Method for designing layout of aircraft electrostatic discharge device

Abstract

The aircraft electrostatic discharge device layout design method disclosed by the application comprises the following steps: step 1, calculating and obtaining the total deposited static current of the aircraft; step 2, calculating the number of electrostatic discharge devices required to be arranged on the aircraft according to the total deposited static current; step 3, carrying out simulation of the distribution of the deposited static of the aircraft to determine the final electrostatic discharge device arrangement area and the number of areas; step 4, forming multiple preliminary layout schemes of the full-aircraft electrostatic discharge device according to the number of electrostatic discharge devices and the number of areas; step 5, taking the total discharge current I Q as the judgment standard, determining the layout design scheme of the full-aircraft electrostatic discharge device; and step 6, evaluating the rationality of the full-aircraft electrostatic discharge device layout scheme to obtain the final layout scheme of the full-aircraft electrostatic discharge device. The aircraft electrostatic discharge device layout design method can realize balanced discharge or maximum deposited static discharge of multiple electrostatic discharge devices.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of electromagnetic compatibility, and particularly relates to a layout design method of an aircraft electrostatic discharge device. BACKGROUND

[0002] The aircraft electrostatic discharge device is used for discharging and controlling accumulated static electricity during aircraft flight, and effective discharge of the electrostatic discharge device is a necessary means for aircraft electrostatic protection and aircraft electromagnetic compatibility design. The layout of the aircraft electrostatic discharge device on the aircraft has long relied on engineering experience, and multiple electrostatic discharge devices are arranged at a spacing of 300 mm or more on the rear edge of the aircraft wing surface. The shape of the aircraft directly affects the distribution of deposited static electricity on the whole aircraft and the electric field intensity distribution of the tip of the electrostatic discharge device, and further affects the deposited static electricity discharge effect of the electrostatic discharge device. The existing layout design method of the aircraft electrostatic discharge device is difficult to evaluate the deposited static electricity discharge effect of multiple electrostatic discharge devices of the aircraft. SUMMARY

[0003] The purpose of the application is to provide a layout design method of an aircraft electrostatic discharge device, which can realize balanced discharge or maximum deposited static electricity discharge of multiple electrostatic discharge devices.

[0004] The technical solution adopted by the application is that the layout design method of the aircraft electrostatic discharge device comprises the following steps:

[0005] Step 1, calculating and obtaining the total deposited static electricity current of the aircraft;

[0006] Step 2, calculating the number of electrostatic discharge devices needed to be arranged on the aircraft according to the total deposited static electricity current;

[0007] Step 3, carrying out simulation of the deposited static electricity distribution of the aircraft to determine the final electrostatic discharge device arrangement area and the number of areas;

[0008] Step 4, forming multiple preliminary layout schemes of the whole aircraft electrostatic discharge device according to the number of electrostatic discharge devices and the number of areas;

[0009] Step 5, taking the total discharge current I Q Maximum or balanced discharge of the whole aircraft electrostatic discharge device as the judgment standard, to determine the layout design scheme of the whole aircraft electrostatic discharge device;

[0010] Step 6, evaluating the rationality of the layout scheme of the whole aircraft electrostatic discharge device to obtain the final layout scheme of the whole aircraft electrostatic discharge device.

[0011] The application has the following characteristics:

[0012] Step 1 is specifically: calculating and obtaining the total deposited static electricity current of the aircraft according to formula (1) or (2);

[0013] I t = q p vc A eff (1) ;

[0014] wherein, q p Q is the storage charge of a single particle, unit: c / p; c ρ is the particle concentration in unit volume, unit: p / m 3 ; A eff S is the frontal surface area of the aircraft, unit: m 2 ; v V is the speed of the aircraft, unit: m / s;

[0015] I t =I c ×A eff x v / 600 (2) ;

[0016] wherein, I c I is the charging current density, unit: μA / m 2 ; V is the flight speed, unit: knots; A eff S is the frontal surface area of the aircraft, unit: m 2 .

[0017] Step 2 is specifically: according to the single electrostatic discharge device discharge index I q and the total deposited electrostatic current of the aircraft I t , the number of electrostatic discharge devices required to be arranged by the aircraft is calculated N ,

[0018] N 1= I t / I q (3) ;

[0019] N Take the smallest even number greater than N 1.

