CN115355145A - micro-Newton-grade variable thruster based on gas field ionization enhancement - Google Patents
micro-Newton-grade variable thruster based on gas field ionization enhancement Download PDFInfo
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- CN115355145A CN115355145A CN202210877796.3A CN202210877796A CN115355145A CN 115355145 A CN115355145 A CN 115355145A CN 202210877796 A CN202210877796 A CN 202210877796A CN 115355145 A CN115355145 A CN 115355145A
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- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 121
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- 229910021393 carbon nanotube Inorganic materials 0.000 claims abstract description 121
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- 230000003472 neutralizing effect Effects 0.000 claims description 2
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- WABPQHHGFIMREM-UHFFFAOYSA-N lead(0) Chemical compound [Pb] WABPQHHGFIMREM-UHFFFAOYSA-N 0.000 description 2
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- 238000009827 uniform distribution Methods 0.000 description 2
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H1/00—Using plasma to produce a reactive propulsive thrust
- F03H1/0087—Electro-dynamic thrusters, e.g. pulsed plasma thrusters
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H1/00—Using plasma to produce a reactive propulsive thrust
- F03H1/0006—Details applicable to different types of plasma thrusters
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H1/00—Using plasma to produce a reactive propulsive thrust
- F03H1/0006—Details applicable to different types of plasma thrusters
- F03H1/0025—Neutralisers, i.e. means for keeping electrical neutrality
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Abstract
A micro-Newton variable thruster based on gas field ionization enhancement belongs to the technical field of space propulsion. The invention comprises the following steps: the micro-jet pipe of the micro-Newton stage cold air thruster and the field ionization enhancement device are integrated and have a double-working-mode structure, and the carbon nano-tube field ionization thruster is integrated at the outlet of the expansion section of the jet pipe through an interface. The neutralizer is arranged at the periphery of the field ionization thruster. The thrust can work in two modes, and when the field ionization thruster is not electrified, the thrust works in a cold air thruster state; when the field ionization thruster is powered on, gas enters the field ionization thruster through the interface, the curvature radius of the tip of the carbon nano tube is only nano, the carbon nano tube has a strong local electric field, and the introduced gas is ionized to form ion flow. The positive ions are led out through the extraction stage, and are accelerated through the acceleration grid electrode to generate thrust. The neutralizer on the periphery of the field ionization thruster utilizes a tunneling effect, is easy to carry out electron emission, and neutralizes the extracted positive ions.
Description
Technical Field
The invention relates to a micro-Newton variable thruster based on gas field ionization enhancement, and belongs to the technical field of space propulsion.
Background
The micro-Newton grade variable thrust cold air thruster is a basic configuration of an on-orbit flight non-towing control spacecraft at the present stage, a non-towing control technology is applied to a plurality of high-precision scientific detection model tasks of NASA & ESA, including MICROCOPE of ESA, GRACE, GOCE, LISA Pathfinger of NASA & ESA and the like, and the micro-Newton grade cold air thruster technology has the advantages of good working stability, cross-order thrust regulation, high reliability and the like, but is relatively low compared with thrust; in order to improve the specific impulse performance, reduce the carrying amount of propellant and prolong the on-orbit service life of a spacecraft on the basis of the conventional micro-cow cold air variable thrust module, the performance of the micro-cow cold air variable thrust module needs to be improved on the basis of the conventional thruster, the conventional propulsion system is considered, the system cost and the volume are reduced as much as possible, and a uniform propulsion system is formed as much as possible, namely the micro-cow cold air variable thrust module is realized by adopting one set of propulsion system. The invention provides an enhanced micro-Newton variable thruster for gas field ionization, which has the technical advantages of a cold air and electric propulsion mode.
The micro-Newton electric thruster adopting the gas working medium mainly comprises a radio frequency ion thruster, a cusped magnetic field thruster, a microwave ion thruster and the like, and the thrusters are overlarge in weight and volume, complex and difficult to realize integrated integration with a cold air thruster. The field ionization thruster based on the carbon nano tube has the advantages of small size, light weight, simple structure, low power consumption, high current density, high efficiency and the like. The carbon nano tube can be used as an ideal novel vacuum electron emission source and also can be used as an ionization device, and has the main characteristics of small excitation voltage and large generated current, and has certain advantages compared with the traditional ionization device. The carbon nanotube field ionization thruster has the potential of being integrated with a micro-Newton grade cold air thruster to improve the performance of the thruster.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects of the prior art are overcome, the micro-Newton grade variable thruster based on gas field ionization enhancement is provided, the problems that the micro-Newton cold air thruster is low in specific impulse, the field ionization thruster is too large in weight and size, complex in structure and difficult in integration are solved, the service life of the thruster in orbit can be prolonged, and the task range is expanded.
