CN110159501B - 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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- 230000005684 electric field Effects 0.000 claims abstract description 13
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- 239000003990 capacitor Substances 0.000 claims description 54
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 claims description 23
- 229910052710 silicon Inorganic materials 0.000 claims description 23
- 239000010703 silicon Substances 0.000 claims description 23
- 239000000463 material Substances 0.000 claims description 16
- 238000005247 gettering Methods 0.000 claims description 13
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 12
- 229910010271 silicon carbide Inorganic materials 0.000 claims description 10
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 claims description 9
- 239000006260 foam Substances 0.000 claims description 8
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 7
- 229910052799 carbon Inorganic materials 0.000 claims description 7
- 239000002808 molecular sieve Substances 0.000 claims description 7
- URGAHOPLAPQHLN-UHFFFAOYSA-N sodium aluminosilicate Chemical compound [Na+].[Al+3].[O-][Si]([O-])=O.[O-][Si]([O-])=O URGAHOPLAPQHLN-UHFFFAOYSA-N 0.000 claims description 7
- 239000006104 solid solution Substances 0.000 claims description 7
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 6
- 239000007769 metal material Substances 0.000 claims description 6
- 229910052757 nitrogen Inorganic materials 0.000 claims description 6
- 239000001301 oxygen Substances 0.000 claims description 6
- 229910052760 oxygen Inorganic materials 0.000 claims description 6
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims description 3
- 239000011248 coating agent Substances 0.000 claims description 3
- 238000000576 coating method Methods 0.000 claims description 3
- 239000010936 titanium Substances 0.000 claims description 3
- 229910052719 titanium Inorganic materials 0.000 claims description 3
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims description 3
- 229910052721 tungsten Inorganic materials 0.000 claims description 3
- 239000010937 tungsten Substances 0.000 claims description 3
- 230000003014 reinforcing effect Effects 0.000 claims description 2
- 239000007789 gas Substances 0.000 claims 5
- 210000002381 plasma Anatomy 0.000 abstract description 20
- 238000000034 method Methods 0.000 abstract description 7
- 230000000694 effects Effects 0.000 abstract description 6
- 230000008569 process Effects 0.000 abstract description 5
- 238000005507 spraying Methods 0.000 abstract description 4
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- 235000014676 Phragmites communis Nutrition 0.000 description 9
- 238000007599 discharging Methods 0.000 description 4
- 238000012544 monitoring process Methods 0.000 description 3
- 239000003380 propellant Substances 0.000 description 3
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- 230000009286 beneficial effect Effects 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H1/00—Using plasma to produce a reactive propulsive thrust
- F03H1/0081—Electromagnetic plasma thrusters
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
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- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Plasma Technology (AREA)
Abstract
The invention provides an ultralow-rail variable-thrust air suction type magnetic plasma thruster, which comprises an air suction channel, a magnetic control device and a magnetic control device, wherein the air suction channel is provided with an air inlet and an air outlet and is used for compressing lean air and sucking the lean 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, wherein the cathode body and the anode body are electrically connected with the power supply and are used for ionizing compressed lean air into plasma and accelerating and spraying the plasma under the action of an electric field, and a magnetic field is arranged in the discharge cavity so as to further improve the effect of accelerating and spraying the plasma; the air outlet end of the flow limiting valve is communicated with the discharge cavity and is used for controlling the mass flow of the compressed air mass entering the discharge cavity. The processes of capturing, storing, controlling, ionizing, accelerating and the like of the thin air in the environment by the thruster are realized, so that the thrust is stably generated. The invention is applied to the fields of aerospace technology and plasmas.
Description
Technical Field
The invention relates to the field of aerospace technology and plasmas, in particular to an ultralow-orbit variable-thrust air suction type magnetic plasma thruster.
Background
With the increasing 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 capacity of the satellites. Compared with other orbits, the satellite runs on the ultra-low orbit, the method can remarkably reduce the emission cost of the satellite, improves the navigation positioning precision and response speed of the satellite, and has wide application prospects in the fields of weather prediction, two-pole ice coverage monitoring, fire monitoring, agricultural monitoring, electronic communication, positioning navigation, remote sensing and the like. However, the special and complex environment of the ultra-low orbit space makes the satellite stay permanently, which is subject to the problems of short service life, difficult propellant supply, high on-orbit maintenance cost and the like, so that the development of the space ultra-low orbit satellite is severely restricted.
