Twin system and control method of dense array type stealth drag reduction integrated structure

Abstract

The present invention relates to the field of plasma application technology, and specifically to a twin system of a dense array type stealth drag reduction integrated structure, wherein the integrated structure includes a plurality of electrodes arranged and distributed in a matrix, and the twin system includes a physical module, an information processing module, and a digital twin module connected in communication; the physical module is used to monitor and collect multiple data of the aircraft; the information processing module is used to compare the multiple data of the aircraft with the multiple data stored; when the multiple data of the current aircraft do not match the multiple data stored, a virtual physical model constructed based on the physical information of the integrated structure, and the digital twin module is used to simulate and analyze the virtual physical model with the current multiple data as parameters, predict the specific discharge effect of the integrated structure according to the simulation results, and provide optimization and control suggestions. The present invention can reduce the energy consumption of the stealth drag reduction integrated structure applied to the aircraft.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft stealth and drag reduction, and in particular to a twin system of a dense array type stealth and drag reduction integrated structure and a control method. Background Art

[0002] At present, stealth and drag reduction of aircraft are the focus of research by the world's military powers. Breakthroughs in new stealth and drag reduction technologies will greatly enhance the strength of military equipment and also greatly reduce fuel consumption.

[0003] Plasma is the fourth form of matter after solid, liquid and gas, and it is widely present in nature. When any ordinary gas without charge is subjected to external high-energy action (such as high-energy particle bombardment, strong laser irradiation, gas discharge, thermal ionization, etc.), the energy absorbed by the electrons in some atoms exceeds the atomic ionization energy and they break away from the nucleus and become free electrons. The original neutral gas will be transformed into a substance with different properties from the original gas, which is composed of a large number of free electrons, positive ions and some neutral atoms, due to ionization. It is called plasma. The movement of plasma is mainly affected and dominated by electromagnetic field forces, which has a great influence on the propagation of electromagnetic waves, can significantly weaken or refract electromagnetic waves, and interact with the flow around the aircraft to transmit the electrostatic side body force to the aerodynamic boundary layer, reduce the turbulence of the boundary layer, inhibit the formation of turbulent vortex systems, and significantly reduce the aircraft's head-on resistance, wave resistance, friction resistance, etc.

[0004] In the prior art, a plasma generating sheet is usually attached to the strong electromagnetic wave scattering part of the aircraft, which can generate plasma in the surrounding air. In general, the plasma stealth technology that can be applied to aircraft is currently divided into external open type and closed cycle type according to the structure. The so-called external open type means that the plasma used for stealth covers the surface of the aircraft, and is divided into atmospheric ionization type and portable type according to the source of the plasma generating material.

[0005] Among them, the atmospheric ionization type uses various excitation methods to absorb and reflect the interference radar waves generated by the atmosphere on the outer surface of the aircraft to achieve the purpose of stealth, while the portable type is a container that carries an easily ionized gas medium. The working gas is ionized in the generator by various excitation methods such as discharge and microwaves, and then the ionized body is released to the outside of the aircraft to form a plasma layer, thereby achieving the purpose of stealth or drag reduction. Obviously, this type of generator has the advantages of low energy consumption, reliable operation, and convenient maintenance compared to the atmospheric discharge type, but it requires additional volume and weight such as carrying containers.

[0006] The use of external open plasma stealth technology solves the contradiction between stealth and aerodynamics in traditional passive stealth technology, and can achieve stealth capability without sacrificing the aerodynamic shape of the aircraft. In addition, the use of plasma wrapped in the shape can further reduce the flight resistance of the aircraft. However, there are pros and cons. New technologies not only bring new performance, but also new problems.

