CN113062838A - Laser preionization enhanced air suction device and method for air suction electric propulsion technology - Google Patents
Laser preionization enhanced air suction device and method for air suction electric propulsion technology Download PDFInfo
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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
- F03H1/0081—Electromagnetic plasma thrusters
Abstract
The invention discloses a laser preionization enhanced air suction device for air suction electropushing technology, which comprises an air inlet, and a magnetic field generating mechanism and a laser beam generating mechanism which are arranged on the air inlet, wherein the air suction method is that the magnetic field generating mechanism is used for emitting laser beams to a target area set at the air inlet end of the air inlet in a flight environment and ionizing the gas in the target area to form charged particles; the magnetic field generating mechanism is used for forming a magnetic field for trapping the charged particles into the air inlet channel in the target area. According to the invention, gas molecules and atoms contained in the basic collectable area and the peripheral area of the air inlet channel are pre-ionized by the laser beam to form charged particles, and the charged particles formed by ionization can enter the air inlet channel along the magnetic field formed around the air inlet channel, so that the collecting cross section is increased on the premise of not changing the size of the air inlet channel, and the purpose of improving the gas collecting efficiency is achieved.
Description
Technical Field
The invention relates to the technical field of aviation, in particular to a laser preionization enhanced air suction device and method for an air suction electric propulsion technology.
Background
Ultra-low near-earth space is a field of strategic significance, mainly used for earth observation, and also used for civil and military communication. At lower altitudes, earth observation platforms can increase competitiveness by increasing payload performance (increasing image resolution and signal-to-noise ratio), while reducing size and power requirements.
Thrust is required for the aircraft to remain or move in space. Generally, aircraft use chemical propulsion devices like rockets, but electric propulsion is becoming increasingly popular because of its higher efficiency. However, conventional electric propulsion systems still use a propellant (e.g., xenon), and thus, the standby time of the aircraft is limited by the amount of propellant that can be carried by the aircraft. And aircraft operating within hundreds of kilometers of the earth's surface consume more propellant in order to counteract atmospheric drag.
Thus, an air-breathing electric propulsion system is produced. Sufficient air particles are collected as the aircraft sweeps across the top of the atmosphere to fuel the "aspirated" electric propellers, thereby eliminating the need to carry excess propellant during launch, while helping the aircraft to overcome atmospheric drag to continue operation on ultra-low ground tracks.
The air-breathing electric propulsion system for the low rail generally comprises three main parts, namely a trapping air inlet channel, a pressurization storage container and an electric thruster, and in the air-breathing electric propulsion system, a key technology is to trap lean gas in a flight environment to serve as a working medium of a thruster. To ensure adequate gas capture, gas capture efficiency is a critical factor. However, in space, the ambient gas is extremely dilute and the capture efficiency is limited. Therefore, how to effectively improve the gas trapping efficiency becomes a technical problem to be solved by those skilled in the art.
Disclosure of Invention
The invention aims to provide a laser preionization enhanced air suction device and a method for an air suction electric propulsion technology, and aims to solve the technical problems that in the prior art, the environment gas in outer space is extremely thin and the trapping efficiency is limited.
In order to solve the technical problems, the invention specifically provides the following technical scheme:
a laser preionization enhanced air suction device for an air suction electric propulsion technology comprises an air inlet channel, and a magnetic field generating mechanism and a laser beam generating mechanism which are arranged on the air inlet channel;
the magnetic field generating mechanism is used for emitting laser beams to a target area set at an air inlet end of the air inlet channel in a flight environment and ionizing gas in the target area to form charged particles;
the magnetic field generating mechanism is used for forming a magnetic field for trapping the charged particles into the air inlet channel in the target area.
As a preferable aspect of the present invention, the laser beam generating mechanism includes at least one laser disposed in a circumferential direction of the air inlet, and the lasers are all used for laser beams after being expanded according to a target divergence angle.
As a preferable aspect of the present invention, a divergence angle of a laser beam emitted by each of the lasers is set to θ, and it is necessary to satisfy:
wherein, Te，Th，mh，vhAnd U is electron temperature, gas temperature, atomic mass, gas collision rate, and aircraft, respectively.
As a preferable scheme of the present invention, a direction of each laser beam emitted by each laser faces an incoming flow direction relative to the air inlet, and the direction of each laser beam deviates outward to form an angle θ/2 with an axial direction of the air inlet.
