CN113704884B - Electromagnetic environment effect simulation method for aircraft design - Google Patents
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- 238000004088 simulation Methods 0.000 title claims abstract description 271
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- 230000005670 electromagnetic radiation Effects 0.000 claims description 21
- 230000015572 biosynthetic process Effects 0.000 claims description 14
- 230000005855 radiation Effects 0.000 claims description 14
- 238000009826 distribution Methods 0.000 claims description 11
- 238000002955 isolation Methods 0.000 claims description 11
- 238000001228 spectrum Methods 0.000 claims description 10
- 230000008878 coupling Effects 0.000 claims description 7
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- 238000005859 coupling reaction Methods 0.000 claims description 7
- 238000005192 partition Methods 0.000 claims description 7
- 230000035945 sensitivity Effects 0.000 claims description 7
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Abstract
The application relates to the technical field of electromagnetic simulation, in particular to an electromagnetic environmental effect simulation method for aircraft design, which comprises the following steps of S1, determining an aircraft electromagnetic environmental effect simulation and evaluation project; s2, determining an airplane development process, and dividing the airplane development process into a plurality of stages according to time sequence; step S3, classifying the airplane electromagnetic environmental effect simulation and evaluation items according to each stage, and determining airplane electromagnetic environmental effect simulation and evaluation items which need to be completed in each stage; and S4, determining the sequence and the progressive relation of the electromagnetic environment effect simulation and evaluation items of each aircraft. The method and the system are tightly combined with the development stage of the aircraft, different simulation projects are tightly associated, the flow is standard, concise and effective, the simulation efficiency can be greatly improved, the repeated utilization rate of a simulation model and data is improved, unified simulation input conditions are convenient, the consistency of design is ensured, and the electromagnetic compatibility of the aircraft can be rapidly, systematically, fully and comprehensively evaluated.
Description
Technical Field
The application relates to the technical field of electromagnetic simulation, in particular to an electromagnetic environment effect simulation method for aircraft design.
Background
The aircraft faces increasingly complex electromagnetic environment threats, on one hand, along with the increase of the electricity consumption frequency equipment of the aircraft, the electromagnetic interference in a platform system is more serious, and on the other hand, the aircraft faces electromagnetic environment threats generated by early warning aircraft and electronic warships, radar of the ground and the aircraft and electromagnetic environment threats of electronic warship equipment, and natural electromagnetic environment threats such as lightning, static electricity and the like in the using process. How the effect of the aircraft under various electromagnetic environments directly influences the safety of the aircraft and the playing of the fight efficiency.
The traditional aircraft electromagnetic environment effect design mainly depends on the modes of letter collection standard, test, test flight and the like to design and discover problems and correct, and the electromagnetic environment effect design method of the simple letter collection standard has no pertinence and is unquantifiable and can possibly cause underdesign or over design, the labor, capital and time cost required by the test is high, the environment construction is difficult, the risk is high, the aircraft can be required to be developed, and the problem discovery correction cost is high.
Along with the development of computer and simulation software technologies, in recent years, quantitative design of electromagnetic environmental effects is gradually started through electromagnetic simulation, and electromagnetic simulation calculations such as patterns, isolation, electromagnetic environment, signal integrity, lightning and the like are carried out through electromagnetic simulation software such as HFSS, CST, FEKO, ADS, EMA D and the like. However, at present, aiming at electromagnetic environmental effect simulation of an airplane, a standard flow and a standard method are not formed, various electromagnetic simulation projects are discrete and independent, the relevance between the simulation flow and the airplane design flow is poor, the electromagnetic compatibility of the airplane cannot be evaluated rapidly, systematically, fully and comprehensively, simulation input conditions are too many, the reusability of a simulation model and data is not high, and problems of chaotic input conditions, low simulation efficiency and the like are easy to occur.
Disclosure of Invention
Aiming at the problems of lack of standard flow and method of the existing aircraft electromagnetic environmental effect simulation and evaluation, low simulation model and data reusability, low simulation efficiency and the like, the invention provides an aircraft design-oriented electromagnetic environmental effect simulation and evaluation flow, which is closely combined with an aircraft design flow, simulation projects are associated, a simulation flow similar to 'pipelining operation' is formed, and aircraft electromagnetic compatibility can be evaluated rapidly, systematically, fully and comprehensively.
The application provides an electromagnetic environment effect simulation method for aircraft design, which mainly comprises the following steps:
s1, determining airplane electromagnetic environment effect simulation and evaluation items;
s2, determining an airplane development process, and dividing the airplane development process into a plurality of stages according to time sequence;
step S3, classifying the airplane electromagnetic environmental effect simulation and evaluation items according to each stage, and determining airplane electromagnetic environmental effect simulation and evaluation items which need to be completed in each stage;
and S4, determining the sequence and the progressive relation of the electromagnetic environment effect simulation and evaluation items of each aircraft.
