CN111486071A - Air suction type electric propeller - Google Patents
Air suction type electric propeller Download PDFInfo
- Publication number
- CN111486071A CN111486071A CN202010332462.9A CN202010332462A CN111486071A CN 111486071 A CN111486071 A CN 111486071A CN 202010332462 A CN202010332462 A CN 202010332462A CN 111486071 A CN111486071 A CN 111486071A
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- air
- unit
- cavity
- gas
- air suction
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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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- 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
- F03H1/0012—Means for supplying the propellant
Abstract
The invention discloses an air suction type electric propeller which comprises an operating cavity, wherein one side of the cavity is provided with an air suction unit, the other side of the cavity is provided with an air injection unit, an air channel communicated with the air suction unit and the air injection unit is arranged in the cavity, and the air channel is also provided with a magnetic field unit and a radio frequency unit. The gas is ionized to form plasma through the radio frequency unit, and the plasma is collected and accelerated by the gas channel under the action of the magnetic field to obtain higher kinetic energy, so that the track maintenance operation is completed.
Description
Technical Field
The invention relates to the technical field of electric propulsion of spacecrafts, in particular to an air suction type electric propeller.
Background
In the past, the maintenance of ultra-low orbit (typically referring to orbits in the range of 100km to 300 km) satellite orbits has employed chemical thrusters to provide thrust, but for long term on-orbit satellites, chemical thrusts have consumed a large amount of resources and have had major limitations on life.
In recent years, foreign related research institutions adopt an electric propulsion mode as a space propulsion system, compared with the traditional chemical propulsion, the electric propulsion ratio is high, and the acceleration can be greatly accelerated under the condition of the same quality of carried propellant. Electric propulsion utilizes solar energy to supply power, ionizes the propellant and generates high-speed ejected plasma. Scientists have now conducted many years of research on the technology of aspirated electric propulsion, and research on aspirated grid-type ion thrusters, as represented in the united states, europe and japan, has achieved a series of results, analyzed and improved in terms of aspiration, ionization, heating and propulsion processes, but at present such aspirated electric thrusters still need to carry limited propellant to maintain long-term on-track operation.
Therefore, how to fully utilize the residual atmosphere of the satellite orbit as a propelling working medium to maintain the long-term on-orbit service of the satellite ultra-low orbit becomes a subject to be researched.
Disclosure of Invention
In view of the above-mentioned drawbacks and deficiencies of the prior art, it would be desirable to provide an air-breathing electric thruster that addresses the problem of how the electric thruster does not need to carry propellant to maintain orbital motion.
The application provides a formula of breathing in electric propulsor, including the cavity of operation, cavity one side is equipped with the unit of breathing in, and the opposite side is equipped with jet-propelled unit, the cavity is inside to be equipped with the intercommunication the unit of breathing in with the gas passage of jet-propelled unit, last magnetic field unit and the radio frequency unit of still being equipped with of gas passage.
Furthermore, the air suction unit is positioned at the front end of the cavity in the running direction, and the air injection unit is positioned at the tail end of the cavity in the running direction.
Further, the air suction unit is an air suction port formed at the front end of the cavity, and the air injection unit is an air injection port formed at the tail end of the cavity.
Furthermore, the air suction unit comprises a contraction port positioned at the front end of the cavity and an expansion port extending out of the cavity along the contraction port, and the air injection unit comprises a contraction port positioned at the tail end of the cavity and an expansion port extending out of the cavity along the contraction port.
Furthermore, the contraction port of the air suction unit and the contraction port of the air injection unit are fixedly connected with the air channel.
Further, the magnetic field unit comprises two electromagnetic coils, and the two electromagnetic coils are fixedly arranged around the periphery of the gas collecting channel.
Further, the radio frequency unit is a radio frequency antenna, and the radio frequency antenna is fixedly arranged around the periphery of the gas collecting channel.
Further, the radio frequency unit is located between the two magnetic field units.
Further, the cavity is a satellite cabin.
The application provides a formula of breathing in electric propulsor, with the track gas as propulsion working medium, the track gas gets into gas passage under the magnetic field unit effect through breathing in behind the unit, receives the radio frequency unit ionization and accelerates after that, forms high-speed plasma and by the jet orifice blowout, finally forms the electric propulsion plume that has thrust, adopts this kind of formula of breathing in electric propulsor can maintain the track height of ultralow orbit satellite, need not to carry working medium and can be long-term in-orbit operation.
