CN113704884A - Electromagnetic environment effect simulation method for airplane design - Google Patents
Electromagnetic environment effect simulation method for airplane design Download PDFInfo
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- 230000007613 environmental effect Effects 0.000 claims description 10
- 238000001228 spectrum Methods 0.000 claims description 10
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Abstract
The application relates to the technical field of electromagnetic simulation, in particular to an electromagnetic environment effect simulation method for airplane design, which comprises the steps of S1, determining airplane electromagnetic environment effect simulation and evaluation items; step S2, determining an aircraft development process, and dividing the aircraft development process into a plurality of stages according to a time sequence; step S3, classifying the aircraft electromagnetic environment effect simulation and evaluation projects according to stages, and determining the aircraft electromagnetic environment effect simulation and evaluation projects to be completed in each stage; and step S4, determining the sequence and the progressive relation of the electromagnetic environment effect simulation and evaluation projects of each airplane. The method is closely combined with the development stage of the airplane, different simulation projects are closely associated, the flow is standard, concise and effective, the simulation efficiency can be greatly improved, the repeated utilization rate of simulation models and data is improved, the unified simulation input conditions are convenient, the consistency of design is ensured, and the electromagnetic compatibility of the airplane can be evaluated quickly, systematically, fully and comprehensively.
Description
Technical Field
The application relates to the technical field of electromagnetic simulation, in particular to an electromagnetic environment effect simulation method for airplane design.
Background
The airplane faces increasingly complex electromagnetic environment threats, on one hand, electromagnetic interference in a platform system is more serious along with the increase of frequency devices for electricity utilization of the airplane, and on the other hand, the airplane also faces electromagnetic environment threats from electromagnetic environments generated by a local aircraft carrier, an early warning machine and an electronic warfare airplane, and electromagnetic environment threats of radar and electronic warfare equipment of an enemy ship, the ground and the airplane, and threats of natural electromagnetic environments such as thunder, static electricity and the like in the using process. How the effect of the airplane in various electromagnetic environments directly influences the safety of the airplane and the exertion of the fighting effect.
The traditional airplane electromagnetic environment effect design mainly depends on the modes of letter collecting standard, test, test flight and the like to design, find problems and correct the problems, the simple method for designing the electromagnetic environment effect of the letter collecting standard has no pertinence and can not be quantized, under-design or over-design can be caused, the cost of manpower, capital and time required by the test is high, the environment is difficult to construct, the risk is high, the method can be carried out after the airplane is developed, and the cost for finding the problems is high.
With the development of computer and simulation software technologies, electromagnetic environment effect quantization design through electromagnetic simulation is gradually started in recent years, and electromagnetic simulation calculation such as directional patterns, isolation, electromagnetic environment, signal integrity, lightning and the like is performed through electromagnetic simulation software such as HFSS, CST, FEKO, ADS, EMA3D and the like. However, at present, no standard flow and method are formed for the simulation of the electromagnetic environment effect of the aircraft, various electromagnetic simulation projects are discrete and independent, the correlation between the simulation flow and the aircraft design flow is poor, the electromagnetic compatibility of the aircraft cannot be evaluated quickly, systematically, sufficiently and comprehensively, too many simulation input conditions exist, the reusability of a simulation model and data is not high, and the problems of disordered input conditions, low simulation efficiency and the like easily occur.
Disclosure of Invention
Aiming at the problems that the conventional airplane electromagnetic environment effect simulation and evaluation lacks a normative flow and method, the reusability of a simulation model and data is not high, the simulation efficiency is low and the like, the invention provides an airplane design-oriented electromagnetic environment effect simulation and evaluation flow, the simulation and evaluation flow and the airplane design flow are closely combined, simulation projects are associated to form a simulation flow similar to pipeline operation, and the airplane electromagnetic compatibility can be evaluated quickly, systematically, fully and comprehensively.
The application provides an electromagnetic environment effect simulation method for airplane design, which mainly comprises the following steps:
step S1, determining simulation and evaluation items of the electromagnetic environment effect of the airplane;
step S2, determining an aircraft development process, and dividing the aircraft development process into a plurality of stages according to a time sequence;
step S3, classifying the aircraft electromagnetic environment effect simulation and evaluation projects according to stages, and determining the aircraft electromagnetic environment effect simulation and evaluation projects to be completed in each stage;
and step S4, determining the sequence and the progressive relation of the electromagnetic environment effect simulation and evaluation projects of each airplane.
Preferably, in step S2, the plurality of stages include an argument demonstration stage, a project design stage, and a detailed design stage.
