CN115355145B - Micro-bovine-grade variable thruster based on gas field ionization enhancement - Google Patents
Micro-bovine-grade variable thruster based on gas field ionization enhancement Download PDFInfo
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- CN115355145B CN115355145B CN202210877796.3A CN202210877796A CN115355145B CN 115355145 B CN115355145 B CN 115355145B CN 202210877796 A CN202210877796 A CN 202210877796A CN 115355145 B CN115355145 B CN 115355145B
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- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 118
- 239000002041 carbon nanotube Substances 0.000 claims abstract description 118
- 229910021393 carbon nanotube Inorganic materials 0.000 claims abstract description 118
- 150000002500 ions Chemical class 0.000 claims abstract description 43
- 238000000605 extraction Methods 0.000 claims abstract description 42
- 230000001133 acceleration Effects 0.000 claims abstract description 39
- 230000000694 effects Effects 0.000 claims abstract description 7
- 230000005641 tunneling Effects 0.000 claims abstract description 7
- 239000007789 gas Substances 0.000 claims description 51
- 238000002955 isolation Methods 0.000 claims description 16
- 239000007921 spray Substances 0.000 claims description 14
- 239000002245 particle Substances 0.000 claims description 10
- 239000011810 insulating material Substances 0.000 claims description 8
- 238000009413 insulation Methods 0.000 claims description 8
- 238000001514 detection method Methods 0.000 claims description 5
- 238000006073 displacement reaction Methods 0.000 claims description 4
- 239000000463 material Substances 0.000 claims description 4
- 229910052751 metal Inorganic materials 0.000 claims description 4
- 239000002184 metal Substances 0.000 claims description 4
- 238000006386 neutralization reaction Methods 0.000 claims description 4
- 230000009977 dual effect Effects 0.000 claims description 2
- 239000011261 inert gas Substances 0.000 claims description 2
- 238000002347 injection Methods 0.000 claims description 2
- 239000007924 injection Substances 0.000 claims description 2
- 230000005684 electric field Effects 0.000 abstract description 3
- 230000010354 integration Effects 0.000 description 6
- 238000005516 engineering process Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 230000002035 prolonged effect Effects 0.000 description 4
- 239000000243 solution Substances 0.000 description 4
- 230000001276 controlling effect Effects 0.000 description 3
- 230000007797 corrosion Effects 0.000 description 3
- 238000005260 corrosion Methods 0.000 description 3
- 230000001105 regulatory effect Effects 0.000 description 3
- 239000000446 fuel Substances 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 239000002071 nanotube Substances 0.000 description 2
- 239000003380 propellant Substances 0.000 description 2
- 238000009827 uniform distribution Methods 0.000 description 2
- IVDRCZNHVGQBHZ-UHFFFAOYSA-N 2-butoxyethyl 2-(3,5,6-trichloropyridin-2-yl)oxyacetate Chemical compound CCCCOCCOC(=O)COC1=NC(Cl)=C(Cl)C=C1Cl IVDRCZNHVGQBHZ-UHFFFAOYSA-N 0.000 description 1
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 description 1
- 238000004378 air conditioning Methods 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 229910052750 molybdenum Inorganic materials 0.000 description 1
- 239000011733 molybdenum Substances 0.000 description 1
- 238000004806 packaging method and process Methods 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
Classifications
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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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- Plasma & Fusion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Plasma Technology (AREA)
Abstract
A micro-bovine 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-cow-level cold air thruster and the field ionization enhancement device are integrated into a structure with a double working mode, and the outlet of the expansion section of the jet pipe is integrated with the carbon nano tube field ionization thruster through an interface. The neutralizer is disposed at the periphery of the field ionization thruster. The thrust can work in two modes, and when the on-site ionization thruster is not powered, the on-site ionization thruster 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 radius of curvature of the tip of the carbon nanotube is only nanometer, and the carbon nanotube has a strong local electric field, so that the introduced gas is ionized, and an ion flow is formed. Positive ions are led out through the extraction stage, and are accelerated through the acceleration grid electrode to generate thrust. The neutralizer at the periphery of the field ionization thruster utilizes tunneling effect, so that electron emission is easy to carry out, and the extracted positive ions are neutralized.
