Aircraft lightning partitioning method based on multi-method correction
By using similarity comparison analysis, simulation models, and multi-feature experiments, the adaptability problem of traditional aircraft lightning zoning methods has been solved, enabling rapid and accurate lightning zoning design and reducing resource consumption and protection costs.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-12-31
- Publication Date
- 2026-04-10
AI Technical Summary
Traditional aircraft lightning zoning methods are difficult to adapt to aircraft with different aerodynamic shapes, and lightning attachment tests consume too many resources and time, which cannot meet the needs of rapid model development.
A preliminary scheme was developed by combining similarity comparison analysis with model development experience. A simulation model was constructed to simulate lightning effects, and the scheme was verified through lightning attachment tests using multiple methods and features. Finally, the lightning zoning scheme for the aircraft was determined.
It achieves rapid, efficient, and accurate aircraft lightning zoning, reducing resource consumption and overall protection costs, and adapting to the development needs of aircraft models with different aerodynamic shapes.
Smart Images
Figure CN121835191A_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The application belongs to the technical field of aircraft lightning protection, and particularly relates to an aircraft lightning partitioning method based on multi-method correction. BACKGROUND
[0002] Lightning is a long-distance instantaneous discharge in thunderstorm weather, which is a natural phenomenon with extremely strong destructive power, and seriously threatens the flight safety and task execution of an aircraft. Therefore, aircraft lightning protection design needs to be carried out, and the core of the aircraft lightning protection design is to carry out aircraft lightning partitioning design.
[0003] The traditional aircraft lightning partitioning method mainly refers to the partitioning cases of similar aerodynamic shape aircraft provided in the relevant standard specifications, and forms an aircraft lightning partitioning scheme according to the lightning attachment law by carrying out lightning attachment tests on a full-metal model. However, with the increase of aircraft models, the aerodynamic shapes of current aircrafts are different, and the partitioning cases provided in the existing standard specifications have been difficult to meet the needs of similarity comparison analysis. At the same time, the lightning attachment test occupies too much time period and resources. In the early stage of development of each aircraft model, only similarity analysis and test cannot cope with the constantly iterating aircraft aerodynamic shape scheme. SUMMARY
[0004] The purpose of the present application is to provide an aircraft lightning partitioning method based on multi-method correction to solve or alleviate at least one problem in the background art.
[0005] The technical solution of the present application is: an aircraft lightning partitioning method based on multi-method correction, comprising:
[0006] Step S1, forming an aircraft lightning partitioning preliminary scheme based on similarity comparison analysis and combining model development experience;
[0007] Step S2, constructing a simulation model based on the aircraft lightning partitioning preliminary scheme, carrying out lightning action simulation based on the simulation model, and iteratively obtaining an aircraft lightning partitioning scheme by combining model development experience on the aircraft lightning partitioning preliminary scheme;
[0008] Step S3, verifying the aircraft lightning partitioning scheme by lightning attachment test, and determining the final aircraft lightning partitioning scheme by combining attachment law analysis.
[0009] Preferably, the process of step S2, constructing a simulation model based on the aircraft lightning partitioning preliminary scheme, carrying out lightning action simulation based on the simulation model, and iteratively obtaining an aircraft lightning partitioning scheme by combining model development experience on the aircraft lightning partitioning preliminary scheme, comprises:
[0010] optimizing the original numerical model of the aircraft according to the aircraft lightning partitioning preliminary scheme, and constructing a multi-impedance aircraft model with typical structural material characteristics.