Preferably, in step S3, the determining the aircraft electromagnetic environment effect simulation and evaluation items to be completed in each stage includes:
simulation projects required to be completed in the project demonstration stage comprise: simulating and evaluating the performance of an antenna, simulating and evaluating the layout of the antenna, and simulating and evaluating the external electromagnetic environment of the airplane;
the simulation projects needed to be completed in the scheme design stage comprise: the method comprises the following steps of antenna performance simulation and evaluation, antenna layout simulation and evaluation, antenna isolation simulation and evaluation, aircraft external electromagnetic environment simulation and evaluation, aircraft internal electromagnetic environment simulation and evaluation, lightning attachment point simulation and lightning partition, lightning current distribution simulation and evaluation, static electricity distribution simulation and evaluation, shielding efficiency simulation and evaluation, and frequency spectrum compatibility simulation and evaluation;
simulation projects required to be completed in the detailed design stage include: the simulation and evaluation method comprises the following steps of antenna layout simulation and evaluation, antenna-to-antenna isolation simulation and evaluation, electromagnetic radiation hazard simulation and evaluation on personnel, electromagnetic radiation hazard simulation and evaluation on military hardware, electromagnetic radiation hazard simulation and evaluation on fuel oil, lightning direct effect simulation and evaluation, lightning indirect effect simulation and evaluation, wiring harness radiation characteristic simulation and evaluation, wiring harness crosstalk characteristic simulation and evaluation, wiring harness radiation sensitive characteristic simulation and evaluation, shielding efficiency simulation and evaluation, frequency spectrum compatibility simulation and evaluation, antenna interference coupling simulation and evaluation between airplane teams, electromagnetic environment simulation and evaluation between airplane teams, and complex electromagnetic environment adaptability simulation and evaluation.
Preferably, in step S4, the sequence and progression relationship of the electromagnetic environmental effect simulation and evaluation items of each aircraft are determined according to the development stage, input and output of the electromagnetic environmental effect simulation items.
Preferably, in step S4, the sequence and progression relationship of the simulation and evaluation items of the electromagnetic environment effect of the aircraft include:
firstly, simulating and evaluating the performance of an antenna, secondly, simulating and evaluating the layout of the antenna, then, simulating and evaluating the isolation of the antenna, and finally, simulating and evaluating the compatibility of a frequency spectrum; and
firstly, simulating and evaluating the performance of the antenna, secondly, simulating and evaluating the layout of the antenna, and finally, simulating and evaluating the external electromagnetic environment of the airplane.
Preferably, in step S4, the sequence and progression relationship of the simulation and evaluation items of the electromagnetic environment effect of the aircraft include:
firstly carrying out shielding efficiency simulation and evaluation and aircraft external electromagnetic environment simulation and evaluation, secondly carrying out aircraft internal electromagnetic environment simulation and evaluation, and finally carrying out electromagnetic radiation to personnel hazard simulation and evaluation or electromagnetic radiation to military hazard simulation and evaluation or electromagnetic radiation hazard simulation and evaluation.
Preferably, in step S4, the sequence and progression relationship of the simulation and evaluation items of the electromagnetic environment effect of the aircraft include:
firstly carrying out lightning attachment point simulation and lightning zoning, secondly carrying out lightning current distribution simulation and evaluation, thirdly carrying out lightning direct effect simulation and evaluation, and lastly carrying out lightning indirect effect simulation and evaluation.
Preferably, in step S4, the sequence and progression relationship of the simulation and evaluation items of the electromagnetic environment effect of the aircraft include:
firstly, simulating and evaluating the electromagnetic environment in the airplane, and secondly, simulating and evaluating the radiation sensitivity characteristic of the wire harness.
Preferably, in step S4, the sequence and progression relationship of the simulation and evaluation items of the electromagnetic environment effect of the aircraft include:
firstly, simulating and evaluating the radiation characteristic of the wire harness, and secondly, simulating and evaluating the crosstalk characteristic between the wire harnesses.
Preferably, in step S4, the sequence and progression relationship of the simulation and evaluation items of the electromagnetic environment effect of the aircraft include:
firstly, simulation and evaluation of antenna interference coupling between airplane formation and simulation and evaluation of electromagnetic environment between airplane formation are carried out, and secondly, simulation and evaluation of adaptability of complex electromagnetic environment are carried out.
Electromagnetic environment effect simulation calculation and evaluation are carried out according to the process, the airplane electromagnetic environment effect simulation efficiency can be effectively improved, the problem of airplane electromagnetic compatibility is found and evaluated, and a basis is provided for airplane electromagnetic environment effect quantitative design. The method is applied to the aspect of aviation electromagnetic compatibility design, and can also be applied to the simulation and evaluation of electromagnetic environment effects of other weaponry such as vehicles, ships, missiles and the like.