[0020] Step 3 is specifically: developing an aircraft deposition static electricity distribution simulation, according to the electric field intensity distribution of the aircraft, selecting the area with the largest electric field distribution at the rear edge of the aircraft as the static electricity discharger arrangement area, excluding the area where the structural material is not suitable for arranging the static electricity discharger and the area where other airborne equipment has been arranged in the static electricity discharger arrangement area, and the remaining area is the final static electricity discharger arrangement area and the number of areas M .

[0021] Step 4 is specifically: distributing N static electricity dischargers to M static electricity discharger arrangement areas, if N / M >2, then 2 static electricity dischargers should be arranged in each static electricity discharger arrangement area to form multiple full-aircraft static electricity discharger preliminary layout schemes.

[0022] Step 5 is specifically: for each full-aircraft static electricity discharger preliminary layout scheme, taking the maximum number of static electricity dischargers arranged in one static electricity discharger arrangement area in the full-aircraft static electricity discharger preliminary layout scheme as Q ;

[0023] placing the first static electricity discharger in each static electricity discharger arrangement area, L A is the distance between the first static electricity discharger and the structural tip, L A is a value greater than 100 mm, and the T static electricity discharger is arranged inside the T +1 static electricity discharger, L T is the distance between the T static electricity discharger and the T +1 static electricity discharger, L T is a value greater than 100 mm, T =1, 2, …, Q ;

[0024] Simulation obtains the steady-state electric potential V of each static electricity discharger of the same aircraft I F and the total discharge current I Q , wherein F =1, 2, …, N , V is a value greater than 20 kV;

[0025] The full-aircraft static electricity discharger layout scheme is formed according to the judgment standard that the total discharge current I Q of the full-aircraft static electricity discharger layout scheme is the largest, and theL A and L T configuration.

[0026] or the full machine electrostatic discharge device layout scheme is selected as the judgment standard, in N F the standard deviation is less than the standard deviation limit value I F the total discharge current of the full machine electrostatic discharge device layout scheme is selected P Q the largest full machine electrostatic discharge device layout scheme, forming the aircraft full machine electrostatic discharge device layout scheme and the I A and L T configuration. L t

[0027] Step 6 is specifically: according to the aircraft full machine electrostatic discharge device layout scheme determined in step 5, simulation is obtained The steady-state potential of the aircraft I t V and the maximum discharge current of the electrostatic discharge device under the steady-state potential of the aircraft I Z , according to the steady-state potential of the aircraft V and the maximum discharge current of the electrostatic discharge device I Z evaluate the rationality of the aircraft full machine electrostatic discharge device layout scheme, get the final layout scheme of the aircraft full machine electrostatic discharge device.

[0028] The rationality of the aircraft full machine electrostatic discharge device layout scheme in step 6 is specifically: the steady-state potential of the aircraft V is less than or equal to 75kV ， the maximum discharge current of the electrostatic discharge device I Z is less than or equal to k I q , k is a correction coefficient, k is a value greater than 1, then the aircraft full machine electrostatic discharge device layout scheme is reasonable, as the final layout scheme of the aircraft full machine electrostatic discharge device; if V >75kV or I Z >k I q , select other aircraft full machine electrostatic discharge device layout scheme in step 5 and repeat step 6 until V is less than or equal to 75kV, I Z is less than or equal to k I q , forming the final layout scheme of the aircraft full machine electrostatic discharge device.

[0029] The beneficial effects of the present application are:

[0030] The aircraft electrostatic discharge device layout design method provided by the present application is based on electromagnetic modeling and simulation technology, and quantitatively simulates and evaluates deposition static discharge current and aircraft deposition static steady-state potential of various layout schemes of the aircraft electrostatic discharge device, optimizes the installation position of the aircraft electrostatic discharge device, and reduces the aircraft deposition static steady-state potential through balanced discharge design of the electrostatic discharge device. The design method is agile, efficient and accurate, and effectively supports quantitative design and evaluation of various aircraft electrostatic protection, can guide the design of aircraft electrostatic protection and the design of electrostatic discharge device indicators, and has a broad application prospect in the field of aircraft electrostatic protection design. BRIEF DESCRIPTION OF DRAWINGS

[0031] Figure 1 is a flowchart of the aircraft electrostatic discharge device layout design method of the present application;

[0032] Figure 2 is a configuration diagram of the isolation distance of the aircraft electrostatic discharge device layout area. DETAILED DESCRIPTION

[0033] The present application will be described in detail below in combination with the drawings and specific embodiments.

