating through the surface of the acceleration grid is arranged on the end face, away from the screen grid, in the cavity. According to the utility model, simple switching of multiple propulsion modes is realized under the condition that the weight of the grid electrode is not increased.

Description

Technical Field

[0001] The utility model relates to a combined multi-mode ion grid system, which provides propulsion performance in multiple working modes for a satellite thruster and belongs to the field of aerospace technology. Background Art

[0002] The diversity and complexity of space missions have led to a wide variety of incompatible space propulsion technologies. Against the backdrop of low-cost commercial space development, space combined propulsion technology has become an important technology development route, such as ion Hall combined thrusters, multi-ring Hall thrusters, etc.

[0003] Chinese invention patent CN115355145A discloses a micro-newton variable thruster based on gas field ionization enhancement, which realizes two working modes. However, this solution has the following limitations:

[0004] First, it can only provide thrust in the μN range, which limits the scope of application;

[0005] Second, due to the structural design of the cold gas thruster micro-nozzle located downstream of the carbon nanotube field ionization thruster, it is impossible to achieve a complete cold gas propulsion and ion propulsion parallel mode (because when the cold gas flow rate increases, the gas working fluid as the propellant cannot be effectively and completely ionized, but can only be partially ionized, resulting in the ion propulsion mode not being able to work efficiently);

[0006] Third, the structure of the carbon nanotube field ionization thruster is relatively complex, which affects its reliability;

[0007] Fourth, the design of the cold gas thruster micro-nozzle located downstream of the carbon nanotube field ionization thruster leads to an increase in the axial size, which limits the application occasions;

[0008] Fifth, the switching of ion propulsion mode depends on the cold gas propulsion mode. When switching from the cold gas propulsion mode to the ion propulsion mode, the cold gas thruster micronozzle and the carbon nanotube field ionization thruster need to work synchronously, and the switching process is relatively complicated.

[0009] The existing technical solutions for increasing propulsion modes have technical difficulties to varying degrees, such as complex working mode switching and significant increase in size. These technical problems pose greater technical challenges to the overall design. Summary of the invention

[0010] The utility model aims to provide a combined multi-mode ion grid to cope with the complexity of deep space exploration missions, realize simple switching of multiple propulsion modes and parallel operation of multiple modes without increasing the weight and complexity of the grid, expand the magnitude range of thrust and be stable and reliable.

[0011] In order to achieve the above purpose, the utility model adopts the following technical solutions:

[0012] Combined multi-modal ion grid, including:

[0013] A screen grid, the screen grid is connected to the upstream ionization chamber, and a plurality of first through holes with parallel axes are formed on the screen grid, the first through holes forming a first extraction channel for extracting positive ions in the plasma;

[0014] An acceleration grid is provided, the acceleration grid is located downstream of the screen grid and is spaced apart from the screen grid, a plurality of second through holes are provided on the acceleration grid, the second through holes constitute a second extraction channel for extracting cations in the plasma, the number of the second through holes is consistent with the number of the first through holes, each of the second through holes is coaxial with a first through hole on the screen grid, a cavity is provided inside the acceleration grid, the cavity is not connected with the second through holes, and the cavity is connected with a cold air source through a cold air interface on the surface of the acceleration grid, and a micro-conical nozzle penetrating the surface of the acceleration grid is provided on the end surface of the cavity away from the screen grid.

[0015] As an option, the screen grid and the acceleration grid are in the shape of disks.

[0016] As an option, the first through holes are distributed on a plurality of concentric regular hexagonal edges and vertices on the end surface of the screen grid, as well as at the center of the regular hexagon;

[0017] The second through holes are distributed on a plurality of concentric regular hexagonal edges and vertices on the end face of the acceleration gate, as well as at the center of the regular hexagon.

[0018] Furthermore, the first through hole and the second through hole are both circular holes, and the aperture of the first through hole is larger than the aperture of the second through hole.

[0019] As an option, the diameter of the first through hole is 1.7 mm to 2.4 mm, and the diameter of the second through hole is 1 mm to 1.5 mm.

[0020] As an option, the micro-cone nozzle is a Laval nozzle.

[0021] As an option, the cavity intersects with but is not connected to the second through hole, and the second through hole is located within the outer contour area of ​​the cavity.

[0022] As an option, the micro-conical nozzles are distributed at the vertices of a regular hexagon centered at the center of the second through hole.

[0023] Compared with the prior art, the utility model realizes the design of a dual-mode ion grid system by arranging a cold air propulsion structure downstream of the ion grid system, and its advantages include the following four aspects:

[0024] First, the number of propulsion modes increases, and both the ion propulsion mode and the cooling propulsion mode are available, which meets the needs of coping with the complexity of deep space exploration missions. When the solution of the utility model is applied to the ion thruster, its working range is wide, and it can provide thrust of the order of mN to N, which is suitable for deep space exploration and satellite attitude control. When the cold gas propulsion mode is adopted, its thrust is greater, for example, the thrust is increased to the order of 10N.

[0025] Second, for the propulsion system, the structural weight of the thruster is simplified, but the size is not significantly increased. The cold gas propulsion mode utilizes the inherent structure of the acceleration grid in the ion propulsion mode, without adding extra deadweight and structural complexity.

[0026] Third, it is easier to switch between propulsion modes. The cold gas propulsion mode and the ion propulsion mode are relatively independent and do not affect each other. The switching process does not need to consider the working conditions of the other working mode, which is more reliable.

