CN113212806A - Nanowire array electric thruster and thrust vector control method thereof - Google Patents
Nanowire array electric thruster and thrust vector control method thereof Download PDFInfo
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- CN113212806A CN113212806A CN202110647609.8A CN202110647609A CN113212806A CN 113212806 A CN113212806 A CN 113212806A CN 202110647609 A CN202110647609 A CN 202110647609A CN 113212806 A CN113212806 A CN 113212806A
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- 239000013598 vector Substances 0.000 title claims abstract description 53
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- 239000003380 propellant Substances 0.000 claims abstract description 44
- 230000005684 electric field Effects 0.000 claims abstract description 24
- 230000000149 penetrating effect Effects 0.000 claims abstract description 17
- 238000002955 isolation Methods 0.000 claims abstract description 12
- 239000000758 substrate Substances 0.000 claims description 59
- 238000005192 partition Methods 0.000 claims description 47
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- GWEVSGVZZGPLCZ-UHFFFAOYSA-N Titan oxide Chemical compound O=[Ti]=O GWEVSGVZZGPLCZ-UHFFFAOYSA-N 0.000 claims description 6
- XLOMVQKBTHCTTD-UHFFFAOYSA-N Zinc monoxide Chemical compound [Zn]=O XLOMVQKBTHCTTD-UHFFFAOYSA-N 0.000 claims description 6
- 238000003491 array Methods 0.000 claims description 5
- 239000000463 material Substances 0.000 claims description 5
- QPLDLSVMHZLSFG-UHFFFAOYSA-N Copper oxide Chemical compound [Cu]=O QPLDLSVMHZLSFG-UHFFFAOYSA-N 0.000 claims description 3
- 239000005751 Copper oxide Substances 0.000 claims description 3
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims description 3
- 239000000956 alloy Substances 0.000 claims description 3
- 229910045601 alloy Inorganic materials 0.000 claims description 3
- 229910052799 carbon Inorganic materials 0.000 claims description 3
- 239000002041 carbon nanotube Substances 0.000 claims description 3
- 229910021393 carbon nanotube Inorganic materials 0.000 claims description 3
- 239000000919 ceramic Substances 0.000 claims description 3
- 229910000431 copper oxide Inorganic materials 0.000 claims description 3
- 229910052751 metal Inorganic materials 0.000 claims description 3
- 239000002184 metal Substances 0.000 claims description 3
- 229910052750 molybdenum Inorganic materials 0.000 claims description 3
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- 239000010703 silicon Substances 0.000 claims description 3
- 229910052710 silicon Inorganic materials 0.000 claims description 3
- 239000004408 titanium dioxide Substances 0.000 claims description 3
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- 229910052721 tungsten Inorganic materials 0.000 claims description 3
- 239000010937 tungsten Substances 0.000 claims description 3
- 229910001930 tungsten oxide Inorganic materials 0.000 claims description 3
- 239000011787 zinc oxide Substances 0.000 claims description 3
- 239000007789 gas Substances 0.000 description 65
- 239000003570 air Substances 0.000 description 23
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 4
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- 230000000694 effects Effects 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/26—Guiding or controlling apparatus, e.g. for attitude control using jets
Abstract
The invention provides a nanowire array electric thruster and a thrust vector control method thereof, wherein the method comprises the following steps: a gas path component configured to perform the following actions: forming an air passage so that the propellant gas flows through the air passage components in sequence; a plurality of isolation modules configured to divide an air passage penetrating the nanowire array electric thruster into a plurality of air passages so that propellant gas flowing through the nanowire array electric thruster is divided into multiple paths; each path of propellant gas is ionized by a strong electric field between a nanowire array and a grid in the nanowire array electric thruster and is accelerated by the strong electric field to be ejected out to generate thrust; and the control module is configured to adjust the magnitude of the output thrust of each thrust output area by controlling the on-off of each air path or the gas flow or the voltage between the nanowire array and the grid according to different thrust vector adjustment requirements, so that the thrust vector adjustment of the nanowire array electric thruster is realized.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to a nanowire array electric thruster and a thrust vector control method thereof.