The technical solution of the invention is as follows: a micro-Newton variable thruster based on gas field ionization enhancement comprises a micro-Newton cold air thruster micro-jet pipe structure, a carbon nano-tube field ionization thruster connected to the outlet end of the micro-jet pipe structure of the micro-Newton cold air thruster, and a neutralizer arranged at the periphery of the carbon nano-tube field ionization thruster to form an integrated structure, wherein the thruster works in a cold air mode, a field ionization thruster mode or a cold air and field ionization thruster mode;
the micro-jet pipe structure of the micro-Newton cold air thruster is used for providing cold air thrust, and the working medium is inert gas;
the carbon nanotube field ionization thruster is used for carrying out field ionization on a gas working medium to form ion current, positive ions are led out through an extraction stage, the ions are accelerated through an acceleration grid to generate thrust, and the specific impulse of the thruster is improved in a plasma forming mode;
the neutralizer is used for electron emission, is arranged around the micro-Newton level cold air thruster and neutralizes the extracted positive ions by utilizing a tunneling effect.
Further, the micro-jet pipe structure of the micro-Newton cold air thruster comprises a piezoelectric driver, a pintle, a micro-channel and a jet pipe expansion section;
the pintle is connected with the piezoelectric driver, and displacement is controlled by the piezoelectric driver, so that the flow area of the throat is adjusted;
the micro-channel is positioned between the contraction spray pipe and the expansion spray pipe and is used for controlling the flow rate of the supplied working medium and the gas injection speed;
the rear part of the nozzle expansion section is communicated with the carbon nano tube anode of the carbon nano tube field ionization thruster through an interface.
Furthermore, the gas enters the micro-channel and the expansion nozzle through the pressure applied by the pressure storage cabin and then enters the carbon nano-tube field ionization thruster through an interface integrated at the rear part of the nozzle expansion section, and the working mode of the thruster is determined according to the working state of the carbon nano-tube field ionization thruster.
Further, the carbon nanotube field ionization thruster comprises a carbon nanotube anode, a power module, an extraction grid, an acceleration grid and a thruster insulation isolation structure;
the carbon nano tube anode comprises emitting electrode bases which are circularly arranged and is connected with the positive polarity through a lead with the power supply module;
the extraction grid and the acceleration grid are both metal plate circles which are of a net structure, have the same aperture and are uniformly distributed, and are connected with the negative polarity of the power module through a lead;
the insulating isolation structure of the thruster is made of insulating materials, is arranged on the outer side of the field ionization thruster in a barrel-shaped structure and is coaxially connected with the thruster structure.
Further, gas introduced through the micro-nozzle structure of the micro-Newton cold air thruster is ionized to form an ion flow; positive ions are led out through the extraction grid electrode, and the ions are accelerated through the acceleration grid electrode; the thrust is formed by leading out ions, and the control of the particle speed is realized by changing the potential difference between the extraction grid and the acceleration grid.
Further, the accelerating grid is used for increasing the ion speed after being accelerated by the extracting grid and reducing the beam divergence angle.
Furthermore, the neutralizer is in a hollow cylindrical shape with a certain thickness, and comprises a carbon nanotube cathode, an extraction grid, an acceleration grid and a neutralizer insulating and isolating structure, wherein the carbon nanotube cathode, the extraction grid, the acceleration grid and the neutralizer insulating and isolating structure are all hollow round plates;
the carbon nanotube cathode is connected with the negative polarity of the power supply module through a lead, the structures and materials of the extraction grid and the acceleration grid are consistent with those of the carbon nanotube field ionization thruster, and the carbon nanotube cathode is connected with the positive polarity of the power supply module through a lead;
the insulating isolation structure of the neutralizer is made of insulating materials, is arranged on the outer side of the neutralizer in a barrel-shaped structure, and is coaxially connected with the structures of the neutralizer and the thruster.
Further, the curvature radius of the carbon nanotube cathode tip is in the nanometer level.
Further, a negative voltage is applied to the carbon nanotube cathode of the neutralizer, electrons are emitted by utilizing a tunneling effect, and the electrons reach a particle neutralizing area at the tail of the thruster through the extraction grid and the acceleration grid to neutralize positive ions extracted by the carbon nanotube field emission.
