CN110439771A - A kind of air-breathing pulse plasma thruster - Google Patents
A kind of air-breathing pulse plasma thruster Download PDFInfo
- Publication number
- CN110439771A CN110439771A CN201910740846.1A CN201910740846A CN110439771A CN 110439771 A CN110439771 A CN 110439771A CN 201910740846 A CN201910740846 A CN 201910740846A CN 110439771 A CN110439771 A CN 110439771A
- Authority
- CN
- China
- Prior art keywords
- air
- anode
- cathode
- pulse plasma
- gas
- 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.)
- Pending
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
Abstract
The present invention relates to a kind of air-breathing pulse plasma thrusters, including gas collector, flow regulator, inlet channel, storage tank, air inlet jet pipe, anode, cathode, electric discharge chamber enclosure, spark plug, power-supply system, storage capacitor.High-speed gas enters gas collector, enters the disturbance that storage tank reduces high-speed gas by flow control valve, is adjusted before gas enters discharge channel to air-flow；Power-supply system charges to capacitor, make to hold high pressure between cathode and anode, Incoming gas enters discharge channel by air inlet jet pipe, generating charged particle by plug ignition makes that electric discharge is connected between electrode, under the electric field collective effect that plasma is formed between the magnetic field that loop current is formed and electrode, it generates electromagnetism and accelerates and spray electric discharge chamber enclosure, generate thrust.
Description
Technical field
The invention belongs to spacecraft space Push Technology fields, are related to a kind of air-breathing pulse plasma thruster, tool
It says to body, refers to a kind of for space rarefied air to be sucked propulsion device and as the pulse plasma thrust body of propellant
Device.
Background technique
One of important subsystem as Space Vehicle System, propulsion system are the important guarantors of the in-orbit normal work of spacecraft
Barrier.Electric propulsion is a kind of advanced space propulsion system, and compared with traditional chemical propulsion, electric propulsion ratio is leapt high, and is pushed away in carrying
Into agent it is identical in quality under conditions of, bigger acceleration can be generated.Propellant is ionized and is produced using solar powered by electric propulsion
The plasma of raw high speed ejection.Pulsed plasma thruster is the earliest electric thruster for carrying out space application, before 1962
Pulsed plasma thruster is used to execute the drag compensation task of -14 satellite of universe by the Soviet Union for the first time.
Pulsed plasma thruster has under lower power levels high specific impulse, structure simple, high reliablity, pulsed discharge just
It is with the obvious advantage in the tasks such as spacecraft Attitude and track accurately controls, space precise operates in the accurate control the features such as,
Receive lasting concern.
When pulsed plasma thruster works, DC power supply charges to storage capacitor, makes to hold kilovolt height between electrode
Pressure, plug ignition generate plasma, so that electrode conduction is discharged, propellant is ionized, and are formed " current sheet ".Current sheet and electricity
The closed circuit electric current J that pole, circuit are formed generates induced magnetic field B in discharge channel, and plasma is formed in electric current and magnetic field
Lorentz force J × B effect under accelerate and spray thruster, generate the thrust of recoil.
Although the propellant that electric propulsion needs to carry is less, and the quality of propellant still occupies compared with chemical propulsion
The quality of spacecraft payload, especially on away from ground 200km and low orbit below, spacecraft is larger by atmospheric drag,
It needs to carry more propellants, therefore improves the cost of transmitting；In addition, limited propellant also limits the longevity of spacecraft
Life.
Summary of the invention
It is an object of the invention to: overcome the deficiencies in the prior art proposes a kind of using space rarefied air as propulsion
The pulsed plasma thruster of agent, the angle utilized from space resources, by collecting low rail atmosphere as propellant, drop
Low propulsion system throw-weight, and by Flux Valve Control air inflow, to meet requirement of the space tasks to change propulsive.
