CN103293397B - A kind of aircraft that generates initially is struck by lightning the method for attachment point - Google Patents
A kind of aircraft that generates initially is struck by lightning the method for attachment point Download PDFInfo
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Abstract
The invention discloses a kind of aircraft that generates initially to be struck by lightning the method for attachment point, belong to aircraft thunder and lightning direct effect simulation technical field.The first selected simulated domain of the present invention, calculates the Probability p of each discharge channel to each possibility breakdown point i development
iby wheel disc robin according to probability determine may in breakdown point one for after next breakdown point, calculate the electromotive force of the point of discharge that this may develop, and adjusting the boundary condition of simulated domain accordingly, double counting hits aircraft or descending leader is developed to solution room border until meet lightning channel; Record thunder and lightning in each discharge process hit the number of times of aircraft and hit the number of times at the some positions of aircraft respectively, obtain the lightning strike probability at each position.Adopt method of the present invention carry out aircraft thunder and lightning subregion avoid analogy method limitation, than induction field simulation method closer to actual conditions, more to save time than ground experiment and flight experiment, safety and economy.
Description
Technical field
The invention belongs to aircraft thunder and lightning direct effect simulation technical field, particularly relate to a kind of aircraft that generates and to be initially struck by lightning the emulation mode of attachment point.
Background technology
Thunder and lightning is the spontaneous phenomenon can not evaded in aircraft flight, thunder and lightning direct effect refers to that aircraft is costed in thunderbolt, lightning current by time heat even puncture aircraft skin, radome etc. outside install parts, destroy the phenomenon of aircraft physical arrangement, owing to being directly connected to flight safety to the thunderbolt of aircraft, so the lightning Protection design of aircraft must be carried out in advance.Numerous standard is had to mention the experiment of thunder and lightning direct effect and the lightning protection of aircraft both at home and abroad, as: SAEARP5416(aircraft Lightning Test method); SAEARP5414A(aircraft thunder and lightning subregion), in RTCA/DO.160 " airborne equipment environmental baseline and test procedure " Section 23 " thunder and lightning direct effect ", these standards have great influence power and widespread use in international airline field.China's respective standard has HB6129 and GJB3567A.According to above standard, aircraft thunder and lightning subregion is divided into 1st district substantially--be initially struck by lightning attachment region, 2nd district--thunderbolt scan impact zone and 3rd district--extremely low probability lightning strike area.The lightning protection design of each parts needs to carry out according to different thunder and lightning subregion, and first thunder and lightning subregion will determine the attachment point that is initially struck by lightning.So the physical phenomenon that simulating nature thunder and lightning occurs generates the initial thunderbolt attachment point of aircraft, and the relevant position of record thunderbolt and probability are the crucial first steps determining aircraft thunder and lightning subregion.
According to current literature survey, the lightning region of new developmental flight device define 4 kinds of methods: 1) first method, compared by the known aircraft similar with the contour structures subregion that is struck by lightning, and rule of thumb adjusting subregion: these class methods are the simplest, but can only be applied to the aircraft that materials and structures is all highly similar, the scope of application is too little; 2) second method, by the high-voltage testing equipment of testing laboratory, to the full-scale of aircraft or scale model electric discharge, the test of record thunderbolt attachment point obtains: this comparison is accurate, be each standard recommendation method, but obvious consumptive material consuming time, and have high-voltage electric shock or to ignite etc. dangerous.3) the third method, scholar is had to propose to adopt the condition identical with second method (the thunderbolt attachment point of testing laboratory is tested) to carry out analogue simulation recently, value determination aircraft thunder and lightning subregion by Electrostatic field calculation aircraft surface induction field: this emulation mode has certain scientific basis, but have ignored thunderbolt itself is probability event, institute in a second approach just each assigned position of regulation sparking electrode must discharge more than 10 times.And the value of induction field is directly equal to lightning strike area division by the method, there is deviation with true experiment.Comparatively big error can be caused in application.4) the 4th kind of method, uses true aircraft to leap thunderstorm belt, directly records aircraft nature lightning subregion: this experimental technique result is the most accurate, but the method is obviously very dangerous, and testing expenses are extremely expensive, and find thunderstorm belt because of needs repeatedly to take a flight test, the test period is also longer.