[0007] First of all, ionizing gas places high demands on the performance of the power supply. Gas ionization requires a high voltage of more than 10,000 volts, and for the plasma to cover the entire surface of the aircraft, a high-power power supply must be used to produce a sufficient amount of low-temperature plasma. The energy consumption is too high, and the power supply and fuel are too heavy. Therefore, it seems unrealistic to produce a plasma layer covering the entire aircraft, and it can only be used in individual key strong reflective parts. The same is true for portable types. In order to cover the surface of the aircraft, many plasma generators are needed, and the power required is very high. It is still unknown whether the generator can fly. In addition, the external open plasma flow field itself is difficult to stabilize, and it is difficult to form a large area of ​​uniform plasma coverage. In addition, the aircraft constantly changes its posture in the air, and there are various air currents in the atmosphere. It is difficult to imagine how to maintain the stability of the plasma cloud distribution under various circumstances. Summary of the invention

[0008] The purpose of the present invention is to provide a dense array type stealth drag reduction integrated structure to solve the problem that the high voltage power supply of the plasma generator is heavy and thus leads to high energy consumption when the aircraft is carried.

[0009] The present invention is achieved through the following technical solutions:

[0010] A twin system of a dense array type stealth drag reduction integrated structure, the dense array type stealth drag reduction integrated structure comprising a plurality of electrodes arranged and distributed in a matrix, the twin system being used to control all electrodes of the dense array type stealth drag reduction integrated structure;

[0011] The twin system includes a physical module, an information processing module and a digital twin module that are communicatively connected;

[0012] The physical module is used to monitor and collect multiple data of the aircraft;

[0013] The information processing module is used to process and store multiple data of the aircraft, and compare the multiple data of the current aircraft with the multiple data of the stored aircraft;

[0014] When it is detected that multiple data of the current aircraft are identical to multiple data of the stored aircraft, the physical module controls the dense array type stealth drag reduction integrated structure to generate a plasma cloud under low voltage input;

[0015] When it is not detected that multiple data of the current aircraft are the same as multiple data of the stored aircraft, the virtual physical model constructed based on the physical information of the dense array type stealth drag reduction integrated structure, the digital twin module is used to simulate and analyze the virtual physical model of the dense array type stealth drag reduction integrated structure with the multiple data of the current aircraft as parameters, and then predict the specific discharge effect of the dense array type stealth drag reduction integrated structure according to the simulation results, and provide optimization and control suggestions.

[0016] Furthermore, the physical module includes a circuit control system, a sensor component and a data acquisition system; the sensor component is used to detect multiple data of the aircraft; the data acquisition system is used to collect multiple data of the aircraft;

[0017] The information processing module includes a data transmission system, a data processing unit and a database system; the data transmission system is used to transmit the multiple data of the aircraft collected by the data collection system to the database system; the database system is used to store the multiple data of the aircraft; the data processing unit is used to process the multiple data of the aircraft and compare them with the data stored in the database system;

[0018] The digital twin module includes a virtual physical model of the dense array type stealth drag reduction integrated structure and an analysis and optimization tool;

[0019] When it is detected that multiple data of the current aircraft are identical to multiple data of the stored aircraft, the data processing unit transmits an output command to the circuit control system, the circuit control system controls the dense array type stealth drag reduction integrated structure to generate a plasma cloud under low voltage input, and the data processing unit transmits multiple data of the current aircraft to the virtual physical model for real-time simulation;

[0020] When it is not detected that the multiple data of the current aircraft are the same as the multiple data of the stored aircraft, the data processing unit directly transmits the multiple data of the aircraft to the virtual physical model, and the virtual physical model performs simulation with the multiple data of the current aircraft as parameters. The analysis and optimization tool provides optimization and control suggestions for the specific execution of the dense array type stealth drag reduction integrated structure, derives the execution command, and transmits the execution command to the circuit control system for execution, and at the same time transmits the multiple data of the current aircraft to the database for storage.

[0021] Furthermore, the dense array type stealth drag reduction integrated structure comprises a plurality of mounting plates (1) arranged opposite to each other, a plurality of positive electrodes (2) and a plurality of negative electrodes (3) being arranged between two adjacent mounting plates (1), the plurality of positive electrodes (2) and the plurality of negative electrodes (3) being arranged to form a matrix structure, and the positive electrodes (2) and the negative electrodes (3) of the matrix structure are alternately distributed in the transverse and longitudinal directions, and both ends of the plurality of positive electrodes (2) and the plurality of negative electrodes (3) are insulated and abutted against the corresponding mounting plates (1).