The technical solution of the invention is as follows:
A kind of air-breathing pulse plasma thruster, including gas collector, flow regulator, inlet channel,
Storage tank, air inlet jet pipe, anode, cathode, electric discharge chamber enclosure, spark plug, power-supply system, storage capacitor；
The gas collector is connect with inlet channel, on inlet channel, is provided with flow regulator and storage tank；
Inlet channel connect with thruster anode downstream through electric discharge chamber enclosure, air inlet jet pipe is provided on anode；Discharge chamber enclosure
In tubular open at one end, cathode is provided on the inner wall of open end, the space between cathode and anode is discharge channel, spark plug
It is fixed on electric discharge chamber enclosure, and is electrically connected with cathode；Cathode and anode are connected with the both ends of storage capacitor respectively, storage capacitor
It is connected with the charging module of power-supply system, the anode of spark plug and the ignition module of power-supply system are connected；
High-speed gas enters gas collector, enters the disturbance that storage tank reduces high-speed gas, In by flow control valve
Gas is adjusted air-flow before entering discharge channel；
Power-supply system charges to capacitor, makes to hold high pressure between cathode and anode, and Incoming gas passes through air inlet jet pipe
Into discharge channel, generating charged particle by plug ignition makes that electric discharge is connected between electrode, and plasma is in loop current shape
At magnetic field and electrode between under the electric field collective effect that is formed, generate electromagnetism and accelerate and spray electric discharge chamber enclosure, generation thrust.
Further include control module, for controlling flow regulator, realizes the adjusting of charge flow rate.
Further include heating module, is heated for the Incoming gas before entering discharge channel, adjust temperature.
The flow regulator is realized using shaft valve.
The thrust F finally generated are as follows:
Wherein, IbitFor first momentum,For charge flow rate, ε is the ionization rate of working medium, and η is the efficiency of thruster, and C is energy storage
The capacitance of capacitor, U are the charging voltage of power-supply system charging module, and f is the spark rate of power-supply system ignition module.
Electric discharge chamber enclosure is using insulation and heat-resisting material is made.
Gas collector leading portion is cylindrical shape, and back segment is shrinkage type channel, and gas collector leading portion diameter is in 80-
150mm；Angular range between leading portion and back segment is 120 °~150 °, and gas collector uses glass steel material.
The storage tank is spherical storage tank, a diameter of 80-100mm.
Air inlet jet pipe is uniformly distributed circumferentially on anode, the angular range between air inlet jet pipe and anode be 30 °~
60 °, the diameter of air inlet jet pipe is 2mm~4mm.
The cathode of the cathode electrode and spark plug is conducted, and the two closely connects.
The axis of the anode of open column shape and electric discharge chamber enclosure it is axially coincident, insulate between cathode and anode, the two it
Between distance be greater than 20mm；The material of cathode and anode is copper.
The cathode end is the jet pipe of propulsion system, is expansion structure, reduces the electrode corrosion that particle bombardment generates；Yin
Extremely ring structure, axial length 60mm.
Compared with the prior art, the invention has the advantages that:
(1) present invention does not need self-contained propellant using room atmosphere as propellant, and propulsion-system mass is light, transmitting
At low cost, the lifetime of satellite is extended；
(2) present invention is using the N in the rarefied atmosphere of space2、O2, O as propellant, no noxious products do not pollute atmosphere；
(3) present invention has flow regulator, can control gas ionization amount by adjusting air inflow according to mission requirements
To adjust thrust；
(4) satellite velocities of low rail flight are up to 7.75~7.81km/s, and high speed incoming flow is easily to thruster discharge channel shape
At disturbance.Present invention setting thus has the storage tank for adjusting incoming flow, reduces the disturbance of high-speed gas bring；
(5) thruster electrode of the present invention uses the coaxial configuration more compacter than parallel-plate electrode, reduces the diffusion of gas
Loss；
(6) multiple air inlet jet pipe settings are in hollow anode circumferential direction, being uniformly distributed and ionizing convenient for propellant；
(7) expanding channel outlet can reduce deposition of the plasma on discharge channel wall surface (i.e. cathode).
Detailed description of the invention
Fig. 1 is air-breathing pulse plasma thruster basic structure and system schematic of the invention.
Specific embodiment
A specific embodiment of the invention is further described in detail with reference to the accompanying drawing.
