CN108869220B - A kind of propulsion device and propulsion method for Spatial kinematics - Google Patents
A kind of propulsion device and propulsion method for Spatial kinematics Download PDFInfo
- Publication number
- CN108869220B CN108869220B CN201810579122.9A CN201810579122A CN108869220B CN 108869220 B CN108869220 B CN 108869220B CN 201810579122 A CN201810579122 A CN 201810579122A CN 108869220 B CN108869220 B CN 108869220B
- Authority
- CN
- China
- Prior art keywords
- anode
- propulsion
- cathode
- fixed plate
- chemical
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H1/00—Using plasma to produce a reactive propulsive thrust
- F03H1/0087—Electro-dynamic thrusters, e.g. pulsed plasma thrusters
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Plasma Technology (AREA)
Abstract
The present invention relates to a kind of propulsion devices and propulsion method for Spatial kinematics, belong to spacemarching field, and this method is a kind of compound propulsion method that chemical propulsion and electric propulsion combine.The present invention provides a kind of propulsion device for Spatial kinematics, and chemical propulsion and electric propulsion process is combined to form new compound propulsion method；The chemical propulsion process, which refers to, to be ionized fuel gas working medium mixture and lights under high voltage pulse effect, induce chemical combustion reaction, releasing a large amount of chemical energy accelerates mixed gas expansion, since the blocking of preceding end thrust wall will provide forward thrust for device；The electric propulsion process refers to that the plasma mixture that ionization and combustion chemistry reaction generate accelerates backward under the Lorentz force effect that high current is generated with autonomous induction magnetic field interaction and sprays through jet pipe, provides forward thrust for whole device.
Description
Technical field
The present invention relates to a kind of propulsion devices and propulsion method for Spatial kinematics, belong to spacemarching neck
Domain, this method are a kind of compound propulsion method that chemical propulsion and electric propulsion combine.
Background technique
Spatial kinematics can carry a variety of payload, be shipped to not as a kind of orbit transfer vehicle
With rail effect in different spaces target.For the timeliness and multiple target ability to function for improving space maneuver, it is desirable that space maneuver
Platform has a wide range of quickly change rail and repeatedly becomes rail ability, this just proposes urgently high thrust, high specific impulse space propulsion
Demand.
According to the difference in energy source and conversion regime, current spatial promotes type to be broadly divided into chemical propulsion and non-chemical
It promotes.Wherein, the thrust of chemical propulsion system is shifted up to million Ns of magnitudes more suitable for spacecraft fast railway.But pure chemistry
The specific impulse of propulsion is not high, only several hundred seconds, and since specific impulse is lower, working medium consumption is bigger, applied to multiple Orbit Transformation or greatly
When the motor-driven task of range, chemical propulsion will usually consume a large amount of fuel, on the one hand greatly reduce the bearing capacity of payload, separately
On the one hand it is primary a wide range of it is motor-driven after, the fuel that aircraft carries generally also exhausts substantially, is difficult to carry out secondary or machine three times again
It is dynamic.It is most widely used with electric propulsion most study in non-chemical propulsion.Traditional electric propulsion system is as ion thruster and Hall thrust
Device thrust usually all very little, only in milli ox to hundred milli ox magnitudes.For fast railway transfer, deep space manned exploration this kind for
There is a task of rigors in task time, and low thrust electric propulsion system then shows very poor, and an inter-orbital transfer time generally needs
Hundred days or more are taken, this not only greatly reduces the real-time of satellite investment, and it counteracts and saves fuel bring economy, while
Requirements at the higher level are proposed to the problems such as observing and controlling during transfer, considerably increase human cost.And high-power electric propulsion system,
As magnetic plasma propeller, Helicon wave plasma thruster etc., although can be realized biggish thrust and higher specific impulse,
But power consumption is up to surprising megawatt magnitude.It is measured with current and coming years space solar power supply capacity, far not
The power demands of such high-power electric propulsion system are able to satisfy, it is following also to power by space nuclear, but space core at present
Energy power supply technique is also very immature.Therefore, the high-power short-term internal space of pure electric propulsion system is difficult to be applied.