The pursuit of stable performance, long life, light weight and low cost propulsion systems is the leading research focus in the current aerospace field. The novel propulsion scheme is developed by using substances existing in the space environment as much as possible, so that the related cost of the satellite can be effectively reduced, the service life is prolonged, and the novel scheme is provided for the orbit control of the ultra-low orbit satellite. However, related researches are few, accurate and variable thrust cannot be realized, and the power requirements of multiple flight missions of the ultra-low orbit satellite cannot be met.
Disclosure of Invention
Aiming at the prior art, the invention aims to provide an ultralow-rail variable-thrust air suction type magnetic plasma thruster.
The technical scheme adopted by the method is as follows:
an ultra-low track variable thrust gettering type magnetic plasma thruster comprising:
the air suction channel is positioned at the head end of the thruster and is provided with an air inlet and an air outlet for compressing the lean air and sucking the lean air into the thruster;
the discharge cavity is positioned at the tail end of the thruster and 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 lean air into plasma and accelerating and spraying the plasma 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 and spraying the plasma;
the air outlet end of the flow limiting valve is communicated with the discharge cavity and is used for controlling the mass flow of the compressed air mass entering the discharge cavity.
Further preferably, the discharge device further comprises a shunt, wherein the shunt is positioned between the current limiting valve and the discharge cavity;
the cathode body and the anode body are of hollow columnar structures, the cathode body is positioned in a cavity of the anode body, an annular cavity is formed between the outer wall of the cathode body and the inner wall of the anode body, the discharge cavity consists of the annular cavity and the rest cavity in the anode body, a magnetic coil is wound on the outer wall of the anode body, and the accelerating magnetic field is generated by the magnetic coil;
one end of the diverter is provided with a diverter inlet, the other end of the diverter is provided with a first diverter outlet and a second diverter outlet which surrounds the first diverter outlet, and the first diverter outlet and the second diverter outlet are communicated with the diverter inlet through diverter structures in the diverter;
the split inlet is communicated with the air outlet end of the flow limiting valve, the first split outlet is communicated with the cavity of the cathode body, and the second split 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 performing ignition operation 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;
the first capacitor comprises a first terminal and a second terminal, the first terminal of the first capacitor is coupled with the anode of the first charging power supply, the second terminal of the first capacitor is coupled with the cathode of the first charging power supply, and the cathode body is coupled with the second terminal of the first capacitor and the cathode of the first charging power supply;
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 comprises a second charging power supply and a second charging power supplySilicon controlled rectifier, diode, protection resistor, relay, n second capacitors C 1 ～C n And n inductances L 1 ～L n Wherein n is a natural number greater than 1;
the second silicon controlled rectifiers, the protection resistor, the relay and each second capacitor comprise a first terminal and a second terminal;
first and second capacitors C 1 An ith second capacitor C coupled to the anode of the second charging source i And (i+1th) second capacitor C i+1 Is coupled through an ith inductance Li, each second capacitance C 1 ～C n Is coupled to the cathode of the second charging source, wherein 1.ltoreq.i<n；
Nth second capacitor C n Also through the nth inductance L n The output end of the diode 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 C 1 ～C n A second terminal of the second silicon controlled rectifier is coupled to the cathode body;
first and second capacitors C 1 The first terminal of the protection resistor is also coupled with the first terminal of the relay, the second terminal of the protection resistor is coupled with the second terminal of the relay, the second capacitor C 2 Is coupled to the second terminal of the relay and is grounded.
Further preferably, the air suction channel is in a horn-shaped structure, the air inlet is positioned at the large end of the horn-shaped structure, and the air outlet is positioned at the small end of the horn-shaped structure.
Further preferably, a part of the air suction channels close to the air outlet are made of nitrogen storage and oxygen storage solid solution materials, the rest of the air suction channels are made of foam silicon carbide materials, and carbon molecular sieves are filled in the foam silicon carbide materials on the air suction channels.
Further preferably, 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.
Further preferably, the air intake channel is provided with a reinforcing coating at a position of the air intake.
Further preferably, the cathode body is made of tungsten metal material, and the anode body is made of titanium metal material.
The beneficial technical effects of the invention are as follows:
1. the invention has simple structure, generates thrust by ionizing and accelerating compressed lean air, does not need to carry propellant, not only can avoid the limitation of propellant exhaustion on the service life of the thruster, but also can omit the complex thruster supply device and ground assembly, can effectively reduce the overall weight and cost of the thruster, and further improves the performance.