As a preferable scheme of the invention, at least one laser in the circumferential direction of the air inlet is used for emitting laser beams with energy of 14.5eV and laser beams with energy of 13.6eV into a target area in the flight environment;
at least one of the lasers includes at least one laser for emitting a laser beam having an energy of 20 eV.
As a preferable scheme of the present invention, at least one of the lasers in the circumferential direction of the air inlet channel includes at least one ultraviolet laser for simultaneously emitting laser beams with a wavelength of 85.72nm and a wavelength of 91.40nm or at least two ultraviolet lasers for respectively emitting laser beams with a wavelength of 85.72nm and a wavelength of 91.40 nm;
at least one of the lasers comprises at least one extreme ultraviolet laser for emitting a laser beam having a wavelength of 62.1 nanometers.
As a preferable scheme of the invention, laser beam envelopes formed by laser beams emitted by adjacent lasers are partially overlapped, so that a trapping area formed by each laser beam around the circumferential direction of the air inlet channel is larger than a laser beam ionization area envelope formed by an air inlet section of the air inlet channel in a flight environment.
As a preferable scheme of the present invention, the magnetic field generating mechanism includes a plurality of permanent magnets arranged uniformly in the circumferential direction of the air inlet or an electromagnetic coil surrounding the circumferential direction of the air inlet, and the magnetic field generating mechanism is configured to form magnetic lines of force in a nozzle configuration at the air inlet end of the air inlet.
The invention provides an air suction method for enhancing an air suction device by laser preionization according to the air suction electric pushing technology, which comprises the following steps:
ionizing gas in a target region in a flight environment to form charged particles by emitting a laser beam into the target region;
and providing acting force for the charged particles through a magnetic field formed around the air inlet channel, and trapping the charged particles into the air inlet channel.
As a preferable mode of the present invention, the energy of the laser beam is not lower than the first ionization energy required for the ionization of the gas.
Compared with the prior art, the invention has the following beneficial effects:
according to the invention, gas molecules and atoms contained in the basic collectable area and the peripheral area of the air inlet channel are pre-ionized by laser beams to form charged particles, and the charged particles formed by ionization can enter the air inlet channel along the magnetic field formed around the air inlet channel.
The invention can ionize the gas in the basic trapping area of the air inlet channel and the gas contained in the peripheral area of the basic trapping area of the air inlet channel, thereby increasing the trapping cross section on the premise of not changing the size of the air inlet channel and achieving the purpose of improving the gas trapping efficiency compared with the traditional method which can only trap the gas in the basic trapping area of the air inlet channel.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below. It should be apparent that the drawings in the following description are merely exemplary, and that other embodiments can be derived from the drawings provided by those of ordinary skill in the art without inventive effort.
FIG. 1 is a schematic diagram of a laser beam pre-ionization enhanced getter device for getter electrokinetic pushing technology according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of the magnetic field lines distribution of a getter device enhanced by laser beam pre-ionization according to an embodiment of the present invention;
FIG. 3 is a schematic view of a laser beam enhanced trapping region of a getter device enhanced by laser beam pre-ionization according to one embodiment of the present invention;
FIG. 4 is a flow chart of a method for enhancing gettering using laser beam pre-ionization for one gettering electroboosting technique emitted by an embodiment of the present invention;
FIG. 5 is a schematic diagram of the overall composition of an air-breathing electric propulsion system.
The reference numerals in the drawings denote the following, respectively:
1-air inlet channel, 2-laser beam generating mechanism, 3-magnetic field generating mechanism, 4-laser beam, 5-magnetic line, 6-laser beam envelope, 7-laser ionization region envelope, 8-catcher, 9-pressurizing storage and 10-electric thruster.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The life of conventional electric propulsion technology is limited by the carrying capacity of the propulsion medium and obviously does not meet the demand, and air-breathing electric propulsion has received attention as an advanced concept. The air-breathing electric propulsion is a propulsion technology with great potential for realizing the long-term orbit maintenance of the ultra-low orbit spacecraft. The technology does not need to carry a propelling working medium from the ground, but gas molecules in the rarefied atmosphere of a capture space are used as the propelling working medium to be supplied to the electric thruster after being decelerated and pressurized, as shown in figure 5.