Background
Based on the nanowire array electric thruster, the gas propellant is ionized by a strong electric field between the nanowire array and the grid and is accelerated to be sprayed out to generate the thrust. The thruster has the characteristics of simple structure, wide thrust range, high specific impulse, capability of using various gases as propellants and the like, and is suitable for attitude control, orbit maintenance and transfer of satellites. Because the thrust direction of the thruster is generally the axial direction of the nozzle of the thruster, in order to meet the requirement of attitude and orbit control of the satellite on thrust vector adjustment, a plurality of thrusters are generally required to be installed in different directions of the satellite, or the thrust vector is changed in a mode of adjusting the nozzle orientation of the thruster through a vector adjusting mechanism, so that the effect of replacing a plurality of thrusters by one thruster is achieved; by adopting the scheme of the first thrust vector adjusting mechanism, a satellite needs to be provided with a plurality of thrusters, the mass and the cost of the satellite are increased, and although the quantity of the thrusters can be reduced, the thrust vector adjusting mechanism still occupies certain volume and mass, and the structural layout and the control algorithm have certain complexity, so that the reliability of the system is reduced.
Chinese patent application No. CN201980051270.6, ion thruster for thrust vector propulsion of spacecraft, discloses an ion thruster capable of thrust vector control, which is mainly suitable for thrusters in which the propellant is solid or liquid, but not for electric thrusters in which gas is used as the propellant in the present invention.
Disclosure of Invention
The invention aims to provide a nanowire array electric thruster and a thrust vector control method thereof, and aims to solve the problem that the existing electric thruster is difficult to meet the requirement of satellite attitude and orbit control on thrust vector regulation.
In order to solve the above technical problem, the present invention provides a nanowire array electric thruster, comprising:
a gas path component configured to perform the following actions:
a plurality of isolation modules configured to divide an air passage penetrating the nanowire array electric thruster into a plurality of air passages so that propellant gas flowing through the nanowire array electric thruster is divided into multiple paths;
each path of propellant gas is ionized by a strong electric field between a nanowire array and a grid in the nanowire array electric thruster and is accelerated by the strong electric field to be ejected out to generate thrust;
and the control module is configured to adjust the magnitude of the output thrust of each thrust output area by controlling the on-off of each air path or the gas flow or the voltage between the nanowire array and the grid according to different thrust vector adjustment requirements, so that the thrust vector adjustment of the nanowire array electric thruster is realized.
Optionally, in the nanowire array electric thruster, the gas path assembly includes:
a gate configured to generate an electric field in cooperation with the nanowire array;
a nanowire array configured to generate an electric field in cooperation with a gate;
a substrate configured to support the nanowire array;
a base configured to support a substrate;
a shell configured to provide external radial support for the gate, the nanowire array, the substrate, and the base.
Optionally, in the nanowire array electric thruster, the gate, the nanowire array, the substrate and the base are sequentially connected in a matching manner and then accommodated in the housing to form an air passage;
the grid electrode is in a circular sheet structure, a grid electrode hole array penetrating through the height direction of the grid electrode is distributed on the grid electrode, and the grid electrode is made of tungsten, molybdenum or carbon;
the distance between the nanowire array and the grid is 50-500 micrometers;
the material of the nanowire array comprises at least one of zinc oxide, carbon nanotubes, tungsten oxide, copper oxide and titanium dioxide.
Optionally, in the nanowire array electric thruster,
the substrate is parallel to the grid electrode, and the material of the substrate comprises at least one of silicon, ceramic, metal and alloy;
a substrate hole array penetrating through the height direction of the substrate is distributed on the substrate and used for the flow of propellant gas;
the base is parallel to the substrate;
the base is provided with base holes penetrating through the height direction of the base, and each base hole corresponds to one air path.
Optionally, in the nanowire array electric thruster, the plurality of isolation modules comprise an upper partition plate, wherein:
the upper partition plates are a plurality of flat plates perpendicular to the grid and the substrate, the upper partition plates are fixed on the upper surface of the substrate, the flat plates of the upper partition plates are in a shape of radiating from the center of the substrate to the periphery, the upper partition plates are uniformly distributed on the substrate, the upper surfaces of the upper partition plates are close to the lower surface of the grid, and the side surfaces of the upper partition plates are close to the shell.