Drawings
Other features, objects and advantages of the present application will become more apparent upon reading of the following detailed description of non-limiting embodiments thereof, made with reference to the accompanying drawings in which:
fig. 1 is a schematic structural diagram of an air-breathing electric propeller provided in an embodiment of the present invention.
Reference numerals: the device comprises an air suction unit 1, a cavity 2, an air injection unit 3, a gas channel 4, a magnetic field unit 5 and a radio frequency unit 6.
Detailed Description
The present application will be described in further detail with reference to the following drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant invention and not restrictive of the invention. It should be noted that, for convenience of description, only the portions related to the present invention are shown in the drawings.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
The embodiment of the application provides a formula of breathing in electric propeller, as shown in fig. 1, this formula of breathing in electric propeller includes cavity 2 of operation, 2 one sides of cavity are equipped with the unit of breathing in 1, and the opposite side is equipped with jet-propelled unit 3, 2 inside intercommunications that are equipped with of cavity inhale unit 1 with the gas passage 4 of jet-propelled unit 3, still be equipped with magnetic field unit 5 and radio frequency unit 6 on the gas passage 4.
The cavity 2 is a cavity with a certain operation speed and operation direction, preferably, the cavity 2 in operation refers to a satellite cabin, preferably, the gas in operation refers to orbital gas, also called neutral gas, in the embodiment, the orbital gas is used as a propelling working medium of the satellite cabin, and for an ultra-low orbit satellite in ultra-low orbit height, the orbital gas is residual atmosphere in an ultra-low orbit environment. The gas channel 4 is used here for collecting the rail gas sucked in by the suction unit and also for the passage of the rail gas propelled out of the chamber by the gas injection unit.
Specifically, one end of a gas channel 4 in the cavity 2 is structurally communicated with the air suction unit 1 on one side of the cavity 2, and the other end of the gas channel 4 in the cavity is structurally communicated with the air injection unit on the other side of the cavity 2, namely, in the cavity operation process, the rail gas is directly fed into the gas channel 4 after being sucked by the air suction unit 1, and preferably, the gas channel 4 is cylindrical.
Here, the gas passage 4 in the cavity 2 is further provided with a magnetic field unit 5 and a radio frequency unit 6, specifically, the gas passage 4 is internally provided with a gas circulation passage, so the magnetic field unit 4 and the radio frequency unit 3 can be arranged at any position on the outer surface of the gas passage 4, the gas passage 4 close to the air suction unit 1 can be sequentially provided with the magnetic field unit 5 and the radio frequency unit 6, or sequentially provided with the radio frequency unit 6 and the magnetic field unit 5, and in addition, a certain distance is formed between the magnetic field unit 5 and the radio frequency unit 6. More specifically, the magnetic field unit 5 is a component or device that can generate an electromagnetic field, and the radio frequency unit 6 is a component or device that can generate radio frequency and ionize gas.
Further, the air suction unit 1 is located at the front end of the cavity 2 in the running direction, and the air injection unit 3 is located at the tail end of the cavity 2 in the running direction.
Specifically, as shown in fig. 1, a suction unit 1 is disposed at the front end of the cavity 2 in the running direction, and an air injection unit 3 is disposed at the rear end of the cavity 2 in the running direction. Because the operation speed of the cavity 2 is higher than the atmospheric speed of the environment where the cavity 2 is located, in the process of advancing the cavity 2, the air suction unit 1 is equivalent to actively sucking the atmosphere in the environment where the cavity 2 is located, for a satellite cabin body which runs, the on-orbit operation speed of a satellite is generally about 7.8km/s, the acoustic velocity of orbital gas is about 340m/s, and the air suction unit 1 is used for actively sucking the orbital gas in the environment. In addition, the gas injection unit is used for actively injecting high-speed gas subjected to radio frequency ionization and magnetic field constraint in the gas channel to form electric propulsion plume with thrust, so that the orbit height of the ultra-low orbit satellite is maintained.
Optionally, the air suction unit 1 is an air suction port formed at the front end of the cavity 2, and the air injection unit 3 is an air injection port formed at the tail end of the cavity 2.