Drawings
Fig. 1 is a schematic diagram of electromagnetic environment effect simulation which needs to be completed in different aircraft development stages of the aircraft design-oriented electromagnetic environment effect simulation method of the present application.
FIG. 2 is a flowchart of an electromagnetic environment effect simulation method for aircraft design according to the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
The application provides an electromagnetic environment effect simulation method for aircraft design, as shown in fig. 1, which mainly comprises the following steps:
step S1, determining simulation and evaluation items of the electromagnetic environment effect of the airplane;
step S2, determining an aircraft development process, and dividing the aircraft development process into a plurality of stages according to a time sequence;
step S3, classifying the aircraft electromagnetic environment effect simulation and evaluation projects according to stages, and determining the aircraft electromagnetic environment effect simulation and evaluation projects to be completed in each stage;
and step S4, determining the sequence and the progressive relation of the electromagnetic environment effect simulation and evaluation projects of each airplane.
In step S1, the simulation and evaluation items of the electromagnetic environment effect of the aircraft include: simulation and evaluation of antenna performance, simulation and evaluation of antenna layout, simulation and evaluation of isolation between antennas, simulation and evaluation of electromagnetic environment outside the aircraft, simulation and evaluation of electromagnetic environment inside the aircraft, simulation and evaluation of personnel hazard by electromagnetic radiation, simulation and evaluation of military hazard by electromagnetic radiation, simulation and evaluation of fuel hazard by electromagnetic radiation, simulation and evaluation of lightning attachment points and lightning zoning, simulation and evaluation of lightning current distribution, simulation and evaluation of lightning direct effect, simulation and evaluation of indirect lightning effects, simulation and evaluation of electrostatic distribution, simulation and evaluation of radiation characteristics of wire harnesses, simulation and evaluation of crosstalk characteristics between wire harnesses, simulation and evaluation of radiation sensitivity characteristics of wire harnesses, simulation and evaluation of shielding effectiveness, simulation and evaluation of frequency spectrum compatibility, simulation and evaluation of antenna interference coupling between airplane teams, simulation and evaluation of electromagnetic environments between airplane teams, simulation and evaluation of adaptability to complex electromagnetic environments and the like.
In some alternative embodiments, in step S2, the plurality of phases includes a project demonstration phase, a project design phase, and a detailed design phase. The overlapping of simulation projects in different development stages is caused by the fact that along with the development of the airplane, the airplane and a matching system may have continuous improvement of schemes or change of states, and iterative optimization simulation is required.
In some alternative embodiments, the step S3 of determining the aircraft electromagnetic environment effect simulation and evaluation items to be completed in each stage includes:
simulation projects required to be completed in the project demonstration stage comprise: simulating and evaluating the performance of an antenna, simulating and evaluating the layout of the antenna, and simulating and evaluating the external electromagnetic environment of the airplane;
the simulation projects needed to be completed in the scheme design stage comprise: the method comprises the following steps of antenna performance simulation and evaluation, antenna layout simulation and evaluation, antenna isolation simulation and evaluation, aircraft external electromagnetic environment simulation and evaluation, aircraft internal electromagnetic environment simulation and evaluation, lightning attachment point simulation and lightning partition, lightning current distribution simulation and evaluation, static electricity distribution simulation and evaluation, shielding efficiency simulation and evaluation, and frequency spectrum compatibility simulation and evaluation;
simulation projects required to be completed in the detailed design stage include: the simulation and evaluation method comprises the following steps of antenna layout simulation and evaluation, antenna-to-antenna isolation simulation and evaluation, electromagnetic radiation hazard simulation and evaluation on personnel, electromagnetic radiation hazard simulation and evaluation on military hardware, electromagnetic radiation hazard simulation and evaluation on fuel oil, lightning direct effect simulation and evaluation, lightning indirect effect simulation and evaluation, wiring harness radiation characteristic simulation and evaluation, wiring harness crosstalk characteristic simulation and evaluation, wiring harness radiation sensitive characteristic simulation and evaluation, shielding efficiency simulation and evaluation, frequency spectrum compatibility simulation and evaluation, antenna interference coupling simulation and evaluation between airplane teams, electromagnetic environment simulation and evaluation between airplane teams, and complex electromagnetic environment adaptability simulation and evaluation.
