CN113212805A - Nanowire array electric propulsion system capable of on-orbit autonomous repair - Google Patents
Nanowire array electric propulsion system capable of on-orbit autonomous repair Download PDFInfo
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- 239000011787 zinc oxide Substances 0.000 claims description 4
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- 229910001297 Zn alloy Inorganic materials 0.000 claims description 3
- 229910052786 argon Inorganic materials 0.000 claims description 3
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- 229910052721 tungsten Inorganic materials 0.000 claims description 2
- 239000010937 tungsten Substances 0.000 claims description 2
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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
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Abstract
The invention provides an on-orbit self-repairing nanowire array electric propulsion system, which comprises: a nanowire array thruster configured to perform the following actions: the propellant is ionized by an electric field to generate thrust; growing the nanowire by adopting a repairing agent to carry out a thermal oxidation method; a propellant delivery system configured to provide a propellant to the nanowire array thruster in a nanowire array thruster mode of operation; and a repair agent delivery system configured to provide a repair agent to the nanowire array thruster in the nanowire array thruster repair mode.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to a nanowire array electric propulsion system capable of on-orbit autonomous repair.
Background
The electric thruster based on the zinc oxide nanowire array ionizes gas propellant through a strong electric field between the nanowire array and a grid and accelerates the gas propellant to be ejected to generate thrust. The thruster has the characteristics of simple structure, wide thrust range, high specific impulse, capability of using any gas as a propellant and the like, and is suitable for the orbit maintenance and transfer of satellites. However, the tip of the zinc oxide nanowire is eroded under the long-term action of a strong electric field, ion bombardment and the like, thereby affecting the performance and the service life of the thruster.
Disclosure of Invention
The invention aims to provide a nanowire array electric propulsion system capable of automatically repairing in orbit, which aims to solve the problem that the tip of the existing zinc oxide nanowire can be corroded under the long-term action of a strong electric field, ion bombardment and the like.
In order to solve the above technical problem, the present invention provides an in-orbit self-repairing nanowire array electric propulsion system, including:
a nanowire array thruster configured to perform the following actions:
the propellant is ionized by an electric field to generate thrust; and
growing a nanowire by adopting a repairing agent to carry out a thermal oxidation method;
a propellant delivery system configured to provide a propellant to the nanowire array thruster in a nanowire array thruster mode of operation; and
a repair agent delivery system configured to provide a repair agent to the nanowire array thruster in a nanowire array thruster repair mode.
Optionally, in the nanowire array electric propulsion system capable of in-orbit autonomous repair, the nanowire array thruster 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 heating wire configured to heat the substrate to thermally oxidize the substrate to grow the nanowire; and
a housing configured to externally support the gate, the nanowire array, the substrate and the heating wire.
Optionally, in the in-orbit self-repairing nanowire array electric propulsion system, the grid, the nanowire array, the substrate and the heating wire are sequentially connected in a matching manner and then accommodated in the housing;
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 nanowire array is a zinc oxide nanowire, and the distance between the nanowire array and the grid is 50-500 micrometers;
the substrate is parallel to the grid, the substrate is made of zinc or zinc alloy, and a substrate hole array penetrating through the substrate in the height direction is distributed on the substrate and used for flowing of a propellant or a repairing agent;
the heating wires are uniformly distributed on one side of the substrate, which is not distributed with the nanowire array.
Optionally, in the nanowire array electric propulsion system capable of in-orbit autonomous repair, growing nanowires by a thermal oxidation method using a repair agent includes:
and heating the substrate in a repairing agent environment to oxidize zinc elements in the substrate, so that the zinc oxide nanowire grows from the substrate towards the grid electrode direction, and cooling the zinc oxide nanowire to finish the growth of the nanowire.
Optionally, in the nanowire array electric propulsion system capable of in-orbit autonomous repair, the propellant delivery system includes:
a propellant reservoir configured to store propellant;
a working solenoid valve disposed downstream of the propellant tank as a switch for controlling the flow of propellant;
a remediation agent delivery system comprising:
a repair agent reservoir configured to store a repair agent;
a repair solenoid valve disposed downstream of the repair agent reservoir as a switch for controlling the flow of the repair agent.