Preferably, in step S2, the plurality of stages includes a stand-off stage, a project design stage, and a detailed design stage.
Preferably, in step S3, determining the simulation and evaluation items of the electromagnetic environmental effect of the aircraft to be completed in each stage includes:
the simulation items to be completed in the stand-off demonstration stage include: simulation and evaluation of antenna performance, simulation and evaluation of antenna layout, and simulation and evaluation of external electromagnetic environment of an aircraft;
the simulation project to be completed in the scheme design stage comprises the following steps: 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 an aircraft, simulation and evaluation of electromagnetic environment inside an aircraft, simulation and lightning partition of lightning attachment points, simulation and evaluation of lightning current distribution, simulation and evaluation of electrostatic distribution, simulation and evaluation of shielding effectiveness, simulation and evaluation of spectrum compatibility;
the simulation items that the detailed design phase needs to complete include: antenna layout simulation and evaluation, inter-antenna isolation simulation and evaluation, electromagnetic radiation to personnel hazard simulation and evaluation, electromagnetic radiation to ordnance hazard simulation and evaluation, electromagnetic radiation to fuel hazard simulation and evaluation, lightning direct effect simulation and evaluation, lightning indirect effect simulation and evaluation, wire harness radiation characteristic simulation and evaluation, wire harness cross-talk characteristic simulation and evaluation, wire harness radiation sensitivity characteristic simulation and evaluation, shielding effectiveness simulation and evaluation, spectrum compatibility simulation and evaluation, inter-aircraft formation antenna interference coupling simulation and evaluation, inter-aircraft formation electromagnetic environment simulation and evaluation, and complex electromagnetic environment adaptability simulation and evaluation.
Preferably, in step S4, the sequence and progressive relationship of the electromagnetic environmental effect simulation and evaluation items of each aircraft are determined through the development stage and input and output of the electromagnetic environmental effect simulation items.
Preferably, in step S4, the sequence and progressive relationship between the simulation and evaluation items of the electromagnetic environmental effect of the aircraft include:
firstly, performing antenna performance simulation and evaluation, secondly, performing antenna layout simulation and evaluation, then performing antenna isolation simulation and evaluation, and finally performing spectrum compatibility simulation and evaluation; and
firstly, performing antenna performance simulation and evaluation, secondly, performing antenna layout simulation and evaluation, and finally, performing aircraft external electromagnetic environment simulation and evaluation.
Preferably, in step S4, the sequence and progressive relationship between the simulation and evaluation items of the electromagnetic environmental effect of the aircraft include:
firstly, performing shielding effectiveness simulation and evaluation and aircraft external electromagnetic environment simulation and evaluation, secondly, performing aircraft internal electromagnetic environment simulation and evaluation, and finally performing electromagnetic radiation to personnel hazard simulation and evaluation or electromagnetic radiation to ordnance hazard simulation and evaluation or electromagnetic radiation hazard simulation and evaluation.
Preferably, in step S4, the sequence and progressive relationship between the simulation and evaluation items of the electromagnetic environmental effect of the aircraft include:
firstly, lightning attachment point simulation and lightning partition are carried out, secondly lightning current distribution simulation and evaluation are carried out, then lightning direct effect simulation and evaluation are carried out, and finally lightning indirect effect simulation and evaluation are carried out.
Preferably, in step S4, the sequence and progressive relationship between the simulation and evaluation items of the electromagnetic environmental effect of the aircraft include:
firstly, simulating and evaluating the electromagnetic environment in the aircraft, and secondly, simulating and evaluating the radiation sensitivity characteristics of the wire harness.
Preferably, in step S4, the sequence and progressive relationship between the simulation and evaluation items of the electromagnetic environmental effect of the aircraft include:
firstly, carrying out simulation and evaluation of radiation characteristics of the wire harnesses, and secondly, carrying out simulation and evaluation of crosstalk characteristics among the wire harnesses.
Preferably, in step S4, the sequence and progressive relationship between the simulation and evaluation items of the electromagnetic environmental effect of the aircraft include:
firstly, simulation and evaluation of interference coupling of antennas among airplane formation and simulation and evaluation of electromagnetic environment among airplane formation are carried out, and secondly, simulation and evaluation of adaptability of complex electromagnetic environment are carried out.