Summary of the invention
The technical problems to be solved by the present invention are: overcome the deficiencies in the prior art, proposes a kind of flat for space maneuver
The propulsion device and propulsion method of platform.
The technical solution of the invention is as follows:
A kind of propulsion device for Spatial kinematics, it is characterised in that: the device includes power supply, fixed plate, thrust
Wall, anode, jet pipe, cathode and mixed gas input unit；
Power supply is used for supply electric current and pulse between cathode and anode；
Fixed plate is fixedly connected on the bottom end of anode；
Thrust wall is fixedly mounted in anode；
Jet pipe is fixedly connected on the top of anode；
Cathode is coaxially mounted in anode, and cavity is formed between cathode and anode；
Mixed gas input unit is used to input mixed gas to the cavity formed between cathode and anode.
Cathode is fixed in fixed plate after passing through thrust wall and fixed plate.
The anode is a cylinder, and the material of anode is conductive metal material, and the bottom end of anode has flange mounting surface
And step, the top of anode have flange mounting surface；The cathode is a solid cylinder, and the material of cathode is metallic conduction
Material.
Mixed gas input unit includes gaseous fuel bottle, oxidant bottle and premixer；Gaseous fuel bottle is for holding gas
Fluid fuel；Oxidant bottle is for holding oxidant；Premixer is for mixing gaseous fuel and oxidant；The one of premixer
End passes through piping connection with gaseous fuel bottle, has valve and barometer on connecting line；The other end and oxidant bottle of premixer
By piping connection, there are valve and barometer on connecting line.
The fixed plate is the plectane with flange mounting surface, the flange mounting surface of anode bottom end and the flange of fixed plate
Mounting surface is fixedly connected, and thrust wall is fixedly mounted between the step and fixed plate of anode bottom end；The fixed peace of the jet pipe
On the flange mounting surface on anode top.
A through-hole, air inlet of the through-hole as mixed gas are had on the side wall of the anode；The jet pipe
Material be conductive metal material；The material of the thrust wall is insulating materials；The material of the fixed plate is insulation material
Material.
A kind of the step of propulsion method of Spatial kinematics, this method includes:
(1) it vacuumizes, is in fixed plate, thrust wall, anode, jet pipe, cathode in vacuum environment；
(2) mixed gas is inputted to the cavity formed between cathode and anode using mixed gas input unit；
(3) power supply output pulse and electric current add between a cathode and an anode；
(4) when mixed gas is after jet pipe ejection, power termination is exported, a pulsed operation end cycle.
Next duty cycle repeats (1)~(4) step, after the completion of motor-driven task, work is promoted to stop.
The pulse amplitude V of the power supply output is determined by following formula:
Wherein, A, B, γ are the constant related with gaseous species and cathode material being determined by experiment, for example work as gas
Corresponding A, B, γ value is respectively 3.8,97.5 and 0.053 when for hydrogen, cathode material using nickel, when gas is air, cathode
Corresponding A, B, γ value is respectively 11.0,273.8 and 0.019 when material is using nickel, and P is pressure, and d is between cathode and anode
Distance.
The electric current I of the power supply output is determined by following formula:
Wherein, μ0For space permeability, π is pi, raFor anode radius, rcFor cathode radius, T is needed for thruster
Thrust.
Beneficial effect
(1) present invention provides a kind of propulsion device for Spatial kinematics, and combines chemical propulsion and electric propulsion
Journey forms new compound propulsion method；The chemical propulsion process, which refers to, makees fuel gas working medium mixture in high voltage pulse
It with lower ionization and lights, induces chemical combustion reaction, releasing a large amount of chemical energy accelerates mixed gas expansion, due to front end
The blocking of thrust wall will provide forward thrust for device；The electric propulsion process refer to ionization and combustion chemistry reaction generate etc.
Gas ions mixture accelerates under the Lorentz force effect that high current and autonomous induction magnetic field interaction generate backward and through tail
Jet pipe sprays, and provides forward thrust for whole device.