Further, the carbon nanotube field ionization thruster is integrated into a jet pipe of the micro-Newton cold air thruster, and a corresponding working mode is selected according to whether the carbon nanotube field ionization thruster works or not:
when the carbon nanotube field ionization thruster is applied in space, the carbon nanotube field ionization thruster does not work, and a cold air thruster working mode is adopted to provide sub-micron thrust;
when a space detection task is carried out, the carbon nanotube field ionization thruster works, an electric thruster working mode is adopted to provide thrust above a micro-Newton level, and the carbon nanotube field ionization thruster emits electrons to neutralize gas ions by controlling the polarity of a direct current power supply.
Compared with the prior art, the invention has the advantages that:
(1) The performance of the gas field ionization thruster as a cold air thruster is enhanced, the original propulsion system is shared to realize space dual-mode propulsion, the large thrust and wide range of the original cold air propulsion are reserved, the integrated electric propulsion promotes the specific impulse of the thruster, the specific impulse can be promoted to be more than 1000s from 60s, the propellant utilization rate is effectively improved, and the on-orbit service life of the thruster is prolonged.
(2) The field ionization thruster based on the carbon nano tube is adopted as an integration scheme, the structural integration difficulty is reduced, and the integrated high integration of cold air and electric propulsion can be realized.
(3) The carbon nanotube array is adopted for gas field ionization, so that the length-diameter ratio is high, the gas ionization is very easy to realize, the energy is saved, and meanwhile, the insulation packaging cost caused by high voltage is reduced.
(4) And an integrated structure of anode ionization and a neutralizer cathode is adopted, so that the structural complexity is reduced.
(5) The field ionization thruster is added with an acceleration stage, so that the ion speed of the ionization thruster is further improved, and the specific impulse of the whole thruster is improved.
(6) The field ionization thruster is additionally provided with the accelerating grid, the plume particle beams can be focused, the collision corrosion of particles to the extraction grid is reduced, and the service life of the thruster is effectively prolonged.
(7) The technology can be used as an independent thruster technology and can also be used as the enhancement application of a cold air thruster, the space dual-mode propulsion is realized, and the application is flexible.
Drawings
FIG. 1 is an integrated structure diagram of an enhanced micro-Newton variable thruster based on gas field ionization according to the present invention;
FIG. 2 is a schematic view of the ionization of a carbon nanotube-based gas field according to the present invention;
FIG. 3 is a schematic diagram of the operation of the carbon nanotube field ionization thruster and neutralizer of the present invention;
fig. 4 is a system diagram of the enhanced micro-Newton variable thruster based on gas field ionization according to the present invention.
Detailed Description
In order to better understand the technical solutions, the technical solutions of the present application are described in detail below with reference to the drawings and specific embodiments, and it should be understood that the specific features in the embodiments and examples of the present application are detailed descriptions of the technical solutions of the present application, and are not limitations of the technical solutions of the present application, and the technical features in the embodiments and examples of the present application may be combined with each other without conflict.
The micro-Newton variable thruster based on gas field ionization enhancement provided by the embodiments of the present application is further described in detail with reference to the accompanying drawings in the specification, and specific implementations may include (as shown in fig. 1 to 4): a micro-jet pipe of a micro-Newton cold air thruster, a field ionization thruster based on a carbon nano tube and a cathode neutralizer based on the carbon nano tube. The micro-jet pipe structure of the micro-Newton cold air thruster comprises a piezoelectric driver 1, a pintle 2, a micro-channel 3 and a jet pipe expansion section 4. The carbon nanotube field ionization thruster is integrated at the outlet of the nozzle expansion section 4 through an interface, and the latter structure comprises a carbon nanotube anode 5, a power supply module 6, an extraction grid 7, an acceleration grid 8 and a thruster insulation isolation structure 9. The neutralizer is arranged at the periphery of the carbon nanotube field ionization thruster, and the structure of the neutralizer comprises a nanotube cathode, a power supply module 6, an extraction grid 11, an acceleration grid 12 and a neutralizer insulating and isolating structure 13.
And a carbon nanotube field ionization thruster is integrated at the outlet of a nozzle expansion section 4 of the micro-nozzle of the micro-Newton stage cold air thruster, and a neutralizer based on carbon nanotubes is integrated at the periphery of the field power thruster.
The pintle 2 of the micro-jet pipe of the micro-Newton grade cold air thruster is connected with the piezoelectric drive controller of the cold air thruster, and the rear part of the expansion section 4 of the jet pipe is communicated with the carbon nano tube anode 5 of the carbon nano tube field ionization thruster through an interface.