[0011] Based on the electrostatic field distribution theory, cloud charge aggregation simulation is carried out, a simulation model with charged cloud layer, ground and aircraft is constructed, the induced field intensity distribution of the aircraft body surface under different flight attitudes is obtained, and the lightning attachment area is preliminarily predicted through the field intensity threshold division;
[0012] Based on the multi-physical field fluid calculation method, lightning leader formation simulation is carried out, the formation process and path of the lightning downward leader and the induced field intensity distribution of the aircraft body surface are obtained, the induced field intensity distribution of the aircraft body surface under different flight attitudes is obtained, and the lightning attachment area is preliminarily predicted through the field intensity threshold division;
[0013] When the initial attachment area of the lightning current injection including the nose and the wing tip is obtained, the transmission path of the lightning current on the surface layer of the aircraft under different attitudes is obtained to obtain the distribution of the low impedance current path of the aircraft, the hovering area of the lightning current on the trailing edge of the aircraft is divided into 1B area, and the lightning attachment area of the aircraft is obtained.
[0014] Preferably, the lightning attachment test is based on the test method provided by the relevant standard specification, combined with the aerodynamic shape, structural material properties and characteristics of the aircraft, and a multi-method, multi-characteristic lightning attachment test is carried out.
[0015] Preferably, the multi-method, multi-characteristic lightning attachment test comprises:
[0016] Full-metal aircraft model test based on standard method;
[0017] Comparison test of electrode position offset;
[0018] Comparison test of different discharge gaps;
[0019] Comparison test of aircraft model with typical material properties;
[0020] Comparison test of aircraft model with typical structure characteristics.
[0021] Preferably, the aircraft model is a scaled model, and the scale of the scaled model is not less than 1:20.
[0022] The method of the present application can quickly and efficiently form a preliminary lightning zoning scheme for an aircraft based on relevant domestic and foreign standard specifications and existing lightning zoning schemes for similar aerodynamic shapes of aircraft, and can simulate and verify different versions of aerodynamic shape schemes at the initial stage of type development based on lightning action simulation of the whole process, quickly complete the iteration of the preliminary lightning zoning scheme for the aircraft, and has high efficiency, precision and economy; Based on the lightning attachment test of multiple methods and multiple characteristics, the partition scheme can be checked and corrected for the local characteristics of the aircraft, precise input is provided for lightning protection design of the aircraft, and the overall protection cost of the aircraft is greatly reduced. BRIEF DESCRIPTION OF DRAWINGS
[0023] In order to more clearly illustrate the technical solutions provided by the present application, the following will briefly introduce the drawings. Obviously, the drawings described below are only some embodiments of the present application.
[0024] Figure 1 The figure is a schematic diagram of the aircraft lightning zoning method of the present application.
[0025] Figure 2 The figure is a schematic diagram of the lightning attachment test of the electrode position offset of an embodiment of the present application.
[0026] Figure 3 The figure is a schematic diagram of the flat plate electrode lightning attachment test of different discharge gaps of an embodiment of the present application. DETAILED DESCRIPTION
[0027] In order to make the purpose, technical solutions and advantages of the present application more clear, the following will describe the technical solutions in the embodiments of the present application in more detail in combination with the drawings in the embodiments of the present application.
[0028] The present application provides an aircraft lightning zoning method, which enriches the traditional standard-based, single aircraft lightning zoning method into an aircraft lightning zoning technical system covering similarity comparison analysis means, whole-process lightning action simulation means and multi-feature lightning attachment test means.
[0029] As shown in Figure 1 The aircraft lightning zoning method based on multi-method correction provided by the present application includes the following steps:
[0030] Step S1, forming an initial aircraft lightning zoning scheme based on similarity comparison analysis and combined with model development experience.
[0031] In the initial stage of model development, based on the original numerical model of the aircraft, the similarity comparison analysis is performed on the lightning zoning cases of similar aerodynamic shape aircrafts provided in the relevant domestic and foreign lightning protection standards and specifications such as SAE ARP5414, GJB2639 and HB8454 and formed at home and abroad, and the size and proportion of the regions such as the aircraft nose, fuselage, tail and wing tip are evaluated.
[0032] Based on the results of the similarity comparison analysis and combined with the model development experience, some typical structure and material regions are divided into lightning attachment regions, for example, the transparent parts, rudder surfaces, glass antenna covers and composite skin, etc. The above-mentioned typical structures and materials are divided into aircraft lightning zoning regions, so as to form an initial aircraft lightning zoning scheme, which is used to support the lightning protection development in the aircraft scheme and preliminary design stage.