In some optional embodiments, in step S4, the sequence and progression relationship of the electromagnetic environmental effect simulation and evaluation projects of each aircraft are determined according to the development stage, input and output of the electromagnetic environmental effect simulation projects. Through the development stage and the input and output analysis of the electromagnetic environment effect simulation project, the transmission relation similar to 'pipeline operation' exists between different simulation projects, namely the result of the former simulation project can be used as the input of the latter simulation project. The input and output of all simulation projects of the aircraft development are arranged, and the simulation and evaluation flow similar to the 'pipeline operation' of the aircraft electromagnetic environment effect is established, so that the input conditions of the simulation are unified, the simulation model and part of simulation results are repeatedly utilized, and the simulation efficiency can be greatly improved.
By analyzing the simulation input and output of each electromagnetic environment effect, in the process of aircraft development, different electromagnetic environment effect simulation projects have a sequence and progressive relation, and the following relation can be obtained: 1. firstly, simulating and evaluating the performance of an antenna, secondly, simulating and evaluating the layout of the antenna, then, simulating and evaluating the isolation of the antenna, and finally, simulating and evaluating the compatibility of a frequency spectrum; and firstly, simulating and evaluating the performance of the antenna, secondly, simulating and evaluating the layout of the antenna, and finally, simulating and evaluating the external electromagnetic environment of the airplane.
2. Firstly carrying out shielding efficiency simulation and evaluation and aircraft external electromagnetic environment simulation and evaluation, secondly carrying out aircraft internal electromagnetic environment simulation and evaluation, and finally carrying out electromagnetic radiation to personnel hazard simulation and evaluation or electromagnetic radiation to military hazard simulation and evaluation or electromagnetic radiation hazard simulation and evaluation.
3. Firstly carrying out lightning attachment point simulation and lightning zoning, secondly carrying out lightning current distribution simulation and evaluation, thirdly carrying out lightning direct effect simulation and evaluation, and lastly carrying out lightning indirect effect simulation and evaluation.
4. Firstly, simulating and evaluating the electromagnetic environment in the airplane, and secondly, simulating and evaluating the radiation sensitivity characteristic of the wire harness.
5. Firstly, simulating and evaluating the radiation characteristic of the wire harness, and secondly, simulating and evaluating the crosstalk characteristic between the wire harnesses.
6. Firstly, simulation and evaluation of antenna interference coupling between airplane formation and simulation and evaluation of electromagnetic environment between airplane formation are carried out, and secondly, simulation and evaluation of adaptability of complex electromagnetic environment are carried out.
The electromagnetic environment effect simulation and evaluation flow facing to airplane design is closely combined with an airplane development stage, different simulation projects are closely associated, the flow is standard, concise and effective, the simulation efficiency can be greatly improved, the repeated utilization rate of simulation models and data is improved, the unified simulation input condition is convenient, the design consistency is ensured, and the electromagnetic compatibility of the airplane can be evaluated quickly, systematically, fully and comprehensively.
Although the invention has been described in detail hereinabove with respect to a general description and specific embodiments thereof, it will be apparent to those skilled in the art that modifications or improvements may be made thereto based on the invention. Accordingly, such modifications and improvements are intended to be within the scope of the invention as claimed.
Claims (10)
1. An electromagnetic environment effect simulation method for aircraft design is characterized by comprising the following steps:
step S1, determining simulation and evaluation items of the electromagnetic environment effect of the airplane;
step S2, determining an aircraft development process, and dividing the aircraft development process into a plurality of stages according to a time sequence;
step S3, classifying the aircraft electromagnetic environment effect simulation and evaluation projects according to stages, and determining the aircraft electromagnetic environment effect simulation and evaluation projects to be completed in each stage;
and step S4, determining the sequence and the progressive relation of the electromagnetic environment effect simulation and evaluation projects of each airplane.
2. An aircraft design-oriented electromagnetic environmental effect simulation method according to claim 1, wherein in step S2, the multiple stages include a project demonstration stage, a project design stage, and a detailed design stage.
