CN106286179A - Air suction type ion engine - Google Patents
Air suction type ion engine Download PDFInfo
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- CN106286179A CN106286179A CN201610895188.XA CN201610895188A CN106286179A CN 106286179 A CN106286179 A CN 106286179A CN 201610895188 A CN201610895188 A CN 201610895188A CN 106286179 A CN106286179 A CN 106286179A
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- 239000003380 propellant Substances 0.000 claims abstract description 20
- 150000002500 ions Chemical class 0.000 claims description 60
- 238000006243 chemical reaction Methods 0.000 claims description 3
- 230000005684 electric field Effects 0.000 claims description 3
- 230000029058 respiratory gaseous exchange Effects 0.000 claims description 3
- 238000009825 accumulation Methods 0.000 claims description 2
- 238000007599 discharging Methods 0.000 claims description 2
- 230000007774 longterm Effects 0.000 claims description 2
- 230000007935 neutral effect Effects 0.000 claims description 2
- 230000001105 regulatory effect Effects 0.000 claims description 2
- 238000012216 screening Methods 0.000 claims description 2
- 239000000470 constituent Substances 0.000 claims 1
- 238000012423 maintenance Methods 0.000 abstract description 2
- 238000005183 dynamical system Methods 0.000 abstract 1
- 230000001133 acceleration Effects 0.000 description 5
- 230000008901 benefit Effects 0.000 description 5
- 239000000126 substance Substances 0.000 description 5
- 238000013461 design Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 238000004458 analytical method Methods 0.000 description 3
- 238000011161 development Methods 0.000 description 3
- 230000006872 improvement Effects 0.000 description 2
- 229910052760 oxygen Inorganic materials 0.000 description 2
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007405 data analysis Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
- 238000010891 electric arc Methods 0.000 description 1
- 238000005485 electric heating Methods 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000005433 ionosphere Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000003472 neutralizing effect Effects 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 238000006479 redox reaction Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000004065 semiconductor Substances 0.000 description 1
- 230000003068 static 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
- F03H1/0006—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
- F03H1/0037—Electrostatic ion 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
- F03H1/0081—Electromagnetic plasma thrusters
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Electromagnetism (AREA)
- Plasma Technology (AREA)
Abstract
The present invention provides a kind of air suction type ion engine, can complete the tasks such as gesture stability, track maintenance, orbit maneuver as the dynamical system of the spacecrafts such as artificial satellite, airship, space station.The maximum feature of this invention is to use air suction type scheme, make full use of the rarefied atmosphere component working media as electromotor of orbit altitude, the demand even completely avoiding conventional aerospace device to self-contained propellant can be reduced largely, thus obtain and satellite weight and rocket launching cost are greatly lowered, significantly improve the incomes such as the lifetime of satellite, there is great application prospect and and considerable economic worth.Whole air suction type ion engine is mainly made up of following 5 parts: air intake duct, ionization chamber, accelerating grid electrode, ion neutralizer, power supply and management system.
Description
[ technical field ] A method for producing a semiconductor device
The invention relates to an air-breathing ion engine which can be used as a power system of spacecrafts such as artificial satellites, spacecrafts, space stations and the like to complete tasks such as spacecraft attitude control, orbit maintenance, orbit maneuvering and the like. According to the invention, the thin atmospheric component with the orbit height is used as the working medium of the engine through an air suction type scheme, so that the dependence of the traditional spacecraft on propellant carried by the spacecraft can be greatly reduced or even completely avoided, the benefits of greatly reducing the weight of the satellite and the launching cost of the rocket, remarkably prolonging the service life of the satellite and the like are obtained, and the engine has great application prospect and considerable economic value.
[ background of the invention ]
The engine system is a power source necessary for finishing various tasks of spacecrafts such as rockets, satellites and space stations, and the performance index of the engine directly determines the overall technical level of the spacecrafts. In recent years, the electric propulsion mode has obvious advantages compared with the traditional chemical propulsion mode due to the characteristics of high specific impulse and long service life, so that the electric propulsion mode is increasingly applied to the aspects of orbital satellites, deep space exploration and the like. According to different working principles, the electric propulsion can be classified into an electric heating type, an electromagnetic type and an electrostatic type. The ion engine belongs to an electrostatic electric propulsion technology which is widely applied at present.