To ensure adequate gas capture, gas capture efficiency is a critical factor. However, the aperture of the air inlet is limited, only lean gas molecules and atoms in a basic collectable area of the air inlet can be captured, and the size of the basic collectable area is determined according to the cross-sectional dimension of the air inlet, so that the capture efficiency is improved by increasing the capture surface, and only the cross-sectional dimension of the air inlet can be increased, but the weight of the aircraft is increased by increasing the size of the air inlet, so that the energy consumption of the aircraft can be increased in the process of launching or flying.
The scheme provided by the application aims to pre-ionize gas molecules and atoms contained in a basic collectable area and a peripheral area of the basic collectable area of the air inlet channel into charged particles through laser beams, and the charged particles formed through ionization can enter the air inlet channel along a magnetic field formed around the air inlet channel.
Because the gas in the basic trapping area of the air inlet channel can be ionized, and the gas contained in the peripheral area of the basic trapping area of the air inlet channel can be ionized, compared with the traditional method which can only trap the gas in the basic trapping area of the air inlet channel, the trapping cross section is increased on the premise of not changing the size of the air inlet channel, and the purpose of improving the gas trapping efficiency is achieved.
Examples
Referring to fig. 1, a laser preionization enhanced getter device for getter electropushing technology provided by an embodiment of the present invention, as shown in fig. 1, may include:
the device comprises a laser beam generating mechanism 2, a laser beam generating mechanism and a control mechanism, wherein the laser beam generating mechanism is used for emitting a laser beam 4 to a target area in a flight environment to ionize gas in the target area to form charged particles; the energy of the laser beam is not lower than the first ionization energy required by the gas ionization;
and the magnetic field generating mechanism 3 is used for providing acting force for the charged particles through a magnetic field formed around the air inlet 1 and trapping the charged particles into the air inlet 1.
Wherein the first ionization energy is the energy required for gaseous atoms of the ground state to lose one electron of the outermost layer. After the energy emitted by the laser beam reaches the first ionization energy required by gas ionization, the gas atoms form + 1-valent gas cations, so that the requirement of forming driving particles can be met, and the purpose of saving energy can be achieved.
Specifically, the target region may be a basic capturable region corresponding to the air intake duct (typically, a region corresponding to a frontal area of the air intake duct), or in another implementation, the target region may further include the basic capturable region of the air intake duct and a peripheral region thereof, so as to increase an air capture cross section.
The target area range can be determined according to actual needs, and the target area range is ensured to be positioned right in front of the aircraft gas capture system and larger than the cross section area of the air inlet channel.
Various implementations are possible for achieving the above-described purpose of increasing the gas trapping cross-section. For example, in one implementation, the laser beam generating mechanism 2 may include at least one laser beam generator disposed in the circumferential direction of the air intake duct, and the plurality of laser beam generators may emit oblique laser beams, so that each laser beam obliquely passes through the air intake duct base trapping area, thereby increasing the air trapping cross section.
Or, in another implementation manner, in order to obtain a further trapping effect, the laser beam generator includes a plurality of laser beam generators uniformly arranged along the circumferential direction of the air inlet, and each laser beam generator can emit laser according to a target divergence angle, so that the purpose of increasing the gas trapping section can be achieved more effectively through beam expanding treatment of the emitted laser beam.
Wherein, in a preferred embodiment, the divergence angle of each of the laser beam generators can be set to θ;
wherein, Te，Th，mh，vhAnd U is electron temperature, gas temperature, atomic mass, gas collision rate, and aircraft, respectively.
In order to further increase the ionization section formed after the laser beams are emitted, the direction of each laser beam faces to the incoming flow direction and deviates outwards to form an included angle theta/2 with the axial direction of the air inlet channel.
It should be noted that, in order to achieve the best capture efficiency enhancement in the solution provided by the present application, the laser beam generator included in the laser beam generating mechanism is disposed at the periphery of the air inlet, and in practical applications, the laser beam generator may also be installed at other positions of the aircraft, as long as it is ensured that the generated laser beam can irradiate the incoming air directly in front of the air inlet.
The magnetic force generating mechanism 3 can generate a magnetic field through a magnet and other devices, so that magnetic force lines are formed at the air inlet of the air inlet channel, and the charged particles enter the air inlet channel along the magnetic force lines. Further, in order to improve the acting force between the magnetic field and the charged particles, the charged particles are guided into the air inlet channel, and the magnetic field generating mechanism may include a plurality of permanent magnets which are uniformly arranged in the circumferential direction of the air inlet channel or an electromagnetic coil which surrounds the circumferential direction of the air inlet channel.