Optionally, in the nanowire array electric thruster, the plurality of isolation modules further include a lower partition plate, wherein:
the lower partition plates are flat plates which are perpendicular to the substrate and the base and have the same number as the upper partition plates, the lower partition plates are aligned with the upper partition plates in the direction perpendicular to the surface of the substrate, the lower partition plates are fixed on the upper surface of the base, the upper surfaces of the lower partition plates are close to the lower surface of the substrate, and the side surfaces of the lower partition plates are close to the shell.
Optionally, in the nanowire array electric thruster,
each base hole is connected with one gas circuit respectively so as to convey propellant gas to the corresponding gas circuit;
each gas path corresponds to an electromagnetic valve which is used as a switch for controlling the on-off of the corresponding gas path so as to control the flow of propellant gas in each gas path;
each gas path corresponds to one flow regulating module, and the flow regulating module is used for regulating the flow of the propellant gas flowing in the corresponding gas path;
propellant gas enters the nanowire array electric thruster through the base hole and is secondarily distributed through the substrate hole array, so that the propellant gas uniformly flows to the tip of the nanowire array, is ionized by a strong electric field between the nanowire array and the grid and is accelerated to be sprayed out to generate thrust.
Optionally, in the nanowire array electric thruster,
when all the electromagnetic valves are in an open state, gas flows through the nanowire arrays in all the areas on the substrate, at the moment, the thrust is uniformly output on the nozzle plane of the nanowire array electric thruster, the thrust of the nanowire array electric thruster is output along the axis of the nozzle, and the magnitude of the thrust is the sum of the thrust output by all the areas.
Optionally, in the nanowire array electric thruster,
when part of the electromagnetic valves are in an open state, propellant gas flows through the corresponding gas path, the flowing gas is ionized by a strong electric field between the nanowire array and the grid electrode corresponding to the gas path and outputs thrust, and the region corresponding to the gas path is a thrust output region;
at the moment, the thrust output direction of the nanowire array electric thruster is the direction of the resultant force of the thrust output by each thrust output area, and the magnitude of the thrust is the sum of the thrust output by the thrust output areas;
the output thrust of each thrust output area is realized by adjusting the gas flow of the thrust output area or/and the voltage between the nanowire array and the grid.
The invention also provides a thrust vector control method of the nanowire array electric thruster, which comprises the following steps:
the gas path component of the nanowire array electric thruster forms a gas path, so that propellant gas sequentially flows through the gas path component;
the isolation modules divide an air passage penetrating through the nanowire array electric thruster into a plurality of air passages so that propellant gas flowing through the nanowire array electric thruster respectively passes through the air passages, and each path of propellant gas is ionized by a strong electric field between the nanowire array and the grid and is accelerated by the strong electric field to be sprayed out to generate thrust;
the control module adjusts the thrust by controlling the on-off of each gas path or the gas flow or the voltage between the nanowire array and the grid according to different thrust vector adjusting requirements, so that the thrust vector of the nanowire array electric thruster is adjusted.
In the nanowire array electric thruster and the thrust vector control method thereof provided by the invention, an air passage penetrating through the nanowire array electric thruster is divided into a plurality of air passages through a plurality of isolation modules, so that propellant gas flowing through the nanowire array electric thruster is divided into a plurality of paths to generate thrust, the requirement of satellite attitude and orbit control on thrust vector regulation is met, only one nanowire array electric thruster is needed to be installed, the implementation is easy, the installation of a plurality of thrusters is avoided, the satellite quality and cost are reduced, the thrust vector is also prevented from being changed by the direction of a nozzle of the thruster through a vector regulation mechanism, the structural layout is simple, the control module can be used for thrust vector regulation by controlling the on-off of each air passage according to the requirement of different thrust vector regulation, and the control algorithm is simple.
The propellant gas adopted by the invention can be various gases such as xenon, argon, nitrogen and air, and the limit that the conventional Hall thruster and ion thruster usually adopt inert gases such as xenon, argon and the like as the propellant is broken through.