Description
Technical Field
The invention relates to a micro-bovine-grade variable thruster based on gas field ionization enhancement, and belongs to the technical field of space propulsion.
Background
The micro-bovine-grade variable-thrust cold air thruster is the basic configuration of a non-drag control spacecraft for on-orbit flight at the present stage, the non-drag control technology is applied to a plurality of ultra-high-precision scientific detection model tasks of NASA & ESA, including tasks of MICROSOPE of ESA, GRACE, GOCE, LISA PATHFINDER of NASA & ESA and the like, and the micro-bovine-grade cold air propulsion technology has the advantages of good working stability, cross-order-of-magnitude thrust adjustment, high reliability and the like, but has relatively low specific thrust; in order to improve specific impact performance on the basis of the existing micro-cow cold air variable thrust module, reduce the carrying quantity of the propellant and improve the on-orbit service life of the spacecraft, the performance is improved on the basis of the existing thruster, the existing propulsion system is considered, the cost and the volume of the system are reduced as much as possible, and a unified propulsion system is formed as much as possible, namely, the system is realized by adopting one set of propulsion system. The invention provides an enhanced micro-cow variable thruster for gas field ionization, which has the technical advantages of cold air and electric pushing modes.
The micro-cow-level electric thruster adopting the gas working medium mainly comprises a radio frequency ion thruster, a cusp magnetic field thruster, a microwave ion thruster and the like, and the thruster has overlarge weight volume and is relatively complex, so that the integrated integration with the cold air thruster is difficult to realize. The field ionization thruster based on the carbon nano tube has the advantages of small volume, light weight, simple structure, low power consumption, high current density, high efficiency and the like. Besides being an ideal novel vacuum electron emission source, the carbon nano tube can also be used as an ionization device, and has the main characteristics of small excitation voltage and large generation 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-cow cold air thruster to improve the performance of the thruster.
Disclosure of Invention
The invention solves the technical problems that: the utility model provides a little ox class change propeller based on gas field ionization reinforcing, has solved little ox air conditioning propeller than dashing down, the field ionization propeller weight volume is too big, the complicated structure and the integrated difficult problem of integration, can prolong the life-span and the extension task scope of propeller on orbit simultaneously.
The technical scheme of the invention is as follows: a micro-cow-level variable thruster based on gas field ionization enhancement comprises a micro-cow-level cold air thruster micro-jet pipe structure, a carbon nano tube field ionization thruster connected to the outlet end of the micro-cow-level cold air thruster micro-jet pipe structure, and a neutralizer arranged on 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 dual mode;
The micro-jet pipe structure of the micro-cow-level cold air thruster is used for providing cold air thrust, and working medium is inert gas;
The carbon nano tube field ionization thruster is used for field ionization of a gas working medium to form an ion flow, positive ions are led out through an extraction stage, the ions are accelerated through an acceleration gate to generate thrust, and the specific impulse of the thruster is improved in a form of forming plasma;
the neutralizer is used for electron emission, is arranged around the micro-cow cold air thruster, and neutralizes the extracted positive ions by utilizing a tunneling effect.
Further, the micro-jet pipe structure of the micro-cow-level 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 throat flow area is adjusted;
The micro-flow channel is positioned between the contracting jet pipe and the expanding jet pipe and is used for controlling the flow of the supplied working medium and the gas injection speed;
And the rear part of the spray pipe expansion section is communicated with a carbon nano tube anode of the carbon nano tube field ionization thruster through an interface.
Further, the gas enters the micro-channel through the pressure of the pressure storage cabin and enters the carbon nano tube field ionization thruster through the interface integrated behind the expansion section of the spray pipe after expanding the spray pipe, 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 nanotube anode comprises emitter bases which are circularly arranged and is connected with the power supply module through wires and positive polarity;
the extraction grid and the acceleration grid are of net structures, have the same aperture, are uniformly distributed in metal plate circles, and are connected with the negative polarity of the power supply module by leads;
The thruster insulating isolation structure 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, the gas which is introduced through the micro-jet pipe structure of the micro-cow-level 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 the extracted ions, and the particle speed is controlled by changing the potential difference of the extraction grid and the acceleration grid.