In addition, the specific magnetic field includes magnetic lines of force 5 of a magnetic nozzle configuration formed at the air inlet of the air inlet 1, so that the charged particles more effectively enter the air inlet along the magnetic lines of force 5.
In order to achieve the purpose, the magnetic field generating mechanism can be located at the position, close to the air inlet of the air inlet, of the air inlet in the circumferential direction of the air inlet, so that magnetic lines of force of a magnetic nozzle structure are formed at the air inlet of the air inlet.
The magnetic force lines of the magnetic spray pipe structure gradually diffuse from the inner side of the air inlet to the air inlet basic trapping area and the peripheral area thereof, so that charged particles formed by ionization in the air inlet basic trapping area and the peripheral area thereof can interact with the magnetic force lines, and finally move, contract and converge into the air inlet along the magnetic force lines.
In summary, the embodiment of the present application first ionizes the gas in the target region through the laser beam generating mechanism to ionize the gas into charged particles, and then provides acting force for the charged particles through the magnetic field formed around the air inlet channel, so as to trap the charged particles into the air inlet channel, thereby achieving the purpose of improving the gas trapping efficiency. The emitted laser beams can act on a larger range including the basic trapping area of the air inlet channel and the peripheral area of the basic trapping area by setting a divergence angle for the emitted laser beams, so that the purpose of further improving the trapping efficiency is achieved by enlarging the trapping range of the gas.
It should be noted that, since the first ionization energies required for different gases are usually different, and the gas compositions in different flight environments may be different, the type of laser to be configured may be determined according to the gas composition in a specific flight environment.
For example, when the aircraft flies around the earth, the flying environment is an earth low orbit flying environment, and the gas is an earth low orbit ambient gas; the laser beam generating mechanism is specifically configured to: a laser beam with energy of 14.5eV and a laser beam with energy of 13.6eV are emitted into a target region in a flight environment. Since the main components of the gas near the earth are nitrogen and oxygen, in practical use, the laser beams with two energies can be provided to ionize the nitrogen and the oxygen.
In one embodiment, at least one of the lasers includes at least one laser for simultaneously emitting a laser beam having an energy of 14.5eV and a laser beam having an energy of 13.6eV or at least two lasers for respectively emitting a laser beam having an energy of 14.5eV and a laser beam having an energy of 13.6 eV. The laser may be any laser that can simultaneously emit a laser beam having an energy of 14.5eV and a laser beam having an energy of 13.6 eV.
For example, it may be an active mode-locked laser that can simultaneously emit laser light at two target energies.
But may be any of a laser for emitting a laser beam having an energy of 14.5eV and a laser for emitting a laser beam having an energy of 13.6eV, respectively.
When two lasers for emitting different energies are configured, any one of the lasers capable of generating a laser beam with fixed energy may be selected, for example, any one of a gas laser, a solid laser, and a semiconductor laser.
In specific implementation, the transmitting frequency of the laser is set on the ground according to requirements.
It is conceivable that, in order to ensure that the emitted laser beams can uniformly act on the gas in the basic trapping area of the air inlet channel and the surrounding area thereof, the lasers emitting different energies may be arranged in a spaced distribution manner, and simultaneously, a part of the laser beams emitted by two adjacent lasers emitting the same energy may be overlapped.
Alternatively, in another embodiment, at least one of the lasers includes at least one uv laser for simultaneously emitting a laser beam having a wavelength of 85.72nm and a laser beam having a wavelength of 91.40nm or at least two uv lasers for respectively emitting a laser beam having a wavelength of 85.72nm and a laser beam having a wavelength of 91.40 nm. The ultraviolet laser with two wavelengths is adopted to emit ultraviolet laser with two wavelengths, namely laser beams with energy of 14.5eV and 13.6eV respectively can be formed by the ultraviolet laser with two wavelengths, and gas in the target area is ionized to form charged particles.
For another example, when the aircraft flies around a spark, the flying environment is a flying environment around the spark, and the gas is a spark atmospheric environment gas; the laser beam generating mechanism is specifically configured to: a laser beam with energy of 20eV is emitted into a target region in a flight environment.
