A simulation evaluation method for discharge effect of aircraft electrostatic discharger

Abstract

The present application belongs to the field of electrostatic protection and electromagnetic compatibility technology, and in particular, relates to a method for simulating and evaluating the discharge effect of an aircraft electrostatic discharger. The method for simulating and evaluating the discharge effect of an aircraft electrostatic discharger of the present application uses electromagnetic modeling and simulation methods to carry out an evaluation of the effect of an aircraft electrostatic discharger, is not limited by the development progress of the electrostatic discharger and the production of test pieces, and can perform a large number of iterative optimizations on the electrostatic discharger design at a very low cost; the method is applicable to all fixed-wing aircraft platforms, and belongs to the verification of the discharge effect of the entire aircraft after the electrostatic discharger is installed, and can be used as a basis for evaluating the electrostatic protection design of the entire aircraft.

Description

Technical Field

[0001] The present application belongs to the technical field of electrostatic protection and electromagnetic compatibility, and in particular relates to a method for simulating and evaluating the discharge effect of an aircraft electrostatic discharger. Background Art

[0002] Aircraft electrostatic dischargers are used to discharge and control the static charge accumulated during the flight of an aircraft. The effective discharge of electrostatic dischargers is a necessary means for aircraft electrostatic protection and electromagnetic compatibility design.

[0003] The existing aircraft electrostatic discharger discharge effect evaluation is mainly based on relevant standards to conduct discharge tests on rectangular templates, and the discharge effect is evaluated based on the test results. The shortcomings are that on the one hand, the discharge effect of the electrostatic discharger is affected by the shape of the aircraft and the installation position, and it is difficult to truly reflect the discharge effect of the electrostatic discharger after it is installed on the aircraft. On the other hand, the design of the electrostatic discharger is a complex iterative process, and relying solely on experimental tests leads to high costs.

[0004] Therefore, it is desired to have a technical solution to overcome or at least alleviate at least one of the above-mentioned defects of the prior art. Summary of the invention

[0005] The purpose of the present application is to provide a method for simulating and evaluating the discharge effect of an aircraft electrostatic discharger to solve at least one problem existing in the prior art.

[0006] The technical solution of this application is:

[0007] A discharge effect simulation evaluation method for an aircraft electrostatic discharger, comprising:

[0008] Step 1:

[0009] S101, arranging a first metal body Y1 at a first predetermined distance from the tip of the aircraft body in a normal direction;

[0010] S102, arrange a current density monitor at the tip of the aircraft body to configure an electric potential for the aircraft body The potential of the first metal body Y1 is

[0011] S103, start electromagnetic simulation, and obtain the discharge current density distribution Ψ at the tip of the aircraft body 1F ;

[0012] S104, current density distribution of discharge to the aircraft body tip Ψ 1F Perform surface integration to calculate the electric potential and The corresponding total discharge current is J F ;

[0013] S105. Change the aircraft body configuration potential and the potential of the first metal body Y1 Repeat steps S102-S105 to obtain multiple sets of potentials and Total discharge current J under combination F_i , where i represents the i-th group of simulations;

[0014] Step 2:

[0015] S201, installing an electrostatic discharger on the aircraft body, and arranging a second metal body Y2 at a second predetermined distance from the trailing edge of the electrostatic discharger in the normal direction;

[0016] S202. Arrange a current density monitor at the trailing edge of the electrostatic discharger to configure an electric potential for the aircraft body. The potential of the second metal body Y2 is

[0017] S203, start electromagnetic simulation to obtain the discharge current density distribution Ψ at the trailing edge of the electrostatic discharger 2J ;

[0018] S204, the discharge current density distribution Ψ at the trailing edge of the electrostatic discharger 2J Perform surface integration to calculate the electric potential and The corresponding total discharge current is J Q ;

[0019] S205, change the aircraft body configuration potential and the potential of the second metal body Y2 Repeat steps S202-S205 to obtain multiple sets of potentials and Total discharge current J under combination Q_i , where i represents the i-th group of simulations;

[0020] Step 3: Based on multiple sets of potentials and Total discharge current J under combination F_i , and multiple sets of potentials and Total discharge current J under combination Q_i The discharge current diagrams under different excitation voltages are plotted, and the discharge effect of the aircraft electrostatic discharger is evaluated based on the discharge current diagrams under different excitation voltages.

[0021] In at least one embodiment of the present application, the first predetermined distance d1 and the second predetermined distance d2 are: d1<200 mm, d2<200 mm.

[0022] In at least one embodiment of the present application, the first metal body and the second metal body are both discs with a diameter of not less than 200 mm.

[0023] In at least one embodiment of the present application, in step three, evaluating the discharge effect of the aircraft electrostatic discharger according to the discharge current diagram under different excitation voltages includes:

[0024] If the discharge current of the aircraft electrostatic discharger under the typical excitation voltage is larger and the excitation voltage under the typical discharge current is smaller, it is determined that the discharge effect of the aircraft electrostatic discharger meets the design requirements.