[0033] Step S2, based on the preliminary scheme of aircraft lightning zoning, a simulation model is constructed, based on which lightning action simulation is carried out, and the preliminary scheme of aircraft lightning zoning is iterated to obtain the aircraft lightning zoning scheme in combination with the experience of model development.
[0034] Lightning action simulation needs to go through all links of the aircraft lightning process, i.e. cloud charge accumulation, lightning downward leader approaching the aircraft, aircraft induction generating upward leader, lightning leader connection and forming a channel, and large current conduction sweeping and hovering process after lightning reaches the aircraft.
[0035] Based on this, the simulation model is constructed based on the preliminary scheme of aircraft lightning zoning, and the lightning action simulation based on the simulation model includes the following processes:
[0036] 1) According to the preliminary scheme of aircraft lightning zoning, the original numerical model of the aircraft is optimized to construct a multi-impedance aircraft model with typical structural material characteristics;
[0037] In order to consider the simulation calculation efficiency, the protrusions with small size on the surface of the aircraft model can be simplified;
[0038] The initial attitude of the aircraft model is pitch 0°, roll 0°, and yaw 0°;
[0039] 2) Based on the electrostatic field distribution theory, cloud charge accumulation simulation is carried out to construct a simulation model with charged cloud layer, ground and aircraft, and through obtaining the induced field strength distribution on the surface of the aircraft under different flight attitudes, the preliminary prediction of lightning attachment area is carried out through field strength threshold division;
[0040] 3) Lightning leader formation simulation based on multi-physical field fluid calculation method is carried out to obtain the formation process and path of lightning downward leader and the induced field strength distribution on the surface of the aircraft, and through obtaining the induced field strength distribution on the surface of the aircraft under different flight attitudes, the preliminary prediction of lightning attachment area is carried out through field strength threshold division;
[0041] 4) When the lightning current is injected into the initial attachment area including the nose and wing tip, the transmission path of the lightning current on the surface layer of the aircraft under different attitudes is obtained to obtain the distribution of the low impedance current resistance path of the aircraft, and the hovering area of the lightning current on the trailing edge of the aircraft is divided into 1B area, so as to further converge the aircraft lightning attachment area.
[0042] Based on the results of lightning action simulation, in combination with the experience of model development, the aircraft lightning zoning scheme is further iterated to support the lightning protection development in the preliminary design stage of the aircraft.
[0043] Step S3, the aircraft lightning zoning scheme is verified through lightning attachment test, and the final aircraft lightning zoning scheme is determined in combination with the attachment law analysis.
[0044] The lightning attachment test should be based on the test methods provided in the relevant domestic and foreign standards and specifications such as SAE ARP5416 A2013 and GJB 3567, combined with the characteristics of the aerodynamic shape and structural material properties of the aircraft, and multi-method and multi-feature lightning attachment tests should be carried out. The specific content is as follows:
[0045] 1) Process and manufacture test pieces (aircraft scale models): The scale of the test pieces should not be less than 1:20, and the surface gaps should be treated to make the surface as complete and smooth as possible;
[0046] 2) Carry out full-metal model tests based on standard methods;
[0047] 3) Carry out multi-method and multi-feature exploratory tests to modify the test results based on standard methods for local areas of the aircraft:
[0048] 31) Carry out comparative tests of electrode position offset;
[0049] 32) Carry out comparative tests of different discharge gaps: 50m, 60m, 70m, …;
[0050] 33) Carry out comparative tests of models with typical material properties: transparent parts, composite materials, …;
[0051] 34) Carry out comparative tests of models with typical structural properties: rudders, radars, ….
