Plasma jet device and method adaptive to aircraft

Abstract

The invention provides a plasma jet device and method adaptive to an aircraft, and relates to the technical field of aircraft auxiliary devices. The device comprises a high-pressure gas module, a plasma generation device, an electromagnetic field regulation and control module, a buffer module and a jet pipe module, a gas output end in the high-pressure gas module is communicated with an input end of the plasma generating device; the output end of the plasma generating device is communicated with the input end of the spiral diversion trench; the output end of the electric field generator is communicated with the input end of the gas mixer; the output end of the gas mixer is communicated with the input end of the jet pipe module; the jet flow pipe module sprays out plasma jet flow conveyed by the gas mixer in different directions by arranging a jet flow pipe. The plasma and the inert gas are subjected to multi-stage combination, the plasma jet is regulated and controlled through the mechanical flow guide structure and the electric field and magnetic field regulation and control mechanism, and finally the stability of the plasma is greatly improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft auxiliary devices, and in particular to a plasma jet device and method adapted for an aircraft. Background Art

[0002] When electromagnetic waves are incident on plasma, they interact with electrons and ions in the plasma; the characteristics of plasma on electromagnetic wave propagation are as follows: when electromagnetic waves are incident on the plasma layer, if their frequency is higher than the cutoff frequency, the electromagnetic waves can penetrate the plasma and continue to propagate, but in this process they will experience energy attenuation caused by the plasma. On the contrary, if the frequency of the electromagnetic wave is lower than the cutoff frequency, it usually cannot penetrate the plasma layer, but will be totally reflected on its surface. At this time, the plasma acts as an electromagnetic wave reflector, interfering with the electromagnetic waves, including possible scattering effects. Radar stealth or jamming devices can be designed using the frequency cutoff characteristics of plasma. When a layer of plasma is covered on the surface of an aircraft or device, it can absorb or reflect the electromagnetic waves emitted by the radar, thereby achieving the effect of radar stealth or jamming detection.

[0003] The existing plasma radar stealth technology solution is mainly to set up a plasma generator on the surface of the aircraft and "wrap" the entire device or aircraft in the generated plasma cloud. At present, such equipment has the following problems: (1) high energy consumption, it is difficult to supply energy to the aircraft for a long time; (2) the current technical level is difficult to ensure that the plasma layer maintains a stable stealth / interference effect for a long time; (3) poor system stability, the plasma generator array covering the surface of the device or aircraft is easily disturbed by airflow or foreign objects, resulting in decreased stability and disability; (4) high cost, difficult to apply on a large scale.

[0004] In view of the above problems, the present invention aims to provide a new type of plasma jet device equipped with an aircraft, so as to realize a plasma radar detection and interference device with low energy consumption, low cost and high stability. Summary of the invention

[0005] In order to address the deficiencies in the background technology, the present invention provides a plasma jet device and method adapted for aircraft. The device adopts dielectric barrier discharge technology to combine plasma and inert gas in multiple stages, and then controls the plasma jet through a mechanical guide structure and an electric field and magnetic field control mechanism, thereby greatly improving the plasma stability. Plasma clouds with different shapes and different cutoff frequencies are achieved by ejecting plasma jets through multiple jet pipes, which can simulate the RCS (radar reflection area) characteristics of different aircraft and achieve radar stealth and interference effects. The entire device only requires one set of plasma generator, which greatly reduces the equipment manufacturing and maintenance costs.

[0006] The first object of the present invention is to provide a plasma jet device adapted for an aircraft, comprising a high-pressure gas module, a plasma generating device, an electromagnetic field control module, a buffer module and a jet pipe module; The electromagnetic field control module includes a spiral guide groove, a magnetic field generator and an electric field generator which are connected in sequence; The buffer module includes a buffer gas cylinder and a gas mixer, and the buffer gas cylinder is connected to the gas mixer through a pipe body; The gas output end of the high-pressure gas module is connected to the input end of the plasma generating device; The output end of the plasma generating device is connected to the input end of the spiral guide groove; The output end of the electric field generator is connected to the input end of the gas mixer; The output end of the gas mixer is in communication with the input end of the jet pipe module; The jet pipe module is provided with a jet pipe to eject the plasma jet delivered by the gas mixer in different directions.