(2) vacuum tank is evacuated using vacuum pump by a kind of propulsion method for Spatial kinematics first, until in tank
Vacuum degree reaches requirement, closes extraction valve, stops vacuum pump；After pumping, by the fuel gas of fuel and oxidant composition
Working medium injects accelerating cavity after mixing by stoichiometric ratio injection premixer, and closes air inlet main valve；Then high-voltage pulsed source and big
Current source distinguishes output HIGH voltage pulse and high current adds between a cathode and an anode, and high voltage ionizes gas, and point
Fire mixed gas.The chemical energy of chemical combustion reaction release causes gas expansion to accelerate, due to the blocking of preceding end thrust wall, it will
Forward thrust is provided for whole device；Meanwhile high current channel generates circumferential induced magnetic field, high current and magnetic field interaction
Lorentz force backward is generated, plasma mixture accelerates backward under Lorentz force effect, provides forward for whole device
Thrust；After the ejection of rear end jet pipe, power termination output a, duty cycle terminates plasma mixture.This is compound
Propulsion method is pulse repetition operating mode, and the subsequent work period will repeat above-mentioned process.
(3) Lorentz force is generated by the high current and the induced magnetic field itself generated interaction in the present invention
, accelerate the plasma mixture generated by high pressure ionization and chemical combustion reaction to the back-end.
(4) a kind of propulsion device and propulsion method for Spatial kinematics disclosed by the invention, with existing propulsion skill
Art is compared has more technical advantage in space platform repeatedly a wide range of fast reserve task application.The invention and pure chemistry promote
Device is compared, and specific impulse has a distinct increment；Compared with pure electric propulsion device, power consumption can reduce.
(5) present invention applies not in space platform repeatedly a wide range of orbit maneuver task for existing Push Technology
Foot, provides a kind of propulsion device and propulsion method for Spatial kinematics, can either realize high thrust using chemical propulsion
Output, and the specific impulse of the injection raising chemical propulsion by electric energy, are effectively reduced fuel consumption, meet repeatedly a wide range of quickly change
Rail demand, and the chemical energy of chemical propulsion release can be efficiently used to reduce the power consumption of electric propulsion.Too with space
The development of positive energy power supply capacity, this method are expected to solve the propulsion problem of Spatial kinematics in a short time.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of propulsion device of the invention.
Specific embodiment
A kind of propulsion device for Spatial kinematics, the device include high-voltage pulsed source 1, current source 2, fixed plate 3,
Thrust wall 4, anode 6, jet pipe 7, cathode 8, air inlet 9, air inlet main valve 10, premixer 11, gaseous fuel bottle 12, oxidant bottle
13, intake valve 14 and 17, barometer 15 and 16, vacuum tank 18, vacuum pump 19 and extraction valve 20；
The anode 6 is a cylinder, and the material of anode 6 is conductive metal material, and the bottom end of anode 6 is installed with flange
The top of face and step, anode 6 has flange mounting surface；
The cathode 8 is a solid cylinder, and the material of cathode 8 is conductive metal material；
The gaseous fuel bottle 12 is for holding gaseous fuel；
The oxidant bottle 13 is for holding oxidant；
The premixer 11 is for mixing gaseous fuel and oxidant；
The fixed plate 3 is the plectane with flange mounting surface；
The flange mounting surface of 6 bottom end of anode is fixedly connected with the flange mounting surface of fixed plate 6, and thrust wall 4 is fixed
It is mounted between the step and fixed plate 3 of 6 bottom end of anode；
The cathode 8 is coaxially mounted in anode 6, and is fixed in fixed plate 3 after passing through thrust wall 4 and fixed plate 3；
Space between the anode 6 and cathode 8 forms accelerating cavity 5；
The jet pipe 7 is fixedly mounted on the flange mounting surface on 6 top of anode；
A through-hole is had on the side wall of the anode 6, the through-hole is as air inlet 9；
The output plus terminal of the high-voltage pulsed source 1 and current source 2 is connect with anode 6 simultaneously, and is grounded；
The output negative terminal of the high-voltage pulsed source 1 and current source 2 is connect with cathode 8 simultaneously；
Described 10 one end of air inlet main valve is connected to by pipeline with the air inlet 9 on 6 side wall of anode, air inlet main valve 10 it is another
One end is attached by pipeline with premixer 11；
One end of the premixer 11 and gaseous fuel bottle 12 pass through piping connection, have valve 14 gentle on connecting line
Pressure meter 15；
The other end and oxidant bottle 13 of the premixer 14 pass through piping connection, have valve 17 gentle on connecting line
Pressure meter 16；
The vacuum tank 18 and vacuum pump 19 is connected for providing vacuum working environment, the two with extraction valve 20；
The material of the jet pipe 7 is conductive metal material；
The material of the thrust wall 4 is insulating materials；
The material of the fixed plate 3 is insulating materials；
Fixed plate 3, thrust wall 4, anode 6, jet pipe 7 and cathode 8 are placed in vacuum tank 18, vacuum pump 19 and vacuum tank
18 are connected by extraction valve 20, for maintaining vacuum degree and practical vacuum environment in vacuum tank 18 close.