[0034] Example 1

[0035] The aircraft electrostatic discharge device layout design method proposed in this embodiment, as shown in Figure 1 , includes the following steps:

[0036] Step 1, calculate and obtain the total deposition static current of the aircraft;

[0037] Step 2, calculate the number of electrostatic discharge devices needed to be arranged according to the total deposition static current;

[0038] Step 3, carry out aircraft deposition static distribution simulation to determine the final electrostatic discharge device layout area and the number of areas;

[0039] Step 4, form multiple preliminary layout schemes of the aircraft electrostatic discharge device according to the number of electrostatic discharge devices and the number of areas;

[0040] Step 5, take the total discharge current I Q as the judgment standard, determine the layout design scheme of the aircraft electrostatic discharge device;

[0041] Step 6, evaluate the rationality of the aircraft electrostatic discharge device layout scheme, and obtain the final layout scheme of the aircraft electrostatic discharge device.

[0042] Embodiment 2

[0043] The aircraft electrostatic discharge device layout design method proposed in this embodiment, as shown in Figure 1 includes the following steps:

[0044] Step 1, calculate and obtain the total deposited static current of the aircraft;

[0045] Specifically, the total deposited static current of the aircraft is calculated and obtained according to formula (1) or (2);

[0046] I t = q p vc A eff (1);

[0047] wherein, q p Q is the storage charge of a single particle, unit: c / p; c ρ is the particle concentration in unit volume, unit: p / m 3 ; A eff S is the front surface area of the aircraft, unit: m 2 ; v V is the speed of the aircraft, unit: m / s;

[0048] I t =I c ×A eff x v / 600 (2);

[0049] wherein, I c I is the charging current density, unit: μA / m 2 ; V is the flight speed, unit: knots; A eff S is the front surface area of the aircraft, unit: m 2 ;

[0050] Step 2, calculate the number of electrostatic discharge devices needed to be arranged according to the total deposited static current;

[0051] Step 3, carry out simulation of the distribution of deposited static electricity of the aircraft to determine the final electrostatic discharge device arrangement area and the number of areas;

[0052] Step 4, form multiple preliminary layout schemes of the full-machine electrostatic discharge device according to the number of electrostatic discharge devices and the number of areas;

[0053] Step 5, take the total discharge current I QThe maximum or full-machine static discharge equalization discharge is taken as a judgment standard to determine the layout design scheme of the full-machine static discharge device.

[0054] Step 6, evaluating the rationality of the layout scheme of the full-machine static discharge device of the aircraft to obtain the final layout scheme of the full-machine static discharge device of the aircraft.

[0055] Embodiment 3

[0056] The layout design method of the aircraft static discharge device provided in the embodiment includes the following steps, as shown in the figure: Figure 1

[0057] Step 1, calculating and obtaining the total deposited static current of the aircraft;

[0058] Specifically, the total deposited static current of the aircraft is calculated and obtained according to formula (1) or (2);

[0059] I t = q p vc A eff (1);

[0060] wherein, q p Q is the storage charge of a single particle, unit: c / p; c ρ is the particle concentration in unit volume, unit: p / m 3 ; A eff S is the front end surface area of the aircraft, unit: m 2 ; v V is the speed of the aircraft, unit: m / s;

[0061] I t =I c ×A eff x v / 600 (2);

[0062] wherein, I c I is the charging current density, unit: μA / m 2 ; V is the flight speed, unit: knots; A eff S is the front end surface area of the aircraft, unit: m 2 ;

[0063] Step 2, calculating the number of static discharge devices needed to be arranged according to the total deposited static current;

[0064] Specifically, the number of static discharge devices needed to be arranged is calculated according to the discharge index of a single static discharge device I ​q And the total static current deposited on the aircraft I t Calculate the number of electrostatic dischargers that need to be installed on the aircraft. N ,