The emitter bases of the carbon nanotube field ionization thrustor are circularly arranged to form a carbon nanotube anode 5 and are connected with the power module 6 through a lead wire and a positive polarity, and the extraction grid 7 and the acceleration grid 8 are both formed by metal plate circles with a net structure, the same aperture and uniform distribution and are connected with the negative polarity of the power module 6 through a lead wire. The thruster insulation isolation structure 9 is made of insulation materials, is arranged on the outer side of the carbon nanotube field ionization thruster in a barrel-shaped structure, is coaxially connected with the thruster structure, and protects the internal structure from being interfered by external factors.
The neutralizer is integrated on the outer side of the carbon nanotube field ionization thruster through a base, the structure is in a hollow cylindrical shape with a certain thickness, and the configurations of the carbon nanotube cathode 10, the extraction grid 11 and the acceleration grid 12 are hollow round plates. The carbon nanotube cathode 10 of the neutralizer is connected with the negative polarity of the power module 6 through a lead, the structures and materials of the extraction grid 11 and the acceleration grid 12 are consistent with those of the carbon nanotube field ionization thruster, and the structures and materials are connected with the positive polarity of the power module 6 through a lead. The insulating isolation structure 13 of the neutralizer is made of insulating materials, is arranged on the outer side of the neutralizer in a barrel-shaped structure, is coaxially connected with the structures of the neutralizer and the thruster, and protects the internal structure from being interfered by external factors.
The micro-Newton variable thruster based on gas field ionization enhancement is characterized by comprising a pintle 2 of a micro-jet pipe of the micro-Newton cold gas thruster, wherein the pintle is controlled to move by a piezoelectric driver 1 of the cold gas thruster, so that the high-precision adjustment of the flow area of the throat part is realized. The gas enters the micro-channel 3 and the expansion nozzle through the pressure of the pressure storage cabin and then enters the carbon nano tube field ionization thruster through an integrated interface behind the nozzle expansion section 4, and the working mode of the enhanced micro-Newton variable thruster based on gas field ionization is determined according to the working state of the carbon nano tube field ionization thruster. Under the dormant state of the carbon nanotube field ionization thruster, the enhanced micro-Newton variable thruster reserves the sub-micro-Newton thrust of the original micro-Newton level cold air thruster and is in a cold air propulsion mode. After a certain voltage is applied, the carbon nanotube field ionization thruster can generate a micro-Newton thrust with high specific impulse under the working state, and the electric propulsion mode is adopted at the moment.
The micro-Newton variable thruster based on gas field ionization enhancement is characterized by further comprising an emitting electrode base of the carbon nano tube field ionization thruster, wherein the emitting electrode base forms a carbon nano tube cathode 10, the structure of the carbon nano tube has a large length-diameter ratio, the curvature radius of the tip of the carbon nano tube is only nano, the tip has a strong local electric field after the power supply is switched on, and gas introduced through a micro-jet pipe of the cold air thruster can be ionized to form ion flow. The positive ions are extracted by the extraction grid 7 and accelerated by the acceleration grid 8. The thrust is formed by extracting ions, and the control of the particle speed is realized by changing the potential difference between the extraction grid 7 and the acceleration grid 8. The performance enhancement characteristic and the variable thrust capability of the thruster are realized.
According to the gas field ionization enhancement-based micro-Newton variable thruster, the accelerating grid 8 is further used for accelerating ions accelerated by the extraction grid 7, the beam divergence angle is reduced, and the collision loss between the ions and the extraction grid 7 is reduced, so that the specific impulse of the whole thruster is improved, the corrosion of the extraction pole is reduced, and the service life of the thruster is prolonged.
The micro-Newton-scale variable thruster based on gas field ionization enhancement is characterized by further comprising a neutralizer, wherein the neutralizer is arranged at the periphery of the carbon nanotube field ionization thruster, a certain negative voltage is applied to a carbon nanotube cathode 10 of the neutralizer, electrons are emitted by utilizing a tunneling effect, and the electrons reach a particle neutralization area at the tail of the thruster through an extraction grid 11 and an acceleration grid 12 to neutralize positive ions emitted and led out by the carbon nanotube field.
The micro-Newton variable thruster based on gas field ionization enhancement is characterized by further comprising an integration mode of the micro-Newton cold air thruster and the carbon nanotube field ionization thruster. Integrate carbon nanotube field ionization thrustor to little ox level air conditioning thrustor spray tube, can form dual mode working method according to the state that whether carbon nanotube field ionization thrustor worked, during the space application, at no drag control initial stage usually, it is great to need thrust, can adopt air conditioning thrustor working mode, provides the thrust of submicron ox. When the space detection task is carried out, the working mode of the electric thruster is adopted to provide thrust above a micro-Newton level, higher specific impulse can be output, fuel is saved, and the service life of the thruster is prolonged. The gas ions can be neutralized by controlling the polarity of a direct current power supply so that the carbon nanotube field ionization thruster emits electrons without being provided with an additional neutralizer.