Optionally, in the nanowire array electric propulsion system capable of in-orbit autonomous repair, the system further includes:
the flow regulating module is arranged at the downstream of the working electromagnetic valve and the repairing electromagnetic valve and is used for regulating the gas flow of the propellant and the repairing agent;
the propellant comprises xenon, argon, helium, nitrogen, carbon dioxide or air;
the remediation agent comprises oxygen or air;
the propellant storage tank, the working electromagnetic valve, the repairing agent storage tank, the repairing electromagnetic valve, the flow regulating module and the nanowire array thruster are connected through a gas pipeline.
Optionally, in the nanowire array electric propulsion system capable of in-orbit autonomous repair, the system further includes:
a control module configured to perform the following actions when the in-orbit autonomous repairable nanowire-array electric propulsion system is in an operating mode:
the repair electromagnetic valve is in a closed state;
enabling a heating wire in the nanowire array thruster to be in a power-off state;
opening the working electromagnetic valve to enable the propellant in the propellant storage tank to sequentially pass through the working electromagnetic valve and the flow regulating module to reach the nanowire array thruster;
and adjusting the flow regulating module to enable the propellant in the propellant storage tank to flow to the inside of the nanowire array thruster at a first flow rate, so that the propellant is ionized by a strong electric field between the nanowire array and the grid in the nanowire array thruster and is accelerated by the strong electric field to be ejected out to generate thrust.
Optionally, in the nanowire array electric propulsion system capable of on-orbit autonomous repair,
a control module further configured to perform the following actions when the in-orbit autonomous repairable nanowire-array electric propulsion system is in a repair mode:
enabling the working electromagnetic valve to be in a closed state;
opening the repair electromagnetic valve to enable the repair agent in the repair agent storage box to sequentially pass through the repair electromagnetic valve and the flow regulating module to reach the nanowire array thruster;
adjusting a flow regulating module to enable the repairing agent in a repairing agent storage box to flow to the inside of the nanowire array thruster at a second flow rate;
enabling the heating wire to be in a power-on state, and enabling the substrate and the zinc oxide nanowire to be heated to a first temperature and to be kept for a first time;
the zinc element in the substrate is oxidized by the repairing agent gas under the action of high temperature to generate zinc oxide, and grows again from the root of the damaged zinc oxide nanowire to carry out self-repairing;
and closing the heating wire and the repairing electromagnetic valve to cool the substrate and the zinc oxide nanowire and keep cooling in the second time to finish the one-time repairing process.
Optionally, in the nanowire array electric propulsion system capable of on-orbit autonomous repair,
calibrating the relationship between the repair times and the working current or the height of the nanowire, and inputting a calibrated value into a control module;
and the working current or nanowire height detection device is configured to detect that the working current or the nanowire height is lower than a threshold value, determine the repairing times according to a calibration value by the control module, and execute corresponding actions.
Optionally, in the nanowire array electric propulsion system capable of in-orbit autonomous repair, the control module is further configured to perform the following actions:
after finishing the primary repairing process, opening the working electromagnetic valve;
loading a first working voltage between the nanowire array and the grid;
adjusting a flow regulation module to flow propellant from the propellant tank to an interior of a nanowire array thruster at a first flow rate;
comparing the current with the current before the nanowires are damaged, and if the current is less than the current before the nanowires are damaged, closing the working electromagnetic valve to carry out the next repairing process;
and if the working current at the moment is equal to the working current before being damaged, finishing all the repairing processes.
In the nanowire array electric propulsion system capable of in-orbit autonomous repair, the repair agent is provided for the nanowire array thruster by the repair agent conveying system in the nanowire array thruster repair mode, so that nanowires are grown by adopting the repair agent through a thermal oxidation method, the repair of the nanowires is realized, and the problem that the tip of the existing zinc oxide nanowire is cut and corroded under long-term actions of a strong electric field, ion bombardment and the like to influence the performance and the service life of the thruster is solved.
The nanowire array electric propulsion system capable of in-orbit autonomous repair provided by the invention is used as a propulsion system of a satellite, and the adopted propellant can be any gas, so that the limitation 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.
Further, aiming at the problem that the nanowire array which works for a long time is damaged due to bombardment of strong electric field and ions, a high-temperature environment is provided by a heating wire in the nanowire array thruster, and oxidizing gases such as oxygen carried by a satellite are utilized to perform chemical action on the substrate and the nanowires, so that the regrowth of the damaged zinc oxide nanowires and the self-repair of the nanowire array thruster are realized, and the service life of the nanowire array thruster is prolonged.