[0022] Furthermore, three mounting plates (1) are arranged relatively to each other, a mounting gap is formed between two adjacent mounting plates (1), and both ends of the two mounting gaps along the same direction are open.

[0023] Furthermore, the gap between two adjacent mounting plates (1) is filled and compacted with an insulating particle layer (4).

[0024] The present invention also provides a control method for a dense array type stealth drag reduction integrated structure, comprising the following steps:

[0025] 1) Installing the dense array type stealth drag reduction integrated structure on the surface of the aircraft;

[0026] 2) Monitor and collect multiple data of the aircraft;

[0027] 3) Compare the collected aircraft data with the stored aircraft data;

[0028] 4) when it is detected that multiple data of the current aircraft are identical to multiple data of the stored aircraft, the data processing unit transmits an output command to the circuit control system, and the circuit control system controls the dense array type stealth drag reduction integrated structure to generate a plasma cloud under low voltage input;

[0029] When it is not detected that the multiple data of the current aircraft are the same as the multiple data of the stored aircraft, the multiple data of the aircraft are directly transmitted to the virtual physical model through the data processing unit. The virtual physical model performs simulation with the multiple data of the current aircraft as parameters, and provides optimization and control suggestions for the specific execution of the dense array type stealth drag reduction integrated structure through analysis and optimization tools, derives execution commands, and transmits the execution commands to the circuit control system for execution. At the same time, the multiple data of the current aircraft are transmitted to the database for storage.

[0030] Furthermore, in step 2), the multiple data include temperature, humidity and vibration data of the aircraft surface.

[0031] Compared with the prior art, the present invention has the following advantages and beneficial effects:

[0032] In the present invention, the dense array type stealth drag reduction integrated structure can obtain a continuous high-density plasma cloud by regulating the density of high-temperature resistant ablation electrodes, the dense array arrangement mode and the input voltage, and utilize the interaction between the plasma cloud and the radar wave to absorb the radar wave, attenuate the reflected signal, and achieve stealth; at the same time, high-speed discharge can form a compression wave with an approximate wave speed, significantly changing the structure of the wave system around the aircraft and the boundary layer structure state, achieving the drag reduction function during flight, and effectively solving the technical problems that restrict the application of plasma stealth drag reduction technology; in addition, a strong insulating coating is attached to the position where the high-temperature resistant ablation electrode contacts the metal sheet, and there is a gap between the high-temperature resistant ablation electrodes. During the compacting of the insulating particles, the metal sheet is compacted at the same time, the positive and negative electrodes are arranged alternately, there are four negative electrodes around each positive electrode, and there are four positive electrodes around each negative electrode, and the voltage of each electrode is precisely controlled through the circuit control system. The dense array of high-temperature resistant ablation electrodes can realize flexible control from glow diffuse discharge to arc discharge under low voltage input, obtain high-density plasma cloud, and improve the stealth and drag reduction performance of the aircraft; the present invention can obtain a high-density plasma cloud under low voltage input, which can reduce the weight of the power supply of the dense array type stealth and drag reduction integrated structure, which is beneficial to reducing the energy consumption of the aircraft during the stealth and drag reduction process. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] The drawings described herein are used to provide a further understanding of the embodiments of the present invention, constitute a part of this application, and do not constitute a limitation of the embodiments of the present invention.

[0034] In the attached picture:

[0035] Figure 1 It is a schematic diagram of the local structure of the present invention;

[0036] Figure 2 It is a structural schematic diagram of the present invention;

[0037] Figure 3 It is the overall structural framework diagram of the twin system of the present invention;

[0038] Figure 4 This is a control logic block diagram of the twin system of the present invention.