According to the electromagnetic environment effect simulation calculation and evaluation performed according to the flow of the method, the electromagnetic environment effect simulation efficiency of the aircraft can be effectively improved, the electromagnetic compatibility problem of the aircraft can be found and evaluated, and a basis is provided for the quantitative design of the electromagnetic environment effect of the aircraft. The method is applied to the field of aviation electromagnetic compatibility design, and can also be applied to electromagnetic environment effect simulation and evaluation of other weaponry such as vehicles, ships, missiles and the like.
Drawings
Fig. 1 is a schematic diagram of electromagnetic environmental effect simulation to be completed in different stages of development of an aircraft for the electromagnetic environmental effect simulation method of aircraft design.
FIG. 2 is a flow chart of an electromagnetic environmental effect simulation method for aircraft design of the present application.
Detailed Description
For the purposes, technical solutions and advantages of the present application, the following describes the technical solutions in the embodiments of the present application in more detail with reference to the 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, of the embodiments of the present application. The embodiments described below by referring to the drawings are exemplary and intended for the purpose of explaining the present application and are not to be construed as limiting the present application. All other embodiments, based on the embodiments herein, which would be apparent to one of ordinary skill in the art without undue burden are within the scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
The application provides an electromagnetic environment effect simulation method for aircraft design, which mainly comprises the following steps as shown in fig. 1:
s1, determining airplane electromagnetic environment effect simulation and evaluation items;
s2, determining an airplane development process, and dividing the airplane development process into a plurality of stages according to time sequence;
step S3, classifying the airplane electromagnetic environmental effect simulation and evaluation items according to each stage, and determining airplane electromagnetic environmental effect simulation and evaluation items which need to be completed in each stage;
and S4, determining the sequence and the progressive relation of the electromagnetic environment effect simulation and evaluation items of each aircraft.
In step S1, the simulation and evaluation items of the electromagnetic environmental effect of the aircraft include: antenna performance simulation and evaluation, antenna layout simulation and evaluation, inter-antenna isolation simulation and evaluation, aircraft exterior electromagnetic environment simulation and evaluation, aircraft interior electromagnetic environment simulation and evaluation, electromagnetic radiation versus personnel hazard simulation and evaluation, electromagnetic radiation versus ordnance hazard simulation and evaluation, electromagnetic radiation versus fuel hazard simulation and evaluation, lightning attachment point simulation and lightning partition, lightning current distribution simulation and evaluation, lightning direct effect simulation and evaluation, lightning indirect effect simulation and evaluation, electrostatic distribution simulation and evaluation, wire harness radiation characteristic simulation and evaluation, inter-wire harness crosstalk characteristic simulation and evaluation, wire harness radiation sensitivity characteristic simulation and evaluation, shielding effectiveness simulation and evaluation, frequency spectrum compatibility simulation and evaluation, inter-aircraft formation antenna interference coupling simulation and evaluation, inter-aircraft formation electromagnetic environment simulation and evaluation, complex electromagnetic environment adaptability simulation and evaluation, and the like.
In some alternative embodiments, in step S2, the plurality of stages includes a stand-off stage, a solution design stage, and a detailed design stage. The overlapping of simulation projects in different development stages is because with the development of the aircraft, the aircraft and the matched system may have continuous perfection of schemes or change of states, and iterative optimization simulation is required.
In some alternative embodiments, in step S3, determining the aircraft electromagnetic environmental effect simulation and evaluation items that each stage needs to complete includes:
the simulation items to be completed in the stand-off demonstration stage include: simulation and evaluation of antenna performance, simulation and evaluation of antenna layout, and simulation and evaluation of external electromagnetic environment of an aircraft;
the simulation project to be completed in the scheme design stage comprises the following steps: 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 an aircraft, simulation and evaluation of electromagnetic environment inside an aircraft, simulation and lightning partition of lightning attachment points, simulation and evaluation of lightning current distribution, simulation and evaluation of electrostatic distribution, simulation and evaluation of shielding effectiveness, simulation and evaluation of spectrum compatibility;
the simulation items that the detailed design phase needs to complete include: antenna layout simulation and evaluation, inter-antenna isolation simulation and evaluation, electromagnetic radiation to personnel hazard simulation and evaluation, electromagnetic radiation to ordnance hazard simulation and evaluation, electromagnetic radiation to fuel hazard simulation and evaluation, lightning direct effect simulation and evaluation, lightning indirect effect simulation and evaluation, wire harness radiation characteristic simulation and evaluation, wire harness cross-talk characteristic simulation and evaluation, wire harness radiation sensitivity characteristic simulation and evaluation, shielding effectiveness simulation and evaluation, spectrum compatibility simulation and evaluation, inter-aircraft formation antenna interference coupling simulation and evaluation, inter-aircraft formation electromagnetic environment simulation and evaluation, and complex electromagnetic environment adaptability simulation and evaluation.