Furthermore, the substrate of the nanowire array thruster is made of zinc or an alloy material containing zinc, and compared with the amount of zinc consumed by growing the nanowires every time, the content of the zinc in the substrate can be considered to be infinite, so that the repeated growth and repair of the nanowire array can be realized.
The invention provides the nanowire array electric propulsion system capable of on-orbit autonomous repair and the on-orbit autonomous repair method thereof, only the heating wires need to be electrified and heated when the damaged nanowires are repaired, the operation is simple and convenient, the adopted repair agent is air or oxygen, and the cost is low.
Drawings
FIG. 1 is a schematic diagram of an in-orbit autonomous repair nanowire array electric propulsion system according to an embodiment of the present invention;
figure 2 is a schematic diagram of a nanowire array thruster in accordance with an embodiment of the present invention;
shown in the figure: 1-a propellant tank; 2-working electromagnetic valve; 3-a repairing agent storage tank; 4-repairing the electromagnetic valve; 5-a flow regulation module; 6-nanowire array thrusters; 7-a grid; 8-zinc oxide nanowire arrays; 9-a substrate; 10-heating wires; 11-a housing.
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 following describes in detail the nanowire array electric propulsion system capable of in-orbit autonomous repair proposed by the present invention 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 propulsion system capable of automatically repairing in orbit, which aims to solve the problem that the tip of the existing zinc oxide nanowire can be corroded under the long-term action of a strong electric field, ion bombardment and the like.
To achieve the above object, the present invention provides an in-orbit self-repairing nanowire array electric propulsion system, comprising: a nanowire array thruster configured to perform the following actions: the propellant is ionized by an electric field to generate thrust; growing the nanowire by adopting a repairing agent to carry out a thermal oxidation method; a propellant delivery system configured to provide a propellant to the nanowire array thruster in a nanowire array thruster mode of operation; and a repair agent delivery system configured to provide a repair agent to the nanowire array thruster in the nanowire array thruster repair mode.
The embodiment of the invention provides an on-orbit self-repairing nanowire array electric propulsion system and an on-orbit self-repairing method thereof, and as shown in fig. 1-2, the on-orbit self-repairing nanowire array electric propulsion system comprises a propellant storage tank 1, a working electromagnetic valve 2, a repairing agent storage tank 3, a repairing electromagnetic valve 4, a flow regulating module 5 and a nanowire array thruster 6; the nanowire array thruster mainly comprises a zinc oxide nanowire array 8, a substrate 9, a grid 7, a heating wire 10, a shell 11 and the like; the propulsion system has two modes, an operating mode and a repair mode.
When the propulsion system is in the working mode: the working electromagnetic valve is in an open state; the repair electromagnetic valve is in a closed state; propellant gas in the propellant storage tank sequentially passes through the working electromagnetic valve and the flow regulating module to reach the nanowire array thruster; the high-power electric field is ionized between the nanowire array and the grid in the nanowire array thruster and is accelerated by the high-power electric field to be ejected out to generate thrust; and a heating wire in the nanowire array thruster is in a power-off state.
When the propulsion system is in the remediation mode: the working electromagnetic valve is in a closed state; the repair electromagnetic valve is in an open state; repairing agent gas in the propellant storage box sequentially passes through the repairing electromagnetic valve and the flow regulating module to the inside of the nanowire array thruster; the zinc oxide nanowire is heated by the heating wire under the action of the repairing agent gas, so that the regrowth and the repair are realized.
The present embodiments provide an in-orbit self-repairable nanowire-array electric propulsion system suitable for use in a propulsion system of a satellite. As shown in fig. 1, the nanowire array electric propulsion system capable of on-orbit autonomous repair comprises a propellant storage tank 1, a working electromagnetic valve 2, a repair agent storage tank 3, a repair electromagnetic valve 4, a flow regulation module 5 and a nanowire array thruster 6; in the present embodiment, the propellant tank 1 stores xenon propellant; the working electromagnetic valve 2 is positioned at the downstream of the propellant storage tank 1 and is a switch for controlling the flow of propellant gas; the repairing agent storage box 3 stores an air repairing agent; the repairing electromagnetic valve 4 is positioned at the downstream of the repairing agent storage tank 3 and is a switch for controlling the flowing of repairing agent gas; the flow regulating module 5 is positioned at the downstream of the working electromagnetic valve 2 and the repairing electromagnetic valve 4 and is used for regulating the flow of propellant and repairing agent gas; the nanowire array thruster 6 is positioned at the downstream of the flow regulating module 5 and is used for ionizing propellant gas and generating thrust; the propellant storage tank 1, the working electromagnetic valve 2, the repairing agent storage tank 3, the repairing electromagnetic valve 4, the flow regulating module 5 and the nanowire array thruster 6 are connected through a gas pipeline.
