CN1904358A - Plasma collision offect propeller - Google Patents
Plasma collision offect propeller Download PDFInfo
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- CN1904358A CN1904358A CNA2005100855246A CN200510085524A CN1904358A CN 1904358 A CN1904358 A CN 1904358A CN A2005100855246 A CNA2005100855246 A CN A2005100855246A CN 200510085524 A CN200510085524 A CN 200510085524A CN 1904358 A CN1904358 A CN 1904358A
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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
- F03H99/00—Subject matter not provided for in other groups of this subclass
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Abstract
A plasma knock-on effect thruster is a propulsion motor without consuming propelling medium. Because of not requiring the consumption of too much fuel, the thruster can make the spacecraft have more spaces to load the payload suitable for the attitude control of the spacecraft or a long-distance, long-time space navigation. The principle of the invention is that: by the action of the induced electric field the plasma is made to accelerate and knock on the member fixed with the spacecraft together, so as to change the momentum of the spacecraft. The plasma as the propelling medium can be used cyclical and the needed energy is only the electric energy.
Description
Technical field:
This invention is a kind of propelling motor that does not need to consume propulsive medium, and its propulsive medium---plasma is recycled, and required energy has only electric energy.Owing to need not consume a large amount of fuel, it can make spacecraft can have more space to load useful load, is applicable to the attitude control of spacecraft or long distance, space travel for a long time.
Background technique:
The most familiar human universe motor should rocket motor, but the shortcoming of this motor is significantly, and the too big thrust of the volume and weight that chemical fuel occupies is then too little, and efficient is limited.So the scientists of various countries has just been found out various more advanced motors: atomic propulsion nuclear engine, interspace pressed engine, antimatter motor, ion engine, photon engine, even expected utilizing the optical pressure of fixed star and the stellar wind light sail of in universe, kicking up.
The most feasible rocket propulsion is divided into 3 types basically at present: chemical rocket, nuclear rocket and electrical rocket.
Chemical rocket carries liquid or solid-state chemical fuel and oxygenant, perhaps contains combustion-supporting oxygen in the chemical fuel, and these fuel and oxygenant are referred to as propellant agent.The fuel of chemical rocket burns in the bowl-shape firing chamber of rocket afterbody, and the shaped design of exhaust nozzle can allow employed propellant agent reach maximum propulsive efficiency.
The working principle of nuclear power rocket is such: the heat that utilizes nuclear reaction to produce heats liquid hydrogen, makes it become hot gaseous gas (temperature surpasses its boiling point).These gases are gone out from the nozzle ejection of rocket afterbody, thereby promote the flight of rocket.
Electric engine uses battery, solar energy or other energy to quicken and launches charged particle, thereby obtains thrust.Electric engine has very high specific impulse, but the thrust that they produce is limited, can only be in a vacuum with the less object of speed promotion more slowly.But, because their thrust is little, the efficient height, so they only need carry fuel seldom.Enough their the use several years of the fuel that some electrical rocket carries are well suited for astrovehicle and use in-flight at deep space.With man-made satellite or other aircraft of electrical rocket as power, must enter space with more powerful chemical rocket emission earlier, perhaps launch from spaceship.
More than the rocket motor of these kinds a common characteristic is all arranged, that is exactly a consume fuel, must rely on to aircraft exterior jet propulsion medium to provide flight or the required power of attitude control for aircraft.
Summary of the invention:
The principle of plasma collision offect propeller is exactly to make plasma quicken under the effect of induced electric field and strike on the parts that are fixed together with astrovehicle, thereby changes the momentum of astrovehicle, enables to change in the space attitude or carries out space travel.Plasma collision offect propeller can produce the momentum on the assigned direction, the just electric energy that self consumed, the plasma that produces knock-on effect reverts to neutral gas and also can reclaim after bump finishes, and then it is carried out ionization and acceleration, clashes into next time.That is to say as long as provide electric energy, just can produce the needed propelling force of spacecraft flight to plasma collision offect propeller.And rocket motor and high-speed gas injection propulsion device consume is chemical fuel and gas, just can not continue flight in case fuel or gas exhaust astrovehicle.