A kind of the step of propulsion method for Spatial kinematics, this method includes:
(1) gas main valve 10 is closed, extraction valve 20 is opened, makes vacuum pump 19 start to be evacuated vacuum tank 18, works as vacuum tank
After vacuum degree reaches requirement in 18, extraction valve 20 is closed, vacuum pump 19 stops working；
(2) gaseous fuel is placed in gaseous fuel bottle 12, oxidant is placed in oxidant bottle 13, then by gas
Fluid fuel and oxidant are injected into premixer 11 according to stoichiometric ratio, and opening air inlet main valve 10 makes the mixing in premixer 11
Gas enters in accelerating cavity 5, closes air inlet main valve 10；
(3) high-voltage pulsed source 1 exports high-voltage pulse and is added between cathode 8 and anode 6, and high-voltage pulse ionizes mixed gas
And bring it about combustion chemistry reaction and expand to the back-end and accelerate, while current source 2 export electric current be added in cathode 8 and anode 6 it
Between, further speed up ionization, combustion product to the back-end；
(4) when mixed gas is after the ejection of jet pipe 7, high-voltage pulsed source 1 and current source 2 terminate output, a pulse
Duty cycle terminates；
(5) next duty cycle repeats (1)~(4) step, after the completion of motor-driven task, work is promoted to stop.
Just in conjunction with attached drawing, the invention will be described further below.
The invention discloses a kind of propulsion devices and propulsion method for Spatial kinematics.The structure of the propulsion device
As shown in Figure 1,1 is high-voltage pulsed source, 2 be high current source, and 3 be fixed plate, and 4 be thrust wall, and 5 be accelerating cavity, and 6 be anode, and 7 are
Jet pipe, 8 be cathode, and 9 be air inlet, and 10 be air inlet main valve, and 11 be premixer, gaseous fuel bottle 12, oxidant bottle 13, air pressure
Meter 15 and 16, intake valve 14 and 17, vacuum tank 18, vacuum pump 19 and extraction valve 20.Wherein, anode 6 is cylindrical structure, cathode 8
It for cylindrical body, and is co-axially mounted, anode 6, cathode 8 and jet pipe 7 are conductive metal material, and thrust wall 4 and fixed plate 3 are insulation
The output plus terminal of material, high-voltage pulsed source 1 and current source 2 connects anode 6 and is grounded, and the negative terminal of high-voltage pulsed source 1 and current source 2 connects
Cathode 8.The propulsion method uses pulse repetition operating mode, and a pulsed operation period specific work process is as follows:
(1) gas main valve 10 is closed, opens extraction valve 20, vacuum pump 19 starts to be evacuated, when vacuum degree reaches in vacuum tank 18
To after requirement, extraction valve 20 is closed, vacuum pump 19 stops working.