Further, the acceleration grid is used for increasing the speed of ions accelerated by the extraction grid and reducing the beam divergence angle.
Further, the structure of the neutralizer is in a hollow barrel shape with a certain thickness, and comprises a carbon nanotube cathode, an extraction grid, an acceleration grid and an insulated isolation structure of the neutralizer, wherein the configuration of the carbon nanotube cathode is a hollow circular plate;
The carbon nanotube cathode is connected with the negative polarity of the power module through a wire, and the structure and the material of the extraction grid and the acceleration grid are consistent with those of the carbon nanotube field ionization thruster and are connected with the positive polarity of the power module through a wire;
The neutralizer insulating isolation structure 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.
Further, the radius of curvature of the carbon nanotube cathode tip is nano-scale.
Further, negative voltage is applied to the carbon nanotube cathode of the neutralizer, electrons are emitted by utilizing tunneling effect, and the electrons reach a particle neutralization area at the tail part of the thruster through the extraction grid and the acceleration grid to neutralize positive ions emitted and led out by the carbon nanotube field.
Further, the carbon nanotube field ionization thruster is integrated into the micro-cow cold air thruster spray pipe, and a corresponding working mode is selected according to whether the carbon nanotube field ionization thruster works or not:
when the space is applied, the carbon nano tube field ionization thruster does not work, and a cold air thruster working mode is adopted to provide submicron cow thrust;
When the space detection task is carried out, the carbon nanotube field ionization thruster works, the electric thruster working mode is adopted to provide thrust above the micro-bovine level, and the polarity of the direct current power supply is controlled to enable the carbon nanotube field ionization thruster to emit electrons to neutralize gas ions.
Compared with the prior art, the invention has the advantages that:
(1) The integrated electric propulsion promotes the specific impulse of the thruster, and the specific impulse can be promoted from 60s to more than 1000s, so that the utilization rate of the propellant 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, so that the structural integration difficulty is reduced, and the integration high integration of cold air and electric pushing can be realized.
(3) The carbon nanotube array is adopted to carry out gas field ionization, so that the length-diameter ratio is high, gas ionization is easy to realize, energy is saved, and the insulation packaging cost caused by high voltage is reduced.
(4) The integrated structure of anode ionization and a neutralizer cathode is adopted, so that the structural complexity is reduced.
(5) The field ionization thruster increases the acceleration stage, and further improves the ion speed of the ionization thruster, thereby improving the specific impulse of the whole thruster.
(6) The field ionization thruster is added with the acceleration grid, so that plume particle beams can be focused, 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, so that the space dual-mode propulsion is realized, and the application is flexible.
Drawings
FIG. 1 is an integrated block diagram of an enhanced micro-cow variable thruster based on gas field ionization of the present invention;
FIG. 2 is a schematic diagram of 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 an enhanced micro-bovine variable propeller based on gas field ionization according to the present invention.
Detailed Description
In order to better understand the above technical solutions, the following detailed description of the technical solutions of the present application is made by using the accompanying drawings and specific embodiments, and it should be understood that the specific features of the embodiments and the embodiments of the present application are detailed descriptions of the technical solutions of the present application, and not limiting the technical solutions of the present application, and the technical features of the embodiments and the embodiments of the present application may be combined with each other without conflict.
The following describes in further detail a micro-bovine-stage variable propeller based on gas field ionization enhancement provided by the embodiment of the application with reference to the accompanying drawings, and the specific implementation manner may include (as shown in fig. 1 to 4): micro-jet pipe of micro-cow cold air thruster, field ionization thruster based on carbon nano tube and cathode neutralizer based on carbon nano tube. The micro jet pipe structure of the micro-cow-level cold air thruster comprises a piezoelectric driver 1, a pintle 2, a micro flow channel 3 and a jet pipe expansion section 4. The outlet of the spray pipe expansion section 4 is integrated with a carbon nano tube field ionization thruster through an interface, and the structure of the carbon nano tube field ionization thruster comprises a carbon nano tube 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 on the periphery of the carbon nanotube field ionization thruster, and the structure of the neutralizer comprises a nanotube cathode, a power module 6, an extraction grid 11, an acceleration grid 12 and a neutralizer insulation isolation structure 13.