[0007] Preferably, the plasma generating device comprises: A first insulating pipe, whose input end is connected to the gas output end of the high-pressure gas module through a second insulating pipe, and whose output end is connected to the input end of the spiral guide groove; A high-voltage electrode probe is suspended on the central axis of the first insulating pipe and does not contact the pipe wall; an annular ground electrode, which is closely attached to the outer wall of the first insulating pipe and has an axial length equal to that of the high-voltage electrode probe; A ground electrode protection film wrapped around the annular ground electrode; An insulating shell, which is sleeved on the ground electrode protective film; The plasma generating power source is arranged on the insulating shell, and is respectively connected to the high voltage electrode probe and the annular ground electrode and applies a high voltage thereto.

[0008] Preferably, the high-pressure gas module comprises a high-pressure gas cylinder; The output end of the high-pressure gas cylinder is communicated with the second insulating pipe, wherein the output end of the high-pressure gas cylinder is also provided with a solenoid valve.

[0009] Preferably, the spiral guide groove is a cylindrical structure, and a double-helix channel is opened in the axial direction inside the spiral guide groove, so that the plasma jet delivered by the plasma generating device is rotated through the double-helix channel and input into the magnetic field generator; The magnetic field generator comprises a first cylinder, and an annular copper magnetic coil is arranged on the inner wall of the first cylinder; the input end of the first cylinder is connected to the output end of the spiral guide groove; The electric field generator comprises a second cylinder, and a ground pole and a positive pole ring arranged in the second cylinder; the input end of the second cylinder is connected to the output end of the first cylinder; The ground pole is suspended on the central axis of the second cylinder; The positive electrode ring is closely attached to the inner wall of the second cylinder; The surface of the ground pole and the inner side of the positive pole ring are covered with insulating ceramics; The output end of the second cylinder is communicated with the input end of the gas mixer.

[0010] Preferably, the gas mixer is a hollow cylindrical structure, the hollow cavity inside the gas mixer serves as a mixed gas chamber, the input end of the mixed gas chamber is connected to the output end of the electric field generator; the output end of the mixed gas chamber is connected to the input end of the jet pipe module; The inner wall of the mixed gas chamber is provided with a plurality of gas outlets at equal intervals, and an annular channel is provided in the inner wall of the mixed gas chamber to connect each gas outlet, and the annular channel is connected with the buffer gas cylinder through a tube body.

[0011] Preferably, the jet pipe module comprises: a cylindrical cavity, the input end of which is connected to the output end of the gas mixer; A plurality of body jet pipes are arranged at equal intervals on the fuselage of the aircraft and are connected to the cylindrical cavity; A plurality of wing tip jet pipes and a plurality of tail jet pipes, all of which are connected to the cylindrical cavity, and the nozzle of each wing tip jet pipe is arranged at the wing tip of the aircraft; and the nozzle of each tail jet pipe is arranged at the tail rudder of the aircraft; Each wing tip jet pipe and each tail jet pipe are provided with omnidirectional vector nozzles at the nozzles; Each jet pipe is provided with a solenoid valve and an air pressure sensor.

[0012] Preferably, it also includes: an integrated control terminal, which is composed of a microcontroller and a radar warning receiver, wherein the microcontroller is used to control the operation of the entire system; the radar warning receiver is used to detect external radar scanning and locking, and collect external radar information.

[0013] Preferably, it also includes: the power supply module is composed of an energy storage battery and a multi-way power supply, the energy storage battery is connected to the multi-way power supply, and the multi-way power supply is connected to different electronic devices of the device to supply electric energy of different powers respectively.

[0014] Preferably, the high-pressure gas module, the plasma generating device, the electromagnetic field regulating module, the buffer module and the jet pipe module are all coaxially arranged.

[0015] The second object of the present invention is to provide a plasma jet method adapted for an aircraft, comprising: A high pressure gas module delivers an inert gas to the plasma generating device; The plasma generating device ionizes the inert gas to form a primary plasma jet; The plasma generating device introduces the primary plasma jet into the electromagnetic field regulating module, and the primary plasma jet passes through the spiral guide groove, the magnetic field generator and the electric field generator in sequence to form a secondary plasma jet; The secondary plasma jet is delivered to the gas mixer, and at the same time, the liquid inert gas in the buffer gas bottle is delivered to the gas mixer through a pipe body, and the gas mixer mixes the neutral inert gas into the secondary plasma jet to form a tertiary plasma jet; The jet pipe module is provided with a jet pipe to eject the three-stage plasma jet delivered by the gas mixer in different directions.

[0016] Compared with the prior art, the present invention has the following beneficial effects: The present invention provides a plasma jet device and method suitable for aircraft. In the process of plasma discharge, the present invention adds inert gas in stages, and then uses a combination of mechanical structure guidance and electric field and magnetic field regulation to greatly improve the stability of the plasma jet and extend the time it stays in the air.

