CN114340126B - Active plasma jet device and active stealth method of hypersonic aircraft - Google Patents
Active plasma jet device and active stealth method of hypersonic aircraft Download PDFInfo
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Abstract
The invention belongs to the technical field of pulse discharge plasma application, and discloses an active plasma jet device and an active stealth method of a hypersonic aircraft; generating high-voltage pulse and large-current pulse by using a pulse synthesis power supply, driving gap discharge and generating plasma jet; injecting plasma into the plasma sheath to regulate the plasma sheath; the power supply is synthesized by adopting the repetition frequency pulse, the repetition frequency pulse discharge is generated, the plasma jet of the repetition frequency pulse is realized, the plasma sheath is continuously regulated and controlled, and the stealth of the hypersonic aircraft is realized. The hypersonic aerocraft has the characteristics of high flexibility, strong controllability, low cost and the like.
Description
Technical Field
The invention belongs to the technical field of pulse discharge plasma application, and particularly relates to an active plasma jet device and an active stealth method of a hypersonic aircraft.
Background
At present, when a high-speed aircraft enters the atmosphere again, air is compressed rapidly, and a strong shock wave is formed at the front end of the aircraft. Because the wall surface of the aircraft and air molecules generate strong friction, the temperature and the pressure of the air around the aircraft are increased sharply, so that electrons of the molecules and atoms in the air are excited to a high energy level, ionization occurs, ions and free electrons are generated, and a plasma sheath is formed at the periphery of the aircraft. In the process of propagating electromagnetic waves in the plasma sheath, the electromagnetic wave intensity is attenuated due to the reflection and absorption of the electromagnetic waves by the plasma sheath, and effects such as deflection, time delay, phase shift and the like are generated, so that a series of electromagnetic effects are caused by the transmission attenuation or reflection of the electromagnetic waves for communication or detection, a series of problems such as target detection abnormity are generated, and the problems become bottlenecks restricting the development of near-space high-speed aircrafts and are urgently solved.
The plasma sheath enables the periphery of the target aircraft to uniformly surround the plasma cloud, under the combined action of the electromagnetic wave emitted by the radar of the opposite side and the plasma cloud, firstly, when the electromagnetic wave passes through the plasma, the electromagnetic wave can interact with charged particles of the plasma, partial energy is transferred to the charged particles, the energy of the electromagnetic wave is absorbed, and therefore the energy of the electromagnetic wave is gradually attenuated. Secondly, under the influence of a series of physical actions, the electromagnetic wave will bypass the plasma or cause refraction to change the propagation direction. The electromagnetic energy returned to the radar receiver is small, making it difficult for the radar to discover aircraft hidden in the plasma cloud for stealth.
In recent years, by researching the fluid characteristics of a hypersonic flow field and exploring the interaction between electromagnetic waves and a sheath plasma layer, more and more methods can carry out radar detection on a hypersonic aircraft under the sheath plasma layer, obtain the RCS of the hypersonic aircraft, and break through the possibility that the hypersonic aircraft is detected by the sheath plasma layer.
Because the hypersonic aerocraft is in a complex aerodynamic thermal environment, the material stealth technology is difficult to realize, and the plasma stealth technology has no precedent of engineering application in China, the hypersonic aerocraft mainly realizes stealth design by means of appearance design at present. At present, domestic research on stealth design technology of aircrafts mainly focuses on low-speed aircrafts. These studies have focused primarily on low speed aircraft; in the aspect of stealth performance evaluation, the method is limited by computing hardware, RCS (Radar Cross section) computing and pneumatic computing methods generally mainly use a high-frequency algorithm, even if a high-precision algorithm-moment method is adopted, the computing frequency is low, and the common defects are that the computing method is low in precision, the frequency of a stealth computing wave band is low, and the credibility of the method is greatly reduced. Aiming at the hypersonic aircraft, the RCS of the aircraft is calculated by adopting a moment method, the aerodynamic performance is solved by adopting a method for solving an N-S equation, a pneumatic stealth design platform based on a direct global optimization algorithm, a quadratic curve parameterization method and a Kriging surrogate model is established, the hypersonic aircraft is subjected to optimization design research, and the aerodynamic performance is verified by a wind tunnel test.
