CN103912466A - Electric hydrodynamic force propeller - Google Patents
Electric hydrodynamic force propeller Download PDFInfo
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- CN103912466A CN103912466A CN201410140861.XA CN201410140861A CN103912466A CN 103912466 A CN103912466 A CN 103912466A CN 201410140861 A CN201410140861 A CN 201410140861A CN 103912466 A CN103912466 A CN 103912466A
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Abstract
The invention relates to an electric hydrodynamic force propeller which comprises a contracting nozzle connected with a synchronous multistage accelerator. An alternating positive-negative plasma generator is fixed at the air inlet end of the synchronous multistage accelerator. A support plate is disposed at the outer edge of the alternating positive-negative plasma generator. Connecting plates are located on the inner side of the support plate. Every two adjacent layers of connecting plates and the corresponding hollow connecting plate enclose an air passage. Each annular electrode is connected with a high-frequency pulse power supply, which is grounded, through a wire. An alternating positive-negative plasma emitting unit is disposed in each mounting hole. Each high-frequency tip electrode and the corresponding high-frequency circular electrode form corona discharge, the plasma of the corresponding alternating positive-negative plasma emitting unit is sprayed, the plasma mixed with the air flowing in from the air passage enters the synchronous multistage accelerator, and charge particles and the air accelerated by the synchronous multistage accelerator enter the contracting nozzle and are sprayed out by the same after acceleration. By the electric hydrodynamic force propeller, bottlenecks of high temperature and high pressure are overcome, aero-space flight is achieved, high specific impulse and propelling efficiency are achieved, and propellant mass is reduced.
Description
Technical field
The invention belongs to field of aerospace technology, be specifically related to a kind of electrical fluid power propeller.
Background technique
In current propulsion device field, traditional solid propellant rocket and the propulsive efficiency of liquid propellant rocket engine are on the low side, and entrained propellant mass is large, and useful load is less than normal; Traditional airplane engine such as whirlpool spray, turbofan cannot be realized flight in empty day, and has the bottleneck problems such as High Temperature High Pressure; The new concept engine such as pressed engine and pulse-knocking engine also cannot be realized flight in empty day; Although the new electrofluid propulsion device proposing and mhd thruster be than leaping high, also and be not suitable for the flight in atmosphere.Therefore develop a kind of new Push Technology with high-energy utilization ratio and realize flight in empty day, to promoting aerospace development to there is important future in engineering applications and practical significance.
Electrofluid Push Technology aspect, did a lot of research and trial abroad.Wherein EHD(electrofluid advances) air pump has been realized the acceleration to air in atmosphere, but acceleration performance is on the low side.In current disclosed foreign language document, air pump makes air accelerate to be difficult to exceed 10M/S from static beginning under mark condition, the efficiency of its single-stage pump all below 10%, the trend that the efficiency of multistage pump tapers off along with the increase of progression.In structure, causing EHD(electrofluid to advance) air pump efficiency is lower, and thrust reason less than normal is that ionization do not carry out separating of function with accelerating, and ionizes and accelerate to carry out in the same area.This structure makes to ionize required noncontinuous electrode spacing, the long acceleration distance that large voltage gradient is required with acceleration, and small voltage gradient is conflicting, thereby has caused the efficiency of whole system lower, and thrust is less than normal.
At home, patent of invention [201010107194.7] discloses a kind of high-frequency and high-voltage single electrode plasma propulsion device as astrovehicle auxiliary propulsion, this propeller structure is simple, than leaping high, but be only suitable in the auxiliary propulsion of exoatmosphere astrovehicle, and thrust is less, be not suitable as the major impetus of flight in empty day.
Two critical bottlenecks finding electric propulsion technology by a large amount of research are that thrust is little, and efficiency is low.Patent of the present invention has solved above two technical bottlenecks by designing the positive and negative plasma generator of unique alternation with synchronous multi-stage accelerator, has obtained a kind of novel propulsion device based on electrohydrodynamics.This propulsion device has the needs of three kinds of mode of operations corresponding to low latitude, near space and three kinds of working environments of space, is a kind of propulsion device of the empty day aircraft with extensive adaptive capacity truly.
Summary of the invention
In order to overcome above-mentioned the deficiencies in the prior art, the object of this invention is to provide a kind of electrical fluid power propeller, overcome the High Temperature High Pressure bottleneck existing in prior art, realize flight in empty day, there is higher specific impulse and propulsive efficiency, reduce propellant mass.