As shown in fig. 2, in the in-orbit self-repairing nanowire array electric propulsion system, the nanowire array thruster 6 includes a grid 7, a nanowire array 8, a substrate 9, a heating wire 10, and an outer casing 11 for supporting, which are sequentially connected from top to bottom, wherein: the grid electrode 7 is in a circular sheet structure, and a grid electrode hole array penetrating through the height direction of the grid electrode is distributed on the grid electrode 7; the diameter of the hole is 2.5 mm; the grid 7 is made of carbon; the nanowire array 8 is a zinc oxide nanowire and is grown by a thermal oxidation method: heating the substrate 9 in an oxygen/air environment to oxidize zinc elements in the substrate 9 so as to grow zinc oxide nanowires, and cooling for a period of time to finish the growth of the nanowires; the distance between the nanowire array 8 and the grid 7 is 150 micrometers; the substrate 9 is parallel to the grid 7; the substrate 9 is made of tungsten-zinc alloy; an array of holes penetrating the height direction of the substrate 9 is distributed on the substrate 9 and used for the flow of gas propellant; the diameter of the pores is 300 microns; the heating wires 10 are fixed and uniformly distributed on the lower surface of the substrate 9; the shell 11 is located at the periphery of the thruster and plays a role in supporting and protecting.
In one embodiment of the present invention, the operation mode of the in-orbit self-repairing nanowire array electric propulsion system is as follows: the working electromagnetic valve 2 is in an open state; the repair solenoid valve 4 is in a closed state; propellant gas in the propellant storage tank 1 sequentially flows to the nanowire array thruster 6 through the working electromagnetic valve 2 and the flow regulating module 5 at a working flow of 6 sccm; propellant gas is ionized by a strong electric field generated by 600V voltage loaded between the nanowire array 8 and the grid 7 in the nanowire array thruster 6 and is accelerated to be ejected out to generate 10mN thrust; the heating wire 10 of the nanowire array thruster 6 is in a power-off state.
The embodiment provides an on-orbit autonomous repair method for an on-orbit autonomous repairable nanowire array electric propulsion system, which includes: the repairing agent in the repairing agent storage box flows into the thruster through the repairing electromagnetic valve and the flow regulating module in sequence; the heating wire heats the substrate, so that the substrate is oxidized by the oxidizing gas under the action of high temperature, the regrowth of the nanowire is realized, and the primary repair is completed.
Specifically, in the in-orbit self-repairing method of the in-orbit self-repairable nanowire array electric propulsion system, the repairing agent in the repairing agent storage tank is air; further, the repair solenoid valve is in an open state; further, the working electromagnetic valve is in a closed state; further, the flow regulating module is regulated, so that the collected gas flows into the nanowire array thruster at the repair flow rate of 1 sccm; further, the heating wire is in a power-on state, so that the substrate and the zinc oxide nanowire are heated to 450 ℃ and are kept warm for 0.5 h; furthermore, the zinc element in the substrate is oxidized by the repairing agent gas under the action of high temperature to generate zinc oxide, and the zinc oxide grows again from the root of the damaged zinc oxide nanowire to carry out self-repairing; further, the heating wire and the repair electromagnetic valve are closed, so that the substrate and the zinc oxide nanowire are cooled and cooled for a period of time, and the first iteration of the repair process is completed.