The process that plasma collision offect propeller produces kinetic energy can be divided into following 4 steps:
1. generation plasma
Natural material has four kinds of forms usually, promptly solid-state, liquid, gaseous state and plasma state.Make material carry out the transition to the energy minimum that plasma state consumes, so using gases simultaneously in order to improve the kinetic energy that plasma strike produces, needs to consider to use the bigger gas of molecular mass as the hyle that produces plasma here from gaseous state.The principle of gas being carried out ionization is very simple, near the very big point electrode of radius of curvature, the low voltage of importing is upgraded to dc high voltage by impulse circuit, because local electric field strength surpasses the ionisation of gas field intensity, make gas generation ionization, just coronal discharge.Make gas generation ionization by coronal discharge, those gas molecules that lose electronics become positive ion, quicken thereby can enter in the induced electric field accelerating cavity.
2. induced electric field quickens gaseous ion
Gas after the ionization will enter the induced electric field zone and quicken, and this principle to the same electric field accelerator of inducting of principle that ion quickens is the same substantially.Its principle is: lay a toroidal vacuum chamber in the gap at the two poles of the earth of a U-shaped electromagnet, electromagnet comes excitation with powerful transient current, the magnetic induction intensity of two interpolars is changed fast, thereby go out very strong eddy electric field at the doughnut internal induction, gaseous ion is injected doughnut, they are accelerated under the effect of eddy electric field, are subjected to the effect of Lorentz force simultaneously in magnetic field, move along circular track.The magnetic field that changes can inspire a kind of electric field around it, be commonly referred to eddy electric field or induced electric field, and its line of electric force is some closed curves, belongs to non-conservative, and is the same with electrostatic field, and it also can be to being in charge generation active force wherein:
If L is a radius is the circle of r, then:
For the carried charge that is in the induced electric field is the electric charge of q, and the electric field action power that it is subjected to is:
F=qE
Revolve
E
Revolve: induced electric field
B: mM disodium hydrogen phosphate
S: perpendicular to the area in the cross section of the magnetic line of force
L: perpendicular to the girth in the cross section of the magnetic line of force
Another basic problem of induced electric field accelerator is ion to be maintained on the constant circular track quicken the requirement that this is certain to being radially distributed with of magnetic field.If the magnetic field at ion trajectory place is B
R, it is Lorentz force to suffered centripetal force that ion is done the circular track motion, therefore just has
mv＝ReB
R
Following formula shows, as long as the ion momentum increases pro rata with magnetic induction intensity, just can keep ion and move on certain track.Realize this condition, will analyze the accelerating process of ion.
Induced electric field is:
According to newton's second law of motion:
Promptly have:
When if accelerating process begins, =0, the speed v=0 of ion then can get the following formula integration:
B is the average magnetic induction intensity in the ion motion track in the formula.Then have:
Here it is keeps the condition that ion moves on constant circular track.This condition shows that the magnetic induction intensity value on the track equals a half of the mean value of track intrinsic inductance, and ion just can be accelerated on stable circular track.
3. gaseous ion clashes into target plate
The ion that process is quickened is with near the target plate the high-speed impact circular orbit.Because target plate is fixed on angle of rake inside, thereby ion is because the momentum that quickens to be produced can be delivered to propulsion device by bump, momentum on the identical direction of moving direction when making propulsion device produce with ionic bombardment, this also is the link that plasma collision offect propeller can finally produce momentum:
m
iv＝M
pV
m
iBe respectively the quality of ion and its speed that before bump, has, M with v
pThe speed that is respectively angle of rake quality and produces owing to the bump of ion with V.
A key that realizes ionic bombardment is to reduce any reflection of ion behind bump, this just requires the target plate surface can not be plane completely, must be a kind ofly to have intensive and the surface of the pit of certain depth is arranged, can guarantee that like this ion comes back reflective to exhaust up to kinetic energy in pit.