Summary of the invention
The object of this invention is to provide a kind of aircraft that generates initially to be struck by lightning the emulation test method of attachment point, the dielectric breakdown followed is there is and containing discharge threshold model with adopt finite difference method to calculate the thunder and lightning field that there is lightning channel and aircraft simultaneously based on nature thunder and lightning Fractal Phenomenon, effectively can determine that aircraft is initially struck by lightning the position of attachment point, the lightning strike probability of its each parts can be recorded, for aircraft thunder and lightning subregion provides foundation.
A kind of aircraft that generates that the present invention proposes initially is struck by lightning the method for attachment point, comprises the following steps:
The first step, selected simulated domain, setting thunder and lightning reference position and position of aircraft, calculating simulation regional space Potential Distributing.
Getting the square air box that length, width and height are more than or equal to model aircraft full-size 3 times is simulated domain, the setting reference position of thunder and lightning and initial breakdown point are positioned at air box top center, and below the reference position that aircraft is positioned at thunder and lightning, the reference position of distance thunder and lightning is model aircraft full-size 1.5 times place; Adopt the electromotive force in method of finite difference calculating simulation region, simulated domain outer boundary and jointly form Dirichlet(Di Li Cray by the Potential Distributing on the inner boundary that discharge channel is formed) boundary condition, the electromotive force in described simulated domain
meet Laplace(Laplce) equation, that is:
Wherein
for the border (comprising inner boundary and outer boundary) of simulated domain Ω, x, y, z are the coordinate of any point in simulated domain, x ', y ', z ' is the coordinate of any point on simulated domain border,
for the electromotive force of simulated domain any point, and f (x ', y ', z ') be border
potential function.
Second step, calculates the Probability p of the point of discharge development that may develop to each
i:
Wherein,
for the field intensity between the point of discharge that may develop and current breakdown point,
for the point of discharge electromotive force that may develop in discharge channel,
for the breakdown point electromotive force be connected with the point of discharge that may develop, it is wherein the distance between the point of discharge that may develop accordingly and current breakdown point; E
thbe discharge threshold electric field intensity, for atmospheric environment is to the Intrusion Index of discharge channel, characterize the power of Faraday effect, value 0 ~ 5, by wheel disc robin according to Probability p
ia point in the point of discharge that Stochastic choice may develop is the next one side of puncturing point, and lightning channel guide develops a step;
3rd step, calculates the electromotive force selecting the next breakdown point i obtained;
Represent along the distance of discharge channel Σ Δ l between initial breakdown point and the point of discharge that may develop, then the electromotive force of the point of discharge that may develop in discharge channel is
wherein, E
infor discharge channel axis is to internal electric field,
for the reference potential of initial breakdown point.Current breakdown point for the first time in discharge process is that initial breakdown point is thunder and lightning reference position point, and the current breakdown point later in each discharge process is the next breakdown point chosen in the point of discharge that may develop in last discharge process.
4th step, the boundary condition of the electromotive force adjustment simulated domain of the next breakdown point calculated according to the 3rd step, repeats the first step ~ the 3rd step, until meet lightning channel to hit aircraft or descending leader is developed to solution room border;
5th step, repeats the first step ~ the 4th step, and record thunder and lightning hits the number of times a of aircraft and hits the number of times a of the some position j of aircraft respectively
j, be wherein the label of Parts of Aircraft j;
6th step, hits the several a in j time, aircraft a certain position according to thunder and lightning
jhit number of times a with total thunder and lightning, obtain the lightning strike probability a at each position
j/ a.