[0039] Marks and corresponding parts names in the attached drawings:

[0040] 1. Mounting plate; 2. Positive electrode; 3. Negative electrode; 4. Insulating particle layer. DETAILED DESCRIPTION

[0041] In order to make the purpose, technical scheme and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the embodiments and drawings. The schematic implementation modes and descriptions of the present invention are only used to explain the present invention and are not intended to limit the present invention. It should be noted that the present invention is already in the actual development and use stage. Example 1

[0042] A twin system of a dense array type stealth drag reduction integrated structure, the dense array type stealth drag reduction integrated structure comprising a plurality of electrodes arranged and distributed in a matrix, the twin system being used to control all electrodes of the dense array type stealth drag reduction integrated structure;

[0043] The twin system includes a physical module, an information processing module and a digital twin module that are communicatively connected;

[0044] The physical module is used to monitor and collect multiple data of the aircraft;

[0045] The information processing module is used to process and store multiple data of the aircraft, and compare the multiple data of the current aircraft with the multiple data of the stored aircraft;

[0046] When it is detected that multiple data of the current aircraft are identical to multiple data of the stored aircraft, the physical module controls the dense array type stealth drag reduction integrated structure to generate a plasma cloud under low voltage input;

[0047] When it is not detected that multiple data of the current aircraft are the same as multiple data of the stored aircraft, the virtual physical model constructed based on the physical information of the dense array type stealth drag reduction integrated structure, the digital twin module is used to simulate and analyze the virtual physical model of the dense array type stealth drag reduction integrated structure with the multiple data of the current aircraft as parameters, and then predict the specific discharge effect of the dense array type stealth drag reduction integrated structure according to the simulation results, and provide optimization and control suggestions.

[0048] Furthermore, the physical module includes a circuit control system, a sensor component and a data acquisition system; the sensor component is used to detect multiple data of the aircraft; the data acquisition system is used to collect multiple data of the aircraft;

[0049] The information processing module includes a data transmission system, a data processing unit and a database system; the data transmission system is used to transmit the multiple data of the aircraft collected by the data collection system to the database system; the database system is used to store the multiple data of the aircraft; the data processing unit is used to process the multiple data of the aircraft and compare them with the data stored in the database system;

[0050] The digital twin module includes a virtual physical model of the dense array type stealth drag reduction integrated structure and an analysis and optimization tool;

[0051] When it is detected that multiple data of the current aircraft are identical to multiple data of the stored aircraft, the data processing unit transmits an output command to the circuit control system, the circuit control system controls the dense array type stealth drag reduction integrated structure to generate a plasma cloud under low voltage input, and the data processing unit transmits multiple data of the current aircraft to the virtual physical model for real-time simulation;

[0052] When it is not detected that the multiple data of the current aircraft are the same as the multiple data of the stored aircraft, the data processing unit directly transmits the multiple data of the aircraft to the virtual physical model, and the virtual physical model performs simulation with the multiple data of the current aircraft as parameters. The analysis and optimization tool provides optimization and control suggestions for the specific execution of the dense array type stealth drag reduction integrated structure, derives the execution command, and transmits the execution command to the circuit control system for execution, and at the same time transmits the multiple data of the current aircraft to the database for storage.

[0053] Furthermore, the dense array type stealth drag reduction integrated structure comprises a plurality of mounting plates 1 arranged opposite to each other, a plurality of positive electrodes 2 and a plurality of negative electrodes 3 are arranged between two adjacent mounting plates 1, the plurality of positive electrodes 2 and a plurality of negative electrodes 3 are arranged to form a matrix structure, and the positive electrodes 2 and negative electrodes 3 in the matrix structure are alternately distributed in the transverse and longitudinal directions, and both ends of the plurality of positive electrodes 2 and the plurality of negative electrodes 3 are insulated and abutted against the corresponding mounting plates 1. Among them, the plurality of positive electrodes 2 and the plurality of negative electrodes 3 are both high temperature resistant ablation electrodes, and the discharge between the positive electrode 2 and the negative electrode 3 will generate high temperature, and the high temperature resistant ablation electrodes can extend the service life of the stealth drag reduction integrated structure.

[0054] Furthermore, three mounting plates 1 are arranged relatively to each other, and mounting gaps are formed between two adjacent mounting plates 1, and both ends of the two mounting gaps are opened in the same direction. By setting up a two-layer matrix structure, it is convenient to increase the density of plasma cloud generation and distribution, which is beneficial to improving the stealth drag reduction effect of the aircraft; when installing the stealth drag reduction integrated structure, the openings at both ends of the mounting gap correspond to the forward direction and the backward direction of the aircraft, respectively, so as to facilitate the replenishment of gas into the mounting gap.