In some optional embodiments, in step S4, the sequence and progressive relationship of the electromagnetic environmental effect simulation and evaluation items of each aircraft are determined through the development stage and input and output of the electromagnetic environmental effect simulation items. Through the development stage and input and output analysis of the electromagnetic environment effect simulation project, the transmission relation similar to the pipeline operation between different simulation projects can be found, 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 airplane development are arranged, and an airplane electromagnetic environment effect simulation and evaluation flow similar to 'pipelining operation' is established, so that unified simulation input conditions are facilitated, a simulation model and partial simulation results are recycled, and simulation efficiency can be greatly improved.
By analyzing the simulation input and output of each electromagnetic environment effect, in the development process of the aircraft, different electromagnetic environment effect simulation projects have a sequence and progressive relationship, and the following relationship can be obtained: 1. firstly, performing antenna performance simulation and evaluation, secondly, performing antenna layout simulation and evaluation, then performing antenna isolation simulation and evaluation, and finally performing spectrum compatibility simulation and evaluation; and firstly, performing antenna performance simulation and evaluation, secondly, performing antenna layout simulation and evaluation, and finally, performing aircraft external electromagnetic environment simulation and evaluation.
2. Firstly, performing shielding effectiveness simulation and evaluation and aircraft external electromagnetic environment simulation and evaluation, secondly, performing aircraft internal electromagnetic environment simulation and evaluation, and finally performing electromagnetic radiation to personnel hazard simulation and evaluation or electromagnetic radiation to ordnance hazard simulation and evaluation or electromagnetic radiation hazard simulation and evaluation.
3. Firstly, lightning attachment point simulation and lightning partition are carried out, secondly lightning current distribution simulation and evaluation are carried out, then lightning direct effect simulation and evaluation are carried out, and finally lightning indirect effect simulation and evaluation are carried out.
4. Firstly, simulating and evaluating the electromagnetic environment in the aircraft, and secondly, simulating and evaluating the radiation sensitivity characteristics of the wire harness.
5. Firstly, carrying out simulation and evaluation of radiation characteristics of the wire harnesses, and secondly, carrying out simulation and evaluation of crosstalk characteristics among the wire harnesses.
6. Firstly, simulation and evaluation of interference coupling of antennas among airplane formation and simulation and evaluation of electromagnetic environment among airplane formation are carried out, and secondly, simulation and evaluation of adaptability of complex electromagnetic environment are carried out.
The electromagnetic environmental effect simulation and evaluation flow for the aircraft design, which is provided by the application, is tightly combined with the development stage of the aircraft, is tightly associated with different simulation projects, is standard, concise and effective, can greatly improve the simulation efficiency, improves the repeated utilization rate of a simulation model and data, is convenient for unifying simulation input conditions, ensures the consistency of the design, and can evaluate the electromagnetic compatibility of the aircraft quickly, systematically, fully and comprehensively.
While the invention has been described in detail in the foregoing general description and with reference to specific embodiments thereof, it will be apparent to one skilled in the art that modifications and improvements can be made thereto. Accordingly, such modifications or improvements may be made without departing from the spirit of the invention and are intended to be within the scope of the invention as claimed.
Claims (8)
1. An electromagnetic environmental effect simulation method for aircraft design is characterized by comprising the following steps:
s1, determining airplane electromagnetic environment effect simulation and evaluation items;
s2, determining an airplane development process, and dividing the airplane development process into a plurality of stages according to time sequence;
step S3, classifying the airplane electromagnetic environmental effect simulation and evaluation items according to each stage, and determining airplane electromagnetic environmental effect simulation and evaluation items which need to be completed in each stage;
s4, determining the sequence and the progressive relation of electromagnetic environment effect simulation and evaluation items of each aircraft;
in step S2, the multiple stages include a stand-off stage, a solution design stage, and a detailed design stage;
in step S3, determining the simulation and evaluation items of the electromagnetic environmental effect of the aircraft to be completed in each stage includes:
the simulation items to be completed in the stand-off demonstration stage include: simulation and evaluation of antenna performance, simulation and evaluation of antenna layout, and simulation and evaluation of external electromagnetic environment of an aircraft;
the simulation project to be completed in the scheme design stage comprises the following steps: 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 an aircraft, simulation and evaluation of electromagnetic environment inside an aircraft, simulation and lightning partition of lightning attachment points, simulation and evaluation of lightning current distribution, simulation and evaluation of electrostatic distribution, simulation and evaluation of shielding effectiveness, simulation and evaluation of spectrum compatibility;
the simulation items that the detailed design phase needs to complete include: antenna layout simulation and evaluation, inter-antenna isolation simulation and evaluation, electromagnetic radiation to personnel hazard simulation and evaluation, electromagnetic radiation to ordnance hazard simulation and evaluation, electromagnetic radiation to fuel hazard simulation and evaluation, lightning direct effect simulation and evaluation, lightning indirect effect simulation and evaluation, wire harness radiation characteristic simulation and evaluation, wire harness cross-talk characteristic simulation and evaluation, wire harness radiation sensitivity characteristic simulation and evaluation, shielding effectiveness simulation and evaluation, spectrum compatibility simulation and evaluation, inter-aircraft formation antenna interference coupling simulation and evaluation, inter-aircraft formation electromagnetic environment simulation and evaluation, and complex electromagnetic environment adaptability simulation and evaluation.