To achieve these goals, the technical solution used in the present invention is: a kind of electrical fluid power propeller, comprises alternation kation anion generator, synchronous multi-stage accelerator and contracting nozzle three parts; Contracting nozzle with synchronize multi-stage accelerator be connected, the inlet end of synchronous multi-stage accelerator is fixed with the positive and negative plasma generator of alternation, the outer rim of the positive and negative plasma generator of alternation is provided with dunnage, connecting plate is positioned at dunnage inner side, be divided into from the inside to the outside five layers, connecting plate is hollow annular slab, is connected between layers by equally distributed four hollow connecting plates, and the runner that adjacent two layers connecting plate and four corresponding hollow connecting plates surround is air flow channel;
Described synchronous multi-stage accelerator is made up of screw pilot hole, synchronous multi-stage accelerator unit, accelerator tube wall, ground connection, electric wire and high frequency pulse power supply; Four screw pilot holes are corresponding with the position of the screw hole of the positive and negative plasma generator of alternation; Accelerator tube wall is divided into inside and outside two-layer, is cavity between internal and external layer; Synchronous multi-stage accelerator unit is made up of ring electrode and insulating material; Ring electrode is connected by electric wire and high frequency pulse power supply; Filling insulating material, in the cavity of whole accelerator tube wall, is opened every one-level ring electrode isolation; High frequency pulse power supply is arranged on the outside of synchronous multi-stage accelerator, and by ground connection ground connection;
The positive and negative plasma generator of described alternation is made up of screw hole, dunnage, the positive and negative plasma emission of alternation unit, air flow channel and connecting plate; The annular backup pad of the positive and negative plasma generator of alternation by its outer rim with synchronize the front end of multi-stage accelerator and be connected; Four screw holes run through dunnage and are uniformly distributed in dunnage; In mounting hole in connecting plate, be provided with the positive and negative plasma emission of alternation unit.
The positive and negative plasma emission of described alternation unit, is made up of electric wire, high frequency round loop electrode, insulating material, plasma emission unit body and high-frequency and high-voltage point electrode; Described electric wire is divided into two-way, and wherein a road is connected with high frequency round loop electrode, and another road is connected with high-frequency and high-voltage point electrode, and there is a circular hole in described plasma emission unit body bottom centre; High-frequency and high-voltage point electrode is a needle-like metal body, the butt end cylindrical section of needle-like metal body is fixed on the center of insulating material, and taper end pointed cone section is passed bottom centre's circular hole of plasma emission unit body and made the tip of pointed cone stretch into the inside of plasma emission unit body; High frequency round loop electrode is nested in the butt end cylindrical section surrounding of high-frequency and high-voltage point electrode, between high frequency round loop electrode and high-frequency and high-voltage point electrode, has insulating material to intercept and wraps up;
Totally 126 of described mounting holes, from centre to outer rim, the mounting hole quantity of each layer is respectively 6,14,26,34 and 46, between mounting hole and mounting hole, closely arranges.
The hollow cavity of described hollow connecting plate and connecting plate is used for installing external circuits, and circuit is connected with high frequency pulse power supply and is the power supply of the positive and negative plasma emission of alternation unit.
Described outermost connecting plate and the interior sidewall surface of dunnage are welded to connect;
Described plasma emission unit body is a flat cylindrical shape.
Described high frequency round loop electrode is a circular ring metal body.
The cross section of fluid channel of described contracting nozzle is for shrinking shape conical surface, and gas inlet cross section is circular, and diameter is relatively large, and outlet is also circular, and diameter is relatively little.
The gas inlet end of described contracting nozzle with synchronize the gas outlet end of multi-stage accelerator by being weldingly connected.
Kation anion generator utilizes the high voltage of alternation to produce the plasma that positive and negative (electric charge) replaces, and makes plasma and the even blending of air; Synchronous multi-stage accelerator is for having the air of plasma to accelerate step by step blending, and the reaction force that accelerates air generation promotes propulsion device and travels forward; Plasma after contracting nozzle will speed up and air carry out blending, make it to become electroneutrality, and further rectification and acceleration; Last neutral air has sprayed angle of rake function and object from contracting nozzle end.