[0025] The invention has at least the following beneficial technical effects:

[0026] The discharge effect simulation evaluation method of an aircraft electrostatic discharger of the present application utilizes emerging electromagnetic simulation means to conduct a simulation evaluation of the discharge effect of the aircraft electrostatic discharger on the entire aircraft, and verifies the discharge effect of the electrostatic discharger by comparing the discharge current between the tip of the aircraft body and the electrostatic discharger under different aircraft body potentials. This method is convenient and efficient, and has broad application prospects in the field of aircraft electrostatic protection design. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 is a diagram of a simulation scenario of an aircraft electrostatic discharger according to an embodiment of the present application;

[0028] Figure 2 It is a schematic diagram of discharge simulation results of an aircraft wing electrostatic discharger according to one embodiment of the present application. DETAILED DESCRIPTION

[0029] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the embodiment of this application will be described in more detail below in conjunction with the drawings in the embodiment of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described embodiments are part of the embodiments of this application, not all of them. The embodiments described below with reference to the drawings are exemplary and are intended to be used to explain this application, and should not be construed as limitations on this application. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The embodiments of this application are described in detail below in conjunction with the drawings.

[0030] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the scope of protection of the present application.

[0031] The following is combined with Figure 1 to Figure 2 This application is described in further detail.

[0032] The present application provides a method for simulating and evaluating the discharge effect of an aircraft electrostatic discharger, comprising the following steps:

[0033] Step 1:

[0034] S101, arranging a first metal body Y1 at a first predetermined distance from the tip of the aircraft body in a normal direction;

[0035] S102, arrange a current density monitor at the tip of the aircraft body to configure an electric potential for the aircraft body The potential of the first metal body Y1 is

[0036] S103, start electromagnetic simulation, and obtain the discharge current density distribution Ψ at the tip of the aircraft body 1F ;

[0037] S104, current density distribution of discharge to the aircraft body tip Ψ 1F Perform surface integration to calculate the electric potential and The corresponding total discharge current is J F ;

[0038] S105. Change the aircraft body configuration potential and the potential of the first metal body Y1 Repeat steps S102-S105 to obtain multiple sets of potentials and Total discharge current J under combination F_i , where i represents the i-th group of simulations;

[0039] Step 2:

[0040] S201, installing an electrostatic discharger on the aircraft body, and arranging a second metal body Y2 at a second predetermined distance from the trailing edge of the electrostatic discharger in the normal direction;

[0041] S202. Arrange a current density monitor at the trailing edge of the electrostatic discharger to configure an electric potential for the aircraft body. The potential of the second metal body Y2 is

[0042] S203, start electromagnetic simulation to obtain the discharge current density distribution Ψ at the trailing edge of the electrostatic discharger 2J ;

[0043] S204, the discharge current density distribution Ψ at the trailing edge of the electrostatic discharger 2J Perform surface integration to calculate the electric potential and The corresponding total discharge current is J Q ;

[0044] S205, change the aircraft body configuration potential and the potential of the second metal body Y2 Repeat steps S202-S205 to obtain multiple sets of potentials and Total discharge current J under combination Q_i , where i represents the i-th group of simulations;

[0045] Step 3: Based on multiple sets of potentials and Total discharge current J under combination F_i , and multiple sets of potentials and Total discharge current J under combination Q_i The discharge current diagrams under different excitation voltages are plotted, and the discharge effect of the aircraft electrostatic discharger is evaluated based on the discharge current diagrams under different excitation voltages.

[0046] In a preferred embodiment of the present application, the first predetermined distance d1 and the second predetermined distance d2 are: d1<200 mm, d2<200 mm; the first metal body and the second metal body are both discs with a diameter of not less than 200 mm. In this embodiment, d1=d2=152 mm; the first metal body and the second metal body are preferably discs with a diameter of 400 mm.

[0047] The discharge effect simulation evaluation method of the aircraft electrostatic discharger of the present application, in step 3, the discharge effect of the aircraft electrostatic discharger is evaluated according to the discharge current diagram under different excitation voltages, including:

[0048] If the discharge current of the aircraft electrostatic discharger under the typical excitation voltage is larger and the excitation voltage under the typical discharge current is smaller, it is determined that the discharge effect of the aircraft electrostatic discharger meets the design requirements.

[0049] In a specific embodiment of the present application,

[0050] A first metal disk Y1 with a diameter r1 = 400 mm is arranged at a position d1 = 152 mm away from the tip of the aircraft body in the normal direction;

[0051] A current density monitor is placed at the tip of the aircraft body to configure the aircraft body with an electric potential The potential of the first metal disk Y1 is

[0052] Start electromagnetic simulation and obtain the discharge current density distribution Ψ at the tip of the aircraft body 1F ;

[0053] The current density distribution of the discharge to the aircraft body tip 1F Perform surface integration to calculate the electric potential and The corresponding total discharge current is J F =70μA;

[0054] Changing the aircraft body configuration potential and the potential of the first metal body Y1 Repeat the above steps to obtain a series of potentials and Total discharge current J under combination F_i , where i represents the i-th group of simulations;