The existing ion engines (and other electric propulsion modes or chemical propulsion modes) have the inevitable defect that the propellant must be carried by the spacecraft. Generally, the proportion of propellant in the initial weight of a satellite using chemical propulsion may even exceed 60%, if an electric propulsion technology such as an ion engine is used, the carrying amount of the propellant can be significantly reduced, however, the problem still cannot be completely solved, and the consumption of the propellant itself becomes the most important factor for limiting the service life of the satellite and influencing the launching cost of the satellite.
The invention provides an air-breathing type ion engine which innovatively utilizes a rarefied atmosphere component with an orbit height as a propellant, and can remarkably reduce the dependence of a satellite on the propellant carried by the satellite, thereby remarkably prolonging the service life of the satellite and reducing the launching cost.
[ summary of the invention ]
According to one aspect of the present invention, there is provided an air breathing ion engine, the overall system consisting essentially of the following 5 parts: the device comprises an air inlet channel, an ionization chamber, an acceleration grid, an ion neutralizer, a power supply, a management system and the like. The working principle and the system structure of the invention are shown in figure 1, and the functions of each part of the engine and the working flow of the system are described as follows:
the air inlet channel (1) is the most important technical characteristic of the air-breathing type ion engine different from the traditional ion engine and is also the greatest advantage of the air-breathing type ion engine. The air inlet channel (1) is used for collecting incoming flow atmosphere by utilizing the orbital flight speed of a satellite and taking the collected incoming flow atmosphere as a working medium of the ion engine; besides the conventional air inlet function, the positive ions in the incoming flow can be enriched and screened by utilizing a permanent magnet or an electromagnetic coil so as to improve the ion density in the engine and meet the index requirements of the engine on different thrust and power consumption;
the incoming air enters the ionization chamber (2) through the air inlet, the propellant is further ionized in the ionization chamber through electron bombardment or an ionizer (6), and O in the incoming air is enabled2、N2Conversion of isocomponent to O+、N+Plasma positive ions; meanwhile, the ionization chamber is internally provided with a permanent magnet or an electromagnetic coil to realize the deflection and collection of electrons;
o in ionization chamber+、N+Plasma positive ions pass through an accelerating grid (3) positioned at the tail part of the ionization chamber to obtain extremely high speed increment, so that reaction force is generated on the engine per se due to the momentum conservation principle, and the engine generates thrust;
the ion neutralizer (4) is used for collecting electrons generated in the ionization chamber and discharging the electrons from a jet nozzle at the tail of the engine so as to mix the electrons with a positive ion flow sprayed by the accelerating grid, and neutralizing the electric quantity, so that the phenomenon that the performance of the engine and the working environment of other equipment are influenced due to negative charge accumulation of the engine after long-term operation is avoided;
the power supply and management system (5) mainly completes the functions of reasonably and efficiently supplying electric energy on the spacecraft to each part on the engine, and comprises power supply to the ionizer, electromagnetic coil control, acceleration grid electric field control, ion neutralizer control and the like; at present, the most common energy source on spacecrafts such as satellites and the like is a solar battery, has the characteristics of stable energy, mature technology and high reliability, and is an ideal energy source for an air suction type ion engine.
According to one aspect of the present invention, there is provided an air breathing ion engine, characterized by:
1. the air inlet channel (1) is the most main technical characteristics and the greatest advantages of the air-breathing type ion engine different from the traditional ion engine, and comprises an air inlet, a flow regulating device, an ion deflection device and the like, and the air inlet channel (1) is used for collecting incoming flow atmosphere by utilizing the orbital flight speed of a satellite and is used as a propellant for the work of the ion engine;
2. besides the conventional air intake function, the air intake passage (1) can also utilize a permanent magnet or an electromagnetic coil to carry out the original positive ions (O) in the incoming flow+) Enrichment and screening are carried out to improve the surface density of ions and meet the index requirements of the engine on different thrust and power consumption;
3. the air inlet channel (1) has a flow regulation function, namely the mass flow of the engine is changed by adjusting the area of an air inlet, so that variable thrust regulation is realized;
4. the ionization chamber (1) has a secondary ionization function, namely whether neutral atoms in incoming flow atmospheric components are ionized or not can be selected according to the requirements of working modes, so that the requirements of power limitation and thrust under different task modes are met;
5. because the invention adopts the air-breathing scheme and utilizes the rarefied atmosphere component with the orbit height as the working medium of the engine, the invention does not need complex equipment such as a propellant storage tank, a conveying system and the like in the traditional satellite propulsion system, saves the weight, reduces the complexity, and improves the reliability and the service life of the satellite.