A kind of electric plating propulsion device of the present invention, change by controlling the switch on bit interleaving of phase of the high-frequency and high-voltage point electrode 13 of the positive and negative plasma emission of alternation unit 6 and high frequency round loop electrode 10, make to form between two-plate internal field's distortion and form coronal discharge, forming the alternating spray with the plasma of positive and negative charge; This plasma is synchronizeed multi-stage accelerator 2 with entering after the even blending of air, between adjacent two high frequency accelerating electrodes 15 of synchronous multi-stage accelerator 2, form the accelerating field corresponding with plasma charge therebetween, control the optimizing phase of each high frequency accelerating electrode 15, form isoionic lasting acceleration, carry out lasting momentum and energy interchange at whole accelerating process applying plasma and its ambient air neutral molecule, thereby realize the acceleration to dilution air.
Beneficial effect: the present invention utilize electricity and on-fuel mode as the main energy source of propulsion device, adopt alternation formula non-neutral plasma generation technique, synchronous multistage speed technology and frequency match technology, compared with existing aero engine technology, there is no rotatable parts, broken through the bottleneck problems such as High Temperature High Pressure, significantly improved propulsive efficiency and thrust weight ratio, make the thrust weight ratio of aeroengine from 10 current these orders of magnitude, significantly rise to 100 these orders of magnitude; To have broken through the thrust that existing electric propulsion device exists little in this invention in addition, and efficiency is low, cannot be at technical barriers such as endoatmosphere uses, applicable to aerospace field.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention.
Fig. 2 is the structural representation of the positive and negative plasma generator of alternation.
Fig. 3 is the structural representation of the positive and negative plasma emission of alternation unit.
Fig. 4 is the structural representation of synchronous multi-stage accelerator.
Fig. 5 is the charged phase diagram of high frequency round loop electrode 10 and high-frequency and high-voltage point electrode 13.
In figure:
1. contracting nozzle; 2. synchronous multi-stage accelerator; 3. the positive and negative plasma generator of alternation; 4. screw pilot hole; 5. dunnage; 6. the positive and negative plasma emission of alternation unit; 7. air flow channel; 8. connecting plate; 9. electric wire; 10. high frequency round loop electrode; 11. insulating material; The positive and negative plasma emission of 12. alternation unit body; 13. high-frequency and high-voltage point electrodes; 14. screw pilot holes; 15. synchronous multi-stage accelerator unit; 16. accelerator tube walls; 17. ground connection 18. electric wires; 19. high frequency pulse power supplies.
Embodiment
Below in conjunction with accompanying drawing, structural principle of the present invention and working principle are described in further detail.
Referring to Fig. 1, Fig. 2, Fig. 3, Fig. 4, Fig. 5,
The present embodiment is a kind of propulsion device that can be used for empty day aircraft, comprises contracting nozzle 1, synchronous multi-stage accelerator 2, the positive and negative plasma generator 3 of alternation, screw hole 4, dunnage 5, the positive and negative plasma emission of alternation unit 6, air flow channel 7, connecting plate 8, electric wire 9, high frequency round loop electrode 10, insulating material 11, the positive and negative plasma emission of alternation unit body 12, high-frequency and high-voltage point electrode 13, screw pilot hole 14, synchronous multi-stage accelerator unit 15, accelerator tube wall 16, ground connection 17, electric wire 18, high frequency pulse power supply 19.
Referring to Fig. 1,2, the positive and negative plasma generator 3 of described alternation is made up of screw hole 4, dunnage 5, the positive and negative plasma emission of alternation unit 6, air flow channel 7 and connecting plate 8.Described dunnage 5 is an annular slab, be positioned at the outer rim of the positive and negative plasma generator 3 of alternation, be used for supporting the positive and negative plasma generator 3 of whole alternation, and be connected to the front end of synchronous multi-stage accelerator 2, rise and support and connection function, the external diameter of dunnage 5 is between 40～3000mm, and the present embodiment is 100mm, the internal diameter of dunnage 5 is between 30～2700mm, and the present embodiment is 80mm.Totally four of described screw holes 4, run through dunnage 5 and distribute uniformly in dunnage 5, and screw hole 4 is for being fixed on positive and negative alternation plasma generator 3 inlet end of synchronous multi-stage accelerator 2.Described connecting plate 8 is positioned at dunnage 5 inner sides, be divided into from the inside to the outside five layers, every layer is all hollow annular slab, connected by equally distributed four hollow connecting plates between layers, the runner that the hollow annular slab of adjacent two layers and four corresponding hollow connecting plates surround is air flow channel 7, the interior sidewall surface of outermost surface annular slab and dunnage 5 is welded and fixed, and has mounting hole for the positive and negative plasma emission of alternation unit 6 is installed on connecting plate 8.Totally 126 of described mounting holes, from centre to outer rim, the mounting hole quantity of each layer is respectively 6,14,26,34 and 46, between mounting hole and mounting hole, closely arranges.