Furthermore, the substrate is divided into a plurality of parts by the upper partition plate and the lower partition plate, and the substrate and the grid of the thruster are still physically integrated, so that the thrust vector can be adjusted by only loading one path of voltage between the substrate and the grid, and the problems of multi-path power supply and electric insulation caused by physically dividing the substrate or the grid are avoided.
The invention provides a thrust vector control method of an electric thruster, which can realize the regulation of a thrust vector by regulating the switch of each gas pipeline, the gas flow and the voltage between a nanowire array and a grid electrode in a corresponding area.
Drawings
FIG. 1 is a schematic diagram of an electric thruster with controllable thrust vectors according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of an upper and lower partition plates, a nanowire array, and a substrate according to an embodiment of the invention;
shown in the figure: 1-a grid; 2-an upper partition plate; 3-nanowire arrays; 4-a substrate; 5-a lower baffle plate; 6-a base; 7-outer shell.
Detailed Description
The invention is further elucidated with reference to the drawings in conjunction with the detailed description.
It should be noted that the components in the figures may be exaggerated and not necessarily to scale for illustrative purposes. In the figures, identical or functionally identical components are provided with the same reference symbols.
In the present invention, "disposed on …", "disposed over …" and "disposed over …" do not exclude the presence of an intermediate therebetween, unless otherwise specified. Further, "disposed on or above …" merely indicates the relative positional relationship between two components, and may also be converted to "disposed below or below …" and vice versa in certain cases, such as after reversing the product direction.
In the present invention, the embodiments are only intended to illustrate the aspects of the present invention, and should not be construed as limiting.
In the present invention, the terms "a" and "an" do not exclude the presence of a plurality of elements, unless otherwise specified.
It is further noted herein that in embodiments of the present invention, only a portion of the components or assemblies may be shown for clarity and simplicity, but those of ordinary skill in the art will appreciate that, given the teachings of the present invention, required components or assemblies may be added as needed in a particular scenario. Furthermore, features from different embodiments of the invention may be combined with each other, unless otherwise indicated. For example, a feature of the second embodiment may be substituted for a corresponding or functionally equivalent or similar feature of the first embodiment, and the resulting embodiments are likewise within the scope of the disclosure or recitation of the present application.
It is also noted herein that, within the scope of the present invention, the terms "same", "equal", and the like do not mean that the two values are absolutely equal, but allow some reasonable error, that is, the terms also encompass "substantially the same", "substantially equal". By analogy, in the present invention, the terms "perpendicular", "parallel" and the like in the directions of the tables also cover the meanings of "substantially perpendicular", "substantially parallel".
The numbering of the steps of the methods of the present invention does not limit the order of execution of the steps of the methods. Unless specifically stated, the method steps may be performed in a different order.
The nanowire array electric thruster and the thrust vector control method thereof proposed by the present invention are further described in detail with reference to the accompanying drawings and specific embodiments. Advantages and features of the present invention will become apparent from the following description and from the claims. It is to be noted that the drawings are in a very simplified form and are not to precise scale, which is merely for the purpose of facilitating and distinctly claiming the embodiments of the present invention.
The invention aims to provide a nanowire array electric thruster and a thrust vector control method thereof, and aims to solve the problem that the existing electric thruster is difficult to meet the requirement of satellite attitude and orbit control on thrust vector regulation.
The invention aims to provide an electric thruster with a controllable thrust vector and a thrust vector control method thereof, and aims to solve the problem that the mass of a system is increased when the existing scheme is adopted for thrust vector adjustment.
In order to achieve the above object, the present invention provides a nanowire array electric thruster and a thrust vector control method thereof, including: a gas path component configured to perform the following actions: forming an air passage so that the propellant gas flows through the air passage components in sequence; a plurality of isolation modules configured to divide an air passage penetrating the nanowire array electric thruster into a plurality of air passages so that propellant gas flowing through the nanowire array electric thruster is divided into multiple paths; each path of propellant gas is ionized by a strong electric field between a nanowire array and a grid in the nanowire array electric thruster and is accelerated by the strong electric field to be ejected out to generate thrust; and the control module is configured to adjust the magnitude of the output thrust of each thrust output area by controlling the on-off of each air path or the gas flow or the voltage between the nanowire array and the grid according to different thrust vector adjustment requirements, so that the thrust vector adjustment of the nanowire array electric thruster is realized.