[0055] Furthermore, the gap between two adjacent mounting plates 1 is filled and compacted with an insulating particle layer 4. The insulating particle layer 4 can quickly extinguish the sparks generated during the discharge process.

[0056] In this embodiment, the dense array type stealth drag reduction integrated structure can obtain a continuous high-density plasma cloud by regulating the density of high-temperature resistant ablation electrodes, the dense array arrangement mode and the input voltage, and utilize the interaction between the plasma cloud and the radar wave to absorb the radar wave, attenuate the reflected signal, and achieve stealth; at the same time, high-speed discharge can form a compression wave with a similar wave speed, significantly changing the structure of the wave system around the aircraft and the boundary layer structure state, achieving the drag reduction function during flight, and effectively solving the technical problems that restrict the application of plasma stealth drag reduction technology; in addition, a strong insulating coating is attached to the position where the high-temperature resistant ablation electrode contacts the metal sheet, There are compacted insulating particles between the high-temperature resistant ablation electrodes, and the metal sheet is compacted at the same time. The positive and negative electrodes 3 are arranged alternately, and there are four negative electrodes 3 around each positive electrode 2. At the same time, there are four positive electrodes 2 around each negative electrode 3. The voltage of each electrode is precisely controlled by the circuit control system. The dense array of high-temperature resistant ablation electrodes can achieve flexible control from glow diffuse discharge to arc discharge under low voltage input, obtain high-density plasma cloud, and improve the stealth and drag reduction performance of the aircraft. The present invention can obtain a high-density plasma cloud under low voltage input, which is beneficial to reducing the energy consumption of the aircraft during the stealth and drag reduction process.

[0057] The present invention also provides a control method for a dense array type stealth drag reduction integrated structure, comprising the following steps:

[0058] 1) Installing the dense array type stealth drag reduction integrated structure on the surface of the aircraft;

[0059] 2) Monitor and collect multiple data of the aircraft;

[0060] 3) Compare the collected aircraft data with the stored aircraft data;

[0061] 4) when it is detected that multiple data of the current aircraft are identical to multiple data of the stored aircraft, the data processing unit transmits an output command to the circuit control system, and the circuit control system controls the dense array type stealth drag reduction integrated structure to generate a plasma cloud under low voltage input;

[0062] When it is not detected that the multiple data of the current aircraft are the same as the multiple data of the stored aircraft, the multiple data of the aircraft are directly transmitted to the virtual physical model through the data processing unit. The virtual physical model performs simulation with the multiple data of the current aircraft as parameters, and provides optimization and control suggestions for the specific execution of the dense array type stealth drag reduction integrated structure through analysis and optimization tools, derives execution commands, and transmits the execution commands to the circuit control system for execution. At the same time, the multiple data of the current aircraft are transmitted to the database for storage to update the data.

[0063] Furthermore, in step 2), the multiple data include temperature, humidity and vibration data of the aircraft surface.

[0064] The specific implementation methods described above further illustrate the objectives, technical solutions and beneficial effects of the present invention in detail. It should be understood that the above description is only a specific implementation method of the present invention and is not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A twin system of a dense array type stealth drag reduction integrated structure, characterized by: The dense array type stealth drag reduction integrated structure comprises a plurality of electrodes arranged and distributed in a matrix, and the twin system is used to control all electrodes of the dense array type stealth drag reduction integrated structure; The twin system includes a physical module, an information processing module and a digital twin module that are communicatively connected; The physical module is used to monitor and collect multiple data of the aircraft; The information processing module is used to process and store multiple data of the aircraft, and compare the multiple data of the current aircraft with the multiple data of the stored aircraft; When it is detected that multiple data of the current aircraft are identical to multiple data of the stored aircraft, the physical module controls the dense array type stealth drag reduction integrated structure to generate a plasma cloud under low voltage input; When it is not detected that multiple data of the current aircraft are identical to multiple data of the stored aircraft, the virtual physical model constructed based on the physical information of the dense array type stealth drag reduction integrated structure, the digital twin module is used to simulate and analyze the virtual physical model of the dense array type stealth drag reduction integrated structure with multiple data of the current aircraft as parameters, and then predict the specific discharge effect of the dense array type stealth drag reduction integrated structure according to the simulation results, and provide optimization and control suggestions; The dense array type stealth drag reduction integrated structure comprises a plurality of mounting plates (1) arranged opposite to each other, a plurality of positive electrodes (2) and a plurality of negative electrodes (3) being arranged between two adjacent mounting plates (1), the plurality of positive electrodes (2) and the plurality of negative electrodes (3) being arranged to form a matrix structure, and the positive electrodes (2) and the negative electrodes (3) of the matrix structure are alternately distributed in the transverse and longitudinal directions, and both ends of the plurality of positive electrodes (2) and the plurality of negative electrodes (3) are insulated and abutted against the corresponding mounting plates (1).