The hollow cavity of described hollow connecting plate 20 and connecting plate 8 is used for installing external circuits, and hollow connecting plate and hollow annular slab are also played a supporting role.Described circuit is connected with high frequency pulse power supply and is that the positive and negative plasma emission of alternation unit 6 powers.Described air flow channel 7 is that air enters whole angle of rake entrance, also plays the effect of rectification simultaneously.
Referring to, 2,3, the positive and negative plasma emission of described alternation unit 6, is made up of electric wire 9, high frequency round loop electrode 10, insulating material 11, plasma emission unit body 12 and high-frequency and high-voltage point electrode 13, for exciting positive and negative plasma.Described electric wire 9 is divided into two-way, and wherein a road is connected with high frequency round loop electrode 10, and another road is connected with high-frequency and high-voltage point electrode 13, the energy source that electric wire 9 is worked for the positive and negative plasma emission of alternation unit 6.Described plasma emission unit body 12 is a flat cylindrical shape, the height of cylinder is between 3～45mm, the present embodiment is 12mm, internal diameter is 2～45mm, the present embodiment is 6mm, wall thickness is 0.2～2mm, and the present embodiment is 0.7mm, has a circular hole for high-frequency and high-voltage point electrode 13 is installed in the bottom centre of flat cylinder.Described high-frequency and high-voltage point electrode 13 is a needle-like metal body, the butt end cylindrical section of needle-like metal body is fixed on insulating material 11 center, taper end pointed cone section is passed bottom centre's circular hole of plasma emission unit body 12 and is made the tip of pointed cone stretch into the inside of plasma emission unit body 12, butt end external diameter is 0.3～5mm, the present embodiment is 1mm, whole high-frequency and high-voltage point electrode 13 length are 3～45mm, and the present embodiment is 10mm.Described high frequency round loop electrode 10 is a circular ring metal body.Described circular ring metal body is nested in the butt end cylindrical section surrounding of high-frequency and high-voltage point electrode 13, and the external diameter of circular ring metal body is 1.8～40mm, and the present embodiment is 6mm, and internal diameter is 0.8～12mm, and the present embodiment is 2mm.Between described high-frequency and high-voltage point electrode 13 and high frequency round loop electrode 10, there is insulating material 11 to intercept and wrap up.
Referring to Fig. 1,4, described synchronous multi-stage accelerator 2 is between contracting nozzle 1 and the positive and negative plasma generator 3 of alternation, formed by screw pilot hole 14, synchronous multi-stage accelerator unit 15, accelerator tube wall 16, ground connection 17, electric wire 18 and high frequency pulse power supply 19, for accelerate plasma and drive air to accelerate backward to form together thrust forward.Totally four of described screw pilot holes 14, corresponding with the position of the screw hole 4 of the positive and negative plasma generator 3 of alternation, for positive and negative alternation plasma generator 3 is fixed on to synchronous multi-stage accelerator 2.Described accelerator tube wall 16 is divided into inside and outside two-layer, is cavity between internal and external layer, and the diameter of outer wall is 40～3000mm, and the present embodiment is 100mm, and the diameter of internal layer wall is 30～2700mm, and the present embodiment is 80mm.Between described internal and external layer wall, be cavity, for synchronous multi-stage accelerator unit 15 and circuit thereof are installed.Described synchronous multi-stage accelerator unit 15 is made up of ring electrode and insulating material, and ring electrode is connected by electric wire 18 and high frequency pulse power supply 19.The inside and outside two-layer wall of the diameter of described ring electrode and accelerator tube wall 16 adapts, and, between two-layer wall, meets the needs of insulation simultaneously.Distance between described synchronous multi-stage accelerator unit 15, the distance between level and level is 3～300mm, and the present embodiment is 40mm, and the potential difference of inter-stage is 5～30000V, the present embodiment is 5～8000V, and the size variation of inter-stage potential difference is used for regulating angle of rake thrust.
Described electric wire 18 is connected synchronous multi-stage accelerator unit 15 with the corresponding synchro source of high frequency pulse power supply 19.Described filling insulating material, in the cavity of whole accelerator tube wall 16, and is opened every one-level ring electrode isolation.Described high frequency pulse power supply 19 is arranged on the outside of synchronous multi-stage accelerator 2, and by ground connection 17 ground connection.