[0017] The present invention combines the information collected by the radar warning receiver to generate a plasma cloud with a cutoff frequency lower than the detection frequency for different radar characteristics, thereby achieving a radar stealth effect; or generate a plasma cloud with a cutoff frequency higher than the detection frequency; through the airflow control of the jet tube module, the direction and speed of each plasma injection can be accurately controlled, and finally a plasma cloud with different RCS (radar reflection area) characteristics can be generated to achieve the effect of interfering with / deceiving external radars. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a schematic diagram of the appearance structure of a plasma jet device adapted for an aircraft according to the present invention; Figure 2 It is a schematic diagram of the internal structure of a plasma jet device adapted for an aircraft according to the present invention; Figure 3 It is a schematic structural diagram of a plasma generating device of a plasma jet device adapted for an aircraft according to the present invention; Figure 4 It is a schematic diagram of the structure of an electromagnetic field control module of a plasma jet device adapted for an aircraft according to the present invention; Figure 5It is a schematic diagram of the structure of a gas mixer of a buffer module of a plasma jet device adapted for an aircraft according to the present invention; Figure 6 It is a schematic structural diagram of a jet pipe module of a plasma jet device adapted for an aircraft according to the present invention; Figure 7 The present invention is a schematic diagram of the internal structure of a jet tube module of a plasma jet device adapted for an aircraft. DETAILED DESCRIPTION

[0019] Several specific embodiments of the present invention are described in detail below, but it should be understood that the protection scope of the present invention is not limited by the specific embodiments.

[0020] The purpose of the present invention is to provide a new type of plasma jet device equipped with an aircraft, so as to realize a plasma radar detection and interference device with low energy consumption, low cost and high stability.

[0021] To achieve the above purpose, see Figures 1 to 7 As shown, the present invention provides a plasma jet device adapted for an aircraft, comprising a high-pressure gas module, a plasma generating device, an electromagnetic field control module, a buffer module and a jet pipe module; The electromagnetic field control module includes a spiral guide groove 9, a magnetic field generator 10 and an electric field generator 11 which are connected in sequence; The buffer module includes a buffer gas cylinder 12 and a gas mixer 13, and the buffer gas cylinder 12 is connected to the gas mixer 13 through a pipe body; The gas output end of the high-pressure gas module is connected to the input end of the plasma generating device; The output end of the plasma generating device is connected to the input end of the spiral guide groove 9; The output end of the electric field generator 11 is connected to the input end of the gas mixer 13; The output end of the gas mixer 13 is connected to the input end of the jet pipe module; The jet pipe module is provided with a jet pipe to eject the plasma jet delivered by the gas mixer 13 in different directions.

[0022] In order to realize the plasma generating device outputting a plasma jet, the plasma generating device comprises a first insulating pipe, a high voltage electrode probe 6, an annular ground electrode 7, a ground electrode protective film 8, an insulating shell 5 and a plasma generating power supply 4: A first insulating pipe, whose input end is connected to the gas output end of the high-pressure gas module through a second insulating pipe 3, and whose output end is connected to the input end of the spiral guide groove 9; The high-voltage electrode probe 6 is suspended on the central axis of the first insulating pipe and does not contact the pipe wall; the annular ground electrode 7 is closely attached to the outer wall of the first insulating pipe, and its axial length is equal to that of the high-voltage electrode probe 6; The ground electrode protection film 8 is wrapped on the annular ground electrode 7; the insulating shell 5 is sleeved on the ground electrode protection film 8; the plasma generating power supply 4 is arranged on the insulating shell 5, and is respectively connected to the high-voltage electrode probe 6 and the annular ground electrode 7 and applies a high voltage thereto.

[0023] Therefore, when a high voltage is applied to the high voltage electrode probe 6, the plasma breaks through the cavity gas between the high voltage electrode probe 6 and the annular ground electrode 7 to achieve plasma discharge. This process forms a primary plasma jet.

[0024] In order to realize the high-pressure gas module to deliver inert gas to the plasma generator, the high-pressure gas module includes a high-pressure gas cylinder 1; the output end of the high-pressure gas cylinder 1 is connected to the second insulating pipe 3, wherein the output end of the high-pressure gas cylinder 1 is also provided with a solenoid valve. The solenoid valve 2 is controlled by the integrated control terminal, which controls the gas flow rate of the high-pressure gas cylinder 1 and the opening and closing of the gas cylinder; the output end of the high-pressure gas cylinder 1 is connected to the inlet of the insulating pipe in the plasma generator, and is used to deliver inert gas to the plasma generator.