As shown in Figure 1, a kind of air-breathing pulse plasma thruster provided by the invention, including gas collector 1,
Flow regulator 2, inlet channel 3, storage tank 4, air inlet jet pipe 5, anode 6, cathode 7, electric discharge chamber enclosure 8, spark plug 9, power supply
System 10, storage capacitor 11；
The gas collector 1 is connect with inlet channel 3, on inlet channel 3, is provided with 2 He of flow regulator
Storage tank 4；Inlet channel 3 connect with thruster anode 6 downstream through electric discharge chamber enclosure 8, air inlet jet pipe is provided on anode 6
5；The chamber enclosure 8 that discharges is in tubular open at one end, is provided with cathode 7, the space between cathode 7 and anode 6 on the inner wall of open end
For discharge channel, spark plug 9 is fixed on electric discharge chamber enclosure 8, and is electrically connected with cathode 7；Cathode 7 and anode 6 respectively with energy storage
The both ends of capacitor 11 are connected, and the charging module of storage capacitor 11 and power-supply system 10 is connected, the anode and power-supply system of spark plug 9
10 ignition module is connected；
High-speed gas enters gas collector 1, enters the disturbance that storage tank 4 reduces high-speed gas by flow control valve 2,
Air-flow is adjusted before gas enters discharge channel；
Power-supply system 10 charges to capacitor 11, makes to hold high pressure between cathode 7 and anode 6, Incoming gas by into
Gas blowout pipe 5 enters discharge channel, and generating charged particle by the igniting of spark plug 9 makes that electric discharge is connected between electrode, and plasma is returning
Under the electric field collective effect formed between the electric current formed magnetic field in road and electrode, generates electromagnetism and accelerate and spray electric discharge chamber enclosure 8, produce
Raw thrust.
Preferably, thruster of the present invention further includes control module 12, for controlling flow regulator 2, realizes inlet air flow
The adjusting of amount.
Preferably, thruster of the present invention further includes heating module 13, for that will enter the Incoming gas before discharge channel
Heating adjusts temperature.
Preferably, thruster flow regulator 2 of the present invention is realized using shaft valve.
The thrust F finally generated are as follows:
Wherein, IbitFor first momentum,For charge flow rate, ε is the ionization rate of working medium, and η is the efficiency of thruster, and C is energy storage
The capacitance of capacitor 11, U are the charging voltage of 10 charging module of power-supply system, and f is the igniting frequency of 10 ignition module of power-supply system
Rate.
Specific structure parameter is as follows:
(1) electric discharge chamber enclosure 8 is using insulation and heat-resisting material is made.
(2) 1 leading portion of gas collector is cylindrical shape, and to flow into air intake duct convenient for gas, 1 back segment of gas collector is
Shrinkage type channel, 1 leading portion diameter of gas collector is in 80-150mm；Angular range between leading portion and back segment is 120 °~
150 °, gas collector 1 uses glass steel material.
(3) flow regulator 2 uses shaft valve, its working principle is that the shaft in rotating channel changes shaft hole and combustion
The angle of gas passage axis changes axial circulation area, and then controls the flow of combustion gas.This valve body is easy to control, occupancy
Space is small, it is not easy to cause venturi deposition blocking.
(4) storage tank 4 is spherical storage tank, and a diameter of 80-100mm, main function is to stablize incoming flow, to reduce air-flow to putting
The disturbance of plasma in electric channel.
(5) air inlet jet pipe 5 is uniformly distributed circumferentially on anode 6, it is therefore an objective to guarantee that working medium is circumferential each in discharge channel 8
Position is uniformly distributed, and reduces uneven electric discharge bring electrode corrosion.Angular range between air inlet jet pipe 5 and anode 6 is 30 °
~60 °, the diameter of air inlet jet pipe 5 is 2mm~4mm.
(6) 7 electrode of cathode and the cathode of spark plug 9 are conducted, and the two closely connects.
(7) axis of the anode 6 of open column shape and the axially coincident of chamber enclosure 8 of discharging, insulate between cathode 7 and anode 6,
Therebetween distance is greater than 20mm；The material of cathode 7 and anode 6 is copper.
(8) 7 end of cathode is the jet pipe of propulsion system, is expansion structure, reduces the electrode corrosion that particle bombardment generates；Yin
Pole 7 is ring structure, axial length 60mm.