2. The twin system of the dense array type stealth drag reduction integrated structure according to claim 1 is characterized by: The physical module includes a circuit control system, a sensor assembly and a data acquisition system; the sensor assembly is used to detect multiple data of the aircraft; the data acquisition system is used to collect multiple data of the aircraft; The information processing module includes a data transmission system, a data processing unit and a database system; the data transmission system is used to transmit the multiple data of the aircraft collected by the data collection system to the database system; the database system is used to store the multiple data of the aircraft; the data processing unit is used to process the multiple data of the aircraft and compare them with the data stored in the database system; The digital twin module includes a virtual physical model of the dense array type stealth drag reduction integrated structure and an analysis and optimization tool; When it is detected that multiple data of the current aircraft are identical to multiple data of the stored aircraft, the data processing unit transmits an output command to the circuit control system, the circuit control system controls the dense array type stealth drag reduction integrated structure to generate a plasma cloud under low voltage input, and the data processing unit transmits multiple data of the current aircraft to the virtual physical model for real-time simulation; When it is not detected that the multiple data of the current aircraft are the same as the multiple data of the stored aircraft, the data processing unit directly transmits the multiple data of the aircraft to the virtual physical model, and the virtual physical model performs simulation with the multiple data of the current aircraft as parameters. The analysis and optimization tool provides optimization and control suggestions for the specific execution of the dense array type stealth drag reduction integrated structure, derives the execution command, and transmits the execution command to the circuit control system for execution, and at the same time transmits the multiple data of the current aircraft to the database for storage.

3. The twin system of the dense array type stealth drag reduction integrated structure according to claim 1 is characterized by: Three mounting plates (1) are arranged relatively to each other, a mounting gap is formed between two adjacent mounting plates (1), and both ends of the two mounting gaps along the same direction are opened.

4. The twin system of the dense array type stealth drag reduction integrated structure according to claim 3 is characterized by: The gap between two adjacent mounting plates (1) is filled and compacted with an insulating particle layer (4).

5. A control method for a dense array type stealth drag reduction integrated structure, using the dense array type stealth drag reduction integrated structure according to any one of claims 1 to 4, characterized in that: The following steps are involved: 1) Installing the dense array type stealth drag reduction integrated structure on the surface of the aircraft; 2) Monitor and collect multiple data of the aircraft; 3) Compare the collected aircraft data with the stored aircraft data; 4) when it is detected that multiple data of the current aircraft are identical to multiple data of the stored aircraft, the data processing unit transmits an output command to the circuit control system, and the circuit control system controls the dense array type stealth drag reduction integrated structure to generate a plasma cloud under low voltage input; When it is not detected that the multiple data of the current aircraft are the same as the multiple data of the stored aircraft, the multiple data of the aircraft are directly transmitted to the virtual physical model through the data processing unit. The virtual physical model performs simulation with the multiple data of the current aircraft as parameters, and provides optimization and control suggestions for the specific execution of the dense array type stealth drag reduction integrated structure through analysis and optimization tools, derives execution commands, and transmits the execution commands to the circuit control system for execution. At the same time, the multiple data of the current aircraft are transmitted to the database for storage.

6. The control method of the dense array type stealth drag reduction integrated structure according to claim 5 is characterized by: In step 2), the plurality of data includes temperature, humidity and vibration data of the aircraft surface.

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