Specifically, the suction unit 1 in this embodiment is a suction port opened at the front end of the cavity 2 in the operation direction, the track gas directly enters the cavity 2 from the suction port, the gas injection unit 3 in this embodiment is a gas injection port opened at the rear end of the cavity in the operation direction, and the track gas is directly injected from the gas injection port after ionization and magnetic field action in the gas channel. It should be noted that the air suction port can be an opening with any shape formed on the cavity, and the air channel 4 is directly communicated with the air suction port; the gas injection port can be an opening with any shape formed on the cavity, and the gas channel 4 is directly communicated with the gas injection port.
Preferably, the air suction unit 1 includes a contraction port located at the front end of the cavity 2 and an expansion port extending out of the cavity 2 along the contraction port, and the air injection unit 3 includes a contraction port located at the tail end of the cavity 2 and an expansion port extending out of the cavity 2 along the contraction port.
Specifically, as shown in fig. 1, an opening is provided at the front end side of the cavity, the opening is a contraction port of the suction unit, and an opening extending outward from the cavity 2 along the contraction port is an expansion port of the suction unit; an opening is arranged at the tail end side of the cavity and is a contraction opening of the air injection unit, and an opening extending out of the cavity 2 along the contraction opening is an expansion opening of the air injection unit.
It should be noted that, assuming that the cross sections of the constricted opening and the enlarged opening of the suction unit or the air injection unit are both circular, the diameter of the enlarged opening is larger than that of the constricted opening. The air suction unit 1 in the embodiment is in a bell mouth shape, and the bell mouth is arranged to help to reduce the impact resistance of air to the cavity 2 body and to guide the air, namely, to help to suck the air. The air injection unit in the embodiment is in a bell mouth shape, and the arrangement of the bell mouth is favorable for smooth ejection of air along the bell mouth and plays a role in guiding the air.
Furthermore, the contraction port of the air suction unit 1 and the contraction port of the air injection unit 3 are fixedly connected with the air channel 4.
Specifically, as shown in fig. 1, the gas channel 4 in the cavity 2 is connected to the contraction port of the suction unit at the front end of the cavity 2, and the two are communicated with each other, that is, the gas enters from the expansion port and directly enters into the gas channel 4 after passing through the contraction port. The gas channel 4 in the cavity 2 is connected with the contraction port of the gas injection unit at the tail end of the cavity 2 and communicated with the contraction port. It should be noted that the gas passage 4 and the contraction port of the suction unit and the contraction port of the injection unit can be welded or mechanically sealed, and no matter which connection mode is adopted, the sealing performance of the connection position of the two is required to be ensured, and the gas is prevented from leaking from the connection position.
Preferably, the magnetic field unit 5 comprises two electromagnetic coils, and the two electromagnetic coils are fixedly arranged around the periphery of the gas channel 4.
Specifically, as shown in fig. 1, the magnetic field unit 5 is an electromagnetic coil which surrounds the periphery of the gas collecting channel 4 and is hooped on the gas channel 4, wherein the magnetic field generated by the electromagnetic coil is equivalent to a confining magnetic field which has a magnetic field gradient, and the magnetic field intensity which is increased from left to right is formed inside the gas channel, and the magnetic field gradient has a dominant and constraining effect on the gas flow direction in the gas channel 4. For example, the electromagnetic coil is a spiral coil formed by winding a conducting wire on the outer surface of the gas channel 4 in a certain direction, and when the current generated by the solar panel flows through the coil, a magnetic field is generated around the coil, as shown in fig. 1, it is assumed that two electromagnetic coils from left to right are a first electromagnetic coil and a second electromagnetic coil in sequence, the N poles of the two electromagnetic coils are both towards the right side, the coil is held by the right hand, and the thumb is towards the right side, and the direction of the other thumb is the direction of the current in each coil. The first electromagnetic coil is arranged for constraining the rail gas sucked by the gas suction unit to move towards the same direction so as to be collected in the gas channel 4, the second electromagnetic coil is arranged for constraining the plasma generated by radio frequency ionization, and the plasma can generate a magnetic field, so that the second electromagnetic coil not only enables the plasma to move towards the same direction, but also accelerates the plasma, and the high-speed plasma is sprayed out from the gas nozzle to form strong thrust.