3. The aircraft design-oriented electromagnetic environmental effect simulation method of claim 2, wherein the step S3 of determining the aircraft electromagnetic environmental effect simulation and evaluation items to be completed at each stage comprises:
simulation projects required to be completed in the project demonstration stage comprise: simulating and evaluating the performance of an antenna, simulating and evaluating the layout of the antenna, and simulating and evaluating the external electromagnetic environment of the airplane;
the simulation projects needed to be completed in the scheme design stage comprise: the method comprises the following steps of antenna performance simulation and evaluation, antenna layout simulation and evaluation, antenna isolation simulation and evaluation, aircraft external electromagnetic environment simulation and evaluation, aircraft internal electromagnetic environment simulation and evaluation, lightning attachment point simulation and lightning partition, lightning current distribution simulation and evaluation, static electricity distribution simulation and evaluation, shielding efficiency simulation and evaluation, and frequency spectrum compatibility simulation and evaluation;
simulation projects required to be completed in the detailed design stage include: the simulation and evaluation method comprises the following steps of antenna layout simulation and evaluation, antenna-to-antenna isolation simulation and evaluation, electromagnetic radiation hazard simulation and evaluation on personnel, electromagnetic radiation hazard simulation and evaluation on military hardware, electromagnetic radiation hazard simulation and evaluation on fuel oil, lightning direct effect simulation and evaluation, lightning indirect effect simulation and evaluation, wiring harness radiation characteristic simulation and evaluation, wiring harness crosstalk characteristic simulation and evaluation, wiring harness radiation sensitive characteristic simulation and evaluation, shielding efficiency simulation and evaluation, frequency spectrum compatibility simulation and evaluation, antenna interference coupling simulation and evaluation between airplane teams, electromagnetic environment simulation and evaluation between airplane teams, and complex electromagnetic environment adaptability simulation and evaluation.
4. The aircraft design-oriented electromagnetic environmental effect simulation method of claim 1, wherein in step S4, the sequence and progression relationship of each aircraft electromagnetic environmental effect simulation and evaluation project are determined by the development stage, input and output of the electromagnetic environmental effect simulation project.
5. The aircraft design-oriented electromagnetic environment effect simulation method of claim 4, wherein in step S4, the sequence and progression of the aircraft electromagnetic environment effect simulation and evaluation items comprise:
firstly, simulating and evaluating the performance of an antenna, secondly, simulating and evaluating the layout of the antenna, then, simulating and evaluating the isolation of the antenna, and finally, simulating and evaluating the compatibility of a frequency spectrum; and
firstly, simulating and evaluating the performance of the antenna, secondly, simulating and evaluating the layout of the antenna, and finally, simulating and evaluating the external electromagnetic environment of the airplane.
6. The aircraft design-oriented electromagnetic environment effect simulation method of claim 4, wherein in step S4, the sequence and progression of the aircraft electromagnetic environment effect simulation and evaluation items comprise:
firstly carrying out shielding efficiency simulation and evaluation and aircraft external electromagnetic environment simulation and evaluation, secondly carrying out aircraft internal electromagnetic environment simulation and evaluation, and finally carrying out electromagnetic radiation to personnel hazard simulation and evaluation or electromagnetic radiation to military hazard simulation and evaluation or electromagnetic radiation hazard simulation and evaluation.
7. The aircraft design-oriented electromagnetic environment effect simulation method of claim 4, wherein in step S4, the sequence and progression of the aircraft electromagnetic environment effect simulation and evaluation items comprise:
firstly carrying out lightning attachment point simulation and lightning zoning, secondly carrying out lightning current distribution simulation and evaluation, thirdly carrying out lightning direct effect simulation and evaluation, and lastly carrying out lightning indirect effect simulation and evaluation.
8. The aircraft design-oriented electromagnetic environment effect simulation method of claim 4, wherein in step S4, the sequence and progression of the aircraft electromagnetic environment effect simulation and evaluation items comprise:
firstly, simulating and evaluating the electromagnetic environment in the airplane, and secondly, simulating and evaluating the radiation sensitivity characteristic of the wire harness.
9. The aircraft design-oriented electromagnetic environment effect simulation method of claim 4, wherein in step S4, the sequence and progression of the aircraft electromagnetic environment effect simulation and evaluation items comprise:
firstly, simulating and evaluating the radiation characteristic of the wire harness, and secondly, simulating and evaluating the crosstalk characteristic between the wire harnesses.
10. The aircraft design-oriented electromagnetic environment effect simulation method of claim 4, wherein in step S4, the sequence and progression of the aircraft electromagnetic environment effect simulation and evaluation items comprise:
firstly, simulation and evaluation of antenna interference coupling between airplane formation and simulation and evaluation of electromagnetic environment between airplane formation are carried out, and secondly, simulation and evaluation of adaptability of complex electromagnetic environment are carried out.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114162346A (en) * | 2021-12-07 | 2022-03-11 | 上海无线电设备研究所 | Scaling aircraft surface deposition static distribution ground verification method |
| CN114162346B (en) * | 2021-12-07 | 2023-11-14 | 上海无线电设备研究所 | Surface deposition static distribution ground verification method for scaled aircraft |
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