(2) fuel gas working medium, which refers to, can occur gas composition that chemical combustion is reacted by fuel and oxidant are this kind of
Mixture, typical fuel such as hydrogen, methane etc., typical oxidizers such as air, oxygen etc..Gaseous fuel is placed in gaseous fuel
In bottle 12, oxidant is placed in oxidant bottle 13, is then injected into gaseous fuel and oxidant according to stoichiometric ratio
In premixer 11, opening air inlet main valve 10 enters the mixed gas in premixer 11 in accelerating cavity 5, closes air inlet main valve
10。
(3) after air inlet, high-voltage pulsed source 1 exports high-voltage pulse and is added between cathode 8 and anode 6, while current source 2
Output electric current is added between cathode 8 and anode 6.The output pulse width of the high-voltage pulsed source 1 is generally less than 100ns, defeated
Pulse amplitude V is determined by Paschen law out:
Wherein, A, B, γ are the constant related with the material of gaseous species and cathode 8 being determined by experiment, for example work as gas
Body be hydrogen, cathode 8 material when using nickel corresponding A, B, γ value be respectively 3.8,97.5 and 0.053, when gas be air,
Corresponding A, B, γ value is respectively 11.0,273.8 and 0.019 when the material of cathode 8 is using nickel, and P is accelerating cavity 5 after inflation
The pressure inside reached, d are the distance between cathode 8 and anode 6；
The maximum output current I of the current source 2 is determined by Maecker formula:
Wherein, μ0For space permeability, π is pi, raFor 6 radius of anode, rcFor 8 radius of cathode, T is thruster institute
Need thrust.
(4) energy that high-voltage pulsed source 1 injects first opens the chemical bond of a part of mixed gas molecule, is dissociated into list
A gas atom, then can some gas atom obtain or lose electronics and be ionized into charged particle, charged particle will be
It is moved under electric field action, simultaneously positive energy exchange is mutually collided with other particles, aggravates ionization process gradually, finally at yin-yang the two poles of the earth
Between form current channel.Under high-voltage pulse effect, the gas of intracavitary local pressure lower will ionize first, become
Ignition point, to induce chemical combustion reaction.It is logical that local current will be established between yin-yang the two poles of the earth after gas ionization igniting
Road.
(5) in traditional chemical reaction, first happens is that opening the chemical bond in reactant, need to absorb energy, so
It recombinates to form new chemical bond again afterwards, release energy, chemically reacting the gross energy released is the variation of above-mentioned two Process Energy
Difference.In the chemical combustion reaction using high pressure ionization igniting, this part energy needed for opening the chemical bond in reactant
Amount is provided by the high-voltage pulse of high-voltage pulsed source 1, and chemistry can directly occur for the gas atom that the lower dissociation of high pressure effect generates
Combustion reaction will release more energy compared with traditional chemical combustion reaction.Due to the change of chemical combustion reaction release
The kinetic energy after gas expansion accelerates can be converted primarily by learning, therefore using gas after the chemical combustion reaction of high pressure ionization igniting
Spouting velocity is higher, and the specific impulse of corresponding chemical propulsion is also higher.With the progress of combustion reaction, it will release a large amount of chemistry
Can, make when gases are heated, they expand to accelerate, since there is the blocking of thrust wall 4 in 5 front end of accelerating cavity, according to the law of conservation of momentum, gas is backward
End expansion will provide forward thrust for device.
(6) as entire cavity is filled in the aggravation of burning degree, plasma mixture, the impedance of two interpolar of yin-yang is substantially
It reduces and the value that tends towards stability, the electric current that current source 2 exports is up to maximum and tends towards stability.Incude in circumferential will generate of current line
Magnetic field, since cathode 8 flows through electric current maximum, generated Circumferential field is most strong, and electric current and induced magnetic field interaction generate Lip river
Lun Zili.Plasma mixture can accelerate to the back-end under Lorentz force effect, provide forward thrust for device, push away at this time
Power is also up to maximum.Since high-voltage pulsed source 1 and current source 2 are eventually converted into the dynamic of mixed gas by the energy exported
Can, and at the same time a large amount of chemical energy that the chemical combustion reaction carried out releases also translate into the kinetic energy of mixed gas, and it is pure
The kinetic energy of electric propulsion process mixed gas can only be transformed by electric energy, therefore compound propulsion process accelerated compared to pure electric propulsion
The consumption of electric energy will be effectively reduced in journey.
The above process (5) and (6) carry out simultaneously in accelerating cavity 5.
(7) mixed gas is after jet pipe 7 sprays completely, and high-voltage pulsed source 1 and current source 2 stop working, a pulse
Duty cycle terminates.One pulse cycle time was added by pumpdown time, inflationtime, gas ionization Accelerating Removal time
It arrives.Wherein, pumpdown time is mainly related with the pumping speed of vacuum pump；Generally in 10ms or so, gas ionization accelerates inflationtime
Efflux time is generally in 5ms or so.