Preferably, the radio frequency unit 6 is a radio frequency antenna, and the radio frequency antenna is fixedly arranged around the periphery of the gas channel 4.
Specifically, as shown in fig. 1, the rf unit 6 is an rf antenna, and the rf antenna generates an rf current, which is an electromagnetic wave with high frequency alternating current, and the high frequency electromagnetic wave causes gas molecules to collide at high speed to generate ionized gas, wherein positive and negative ions in the ionized gas have equal charges and are neutral as a whole, so that the ionized gas is also called plasma. The rf antenna is also uniformly arranged around the periphery of the gas channel 4 and fixed on the gas channel 4, and the purpose of uniform arrangement is to ionize all the gas entering the gas channel 4 and convert the gas into plasma completely. The generated plasma is a high-frequency moving plasma, the ionized gas obtains higher kinetic energy through coupling electric energy in the gas channel, the plasma jet is ejected at high speed to form thrust, the propelling operation of the satellite can be completed, and the satellite can operate in orbit for a long time without carrying more working media.
Further, the radio frequency unit 6 is located between the two magnetic field units 5.
Specifically, as shown in fig. 1, a first electromagnetic coil, a radio frequency unit and a second electromagnetic coil are sequentially arranged on a gas passage close to the air suction unit along the axial direction of the gas passage, the track gas is sucked into the first electromagnetic coil by the air suction unit, collected to the right side under the influence of the magnetic field gradient of the first electromagnetic coil, and then enters the radio frequency antenna, and is ionized to form plasma through the radio frequency antenna, and the plasma then enters the second electromagnetic coil, and is subjected to the domination and the constraint of the magnetic field of the second electromagnetic coil, and under the action of the magnetic field generated by the plasma, the plasma is accelerated to obtain higher kinetic energy, so that thrust is formed, and the track maintenance operation is completed.
In the embodiment shown in fig. 1, the satellite cabin runs to the left side, the front end of the left side of the satellite cabin is provided with an air suction unit, the tail end of the right side of the satellite cabin is provided with an air injection unit, a gas channel 4 close to the air suction unit 1 is sequentially provided with a magnetic field unit 5, a radio frequency unit 6 and a magnetic field unit 5, wherein the air suction unit 1 comprises a contraction port and an expansion port, the contraction port of the air suction unit is hermetically connected with the satellite cabin, the contraction port of the air injection unit is hermetically connected with the satellite cabin, the magnetic field unit 5 is an electromagnetic coil, the radio frequency unit 6 is a radio frequency antenna, as shown in the figure, the first electromagnetic coil is arranged at a position 20 cm away from the contraction port of the air suction unit, the radio frequency antenna 6 is arranged at a position 30 cm away from the first electromagnetic coil, and the.
The air suction type electric propeller is taken as the power base of an ultra-low orbit satellite, takes 150km orbit high speed as an example, and has the atmospheric density of 2 × 10-9kg·m-3The thrust required for track maintenance at ultra-low track heights is provided by the conversion of electrical energy to kinetic energy to provide the thrust required for position maintenance.
The cross section area of a contraction port of an air suction unit at the front end of a satellite cabin body is 1m2For example, the atmospheric resistance experienced by a satellite capsule is:
F＝ρv2S
wherein, for the drag coefficient, 2 is generally taken; rho is the orbital atmospheric density; v is the orbit running speed of the satellite, generally 7.8km/S, and S is the effective sectional area of a contraction opening.
The atmospheric resistance to the satellite capsule is calculated to be 243 mN.
In order to maintain the orbit effectively, the thrust of the air-breathing electric propeller is kept above 243mN, and when the effective cross-sectional area of the contraction opening of the air-breathing unit is 1m2In time, the mass of gas entering the satellite capsule per unit time is:
the mass of gas entering the satellite capsule per unit time was calculated to be 15.6 mg.
The required track maintenance thrust is provided according to the atmospheric resistance, and the corresponding specific impulse is as follows:
the required specific impulse is calculated to be 1557 s.
The electric power required by the satellite capsule to maintain orbit, calculated according to the efficiency of the electric propulsion system being 60%, is:
wherein η is system efficiency, the required electric power is about 6kW calculated, that is, the satellite solar panel needs to provide about 6kW of electric power to meet the requirement of long-time on-orbit service of the satellite at 150km ultra-low orbit height without carrying propellant working medium.