Because the gas of the spark accessory mainly contains carbon dioxide, in actual use, laser beams with energy can be provided to ionize the carbon dioxide.
In one embodiment, at least one of the lasers includes at least one laser for emitting a laser beam having an energy of 20 eV. The type of laser selected and the arrangement is similar to that applied near the earth and is not as cumbersome here.
Alternatively, in another embodiment, at least one of the lasers comprises at least one extreme ultraviolet laser for emitting a laser beam having a wavelength of 62.1 nanometers. The laser beam with the energy of 20eV can be formed by adopting an extreme ultraviolet laser to emit extreme ultraviolet light with the wavelength of 62.1 nm.
The application provides an inhale electric push technique and use getter device with laser preionization reinforcing for aircraft when earth low orbit environment operation, the reinforcing is to the entrapment efficiency of earth low orbit environment gas. The method can also be used for enhancing the trapping efficiency of the gas in the Mars atmospheric environment when the aircraft operates in the Mars atmospheric environment.
When the material is used in the earth low-orbit environment, because the earth low-orbit environment gas is mainly nitrogen atoms (N) and oxygen atoms (O), the ionization energy is 14.5eV and 13.6eV respectively, under the irradiation of ultraviolet light, the following photoionization processes occur:
N+hν1→N++e,(hν1＝14.5eV) (1)
O+hν2→O++e,(hν2＝13.6eV) (2)
n produced by ionization+(Nitrogen ion), O+(oxygen ions) and e (electrons) have the same macroscopic velocity as the ambient gas and therefore have a relative velocity V with the in-flight inlet duct. A permanent magnet or an electromagnetic coil is arranged at an air inlet of the trapping air inlet channel to generate magnetic lines of force 5 in a magnetic spray pipe configuration, and charged particles move, contract and converge into the trapping air inlet channel along the magnetic lines of force under the constraint of the magnetic lines of force.
The laser beam with energy of 14.5eV and the laser beam with energy of 13.6eV correspond to the ultraviolet laser beam with electromagnetic energy wavelength of 85.72nm and the ultraviolet laser beam with electromagnetic energy wavelength of 91.40nm, and one or more ultraviolet lasers covering these two wavelengths or two ultraviolet lasers respectively corresponding to the wavelengths can generate ultraviolet light corresponding to the two. The ultraviolet light formed irradiates the ambient gas right in front of the aircraft after being expanded, so that the following ionization processes are generated:
N+hν1→N++e,(λ1＝85.72nm) (3)
O+hν2→O++e,(λ2＝91.40nm) (4)
when the device is used in a spark atmosphere environment, the main component of the spark atmosphere is carbon dioxide (CO)2) Under the irradiation of far ultraviolet light with the energy of 20eV, the following ionization reactions can remarkably occur:
CO2+hν1→CO2 ++e,(hν1≈20eV) (5)
from CO2The ionization reaction product is mainly CO+(molecular ions) and e (electrons) have the same macroscopic velocity as the ambient gas and therefore have a relative velocity V with the in-flight inlet. Permanent magnets or electromagnetic coils are arranged at the air inlet to generate magnetic lines of force in a magnetic spray pipe configuration, and charged particles move, contract and converge into the air inlet along the magnetic lines of force under the constraint of the magnetic lines of force.
The energy of 20eV corresponds to the wavelength of electromagnetic energy of 62.1nm, and one or more extreme ultraviolet lasers covering this wavelength generate extreme ultraviolet light corresponding thereto. After beam expansion, the ambient gas right in front of the flight is irradiated, so that the following ionization process is generated:
CO2+hν1→CO2 ++e,(λ≈62.1nm) (6)
n produced by ionization when used in the vicinity of the earth+(Nitrogen ion), O+(oxygen ion) and e (electron), which ionize to produce CO when used near Mars2 +(molecular ion) and e (electron), N + (nitrogen ion), O produced by ionization+(oxygen ion), CO2 +(molecular ions) and e (electrons) are the same as the ambient gasThe macro velocity, and therefore the relative velocity V to the in-flight inlet.
A permanent magnet or an electromagnetic coil is arranged at the air inlet of the air inlet channel to generate magnetic lines of force in a magnetic spray pipe configuration, and charged particles move, contract and converge into the air inlet channel along the magnetic lines of force under the constraint of the magnetic lines of force.