How a key that realizes ionic bombardment also is the ion of high-speed motion is extracted from the circumference acceleration orbit, it can be moved towards target plate, this can apply the magnetic field perpendicular to ion acceleration orbit face by the front end at target plate, and the movement locus that makes the Lorentz force of its generation change ion is realized.
4. gas is recycling
Make the accelerator can continuous firing, gas can be circulated, just to the gaseous ion that clash into target plate be neutralized, make it get back to normal gaseous state and send back to gas ionization device place, carry out the process of ionization next time, acceleration and bump.
At first be to neutralize to gaseous ion.What realize knock-on effect is positive ion, as long as make target plate electronegative, just can make positive ion obtain the electronics that it loses when ionization, gets back to normal gaseous state.
Gas after will neutralizing is exactly then sent ionizer back to.This can be by installing fan near target plate, the air-flow that produces during fan work can send back to ionizer with gas.Certainly, gas must be the circuit system of a sealing through the whole passage of ionization, acceleration, bump and recovery.
For angle of rake entire work process is effectively controlled, must design a special propeller control device, it can be installed on the propulsion device, also can be installed in other positions of spacecraft.As an angle of rake very important constituent element, the design of angle of rake control gear must be satisfied following requirement:
1. provide the mutation current signal for angle of rake U type electromagnet
The magnetic field that changes produces induced electric field.The variance ratio in magnetic field is high more, and the induced electric field of generation is just big more.The exciting current of U type electromagnet must be a very short pulsed current signal of a rise time.The rise time of pulse, the amplitude peak of pulse was dozens or even hundreds of ampere usually in the microsecond level.In order to obtain bigger gaseous ion speed, can be to the pulsed current signal that U type electromagnet applies several times continuously even tens times such, but each impulsive current must apply before beginning to fall from peak point at impulsive current last time, can guarantee that like this gaseous ion can no longer not move along acceleration orbit because of the existence that does not have magnetic field in accelerator.
2. provide the stable DC signal for inclined to one side rail magnetic field generator
Gaseous ion is accelerated to a very high speed in induced electric field after, just gaseous ion need be drawn acceleration orbit, make it along moving towards the direction of target plate, the inclined to one side rail magnetic field generator of installing in the tangent direction of induced electric field acceleration orbit can play such effect.This is to utilize the Lorentz force principle, when just charged particle moves in the magnetic field perpendicular to its moving direction, can be subjected to one with its moving direction and all vertical power of magnetic direction.The rail magnetic field generator is only just started working when gaseous ion has had a proper speed partially, when just the mutation current signal of U type electromagnet has just finished, apply direct current signal just for inclined to one side rail magnetic field generator, and before next accelerating process began, this direct current signal must break.
3. provide high-voltage dc signal for the gas ionization device
Near the very big point electrode of radius of curvature,, make gas generation ionization and excitation, thereby coronal discharge occurs because local electric field strength surpasses the ionisation of gas field intensity.The positive voltage of these one several thousand of coronal discharge needs even volts up to ten thousand.The ionisation of gas process must be carried out before the induced electric field generation in accelerator.
4. provide negative voltage for target plate
Can revert to later neutral gas on the target plate for the gas positive ion that makes high-speed motion strikes, target plate must be electronegative, can catch the electronics on the target plate to guarantee the gas positive ion when colliding with target plate, thereby revert to electroneutral gas.
5. provide stable dc power supply for gas circulation channel
The employed gas of propulsion device must use by circuit, except making gas ionization and recovering the electroneutral cyclic process, gas can be flowed by circuit in angle of rake ionization, acceleration, bump and recovery approach, this gas flow is to rely on the fan of Real Time Drive in the gas circulation channel to realize, it needs a galvanic current source.