[0025] In the present invention, the spiral guide groove 9 is a cylindrical structure, and a double-helix structure channel is opened in the axial direction inside the spiral guide groove 9, and the plasma jet delivered by the plasma generating device is rotated through the double-helix structure channel and input into the magnetic field generator 10; when the plasma jet passes through the spiral guide groove 9, the high-speed airflow is caused to rotate counterclockwise; The magnetic field generator 10 comprises a first cylinder, and an annular copper magnetic coil 27 is arranged on the inner wall of the first cylinder; the input end of the first cylinder is connected to the output end of the spiral guide groove 9; The electric field generator 11 comprises a second cylinder, and a ground pole 24 and a positive pole ring 25 arranged in the second cylinder; the input end of the second cylinder is connected to the output end of the first cylinder; The ground pole 24 is suspended on the central axis of the second cylinder; The positive electrode ring 25 is closely attached to the inner wall of the second cylinder; The surface of the ground pole 24 and the inner side of the positive pole ring 25 are covered with insulating ceramics; The output end of the second cylinder is communicated with the input end of the gas mixer 13 .

[0026] The first cylinder and the second cylinder are made of insulating ceramic.

[0027] When the plasma jet passes through the magnetic field generator 10, a magnetic field is applied to the jet, and the direction of the magnetic field is the direction of gas flow, which converges the positive charge of the jet, making the plasma jet energy more dense and prolonging the retention time; When the plasma jet passes through the electric field generator 11, a positive voltage is applied to the positive electrode ring 25, so that the device generates an electric field in the direction from the circumference to the center of the circle. After being converged by the magnetic field, the positive charges in the plasma jet will gather toward the central axis, and the negative charges will gather toward the circumference. This device further separates the positive and negative charges and further enhances the stability of the plasma.

[0028] In order to enhance the stability of plasma and prolong the retention time of plasma, the gas mixer 13 is set to a hollow cylindrical structure, and the hollow cavity inside it is used as a mixed gas chamber 28, and the input end of the mixed gas chamber 28 is connected to the output end of the electric field generator 11; the output end of the mixed gas chamber 28 is connected to the input end of the jet pipe module; A plurality of gas outlets 29 are arranged at equal intervals on the inner wall of the mixing gas chamber 28 , and an annular channel is provided in the inner wall of the mixing gas chamber 28 to connect each gas outlet 29 , and the annular channel is connected to the buffer gas cylinder 12 through a pipe body.

[0029] To this end, the liquid inert gas contained in the buffer gas cylinder 12 is transported to the annular channel through the tube body, and then output to the mixing gas chamber through each gas outlet 29 to mix with the plasma jet, further enhancing the plasma stability and extending the plasma retention time.

[0030] In order to achieve the goal of spreading the plasma jet throughout the entire aircraft, the jet pipe module is provided, including: a cylindrical cavity, a plurality of body tube jet pipes 16, a plurality of wing tip jet pipes 17 and a plurality of tail jet pipes 18; wherein the input end of the cylindrical cavity is connected to the output end of the gas mixer 13; a plurality of body tube jet pipes 16 are arranged at equal intervals on the fuselage of the aircraft and are connected to the cylindrical cavity; a plurality of wing tip jet pipes 17 and a plurality of tail jet pipes 18 are connected to the cylindrical cavity, and the nozzle of each wing tip jet pipe 17 is arranged at the wing tip of the aircraft; the nozzle of each tail jet pipe 18 is arranged at the tail rudder of the aircraft; an omnidirectional vector nozzle 19 is arranged at the nozzle of each wing tip jet pipe 17 and each tail jet pipe 18; each jet pipe is provided with a solenoid valve and an air pressure sensor 15. It should be noted that the cylindrical cavity is equivalent to a cylinder with a hollow structure.

[0031] To this end, the plasma jet is transmitted into the cylindrical cavity and then sprayed onto the surface of the entire aircraft through a plurality of body jet pipes 16, a plurality of wing tip jet pipes 17 and a plurality of tail jet pipes 18 to form a plasma cloud.

[0032] According to the present invention, it also includes: an integrated control terminal, which is composed of a microcontroller 22 and a radar warning receiver 23, wherein the microcontroller 22 is used to control the operation of the entire system; the radar warning receiver 23 is used to detect external radar scanning and locking, and collect external radar information.