The beneficial effects of the invention patent include:
(1) by adopting the air suction type scheme, the rarefied atmosphere component at the orbit height can be fully utilized as the working medium of the engine, so that the dependence of the satellite on propellant carried by the satellite is reduced or even avoided, the method is equivalent to 'no working medium' propulsion in a certain sense, the satellite launching weight and launching cost can be greatly reduced, the satellite operation life is obviously prolonged, and the method has important application prospect and considerable economic value;
(2) compared with the traditional ion engine, the air suction type scheme provided by the invention omits equipment such as a propellant storage tank, a conveying system and the like, reduces the structural weight, reduces the complexity of the system, and can obviously improve the reliability and the service life of the satellite;
(3) the orbit altitude of the general low-orbit satellite is approximately in the earth atmosphere ionosphere range, in which the atmosphere component is partially ionized due to the action of solar radiation, and a large amount of O is existed+Plasma is a natural propellant of the air-breathing type ion engine, and can further save the ionization energy consumption of the engine;
(4) through years of research development and improvement, the technology of the traditional ion engine (carrying a propellant) is mature, and the traditional ion engine is applied to various satellites in large quantity at present, so that the ion engine is used as the basis of the invention and has the advantages of high technical maturity, small risk, short development period and low development cost;
(5) the air suction type concept adopted in the aviation field can release chemical energy only by utilizing oxygen in a dense atmosphere and still needing oxidation-reduction reaction with fuel carried by the air suction type concept, and the static acceleration method is adopted for accelerating the working medium, so that zero working medium carrying can be completely realized;
(6) the concept of using high-altitude atmospheric components as the propulsion working medium can be applied to other types of electric propulsion engines such as Hall engines, electric arc heating engines, magnetic plasma engines and the like, and has wide popularization value and application prospect.
[ description of the drawings ]
FIG. 1 is a view showing the working principle and system constitution of the present invention
The reference numbers illustrate:
1-inlet 2-ionization chamber 3-acceleration grid
4-ion neutralizer 5-power supply and management system
6-ionizer 7-electromagnetic coil
[ detailed description ] embodiments
The technical scheme of the invention is described in the following by combining the drawings and specific embodiments.
Generally, the environment in which orbital spacecraft such as satellites and space stations operate is close to vacuum, and because the atmosphere is extremely thin, the conventional air-breathing engine for the adjacent space craft cannot work due to insufficient air intake amount in the orbital environment. However, from another point of view, the satellite is in a weightless state when in orbit operation, the requirement on the thrust of the engine is far less than that of the adjacent space aircraft, and therefore, the feasibility of the on-orbit application of the air-breathing type ion engine scheme needs to be researched through specific data analysis.
In order to illustrate the design principle and the design process of the present invention, the following is to perform performance analysis and scheme design of the main parameters of the engine for a specific embodiment.
Assuming that the typical working orbit height of the air-breathing ion engine is 150km, the atmospheric parameter at the height is 3.0 × 10-9kg/m3Atmospheric component is O2、N2、O、O+. By referring to the parameters of common satellites and ion engines, the diameter of an air inlet of the air-breathing type ion engine is determined to be 200mm, and the flight speed of the satellite is about 7.8km/s when the orbit height is 150km, so that the mass flow of the air inlet of the engine is obtained as follows:
wherein,is the mass flow of the gas inlet, SinIs the area of the air inlet, ρ0For high atmospheric density of the track, V0Is the relative speed of the aircraft and the incoming flow (approximately equal to the on-orbit flight speed of the satellite).