(8) next duty cycle repeats (1)~(7) step, and after the completion of motor-driven task, propeller stops working.
Embodiment
(1) Theory comparison of the present invention and traditional chemical propulsion method
Chemical energy of the energy of chemical propulsion from chemical reaction release.Under equal quality working medium, the chemical energy of release
More, the attainable specific impulse of theoretically chemical propulsion institute is bigger.With hydrogen (H2) it is used as fuel, oxygen (O2) as oxidant be
, under traditional chemical propulsion mode, 1mol H2With 0.5mol O2Completely chemical combustion reaction occurs and generates 1mol water vapour
(H2O) energy discharged is about 245kJ, energy equation are as follows:
H2(g)+0.5O2(g)→H2O(g)-245kJ/mol.
And chemical combustion reaction directly occurs for H, O atom generate the chemical energy of 1mol water vapour release to be about 930KJ, energy
Equation are as follows:
2H(g)+O(g)→H2O(g)-930kJ/mol.
If using the propulsion method in the present invention, because occurring, chemical combustion is anti-using high pressure ionization sparking mode
Before answering, some H is understood2And O2H, O atom have been dissociated under action of high voltage.Assuming that H2And O2The rate of dissociation be respectively
10%, then the chemical energy discharged is about are as follows: 313.5kJ, the chemistry compared to the release of traditional chemical propulsion mode can increase 68.5kJ.Root
According to law of conservation of energy, the increased energy in this part will cause the promotion of gas injection speed, corresponding propeller specific impulse
It can increased.In addition, ionization combustion product can also be further speeded up under Lorentz force effect, specific impulse can be promoted further.
(2) Theory comparison of the present invention and pure electric propulsion method
In pure electric propulsion scheme, the energy of propeller derives from the consumption of electric energy.For same design objective, such as thrust
T=50N, specific impulse Isp=1000s, gravity acceleration g take 10m/s2, then corresponding working medium second consumptionFor 5 × 10-3kg/s。
According to law of conservation of energy, use pure electric propulsion scheme and assume efficiency for 100%, power consumption P
It is up to 250kW.
And the existing chemical propulsion process of compound propulsion method of the invention, and have electric propulsion process.In chemical propulsion process
In, a certain proportion of chemical energy will be released by the chemical combustion reaction of working medium, this portion of energy will provide certain
Specific impulse, it is assumed that the specific impulse value takes traditional chemical to promote typical specific impulse value 400s.Then the consumption of electric energy is only used for during electric propulsion
Specific impulse is promoted to 1000s from 400s.According to law of conservation of energy, power consumption will be reduced to 210kW, compare pure electric propulsion method
40kW electric energy will be saved.
Unspecified part of the present invention belongs to common sense well known to those skilled in the art.
Claims (9)
1. a kind of propulsion method for Spatial kinematics, it is characterised in that the step of this method includes:
(1) it vacuumizes, is in fixed plate (3), thrust wall (4), anode (6), jet pipe (7), cathode (8) in vacuum environment；
(2) it is mixed using mixed gas input unit to the cavity input fuel gas formed between cathode (8) and anode (6)
Object；
(3) power supply output pulse and electric current are added between cathode (8) and anode (6)；
(4) after combustible gas mixture is sprayed from jet pipe (7), power termination output, a pulsed operation end cycle；
Propulsion device used in this method includes power supply, fixed plate (3), thrust wall (4), anode (6), jet pipe (7), cathode
(8) and mixed gas input unit；
Power supply is used for supply electric current and pulse between cathode (8) and anode (6)；
Fixed plate (3) is fixedly connected on the bottom end of anode (6)；
Thrust wall (4) is fixedly mounted in anode (6)；
Jet pipe (7) is fixedly connected on the top of anode (6)；
Cathode (8) is coaxially mounted in anode (6), forms cavity between cathode (8) and anode (6)；
Mixed gas input unit is used to input combustible gas mixture to the cavity formed between cathode (8) and anode (6).
2. a kind of propulsion method for Spatial kinematics according to claim 1, it is characterised in that: next work
Period repeats (1)~(4) step, after the completion of motor-driven task, work is promoted to stop.