[0033] It also includes: a power supply module composed of a storage battery 20 and a multi-way power supply 21, the storage battery 20 is connected to the multi-way power supply 21, and the multi-way power supply 21 is connected to different electronic devices of the device to supply electric energy of different powers respectively.

[0034] In order to facilitate the arrangement of the device on the aircraft, the high-pressure gas module, the plasma generating device, the electromagnetic field regulating module, the buffer module and the jet pipe module are all coaxially arranged.

[0035] Specifically, the axes of the high-pressure gas cylinder 1, the first insulating pipe, the spiral guide groove 9, the first cylinder, the second cylinder, the gas mixer 13 and the cylindrical cavity are located on the same axis; According to the present invention, a plasma device adapted for an aircraft is provided, see Figure 1 As shown, from right to left, it includes a power supply module, a buffer gas bottle 12, a high-pressure gas module, an electromagnetic field control module, a gas mixer 13, a jet pipe module and an integrated control terminal, etc. This layout is mainly for adapting to the aircraft.

[0036] In order to further illustrate the plasma device provided by the present invention and equipped on an aircraft, it is further described in conjunction with the accompanying drawings.

[0037] See also Figures 1 to 7 As shown, a plasma jet device adapted for an aircraft mainly includes a high-pressure gas module, a plasma generating device, an electromagnetic field control module, a buffer module, a jet tube module, a power supply module, an integrated control terminal, etc.

[0038] The high-pressure gas module is composed of a high-pressure gas cylinder 1, a solenoid valve 2, and a gas pipeline. The high-pressure gas cylinder 1 is filled with liquid inert gas for plasma jet injection and plasma reaction; the solenoid valve 2 is controlled by an integrated control terminal, which controls the gas flow rate of the high-pressure gas cylinder 1 and the opening and closing of the gas cylinder; the high-pressure gas cylinder 1 is connected to the inlet of the insulating pipeline in the plasma generator through the gas pipeline, and is used to transport the inert gas to the plasma generator.

[0039] The plasma generating device is composed of a plasma generating power supply 4, an insulating pipe, a high-voltage electrode probe 6, an annular ground electrode 7, and a ground electrode protective film 8. Using the coaxial curved surface dielectric barrier discharge technology, the plasma generating power supply 4 is connected to the high-voltage electrode probe 6 and the annular ground electrode 7 and a high voltage is applied thereto; the insulating pipe 5 is a hollow cylinder with double-sided conduction, and the material is high-hardness ceramic; the high-voltage electrode probe 6 is made of an iron probe, which carries a positive voltage and is suspended in the center of the insulating pipe; the annular ground electrode 7 is a copper annular sheet, which is close to the outer wall of the insulating pipe and flush with the high-voltage electrode probe 6; the ground electrode protective film 8 is made of insulating silicone material, which wraps the annular ground electrode 7 on the outermost side to prevent leakage. When a high voltage is applied to the high-voltage electrode probe 6, the ions break through the cavity gas between the high-voltage electrode probe 6 and the annular ground electrode 7 to achieve plasma discharge. This process forms a primary plasma jet.

[0040] The electromagnetic field control module is composed of a spiral guide groove 9, a magnetic field generator 10 and an electric field generator 11, and is located between the plasma generating device and the buffer module. The magnetic field generator 10 and the electric field generator 11 are arranged coaxially. The airflow first passes through the spiral guide groove 9, then passes through the magnetic field generator 10, and finally passes through the electric field generator 11; the spiral guide groove 9 is a cylindrical structure, and a double helix structure is arranged inside to guide the high-speed airflow to rotate. When the plasma jet passes through the spiral guide groove 9, the high-speed airflow is affected by the observation direction of the left-handed guide groove as the gas flow direction, so that the high-speed airflow rotates counterclockwise; the magnetic field generator 10 is a cylindrical structure, and an annular copper magnetic coil 27 is arranged on the inner wall. When the plasma jet passes through the magnetic field generator 10, a magnetic field is applied to the jet, and the magnetic field direction is the gas flow direction, which converges the positive charge of the jet, so that the plasma jet The energy of the plasma jet is more intensive, and the retention time is extended; the electric field generator 11 is cylindrical, and is composed of a ground pole 24, a positive pole ring 25 and an insulating ceramic 26. The ground pole 24 is located at the center of the device and runs through the entire device. The positive pole ring 25 is outside the ground pole 24, and the positive pole ring 25 and the ground pole 24 have the same axial size; insulating ceramics 26 are arranged on the surface of the ground pole 24, the inside and outside of the positive pole ring 25 to prevent direct contact with the plasma and the combination of positive and negative charges. When the plasma jet passes through the electric field generator 11, a positive voltage is applied to the positive pole ring 25, so that the device generates an electric field from the circumference to the center of the circle. After being converged by the magnetic field, the positive charges in the plasma jet will gather toward the central axis, and the negative charges will gather toward the circumference. This device further separates the positive and negative charges and further enhances the stability of the plasma. This process forms a secondary plasma jet.