In an embodiment of the present invention, the enhanced micro-cow variable thruster based on gas field ionization comprises: a micro-jet pipe of a micro-Newton cold air thruster, a field ionization thruster based on a carbon nano tube and a cathode neutralizer based on the carbon nano tube. As shown in the figure 1 and 2, a carbon nanotube field ionization thruster is integrated at the outlet of a nozzle expanding section 4 of a micro nozzle of the micro-Newton stage cold air thruster, and a neutralizer based on carbon nanotubes is integrated at the periphery of a field power thruster.
The micro-jet pipe structure of the micro-Newton cold air thruster comprises a piezoelectric driver 1, a pintle 2, a micro-channel 3 and a jet pipe expansion section 4. The pintle 2 is connected with a piezoelectric drive controller of the cold air thruster, and the rear part of the nozzle expansion section 4 is communicated with a carbon nano tube anode 5 of the carbon nano tube field ionization thruster through an interface.
The carbon nanotube field ionization thruster structurally comprises a carbon nanotube anode 5, a power module 6, an extraction grid 7, an acceleration grid 8 and a thruster insulation isolation structure 9.
The neutralizer is arranged at the periphery of the carbon nanotube field ionization thruster, and the structure of the neutralizer comprises a nanotube cathode, a power supply module 6, an extraction grid 11, an acceleration grid 12 and a neutralizer insulating isolation structure 13.
In the embodiment of the invention, as shown in fig. 1,2 and 3, the emitter bases of the carbon nanotube field ionization thrusters are circularly arranged to form the carbon nanotube anodes 5 and are connected with the power module 6 through the wires and the positive polarity, and the extraction grid 7 and the acceleration grid 8 are both formed by metal plate circles with a net structure, the same aperture and uniform distribution and are connected with the negative polarity of the power module 6 through the wires. The thruster insulation isolation structure 9 is made of insulation materials, is arranged on the outer side of the carbon nanotube field ionization thruster in a barrel-shaped structure, is coaxially connected with the thruster structure, and protects the internal structure from being interfered by external factors. The extraction stage can inhibit the damage caused by the back-bombardment of positive ions to the cathode, the voltage of the extraction stage is 300V-1000V, the voltage of the acceleration stage is 300V-500V, the extraction grid 7 and the acceleration grid 8 are made of molybdenum, the aperture of the extraction stage grid mesh is 30-50 mu m, and the diameter of the acceleration stage grid mesh is 60 mu m-100 mu m.
In the embodiment of the invention, as shown in fig. 1,2 and 3, the neutralizer is integrated outside the carbon nanotube field ionization thruster through a base, and has a hollow cylindrical structure with a certain thickness, and the carbon nanotube cathode 10, the extraction grid 11 and the acceleration grid 12 are all hollow circular plates. The carbon nanotube cathode 10 of the neutralizer is connected with the negative polarity of the power module 6 through a lead, the structures and materials of the extraction grid 11 and the acceleration grid 12 are consistent with those of the carbon nanotube field ionization thruster, and the structures and materials are connected with the positive polarity of the power module 6 through a lead. The neutralizer and the field ionization thruster share one set of power supply. The insulating isolation structure 13 of the neutralizer is made of insulating materials, is arranged on the outer side of the neutralizer in a barrel-shaped structure, is coaxially connected with the structures of the neutralizer and the thruster, and protects the internal structure from being interfered by external factors.