And a carbon nano tube field ionization thruster is integrated at the outlet of the spray pipe expansion section 4 of the micro-jet pipe of the micro-cow-level cold air thruster, and a carbon nano tube-based neutralizer is integrated at the periphery of the field electric thruster.
The pintle 2 of the micro-jet pipe of the micro-cow-level cold air thruster is connected with the piezoelectric driving controller of the cold air thruster, and the rear part of the jet pipe expansion section 4 is communicated with the carbon nanotube anode 5 of the carbon nanotube field ionization thruster through an interface.
The emitter bases of the carbon nanotube field ionization thruster are circularly distributed to form a carbon nanotube anode 5 and are connected with a power module 6 through wires and a positive polarity, and the extraction grid 7 and the acceleration grid 8 are respectively 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 wires. The thruster insulating isolation structure 9 is made of insulating materials, is arranged on the outer side of the carbon nano tube 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 nano tube field ionization thruster through a base, the structure is in a hollow barrel shape with a certain thickness, and the configurations of the carbon nano tube cathode 10, the extraction grid 11 and the acceleration grid 12 are hollow circular plates. The carbon nanotube cathode 10 of the neutralizer is connected with the negative polarity of the power module 6 through a wire, and the structure 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 are connected with the positive polarity of the power module 6 through a wire. The neutralizer insulating isolation structure 13 is made of insulating materials, is arranged on the outer side of the neutralizer in a barrel-shaped structure, is coaxially connected with the neutralizer and the thruster structure, and protects the internal structure from being interfered by external factors.
The micro-bovine-level variable thruster based on gas field ionization enhancement is characterized by comprising a pintle 2 of a micro-jet pipe of the micro-bovine-level cold air thruster, wherein the pintle 2 controls displacement through a piezoelectric driver 1 of the cold air thruster, so that the high-precision adjustment of the throat flow area is realized. The gas enters the micro-channel 3 through the pressure of the pressure storage cabin and enters the carbon nano tube field ionization thruster through the interface integrated at the rear of the expansion section 4 of the spray pipe after expanding the spray pipe, and the working mode of the enhanced micro-cow variable thruster based on the gas field ionization is determined according to the working state of the carbon nano tube field ionization thruster. In the dormant state of the carbon nanotube field ionization thruster, the enhanced micro-cow variable thruster keeps the sub-micro cow thrust of the original micro cow cold air thruster and is in a cold air propulsion mode. After a certain voltage is applied, under the working state of the carbon nano tube field ionization thruster, the thrust above the micro-bovine level with high specific impulse can be generated, and the electric propulsion mode is adopted at the moment.
The micro-bovine-grade variable thruster based on gas field ionization enhancement is characterized by further comprising an emitter base of the carbon nanotube field ionization thruster for forming the carbon nanotube cathode 10, wherein the carbon nanotube has a structure with a large length-diameter ratio, the curvature radius of the tip is only nanometers, and the tip has a strong local electric field after being powered on, so that gas introduced through the micro-jet pipe of the cold air thruster can be ionized to form ion flow. Positive ions are extracted through the extraction grid 7 and accelerated through the acceleration grid 8. By extracting ions to form thrust, the particle speed is controlled by changing the potential difference between the extraction grid 7 and the acceleration grid 8. The performance enhancement characteristic and the thrust variation capability of the thruster are realized.
The micro-bovine stage variable thruster based on gas field ionization enhancement is characterized by further comprising an acceleration grid 8 for further accelerating ions accelerated by the extraction grid 7, reducing beam divergence angle, reducing collision loss of the ions and the extraction grid 7, thereby improving specific impact of the whole thruster, reducing corrosion of the extraction electrode and improving service life of the thruster.
The micro-bovine-grade variable thruster based on gas field ionization enhancement is characterized by further comprising a neutralizer which is arranged on the periphery of the carbon nanotube field ionization thruster, wherein a certain negative voltage is applied to a carbon nanotube cathode 10 of the neutralizer, electrons are emitted by utilizing tunneling effect, and the electrons reach a particle neutralization area at the tail part of the thruster through an extraction grid 11 and an acceleration grid 12 to neutralize positive ions led out by carbon nanotube field emission.