Assuming that the ionization rate of the mass flow is 100% after passing through the ionization chamber, namely, the incoming air components are completely converted into O+、N+A positive ion. With an acceleration grid of 500V, the propellant can achieve the following velocity increments:
where Δ V is the propellant velocity increment, VaccTo accelerate the gate voltage, meThe/q is the average mass-to-charge ratio of the propellant and is 1.55 × 10-7kg/C。
According to the momentum theorem, the thrust generated is:
with reference to the conventional ion engine parameters, taking the engine efficiency of the present example as 0.5, the input power is required to be
The windward side is 1m2The atmospheric resistance of the satellite at the orbital altitude is generally 4.0 × 10-4N is far less than the thrust generated by the air-breathing type ion engine, namely, the residual thrust of the scheme adopting the air-breathing type ion engine is positive, and the design has technical feasibility and application value.
According to the analysis, the theoretical specific impulse of the air-breathing type ion engine is 8196s, the performance of the air-breathing type ion engine is far higher than that of a conventional chemical rocket engine (200 s-450 s), and the thrust and the specific impulse of the air-breathing type ion engine still have a larger improvement space within a power bearable range by increasing the voltage of an accelerating grid.
According to the above design and analysis process, the main performance parameters of the embodiments of the present invention can be obtained as follows:
the diameter of an air inlet of the engine is 200mm, the input power is 4742W, the acceleration grid voltage is 500V, the specific impulse of the engine is 8196s, the thrust of the engine is 59mN, and the mass of the carried propellant is 0 kg.
Claims (4)
1. An air breathing ion engine, characterized in that it comprises the following 5 parts:
the air inlet channel (1) is the most main characteristic of an air-breathing type ion engine different from the traditional ion engine, comprises an air inlet, a flow regulating device, an ion deflection device and the like, and is used for collecting incoming air by utilizing the orbital flight speed of a satellite to serve as a working medium of the ion engine;
an ionization chamber (2) comprising chamber wall, ionizer, electromagnetic coil, etc., wherein the ionization chamber ionizes the propellant by electron bombardment or contact ionizerDeep ionization to make O in the incoming air2、N2Conversion of isocomponent to O+、N+Plasma positive ions; meanwhile, the ionization chamber is internally provided with a permanent magnet or an electromagnetic coil to realize the deflection and collection of electrons;
the accelerating grid (3) is positioned at the tail part of the ionization chamber, consists of one or more groups of high-voltage electric fields, accelerates positive ions in the ionization chamber through electrostatic force (coulomb force), and ejects the positive ions from the tail part at a high speed, so that the engine generates thrust due to the momentum conservation principle;
the ion neutralizer (4) is used for discharging electrons generated in the ionization chamber from a tail nozzle of the engine to mix the electrons with a high-speed positive ion flow passing through the accelerating grid to neutralize the electric quantity, so that the phenomenon that the performance of the engine and the working environment of other equipment are influenced due to negative charge accumulation of the engine after long-term operation is avoided;
and the power supply and management system (5) is mainly used for completing the functions of energy supply, regulation and the like of each part of the engine, and comprises power supply to the ionizer, electromagnetic coil control, accelerating grid electric field control, ion neutralizer control and the like.
2. Air-breathing ion engine according to claim 1, characterised in that the inlet duct (1) is adapted to perform, in addition to the conventional air intake, a conventional air intake, also by means of an ion deflection device for the positive ions (O) already present in the incoming air+) And (4) enriching and screening to improve the surface density of ions in the engine and meet the index requirements of the engine on different thrust and power consumption.
3. Air-breathing ion engine according to claim 1, characterized in that the air inlet duct (1) has a flow regulation function, i.e. by adjusting the air inlet area, the mass flow of the engine is changed, thus achieving a variable thrust regulation.