[0052] For example Figure 2 and Figure 3 The lightning attachment test schematic diagrams of different discharge electrodes provided in this embodiment of the application are shown in Figure 2 In the rod electrode lightning attachment test shown in Figure 3 In the plate electrode lightning attachment test shown in
[0053] The method of the present application can quickly and efficiently form a preliminary lightning partition scheme of an aircraft based on relevant domestic and foreign standards and existing similar aerodynamic configuration aircraft lightning partition schemes, can simulate and verify different versions of aerodynamic configuration schemes in the early stage of model development based on whole-process lightning action simulation, quickly complete iteration of the preliminary lightning partition scheme of the aircraft, and has high efficiency, accuracy and economy; lightning attachment tests based on multiple methods and multiple characteristics can check and correct the partition scheme according to the local characteristics of the aircraft, provide accurate input for the lightning protection design of the aircraft, and greatly reduce the overall protection cost of the aircraft.
[0054] The above is only a specific embodiment of the present application, but the protection scope of the present application is not limited thereto, any person skilled in the art can easily think of changes or replacements within the technical range disclosed in the present application, which should be covered within the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.
Claims
1. A multi-method correction method for aircraft lightning zoning, characterized in that, include: Step S1: Based on similarity comparison analysis and combined with model development experience, a preliminary scheme for aircraft lightning zoning is formed; Step S2: Construct a simulation model based on the preliminary aircraft lightning zoning scheme, conduct lightning action simulation based on the simulation model, and iterate the preliminary aircraft lightning zoning scheme based on model development experience to obtain the aircraft lightning zoning scheme. Step S3: Verify the aircraft lightning zoning scheme through lightning adhesion tests, and determine the final aircraft lightning zoning scheme by combining adhesion pattern analysis.
2. The aircraft lightning zoning method based on multi-method correction as described in claim 1, characterized in that, Step S2, constructing a simulation model based on the preliminary aircraft lightning zoning scheme, conducting lightning effect simulations based on the simulation model, and iteratively obtaining the aircraft lightning zoning scheme by combining model development experience, includes the following steps: Based on the preliminary scheme of aircraft lightning zoning, the original aircraft digital model was optimized and processed to construct a multi-impedance aircraft model with typical structural material characteristics. Based on the electrostatic field distribution theory, cloud charge accumulation simulation was carried out. A simulation model with charged clouds, ground and aircraft was constructed. By obtaining the induced field strength distribution on the surface of the aircraft under different flight attitudes, the lightning attachment area was preliminarily predicted by dividing the field strength threshold. We conducted a simulation of lightning leader formation based on multiphysics fluid computation method to obtain the formation process and path of the lightning downlink leader and the distribution of induced field strength on the aircraft surface. By obtaining the distribution of induced field strength on the aircraft surface under different flight attitudes, we preliminarily predicted the lightning attachment area by dividing the field strength threshold. When obtaining the initial attachment area of lightning current injection, including the nose and wingtip, the transmission path of lightning current on the aircraft surface under different attitudes is obtained to obtain the distribution of low impedance withstand current path of the aircraft. The hovering area of lightning current at the trailing edge of the aircraft is divided into region 1B, and the lightning attachment area of the aircraft is obtained by convergence.
3. The aircraft lightning zoning method based on multi-method correction as described in claim 2, characterized in that, The lightning adhesion test is based on the test methods provided by relevant standards and specifications, and takes into account the characteristics of the aircraft's aerodynamic shape and structural material properties to carry out lightning adhesion tests with multiple methods and characteristics.
4. The aircraft lightning zoning method based on multi-method correction as described in claim 3, characterized in that, The multi-method, multi-feature lightning adhesion test includes: Testing of all-metal aircraft models based on standard methods; Comparative test of electrode position offset; Comparative tests of different discharge air gaps; Comparative tests of typical material properties were conducted on the aircraft model. Comparative tests of aircraft models with typical structural characteristics.
5. The aircraft lightning zoning method based on multi-method correction as described in claim 4, characterized in that, The aircraft model is a scaled-down model, with a scale of not less than 1:20.