[0065] N 1= I t / I q (3);

[0066] N Take greater than N The smallest even number equal to 1;

[0067] Step 3: Conduct simulation of electrostatic distribution on the aircraft to determine the final electrostatic discharger placement area and number of areas;

[0068] Step 4: Based on the number of electrostatic dischargers and the number of areas, formulate several preliminary layout schemes for the electrostatic dischargers of the entire machine;

[0069] Step 5: Use the total discharge current I Q The maximum or balanced discharge of all electrostatic dischargers in the machine is used as the criterion to determine the layout design scheme of the electrostatic dischargers in the machine.

[0070] Step 6: Evaluate the rationality of the overall electrostatic discharger layout scheme of the aircraft to obtain the final layout scheme of the overall electrostatic discharger of the aircraft.

[0071] Example 4

[0072] The aircraft electrostatic discharger layout design method proposed in this embodiment, such as Figure 1 As shown, it includes the following steps:

[0073] Step 1: Calculate and obtain the total deposited electrostatic current of the aircraft;

[0074] Specifically, the total electrostatic current deposited on the aircraft is calculated and obtained according to formula (1) or (2);

[0075] I t = q p vc A eff (1);

[0076] in, q p Stored charge of a single particle, unit: c / p; c Particle concentration per unit volume, unit: p / m 3 ; A effS is the frontal surface area of the aircraft, unit: m 2 ; v V is the speed of the aircraft, unit: m / s;

[0077] I t =I c ×A eff x v / 600 (2);

[0078] wherein, I c I is the charging current density, unit: μA / m 2 ; V is the flight speed, unit: knots; A eff S is the frontal surface area of the aircraft, unit: m 2 ;

[0079] Step 2, according to the total deposited static electricity current, the number of static electricity dischargers arranged on the aircraft is calculated;

[0080] Specifically, according to the discharge index of a single static electricity discharger I q and the total deposited static electricity current of the aircraft I t , the number of static electricity dischargers arranged on the aircraft is calculated N ,

[0081] N 1= I t / I q (3);

[0082] N The smallest even number greater than 1 is taken; N

[0083] Step 3, the distribution simulation of the deposited static electricity of the aircraft is carried out to determine the final static electricity discharger arrangement area and the number of areas;

[0084] Specifically, the distribution simulation of the deposited static electricity of the aircraft is carried out, according to the electric field intensity distribution of the aircraft, the area with the largest electric field distribution at the trailing edge of the aircraft is selected as the static electricity discharger arrangement area, the area where the structural material is not suitable for arranging the static electricity discharger is excluded from the static electricity discharger arrangement area, the area where other airborne equipment has been arranged is excluded, and the remaining area is the final static electricity discharger arrangement area and the number of areas M ;

[0085] Step 4, according to the number of static electricity dischargers and the number of areas, a plurality of preliminary layout schemes of the static electricity dischargers of the whole aircraft are formed;

[0086] ​Step 5, total bleed current I Q The layout design scheme of the whole aircraft electrostatic discharge device is determined according to the maximum or whole machine electrostatic discharge device balanced discharge as the judgment standard.

[0087] Step 6, evaluate the rationality of the layout scheme of the whole aircraft electrostatic discharge device, and obtain the final layout scheme of the whole aircraft electrostatic discharge device.

[0088] Example 5

[0089] The aircraft electrostatic discharge device layout design method provided in the embodiment, as shown in the figure, includes the following steps: Figure 1

[0090] Step 1, calculate and obtain the total deposited static current of the aircraft;

[0091] Specifically, the total deposited static current of the aircraft is calculated and obtained according to formula (1) or (2);

[0092] I t = q p vc A eff (1);

[0093] Wherein, q p Q is the storage charge of a single particle, unit: c / p; c ρ is the particle concentration in unit volume, unit: p / m 3 ; A eff S is the front surface area of the aircraft, unit: m 2 ; v V is the speed of the aircraft, unit: m / s;

[0094] I t =I c ×A eff x v / 600 (2);