The employed energy of plasma collision offect propeller is electric energy, advancing material is the gas of callable big molecular mass, as long as spacecraft can provide enough electric energy to propulsion device, propulsion device just can proper functioning, provides space flight or the required kinetic energy of attitude control to aircraft.Certainly, principle was the same when the plasma collision offect propeller was controlled power as the thrust power of spacecraft with attitude, but both have dimensionally than big-difference.When coming this propulsion device of simple computation to be installed on the spacecraft once below by several typical parameters the momentum that can provide for spacecraft:
The quality of getting gas is m=0.5kg, speed v=4000m/s that it can access in the induction field accelerator, the mass M=5000kg of spacecraft, initial velocity are 0, once clashing into the required time is 10s, and the speed that the n time knockout process aircraft obtains is V
n, according to principle of momentum conservation:
Knockout process: mv=MV for the first time
1
Knockout process for the second time: m (v+V
1)-mV
2=M (V
2-V
1)
Knockout process for the third time: m (v+V
2)-mV
3=M (V
3-V
2)
·
·
·
·
·
·
The n time knockout process: m (v+V
N-1)-mV
n=M (V
n-V
N-1)
With top various about respectively addition obtain: mV
1-mV
n+ nmv=MV
n
Get n=10
2The time, V
n=40m/s, needing the time is 16.7 minutes.
N=10
6The time, V
n=4 * 10
5M/s, needing the time is 116 days.
Plasma collision offect propeller wants to make aircraft to obtain bigger speed to the accelerating process of spacecraft and rapid unlike chemical rocket engine as can be seen, and the required time is longer relatively.In order to improve angle of rake performance, can realize by the intensity that increases gaseous mass, increasing induced electric field, just can use the bigger gas of molecular mass, and in the circulation canal of gas, it is compressed, can obtain bigger density like this, can improve simultaneously the mutation current waveform of U type electromagnet, make it have bigger peak value and shorter rise time.
Description of drawings:
Fig. 1 is the plan view of plasma collision offect propeller in the accompanying drawing.
Fig. 2 is the front view of plasma collision offect propeller.
Fig. 3 is that plasma collision offect propeller is at the sectional view of overlooking on the direction.
1. ionic bombardments and recovering device in the accompanying drawing, 2. inclined to one side rail magnetic field generator, 3.U shape electromagnet, 4. gas circulation channel, 5. gas ionization device, 6. induced electric field accelerator, 7. the gas circulation flow direction, 8. gaseous ion acceleration track, 9. gaseous ion bump track.
Embodiment:
Plasma collision offect propeller generally includes ionic bombardment and recovering device, inclined to one side rail magnetic field generator, U-shaped electromagnet, gas circulation channel, gas ionization device, induced electric field accelerator and control gear as a complete propulsion system.
Can very clearly see angle of rake working procedure from accompanying drawing: gas is through entering the acceleration orbit of induced electric field accelerator (6) after the ionization, after treating that the gas positive ion reaches certain speed, the magnetic field perpendicular to gaseous ion acceleration track (8) plane that utilizes inclined to one side rail magnetic field generator (2) to produce changes the movement locus of ion, make it towards the target plate motion that has negative electricity, the ionic bombardment of high-speed motion is to target plate, make the momentum on the propulsion device generation direction identical with the ion motion direction, while ion trap electronics, become electroneutral gas, gas circulation channel (4) can make gas flow to along gas circulation and reenter gas ionization device (5), enters knockout process next time.
U-shaped electromagnet (3) is as the parts of propulsion device upper volume maximum, and its weight also accounts for the significant proportion of propulsion device gross weight.In order to reduce the weight of U-shaped electromagnet (3), can use the conductive material of some lightweights such as carbon fiber to be used as the magnetic core of electromagnet.
Point electrode that radius of curvature is very big of gas ionization device (5) needs because local electric field strength surpasses the ionisation of gas field intensity, makes gas generation ionization in its vicinity, the positive voltage of these one several thousand of coronal discharge needs even volts up to ten thousand.During gas ionization because the abrupt release of electronics in the gas molecule, can produce the electromagnetic radiation phenomenon of transient state, its frequency spectrum can be from tens MHz to tens GHz, this electromagnetic radiation meeting constitutes electromagnetic interference to carry-on other electronic equipments, so the shell of gas ionization device (3) must pass through good shielding, and also will with aircraft structurally well the overlap joint.