4. The air-breathing ion engine according to claim 1, characterized in that the ionization chamber (2) has a secondary ionization function, i.e. it is selected whether to ionize neutral atoms in the incoming atmospheric constituents according to the needs of the working mode, so as to adapt to the power limitation and thrust requirements in different mission modes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610895188.XA CN106286179A (en) | 2016-10-14 | 2016-10-14 | Air suction type ion engine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201610895188.XA CN106286179A (en) | 2016-10-14 | 2016-10-14 | Air suction type ion engine |
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| CN106286179A true CN106286179A (en) | 2017-01-04 |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110159501A (en) * | 2019-06-28 | 2019-08-23 | 中国人民解放军国防科技大学 | Ultra-low orbit variable thrust air-breathing magnetoplasma thruster |
| CN110439771A (en) * | 2019-08-12 | 2019-11-12 | 北京精密机电控制设备研究所 | A kind of air-breathing pulse plasma thruster |
| CN111997853A (en) * | 2020-06-05 | 2020-11-27 | 中国科学院合肥物质科学研究院 | Near space environment air suction type radio frequency plasma propeller |
| CN113048033A (en) * | 2021-04-30 | 2021-06-29 | 中国科学院力学研究所 | Semiconductor precooling rarefied gas trapping device and implementation method |
| CN114294191A (en) * | 2021-12-06 | 2022-04-08 | 兰州空间技术物理研究所 | High-efficient ECR electric thruster of major diameter air inlet pipeline |
| CN114776547A (en) * | 2022-03-28 | 2022-07-22 | 广州大学 | A fuel-free satellite propulsion device and propulsion method |
| WO2022183920A1 (en) * | 2021-03-01 | 2022-09-09 | 陈晓彬 | Electromagnetic fluid vortex power device |
| CN115653859A (en) * | 2022-09-15 | 2023-01-31 | 北京航空航天大学 | Ignition method and system for self-neutralization radio frequency ion thruster |
| CN115949562A (en) * | 2023-02-27 | 2023-04-11 | 中国人民解放军国防科技大学 | A self-cooling air-breathing radio frequency plasma electric thruster |
| CN116022359A (en) * | 2022-12-27 | 2023-04-28 | 广州大学 | A low-orbit satellite jet-type attitude adjustment device |
| JP7455439B1 (en) | 2023-05-31 | 2024-03-26 | Ｍｕｓｃａｔスペース・エンジニアリング株式会社 | Artificial object control method, artificial object control device, and artificial object equipped with the same |
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2016
- 2016-10-14 CN CN201610895188.XA patent/CN106286179A/en active Pending
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110159501A (en) * | 2019-06-28 | 2019-08-23 | 中国人民解放军国防科技大学 | Ultra-low orbit variable thrust air-breathing magnetoplasma thruster |
| CN110159501B (en) * | 2019-06-28 | 2024-03-19 | 中国人民解放军国防科技大学 | Ultra-low rail variable thrust air suction type magnetic plasma thruster |
| CN110439771A (en) * | 2019-08-12 | 2019-11-12 | 北京精密机电控制设备研究所 | A kind of air-breathing pulse plasma thruster |
| CN111997853A (en) * | 2020-06-05 | 2020-11-27 | 中国科学院合肥物质科学研究院 | Near space environment air suction type radio frequency plasma propeller |
| WO2022183920A1 (en) * | 2021-03-01 | 2022-09-09 | 陈晓彬 | Electromagnetic fluid vortex power device |
| CN113048033A (en) * | 2021-04-30 | 2021-06-29 | 中国科学院力学研究所 | Semiconductor precooling rarefied gas trapping device and implementation method |
| CN114294191A (en) * | 2021-12-06 | 2022-04-08 | 兰州空间技术物理研究所 | High-efficient ECR electric thruster of major diameter air inlet pipeline |
| CN114776547A (en) * | 2022-03-28 | 2022-07-22 | 广州大学 | A fuel-free satellite propulsion device and propulsion method |
| CN115653859A (en) * | 2022-09-15 | 2023-01-31 | 北京航空航天大学 | Ignition method and system for self-neutralization radio frequency ion thruster |
| CN116022359A (en) * | 2022-12-27 | 2023-04-28 | 广州大学 | A low-orbit satellite jet-type attitude adjustment device |
| CN115949562A (en) * | 2023-02-27 | 2023-04-11 | 中国人民解放军国防科技大学 | A self-cooling air-breathing radio frequency plasma electric thruster |
| JP7455439B1 (en) | 2023-05-31 | 2024-03-26 | Ｍｕｓｃａｔスペース・エンジニアリング株式会社 | Artificial object control method, artificial object control device, and artificial object equipped with the same |
| WO2024247909A1 (en) * | 2023-05-31 | 2024-12-05 | Ｍｕｓｃａｔスペース・エンジニアリング株式会社 | Artificial object control method, artificial object control device, and artificial object comprising same |
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