In the embodiment of the invention, as shown in fig. 2 and 4, the micro-Newton variable thruster based on gas field ionization enhancement is further characterized in that a pintle 2 of a micro-jet pipe of the micro-Newton cold gas thruster controls displacement through a piezoelectric driver 1 of the cold gas thruster, so that high-precision adjustment of the flow area of the throat is realized. The gas enters the micro-channel 3 and the expansion nozzle through the pressure of the pressure storage cabin and then enters the carbon nano tube field ionization thruster through an integrated interface behind the nozzle expansion section 4, and the working mode of the enhanced micro-Newton variable thruster based on gas field ionization is determined according to the working state of the carbon nano tube field ionization thruster. Under the dormant state of the carbon nanotube field ionization thruster, the enhanced micro-Newton variable thruster reserves the sub-micro-Newton thrust of the original micro-Newton level cold air thruster and is in a cold air propulsion mode. After a certain voltage is applied, the carbon nanotube field ionization thruster can generate a thrust above a micro-Newton level with high specific impulse under the working state, and the electric propulsion mode is adopted at the moment. In the embodiment of the present invention, as shown in fig. 1,2 and 3, the micro-Newton's varying thruster based on gas field ionization enhancement is characterized by further comprising an emitter base of the carbon nanotube field ionization thruster, the emitter base constituting a carbon nanotube cathode 10, wherein the structure of the carbon nanotube has a large length-diameter ratio, the curvature radius of the tip of the carbon nanotube is only nanometers, and after the power supply is turned on, the tip has a strong local electric field, so that gas introduced through the micro-jet tube of the cold gas thruster can be ionized to form an ion flow. The positive ions are extracted by the extraction grid 7 and accelerated by the acceleration grid 8. The thrust is formed by extracting ions, and the control of the particle speed is realized by changing the potential difference between the extraction grid 7 and the acceleration grid 8. The performance enhancement characteristic and the variable thrust capability of the thruster are realized.
In the embodiment of the invention, as shown in fig. 3, the micro-Newton variable thruster based on gas field ionization enhancement is characterized by further accelerating ions accelerated by the extraction grid 7 by the acceleration grid 8, reducing a beam divergence angle, and reducing collision loss of the ions and the extraction grid 7, thereby improving a specific impulse of the whole thruster, reducing corrosion of the extraction pole, and improving the service life of the thruster.
In the embodiment of the invention, as shown in fig. 1,2 and 3, the micro-Newton variable thruster based on gas field ionization enhancement is characterized in that a neutralizer is arranged at the periphery of the carbon nanotube field ionization thruster, a certain negative voltage is applied to a carbon nanotube cathode 10 of the neutralizer, electrons are emitted by utilizing a tunneling effect, and the electrons reach a particle neutralization region at the tail of the thruster through an extraction grid 11 and an acceleration grid 12 to neutralize positive ions extracted by carbon nanotube field emission.
In an embodiment of the present invention, as shown in fig. 4, the micro-newton-degree variable thruster based on gas field ionization enhancement is characterized by further including an integration manner of a micro-jet pipe of the micro-newton-degree cold gas thruster and a carbon nanotube field ionization thruster. The carbon nanotube field ionization thruster is integrated to the micro-jet pipe of the micro-Newton cold air thruster, a dual-mode working mode can be formed according to the working state of the carbon nanotube field ionization thruster, when the carbon nanotube field ionization thruster is applied in space, the required thrust is large at the initial stage of drag-free control, the working mode of the cold air thruster can be adopted, the sub-Newton thrust is provided, and the thrust range can cover 0.1-1000 mu N. When a space detection task is carried out, the working mode of the electric thruster is adopted to provide thrust above the micro-Newton level, and higher specific impulse (more than 1000 s) can be output in the 1-30 mu N mode, so that fuel is saved, and the service life of the thruster is prolonged. The gas ions can be neutralized by controlling the polarity of a direct current power supply so that the carbon nanotube field ionization thruster emits electrons without being provided with an additional neutralizer.
In the embodiment of the invention, when variable thrust regulation is carried out, variable thrust control is realized by regulating and controlling voltage and flow, the thrust regulation range is wider, and the regulation of the high specific impulse thrust working mode of 0.1-1000 muN can be realized.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present application without departing from the spirit and scope of the application. Thus, if such modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is intended to include such modifications and variations as well.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are not particularly limited to the specific examples described herein.
Claims (10)
1. A micro-Newton variable thruster based on gas field ionization enhancement is characterized by comprising a micro-Newton cold air thruster micro-jet pipe structure, a carbon nano-tube field ionization thruster connected to the outlet end of the micro-jet pipe structure of the micro-Newton cold air thruster, and a neutralizer arranged at the periphery of the carbon nano-tube field ionization thruster to form an integrated structure, wherein the thruster works in a double mode of cold air or field ionization thrusters;
the micro-jet pipe structure of the micro-Newton cold air thruster is used for providing cold air thrust, and the working medium is inert gas;
the carbon nanotube field ionization thruster is used for carrying out field ionization on a gas working medium to form ion current, positive ions are led out through an extraction stage, the ions are accelerated through an acceleration grid to generate thrust, and the specific impulse of the thruster is improved in a plasma forming mode;
the neutralizer is used for electron emission, is arranged around the micro-Newton level cold air thruster and neutralizes the extracted positive ions by utilizing a tunneling effect.