As shown in FIG. 3, the laser beam envelopes 5 formed by adjacent laser beam generating mechanisms partially overlap each other, and each laser beam forms a laser beam ionization region envelope 7 with a trapping section which is much larger than the air inlet section of the air inlet channel.
In order to obtain better gas trapping effect, the divergence angle of the laser beams can be adjusted through asymmetrical activation channels, and N laser beam generators can be uniformly arranged along the circumferential direction of the gas inlet channel, so that N laser beams uniformly distributed along the circumferential direction are generated. The divergence angle of each laser beam is θ.
In a preferred embodiment, the direction of each laser beam can be deviated from the axial direction theta/2 of the air inlet channel, so that the laser beam is mainly used for ionizing the peripheral gas of the trapping area (the area opposite to the cross section of the air inlet channel) of the trap. Compared with the gas trapping technology of the existing air suction type electric propulsion system, the device can improve the gas trapping area by 10-100 times (depending on the rarefied degree of the environmental gas and the number of laser beam generators).
Design regarding the divergence angle Q:
ionization triggered by the laser beam occurs predominantly after 1 photon free path λ. After the aircraft has flown for a distance λ, the charged particles should remain in the laser beam region, otherwise they will be lost compositely. The speed of the aircraft is U, then the time to flight the λ distance is:
according to the plasma bipolar diffusion law, the diffusion speed can be obtained as follows:
vd＝Dalnne (8)
wherein the bipolar diffusion coefficient is:
wherein n ise、Te、Th、mhV and vhRespectively electron number density, electron temperature, gas temperature, atomic mass and gas collision frequency. Thus, at a distance λ of flight of the aircraft, the distance of diffusion is:
to ensure that it is still within the laser beam, there should be: λ tan θ > Δ LdThus, it is possible to obtain:
according to formula (5) or formula (6), since an atom generates one electron every time it absorbs one photon, the electron density is proportional to the laser beam intensity. The variation of the laser beam intensity in the absorption medium is:
accordingly, lnneAvailable as lni (z) -z/λ:
since z > λ, so:
the application provides a inhale electric push technique and strengthen getter device with laser beam preionization, adopt the laser beam can become charged particle to the gas ionization in the target area, and the interact of rethread magnetic field and charged particle makes the charged particle in the wider scope enter into the intake duct to improve gaseous entrapment efficiency. The advantage of promoting the gas entrapment cross-section lies in, and adaptability is good, at the higher track of rarefied degree, because the increase of gas entrapment cross-section for the aircraft can catch sufficient propulsion working medium on the higher track of rarefied degree, avoids traditional air-breathing formula thruster to be difficult to the problem of continuous operation because of catching insufficient working medium.
As shown in fig. 4, the present application may further provide a method for enhancing gettering by laser pre-ionization in gettering electropushing technology, including:
s101, emitting laser beams into a target area in a flight environment, and ionizing gas in the target area to form charged particles; the energy of the laser beam is not lower than the first ionization energy required by the gas ionization;
specifically, the target region includes the air intake duct trapping region and a peripheral region thereof. Through ionizing the gas in the peripheral area of the air inlet channel, the gas contained in the peripheral area can also enter the air inlet channel, so that the aim of increasing the gas trapping section is fulfilled.
In practical use, laser beams with corresponding energy emitted to a target area by lasers capable of emitting laser beams with different energies can be configured according to different components in the flight environment of the aircraft according to the types of gases, so that the optimal ionization effect is achieved.
In particular, the method comprises the following steps of,
the emitting a laser beam into a target area in a flight environment includes:
a laser beam with energy of 14.5eV and a laser beam with energy of 13.6eV are emitted into a target region in a flight environment.
The flying environment is a spark-surrounding flying environment, and the gas is a spark atmospheric environment gas;
the emitting a laser beam into a target area in a flight environment includes:
a laser beam with energy of 20eV is emitted into a target region in a flight environment.
The specific configuration method may include:
according to the gas composition in different flight environments, a laser capable of emitting laser light required for ionizing the gas composition is configured on the ground on the aircraft, so that the gas in a target area in the flight environment is ionized to form charged particles, and the optimal ionization efficiency is guaranteed.
And S102, providing acting force for the charged particles through a magnetic field formed around the air inlet channel, and trapping the charged particles into the air inlet channel.