2. The electromagnetic environment effect simulation method for aircraft design according to claim 1, wherein in step S4, the sequence and progressive relationship of the electromagnetic environment effect simulation and evaluation items of each aircraft are determined through the development stage and input and output of the electromagnetic environment effect simulation items.
3. The method for simulating electromagnetic environmental effects of aircraft design according to claim 2, wherein in step S4, the sequence and progressive relationship of the aircraft electromagnetic environmental effect simulation and evaluation items include:
firstly, performing antenna performance simulation and evaluation, secondly, performing antenna layout simulation and evaluation, then performing antenna isolation simulation and evaluation, and finally performing spectrum compatibility simulation and evaluation; and
firstly, performing antenna performance simulation and evaluation, secondly, performing antenna layout simulation and evaluation, and finally, performing aircraft external electromagnetic environment simulation and evaluation.
4. The method for simulating electromagnetic environmental effects of aircraft design according to claim 2, wherein in step S4, the sequence and progressive relationship of the aircraft electromagnetic environmental effect simulation and evaluation items include:
firstly, performing shielding effectiveness simulation and evaluation and aircraft external electromagnetic environment simulation and evaluation, secondly, performing aircraft internal electromagnetic environment simulation and evaluation, and finally performing electromagnetic radiation to personnel hazard simulation and evaluation or electromagnetic radiation to ordnance hazard simulation and evaluation or electromagnetic radiation hazard simulation and evaluation.
5. The method for simulating electromagnetic environmental effects of aircraft design according to claim 2, wherein in step S4, the sequence and progressive relationship of the aircraft electromagnetic environmental effect simulation and evaluation items include:
firstly, lightning attachment point simulation and lightning partition are carried out, secondly lightning current distribution simulation and evaluation are carried out, then lightning direct effect simulation and evaluation are carried out, and finally lightning indirect effect simulation and evaluation are carried out.
6. The method for simulating electromagnetic environmental effects of aircraft design according to claim 2, wherein in step S4, the sequence and progressive relationship of the aircraft electromagnetic environmental effect simulation and evaluation items include:
firstly, simulating and evaluating the electromagnetic environment in the aircraft, and secondly, simulating and evaluating the radiation sensitivity characteristics of the wire harness.
7. The method for simulating electromagnetic environmental effects of aircraft design according to claim 2, wherein in step S4, the sequence and progressive relationship of the aircraft electromagnetic environmental effect simulation and evaluation items include:
firstly, carrying out simulation and evaluation of radiation characteristics of the wire harnesses, and secondly, carrying out simulation and evaluation of crosstalk characteristics among the wire harnesses.
8. The method for simulating electromagnetic environmental effects of aircraft design according to claim 2, wherein in step S4, the sequence and progressive relationship of the aircraft electromagnetic environmental effect simulation and evaluation items include:
firstly, simulation and evaluation of interference coupling of antennas among airplane formation and simulation and evaluation of electromagnetic environment among airplane formation are carried out, and secondly, simulation and evaluation of adaptability of complex electromagnetic environment are carried out.
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| 机载无线电设备兼容性内场试验方法;张丙伟;吴惠明;江志平;;电讯技术(12);全文 * |
| 民用飞机电磁环境效应设计偏离控制管理浅析;陈洁;宁敏;;科技创新导报(16);全文 * |
| 现代军机飞行仿真系统的研究;黄安祥,刘长华,陈宗基,李明,贾荣珍;系统仿真学报(02);全文 * |
| 飞机电子信息系统电磁兼容顶层量化的仿真模型设计研究;侯艳红;;自动化与仪器仪表(10);全文 * |
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