2. The micro-Newton grade variable thruster based on gas field ionization enhancement is characterized in that: the micro-jet pipe structure of the micro-Newton stage cold air thruster comprises a piezoelectric driver (1), a pintle (2), a micro-channel (3) and a jet pipe expansion section (4);
the pintle (2) is connected with the piezoelectric driver (1), and displacement is controlled by the piezoelectric driver (1) to realize adjustment of the flow area of the throat;
the micro-channel (3) is positioned between the contraction spray pipe and the expansion spray pipe and is used for controlling the flow rate of the supplied working medium and the gas injection speed;
the rear part of the spray pipe expansion section (4) is communicated with a carbon nano tube anode (5) of the carbon nano tube field ionization thruster through an interface.
3. The micro-Newton variable thruster based on gas field ionization enhancement is characterized in that: and gas enters the micro-channel (3) and the expansion nozzle through the pressure applied by the pressure storage cabin and then enters the carbon nano-tube field ionization thruster through an interface integrated at the rear part of the nozzle expansion section (4), and the working mode of the thruster is determined according to the working state of the carbon nano-tube field ionization thruster.
4. The micro-Newton variable thruster based on gas field ionization enhancement is characterized in that: the carbon nanotube field ionization thruster comprises a carbon nanotube anode (5), a power module (6), an extraction grid (7), an acceleration grid (8) and a thruster insulation isolation structure (9);
the carbon nano tube anode (5) comprises emitting electrode bases which are circularly arranged and is connected with the positive polarity through a lead with the power supply module (6);
the extraction grid (7) and the acceleration grid (8) are both metal plate circles which are of a net structure, have the same aperture and are uniformly distributed, and are connected with the negative polarity of the power module (6) through a lead;
the insulating isolation structure (9) of the thruster is made of insulating materials, is arranged on the outer side of the field ionization thruster in a barrel-shaped structure, and is coaxially connected with the thruster structure.
5. The micro-Newton grade variable thruster based on gas field ionization enhancement is characterized in that: ionizing gas introduced through the micro-nozzle structure of the micro-Newton cold air thruster to form an ion flow; positive ions are led out through the extraction grid (7), and are accelerated through the acceleration grid (8); the thrust is formed by extracting ions, and the control of the particle speed is realized by changing the potential difference between the extraction grid (7) and the acceleration grid (8).
6. The micro-Newton variable thruster based on gas field ionization enhancement is characterized in that: the accelerating grid (8) is used for increasing the ion speed accelerated by the extraction grid (7) and reducing the beam divergence angle.
7. The micro-Newton grade variable thruster based on gas field ionization enhancement is characterized in that: the neutralizer is in a hollow cylindrical shape with a certain thickness and comprises a carbon nano tube cathode (10), an extraction grid (11), an acceleration grid (12) and a neutralizer insulating isolation structure (13), wherein the carbon nano tube cathode, the extraction grid, the acceleration grid and the neutralizer insulating isolation structure are all hollow round plates;
the carbon nanotube cathode (10) is connected with the negative polarity of the power supply module (6) through a lead, the structures and the materials of the extraction grid (11) and the acceleration grid (12) are consistent with those of the carbon nanotube field ionization thruster, and the carbon nanotube cathode is connected with the positive polarity of the power supply module (6) through a lead;
the insulating isolation structure (13) of the neutralizer is made of insulating materials, is arranged on the outer side of the neutralizer in a barrel-shaped structure, and is coaxially connected with the neutralizer and the thruster structure.
8. The micro-Newton variable thruster based on gas field ionization enhancement is characterized in that: the curvature radius of the tip of the carbon nanotube cathode (10) is in a nanometer level.
9. The micro-Newton grade variable thruster based on gas field ionization enhancement is characterized in that: and applying negative voltage to a carbon nano tube cathode (10) of the neutralizer, and emitting electrons by utilizing a tunneling effect, wherein the electrons reach a particle neutralizing area at the tail part of the thruster through an extraction grid (11) and an acceleration grid (12) to neutralize positive ions extracted by the carbon nano tube field emission.
10. The micro-Newton varying thruster based on gas field ionization enhancement according to any one of claims 1 to 9, wherein a carbon nanotube field ionization thruster is integrated to a jet tube of the micro-Newton cold gas thruster, and a corresponding working mode is selected according to whether the carbon nanotube field ionization thruster is in a working state:
when the carbon nanotube field ionization thruster is applied in space, the carbon nanotube field ionization thruster does not work, and a cold air thruster working mode is adopted to provide sub-micron thrust;
when a space detection task is carried out, the carbon nanotube field ionization thruster works, an electric thruster working mode is adopted to provide thrust above a micro-Newton level, and the carbon nanotube field ionization thruster emits electrons to neutralize gas ions by controlling the polarity of a direct current power supply.