Induced electric field accelerator (6) can accelerate to gaseous ion very high speed, because aircraft is in the weightlessness of space environment, so do not exist gaseous ion to be subjected to the influence of the earth or other celestial body gravitation and the phenomenon of colliding mutually with induced electric field accelerator (6) acceleration channel.Equally, be in the gaseous ion in the continuous accelerating process at a high speed, it can equivalence be a ring current that constantly changes that its circular gaseous ion quickens track (8), can produce the electromagnetic interference of the non-constant width of frequency spectrum, so the shell of induced electric field accelerator (6) acceleration channel also will carry out shielding processing, and will with aircraft structurally well the overlap joint.
Partially rail magnetic field generator (2) can be drawn the gaseous ion of high-speed motion by the Lorentz effect from the acceleration channel of induced electric field accelerator (6), makes its tangent direction of quickening track (8) along gaseous ion move and clash into target plate.The structure of rail magnetic field generator (2) is exactly the electromagnet of a U type partially, its the two poles of the earth are stuck in the acceleration channel of gaseous ion middle, like this when electromagnet is logical galvanic, between the two poles of the earth of electromagnet, just formed a magnetic field of quickening track (8) plane perpendicular to gaseous ion, the gaseous ion of high-speed motion will be subjected to the effect of two Lorentz forces by this magnetic field the time, one is induced electric field accelerator (6), one is exactly inclined to one side rail magnetic field generator (2), when these two power equate, gaseous ion will clash into the motion of track (9) direction along gaseous ion, hits target plate.
Ionic bombardment and recovering device (1) mainly are exactly an electronegative metal target plate that is covered with small wedge-shaped structure, wedge-shaped structure is can constantly clash into back and forth when making gaseous ion on bumping against these structures, thereby the kinetic energy of spent gas ion reduces gaseous ion comes back reflective in ionic bombardment and recovering device (1) effect as much as possible.Metallic target strip negative electricity is exactly in order to make the gaseous ion can trapped electrons and become electroneutral gas so that recycle.Ionic bombardment and recovering device (1) also will take shielding measure to suppress to change the electromagnetic interference that produces suddenly owing to the speed of gaseous ion.
Gas circulation channel (4) is exactly will pump to gas ionization device (5) to the electroneutral gas through collision process to locate, and carries out knockout process next time.The fan of a Real Time Drive is installed at the middle part of gas circulation channel (4), and it can make gas flow to (7) along gas circulation and enter gas ionization device (5).
The control gear of plasma collision offect propeller is responsible for angle of rake U type electromagnet the mutation current signal is provided, for inclined to one side rail magnetic field generator provides the stable DC signal, for the gas ionization device provides high-voltage dc signal, for target plate provides negative voltage and provides stable dc power supply for gas-recycling plant.To knockout process each time, target plate in fan in the gas circulation channel (4), gas ionization device (5) and ionic bombardment and the recovering device (1) all is a uninterruptable power supply (UPS), coil to U-shaped electromagnet (3) will apply continual transient pulse electric current, after accelerating to a certain degree Deng gaseous ion, connect the power supply of inclined to one side rail magnetic field generator (2), gaseous ion is drawn gaseous ion quicken track (8), enter into ionic bombardment and recovering device (1).
Claims (9)
1. plasma collision offect propeller is a kind of propelling motor that does not need to consume propulsive medium, and its propulsive medium---plasma is recycled, and required energy has only electric energy.Owing to need not consume a large amount of fuel, it can make spacecraft can have more space to load useful load, is applicable to the attitude control of spacecraft or long distance, space travel for a long time.The principle of plasma collision offect propeller is exactly to make plasma quicken under the effect of induced electric field and strike on the parts that are fixed together with astrovehicle, thereby changes the momentum of astrovehicle, enables to change in the space attitude or carries out space travel.Plasma collision offect propeller can produce the momentum on the assigned direction, the just electric energy that self consumed, and plasma reverts to electroneutral gas after bump finishes, and can reclaim as bump, circulation and so forth next time.