The thrust vector control method of the electric thruster divides gas flowing through the nanowire array into a plurality of paths through the partition plates, and realizes thrust vector control by changing the gas flow of the nanowire array in each area and the voltage between the nanowire array and the grid.
The present embodiment provides an electric thruster with controllable thrust vectors, which is suitable for attitude and orbit control of satellites. As shown in fig. 1 and 2, the electric thruster with controllable thrust vector comprises a grid 1, an upper partition plate 2, a nanowire array 3, a substrate 4, a lower partition plate 5, a base 6, and a housing 7 which is externally used for supporting, which are sequentially connected in a matching manner from top to bottom. The grid 1 is in a circular sheet structure, and a grid hole array penetrating through the height direction of the grid is distributed on the grid 1; the grid electrode 1 is made of tungsten, molybdenum or carbon;
the upper partition plates 2 are a plurality of flat plates vertical to the grid 1 and the substrate 4; the upper clapboard 2 is fixed on the upper surface of the substrate 4; each flat plate of the upper partition plate 2 is in a shape of radiating from the center of the substrate 4 to the periphery; the upper partition boards 2 are uniformly distributed on the substrate 4; the upper surface of the upper partition plate 2 is close to the lower surface of the grid 1; the side of the upper partition plate 2 is adjacent to the shell 7;
the nanowire array 3 includes but is not limited to nanowires such as zinc oxide, carbon nanotubes, tungsten oxide, copper oxide, titanium dioxide, and the like; the distance between the nanowire array 3 and the grid 1 is tens of micrometers to hundreds of micrometers; the substrate 4 is parallel to the grid 1; the substrate 4 material includes but is not limited to silicon, ceramic, metal, alloy, etc.; the substrate 4 is distributed with an array of holes penetrating the height direction of the substrate for the flow of gas propellant;
the lower partition plates 5 are flat plates which are vertical to the substrate and the base and have the same number as the upper partition plates 2; the lower partition 5 is aligned with the upper partition 2 in a direction perpendicular to the surface of the substrate 4; the lower clapboard 5 is fixed on the upper surface of the base 6; the upper surface of the lower partition plate 5 is adjacent to the lower surface of the substrate 4; the side of the lower partition 5 is adjacent to the housing 7; the base 6 is parallel to the substrate 4; holes penetrating through the height direction of the base 6 are distributed on the base 6, and the number of the holes is the same as that of the flat plates of the upper partition plate 5; each hole on the base 6 is positioned at the center between two adjacent lower flat plates; the shell 7 is positioned at the periphery of the thruster and plays a role in supporting and protecting.
The embodiment also provides a thrust vector control method of an electric thruster, which comprises the following steps: the gas path component of the nanowire array electric thruster forms a gas path, so that propellant gas sequentially flows through the gas path component; the isolation modules divide an air passage penetrating through the nanowire array electric thruster into a plurality of air passages, so that propellant gas flowing through the nanowire array electric thruster respectively passes through the air passages, is ionized by a strong electric field between the nanowire array and a grid electrode, and is accelerated by the strong electric field to be ejected out to generate thrust; the control module controls the on-off of each gas path, the flow and/or the working voltage of propellant gas in the gas path according to different requirements for thrust vector adjustment so as to realize thrust vector adjustment of the nanowire array electric thruster.