The nanowire array thruster can achieve the repairing effect only by needing to repair for many times, the repairing times need to be determined, and the first mode can be used for calibrating in advance, for example, the relationship between the repairing times and the working current or the height of the nanowire is calibrated, and a calibrated value is input into a control module; after the working current or nanowire height detection device detects that the working current or the nanowire height is lower than a threshold value, the control module determines the repairing times according to a calibration value and executes corresponding actions;
the second method may perform a detection after each repair, to determine whether a repair target is reached, for example, after a repair process is completed, open the working solenoid valve, apply a working voltage of 600V between the nanowire array and the gate, adjust the flow rate adjustment module to allow propellant gas to flow from the propellant tank to the interior of the thruster at a working flow rate of 6sccm, record that a working current of the thruster at this time is 0.3A, which is lower than 0.4A before the nanowire is damaged, and determine that a growth height of the nanowire at this time is lower than a height before the nanowire is damaged; and closing the working electromagnetic valve. The iterative process of opening the repair electromagnetic valve, electrifying, heating, heat preservation and cooling is repeatedly carried out, the inventor of the invention carries out calibration through experiments, and the fact proves that the working current of the thruster is 0.392mA until the 6 th iterative repair is carried out, so that the repair process is completed.
In summary, the above embodiments have described in detail different configurations of the in-orbit self-repairing nanowire array electric propulsion system, 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. An in-orbit self-repairable nanowire array electric propulsion system, comprising:
a nanowire array thruster configured to perform the following actions:
the propellant is ionized by an electric field to generate thrust; and
growing a nanowire by adopting a repairing agent to carry out a thermal oxidation method;
a propellant delivery system configured to provide a propellant to the nanowire array thruster in a nanowire array thruster mode of operation; and
a repair agent delivery system configured to provide a repair agent to the nanowire array thruster in a nanowire array thruster repair mode.
2. The in-orbit, self-remediable nanowire array electric propulsion system of claim 1, wherein the nanowire array thruster 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 heating wire configured to heat the substrate to thermally oxidize the substrate to grow the nanowire; and
a housing configured to externally support the gate, the nanowire array, the substrate and the heating wire.
3. The in-orbit self-repairing nanowire array electric propulsion system of claim 2, wherein the grid, the nanowire array, the substrate and the heating wire are sequentially and cooperatively connected and then accommodated in the housing;
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 nanowire array is a zinc oxide nanowire, and the distance between the nanowire array and the grid is 50-500 micrometers;
the substrate is parallel to the grid, the substrate is made of zinc or zinc alloy, and a substrate hole array penetrating through the substrate in the height direction is distributed on the substrate and used for flowing of a propellant or a repairing agent;
the heating wires are uniformly distributed on one side of the substrate, which is not distributed with the nanowire array.
4. The in-orbit, self-repairable nanowire array electric propulsion system of claim 3, wherein the growing nanowires using a thermal oxidation method with a repair agent comprises:
and heating the substrate in a repairing agent environment to oxidize zinc elements in the substrate, so that the zinc oxide nanowire grows from the substrate towards the grid electrode direction, and cooling the zinc oxide nanowire to finish the growth of the nanowire.
5. The in-orbit self-repairable nanowire array electric propulsion system of claim 4,
the propellant delivery system comprises:
a propellant reservoir configured to store propellant;
a working solenoid valve disposed downstream of the propellant tank as a switch for controlling the flow of propellant;
a remediation agent delivery system comprising:
a repair agent reservoir configured to store a repair agent;
a repair solenoid valve disposed downstream of the repair agent reservoir as a switch for controlling the flow of the repair agent.
6. The in-orbit, autonomously repairable nanowire array electric propulsion system of claim 5, further comprising:
the flow regulating module is arranged at the downstream of the working electromagnetic valve and the repairing electromagnetic valve and is used for regulating the gas flow of the propellant and the repairing agent;
the propellant comprises xenon, argon, helium, nitrogen, carbon dioxide or air;
the remediation agent comprises oxygen or air;
the propellant storage tank, the working electromagnetic valve, the repairing agent storage tank, the repairing electromagnetic valve, the flow regulating module and the nanowire array thruster are connected through a gas pipeline.
7. The in-orbit, autonomously repairable nanowire array electric propulsion system of claim 6, further comprising:
a control module configured to perform the following actions when the in-orbit autonomous repairable nanowire-array electric propulsion system is in an operating mode:
the repair electromagnetic valve is in a closed state;
enabling a heating wire in the nanowire array thruster to be in a power-off state;
opening the working electromagnetic valve to enable the propellant in the propellant storage tank to sequentially pass through the working electromagnetic valve and the flow regulating module to reach the nanowire array thruster;
and adjusting the flow regulating module to enable the propellant in the propellant storage tank to flow to the inside of the nanowire array thruster at a first flow rate, so that the propellant is ionized by a strong electric field between the nanowire array and the grid in the nanowire array thruster and is accelerated by the strong electric field to be ejected out to generate thrust.