3. a kind of propulsion method for Spatial kinematics according to claim 1 or 2, it is characterised in that: described
The pulse amplitude V of power supply output is determined by following formula:
Wherein, A, B, γ are constant, and P is pressure, and d is the distance between cathode and anode.
4. a kind of propulsion method for Spatial kinematics according to claim 1 or 2, it is characterised in that: described
The electric current I of power supply output is determined by following formula:
Wherein, μ0For space permeability, π is pi, raFor anode radius, rcFor cathode radius, T is thrust needed for thruster.
5. a kind of propulsion method for Spatial kinematics according to claim 1 or 2, it is characterised in that: cathode (8)
It is fixed on fixed plate (3) after thrust wall (4) and fixed plate (3).
6. a kind of propulsion method for Spatial kinematics according to claim 1 or 2, it is characterised in that: described
Anode (6) is a cylinder, and the material of anode (6) is conductive metal material, and the bottom end of anode (6) has flange mounting surface and platform
The top of rank, anode (6) has flange mounting surface；The cathode (8) is a solid cylinder, and the material of cathode (8) is gold
Belong to conductive material.
7. a kind of propulsion method for Spatial kinematics according to claim 1 or 2, it is characterised in that: gaseous mixture
Body input unit includes gaseous fuel bottle, oxidant bottle and premixer；Gaseous fuel bottle is for holding gaseous fuel；Oxidant bottle
For holding oxidant；Premixer is for mixing gaseous fuel and oxidant；One end of premixer and gaseous fuel bottle
By piping connection, there are valve and barometer on connecting line；The other end and oxidant bottle of premixer are by piping connection, even
There are valve and barometer in adapter tube road.
8. a kind of propulsion method for Spatial kinematics according to claim 1 or 2, it is characterised in that: described
Fixed plate (3) is the plectane with flange mounting surface, and the flange mounting surface of anode (6) bottom end and the flange of fixed plate (3) are installed
Face is fixedly connected, and thrust wall (4) is fixedly mounted between the step and fixed plate (3) of anode (6) bottom end；The jet pipe
(7) it is fixedly mounted on the flange mounting surface on anode (6) top.
9. a kind of propulsion method for Spatial kinematics according to claim 1 or 2, it is characterised in that: described
A through-hole, air inlet of the through-hole as mixed gas are had on the side wall of anode (6)；The material of the jet pipe (7) is
Conductive metal material；The material of the thrust wall (4) is insulating materials；The material of the fixed plate (3) is insulating materials.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810579122.9A CN108869220B (en) | 2018-06-07 | 2018-06-07 | A kind of propulsion device and propulsion method for Spatial kinematics |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810579122.9A CN108869220B (en) | 2018-06-07 | 2018-06-07 | A kind of propulsion device and propulsion method for Spatial kinematics |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108869220A CN108869220A (en) | 2018-11-23 |
| CN108869220B true CN108869220B (en) | 2019-08-09 |
Family
ID=64337184
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810579122.9A Active CN108869220B (en) | 2018-06-07 | 2018-06-07 | A kind of propulsion device and propulsion method for Spatial kinematics |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108869220B (en) |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110012584B (en) * | 2019-03-22 | 2020-06-09 | 北京交通大学 | Pulse vacuum arc plasma thruster with segmented micropore insulation anode |
| CN110821770B (en) * | 2019-08-29 | 2021-07-09 | 西安空间无线电技术研究所 | Electric propulsion system based on satellite-borne application system microwave source |
| CN111005848A (en) * | 2019-10-31 | 2020-04-14 | 西安空间无线电技术研究所 | Working medium supply system and method for space electrochemical composite thruster |
| CN111017267B (en) * | 2019-12-23 | 2022-05-13 | 大连理工大学 | High-thrust near space thruster based on corona discharge and Hall effect |