Air-breathing pulse plasma thruster works in the satellite orbit away from ground 150km-250km, for the mesh for reaching air-breathing
, thruster air-breathing plane need to be perpendicular to direction of flow, therefore is different from traditional thruster, needs for this thruster to be arranged in
Four sides of aircraft.
The thruster course of work of the invention is described as follows:
When spacecraft orbits, gas will to enter gas collector 1 at a high speed, by flow regulator 2,
The flow of air inlet is controlled by flow-control module 13.The effect of storage tank 4 is to reduce the disturbance of high-speed gas, enters electric discharge in gas
Air-flow is adjusted before channel.Gas is preheated by heating device 12, enhances the electric heating acceleration of thruster.
Electric discharge and accelerating part are by the anode 6 equipped with air inlet jet pipe 5, cathode 7, discharge channel 8, and electric discharge trigger device
Spark plug 9 is constituted.Power unit is made of power-supply system 10 and storage capacitor 11, the control charged and lighted a fire.Power supply system
System charges to capacitor, makes to hold kilovolt high pressure between electrode, Incoming gas enters discharge channel, circuit by air inlet jet pipe
Plug ignition is controlled, generating charged particle makes that electric discharge is connected between electrode, and plasma is in the magnetic field that loop current is formed and electricity
Under the electric field action that interpolar is formed, electromagnetism acceleration is generated, accelerates to spray thruster, generates thrust.
A specific embodiment is given below:
On the typical low orbit away from ground 150km, running spacecraft speed is about 7.8km/s, therefore working medium will be with
The relative velocity of 7.8km/s enters propulsion system along gas collector, and gas collector is arranged in thruster front end.With
Afterwards, after Working medium gas enters inlet channel 3, air inflow is controlled by flow regulator 2 first, adjusts and enters discharge channel
Gas flow simultaneously limits the amount for generating plasma, to achieve the effect that control thrust；Subsequent working medium enters the storage in channel middle section
The air-flow of case, disorder is adjusted in storage tank, to reduce disturbance of the air-flow to discharge channel.Stable low-temperature airflow is from storage tank
By the pre-add heat effect of heating device 12, into anode 6, the anode 6 of thruster is hollow structure, and Incoming gas is introduced into
Inside anode 6, then from anode 6 air inlet jet pipe 5 enter discharge channel 8.The main component of working medium is in rarefied atmosphere
N2、O2And O, under the firing circuit control in power-supply system 10,9 discharge igniting of spark plug, storage capacitor electric discharge makes working medium exist
Ionization in discharge channel 8, main cation product are N+And O+, ion accelerate in electromagnetic field spray, generate thrust.
The relationship of the thrust F and charge flow rate that finally generate can be derived as follows:
E0=CU2/2
Ek=E0η
Δ v=(2Ek/mbit/ε)1/2
Ibit=mbitεΔv
Wherein, IbitFor first momentum, mbitFor single pulse consumption working medium quality,For charge flow rate, ε is the electricity of working medium
From rate, η is the efficiency of thruster, and C is the capacitance of storage capacitor 11, and U is the charging voltage of 10 charging module of power-supply system, f
For the spark rate of 10 ignition module of power-supply system.
Principle and design scheme based on the invention estimate engine parameter as follows:
According to the data of NASA atmospheric model MSISE-1990, the particle being primarily present on away from ground 150km height track
There is N2、O2, O, particle density is respectively 3.2 × 1016、3.3×1015And 1.9 × 1016m-3, herein according to each component particle
Density in orbit altitude, it is about m that average weighted single particle quality, which is calculated,0=4 × 10-26Kg, total population density
About N=5.43 × 1016m-3.Air inlet diameter d=0.1m, entrance particle rapidity are v=7.8km/s.Work as pulsed plasma
When thruster discharge frequency is 1Hz, the working medium quality into arc chamber is
mbit=NvSm0T=3 × 10-7kg
Wherein S is air inlet open area, and t=1s is the time interval between electric discharge twice.It is pushed away according to certain pulsed plasma
Power implement body example, if thruster ionization rate be ε=30%, thruster efficiency be η=15%, charging voltage U=2500V,
The capacitance of thruster storage capacitor is C=200 μ F, the electric energy E of impulse discharge thruster consumption0, plasma obtain it is dynamic
It can EkAnd the speed increment Δ v of plasma is respectively
E0=CU2/ 2=625J
Ek=E0η=94J
Δ v=(2Ek/mbit/ε)1/2=46km/s
First momentum is
Ibit=mbitε Δ v=4.1mNs
When discharge frequency is 2Hz, thrust 8.2mN, and atmospheric drag is less than 1mN, therefore illustrates pushing away for thruster generation
Power is much larger than the resistance that is subject to of satellite, other thruster parameters are set also in the normal parameters of this type of thruster
Count feasible, scheme is specifically implementable, and the value with practical application.