[0041] The buffer module is composed of a buffer gas cylinder 12, a solenoid valve 2, a gas pipeline 30, and a gas mixer 13. The buffer gas cylinder 12 is a high-pressure gas cylinder filled with liquid inert gas; the solenoid valve 2 is connected to the outlet of the buffer gas cylinder 12 and is controlled by the integrated control terminal, which controls the gas flow rate of the buffer gas cylinder 12 and the opening and closing of the gas cylinder; the gas pipeline 30 is used for gas transportation; the gas mixer 13 is a hollow cylindrical structure, and a mixed gas chamber 28 is arranged inside, which is located between the electromagnetic field control module and the jet tube module, and an annular four-way gas outlet 29 is arranged on the inner wall, which is evenly distributed on the inner wall of the gas mixer 13, and is used to mix neutral inert gas into the secondary plasma jet, further enhance the plasma stability, and prolong the retention time of the plasma. This process forms a tertiary plasma jet.

[0042] After the organic combination of the plasma generating device, the electromagnetic field control module and the buffer module in the present invention, the stability of the plasma jet is greatly improved, and the time it stays in the air is prolonged. The following are specific simulation data, see Table 1.

[0043] Table 1 shows the simulation parameters of the organic combination of the plasma generating device, the electromagnetic field control module and the buffer module in the plasma jet device.

[0044]

[0045] The jet tube module is composed of a combined magnetic control switch 14, an air pressure sensor 15, a tube jet tube 16, a wing tip jet tube 17, a tail jet tube 18 and an omnidirectional vector nozzle 19; the combined magnetic control switch 14 is composed of several groups of electromagnetic valves 2, which respectively control the gas flow rate of each jet tube; the air pressure sensor 15 is located in each jet tube, which is used to detect the air pressure in the jet tube to achieve closed-loop control; the tube jet tube 16 is composed of four jet tubes, which are distributed in an annular manner on the outside of the jet tube module to achieve the effect of imitating the fuselage of an aircraft; the wing tip jet tube 17 is located on the left and right sides of the device, and is composed of two jet tubes, which are used to spray plasma jets to both sides to achieve the effect of imitating the flying wing of an aircraft; the tail jet tube 18 is composed of three jet tubes, which is located at the end of the device to achieve the effect of imitating the tail rudder of an aircraft; the omnidirectional vector nozzle 19 is located at the outlet of each jet tube in the wing tip jet tube 17 and the tail jet tube 18, and is used to change the airflow injection direction of each jet tube.

[0046] The power supply module is composed of a storage battery 20 and a multi-way power supply 21. The storage battery 20 is connected to the multi-way power supply 21. The multi-way power supply 21 is connected to different electronic devices of the device to supply electric energies of different powers respectively.

[0047] The integrated control terminal is composed of a microcontroller 22 and a radar warning receiver 23. The microcontroller 22 is used to control the operation of the entire system; the radar warning receiver 23 is used to detect external radar scanning and locking, and collect external radar information.

[0048] The basic working process of a plasma jet device adapted for an aircraft provided by the present invention is as follows: When the system starts working, the high-pressure gas module, the plasma generator, and the electromagnetic field control module operate synchronously. First, the solenoid valve 2 of the high-pressure gas cylinder 1 is opened, and the plasma generator starts working at the same time. When the high-pressure inert gas passes through the plasma generator, the plasma discharge process starts, the inert gas is ionized, and a primary plasma jet is formed. The high-speed airflow is affected by the observation direction of the left-handed guide groove in the direction of gas flow, so that the high-speed airflow rotates counterclockwise. Then, the jet passes through the magnetic field control device, and the magnetic field is applied to the jet. The direction of the magnetic field is the direction of gas flow, and the positive charge of the jet is converged, so that the energy of the plasma jet is more dense. Further, when the jet passes through the electric field generator 11, a positive voltage is applied to the positive pole ring 25, so that the device generates an electric field in the direction of the circumference to the center of the circle. The positive charge in the plasma jet after being converged by the magnetic field will gather toward the central axis, and the negative charge will gather toward the circumference. This device further separates the positive and negative charges, and the jet will further shrink, enhancing the stability of the plasma and forming a plasma secondary jet. Then, when the secondary plasma jet enters the buffer module, the solenoid valve 2 of the buffer module controls the buffer gas bottle 12 to open, and neutral inert gas is mixed into the secondary plasma jet. The two are evenly mixed in the mixed gas chamber 28 to form a tertiary plasma jet. After the jet enters the jet tube module, it is acted on by the solenoid valves 2 of different jet tubes. The tertiary plasma jet passes through different jet tube ejection devices. The air pressure sensor 15 monitors the air pressure in each jet tube and cooperates with the solenoid valve 2 to close the loop to control the flow rate of each jet tube. The omnidirectional vector nozzle 19 controls the injection direction to form a plasma cloud, and the work is completed.