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115753172A (en) * | 2022-11-22 | 2023-03-07 | 兰州空间技术物理研究所 | Method for monitoring unstable working state of ion thruster |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4663932A (en) * | 1982-07-26 | 1987-05-12 | Cox James E | Dipolar force field propulsion system |
| US20060168936A1 (en) * | 2005-01-31 | 2006-08-03 | The Boeing Company | Dual mode hybrid electric thruster |
| US20070234705A1 (en) * | 2003-03-20 | 2007-10-11 | Gregory Emsellem | Spacecraft thruster |
| 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 |
| US20160207642A1 (en) * | 2013-08-27 | 2016-07-21 | The Regents Of The University Of Michigan | Electrodeless plasma thruster |
| US20170210493A1 (en) * | 2014-07-30 | 2017-07-27 | Safran Aircraft Engines | Spacecraft propulsion system and method |
| WO2019025174A1 (en) * | 2017-07-31 | 2019-02-07 | Technische Universität Dresden | Field emission propulsion system and method for calibrating and operating a field emission propulsion system |
| CN110056491A (en) * | 2019-05-14 | 2019-07-26 | 大连理工大学 | A kind of carbon nano pipe array thruster |
| US20200340459A1 (en) * | 2017-12-12 | 2020-10-29 | Enpulsion Gmbh | Ion thruster |
| US20210300599A1 (en) * | 2018-08-02 | 2021-09-30 | Enpulsion Gmbh | Ion thruster for thrust vectored propulsion of a spacecraft |
-
2022
- 2022-07-25 CN CN202210877796.3A patent/CN115355145B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4663932A (en) * | 1982-07-26 | 1987-05-12 | Cox James E | Dipolar force field propulsion system |
| US20070234705A1 (en) * | 2003-03-20 | 2007-10-11 | Gregory Emsellem | Spacecraft thruster |
| US20060168936A1 (en) * | 2005-01-31 | 2006-08-03 | The Boeing Company | Dual mode hybrid electric thruster |
| 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 |
| US20160207642A1 (en) * | 2013-08-27 | 2016-07-21 | The Regents Of The University Of Michigan | Electrodeless plasma thruster |
| US20170210493A1 (en) * | 2014-07-30 | 2017-07-27 | Safran Aircraft Engines | Spacecraft propulsion system and method |
| WO2019025174A1 (en) * | 2017-07-31 | 2019-02-07 | Technische Universität Dresden | Field emission propulsion system and method for calibrating and operating a field emission propulsion system |
| US20200340459A1 (en) * | 2017-12-12 | 2020-10-29 | Enpulsion Gmbh | Ion thruster |
| US20210300599A1 (en) * | 2018-08-02 | 2021-09-30 | Enpulsion Gmbh | Ion thruster for thrust vectored propulsion of a spacecraft |
| CN110056491A (en) * | 2019-05-14 | 2019-07-26 | 大连理工大学 | A kind of carbon nano pipe array thruster |
Non-Patent Citations (5)
| Title |
|---|
| L.-Y. CHEN ETAL.: "A Micro Ionizer for Portable Mass Spectrometers using Double-gated Isolated Vertically Aligned Carbon Nanofiber Arrays", 2007 IEEE INTERNATIONAL ELECTRON DEVICES MEETING, 12 December 2007 (2007-12-12) * |
| 孙新锋;温晓东;张天平;郭宁;贾艳辉;吴辰宸;: "大功率射频场反构型等离子体电推进研究", 火箭推进, no. 01, 15 February 2018 (2018-02-15) * |
| 李永;刘旭辉;汪旭东;耿金越;龙军;胡鹏;秦宇;: "空间极小推力宽范围可调推进技术研究进展", 空间控制技术与应用, no. 06, 15 December 2019 (2019-12-15) * |
| 郭明坤 等: "微纳卫星新型动力系统研究进展", 上海航天, vol. 36, no. 6, 31 December 2019 (2019-12-31) * |
| 郭登帅;康小明;刘欣宇;贺伟国;杭观荣;李彦达;张锐;王政伟;余勇;: "场发射电推力器的研究现状及其关键技术", 火箭推进, no. 04, 15 August 2018 (2018-08-15) * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115753172A (en) * | 2022-11-22 | 2023-03-07 | 兰州空间技术物理研究所 | Method for monitoring unstable working state of ion thruster |
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