The cross section of fluid channel of described contracting nozzle 1 is for shrinking shape conical surface, and gas inlet cross section is circular, and diameter is relatively large, and outlet is also circular, and diameter is relatively little, and the inlet diameter of the present embodiment is 80mm, and outlet diameter is 65mm.The gas inlet end of described contracting nozzle 1 with synchronize the gas outlet end of multi-stage accelerator 2 by being weldingly connected, contracting nozzle 1 can further accelerate the gas after accelerating by synchronous multi-stage accelerator 2.
Referring to Fig. 5, a kind of electric plating propulsion device is work like this: start high frequency pulse power supply 19, the positive and negative plasma emission of all alternations unit 6 of the positive and negative plasma generator 3 of alternation all will obtain the pulsed voltage shown in Fig. 5, wherein voltage U
1be carried on high-frequency and high-voltage point electrode 13, voltage is 3000～60000V, and the present embodiment is 7000V, U
2be carried on high frequency round loop electrode 10, voltage is 3000～60000V, and the present embodiment is 7000V.0～t as shown in Figure 5
1moment, high-frequency and high-voltage point electrode 13 is with the positive voltage of 7000V, high frequency round loop electrode 10 is with the negative voltage of 7000V, high-frequency and high-voltage point electrode 13 will form coronal discharge with high frequency round loop electrode 10, the plasma of the positively charged of discharge generation will constantly accumulate and form certain concentration in the bottom of the positive and negative plasma emission of alternation unit body 12, and insulating material 11 will not puncture between protection high frequency round loop electrode 10 and high-frequency and high-voltage point electrode 13; At t
1～t
2moment, on high-frequency and high-voltage point electrode 13 with voltage be 0V, high frequency round loop electrode 10 is with the positive voltage of 7000V, and within this time period, coronal discharge finishes, and the plasma of the positively charged of the bottom accumulation of the positive and negative plasma emission of alternation unit body 12 is ejected; At t
2～t
3moment, high-frequency and high-voltage point electrode 13 is with the negative voltage of 7000V, high frequency round loop electrode 10 is with the positive voltage of 7000V, high-frequency and high-voltage point electrode 13 will form coronal discharge with high frequency round loop electrode 10, and the electronegative plasma of discharge generation will constantly accumulate and form certain concentration in the bottom of the positive and negative plasma emission of alternation unit body 12; At t
3～t
4moment, on high-frequency and high-voltage point electrode 13 with voltage be 0V, high frequency round loop electrode 10 is with the negative voltage of 7000V, within this time period, coronal discharge finishes, the electronegative plasma of the bottom accumulation of the positive and negative plasma emission of alternation unit body 12 is ejected, so move in circles, the positive and negative plasma generator 3 of alternation just can constantly eject the plasma with like charges according to required frequency and plasma ion concentration, and the frequency of the present embodiment is 10～2000HZ.The plasma that the positive and negative plasma generator 3 of described alternation sprays is synchronizeed multi-stage accelerator 2 with entering from air flow channel 7 leaked-in air blending.The synchronous multi-stage accelerator of described every one-level unit 15 is all connected with high frequency pulse power supply 19, and be loaded with pulsed voltage, pulsed voltage constantly circulates as one-period using positive voltage, no-voltage, negative voltage, no-voltage, 1/4 cycle of voltage phase difference that the synchronous multi-stage accelerator of adjacent two-stage unit 15 loads.The synchronous multi-stage accelerator of described every one-level unit 15 forms an equipotential surface when charged.Between described equipotential surface, form accelerating field, accelerating field is accelerated plasma and is driven air to accelerate together, and the reaction force that accelerate plasma produces has formed propulsion device thrust forward.The electric voltage frequency loading on the pulse repetition frequency loading on described synchronous multi-stage accelerator unit 15 and the positive and negative plasma emission of alternation unit 6 matches.The frequency of the pulsed voltage loading on described synchronous multi-stage accelerator unit 15 is higher, and the pressure reduction between pulse generating positive and negative voltage is larger, and angle of rake thrust is just larger.Charged particle and air after synchronous multi-stage accelerator 2 accelerates will enter contracting nozzle 1, to there is neutralization reaction in the plasma with different electric charges in contracting nozzle 1, form neutral air molecule and together with other air in the interior acceleration of contracting nozzle 1, finally from contracting nozzle 1 outlet port ejection.