[0049] In addition, users can also choose different working modes according to different situations, namely radar stealth mode and radar interference mode.

[0050] Radar Stealth Mode: During use, when it is detected that an external radar has locked onto the aircraft or other similar situations, the radar warning receiver 23 analyzes the external radar characteristic information, and the microcontroller 22 adjusts the plasma power supply to generate plasma with a cutoff frequency lower than the electromagnetic wave detection frequency according to different radar characteristic information. Through the basic working process, the omnidirectional vector nozzle 19 is controlled to wrap the aircraft in a plasma cloud to achieve a radar stealth effect.

[0051] Radar Jamming Mode: When in use, when it is detected that an external radar has locked onto an aircraft or other similar situations, the microcontroller 22 uses the characteristics of plasma reflecting electromagnetic waves to regulate the plasma power supply, generate a plasma cloud with a cutoff frequency higher than the detection frequency, and accurately control the airflow through the jet tube module to precisely control the direction and speed of each plasma injection, ultimately generating a plasma cloud with different RCS radar reflection area characteristics, so as to achieve the effect of interfering with / deceiving external radars.

[0052] The present invention provides a plasma jet method adapted for an aircraft, comprising: A high pressure gas module delivers an inert gas to the plasma generating device; The plasma generating device ionizes the inert gas to form a primary plasma jet; The plasma generating device introduces the primary plasma jet into the electromagnetic field control module, and the primary plasma jet passes through the spiral guide groove 9, the magnetic field generator 10 and the electric field generator 11 in sequence to form a secondary plasma jet; The secondary plasma jet is delivered to the gas mixer 13. At the same time, the liquid inert gas in the buffer gas bottle 12 is delivered to the gas mixer 13 through a pipe body. The gas mixer 13 mixes the neutral inert gas into the secondary plasma jet to form a tertiary plasma jet. The jet pipe module is provided with a jet pipe to eject the three-stage plasma jet delivered by the gas mixer 13 in different directions.

Claims

1. A plasma jet device adapted for an aircraft, characterized in that: It includes a high-pressure gas module, a plasma generating device, an electromagnetic field control module, a buffer module and a jet pipe module; The electromagnetic field control module comprises a spiral guide groove (9), a magnetic field generator (10) and an electric field generator (11) which are connected in sequence; The buffer module comprises a buffer gas cylinder (12) and a gas mixer (13), and the buffer gas cylinder (12) is connected to the gas mixer (13) via a pipe body; The gas output end of the high-pressure gas module is connected to the input end of the plasma generating device; The output end of the plasma generating device is connected to the input end of the spiral guide groove (9); The output end of the electric field generator (11) is connected to the input end of the gas mixer (13); The output end of the gas mixer (13) is in communication with the input end of the jet pipe module; The jet pipe module is provided with a jet pipe to eject the plasma jet delivered by the gas mixer (13) in different directions.

2. The plasma jet device adapted for an aircraft according to claim 1, characterized in that: The plasma generating device comprises: A first insulating pipe, the input end of which is connected to the gas output end of the high-pressure gas module through a second insulating pipe (3), and the output end of which is connected to the input end of the spiral guide groove (9); A high-voltage electrode probe (6) is suspended on the central axis of the first insulating pipe; an annular ground electrode (7), which is closely attached to the outer wall of the first insulating pipe and has an axial length equal to that of the high-voltage electrode probe (6); A ground electrode protection film (8), which is wrapped around the annular ground electrode (7); An insulating shell (5) which is sleeved on the ground electrode protective film (8); A plasma generating power source (4) is arranged on the insulating housing (5), and is respectively connected to the high-voltage electrode probe (6) and the annular ground electrode (7) and applies a high voltage thereto.