The micro-bovine-level variable thruster based on gas field ionization enhancement is characterized by further comprising an integrated mode of the micro-bovine-level cold air thruster and the carbon nano tube field ionization thruster. The carbon nanotube field ionization thruster is integrated into the micro-cow cold air thruster spray pipe, a dual-mode working mode can be formed according to whether the carbon nanotube field ionization thruster works or not, and when the carbon nanotube field ionization thruster is applied in space, the thrust is required to be larger at the initial stage of non-dragging control, and the cold air thruster working mode can be adopted to provide sub-micro cow thrust. When the space detection task is carried out, the electric thruster working mode is adopted to provide thrust above the micro-bovine level, and the high specific impulse can be output, so that the fuel is saved, and the service life of the thruster is prolonged. The carbon nano tube field ionization thruster emits electrons to neutralize gas ions by controlling the polarity of a direct current power supply without being provided with an additional neutralizer.
In an embodiment of the invention, the gas field ionization-based enhanced micro-calf variable thruster comprises: micro-jet pipe of micro-cow cold air thruster, field ionization thruster based on carbon nano tube and cathode neutralizer based on carbon nano tube. As shown in fig. 1 and 2, the outlet of the nozzle expansion section 4 of the micro-jet nozzle of the micro-cow cold air thruster is integrated with a carbon nano tube field ionization thruster, and a neutralizer based on carbon nano tubes is integrated at the periphery of the field electric thruster.
The micro-jet pipe structure of the micro-cow-level 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 driving controller of the cold air thruster, and 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.
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 on the periphery of the carbon nanotube field ionization thruster, and the structure of the neutralizer comprises a nanotube cathode, a power module 6, an extraction grid 11, an acceleration grid 12 and a neutralizer insulation isolation structure 13.
In the embodiment of the present invention, as shown in fig. 1,2 and 3, the emitter bases of the carbon nanotube field ionization thruster are circularly arranged to form a carbon nanotube anode 5 and are connected with the power module 6 through wires and positive polarity, and the extraction grid 7 and the acceleration grid 8 are both formed by metal plate circles with a mesh structure, the same aperture and uniform distribution and are connected with the negative polarity of the power module 6 through wires. The thruster insulating isolation structure 9 is made of insulating materials, is arranged on the outer side of the carbon nano tube 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 damage caused by positive ion back-bombing the cathode, the voltage of the extraction stage is 300-1000V, the voltage of the acceleration stage is 300-500V, the extraction grid 7 and the acceleration grid 8 are made of molybdenum, the aperture of the extraction stage grid is 30-50 mu m, and the diameter of the acceleration stage grid hole is 60-100 mu m.
In the embodiment of the present invention, as shown in fig. 1,2 and 3, the neutralizer is integrated on the outer side of the carbon nanotube field ionization thruster through the base, and 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 circular plates. The carbon nanotube cathode 10 of the neutralizer is connected with the negative polarity of the power module 6 through a wire, and the structure 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 are connected with the positive polarity of the power module 6 through a wire. The neutralizer and the field ionization thruster share a set of power supply. The neutralizer insulating isolation structure 13 is made of insulating materials, is arranged on the outer side of the neutralizer in a barrel-shaped structure, is coaxially connected with the neutralizer and the thruster structure, 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-cow-level variable thruster based on the gas field ionization enhancement is further characterized in that the pintle 2 of the micro-nozzle of the micro-cow-level cold air thruster controls displacement through the piezoelectric driver 1 of the cold air thruster, thereby realizing high-precision adjustment of the throat flow area. The gas enters the micro-channel 3 through the pressure of the pressure storage cabin and enters the carbon nano tube field ionization thruster through the interface integrated at the rear of the expansion section 4 of the spray pipe after expanding the spray pipe, and the working mode of the enhanced micro-cow variable thruster based on the gas field ionization is determined according to the working state of the carbon nano tube field ionization thruster. In the dormant state of the carbon nanotube field ionization thruster, the enhanced micro-cow variable thruster keeps the sub-micro cow thrust of the original micro cow 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 thrust with high specific impulse above the micro-bovine level in the working state, and is in an electric propulsion mode. In the embodiment of the invention, as shown in fig. 1,2 and 3, the micro-cow-level variable thruster based on gas field ionization enhancement is characterized by further comprising an emitter base of the carbon nanotube field ionization thruster for forming the carbon nanotube cathode 10, wherein the carbon nanotube has a large length-diameter ratio, the curvature radius of the tip of the carbon nanotube is only nanometer, the tip of the carbon nanotube has a strong local electric field after being connected with a power supply, and gas introduced through the micro-spray pipe of the cold air thruster can be ionized to form ion flow. Positive ions are extracted through the extraction grid 7 and accelerated through the acceleration grid 8. By extracting ions to form thrust, the particle speed is controlled by changing the potential difference between the extraction grid 7 and the acceleration grid 8. The performance enhancement characteristic and the thrust variation capability of the thruster are realized.