[0095] Wherein, I c I is the charging current density, unit: μA / m 2 ; V is the flight speed, unit: knots; A eff S is the front surface area of the aircraft, unit: m 2 ;

[0096] Step 2, calculate the number of electrostatic discharge devices needed to be arranged according to the total deposited static current; ​

[0097] Specifically, according to the single electrostatic discharge device discharge index I q And the total electrostatic current of the aircraft I t , the number of electrostatic discharge devices required to be arranged on the aircraft is calculated N ,

[0098] N 1= I t / I q (3);

[0099] N Take the smallest even number greater than 1; N

[0100] Step 3, carry out aircraft deposited electrostatic distribution simulation to determine the final electrostatic discharge device arrangement area and area number;

[0101] Specifically, the aircraft deposited electrostatic distribution simulation is carried out, according to the electric field intensity distribution of the aircraft, the area with the largest electric field distribution at the rear edge of the aircraft is selected as the electrostatic discharge device arrangement area, the areas where the structural materials are not suitable for arranging electrostatic discharge devices and the areas where other airborne equipment has been arranged are excluded, and the remaining areas are the final electrostatic discharge device arrangement area and area number M ;

[0102] Step 4, according to the number of electrostatic discharge devices and the number of areas, form multiple full-aircraft electrostatic discharge device preliminary layout schemes;

[0103] Specifically, the N electrostatic discharge devices are distributed to the M electrostatic discharge device arrangement areas, if N / M >2, then 2 electrostatic discharge devices should be arranged in each electrostatic discharge device arrangement area, forming multiple full-aircraft electrostatic discharge device preliminary layout schemes;

[0104] Step 5, taking the total discharge current I Q Maximum or full-aircraft electrostatic discharge device balanced discharge as the judgment standard, determine the layout design scheme of the full-aircraft electrostatic discharge device;

[0105] Specifically, for each full-aircraft electrostatic discharge device preliminary layout scheme, take the maximum number of electrostatic discharge devices arranged in an electrostatic discharge device arrangement area in the full-aircraft electrostatic discharge device preliminary layout scheme as Q ;

[0106] Place the first electrostatic discharge device in each electrostatic discharge device arrangement area, L A ​The spacing between the first electrostatic discharge device and the structure tip, L A is greater than 100 mm, T The first electrostatic discharge device is arranged inside the T +1 electrostatic discharge device, L T The spacing between the first electrostatic discharge device and the T +1 electrostatic discharge device, T L T is greater than 100 mm, T =1, 2, …, Q ;

[0107] The simulation obtains the steady-state potential of the same aircraft V The discharge current of each electrostatic discharge device I F And the total discharge current I Q , wherein F =1, 2, …, N V is greater than 20 kV;

[0108] The total discharge current of the aircraft electrostatic discharge device layout scheme I Q The maximum is the judgment standard, and the L A and L T configuration of the aircraft electrostatic discharge device layout scheme and the arrangement area of each electrostatic discharge device is formed.

[0109] Or take the equal discharge of the aircraft N electrostatic discharge device as the judgment standard, and in the I F The standard deviation is less than the standard deviation limit value P The aircraft electrostatic discharge device layout scheme with the maximum total discharge current I Q is selected, and the L A and L T configuration of the aircraft electrostatic discharge device layout scheme and the arrangement area of each electrostatic discharge device is formed.

[0110] Step 6, evaluate the rationality of the aircraft electrostatic discharge device layout scheme, and obtain the final layout scheme of the aircraft electrostatic discharge device;

[0111] Specifically, according to the aircraft electrostatic discharge device layout scheme determined in step 5, the simulation obtains the total deposition static current of the aircraft I t ​Aircraft steady state potential V And maximum discharge current of electrostatic discharge device under aircraft steady state potential I Z According to aircraft steady state potential V And maximum discharge current of electrostatic discharge device I Z Evaluate the rationality of the aircraft full-machine electrostatic discharge device layout scheme, and obtain the final layout scheme of the aircraft full-machine electrostatic discharge device;

[0112] The rationality of the aircraft full-machine electrostatic discharge device layout scheme is specifically to meet the aircraft steady state potential V Less than or equal to 75kV ， Maximum discharge current of electrostatic discharge device I Z Less than or equal to k* I q , k is a correction coefficient, k is a value greater than 1, then the aircraft full-machine electrostatic discharge device layout scheme is reasonable, and is taken as the final layout scheme of the aircraft full-machine electrostatic discharge device; if V > 75kV or I Z >k* I q , select other aircraft full-machine electrostatic discharge device layout schemes in step 5 and repeat step 6 until V Less than or equal to 75kV, I Z Less than or equal to k* I q , form the final layout scheme of the aircraft full-machine electrostatic discharge device.