2. According to the invention, through absorbing, compressing and storing the thin air, the flow control of the compressed air entering the discharge cavity is realized by utilizing the flow limiting valve, meanwhile, the discharge power of the thin air in the discharge cavity is controlled by utilizing the power supply, the accurate control of the thrust can be effectively realized, and the requirements of different tasks of a satellite are effectively met.
3. According to the invention, the accelerating magnetic field is arranged in the discharge cavity, and the electric field generated between the anode body and the cathode body is combined to play a stable accelerating effect on plasmas generated by air discharge, so that thrust is obtained.
Drawings
Fig. 1 is a sectional view of a thruster in the present embodiment;
FIG. 2 is a schematic diagram of the shunt process of the shunt in this embodiment;
FIG. 3 is a schematic view of the structure of the restrictor valve in the present embodiment;
fig. 4 is a schematic circuit diagram of the power supply in the present embodiment.
Detailed Description
The present invention will be further described in detail below with reference to specific embodiments in order to make the objects, technical solutions and advantages of the present disclosure more apparent, and in accordance with the accompanying drawings. In the drawings or the description, the non-description and a part of english abbreviations are known to those skilled in the art. Some specific parameters given in this example are given by way of example only, and the values may be changed to appropriate values accordingly in different implementations.
The ultra-low track variable thrust air suction type 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 the following parts are specifically:
the air suction channel 1 is in 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, wherein 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 lean air is effectively realized, and the volume density of incoming air is increased; the part of the air suction channel 1, which is close to the air outlet 12, on the air suction channel 1 is made of nitrogen and oxygen storage solid solution materials, the rest part 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 oriented adsorption of thin air is finally realized, and the storage of the nitrogen and oxygen storage solid solution materials in the air suction channel 1 is facilitated; meanwhile, the reinforced coating made of the C-SiC nanocomposite is arranged on 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 the embodiment, part of the air intake passage 1 made of the nitrogen and oxygen storage solid solution material on the air intake passage 1 accounts for 1/3 to 1/2 of the total length of the air intake passage 1, and the nitrogen and oxygen storage solid solution material of the part of the air intake passage 1 is specifically Ce 0. Zr 0. O.xBaO allows the compressed lean air to be stored in both the intake duct 1 and in the solid solution material of the intake duct 1 itself.
The cathode body 4 and the anode body 5 are hollow columnar structures, specifically, the cathode body 4 is a hollow columnar structure made of tungsten metal material, the anode body 5 is a hollow expansion ring structure made of titanium metal material, the cathode body 4 is positioned in a cavity of the anode body 5, an annular cavity 81 is formed between the outer wall of the cathode body 4 and the inner wall of the anode body 5 in a surrounding manner, 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 annular cavity 81 and the part occupied by the cathode body 4 are 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 in particular: 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 positioned on the same cross section, and the other end of the cathode body 4 is positioned in the cavity of the anode body 5. Air compressed and sucked into the thruster through the air suction channel 1 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 located 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 energy to the electric field generated in the discharge cavity and also plays a role in igniting air ionization in the electric field. Meanwhile, the outer wall of the anode body 5 is surrounded with a magnetic coil 6, 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 plasmas generated by air discharge by combining an electric field, so that thrust is obtained, and the ionization rate and the accelerating efficiency of the cathode body 4 and the anode body 5 with hollow structures can be effectively increased. In the process, the power supply 7 is adjusted to adjust the output voltage of the cathode body 4 and the anode body 5 so as to play a role in adjusting an electric field, or adjust the current in the magnetic induction line so as to play a role in adjusting an accelerating magnetic field, so that the thrust can be adjusted.
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 is used for controlling the mass flow of compressed air clusters entering the discharge cavity. Referring to fig. 2, one end of the diverter 3 is provided with a diverter inlet 31, the other end of the diverter 3 is provided with a first diverter outlet 32 and a second diverter outlet 33 surrounding the first diverter outlet 32, and the first diverter outlet 32 and the second diverter outlet 33 are both communicated with the diverter inlet 31 through a diverter structure in the diverter 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 are air flow directions, and air clusters are separated from the first split outlet 32 and the second split outlet 33 and introduced into the discharge cavity 81, so that air can be more uniformly distributed in the discharge cavity 81, and ionization and acceleration efficiency is improved.