8. The in-orbit, self-remediable nanowire array electric propulsion system of claim 7,
a control module further configured to perform the following actions when the in-orbit autonomous repairable nanowire-array electric propulsion system is in a repair mode:
enabling the working electromagnetic valve to be in a closed state;
opening the repair electromagnetic valve to enable the repair agent in the repair agent storage box to sequentially pass through the repair electromagnetic valve and the flow regulating module to reach the nanowire array thruster;
adjusting a flow regulating module to enable the repairing agent in a repairing agent storage box to flow to the inside of the nanowire array thruster at a second flow rate;
enabling the heating wire to be in a power-on state, and enabling the substrate and the zinc oxide nanowire to be heated to a first temperature and to be kept for a first time;
the zinc element in the substrate is oxidized by the repairing agent gas under the action of high temperature to generate zinc oxide, and grows again from the root of the damaged zinc oxide nanowire to carry out self-repairing;
and closing the heating wire and the repairing electromagnetic valve to cool the substrate and the zinc oxide nanowire and keep cooling in the second time to finish the one-time repairing process.
9. The in-orbit, self-remediable nanowire array electric propulsion system of claim 8,
calibrating the relationship between the repair times and the working current or the height of the nanowire, and inputting a calibrated value into a control module;
and the working current or nanowire height detection device is configured to detect that the working current or the nanowire height is lower than a threshold value, determine the repairing times according to a calibration value by the control module, and execute corresponding actions.
10. The on-orbit, autonomous, repairable nanowire array electric propulsion system of claim 8, wherein the control module is further configured to perform the following acts:
after finishing the primary repairing process, opening the working electromagnetic valve;
loading a first working voltage between the nanowire array and the grid;
adjusting a flow regulation module to flow propellant from the propellant tank to an interior of a nanowire array thruster at a first flow rate;
comparing the current with the current before the nanowires are damaged, and if the current is less than the current before the nanowires are damaged, closing the working electromagnetic valve to carry out the next repairing process;
and if the working current at the moment is equal to the working current before being damaged, finishing all the repairing processes.
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040031885A1 (en) * | 2001-07-30 | 2004-02-19 | D'ausilio Robert F. | In orbit space transportation & recovery system |
| US9194379B1 (en) * | 2010-02-10 | 2015-11-24 | The United States Of America As Represented By The Secretary Of The Navy | Field-ionization based electrical space ion thruster using a permeable substrate |
| CN105508165A (en) * | 2015-12-29 | 2016-04-20 | 电子科技大学 | Micro-nano integrated laser propelling device based on surface plasmas |
| CN106981506A (en) * | 2017-04-19 | 2017-07-25 | 华南理工大学 | Nano wire GaN HEMTs |
| CN107887258A (en) * | 2016-09-29 | 2018-04-06 | 中国科学院微电子研究所 | A kind of restorative procedure of Nano-structure |
| CN107902109A (en) * | 2017-10-31 | 2018-04-13 | 中国电子科技集团公司第五十五研究所 | Increase the MEMS micro-thruster array chips of journey module with thrust |
| 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 |
-
2021
- 2021-06-10 CN CN202110647607.9A patent/CN113212805B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040031885A1 (en) * | 2001-07-30 | 2004-02-19 | D'ausilio Robert F. | In orbit space transportation & recovery system |
| US9194379B1 (en) * | 2010-02-10 | 2015-11-24 | The United States Of America As Represented By The Secretary Of The Navy | Field-ionization based electrical space ion thruster using a permeable substrate |
| CN105508165A (en) * | 2015-12-29 | 2016-04-20 | 电子科技大学 | Micro-nano integrated laser propelling device based on surface plasmas |
| CN107887258A (en) * | 2016-09-29 | 2018-04-06 | 中国科学院微电子研究所 | A kind of restorative procedure of Nano-structure |
| CN106981506A (en) * | 2017-04-19 | 2017-07-25 | 华南理工大学 | Nano wire GaN HEMTs |
| CN107902109A (en) * | 2017-10-31 | 2018-04-13 | 中国电子科技集团公司第五十五研究所 | Increase the MEMS micro-thruster array chips of journey module with thrust |
| 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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|---|---|
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