[0027] Fourth, the two propulsion modes can truly work in parallel, that is, the ion propulsion mode and the cooling propulsion mode can be enabled at the same time to expand the adjustable thrust range. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 It is a three-view diagram of the combined multi-modal ion grid system;

[0029] Figure 2 is a front view of a combined multi-modal ion grid system;

[0030] Figure 3 is a side cross-sectional view of a combined multi-modal ion grid system;

[0031] Figure 4 It is a schematic diagram of the working principle of the ion propulsion mode of the combined multi-mode ion grid system;

[0032] Figure 5 It is a schematic diagram of the working principle of the cold gas propulsion mode of the combined multi-mode ion grid system;

[0033] Figure 6 It is a cross-sectional view of the cold gas flow channel of the combined multi-mode ion grid system;

[0034] In the figure: 1 - screen grid; 2 - acceleration grid; 3 - cooling interface; 4 - micro-conical nozzle. DETAILED DESCRIPTION

[0035] The present invention is further described below in conjunction with the accompanying drawings and specific embodiments, but it should not be understood that the scope of the subject matter described in the present invention is limited to the following embodiments. Without departing from the above-mentioned technical ideas of the present invention, various modifications, substitutions and changes made according to the common technical knowledge and customary means in the field are included in the scope of the present invention.

[0036] like Figures 1 to 6 As shown, a combined multi-modal ion grid system provided in this embodiment includes a screen grid 1 and an acceleration grid 2 arranged at intervals.

[0037] The screen grid 1 is located upstream of the acceleration grid 2 (the upstream here refers to the flow direction of cations in the reference plasma, and the downstream used later is the same), connected to the ionization chamber, and in contact with the plasma in the ionization chamber. When the grid system is in the ion propulsion mode, such as Figure 4 , screen grid 1 is connected to a high voltage (1 kV level), and acceleration grid 2 is connected to a low voltage (-100 V level). Screen grid 1 draws out the positive ions in the plasma and discharges them to the downstream acceleration grid 2, while acceleration grid 2 uses the potential difference between the two grids to accelerate the positive ions and discharge them out of the grid system to generate thrust. When the grid system is in the cold gas propulsion mode, such as Figure 5 , the screen grid 1 and the acceleration grid 2 are grounded, and the grid system cannot extract positive ions from the ionization chamber. The cold air enters the cold air propulsion flow channel (i.e., the cavity inside the acceleration grid 2) inside the acceleration grid 2 from the cold air interface 3 on the acceleration grid 2, and then is discharged from the micro-conical nozzle 4 (Laval nozzle in this embodiment) on the acceleration grid 2 to generate thrust.

[0038] like Figure 1 , Figure 2 and Figure 6 The screen grid 1 and the acceleration grid 2 are both in the shape of round cakes and are provided with through holes which correspond to each other and are distributed according to the edges and vertices of a regular hexagon. The aperture of the through hole on the screen grid 1 (1.7mm-2.4mm) is larger than the aperture of the through hole on the screen grid 2 (1mm-1.5mm).

[0039] like Figure 1 and Figure 6 A micro-conical nozzle 4 with the through hole on the acceleration grid 2 as the center and the vertices distributed according to a regular hexagon is provided on the downstream surface of the acceleration grid 2, a cold air propulsion flow channel is provided in the acceleration grid 2, and a cold air interface 3 is provided on the circumferential surface of the acceleration grid 2. The cold air interface 3 is connected to the micro-conical nozzle 4 set on the downstream surface of the acceleration grid 2 through the cold air propulsion flow channel.

[0040] The above are the main concepts of the present invention, and any combined multi-modal ion gate system designed based on the concept of the present invention falls within the protection scope of the present invention.

Claims

1. A combined multi-modal ion gate, characterized in that: include: A screen grid (1), the screen grid (1) is connected to an upstream ionization chamber, and a plurality of first through holes with parallel axes are formed on the screen grid (1), the first through holes forming a first extraction channel for extracting positive ions in the plasma; An acceleration grid (2) is located downstream of the screen grid (1) and is arranged at intervals from the screen grid (1). The acceleration grid (2) is provided with a plurality of second through holes, the second through holes forming a second extraction channel for extracting positive ions in the plasma, the number of the second through holes being the same as the number of the first through holes, each second through hole being coaxial with a first through hole on the screen grid (1), the acceleration grid (2) having a cavity inside, the cavity not being connected to the second through holes, and the cavity being connected to a cold air source via a cold air interface (3) on the surface of the acceleration grid (2), and a micro-conical nozzle (4) penetrating the surface of the acceleration grid (2) being provided on an end surface in the cavity away from the screen grid (1).

2. The combined multi-modal ion gate according to claim 1, characterized in that: The screen grid (1) and the acceleration grid (2) are in the shape of discs.

3. The combined multi-modal ion gate according to claim 1, characterized in that: The first through holes are distributed on a plurality of concentric regular hexagonal edges and vertices on the end face of the screen grid (1), as well as at the center of the regular hexagon; The second through holes are distributed on a plurality of concentric regular hexagonal edges and vertices on the end face of the acceleration grid (2), as well as at the center of the regular hexagon.

4. The combined multi-modal ion gate according to claim 3, characterized in that: The first through hole and the second through hole are both circular holes, and the aperture of the first through hole is larger than the aperture of the second through hole.

5. The combined multi-modal ion gate according to claim 4, characterized in that: The diameter of the first through hole is 1.7 mm to 2.4 mm, and the diameter of the second through hole is 1 mm to 1.5 mm.

6. The combined multi-modal ion gate according to claim 1, characterized in that: The micro-conical nozzle (4) is a Laval nozzle.

7. The combined multi-modal ion gate according to claim 1, characterized in that: The cavity intersects with but is not connected to the second through hole, and the second through hole is located within the outer contour area of ​​the cavity.

8. The combined multi-modal ion gate according to claim 1, characterized in that: The micro-conical nozzles (4) are distributed at the vertices of a regular hexagon centered at the center of the second through hole.

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