Claims (10)
1. an electrical fluid power propeller, comprise alternation kation anion generator (3), synchronous multi-stage accelerator (2) and contracting nozzle (1) three part, it is characterized in that, contracting nozzle (1) with synchronize multi-stage accelerator (2) and be connected, the inlet end of synchronous multi-stage accelerator (2) is fixed with the positive and negative plasma generator of alternation (3); The outer rim of the positive and negative plasma generator of alternation (3) is provided with dunnage (5), connecting plate (8) is positioned at dunnage (5) inner side, connecting plate (8) is hollow annular slab, and connecting plate is connected by equally distributed hollow connecting plate (20) between layers; The runner that adjacent two layers connecting plate (8) and corresponding hollow connecting plate (20) surround is air flow channel (7);
Described synchronous multi-stage accelerator (2) is made up of screw pilot hole (14), synchronous multi-stage accelerator unit (15), accelerator tube wall (16), ground connection (17), electric wire (18) and high frequency pulse power supply (19), accelerator tube wall (16) is divided into inside and outside two-layer, is cavity between internal and external layer; Synchronous multi-stage accelerator unit (15) is made up of ring electrode and insulating material, ring electrode is connected by electric wire (18) and high frequency pulse power supply (19), filling insulating material, in the cavity of whole accelerator tube wall (16), is opened every one-level ring electrode isolation; High frequency pulse power supply (19) is arranged on the outside of synchronous multi-stage accelerator (2), and by ground connection (17) ground connection;
The positive and negative plasma generator of described alternation (3) is by screw hole (4), dunnage (5), the positive and negative plasma emission of alternation unit (6), air flow channel (7) and connecting plate (8) composition, the annular backup pad (5) of the positive and negative plasma generator of alternation (3) by its outer rim is with to synchronize the front end of multi-stage accelerator (2) connected, four screw holes (4) run through dunnage (5) and are uniformly distributed in dunnage (5), in mounting hole in connecting plate (8), be provided with the positive and negative plasma emission of alternation unit (6).
2. a kind of electrical fluid power propeller according to claim 1, it is characterized in that, the positive and negative plasma emission of described alternation unit (6), is made up of electric wire (9), high frequency round loop electrode (10), insulating material (11), plasma emission unit body (12) and high-frequency and high-voltage point electrode (13); Described electric wire (9) is divided into two-way, and wherein a road is connected with high frequency round loop electrode (10), and another road is connected with high-frequency and high-voltage point electrode (13), and there is a circular hole in described plasma emission unit body (12) bottom centre; High-frequency and high-voltage point electrode (13) is a needle-like metal body, the butt end cylindrical section of needle-like metal body is fixed on the center of insulating material (11), and taper end pointed cone section is passed bottom centre's circular hole of plasma emission unit body (12) and made the tip of pointed cone stretch into the inside of plasma emission unit body (12); High frequency round loop electrode (10) is nested in the butt end cylindrical section surrounding of high-frequency and high-voltage point electrode (13), between high frequency round loop electrode (10) and high-frequency and high-voltage point electrode (13), has insulating material (11) to intercept and wrap up.
3. a kind of electrical fluid power propeller according to claim 1 and 2, it is characterized in that, totally 126 of described mounting holes, from centre to outer rim, the mounting hole quantity of each layer is respectively 6,14,26,34 and 46, between mounting hole and mounting hole, closely arranges.
4. a kind of electrical fluid power propeller according to claim 1, it is characterized in that, the hollow cavity of described hollow connecting plate (20) and connecting plate (8) is used for installing external circuits, and circuit is connected with high frequency pulse power supply and is the positive and negative plasma emission of alternation unit (6) power supply.
5. a kind of electrical fluid power propeller according to claim 1, is characterized in that, described outermost connecting plate (8) is welded to connect with the interior sidewall surface of dunnage (5).
6. a kind of electrical fluid power propeller according to claim 2, is characterized in that, described plasma emission unit body (12) is a flat cylindrical shape.
7. a kind of electrical fluid power propeller according to claim 2, is characterized in that, described high frequency round loop electrode (10) is a circular ring metal body.
8. a kind of electrical fluid power propeller according to claim 1, is characterized in that, the cross section of fluid channel of described contracting nozzle (1) is for shrinking shape conical surface, gas inlet cross section is circular, diameter is relatively large, and outlet is also circular, and diameter is relatively little.
9. a kind of electrical fluid power propeller according to claim 1, is characterized in that, the gas inlet end of described contracting nozzle (1) with synchronize the gas outlet end of multi-stage accelerator (2) by being weldingly connected.
10. a kind of electrical fluid power propeller according to claim 1, is characterized in that, described connecting plate (8) is divided into five layers from the inside to the outside, and the quantity of hollow connecting plate (20) is four.
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