Similarly, according to the calculation process, the power supply power required by the specific satellite cabin structure at different ultralow orbit heights can be obtained through analysis, and the satellite cabin can meet the requirement of long-term on-orbit operation based on the air suction type electric propeller under the condition of system power supply.
The above description is only a preferred embodiment of the application and is illustrative of the principles of the technology employed. It will be appreciated by a person skilled in the art that the scope of the invention as referred to in the present application is not limited to the embodiments with a specific combination of the above-mentioned features, but also covers other embodiments with any combination of the above-mentioned features or their equivalents without departing from the inventive concept. For example, the above features may be replaced with (but not limited to) features having similar functions disclosed in the present application.
Claims (9)
1. The air suction type electric propeller is characterized by comprising an operating cavity, wherein an air suction unit is arranged on one side of the cavity, an air injection unit is arranged on the other side of the cavity, an air channel communicated with the air suction unit and the air injection unit is arranged in the cavity, and a magnetic field unit and a radio frequency unit are further arranged on the air channel.
2. The air-breathing electric propeller as claimed in claim 1, wherein the air suction unit is located at a front end of the chamber running direction, and the air injection unit is located at a rear end of the chamber running direction.
3. The air-breathing electric propeller as claimed in claim 2, wherein the air-breathing unit is an air-breathing port formed at the front end of the cavity, and the air-jetting unit is an air-jetting port formed at the rear end of the cavity.
4. The air-breathing electric propeller as claimed in claim 2, wherein the air-breathing unit comprises a contraction opening at the front end of the cavity and an expansion opening extending out of the cavity along the contraction opening, and the air-blowing unit comprises a contraction opening at the rear end of the cavity and an expansion opening extending out of the cavity along the contraction opening.
5. Air-breathing electric thruster according to claim 4, characterized in that the constrictions of the air suction unit and the air injection unit are fixedly connected to the air passage.
6. The aspirating electric thruster of claim 1, wherein said magnetic field unit comprises two electromagnetic coils, both of which are fixedly disposed around the periphery of said gas collection channel.
7. The aspirated electric thruster of claim 6, wherein the radio frequency unit is located between the two magnetic field units.
8. The aspirated electric thruster of claim 1, wherein said radio frequency unit is a radio frequency antenna fixedly arranged around the periphery of said gas collection channel.
9. The aspirating electric thruster of claim 1, wherein said chamber is a satellite pod.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010332462.9A CN111486071A (en) | 2020-04-24 | 2020-04-24 | Air suction type electric propeller |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010332462.9A CN111486071A (en) | 2020-04-24 | 2020-04-24 | Air suction type electric propeller |
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| CN202010332462.9A Pending CN111486071A (en) | 2020-04-24 | 2020-04-24 | Air suction type electric propeller |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113060290A (en) * | 2021-04-29 | 2021-07-02 | 陕西北斗金箭航空科技有限公司 | Electric propeller |
| CN113062839A (en) * | 2021-04-30 | 2021-07-02 | 中国科学院力学研究所 | Device and method for enhancing air suction by electron beam pre-ionization in air suction electric pushing technology |
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| WO2016151609A1 (en) * | 2015-03-24 | 2016-09-29 | Di Canto Gennaro | Plasma propulsion system and method |
| CN110159501A (en) * | 2019-06-28 | 2019-08-23 | 中国人民解放军国防科技大学 | Ultra-low rail variable thrust air suction type magnetic plasma thruster |
| CN110513260A (en) * | 2019-09-27 | 2019-11-29 | 哈尔滨工业大学（深圳） | A kind of radio frequency plasma propeller |
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| US6334302B1 (en) * | 1999-06-28 | 2002-01-01 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Variable specific impulse magnetoplasma rocket engine |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113060290A (en) * | 2021-04-29 | 2021-07-02 | 陕西北斗金箭航空科技有限公司 | Electric propeller |
| CN113062839A (en) * | 2021-04-30 | 2021-07-02 | 中国科学院力学研究所 | Device and method for enhancing air suction by electron beam pre-ionization in air suction electric pushing technology |
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