A kind of aircraft that generates of the present invention is initially struck by lightning the method for attachment point, and its advantage is:
The dielectric breakdown model containing discharge threshold followed is there is based on nature thunder and lightning Fractal Phenomenon, and adopt finite difference method to calculate to exist the emulation lightning stroke process of lightning channel and aircraft simultaneously, more meet the actual conditions of the development of nature lightning channel and thunderbolt aircraft.Can generate aircraft and to be initially struck by lightning attachment point by analogue simulation, record attachment point position on board the aircraft, each position of calculating aircraft suffers lightning strike probability, for aircraft thunder and lightning subregion provides foundation.Calculating shows, adopt method of the present invention carry out aircraft thunder and lightning subregion avoid analogy method limitation, than induction field simulation method closer to actual conditions, more to save time than ground experiment and flight experiment, safety and economy.
Accompanying drawing explanation
Figure 1A is the constitutional diagram that under the identical thunder and lightning reference position same aircraft attitude condition of the generation of method described in the present invention, lightning leader hits head;
Figure 1B is the constitutional diagram that under the identical thunder and lightning reference position same aircraft attitude condition of the generation of method described in the present invention, lightning leader hits wing;
Fig. 1 C is the constitutional diagram that under the identical thunder and lightning reference position same aircraft attitude condition of the generation of method described in the present invention, lightning leader does not hit aircraft;
Fig. 2 A be under the different attitude of flight vehicle conditions of different thunder and lightning reference positions that method described in the present invention generates lightning leader hit head constitutional diagram;
Fig. 2 B is the constitutional diagram that under the different attitude of flight vehicle condition of different thunder and lightning reference positions that method described in the present invention generates, lightning leader hits vertical tail;
Fig. 2 C is the constitutional diagram that under the different attitude of flight vehicle condition of different thunder and lightning reference positions that method described in the present invention generates, lightning leader hits tailplane.
Embodiment
Below in conjunction with drawings and Examples, the present invention is described in detail.
A kind of aircraft that generates that the present invention proposes initially is struck by lightning the emulation test method of attachment point, comprises the following steps:
(1) in simulated domain, set reference position and the position of aircraft of thunder and lightning.Adopt the electromotive force in method of finite difference calculating simulation region, simulated domain outer boundary and jointly form Dirichlet boundary condition by the Potential Distributing on the inner boundary that discharge channel is formed, meet Laplace equation, namely
Wherein
for the border (comprising inner boundary and outer boundary) of region Ω, x, y, z are the coordinate of any point in simulated domain, x ', y ', z ' is the coordinate of any point on simulated domain border,
for the electromotive force of simulated domain any point, and f (x ', y ', z ') be border
potential function.
Its full-scale or scale model is set up with reference to aircraft electrical characteristic to be measured in the present invention; According to the reference position about thunderbolt attachment point experiment regulation setting or sets itself thunder and lightning.
(2) Probability p of the point of discharge development that may develop to each is calculated
i:
Wherein,
for the field intensity between the point of discharge that may develop and corresponding breakdown point;
for the point of discharge electromotive force that may develop in discharge channel,
for the breakdown point electromotive force be connected with the point of discharge that may develop, wherein Δ l is the point of discharge and current breakdown point spacing that may develop accordingly; E
thbe discharge threshold electric field intensity, make passage axis be E to internal electric field
in, the reference potential of initial breakdown point is
η is the Intrusion Index of atmospheric environment to discharge channel, characterizes the power of Faraday effect, and value 0 ~ 5 punctures direction by wheel disc robin according to probability Stochastic choice, and lightning channel guide develops a step;
The dielectric breakdown model that the development of above-mentioned thunder discharge passage adopts nature to follow, thunder and lightning field calculates and adopts method of finite difference.
(3) represent along the distance of passage Σ Δ l between initial breakdown point and the point of discharge that may develop, then the electromotive force of the point of discharge that may develop in discharge channel is
this point of discharge that may develop is the next point of lightning channel guide development, completes a step electric discharge.
(4) electromotive force of the point of discharge that may develop calculated according to step (3), the boundary condition of adjustment simulated domain, repeat step (1)-(3), until meet lightning channel to hit aircraft or descending leader is developed to solution room border;
(5) repeat step (1)-(4), record thunder and lightning respectively and hit the position of aircraft and hit the number of times of this position;
(6) hit the number of times of a certain position of aircraft according to thunder and lightning and hit the total degree of aircraft, obtaining a certain lightning strike probability hitting position of aircraft; According to these lightning strike probability data, foundation can be provided to aircraft thunder and lightning subregion.