Wherein, in order to improve the effort between magnetic field and the charged particle, guide charged particle to in the entrapment intake duct, the magnetic field includes the magnetic line of force that has the magnetic nozzle configuration that forms at the air inlet of intake duct, so that charged particle follows the magnetic line of force gets into in the intake duct.
The above embodiments are only exemplary embodiments of the present application, and are not intended to limit the present application, and the protection scope of the present application is defined by the claims. Various modifications and equivalents may be made by those skilled in the art within the spirit and scope of the present application and such modifications and equivalents should also be considered to be within the scope of the present application.
Claims (10)
1. A laser preionization enhanced air suction device for an air suction electric propulsion technology is characterized by comprising an air inlet channel, a magnetic field generating mechanism and a laser beam generating mechanism, wherein the magnetic field generating mechanism and the laser beam generating mechanism are arranged on the air inlet channel;
the magnetic field generating mechanism is used for emitting laser beams to a target area set at an air inlet end of the air inlet channel in a flight environment and ionizing gas in the target area to form charged particles;
the magnetic field generating mechanism is used for forming a magnetic field for trapping the charged particles into the air inlet channel in the target area.
2. The laser preionization enhanced air suction device for the air suction electropushing technology is characterized in that the laser beam generating mechanism comprises at least one laser arranged on the circumferential direction of the air inlet channel, and the lasers are used for laser beams after being expanded according to a target divergence angle.
3. The laser preionization enhanced getter device for getter electrokinetic technique as claimed in claim 2, wherein the divergence angle of the laser beam emitted by each laser is set to θ, and the following requirements are satisfied:
wherein, Te，Th，mh，vhAnd U is electron temperature, gas temperature, atomic mass, gas collision rate, and aircraft, respectively.
4. The laser preionization enhanced air suction device for the air suction electropushing technology as claimed in claim 3, wherein a direction of each laser beam emitted by each laser is oriented in an incoming flow direction relative to the air inlet, and the direction of each laser beam is outwardly deviated to form an included angle of θ/2 with an axial direction of the air inlet.
5. The air suction and electric pushing technology laser preionization enhanced air suction device for the air suction and electric pushing technology as claimed in claim 2, wherein at least one laser in the circumferential direction of the air inlet channel is used for emitting a laser beam with energy of 14.5eV and a laser beam with energy of 13.6eV into a target area in the flight environment;
at least one of the lasers includes at least one laser for emitting a laser beam having an energy of 20 eV.
6. The laser preionization enhanced gas suction device for the gas suction electrokinetic technology as claimed in claim 5, wherein at least one of the lasers in the circumferential direction of the gas inlet channel includes at least one ultraviolet laser for simultaneously emitting laser beams with a wavelength of 85.72nm and a laser beam with a wavelength of 91.40nm or at least two ultraviolet lasers for respectively emitting laser beams with a wavelength of 85.72nm and a laser beam with a wavelength of 91.40 nm;
at least one of the lasers comprises at least one extreme ultraviolet laser for emitting a laser beam having a wavelength of 62.1 nanometers.
7. The laser preionization enhanced air suction device for the air suction electropushing technology as claimed in claim 6, wherein laser beam envelopes formed by laser beams emitted by adjacent lasers are partially overlapped, so that a capture area formed by each laser beam around the circumferential direction of the air inlet channel is larger than a laser beam ionization region envelope formed by an air inlet section of the air inlet channel in a flight environment.
8. The laser preionization enhanced air suction device for the air suction electropushing technology as claimed in claim 1, wherein the magnetic field generating mechanism comprises a plurality of permanent magnets uniformly arranged in the circumferential direction of the air inlet or electromagnetic coils surrounding the circumferential direction of the air inlet, and the magnetic field generating mechanism is configured to form magnetic lines of force of a nozzle configuration at the air inlet end of the air inlet.
9. A method of gettering a getter device enhanced by laser pre-ionization according to the gettering electrokinetic technique of any one of claims 1-8, comprising:
ionizing gas in a target region in a flight environment to form charged particles by emitting a laser beam into the target region;
and providing acting force for the charged particles through a magnetic field formed around the air inlet channel, and trapping the charged particles into the air inlet channel.
10. The method of claim 9, wherein the energy of the laser beam is not lower than the first ionization energy required for the ionization of the gas.
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