However, by designing the profile to achieve stealth, the aerodynamic performance of a hypersonic aircraft is often sacrificed. Plasma stealth techniques are receiving increasing attention due to the advantages of not requiring changes to the aerodynamic profile of the aircraft. The plasma stealth technology is an emerging technology for avoiding radar detection systems by utilizing the interaction of plasma and electromagnetic waves. The current plasma stealth method comprises the following specific steps: the surface of the aircraft is coated with an absorption layer or an interference layer, so that the radar reflection area of the aircraft can be greatly reduced. However, if the radar frequency is greatly reduced, for example, by using a meter-wave radar, or increased, for example, by using a millimeter-wave radar, the plasma is substantially non-absorbing. Furthermore, the radioisotope method has a great limitation because it is radioactive and difficult to maintain. The other method is a plasma generator installation method, which is to install one or more plasma generators in the aircraft, and utilize plasma airflow ejected by the plasma generators to wrap the surface of the aircraft, thereby absorbing electromagnetic waves, attenuating reflected signals and realizing stealth. The latter method is more suitable for practical use than the radioisotope method. By adopting the plasma generator method, not only can the reflected signal be weakened and the length of the signal be changed, but also some false signals can be sent to the enemy to effectively interfere the enemy radar, so that the enemy radar can detect the false signal to realize information deception and achieve stealth. When the hypersonic aircraft flies at a high speed, a plasma sheath for attaching the aircraft is easy to form, and the plasma stealth can be realized. However, in recent years, by researching the fluid characteristics of the hypersonic flow field and exploring the interaction between the electromagnetic wave and the sheath plasma layer, more and more methods can carry out radar detection on the hypersonic flight vehicle under the plasma sheath so as to obtain the RCS of the hypersonic flight vehicle, and the detection of the hypersonic flight vehicle by breaking through the plasma sheath becomes possible gradually.
Through the above analysis, the problems and defects of the prior art are as follows:
the prior art can carry out radar detection on the hypersonic aerocraft under the plasma sheath package to obtain the RCS of the hypersonic aerocraft, and cannot directly utilize the plasma sheath to realize the stealth of the hypersonic aerocraft.
The difficulty in solving the above problems and defects is: on the basis of a plasma sheath, the plasma jet with the repetition frequency is generated by utilizing the active discharge of the repetition frequency, the plasma jet and the plasma sheath are mixed, and the electromagnetic property of the plasma sheath is regulated and controlled, so that the radar detects abnormity, and the active stealth of the hypersonic aircraft is realized.
The significance for solving the problems and the defects is as follows: the invention provides a method for realizing active stealth of a hypersonic aircraft with low cost and high reliability.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides an active plasma jet device and an active stealth method of a hypersonic aircraft.
The active stealth method of the hypersonic aircraft comprises the following steps:
generating high-voltage pulses and large-current pulses by using a pulse synthesis power supply, driving gap discharge to generate plasma jet, adjusting parameters of the pulse synthesis power supply according to the electromagnetic property of a plasma sheath, and generating plasma jet with different intensities and densities;
injecting plasma into the plasma sheath, mixing the plasma with the plasma sheath, disturbing the electron density distribution and the flow field structure distribution of the plasma sheath, and regulating and controlling the plasma sheath so as to change the electromagnetic characteristic of the plasma sheath;
and thirdly, adopting a repetition frequency pulse synthesis power supply to generate repetition frequency pulse discharge to realize the injection of the repetition frequency pulse plasma, continuously superposing and disturbing on the basis of the previous disturbance, and continuously regulating and controlling the plasma sheath to realize the stealth of the hypersonic aircraft.
Further, the second step is to change the electron density, the collision frequency and the configuration distribution of the plasma sheath in the regulation of the plasma sheath.
Further, in the third step, a repetition frequency pulse synthesis power supply is adopted, in the generation of repetition frequency pulse discharge, plasma sheath electron density data is diagnosed in real time through a plasma sheath electron density online diagnosis method, the data is automatically fed back to the repetition frequency pulse synthesis power supply, and the energy, the electron density and the size of the sprayed plasma are adjusted through adjusting the duty ratio, the voltage parameter and the current parameter of the pulse synthesis power supply.
Another object of the present invention is to provide an active plasma spray apparatus, including:
an in-plasma injector, a plasma sheath, and a repetition rate pulse synthesis power supply;
the in-plasma injector is located at one end of the plasma sheath and is connected to a repetition rate pulse synthesis power supply.
Another object of the present invention is to provide a winged aircraft equipped with the active plasma jet device.
Another object of the present invention is to provide a wingless aircraft equipped with the active plasma jet device.
By combining all the technical schemes, the invention has the advantages and positive effects that: the hypersonic flight vehicle surface plasma sheath is regulated and controlled during hypersonic flight, the hypersonic flight vehicle surface plasma sheath is used for adjusting the electron density, collision frequency, configuration distribution and the like of the plasma sheath, the electromagnetic scattering characteristic of the plasma sheath is further changed, radar detection abnormity is generated, false targets are generated, and the like, so that the stealth efficiency of the hypersonic flight vehicle is improved.