3. The plasma jet device adapted for an aircraft according to claim 2, characterized in that: The high-pressure gas module comprises a high-pressure gas cylinder (1); The output end of the high-pressure gas cylinder (1) is in communication with the second insulating pipe (3), wherein the output end of the high-pressure gas cylinder (1) is also provided with a solenoid valve (2).

4. The plasma jet device adapted for an aircraft according to claim 1, characterized in that: The spiral guide groove (9) is a columnar structure, and a channel with a double helical structure is opened in the axial direction inside the spiral guide groove. The plasma jet delivered by the plasma generating device is rotated through the channel with the double helical structure and input into the magnetic field generator (10); The magnetic field generator (10) comprises a first cylinder, and an annular copper magnetic coil (27) is arranged on the inner wall of the first cylinder; the input end of the first cylinder is connected to the output end of the spiral guide groove (9); The electric field generator (11) comprises a second cylinder, and a ground pole (24) and a positive pole ring (25) arranged in the second cylinder; the input end of the second cylinder is connected to the output end of the first cylinder; The ground pole (24) is suspended on the central axis of the second cylinder; The positive electrode ring (25) is closely attached to the inner wall of the second cylinder; The surface of the ground pole (24) and the inner side of the positive pole ring (25) are both covered with insulating ceramic; The output end of the second cylinder is in communication with the input end of the gas mixer (13).

5. The plasma jet device adapted for an aircraft according to claim 1, characterized in that: The gas mixer (13) is a hollow cylindrical structure, the hollow cavity inside the gas mixer serves as a mixed gas chamber (28), the input end of the mixed gas chamber (28) is connected to the output end of the electric field generator (11); the output end of the mixed gas chamber (28) is connected to the input end of the jet pipe module; The inner wall of the mixed gas chamber (28) is provided with a plurality of gas outlets (29) at equal intervals, and an annular channel is provided in the inner wall of the mixed gas chamber (28) to connect each gas outlet (29), and the annular channel is connected to the buffer gas bottle (12) through a pipe body.

6. The plasma jet device adapted for an aircraft according to claim 1, characterized in that: The jet pipe module comprises: A cylindrical cavity, the input end of which is connected to the output end of the gas mixer (13); A plurality of body jet pipes (16) are arranged at equal intervals on the fuselage of the aircraft and are connected to the cylindrical cavity; A plurality of wing tip jet pipes (17) and a plurality of tail jet pipes (18), all of which are in communication with the cylindrical cavity, the nozzle of each wing tip jet pipe (17) being arranged at the wing tip of the aircraft; and the nozzle of each tail jet pipe (18) being arranged at the tail rudder of the aircraft; Each wing tip jet pipe (17) and each tail jet pipe (18) are provided with an omnidirectional vector nozzle (19) at the nozzle; Each jet pipe is provided with a solenoid valve and an air pressure sensor (15).

7. The plasma jet device adapted for an aircraft according to claim 1, characterized in that: Also includes: The integrated control terminal is composed of a microcontroller (22) and a radar warning receiver (23), wherein the microcontroller (22) is used to control the operation of the entire system; the radar warning receiver (23) is used to detect external radar scanning and locking, and collect external radar information.

8. The plasma jet device adapted for an aircraft according to claim 1, characterized in that: Also includes: The power supply module is composed of an energy storage battery (20) and a multi-channel power supply (21); the energy storage battery (20) is connected to the multi-channel power supply (21); and the multi-channel power supply (21) is connected to different electronic devices of the device to supply electric energy of different powers respectively.

9. The plasma jet device adapted for an aircraft according to claim 1, characterized in that: The high-pressure gas module, the plasma generating device, the electromagnetic field regulating module, the buffer module and the jet pipe module are all coaxially arranged.

10. A plasma jet method adapted for an aircraft, characterized in that: include: A high pressure gas module delivers an inert gas to the plasma generating device; The plasma generating device ionizes the inert gas to form a primary plasma jet; The plasma generating device introduces the primary plasma jet into the electromagnetic field control module, and the primary plasma jet passes through the spiral guide groove (9), the magnetic field generator (10) and the electric field generator (11) in sequence to form a secondary plasma jet; The secondary plasma jet is transported to the gas mixer (13), and at the same time, the liquid inert gas in the buffer gas bottle (12) is transported to the gas mixer (13) through a pipe body, and the gas mixer (13) mixes the neutral inert gas into the secondary plasma jet to form a tertiary plasma jet; The jet pipe module is provided with a jet pipe to eject the three-stage plasma jet delivered by the gas mixer (13) in different directions.

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