[0113] Example 6

[0114] The aircraft electrostatic discharge device layout design method provided in this embodiment comprises the following steps:

[0115] Step 1, calculate and obtain the total deposition static current of the aircraft;

[0116] According to the formula of SAE ARP 5672-2009 "Aircraft Precipitation Static Certification" I t = q p vc A eff Or according to the formula of MIL-STD-464A "Electromagnetic Environmental Effects Requirements For Systems" I t =Ic ×A eff x v / 600 Calculate and obtain the total deposited electrostatic current of the aircraft. I t =500μA;

[0117] Step 2: Calculate the number of electrostatic dischargers that need to be installed on the aircraft;

[0118] Based on the discharge index of a single electrostatic discharger I q =50μA and the total electrostatic current deposited on the aircraft I t =500μA Calculate the number of electrostatic dischargers required for the aircraft N =10;

[0119] Step 3: Conduct simulation of electrostatic distribution on the aircraft to determine the final electrostatic discharger placement area and number of areas;

[0120] Simulations of electrostatic distribution deposition on an aircraft were conducted. Based on the electric field intensity distribution of the aircraft, the outer trailing edges of the wings and tail were selected as the areas for electrostatic discharger (ESD) placement. Considering the symmetry of the aircraft, the final ESD placement areas and the number of areas were determined. M =4.

[0121] Step 4: Formulate a variety of preliminary layout schemes for the electrostatic dischargers of the entire machine;

[0122] Based on the number of aircraft electrostatic dischargers obtained in step 2 N =10 and the electrostatic discharger arrangement area in step 3 M =2, N / M Since 2.5 > 2, each electrostatic discharger (ESD) placement area should ideally have 2 ESDs, resulting in two ESD layout schemes for the entire aircraft. Scheme 1 has 3 ESDs on one wing and 2 on one tail. Scheme 2 has 2 ESDs on one wing and 3 on one tail. The maximum number of ESDs that can be placed in one ESD placement area within any of these layout schemes is taken as... Q =3.

[0123] Step 5, with the total discharge current I Q The maximum or balanced discharge of all electrostatic dischargers in the machine is used as the criterion to determine the layout design scheme of the electrostatic dischargers in the machine.

[0124] like Figure 2 As shown, the first electrostatic discharger is placed in the wing or tail area. L AThe first static discharge device and the structure tip spacing, L A The second static discharge device is arranged inside the first static discharge device, L 1 is the spacing between the first static discharge device and the second static discharge device, L 2 is the spacing between the second static discharge device and the third static discharge device, L 1=200m, L 2=200m;

[0125] The maximum discharge current in the wing area is taken as the judgment standard, and the layout design scheme of Q 3 static discharge devices is formed, and a series of L A and L T values are obtained, wherein L A =310mm 、L 1=300m, L 2=400m; The maximum discharge current in the tail area is taken as the judgment standard, and the layout design scheme of Q 3 static discharge devices is formed, and a series of L A and L T values are obtained, wherein L A =300mm 、L 1=350m, L 2=400m;

[0126] For each full-machine static discharge device layout scheme, the steady-state potential of the aircraft V 40kV discharge current of each static discharge device is obtained by simulation I F and the total discharge current I Q For the first full-machine static discharge device layout scheme, I 1=59μA, I 2=56μA, I 3=53μA, I 4=52μA, I 5=49μA, I 6=47μA, I 7=54μA, I 8=51μA, I 9=61μA, I 10 =62μA, I Q =544μA; For the second full-machine static discharge device layout scheme,I 1 = 53 μA, I 2 = 52 μA, I 3 = 54 μA, I 4 = 52 μA, I 5 = 47 μA, I 6 = 49 μA, I 7 = 51 μA, I 8 = 47 μA, I 9 = 48 μA, I 10 = 47 μA, I Q = 500 μA;