In an embodiment of the present invention, as shown in fig. 3, the micro-bovine stage variable thruster based on gas field ionization enhancement is further characterized in that the accelerating grid 8 accelerates the ions accelerated by the extracting grid 7, reduces the beam divergence angle, reduces the collision loss of the ions and the extracting grid 7, thereby improving the specific impact of the whole thruster, and reduces the corrosion of the extracting electrode to improve the service life of the thruster.
In the embodiment of the present invention, as shown in fig. 1,2 and 3, the micro-bovine-stage variable thruster based on gas field ionization enhancement is characterized in that the micro-bovine-stage variable thruster further comprises 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 tunneling effect, and the electrons reach a particle neutralization area at the tail part of the thruster via an extraction grid 11 and an acceleration grid 12 to neutralize positive ions led out by carbon nanotube field emission.
In an embodiment of the present invention, as shown in fig. 4, the micro-bovine-stage variable thruster based on gas field ionization enhancement is characterized by further comprising an integrated manner of the micro-bovine-stage cold air thruster micro-nozzle and the carbon nanotube field ionization thruster. The carbon nano tube field ionization thruster is integrated into the micro-jet pipe of the micro-cow cold air thruster, a dual-mode working mode can be formed according to whether the carbon nano tube field ionization thruster works or not, when the space application is carried out, the thrust is required to be larger at the initial stage of drag-free control, the cold air thruster working mode can be adopted, the sub-micro cow thrust is provided, and the thrust range can be covered by 0.1-1000 mu N. When the space detection task is carried out, the electric thruster working mode is adopted to provide thrust above the micro-cow level, and a higher specific impulse (more than 1000 s) can be output in the mode of 1-30 mu N, so that the fuel is saved, and the service life of the thruster is prolonged. The carbon nano tube field ionization thruster emits electrons to neutralize gas ions by controlling the polarity of a direct current power supply without being provided with an additional neutralizer.
In the embodiment of the invention, when the variable thrust is regulated, the variable thrust is controlled by regulating the voltage and the flow, so that the variable thrust has a wider thrust regulating range, and the regulation of a 0.1 mu N-1000 mu N high-ratio power-driven thrust working mode can be realized.
It will be apparent to those skilled in the art that various modifications and variations can be made to the present application without departing from the spirit or scope of the application. Thus, it is intended that the present application also include such modifications and alterations insofar as they come within the scope of the appended claims or the equivalents thereof.
What is not described in detail in the present specification is a well known technology to those skilled in the art.
Claims (10)
1. The micro-cow-level variable thruster based on gas field ionization enhancement is characterized by comprising a micro-cow-level cold air thruster micro-jet pipe structure, a carbon nano tube field ionization thruster connected to the outlet end of the micro-cow-level cold air thruster micro-jet pipe structure, and a neutralizer arranged on the periphery of the carbon nano tube field ionization thruster to form an integrated structure, wherein the thruster works in a cold air or field ionization thruster dual mode;
The micro-jet pipe structure of the micro-cow-level cold air thruster is used for providing cold air thrust, and working medium is inert gas;
The carbon nano tube field ionization thruster is used for field ionization of a gas working medium to form an ion flow, positive ions are led out through an extraction stage, the ions are accelerated through an acceleration gate to generate thrust, and the specific impulse of the thruster is improved in a form of forming plasma;
the neutralizer is used for electron emission, is arranged around the micro-cow cold air thruster, and neutralizes the extracted positive ions by utilizing a tunneling effect.