Referring to fig. 3, the restrictor valve 2 in this embodiment adopts a valve disclosed in patent CN 105840904B, and has an annular structure as a whole, and is composed of a restrictor valve air inlet 20, a spiral driving coil 21, a coil frame 22, a truncated cone-shaped reed 23, a sealing gasket 24, a stopper 25, a main valve body 26, a valve cavity 27 and an O-ring 28, and controls the mass flow of compressed air mass entering a discharge cavity so as to adjust the thrust. In this restrictor valve 2, the spiral drive coil 21 and the truncated cone-shaped reed 23 constitute a valve drive mechanism, and the truncated cone-shaped reed 23 is an operation executing member. When a pulse current flows through the helical drive coil 21, a transient magnetic field generated by it induces a circular current in the truncated conical reed 23 in a direction opposite to the flow direction thereof, according to the principle of electromagnetic induction. The interaction of the induced current with the radial component of the magnetic field generated by the coil current will generate an axial lorentz force in the truncated conical reed 23, when the axial lorentz force is much greater than the initial elastic force of the truncated conical reed 23, the outer edge of the truncated conical reed 23 will rapidly rise under the action of the axial lorentz force, and when the axial lorentz force is less than the initial elastic force of the reed, the truncated conical reed 23 will reverse. 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 size of the spiral driving coil 21, the mass flow of the compressed air mass entering the discharge cavity can be accurately controlled, and finally the function of variable thrust of the thruster is realized.
Because the air in the space is thinner, the air in the discharge cavity is still difficult to discharge and ignite in spite of the simple compression of the air by the air suction channel 1. 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 to regulate 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 and is used for performing ignition operation in the discharge cavity; a main discharge circuit 72 electrically connected to the cathode body 4 and the anode body 5 for supplying an electric field to the discharge chamber.
Referring to fig. 4, wherein the ignition circuit 71 includes: a first charging source 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 configured to charge the low-capacity high-voltage capacitor; the first silicon controlled rectifier 713 is used to control conduction between the ignition circuit 71 and the thruster while preventing reverse current from flowing into the ignition circuit 71. The first capacitor 712 and the first silicon controlled rectifier 713 are respectively 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 the anode of the first charging power supply 711, a second terminal of the first capacitor 712 is coupled to the cathode of the first charging power supply 711, and the cathode body 4 is coupled to the second terminal of the first capacitor 712 and the 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, the anode of the first charging power 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 C 1 ～C n N inductances L 1 ～L n A diode 722, a second silicon controlled rectifier 723, a protection resistor 724, and a relay 25, wherein n is a natural number greater than 1. The second charging power 721 of the main discharging circuit 72 is a high-power high-current charging power, the second capacitor is a high-capacity capacitor, and the second charging power 721 is used for charging the high-capacity capacitor; the matching combination of the second capacitor and the inductor provides a required discharge waveform for the thruster; two (II)The pole pipe 722 is used for preventing the high-voltage charging power supply 7 of the ignition circuit 71 from charging the capacitor of the main discharging circuit 72; the second silicon controlled rectifier 723 is used to control conduction between the main discharge circuit 72 and the thruster while preventing reverse current from flowing into the main discharge circuit 72; the protection resistor 724 is used for releasing the electric energy stored in the main discharging circuit 72 through the protection resistor 724 in case of a discharge failure of the thruster; the relay 25 is used to control the communication and disconnection of the protection resistor 724 with the main discharge circuit 72. The matching resistor 73 in fig. 4 is used to load match between the discharge circuit impedance and the thruster discharge impedance to improve the thruster energy utilization 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 C 1 An i-th second capacitor C coupled to the anode of the second charging power supply 721 i And (i+1th) second capacitor C i+1 Through the ith inductance L i Coupling, each second capacitor C 1 ～C n Is coupled to the cathode of the second charging source 721, wherein 1.ltoreq.i<n; nth second capacitor C n Also through the nth inductance L n Coupled 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 supply 721 and each second capacitor C 1 ～C n A second terminal of the second silicon controlled rectifier 723 is coupled to the cathode body 4; first and second capacitors C 1 Also coupled to the first terminal of protection resistor 724, the second terminal of protection resistor 724 is coupled to the first terminal of relay 25, the second capacitor C 2 Is coupled to the second terminal of 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 the lean air at the tail 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 as to achieve the effect of controlling the ionized air quantity, further change the thrust generation and realize the purpose of variable thrust; the flow divider 3 divides the air flowing out of the flow limiting valve 2, the air is simultaneously introduced into the cavity 82 of the cathode body and the cavity 83 of the anode body by adopting a mode of simultaneously introducing air into the anode and the cathode, and the requirements of different working conditions on the air inlet ratios of the cavity of the anode body 5 and the cavity of the cathode body 4 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, and the air mass is ionized to form plasma; the power supply 7 can control the discharge power, so that the thrust can be further controlled, and the double control of the current limiting valve 2 and the power supply 7 effectively improves the control precision of the variable thrust; the plasma is accelerated and ejected under the action of the accelerating magnetic field of the magnetic coil 6 and the electric field of the discharge cavity, so that the thrust is obtained.