[0127] Total discharge current of the whole aircraft electrostatic discharge device layout scheme I Q The first aircraft electrostatic discharge device layout scheme is selected as the maximum criterion, and the L A and L T The configuration is as follows, the wing area L A = 310 mm 、L 1 = 300 m, L 2 = 400 m, the tail area L A = 300 mm 、L 1 = 350 m;

[0128] The whole aircraft N The equal discharge of the electrostatic discharge device is taken as the criterion, and the I F The standard deviation is less than the standard deviation limit P = 3, the total discharge current of the aircraft electrostatic discharge device layout scheme is selected I Q The second aircraft electrostatic discharge device layout scheme is selected as the maximum aircraft electrostatic discharge device layout scheme, and the L A and L T The configuration is as follows, the wing area L A = 310 mm 、L 1 = 300 m, the tail area L A = 300 mm 、L 1 = 350 m, L 2 = 400 m.

[0129] Step 6, evaluate the rationality of the aircraft electrostatic discharge device layout scheme, and obtain the final aircraft electrostatic discharge device layout scheme.

[0130] According to the first kind of aircraft full machine static electricity discharger layout scheme, the aircraft full machine static electricity discharger layout scheme is determined according to the equal discharge of the static electricity discharger as the judgment standard, and the aircraft full machine static electricity discharger layout scheme is determined according to the equal discharge of the static electricity discharger as the judgment standard. N The total deposited static electricity current of the aircraft in step 1 is simulated to obtain the aircraft steady-state potential I t = 500 μA V The maximum discharge current of the static electricity discharger under the aircraft steady-state potential I Z = 40 kV is obtained, and the maximum discharge current of the static electricity discharger under the aircraft steady-state potential

[0131] = 40 kV is obtained, and the maximum discharge current of the static electricity discharger under the aircraft steady-state potential V = 40 kV is obtained, and the maximum discharge current of the static electricity discharger under the aircraft steady-state potential I Z = 40 kV is obtained, and the maximum discharge current of the static electricity discharger under the aircraft steady-state potential V = 40 kV is less than 75 kV ， The maximum discharge current of the static electricity discharger under the aircraft steady-state potential I Z = 40 kV is less than k I q = 40 kV is less than k = 55 μA, k = 1.1, and the second kind of aircraft full machine static electricity discharger layout scheme is selected as the final aircraft full machine static electricity discharger layout scheme.

Claims

1. A method for designing the layout of an aircraft electrostatic discharger, characterized in that, Includes the following steps: Step 1: Calculate and obtain the total deposited electrostatic current of the aircraft; Step 2: Calculate the number of electrostatic dischargers that need to be installed on the aircraft based on the total deposited electrostatic current. Step 3: Conduct simulation of electrostatic distribution on the aircraft to determine the final electrostatic discharger placement area and number of areas; Step 4: Based on the number of electrostatic dischargers and the number of areas, formulate several preliminary layout schemes for the electrostatic dischargers of the entire machine; Step 5: Use the total discharge current I Q The maximum or balanced discharge of all electrostatic dischargers in the machine is used as the criterion to determine the layout design scheme of the electrostatic dischargers in the machine. Step 6: Evaluate the rationality of the overall electrostatic discharger layout scheme of the aircraft to obtain the final layout scheme of the overall electrostatic discharger of the aircraft. Step 5 specifically involves: for each preliminary layout scheme of the electrostatic dischargers for the entire machine, taking the maximum number of electrostatic dischargers arranged in one electrostatic discharger arrangement area within the preliminary layout scheme as... Q ; Place the first electrostatic discharger in each electrostatic discharger deployment area. L A The distance between the first electrostatic discharger and the tip of the structure. L A For values ​​greater than 100 mm, in the first... T The inner side of the electrostatic discharger is arranged with the first T +1 electrostatic discharger, L T For the first T The electrostatic discharger and the first T +1 spacing of electrostatic dischargers, L T For values ​​greater than 100mm, T =1, 2, ..., Q ; Simulation to obtain the steady-state electromotive force of the same aircraft V The discharge current of each electrostatic discharger I F and total discharge current I Q ,in F =1,2,…, N V is a value greater than 20kV; The total discharge current of the electrostatic discharger layout scheme of the whole machine I Q Using the maximum value as the criterion, a layout scheme for the electrostatic dischargers (ESDs) of the entire aircraft and the arrangement areas of each ESD are formed. L A and L T Configuration; Or the whole machine N Using equal discharge of individual electrostatic dischargers as the criterion, I F Standard deviation less than the standard deviation limit P The overall electrostatic discharger layout scheme selects the total discharge current. I Q The largest overall electrostatic discharger (ESD) layout scheme for the entire aircraft, forming the overall ESD layout scheme and the arrangement areas of each ESD device. L A and L T Configuration; Step 6 specifically involves: based on the aircraft-wide electrostatic discharger layout scheme determined in step 5, simulating and obtaining the total deposited electrostatic current of the aircraft that satisfies the requirements of step 1. I t aircraft steady-state electromotive force V Maximum discharge current of electrostatic discharger under steady-state potential of aircraft I Z According to the aircraft's steady-state electromotive force V and the maximum discharge current of the electrostatic discharger I Z The rationality of the overall electrostatic discharger (ESD) layout scheme of the aircraft was evaluated, and the final ESD layout scheme of the aircraft was obtained.