The thrust vector control method includes: each hole on the base 6 is connected with an air inlet pipeline respectively; each air inlet pipe is controlled by an independent electromagnetic valve to open and close the air flow; the gas flow of each gas inlet pipeline is regulated by a single flow regulating module; propellant gas enters the thruster through holes in the base and is secondarily distributed through the hole array on the substrate 4, so that the propellant gas uniformly flows to the tip of the nanowire array 3, is ionized by a strong electric field between the nanowire array 3 and the grid 1 and is accelerated to be ejected out to generate thrust;
when all the electromagnetic valves are in an open state, gas flows through the nanowire arrays 3 in all the areas on the substrate 4, at the moment, the thrust is uniformly output on the nozzle plane of the thruster, the thrust of the thruster is output along the axis of the nozzle, and the magnitude of the thrust is the sum of the thrust output by all the areas;
when part of the electromagnetic valves are in an open state, only the nanowire arrays 3 in the areas corresponding to the gas path have gas to flow through, so that only the areas have thrust output, the thrust output direction of the thruster is the direction of the resultant force of the thrust output of each area, and the thrust is the sum of the thrust output of each area; further, the output thrust of each region can be adjusted by changing the gas flow rate of the region or/and the voltage between the nanowire array 3 and the grid 1.
In summary, the above embodiments describe in detail different configurations of the nanowire array electric thruster and the thrust vector control method thereof, and it goes without saying that the present invention includes but is not limited to the configurations listed in the above embodiments, and any modifications based on the configurations provided by the above embodiments are within the scope of the present invention. One skilled in the art can take the contents of the above embodiments to take a counter-measure.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other. For the system disclosed by the embodiment, the description is relatively simple because the system corresponds to the method disclosed by the embodiment, and the relevant points can be referred to the method part for description.
The above description is only for the purpose of describing the preferred embodiments of the present invention, and is not intended to limit the scope of the present invention, and any variations and modifications made by those skilled in the art based on the above disclosure are within the scope of the appended claims.
Claims (10)
1. A nanowire array electrical thruster, comprising:
a gas path component configured to perform the following actions:
forming an air passage so that the propellant gas flows through the air passage components in sequence;
a plurality of isolation modules configured to divide an air passage penetrating the nanowire array electric thruster into a plurality of air passages so that propellant gas flowing through the nanowire array electric thruster is divided into multiple paths;
each path of propellant gas is ionized by a strong electric field between a nanowire array and a grid in the nanowire array electric thruster and is accelerated by the strong electric field to be ejected out to generate thrust;
and the control module is configured to adjust the magnitude of the output thrust of each thrust output area by controlling the on-off of each air path or the gas flow or the voltage between the nanowire array and the grid according to different thrust vector adjustment requirements, so that the thrust vector adjustment of the nanowire array electric thruster is realized.
2. The nanowire array electric thruster of claim 1, wherein the gas path assembly comprises:
a gate configured to generate an electric field in cooperation with the nanowire array;
a nanowire array configured to generate an electric field in cooperation with a gate;
a substrate configured to support the nanowire array;
a base configured to support a substrate;
a shell configured to provide external radial support for the gate, the nanowire array, the substrate, and the base.
3. The nanowire array electric thruster of claim 2, wherein the gate, the nanowire array, the substrate and the base are sequentially and cooperatively connected and then accommodated in the housing to form an air channel;
the grid electrode is in a circular sheet structure, a grid electrode hole array penetrating through the height direction of the grid electrode is distributed on the grid electrode, and the grid electrode is made of tungsten, molybdenum or carbon;
the distance between the nanowire array and the grid is 50-500 micrometers;
the material of the nanowire array comprises at least one of zinc oxide, carbon nanotubes, tungsten oxide, copper oxide and titanium dioxide.
4. The nanowire array electric thruster of claim 3, wherein,
the substrate is parallel to the grid electrode, and the material of the substrate comprises at least one of silicon, ceramic, metal and alloy;
a substrate hole array penetrating through the height direction of the substrate is distributed on the substrate and used for the flow of propellant gas;
the base is parallel to the substrate;
the base is provided with base holes penetrating through the height direction of the base, and each base hole corresponds to one air path.
5. The nanowire array electrical pusher of claim 3, wherein the plurality of isolation modules comprises an upper baffle, wherein:
the upper partition plates are a plurality of flat plates perpendicular to the grid and the substrate, the upper partition plates are fixed on the upper surface of the substrate, the flat plates of the upper partition plates are in a shape of radiating from the center of the substrate to the periphery, the upper partition plates are uniformly distributed on the substrate, the upper surfaces of the upper partition plates are close to the lower surface of the grid, and the side surfaces of the upper partition plates are close to the shell.