The above description of the preferred embodiments of the present invention has been included to describe in detail the technical features of the present invention, and is not intended to limit the invention to the specific forms described in the embodiments, and other modifications and variations according to the gist of the present invention are also protected by this patent. The gist of the present disclosure is defined by the claims, not by the specific description of the embodiments.
Claims (8)
1. The utility model provides an ultralow rail variable thrust suction type magnetic plasma thruster which is characterized in that the utility model comprises the following components:
the air suction channel is positioned at the head end of the thruster and is provided with an air inlet and an air outlet for compressing the lean air and sucking the lean air into the thruster;
the discharge cavity is positioned at the tail end of the thruster and 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 lean 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;
the air outlet end of the flow limiting valve is communicated with the discharge cavity and is used for controlling the mass flow of compressed air clusters entering the discharge cavity;
the diverter is positioned between the flow limiting valve and the discharge cavity;
the cathode body and the anode body are of hollow columnar structures, the cathode body is positioned in a cavity of the anode body, an annular cavity is formed between the outer wall of the cathode body and the inner wall of the anode body, the discharge cavity consists of the annular cavity and the rest cavity in the anode body, a magnetic coil is wound on the outer wall of the anode body, and the accelerating magnetic field is generated by the magnetic coil;
one end of the diverter is provided with a diverter inlet, the other end of the diverter is provided with a first diverter outlet and a second diverter outlet which surrounds the first diverter outlet, and the first diverter outlet and the second diverter outlet are communicated with the diverter inlet through diverter structures in the diverter;
the first shunt outlet is communicated with the cavity of the cathode body, and the second shunt outlet is communicated with the annular cavity;
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.
2. The ultra-low track variable thrust gettering magnetic plasma thruster of claim 1, wherein the ignition circuit comprises:
the first charging power supply is used for charging the first capacitor;
the first capacitor comprises a first terminal and a second terminal, the first terminal of the first capacitor is coupled with the anode of the first charging power supply, the second terminal of the first capacitor is coupled with the cathode of the first charging power supply, and the cathode body is coupled with the second terminal of the first capacitor and the cathode of the first charging power supply;
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.
3. The ultra-low track variable thrust gettering type magnetic plasma thruster according to claim 1, wherein the main discharge circuit comprises a second charging power supply, a second silicon controlled rectifier, a diode, a protection resistor, a relay, n second capacitors C 1 ～C n And n inductances L 1 ～L n Wherein n is a natural number greater than 1;
the second silicon controlled rectifiers, the protection resistor, the relay and each second capacitor comprise a first terminal and a second terminal;
first and second capacitors C 1 An ith second capacitor C coupled to the anode of the second charging source i And (i+1th) second capacitor C i+1 Is coupled through an ith inductance Li, each second capacitance C 1 ～C n Is coupled to the cathode of the second charging source, wherein 1.ltoreq.i<n；
Nth second capacitor C n Also through the nth inductance L n The output end of the diode 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 C 1 ～C n A second terminal of the second silicon controlled rectifier is coupled to the cathode body;
first and second capacitors C 1 The first terminal of the protection resistor is also coupled with the first terminal of the relay, the second terminal of the protection resistor is coupled with the second terminal of the relay, the second capacitor C 2 Is coupled to the second terminal of the relay and is grounded.
4. An ultra-low track variable thrust gettering magnetic plasma thruster according to any one of claims 1 to 3, wherein the gettering track is a horn-like structure, the gas inlet is located at the large end of the horn-like structure, and the gas outlet is located at the small end of the horn-like structure.