The present invention is explained in detail above in conjunction with drawings and examples, but the present invention is not limited to above-mentioned implementations
Example, within the knowledge of a person skilled in the art, can also make without departing from the inventive concept of the premise
Various change out.The content being not described in detail in the present invention can use the prior art.Do not make in description of the invention in detail
The content carefully described belongs to techniques known.
Claims (12)
1. a kind of air-breathing pulse plasma thruster, it is characterised in that: adjust dress including gas collector (1), flow
Set (2), inlet channel (3), storage tank (4), air inlet jet pipe (5), anode (6), cathode (7), electric discharge chamber enclosure (8), spark plug
(9), power-supply system (10), storage capacitor (11)；
The gas collector (1) connect with inlet channel (3), on inlet channel (3), is provided with flow regulator
(2) and storage tank (4)；Inlet channel (3) is connect, on anode (6) downstream through electric discharge chamber enclosure (8) with thruster anode (6)
It is provided with air inlet jet pipe (5)；Electric discharge chamber enclosure (8) is in tubular open at one end, is provided with cathode (7) on the inner wall of open end,
Space between cathode (7) and anode (6) is discharge channel, and spark plug (9) is fixed in electric discharge chamber enclosure (8), and with cathode (7)
It is electrically connected；Cathode (7) and anode (6) are connected with the both ends of storage capacitor (11) respectively, storage capacitor (11) and power-supply system
(10) charging module is connected, and the anode of spark plug (9) and the ignition module of power-supply system (10) are connected；
High-speed gas enters gas collector (1), enters storage tank (4) by flow control valve (2) and reduces disturbing for high-speed gas
It is dynamic, air-flow is adjusted before gas enters discharge channel；
Power-supply system (10) charges to capacitor (11), makes to hold high pressure between cathode (7) and anode (6), and Incoming gas is logical
Air inlet jet pipe (5) are crossed into discharge channel, being lighted a fire by spark plug (9) generates charged particle and makes to be connected between electrode to discharge, wait from
Under the electric field collective effect that daughter is formed between the magnetic field that loop current is formed and electrode, generates electromagnetism and accelerate and spray discharge cavity
Shell (8) generates thrust.
2. a kind of air-breathing pulse plasma thruster according to claim 1, it is characterised in that: further include control mould
Block realizes the adjusting of charge flow rate for controlling flow regulator (2).
3. a kind of air-breathing pulse plasma thruster according to claim 1, it is characterised in that: further include heated mould
Block heats for the Incoming gas before entering discharge channel, adjusts temperature.
4. air-breathing pulse plasma thruster described in any one of claim 1 to 3, it is characterised in that: described
Flow regulator (2) is realized using shaft valve.
5. air-breathing pulse plasma thruster described in any one of claim 1 to 3, it is characterised in that: final
The thrust F of generation are as follows:
Wherein, IbitFor first momentum,For charge flow rate, ε is the ionization rate of working medium, and η is the efficiency of thruster, and C is storage capacitor
11 capacitance, U are the charging voltage of 10 charging module of power-supply system, and f is the spark rate of 10 ignition module of power-supply system.
6. air-breathing pulse plasma thruster described in any one of claim 1 to 3, it is characterised in that: electric discharge
Chamber enclosure (8) is using insulation and heat-resisting material is made.
7. air-breathing pulse plasma thruster described in any one of claim 1 to 3, it is characterised in that: gas
Collection device (1) leading portion is cylindrical shape, and back segment is shrinkage type channel, and gas collector (1) leading portion diameter is in 80-150mm；Before
Angular range between section and back segment is 120 °~150 °, and gas collector (1) uses glass steel material.