[0055] An electrostatic discharger is installed on the aircraft body, and a second metal disk Y2 with a diameter of r2 = 400 mm is arranged at a distance d2 = 152 mm from the trailing edge of the electrostatic discharger in the normal direction;

[0056] A current density monitor is placed at the trailing edge of the electrostatic discharger to configure the aircraft body with an electric potential The potential of the second metal disk Y2 is

[0057] Start electromagnetic simulation and obtain the discharge current density distribution Ψ at the trailing edge of the electrostatic discharger 2J ;

[0058] The discharge current density distribution Ψ at the trailing edge of the electrostatic discharger 2J Perform surface integration to calculate the electric potential and The corresponding total discharge current is J Q =0.02μA;

[0059] Changing the aircraft body configuration potential and the potential of the second metal body Y2 Repeat the above steps to obtain a series of potentials and Total discharge current J under combination Q_i, where i represents the i-th group of simulations;

[0060] According to multiple potential and Total discharge current J under combination F_i , and multiple sets of potentials and Total discharge current J under combination Q_i Draw a graph of the discharge current at different excitation voltages, such as Figure 2 As shown, under the excitation voltage of 30kV, the discharge current J of the electrostatic discharger Q_i =2.8*10^3μA, the discharge current at the wing tip is 17.4μA, and the discharge current of the electrostatic discharger is 160 times that of the wing tip; under a discharge current of 50μA, the discharge voltage at the wing tip is about 120kV, and the discharge voltage of the electrostatic discharger is about 8kV. The discharge voltage of the electrostatic discharger is less than one tenth of the discharge voltage at the wing tip. The electrostatic discharger of the aircraft has a good discharge effect and meets the discharge requirements of the aircraft's accumulated static charge.

[0061] The aircraft electrostatic discharger discharge effect simulation evaluation method of the present application uses electromagnetic modeling and simulation methods to carry out aircraft electrostatic discharger effect evaluation. It is not limited by the electrostatic discharger development progress and test piece production, and can perform a large number of iterative optimizations on the electrostatic discharger design at a very low cost. The method is applicable to all fixed-wing aircraft platforms, and is a verification of the discharge effect of the entire aircraft after the electrostatic discharger is installed, and can serve as a basis for the evaluation of the electrostatic protection design of the entire aircraft.

[0062] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A method for simulating and evaluating the discharge effect of an aircraft electrostatic discharger, characterized in that: include: Step 1: S101, arranging a first metal body Y1 at a first predetermined distance from the tip of the aircraft body in a normal direction; S102, arrange a current density monitor at the tip of the aircraft body to configure an electric potential for the aircraft body The potential of the first metal body Y1 is S103, start electromagnetic simulation, and obtain the discharge current density distribution Ψ at the tip of the aircraft body 1F ; S104, current density distribution of discharge to the aircraft body tip Ψ 1F Perform surface integration to calculate the electric potential and The corresponding total discharge current is J F ; S105. Change the aircraft body configuration potential and the potential of the first metal body Y1 Repeat steps S102-S105 to obtain multiple sets of potentials and Total discharge current J under combination F_i , where i represents the i-th group of simulations; Step 2: S201, installing an electrostatic discharger on the aircraft body, and arranging a second metal body Y2 at a second predetermined distance from the trailing edge of the electrostatic discharger in the normal direction; S202. Arrange a current density monitor at the trailing edge of the electrostatic discharger to configure an electric potential for the aircraft body. The potential of the second metal body Y2 is S203, start electromagnetic simulation to obtain the discharge current density distribution Ψ at the trailing edge of the electrostatic discharger 2J ; S204, the discharge current density distribution Ψ at the trailing edge of the electrostatic discharger 2J Perform surface integration to calculate the electric potential and The corresponding total discharge current is J Q ; S205, change the aircraft body configuration potential and the potential of the second metal body Y2 Repeat steps S202-S205 to obtain multiple sets of potentials and Total discharge current J under combination Q_i , where i represents the i-th group of simulations; Step 3: Based on multiple sets of potentials and Total discharge current J under combination F_i , and multiple sets of potentials and Total discharge current J under combination Q_i The discharge current diagrams under different excitation voltages are plotted, and the discharge effect of the aircraft electrostatic discharger is evaluated based on the discharge current diagrams under different excitation voltages.

2. The discharge effect simulation evaluation method of an aircraft electrostatic discharger according to claim 1, characterized in that: The first predetermined distance d1 and the second predetermined distance d2 are: d1<200 mm, d2<200 mm.

3. The discharge effect simulation evaluation method of an aircraft electrostatic discharger according to claim 2, characterized in that: The first metal body and the second metal body are both discs with a diameter of not less than 200 mm.

4. The discharge effect simulation evaluation method of an aircraft electrostatic discharger according to claim 3 is characterized in that: In step three, the evaluation of the discharge effect of the aircraft electrostatic discharger according to the discharge current diagram under different excitation voltages includes: If the discharge current of the aircraft electrostatic discharger under the typical excitation voltage is larger and the excitation voltage under the typical discharge current is smaller, it is determined that the discharge effect of the aircraft electrostatic discharger meets the design requirements.

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