5. An ultra-low track variable thrust gettering type magnetic plasma thruster according to any one of claims 1 to 3, wherein a part of the gettering channels near the gas outlet port is made of nitrogen and oxygen storage solid solution material, the remaining part of the gettering channels is made of foam silicon carbide material, and carbon molecular sieve is filled in the foam silicon carbide material on the gettering channels.
6. The ultra-low track variable thrust gettering type magnetic plasma thruster of claim 5, wherein the filling ratio of carbon molecular sieve in the foamed silicon carbide material on the gettering tract gradually increases along the direction from the gas inlet to the gas outlet.
7. An ultra-low track variable thrust gettering type magnetic plasma thruster according to any one of claims 1 to 3, wherein the getter channel is provided with a reinforcing coating at the location of the getter inlet.
8. An ultra-low track variable thrust gettering magnetic plasma thruster according to any one of claims 1 to 3, wherein the cathode body is made of tungsten metal material and the anode body is made of titanium metal material.
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| CN110647034B (en) * | 2019-09-04 | 2020-08-14 | 北京航空航天大学 | Neural network control method of pulse plasma thruster |
| CN111486071A (en) * | 2020-04-24 | 2020-08-04 | 北京卫星环境工程研究所 | Air suction type electric propeller |
| CN113062839B (en) * | 2021-04-30 | 2024-06-14 | 中国科学院力学研究所 | Electron beam pre-ionization enhanced air suction device and method for air suction electric pushing technology |
| CN113931818B (en) * | 2021-11-04 | 2024-01-02 | 中国人民解放军战略支援部队航天工程大学 | Device and method for improving ion density in space electric thruster |
| CN114623060A (en) * | 2022-01-28 | 2022-06-14 | 北京控制工程研究所 | Magnetic plasma power thruster cathode and processing method thereof |
| CN114776547B (en) * | 2022-03-28 | 2024-08-02 | 广州大学 | Fuel-free satellite propulsion device and propulsion method |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| JP2013137024A (en) * | 2013-01-30 | 2013-07-11 | Elwing Llc | Thruster, system therefor, and propulsion generating method |
| CN106246487A (en) * | 2016-08-26 | 2016-12-21 | 北京航空航天大学 | A kind of magnetic plasma propeller utilizing additional electromagnetic field energy to convert |
| CN106286179A (en) * | 2016-10-14 | 2017-01-04 | 楚龙飞 | Air suction type ion engine |
| CN106704133A (en) * | 2017-03-09 | 2017-05-24 | 中国工程物理研究院核物理与化学研究所 | Non-trigger type vacuum arc micro thruster using gas storage electrodes |
| CN207048912U (en) * | 2017-07-11 | 2018-02-27 | 中国人民解放军国防科学技术大学 | The multistage discharge circuit for the magnetic plasma propeller supported for laser |
| CN211397783U (en) * | 2019-06-28 | 2020-09-01 | 中国人民解放军国防科技大学 | Ultra-low rail variable thrust air suction type magnetic plasma thruster |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6834492B2 (en) * | 2001-06-21 | 2004-12-28 | Busek Company, Inc. | Air breathing electrically powered hall effect thruster |
| US6808145B2 (en) * | 2002-02-08 | 2004-10-26 | Cu Aerospace | Dual-mode airbreathing propulsion system |
-
2019
- 2019-06-28 CN CN201910571524.9A patent/CN110159501B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| JP2013137024A (en) * | 2013-01-30 | 2013-07-11 | Elwing Llc | Thruster, system therefor, and propulsion generating method |
| CN106246487A (en) * | 2016-08-26 | 2016-12-21 | 北京航空航天大学 | A kind of magnetic plasma propeller utilizing additional electromagnetic field energy to convert |
| CN106286179A (en) * | 2016-10-14 | 2017-01-04 | 楚龙飞 | Air suction type ion engine |
| CN106704133A (en) * | 2017-03-09 | 2017-05-24 | 中国工程物理研究院核物理与化学研究所 | Non-trigger type vacuum arc micro thruster using gas storage electrodes |
| CN207048912U (en) * | 2017-07-11 | 2018-02-27 | 中国人民解放军国防科学技术大学 | The multistage discharge circuit for the magnetic plasma propeller supported for laser |
| CN211397783U (en) * | 2019-06-28 | 2020-09-01 | 中国人民解放军国防科技大学 | Ultra-low rail variable thrust air suction type magnetic plasma thruster |
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