The active plasma jet device provided by the invention can generate plasma jet with adjustable strength, parameter and time, regulate and control the plasma sheath and change the size and distribution of the electron density of the plasma sheath, so that the hypersonic aerocraft generates target detection abnormity, and the active plasma jet device has important significance for improving the stealth performance of the hypersonic aerocraft. The invention has the characteristics of high flexibility, strong controllability, low cost and the like.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed to be used in the embodiments of the present application will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present application, and it is obvious for those skilled in the art that other drawings can be obtained from the drawings without creative efforts.
Fig. 1 is a flowchart of an active stealth method for a hypersonic aircraft according to an embodiment of the present invention.
FIG. 2 is a schematic diagram illustrating the principle of realizing stealth of a hypersonic aircraft by pulsed plasma jet according to an embodiment of the present invention
Fig. 3 is a schematic structural diagram of an experimental apparatus for high-speed target plasma electromagnetic science in a near space according to an embodiment of the present invention.
Fig. 4 is a diagram illustrating the effect of the actively-excited plasma perturbation process provided by the embodiment of the present invention.
FIG. 5 is a graph of fixed point light intensity over time in a flow field provided by an embodiment of the present invention.
Fig. 6 is a graph of electron density of a plasma flow field over time as provided by an embodiment of the present invention.
FIG. 7 is a graph of an emission spectrum of an actively excited plasma provided by an embodiment of the present invention.
FIG. 8 is a hydrogen atomic line broadening curve provided by an embodiment of the invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail with reference to the following embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
In order to solve the problems in the prior art, the invention provides an active plasma jet device and an active stealth method for a hypersonic flight vehicle, and the invention is described in detail below with reference to the accompanying drawings.
As shown in fig. 1, an active stealth method for a hypersonic aircraft according to an embodiment of the present invention includes:
s101, generating high-voltage pulses and large-current pulses by using a pulse synthesis power supply, driving gap discharge, and generating plasma jet;
s102, injecting plasma into a plasma sheath to regulate and control the plasma sheath;
s103, adopting a repetition frequency pulse synthesis power supply to generate repetition frequency pulse discharge to realize repetition frequency pulse plasma jet, continuously regulating and controlling a plasma sheath, and realizing stealth of the hypersonic aircraft.
The active regulation and control technology of the invention is to use a pulse synthesis power supply, which can generate high voltage pulse and large current pulse to drive gap discharge and generate plasma jet. Injecting the plasma into the plasma sheath modulates the plasma sheath to change the electron density, collision frequency, site profile, etc. of the plasma sheath. A plasma is generated during the gas discharge and the resulting plasma merging with the plasma sheath may increase its electron density, which only lasts a few microseconds. Further, a repetition frequency pulse synthesis power supply is adopted to generate repetition frequency pulse discharge, so that the plasma jet of the repetition frequency pulse is realized, and the plasma sheath can be continuously regulated and controlled, so that the stealth with wide range, long time and long distance is realized.
The technical schematic diagram of the pulsed plasma jet regulation plasma sheath for realizing the active stealth of the hypersonic aircraft is shown in FIG. 2.
By combining with the plasma sheath electron density online diagnosis technology, the plasma sheath electron density data is diagnosed in real time and automatically fed back to the repetition frequency pulse synthesis power supply, and the energy, the electron density, the size and the like of the injected plasma are adjusted by adjusting the duty ratio, the voltage parameter, the current parameter and the like of the pulse synthesis power supply, so that the wide range and only real-time regulation of the plasma sheath electron density are realized.
The early ground experiment verifies that the reliability and the realizability of the technology are verified, experimental research is carried out in a near space high-speed target plasma electromagnetic scientific experimental device, and the schematic diagram of the experimental device is shown in figure 3.
The near space electromagnetic science experiment research device generates a plasma flow field, the active excitation plasma generator generates active excitation plasma under the driving of the high-voltage pulse power supply, and the plasma flow field is disturbed to change the electron density of the plasma flow field. The perturbation process of the actively excited plasma on the plasma flow field is photographed by using a high-speed camera, and the result is shown in fig. 4.
As can be seen from fig. 4, at the position of the jet orifice of the actively-excited plasma generator, the plasma light-emitting brightness gradually increases with the increase of the jet intensity of the actively-excited plasma, which indicates that the electron density gradually increases, and the brightness of the area is much higher than that of the plasma flow field, which indicates that the electron density of the area is much higher than that of the plasma flow field.
The relative light intensity at a position 20mm downstream of the ejection orifice and 10mm above the surface of the actively excited plasma generator was counted as shown in fig. 5.