8. air-breathing pulse plasma thruster described in any one of claim 1 to 3, it is characterised in that: described
Storage tank (4) is spherical storage tank, a diameter of 80-100mm.
9. air-breathing pulse plasma thruster described in any one of claim 1 to 3, it is characterised in that: air inlet
Jet pipe (5) is uniformly distributed circumferentially on anode (6), the angular range between air inlet jet pipe (5) and anode (6) be 30 °~
60 °, the diameter of air inlet jet pipe (5) is 2mm~4mm.
10. air-breathing pulse plasma thruster described in any one of claim 1 to 3, it is characterised in that: described
Cathode (7) electrode and the cathode of spark plug (9) are conducted, and the two closely connects.
11. air-breathing pulse plasma thruster described in any one of claim 1 to 3, it is characterised in that: hollow
The axis of columnar anode (6) and electric discharge chamber enclosure (8) it is axially coincident, insulate between cathode (7) and anode (6), the two it
Between distance be greater than 20mm；Cathode (7) and the material of anode (6) are copper.
12. air-breathing pulse plasma thruster described in any one of claim 1 to 3, it is characterised in that: described
Cathode (7) end is the jet pipe of propulsion system, is expansion structure, reduces the electrode corrosion that particle bombardment generates；Cathode (7) is ring
Shape structure, axial length 60mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910740846.1A CN110439771A (en) | 2019-08-12 | 2019-08-12 | A kind of air-breathing pulse plasma thruster |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910740846.1A CN110439771A (en) | 2019-08-12 | 2019-08-12 | A kind of air-breathing pulse plasma thruster |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110439771A true CN110439771A (en) | 2019-11-12 |
Family
ID=68434680
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910740846.1A Pending CN110439771A (en) | 2019-08-12 | 2019-08-12 | A kind of air-breathing pulse plasma thruster |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110439771A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111120235A (en) * | 2019-12-24 | 2020-05-08 | 兰州空间技术物理研究所 | Air suction type electric propulsion device based on turbocharging |
| CN112224451A (en) * | 2020-10-26 | 2021-01-15 | 中国人民解放军国防科技大学 | Low-space-orbit rarefied atmospheric molecule intake device |
| CN112572833A (en) * | 2020-12-05 | 2021-03-30 | 中国人民解放军国防科技大学 | Intelligent attitude and orbit control system based on air suction type electric propulsion |
| CN114001003A (en) * | 2021-10-26 | 2022-02-01 | 北京理工大学 | Double-section coaxial toothed cathode pulse plasma thruster |
| CN115681057A (en) * | 2023-01-03 | 2023-02-03 | 国科大杭州高等研究院 | Hall propulsion system and operation method thereof |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3923878A1 (en) * | 1989-07-19 | 1991-01-31 | Strobel Christian M Dipl Ing T | Air-breathing perpetual motion machine for vehicular propulsion - eliminates liq. air consumption through continuous recycling of atmos. air through compressor, cooler and gravitonic evaporator |
| US7581380B2 (en) * | 2006-08-07 | 2009-09-01 | Wahl Eric L | Air-breathing electrostatic ion thruster |
| CN102797656A (en) * | 2012-08-03 | 2012-11-28 | 北京卫星环境工程研究所 | Air breathing type helicon wave electric propulsion device |
| CN103453805A (en) * | 2013-09-05 | 2013-12-18 | 兰州空间技术物理研究所 | Air-breathing electric rocket for low-orbit spacecraft |
| CN106286179A (en) * | 2016-10-14 | 2017-01-04 | 楚龙飞 | Air suction type ion engine |
| CN109737023A (en) * | 2018-12-10 | 2019-05-10 | 兰州空间技术物理研究所 | A kind of self breakdown type pulsed plasma thruster of annular vertebral body structure anode |
-
2019
- 2019-08-12 CN CN201910740846.1A patent/CN110439771A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3923878A1 (en) * | 1989-07-19 | 1991-01-31 | Strobel Christian M Dipl Ing T | Air-breathing perpetual motion machine for vehicular propulsion - eliminates liq. air consumption through continuous recycling of atmos. air through compressor, cooler and gravitonic evaporator |