2. A gas field ionization enhanced micro-bovine variable propeller according to claim 1, wherein: the micro-jet pipe structure of the micro-cow-level 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 throat flow area;
the micro-flow channel (3) is positioned between the contracting jet pipe and the expanding jet pipe and is used for controlling the flow 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. A gas field ionization enhanced micro-bovine variable propeller according to claim 2, characterized in that: the gas enters the micro-channel (3) through the pressure of the pressure storage cabin and enters the carbon nano tube field ionization thruster through the interface integrated at the rear of the nozzle expansion section (4) after expanding the nozzle, and the working mode of the thruster is determined according to the working state of the carbon nano tube field ionization thruster.
4. A gas field ionization enhanced micro-bovine variable propeller according to claim 1, wherein: the carbon nano tube field ionization thruster comprises a carbon nano tube anode (5), a power supply module (6), an extraction grid (7), an acceleration grid (8) and a thruster insulation isolation structure (9);
The carbon nanotube anode (5) comprises emitter bases which are circularly arranged and is connected with the power supply module (6) through wires and positive polarity;
the extraction grid (7) and the acceleration grid (8) are of net structures, are uniformly distributed metal plate circles with the same aperture, and are connected with the negative polarity of the power supply module (6) through wires;
the thruster insulating isolation structure (9) 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 gas field ionization enhanced micro-bovine stage variable propeller of claim 4, wherein: ionizing the gas introduced through the micro-jet pipe structure of the micro-cow-level cold air thruster to form an ion flow; positive ions are led out through an extraction grid (7), and the ions are accelerated through an acceleration grid (8); the thrust is formed by the extracted ions, and the particle speed is controlled by changing the potential difference of the extraction grid (7) and the acceleration grid (8).
6. The gas field ionization enhanced micro-bovine stage variable propeller of claim 4, wherein: the accelerating grid (8) is used for increasing the speed of ions accelerated by the extracting grid (7) and reducing the beam divergence angle.
7. The gas field ionization enhanced micro-bovine stage variable propeller of claim 4, wherein: the structure of the neutralizer is in a hollow cylinder shape with a certain thickness, and comprises a carbon nanotube cathode (10), an extraction grid (11), an acceleration grid (12) and a neutralizer insulation isolation structure (13), wherein the configuration of the carbon nanotube cathode is a hollow circular plate;
The carbon nanotube cathode (10) is connected with the negative polarity of the power module (6) through a wire, and the structure and the material of the extraction grid (11) and the accelerating grid (12) are consistent with those of the carbon nanotube field ionization thruster and are connected with the positive polarity of the power module (6) through a wire;
The neutralizer insulating isolation structure (13) 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 gas field ionization enhanced micro-bovine stage variable propeller of claim 7, wherein: the radius of curvature of the tip of the carbon nanotube cathode (10) is nano-scale.
9. The gas field ionization enhanced micro-bovine stage variable propeller of claim 7, wherein: negative voltage is applied to a carbon nano tube cathode (10) of the neutralizer, electrons are emitted by utilizing tunneling effect, and the electrons reach a particle neutralization area at the tail part of the thruster through an extraction grid (11) and an acceleration grid (12) to neutralize positive ions emitted and led out by the carbon nano tube field.
10. The micro-bovine-level variable thruster based on gas field ionization enhancement according to any one of claims 1 to 9, wherein the carbon nanotube field ionization thruster is integrated into a micro-bovine-level cold air thruster nozzle, and the corresponding operation mode is selected according to whether the carbon nanotube field ionization thruster is operated or not:
when the space is applied, the carbon nano tube field ionization thruster does not work, and a cold air thruster working mode is adopted to provide submicron cow thrust;
When the space detection task is carried out, the carbon nanotube field ionization thruster works, the electric thruster working mode is adopted to provide thrust above the micro-bovine level, and the polarity of the direct current power supply is controlled to enable the carbon nanotube field ionization thruster to emit electrons to neutralize gas ions.
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