2. plasma collision offect propeller according to claim 1, it is characterized in that: the working procedure that plasma collision offect propeller produces kinetic energy comprises that using gases ionizer (5) carries out ionization to the gas in the propulsion device, makes it to become the plasma of air inclusion positive ion and free electron; Use the gaseous ion in induced electric field accelerator (6) the article on plasma body to quicken; Use the Magnetic field distribution on the electromagnet change gaseous ion acceleration track (8), gaseous ion is drawn the acceleration track of induced electric field accelerator (6); Draw the gaseous ion and the bump of the metal target plate in ionic bombardment and the recovering device (1) of the high-speed motion of induced electric field accelerator (6), the kinetic energy of gaseous ion is delivered to plasma collision offect propeller, propulsion device obtains kinetic energy, metallic target strip negative electricity, gaseous ion is electron gain when bump, becomes electroneutral gas molecule again; Electroneutral gas after fan in the gas circulation channel (4) will clash into is sent gas ionization device (5) back to, carries out next knockout process.
3. plasma collision offect propeller according to claim 1, it is characterized in that: plasma collision offect propeller generally includes ionic bombardment and recovering device (1), inclined to one side rail magnetic field generator (2), U-shaped electromagnet (3), gas circulation channel (4), gas ionization device (5), induced electric field accelerator (6) and control gear as a complete propulsion system.
4. plasma collision offect propeller according to claim 1, it is characterized in that: very big point electrode of radius of curvature of gas ionization device (5) needs, in its vicinity because local electric field strength surpasses the ionisation of gas field intensity, make gas generation ionization, the positive voltage of these one several thousand of coronal discharge needs even volts up to ten thousand.
5. plasma collision offect propeller according to claim 1 is characterized in that: the conductive material that produces some lightweights such as U-shaped electromagnet use carbon fiber of induced electric field is used as the magnetic core of electromagnet.
6. plasma collision offect propeller according to claim 1, it is characterized in that: the structure of rail magnetic field generator (2) is exactly the electromagnet of a U type partially, its the two poles of the earth are stuck in the acceleration channel of gaseous ion middle, like this when electromagnet is logical galvanic, between the two poles of the earth of electromagnet, just formed a magnetic field of quickening track (8) plane perpendicular to gaseous ion, the gaseous ion of high-speed motion will be subjected to the effect of two Lorentz forces by this magnetic field the time, one is induced electric field accelerator (6), one is exactly inclined to one side rail magnetic field generator (2), when these two power equate, gaseous ion will clash into the motion of track (9) direction along gaseous ion, hits target plate.
7. plasma collision offect propeller according to claim 1, it is characterized in that: ionic bombardment and recovering device (1) mainly are exactly an electronegative metal target plate that is covered with small wedge-shaped structure, wedge-shaped structure is can constantly clash into back and forth when making gaseous ion on bumping against these structures, thereby the kinetic energy of spent gas ion reduces gaseous ion comes back reflective in ionic bombardment and recovering device (1) effect as much as possible.Metallic target strip negative electricity is exactly in order to make the gaseous ion can trapped electrons and become electroneutral gas so that recycle.Ionic bombardment and recovering device (1) also will take shielding measure to suppress to change the electromagnetic interference that produces suddenly owing to the speed of gaseous ion.
8. plasma collision offect propeller according to claim 1 is characterized in that: gas circulation channel (4) is exactly will pump to gas ionization device (5) to the electroneutral gas through collision process to locate, and carries out knockout process next time.The fan of a Real Time Drive is installed at the middle part of gas circulation channel (4), and it can make gas flow to (7) along gas circulation and enter gas ionization device (5).