2. The aircraft electrostatic discharger layout design method according to claim 1, characterized in that, Step 1 specifically involves: calculating and obtaining the total electrostatic current deposited on the aircraft according to formula (1) or (2); I t = q p vc A eff （1）； in, q p Stored charge of a single particle, unit: c / p; c Particle concentration per unit volume, unit: p / m 3 ; A eff The frontal surface area of ​​the aircraft, in meters (m²). 2 ; v The speed of the aircraft, in m / s; I t =I c ×A eff ×ν / 600 （2）； in, I c Charging current density, unit: μA / m 2 ; A eff The frontal surface area of ​​the aircraft, in meters (m²). 2 .

3. The aircraft electrostatic discharger layout design method according to claim 2, characterized in that, Step 2 specifically involves: based on the discharge index of a single electrostatic discharger... I q And the total static current deposited on the aircraft I t Calculate the number of electrostatic dischargers that need to be installed on the aircraft. N , N 1= I t / I q （3）； N Take greater than N The smallest even number equal to 1.

4. The aircraft electrostatic discharger layout design method according to claim 3, characterized in that, Step 3 specifically involves: conducting an electrostatic distribution simulation of the aircraft deposition; selecting the region with the largest electric field distribution at the aircraft's trailing edge as the electrostatic discharger (ESD) placement area based on the aircraft's electric field intensity distribution; excluding areas where the structural materials are unsuitable for ESD placement and areas where other airborne equipment has already been placed within the ESD placement area; and determining the remaining area as the final ESD placement area and the number of areas. M .

5. The aircraft electrostatic discharger layout design method according to claim 4, characterized in that, Step 4 specifically involves: [The text abruptly ends here, likely due to an incomplete sentence or a missing section.] N One electrostatic discharger was assigned to M An area for scattering electrostatic dischargers, if N / M If the value is greater than 2, then each electrostatic discharger placement area should preferentially place 2 electrostatic dischargers to form a variety of preliminary layout schemes for the entire machine's electrostatic dischargers.

6. The aircraft electrostatic discharger layout design method according to claim 5, characterized in that, The evaluation of the rationality of the aircraft's overall electrostatic discharger layout scheme in step 6 specifically involves ensuring that the aircraft's steady-state electrostatic potential is met. V Less than or equal to 75kV ， Maximum discharge current of electrostatic discharger I Z Less than or equal to k* I q If k is a correction coefficient and k is greater than 1, then the overall electrostatic discharger layout scheme of the aircraft is reasonable and will be used as the final layout scheme for the overall electrostatic dischargers of the aircraft; if V >75kV or I Z >k* I q Then select the other aircraft-wide electrostatic discharger layout scheme from step 5 and repeat step 6 until... V Less than or equal to 75kV I Z Less than or equal to k* I q This led to the final layout scheme for the electrostatic dischargers across the entire aircraft.

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