6. The nanowire array electrical thruster of claim 3, wherein the plurality of isolation modules further comprises a lower baffle, wherein:
the lower partition plates are flat plates which are perpendicular to the substrate and the base and have the same number as the upper partition plates, the lower partition plates are aligned with the upper partition plates in the direction perpendicular to the surface of the substrate, the lower partition plates are fixed on the upper surface of the base, the upper surfaces of the lower partition plates are close to the lower surface of the substrate, and the side surfaces of the lower partition plates are close to the shell.
7. The nanowire array electric thruster of claim 1,
each base hole is connected with one gas circuit respectively so as to convey propellant gas to the corresponding gas circuit;
each gas path corresponds to an electromagnetic valve which is used as a switch for controlling the on-off of the corresponding gas path so as to control the flow of propellant gas in each gas path;
each gas path corresponds to one flow regulating module, and the flow regulating module is used for regulating the flow of the propellant gas flowing in the corresponding gas path;
propellant gas enters the nanowire array electric thruster through the base hole and is secondarily distributed through the substrate hole array, so that the propellant gas uniformly flows to the tip of the nanowire array, is ionized by a strong electric field between the nanowire array and the grid and is accelerated to be sprayed out to generate thrust.
8. The nanowire array electrical thruster of claim 7,
when all the electromagnetic valves are in an open state, gas flows through the nanowire arrays in all the areas on the substrate, at the moment, the thrust is uniformly output on the nozzle plane of the nanowire array electric thruster, the thrust of the nanowire array electric thruster is output along the axis of the nozzle, and the magnitude of the thrust is the sum of the thrust output by all the areas.
9. The nanowire array electrical thruster of claim 7,
when part of the electromagnetic valves are in an open state, propellant gas flows through the corresponding gas path, the flowing gas is ionized by a strong electric field between the nanowire array and the grid electrode corresponding to the gas path and outputs thrust, and the region corresponding to the gas path is a thrust output region;
at the moment, the thrust output direction of the nanowire array electric thruster is the direction of the resultant force of the thrust output by each thrust output area, and the magnitude of the thrust is the sum of the thrust output by the thrust output areas;
the output thrust of each thrust output area is realized by adjusting the gas flow of the thrust output area or/and the voltage between the nanowire array and the grid.
10. A thrust vector control method of a nanowire array electric thruster is characterized by comprising the following steps:
the gas path component of the nanowire array electric thruster forms a gas path, so that propellant gas sequentially flows through the gas path component;
the isolation modules divide an air passage penetrating through the nanowire array electric thruster into a plurality of air passages so that propellant gas flowing through the nanowire array electric thruster respectively passes through the air passages, and each path of propellant gas is ionized by a strong electric field between the nanowire array and the grid and is accelerated by the strong electric field to be sprayed out to generate thrust;
the control module adjusts the output thrust of each thrust output area by controlling the on-off of each air path or the gas flow or the voltage between the nanowire array and the grid according to different thrust vector adjusting requirements, so that the thrust vector adjustment of the nanowire array electric thruster is realized.
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| CN111577563A (en) * | 2020-05-25 | 2020-08-25 | 中国科学院微小卫星创新研究院 | Space propulsion system and propulsion method thereof |
| CN112373728A (en) * | 2020-10-26 | 2021-02-19 | 哈尔滨工业大学 | Combined electric propulsion device for space gravitational wave detection and control method |
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| US20090290865A1 (en) * | 2008-05-21 | 2009-11-26 | Hon Hai Precision Industry Co., Ltd. | Zinc oxide nano-wire based actuator, lens module using same and camera module using same |
| CN107472556A (en) * | 2017-07-28 | 2017-12-15 | 北京控制工程研究所 | A kind of MEMS electron sprays thruster array structure and implementation method |
| CN111577563A (en) * | 2020-05-25 | 2020-08-25 | 中国科学院微小卫星创新研究院 | Space propulsion system and propulsion method thereof |
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