9. plasma collision offect propeller according to claim 1, it is characterized in that: the control gear of plasma collision offect propeller is responsible for angle of rake U type electromagnet the mutation current signal is provided, for inclined to one side rail magnetic field generator provides the stable DC signal, for the gas ionization device provides high-voltage dc signal, for target plate provides negative voltage and provides stable dc power supply for gas-recycling plant.To knockout process each time, target plate in fan in the gas circulation channel (4), gas ionization device (5) and ionic bombardment and the recovering device (1) all is a uninterruptable power supply (UPS), coil to U-shaped electromagnet (3) will apply continual transient pulse electric current, after accelerating to a certain degree Deng gaseous ion, connect the power supply of inclined to one side rail magnetic field generator (2), gaseous ion is drawn gaseous ion quicken track (8), enter into ionic bombardment and recovering device (1).
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|---|---|---|---|
| CNA2005100855246A CN1904358A (en) | 2005-07-26 | 2005-07-26 | Plasma collision offect propeller |
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|---|---|---|---|
| CNA2005100855246A CN1904358A (en) | 2005-07-26 | 2005-07-26 | Plasma collision offect propeller |
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| CN1904358A true CN1904358A (en) | 2007-01-31 |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102966463A (en) * | 2012-11-29 | 2013-03-13 | 北京卫星环境工程研究所 | Magnetic heat shielding method for large-thrust orbit maneuver motor venture of satellite |
| CN104712457A (en) * | 2013-12-11 | 2015-06-17 | 黄乐歌 | Hypersonic aircraft engine with low fuel consumption |
| CN104875869A (en) * | 2015-04-28 | 2015-09-02 | 魏明刚 | Recoiling-free magnetic propelling device |
| CN105799955A (en) * | 2016-05-18 | 2016-07-27 | 张金良 | Pushing mechanism applied in vacuum state |
| CN106065852A (en) * | 2015-06-09 | 2016-11-02 | 熵零股份有限公司 | A kind of electromotor |
| CN109707583A (en) * | 2018-04-23 | 2019-05-03 | 李超 | Pulsed momentum cycle engine |
| CN112437837A (en) * | 2018-05-03 | 2021-03-02 | P·奈瑟 | Filtration apparatus and method |
| CN112566350A (en) * | 2020-11-10 | 2021-03-26 | 西安交通大学 | Plasma energy storage system and energy storage method |
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2005
- 2005-07-26 CN CNA2005100855246A patent/CN1904358A/en active Pending
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102966463A (en) * | 2012-11-29 | 2013-03-13 | 北京卫星环境工程研究所 | Magnetic heat shielding method for large-thrust orbit maneuver motor venture of satellite |
| CN104712457A (en) * | 2013-12-11 | 2015-06-17 | 黄乐歌 | Hypersonic aircraft engine with low fuel consumption |
| CN104875869A (en) * | 2015-04-28 | 2015-09-02 | 魏明刚 | Recoiling-free magnetic propelling device |
| CN106065852A (en) * | 2015-06-09 | 2016-11-02 | 熵零股份有限公司 | A kind of electromotor |
| CN105799955A (en) * | 2016-05-18 | 2016-07-27 | 张金良 | Pushing mechanism applied in vacuum state |
| CN105799955B (en) * | 2016-05-18 | 2018-01-05 | 张金良 | With propulsive mechanism under vacuum conditions |
| CN109707583A (en) * | 2018-04-23 | 2019-05-03 | 李超 | Pulsed momentum cycle engine |
| WO2019205651A1 (en) * | 2018-04-23 | 2019-10-31 | Li Chao | Impulse cycle engine |
| CN112437837A (en) * | 2018-05-03 | 2021-03-02 | P·奈瑟 | Filtration apparatus and method |
| CN112566350A (en) * | 2020-11-10 | 2021-03-26 | 西安交通大学 | Plasma energy storage system and energy storage method |
| CN112566350B (en) * | 2020-11-10 | 2022-02-01 | 西安交通大学 | Plasma energy storage system and energy storage method |
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