As can be seen from fig. 5, as the plasma jet is developed, the relative light intensity is gradually increased, and the light intensity is increased by about 100%. The ejection intensity gradually decreases as the ejection energy is consumed.
Electron density diagnostics were performed on the plasma flow field and the actively excited plasma using a far infrared laser interferometer and spectrometer, as shown in fig. 6 and 7.
As can be seen from fig. 6, the electron density of the plasma flow field is 1 × 10 13 cm -3 . From the intensity and line shape of the hydrogen atomic line in the emission spectrum, electron density calculation was performed using Stark broadening, and the hydrogen atomic line is shown in FIG. 7. According to the hydrogen atom spectral line pattern shown in FIG. 7, the electron density of the actively excited plasma can be estimated at 3X 10 by using the stark broadening formula 15 cm -3 。
Since the electron density of the actively excited plasma is much higher than that of the plasma flow field, it can be considered that the electron density of the perturbation region of the actively excited plasma is 10 15 cm -3 Magnitude.
The above description is only for the purpose of illustrating the present invention and the appended claims are not to be construed as limiting the scope of the invention, which is intended to cover all modifications, equivalents and improvements that are within the spirit and scope of the invention as defined by the appended claims.
Claims (5)
1. An active stealth method for a hypersonic aircraft is characterized by comprising the following steps:
generating high-voltage pulse and large-current pulse by using a pulse synthesis power supply, driving gap discharge and generating plasma jet;
injecting plasma into the plasma sheath to regulate the plasma sheath;
thirdly, adopting a repetition frequency pulse synthesis power supply to generate repetition frequency pulse discharge to realize repetition frequency pulse plasma jet, continuously regulating and controlling a plasma sheath and realizing the stealth of the hypersonic aerocraft;
and thirdly, adopting a repetition frequency pulse synthesis power supply, diagnosing sheath electron density data of the plasma in real time by using a plasma sheath electron density online diagnosis method in the generation of repetition frequency pulse discharge, automatically feeding back the data to the repetition frequency pulse synthesis power supply, and adjusting the energy, the electron density and the size of the sprayed plasma by adjusting the duty ratio, the voltage parameter and the current parameter of the pulse synthesis power supply.
2. The active stealth method for hypersonic aircraft according to claim 1, wherein the two steps of conditioning the plasma sheath change the electron density, the collision frequency and the configuration distribution of the plasma sheath.
3. An active plasma jet device for implementing the active stealth method for the hypersonic aircraft according to any one of claims 1 to 2, characterized in that the active plasma jet device comprises:
the plasma sprayer, the online diagnosis device and the repetition frequency pulse synthesis power supply;
the plasma internal ejector is positioned in the hypersonic aircraft and connected with a repetition frequency pulse synthesis power supply.
4. A winged aircraft equipped with the active plasma spraying device according to claim 3.
5. A wingless aircraft equipped with the active plasma spraying device of claim 3.
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| CN108037173A (en) * | 2017-12-06 | 2018-05-15 | 上海无线电设备研究所 | A kind of test system and method for hypersonic two dimension plasma sheath |
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| CN109630312A (en) * | 2018-11-26 | 2019-04-16 | 中国航天空气动力技术研究院 | A kind of high frequency response vector spray |
| CN111511089A (en) * | 2020-06-17 | 2020-08-07 | 沈阳航空航天大学 | Method for realizing equipment stealth by using plasma jet |
| CN211692653U (en) * | 2020-01-09 | 2020-10-16 | 厦门大学 | S-shaped air inlet channel |
| WO2021202629A1 (en) * | 2020-04-03 | 2021-10-07 | University Of Florida Research Foundation | Blade tip vortex control |
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Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108037173A (en) * | 2017-12-06 | 2018-05-15 | 上海无线电设备研究所 | A kind of test system and method for hypersonic two dimension plasma sheath |
| CN108630065A (en) * | 2018-05-15 | 2018-10-09 | 哈尔滨工业大学 | Pulsed magnetic field regulates and controls the experimental provision of spacecraft blackout range dissipation plasma by force |
| CN109630312A (en) * | 2018-11-26 | 2019-04-16 | 中国航天空气动力技术研究院 | A kind of high frequency response vector spray |
| CN211692653U (en) * | 2020-01-09 | 2020-10-16 | 厦门大学 | S-shaped air inlet channel |
| WO2021202629A1 (en) * | 2020-04-03 | 2021-10-07 | University Of Florida Research Foundation | Blade tip vortex control |
| CN111511089A (en) * | 2020-06-17 | 2020-08-07 | 沈阳航空航天大学 | Method for realizing equipment stealth by using plasma jet |
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