| US7581380B2 (en) * | 2006-08-07 | 2009-09-01 | Wahl Eric L | Air-breathing electrostatic ion thruster |
| CN102797656A (en) * | 2012-08-03 | 2012-11-28 | 北京卫星环境工程研究所 | Air breathing type helicon wave electric propulsion device |
| CN103453805A (en) * | 2013-09-05 | 2013-12-18 | 兰州空间技术物理研究所 | Air-breathing electric rocket for low-orbit spacecraft |
| CN106286179A (en) * | 2016-10-14 | 2017-01-04 | 楚龙飞 | Air suction type ion engine |
| CN109737023A (en) * | 2018-12-10 | 2019-05-10 | 兰州空间技术物理研究所 | A kind of self breakdown type pulsed plasma thruster of annular vertebral body structure anode |
Non-Patent Citations (1)
| Title |
|---|
| IAN K. JOHNSON等: "Pulsed Plasma Thrusters for Atmospheric Operation", 《JOINT PROPULSION CONFERENCE》 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111120235A (en) * | 2019-12-24 | 2020-05-08 | 兰州空间技术物理研究所 | Air suction type electric propulsion device based on turbocharging |
| CN111120235B (en) * | 2019-12-24 | 2022-03-18 | 兰州空间技术物理研究所 | Air suction type electric propulsion device based on turbocharging |
| CN112224451A (en) * | 2020-10-26 | 2021-01-15 | 中国人民解放军国防科技大学 | Low-space-orbit rarefied atmospheric molecule intake device |
| CN112572833A (en) * | 2020-12-05 | 2021-03-30 | 中国人民解放军国防科技大学 | Intelligent attitude and orbit control system based on air suction type electric propulsion |
| CN114001003A (en) * | 2021-10-26 | 2022-02-01 | 北京理工大学 | Double-section coaxial toothed cathode pulse plasma thruster |
| CN115681057A (en) * | 2023-01-03 | 2023-02-03 | 国科大杭州高等研究院 | Hall propulsion system and operation method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110439771A (en) | A kind of air-breathing pulse plasma thruster | |
| US9796487B2 (en) | Fuel-free spacecraft propelling system based on spatial atomic oxygen and propelling method | |
| Zheng et al. | A comprehensive review of atmosphere-breathing electric propulsion systems | |
| Mazouffre | Electric propulsion for satellites and spacecraft: established technologies and novel approaches | |
| CN103912466B (en) | A kind of electrical fluid power propeller | |
| US6996972B2 (en) | Method of ionizing a liquid propellant and an electric thruster implementing such a method | |
| CN104696180B (en) | Magnetic field regulation type liquid phase working fluid large area microcavity discharge plasma micro-thruster | |
| US9657725B2 (en) | Ion thruster | |
| CN107939625B (en) | Reflection type laser-electromagnetic field coupling thruster | |
| Nishiyama | Air breathing ion engine concept | |
| EP2853736B1 (en) | Chemical-electromagnetic hybrid propulsion system with variable specific impulse | |
| CN106286179A (en) | Air suction type ion engine | |
| RU2738136C1 (en) | Ionic rocket engine and method of operation thereof | |
| EP3872342A1 (en) | Intake system for an atmosphere breathing electric thruster, spacecraft | |
| CN108612599A (en) | A kind of liquid-electricity interblock space thruster | |
| Aheieva et al. | Vacuum arc thruster development and testing for micro and nano satellites | |
| RU2449170C1 (en) | Inertial engine by bogdanov | |
| Komurasaki | An overview of electric propulsion activities in Japan | |
| JP2017002851A (en) | Vacuum arc propeller | |
| CN116101516B (en) | Satellite with electrostatic electric propulsion system | |
| CN113665848B (en) | Magnetic field force/moment action delivery system and ground testing device thereof | |
| Rosales | Investigation of a Pulsed Plasma Thruster for Atmospheric Applications | |
| JP7455439B1 (en) | Artificial object control method, artificial object control device, and artificial object equipped with the same | |
| Stratton | High current steady state coaxial plasma accelerators. | |
| RU205174U1 (en) | Electric rocket engine for acceleration and trajectory correction of spacecraft |
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 | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20191112 |
|
| RJ01 | Rejection of invention patent application after publication |