| CN111622911A (en) * | 2020-05-20 | 2020-09-04 | 大连理工大学 | Helical wave opening system electrostatic ion thruster |
| CN111891404A (en) * | 2020-07-31 | 2020-11-06 | 上海卫星工程研究所 | Layout method and system for electrified dual-mode thruster of high-orbit maneuvering satellite platform |
| CN112065607A (en) * | 2020-09-18 | 2020-12-11 | 侯瀚宇 | Combustion chamber, engine, method and application |
Family Cites Families (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6216445B1 (en) * | 1999-05-19 | 2001-04-17 | Trw Inc. | Micro pulsed plasma thruster and method of operating same |
| CN101158321A (en) * | 2007-05-18 | 2008-04-09 | 清华大学 | Low-temperature plasma non-hot point fire steadying flame device |
| CN102374146B (en) * | 2010-08-09 | 2013-04-03 | 中国科学院微电子研究所 | Pulse laser plasma electric hybrid micro-propulsion device and method |
| CN102767496B (en) * | 2012-05-22 | 2014-12-03 | 北京卫星环境工程研究所 | Chemical-electromagnetic hybrid propeller with variable specific impulse |
| US9505503B2 (en) * | 2013-03-27 | 2016-11-29 | Lockheed Martin Corporation | Reactants sprayed into plasma flow for rocket propulsion |
| CN103953459B (en) * | 2014-04-21 | 2016-06-08 | 西北工业大学 | A kind of short distance detonates the device of high frequency detonation wave and control method thereof |
| CN103925116B (en) * | 2014-04-28 | 2016-03-02 | 中国航天空气动力技术研究院 | Sliding arc ignition mechanism |
| IL246250A (en) * | 2016-06-15 | 2017-06-29 | Technion Res & Dev Foundation | Inline screw feeding vacuum arc thruster |
| CN206487598U (en) * | 2016-12-15 | 2017-09-12 | 深圳市矛村电子科技有限公司 | Plasma engines |
| CN107091210B (en) * | 2017-05-18 | 2018-12-04 | 西安交通大学 | A kind of pulsed plasma thruster based on capillary discharging |
| CN107939625B (en) * | 2017-11-13 | 2019-04-05 | 中国人民解放军国防科技大学 | Reflection type laser-electromagnetic field coupling thruster |
-
2018
- 2018-06-07 CN CN201810579122.9A patent/CN108869220B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN108869220A (en) | 2018-11-23 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108869220B (en) | A kind of propulsion device and propulsion method for Spatial kinematics | |
| JP7041860B2 (en) | Thermoelectric power generator | |
| US11063282B2 (en) | Separation system | |
| US7509795B2 (en) | Systems and methods for plasma propulsion | |
| CN102767497B (en) | Fuel-free spacecraft propelling system based on spatial atomic oxygen and propelling method | |
| CN102374146B (en) | Pulse laser plasma electric hybrid micro-propulsion device and method | |
| CN102297105A (en) | Pulsed plasma thruster with ceramic nozzles arranged on sidewalls | |
| US9394889B2 (en) | Chemical-electromagnetic hybrid propeller with variable specific impulse | |
| CN104632567A (en) | Electric arc heating device capable of generating ultra-high-speed airflow | |
| CN106640568A (en) | Bipolar solid ablation type plasma accelerator | |
| CN102519704A (en) | Pulse wind tunnel thermal jet flow experiment gas source feed platform | |
| CN201884129U (en) | Nuclear engine | |
| CN110131120A (en) | Solid ablation type magnetic plasma thruster | |
| CN109356714A (en) | A kind of explosion power device mixed using hydrogen-oxygen | |
| GB897577A (en) | Improvements in or relating to apparatus for producing a jet consisting of a plasma of ions and electrons | |
| CN105244522A (en) | Aluminium-water reaction high-energy system apparatus | |
| CN208216967U (en) | It is suitable for the marine electric power propulsion device of speedboat | |
| CN206627467U (en) | One kind improves powder burning product conductive characteristic device | |
| CN204733451U (en) | A kind of insulation gun rack | |
| CN115324771A (en) | Little propeller based on brineelectrolysis suitable for microsatellite | |
| RU2537663C1 (en) | Jet hovercraft | |
| CN114109651B (en) | Solid fuel rocket combined ramjet engine | |
| CN205177937U (en) | Aluminium water reaction high energy system device | |
| RU2538230C1 (en) | Vessel running on hydrogen fuel that features small waterline area | |
| US20030048054A1 (en) | Artificial solar wind generator |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |