CN211397783U - Ultra-low rail variable thrust air suction type magnetic plasma thruster - Google Patents
Ultra-low rail variable thrust air suction type magnetic plasma thruster Download PDFInfo
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- CN211397783U CN211397783U CN201920988094.6U CN201920988094U CN211397783U CN 211397783 U CN211397783 U CN 211397783U CN 201920988094 U CN201920988094 U CN 201920988094U CN 211397783 U CN211397783 U CN 211397783U
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Abstract
The utility model provides an ultra-low rail variable thrust air suction type magnetic plasma thruster, which comprises an air suction channel, an air inlet and an air outlet, wherein the air suction channel is provided with the air inlet and the air outlet and is used for compressing thin air and sucking the air into the thruster; the discharge cavity is communicated with the air outlet and consists of a cathode body, an anode body and a power supply, the cathode body and the anode body are electrically connected with the power supply and are used for ionizing compressed rarefied air into plasma and accelerating the plasma to be sprayed out under the action of an electric field, and a magnetic field is arranged in the discharge cavity to further improve the effect of accelerating the plasma to be sprayed out; and the flow limiting valve is positioned between the air suction channel and the discharge cavity, the air inlet end of the flow limiting valve is communicated with the air outlet, and the air outlet end of the flow limiting valve is communicated with the discharge cavity and used for controlling the mass flow of the compressed air mass entering the discharge cavity. The processes of capture, storage, ionization, acceleration and the like of the weak air in the environment by the thruster are realized, so that the thrust is stably generated. The utility model discloses be applied to aerospace technology and plasma field.
Description
Technical Field
The utility model relates to an aerospace technology and plasma field especially relate to an ultra-low rail variable thrust formula magnetism plasma thrustor of breathing in.
Background
With the gradual saturation of the number of satellites in space orbits, the ultra-low orbit becomes a new choice for expanding the operation range and improving the task capability of the satellites. Compared with other orbits, the satellite operates on an ultra-low orbit, so that the launching cost of the satellite can be obviously reduced, the navigation positioning precision and the response speed of the satellite are improved, and the satellite has wide application prospects in the fields of weather prediction, bipolar ice coverage monitoring, fire monitoring, agricultural monitoring, electronic communication, positioning navigation, remote sensing and the like. However, the particularity and complexity of the ultra-low orbit space environment make the permanent residence of the satellite face the problems of short service life, difficult propellant supply, high on-orbit maintenance cost and the like, and the development of the space ultra-low orbit satellite is severely restricted.
The pursuit of a propulsion system that is stable in performance, long in life, light in weight, and low in cost is the leading research focus in the current aerospace field. The novel propulsion scheme is developed on the basis of substances existing in the space environment as much as possible, the satellite related cost can be effectively reduced, the service life is prolonged, and a novel scheme is provided for the orbit control of the ultra-low orbit satellite. But the related research is still few, the precise variable thrust cannot be realized, and the power requirements of multiple flight missions of the ultra-low orbit satellite cannot be met.
SUMMERY OF THE UTILITY MODEL
To prior art in, the utility model aims at providing an ultra-low rail variable thrust formula magnetic plasma thrustor of breathing in.
The technical scheme is as follows:
an ultra-low rail variable thrust air-breathing magnetic plasma thruster, comprising:
the air suction channel is positioned at the head end of the thruster, is provided with an air inlet and an air outlet and is used for compressing the thin air and sucking the air into the thruster;
the discharge cavity is positioned at the tail end of the thruster, is communicated with the air outlet and consists of a cathode body, an anode body and a power supply, wherein the cathode body and the anode body are electrically connected with the power supply and are used for ionizing compressed thin air into plasma and accelerating the plasma to be sprayed out under the action of an electric field, and an accelerating magnetic field is arranged in the discharge cavity so as to further improve the effect of accelerating the plasma to be sprayed out;
and the flow limiting valve is positioned between the air suction channel and the discharge cavity, the air inlet end of the flow limiting valve is communicated with the air outlet, and the air outlet end of the flow limiting valve is communicated with the discharge cavity and used for controlling the mass flow of the compressed air mass entering the discharge cavity.
Further preferably, the device further comprises a flow divider, wherein the flow divider is positioned between the flow limiting valve and the discharge cavity;
the cathode body and the anode body are both in hollow columnar structures, the cathode body is positioned in a cavity of the anode body, an annular cavity is defined between the outer wall of the cathode body and the inner wall of the anode body, the discharge cavity is composed of the annular cavity and the residual cavity in the anode body, a magnetic coil is arranged on the outer wall of the anode body in a surrounding mode, and the accelerating magnetic field is generated by the magnetic coil;
one end of the flow divider is provided with a flow dividing inlet, the other end of the flow divider is provided with a first flow dividing outlet and a second flow dividing outlet surrounding the first flow dividing outlet, and the first flow dividing outlet and the second flow dividing outlet are both communicated with the flow dividing inlet through a flow dividing structure in the flow divider;
the split-flow inlet is communicated with the air outlet end of the flow limiting valve, the first split-flow outlet is communicated with the cavity of the cathode body, and the second split-flow outlet is communicated with the annular cavity.
Further preferably, the power supply includes:
the ignition circuit is electrically connected with the cathode body and the anode body and is used for igniting the air in the discharge cavity;
and the main discharge circuit is electrically connected with the cathode body and the anode body and is used for providing an electric field for the discharge cavity.
Further preferably, the ignition circuit includes:
the first charging power supply is used for charging the first capacitor;
a first capacitor including a first terminal and a second terminal, the first terminal of the first capacitor being coupled to an anode of the first charging source, the second terminal of the first capacitor being coupled to a cathode of the first charging source, the cathode body being coupled to the second terminal of the first capacitor and the cathode of the first charging source;
and the first silicon controlled rectifier comprises a first terminal and a second terminal, the first terminal of the first silicon controlled rectifier is coupled with the first terminal of the first capacitor and the anode of the first charging power supply, and the second terminal of the first silicon controlled rectifier is coupled with the anode body.
Further preferably, the main discharging circuit includes a second charging power supply, a second silicon controlled rectifier, a diode, a protection resistor, a relay, and n second capacitors C1～CnAnd n inductors L1～LnWherein n is a natural number greater than 1;
the second silicon controlled rectifier, the protective resistor, the relay and each second capacitor comprise a first terminal and a second terminal;
first and second capacitors C1Is coupled to the anode of a second charging source, an ith second capacitor CiAnd the (i + 1) th second capacitor Ci+1Is coupled via an ith inductance Li, each second capacitance C1～CnAre coupled with the cathode of a second charging power supply, wherein i is more than or equal to 1<n；
The nth second capacitor CnAlso through the nth inductance LnCoupled to the input of a diode, diodeThe output end of the tube is coupled with the anode body through a matching resistor;
the first terminal of the second silicon controlled rectifier is respectively connected with the cathode of the second charging power supply and each second capacitor C1～CnA second terminal of the second silicon controlled rectifier is coupled with the cathode body;
first and second capacitors C1Is further coupled to a first terminal of a protection resistor, a second terminal of said protection resistor being coupled to a first terminal of the relay, a second capacitor C2Is coupled to the second terminal of the relay and is grounded.
Further preferably, the air suction channel is of a horn-shaped structure, the air inlet is located at the large end of the horn-shaped structure, and the air outlet is located at the small end of the horn-shaped structure.
Further preferably, a part of the air suction channel on the air suction channel near the air outlet is made of a nitrogen and oxygen storage solid solution material, the rest part of the air suction channel is made of a foam silicon carbide material, and the foam silicon carbide material on the air suction channel is filled with a carbon molecular sieve.
Further preferably, the filling proportion of the carbon molecular sieve in the foamed silicon carbide material on the air suction channel gradually increases along the direction from the air inlet to the air outlet.
Further preferably, a reinforcing coating is arranged on the position, located at the air inlet, of the air suction channel.
Preferably, the cathode body is made of a tungsten metal material, and the anode body is made of a titanium metal material.
The utility model has the advantages of:
1. the utility model discloses simple structure carries out ionization and acceleration through the rarefied air after the compression, and then produces thrust, need not to carry the propellant, not only can avoid the propellant to exhaust the restriction to the thruster life-span, can save complicated propeller feeding device and ground assembly moreover, can effectively reduce the whole weight of thruster and cost, further promotes the performance.
2. The utility model discloses a to rarefied air absorption, compression and storage, recycle restriction valve realizes that compressed air gets into the flow control of discharging the chamber, utilizes the power that discharges of the rarefied air of power control in discharging the intracavity simultaneously, can effectively realize effectively satisfying the demand of the different tasks of satellite to the accurate control of thrust size.
3. The utility model discloses an arrange accelerating magnetic field in the discharge chamber, the electric field that combines to produce between the positive pole body and the negative pole body plays stable acceleration effect to the plasma that the air discharge produced, and then obtains thrust.
Drawings
Fig. 1 is a sectional view of a thruster in this embodiment;
FIG. 2 is a schematic diagram of a flow dividing process of the flow divider according to the present embodiment;
FIG. 3 is a schematic structural diagram of a flow limiting valve in the present embodiment;
fig. 4 is a schematic circuit diagram of the power supply of the present embodiment.
Detailed Description
In order to make the objects, technical solutions and advantages of the present disclosure more apparent, the present invention will be further described in detail with reference to the following specific embodiments, which are illustrated in the accompanying drawings. It should be noted that, in the drawings or the description, the undescribed contents and parts of english are abbreviated as those well known to those skilled in the art. Some specific parameters given in the present embodiment are merely exemplary, and the values may be changed to appropriate values accordingly in different embodiments.
The ultra-low rail variable thrust air-breathing magnetic plasma thruster shown in fig. 1 comprises an air suction channel 1, a flow limiting valve 2, a flow divider 3, a cathode body 4, an anode body 5, a magnetic coil 6, a power supply 7 and the like, wherein specifically:
the air suction channel 1 is of a horn-shaped structure with gradually reduced cross section area, is positioned at the head end of the thruster, and is provided with an air inlet 11 and an air outlet 12, the air inlet 11 is positioned at the large end of the horn-shaped structure, and the air outlet 12 is positioned at the small end of the horn-shaped structure, so that the compression of rarefied air is effectively realized, and the bulk density of incoming air is increased; the part of the air suction channel 1 on the air suction channel 1 close to the air outlet 12 is made of nitrogen and oxygen storage solid solution materials, the rest of the air suction channel 1 is made of foam silicon carbide materials, carbon molecular sieves are filled in the foam silicon carbide materials on the air suction channel 1, and the air suction efficiency of the air suction channel 1 is effectively enhanced by filling the carbon molecular sieves, wherein the filling proportion of the carbon molecular sieves in the foam silicon carbide materials on the air suction channel 1 is gradually increased along the direction from the air inlet 11 to the air outlet 12, so that the directional adsorption of the thin air is finally realized, and the nitrogen and oxygen storage solid solution materials in the air suction channel 1 can conveniently store the air; meanwhile, a reinforced coating made of a C-SiC nano composite material is arranged on the position, located at the air inlet 11, of the air suction channel 1, so that the collision protection performance of the air suction channel 1 on high-speed particles is effectively enhanced.
In this embodiment, the portion of the gas inlet channel 1 made of the solid solution material for storing nitrogen and oxygen on the gas inlet channel 1 occupies 1/3-1/2 of the total length of the gas inlet channel 1, and the solid solution material for storing nitrogen and oxygen of the portion of the gas inlet channel 1 is specifically Ce0.Zr0.O · xBaO, so that the compressed lean air can be stored both in the suction channel 1 and in the solid solution material of the suction channel 1 itself.
The cathode body 4 and the anode body 5 are both hollow columnar structures, specifically, the cathode body 4 is a hollow columnar structure made of a tungsten metal material, the anode body 5 is a hollow expansion ring structure made of a titanium metal material, the cathode body 4 is positioned in a cavity of the anode body 5, so that an annular cavity 81 is enclosed between the outer wall of the cathode body 4 and the inner wall of the anode body 5, and the annular cavity 81 and the residual cavity in the anode body form a discharge cavity together, wherein the residual cavity in the anode body refers to the residual part of the cavity of the anode body after the part occupied by the annular cavity 81 and the cathode body 4 is removed; preferably, the axis of the cathode body 4 and the axis of the anode body 5 are parallel to each other; further, the axis of the cathode body 4 coincides with the axis of the anode body 5, wherein specifically: the length of the cathode body 4 is 1/3 of the length of the anode body 5, one end of the cathode body 4 and one end of the anode body 5 are located on the same cross section, and the other end of the cathode body 4 is located in the cavity of the anode body 5. Air compressed by the air suction channel 1 and sucked into the thruster enters the discharge cavity to be ionized into plasma and the plasma is accelerated and sprayed out under the action of an electric field; the power supply 7 is also positioned in the cavity 83 of the anode body, the cathode body 4 is electrically connected with the cathode of the power supply 7, the anode body 5 is electrically connected with the anode of the power supply 7, and the power supply 7 plays a role in supplying power to the electric field generated in the discharge cavity and also plays a role in igniting air ionization in the electric field. Meanwhile, the magnetic coil 6 is wound on the outer wall of the anode body 5, an accelerating magnetic field along the axial direction of the anode body 5 is generated in the discharge cavity after the magnetic coil 6 is electrified, and the stable accelerating effect is achieved on plasma generated by air discharge by combining an electric field, so that thrust is obtained, wherein the ionization rate and the accelerating efficiency can be effectively increased by the cathode body 4 and the anode body 5 which are of hollow structures. In the process, the power supply 7 is adjusted to output voltage of the cathode body 4 and the anode body 5 so as to adjust the electric field, or the current in the magnetic induction line is adjusted so as to adjust the accelerating magnetic field, so that the effect of adjusting the thrust can be achieved.
The flow limiting valve 2 is positioned between the air suction channel 1 and the discharge cavity, the air inlet end of the flow limiting valve 2 is communicated with the air outlet 12, and the air outlet end of the flow limiting valve 2 is communicated with the discharge cavity through the flow divider 3 and used for controlling the mass flow of the compressed air mass entering the discharge cavity. Referring to fig. 2, one end of the flow divider 3 is provided with a flow dividing inlet 31, the other end of the flow divider 3 is provided with a first flow dividing outlet 32 and a second flow dividing outlet 33 surrounding the first flow dividing outlet 32, and both the first flow dividing outlet 32 and the second flow dividing outlet 33 are communicated with the flow dividing inlet 31 through a flow dividing structure in the flow divider 3; the split inlet 31 is communicated with the air outlet end of the flow limiting valve 2, the first split outlet 32 is communicated with the cavity 82 of the cathode body, the second split outlet 33 is communicated with the annular cavity 81, arrows in fig. 2 indicate the air flowing direction, and air is introduced into the discharge cavity 81 in a separating manner through the first split outlet 32 and the second split outlet 33, so that air can be distributed in the discharge cavity 81 more uniformly, and ionization and acceleration efficiency is improved.
Referring to fig. 3, the flow limiting valve 2 in this embodiment is a valve disclosed in patent CN 105840904B, and the whole of the valve is in an annular structure, and is composed of a flow limiting valve air inlet 20, a spiral driving coil 21, a coil skeleton 22, a truncated cone-shaped reed 23, a sealing gasket 24, a limiting block 25, a main valve body 26, a valve cavity 27, and an O-ring 28, and the mass flow of a compressed air mass entering the discharge cavity is controlled to adjust the thrust. In the flow restriction valve 2, the spiral drive coil 21 and the truncated cone spring 23 constitute a valve drive mechanism, and the truncated cone spring 23 is an operation actuator. When a pulse current flows through the helical drive coil 21, the transient magnetic field generated therefrom induces a circular current in the truncated cone-shaped reed 23 in the opposite direction to the flow direction thereof, according to the principle of electromagnetic induction. The induced current interacts with the radial component of the magnetic field generated by the coil current to generate an axial lorentz force in the truncated cone-shaped reed 23, when the axial lorentz force is far greater than the initial elastic force of the truncated cone-shaped reed 23, the outer edge of the truncated cone-shaped reed 23 is quickly lifted under the action of the axial lorentz force, and when the axial lorentz force is smaller than the initial elastic force of the reed, the truncated cone-shaped reed 23 is reversed. Therefore, in the working process of the flow limiting valve 2, the opening size of the electromagnetic force driving valve port is controlled by adjusting the current of the spiral driving coil 21, the mass flow of the compressed air mass entering the discharge cavity can be accurately controlled, the variable thrust function of the thruster is finally realized, and the variable thrust control valve has the characteristics of quick response, long service life, strong interference resistance and high durability.
Because the air in the space is thin, although the air is simply compressed by the air suction channel 1, the air in the discharge cavity still has certain difficulty in discharging and igniting. Therefore, the present embodiment designs the power supply 7 compatible with the ignition circuit 71 and the main discharge circuit 72 as shown in fig. 4 for the lean atmosphere ignition feature. The power supply 7 not only can effectively improve the ignition success rate and promote the ionization rate, but also has the function of controlling the discharge power and adjusting the thrust change. The power supply 7 mainly includes an ignition circuit 71 and a main discharge circuit 72. The ignition circuit 71 is electrically connected with the cathode body 4 and the anode body 5 for igniting the air in the discharge cavity; and a main discharge circuit 72 electrically connected to the cathode body 4 and the anode body 5 for providing an electric field to the discharge chamber.
Referring to fig. 4, the ignition circuit 71 includes: a first charging power supply 711, a first capacitor 712, and a first silicon controlled rectifier 713. The first charging power supply 711 of the ignition circuit 71 is a low-power high-voltage charging power supply, the first capacitor 712 is a low-capacity capacitor, and the first charging power supply 711 is used for charging the low-capacity high-voltage capacitor; the first silicon controlled rectifier 713 serves to control conduction between the ignition circuit 71 and the thruster while preventing a reverse current from flowing into the ignition circuit 71. The first capacitor 712 and the first silicon controlled rectifier 713 are both provided with a first terminal and a second terminal.
The specific structure of the ignition circuit 71 is: a first terminal of the first capacitor 712 is coupled to an anode of the first charging power supply 711, a second terminal of the first capacitor 712 is coupled to a cathode of the first charging power supply 711, and the cathode body 4 is coupled to a second terminal of the first capacitor 712 and a cathode of the first charging power supply 711; a first terminal of the first silicon controlled rectifier 713 is coupled to a first terminal of the first capacitor 712, to the anode of the first charging source 711, and a second terminal of the first silicon controlled rectifier 713 is coupled to the anode body 5.
The main discharge circuit 72 includes: a second charging power source 721, n second capacitors C1～CnN inductors L1～LnA diode 722, a second silicon controlled rectifier 723, a protective resistor 724 and a relay 25, wherein n is a natural number greater than 1. The second charging power source 721 of the main discharging circuit 72 is a high-power large-current charging power source, the second capacitor is a large-capacity capacitor, and the second charging power source 721 is used for charging the large-capacity capacitor; the matching combination of the second capacitor and the inductor provides a required discharge waveform for the thruster; the diode 722 is used for preventing the high-voltage charging power supply 7 of the ignition circuit 71 from charging the capacitor of the main discharge circuit 72; the second silicon controlled rectifier 723 is used for controlling conduction between the main discharge circuit 72 and the thruster, and simultaneously preventing reverse current from flowing into the main discharge circuit 72; the protective resistor 724 is used for releasing the electric energy stored in the main discharge circuit 72 through the protective resistor 724 under the condition that the thruster fails to discharge; the relay 25 is used for controlling the connection and disconnection of the protective resistor 724 and the main discharge circuit 72. The matching resistor 73 in fig. 4 is used to perform load matching between the discharge circuit impedance and the thruster discharge impedance to improve the thruster energy use efficiency. The second silicon controlled rectifier 723, the protection resistor 724, the relay 25 and each second capacitor are provided with a first terminal and a second terminal.
The specific structure of the main discharge circuit 72 is: first and second capacitors C1First terminal of andthe anode of the second charging source 721 is coupled to the ith second capacitor CiAnd the (i + 1) th second capacitor Ci+1Through the ith inductor LiCoupled, each second capacitor C1～CnAre coupled to the cathode of a second charging power supply 721, wherein i is 1. ltoreq. i<n; the nth second capacitor CnAlso through the nth inductance LnCoupled to the input of diode 722, the output of diode 722 is coupled to anode body 5 through matching resistor 73; the first terminal of the second silicon controlled rectifier 723 is respectively connected with the cathode of the second charging power source 721 and each second capacitor C1～CnA second terminal of the second silicon controlled rectifier 723 is coupled to the cathode body 4; first and second capacitors C1Is further coupled to a first terminal of a protection resistor 724, a second terminal of the protection resistor 724 is coupled to a first terminal of the relay 25, a second capacitor C2Is coupled to a second terminal of the relay 25 and is grounded.
The working process of the embodiment is as follows: the air suction channel 1 is positioned at the head end of the thruster, collects air along with the forward movement of the ultra-low orbit satellite, and captures, compresses and stores rarefied air at the tail part of the air suction channel 1; the flow limiting valve 2 controls the flow of air entering the discharge cavity from the air suction channel 1, so that the effect of controlling the ionized air amount is achieved, the size of the generated thrust is changed, and the purpose of variable thrust is achieved; the flow divider 3 divides the air flowing out of the flow limiting valve 2, the air enters the cavity 82 of the cathode body and the cavity 83 of the anode body simultaneously in an anode and cathode simultaneous air inlet mode, and the air inlet ratio of the cavity of the anode body 5 and the cavity of the cathode body 4 under different working conditions can be realized by utilizing the structural size design of the first flow dividing outlet 32 and the second flow dividing outlet 33; the cathode body 4, the anode body 5 and the power supply 7 form a discharge cavity for ionizing air mass to form plasma; the power supply 7 can control the discharge power, so that the thrust can be further controlled, and the dual control of the current limiting valve 2 and the power supply 7 effectively improves the control precision of the variable thrust; under the action of the accelerating magnetic field of the magnetic coil 6 and the electric field of the discharge cavity, the plasma is accelerated to be sprayed out to obtain thrust.
The foregoing contains a description of the preferred embodiments of the invention in order to provide a more detailed description of the technical features of the invention, and is not intended to limit the invention to the specific forms disclosed in the embodiments, and other modifications and variations, which are within the spirit of the invention, are also protected by this patent. The subject matter of the present disclosure is defined by the claims, not by the detailed description of the embodiments.
Claims (10)
1. Ultra-low rail variable thrust air suction type magnetic plasma thruster is characterized by comprising:
the air suction channel is positioned at the head end of the thruster, is provided with an air inlet and an air outlet and is used for compressing the thin air and sucking the air into the thruster;
the discharge cavity is positioned at the tail end of the thruster, is communicated with the air outlet and consists of a cathode body, an anode body and a power supply, wherein the cathode body and the anode body are electrically connected with the power supply and are used for ionizing compressed thin air into plasma and accelerating the plasma to be sprayed out under the action of an electric field, and an accelerating magnetic field is arranged in the discharge cavity;
and the flow limiting valve is positioned between the air suction channel and the discharge cavity, the air inlet end of the flow limiting valve is communicated with the air outlet, and the air outlet end of the flow limiting valve is communicated with the discharge cavity and used for controlling the mass flow of the compressed air mass entering the discharge cavity.
2. The ultra-low rail variable thrust air-breathing magnetic plasma thruster of claim 1 further comprising a diverter located between the flow-limiting valve and the discharge chamber;
the cathode body and the anode body are both in hollow columnar structures, the cathode body is positioned in a cavity of the anode body, an annular cavity is defined between the outer wall of the cathode body and the inner wall of the anode body, the discharge cavity is composed of the annular cavity and the residual cavity in the anode body, a magnetic coil is arranged on the outer wall of the anode body in a surrounding mode, and the accelerating magnetic field is generated by the magnetic coil;
one end of the flow divider is provided with a flow dividing inlet, the other end of the flow divider is provided with a first flow dividing outlet and a second flow dividing outlet surrounding the first flow dividing outlet, and the first flow dividing outlet and the second flow dividing outlet are both communicated with the flow dividing inlet through a flow dividing structure in the flow divider;
the split-flow inlet is communicated with the air outlet end of the flow limiting valve, the first split-flow outlet is communicated with the cavity of the cathode body, and the second split-flow outlet is communicated with the annular cavity.
3. The ultra-low rail variable thrust air-breathing magnetic plasma thruster of claim 1, wherein the power supply comprises:
the ignition circuit is electrically connected with the cathode body and the anode body and is used for igniting the air in the discharge cavity;
and the main discharge circuit is electrically connected with the cathode body and the anode body and is used for providing an electric field for the discharge cavity.
4. The ultra-low rail variable thrust air-breathing magnetic plasma thruster of claim 3, wherein the ignition circuit comprises:
the first charging power supply is used for charging the first capacitor;
a first capacitor including a first terminal and a second terminal, the first terminal of the first capacitor being coupled to an anode of the first charging source, the second terminal of the first capacitor being coupled to a cathode of the first charging source, the cathode body being coupled to the second terminal of the first capacitor and the cathode of the first charging source;
and the first silicon controlled rectifier comprises a first terminal and a second terminal, the first terminal of the first silicon controlled rectifier is coupled with the first terminal of the first capacitor and the anode of the first charging power supply, and the second terminal of the first silicon controlled rectifier is coupled with the anode body.
5. The ultra-low rail variable thrust air-breathing magnetic plasma thruster of claim 3, wherein the main discharge circuit comprises a second charging power supply, a second silicon controlled rectifier, a diode, and a protectorProtection resistor, relay and n second capacitors C1～CnAnd n inductors L1～LnWherein n is a natural number greater than 1;
the second silicon controlled rectifier, the protective resistor, the relay and each second capacitor comprise a first terminal and a second terminal;
first and second capacitors C1Is coupled to the anode of a second charging source, an ith second capacitor CiAnd the (i + 1) th second capacitor Ci+1Is coupled via an ith inductance Li, each second capacitance C1～CnAre coupled with the cathode of a second charging power supply, wherein i is more than or equal to 1<n；
The nth second capacitor CnAlso through the nth inductance LnThe output end of the diode is coupled with the anode body through the matching resistor;
the first terminal of the second silicon controlled rectifier is respectively connected with the cathode of the second charging power supply and each second capacitor C1～CnA second terminal of the second silicon controlled rectifier is coupled with the cathode body;
first and second capacitors C1Is further coupled to a first terminal of a protection resistor, a second terminal of said protection resistor being coupled to a first terminal of the relay, a second capacitor C2Is coupled to the second terminal of the relay and is grounded.
6. The ultra-low rail variable thrust air-breathing magnetic plasma thruster according to any one of claims 1 to 5, wherein the air suction channel is a trumpet-shaped structure, the air inlet is positioned at the large end of the trumpet-shaped structure, and the air outlet is positioned at the small end of the trumpet-shaped structure.
7. The ultra-low rail variable thrust air-breathing magnetic plasma thruster according to any one of claims 1 to 5, wherein a part of the air suction channel on the air suction channel near the air outlet is made of nitrogen and oxygen storage solid solution material, the rest part of the air suction channel is made of foam silicon carbide material, and the foam silicon carbide material on the air suction channel is filled with carbon molecular sieve.
8. The ultra-low rail variable thrust air-breathing magnetic plasma thruster of claim 7, wherein the filling proportion of the carbon molecular sieve in the foam silicon carbide material on the air suction channel is gradually increased along the direction from the air inlet to the air outlet.
9. The ultra-low rail variable thrust air-breathing magnetic plasma thruster of any one of claims 1 to 5, wherein the air suction channel is provided with a reinforcing coating at the position of the air inlet.
10. The ultra-low rail variable thrust air breathing magnetic plasma thruster of any one of claims 1 to 5, wherein the cathode body is made of tungsten metal material and the anode body is made of titanium metal material.
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| CN201920988094.6U CN211397783U (en) | 2019-06-28 | 2019-06-28 | Ultra-low rail variable thrust air suction type magnetic plasma thruster |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110159501A (en) * | 2019-06-28 | 2019-08-23 | 中国人民解放军国防科技大学 | Ultra-low rail variable thrust air suction type magnetic plasma thruster |
| CN112224450A (en) * | 2020-10-21 | 2021-01-15 | 中国人民解放军国防科技大学 | Low-voltage electrospray emission device |
-
2019
- 2019-06-28 CN CN201920988094.6U patent/CN211397783U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110159501A (en) * | 2019-06-28 | 2019-08-23 | 中国人民解放军国防科技大学 | Ultra-low rail variable thrust air suction type magnetic plasma thruster |
| CN110159501B (en) * | 2019-06-28 | 2024-03-19 | 中国人民解放军国防科技大学 | Ultra-low rail variable thrust air suction type magnetic plasma thruster |
| CN112224450A (en) * | 2020-10-21 | 2021-01-15 | 中国人民解放军国防科技大学 | Low-voltage electrospray emission device |
| CN112224450B (en) * | 2020-10-21 | 2022-04-12 | 中国人民解放军国防科技大学 | Low-voltage electrospray emission device |
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