A kind of aircraft that generates of the present invention is initially struck by lightning the method for attachment point, and each thunder and lightning starting point at least emulates more than 10 times, with aircraft be the center of circle sphere on each thunder and lightning starting point be no more than 30 degree apart.The lightning channel of various different fractal dimension under the present invention can realize different atmospheric conditions by Gas regulation environment to the Intrusion Index of discharge channel and discharge threshold, thus when simulated flight device flies more realistically, meet with the phenomenon of thunderbolt aloft, make result of calculation closer to actual conditions.
The principle of the inventive method is as follows:
The Three-dimensional simulation that lightning leader discharges is from the macroscopic appearance of thunder discharge, by Fractal Theory Applications in thunder discharge guide modeling, according to Laplace equation and the regional boundary condition in space, determine the Potential Distributing in space, under the charged analytic model framework of disk thundercloud, utilize dielectric breakdown model and introduce discharge threshold E
thconstruct lightning leader discharging value modeling algorithm, achieve the Three-dimensional simulation of thunder discharge guide.
Consider that axial electric field that thundercloud produces is along the highly approximate variation tendency in parabolic function, the Electric Field Distribution that can encourage on ground according to thundercloud to electric field under cloud and cloud in electric field edge carry out matching with different quadratic functions highly respectively.Pass through
(wherein
for electric potential difference,
for electric field intensity,
for vector line element) just can obtain the Potential Distributing in space after integration.The initial boundary conditions of numerical simulation gets the Potential Distributing of domain boundary.
Under quasistatic approximation, the electromotive force in simulated domain meets Laplace equation, simulated domain outer boundary and jointly form Dirichlet boundary condition by the Potential Distributing on the inner boundary that discharge channel is formed.Then finite difference method is adopted to solve the distribution of thunder and lightning simulated domain built-in potential.In the method, the development of lightning channel is the coefficient result of determinacy and enchancement factor.What dielectric breakdown model adopted puncture direction according to development probability description, and to make the development of lightning leader obey the probability of the large local development of electric field intensity large, and the local development probability that electric field intensity is little is little.And this dielectric breakdown model introduces discharge threshold voltage in progression of lightning leader and lightning channel internal pressure drops, only have when the voltage applied is higher than discharge threshold voltage, lightning leader just may develop, and lightning channel inside is not equipotential.The introducing of discharge threshold electric field intensity inhibits side in insulating medium (as air) to the growth of upper branch, the number meeting point of discharge to be developed to be reduced, and the introducing of discharge channel pressure drop also makes lightning leader develop than being easier to stopping.
In the process of numerical simulation, in view of the complicacy of thunder and lightning initial breakdown mechanism, think guide originate in field intensity in cloud exceed guide start in threshold region random a bit, this starting point also can be specified by thunder and lightning testing standard.Boundary condition due to zoning (thunder and lightning simulated domain) is that the area outer condition determined by thunder cloud and the internal boundary condition be made up of discharge channel are formed jointly, electric discharge often develops a step, internal boundary condition all can change, again solve Laplace equation computer memory Potential Distributing, then calculate the development probability function in neighbor point i direction around machine plotting pending in leader channel with following formula:
Wherein,
for the electric field intensity between the point of discharge that may develop and corresponding breakdown point; E
thbe discharge threshold electric field intensity, make passage axis be E to internal electric field
in, the reference potential of initial breakdown point is
for atmospheric environment is to the Intrusion Index of discharge channel, characterize the power of Faraday effect, value 0 ~ 5, puncture direction by wheel disc robin according to probability Stochastic choice, lightning channel guide develops a step, completes a step electric discharge; According to the boundary condition of the electromotive force of the point of discharge that may develop adjustment simulated domain, circulate successively, until meet thunder discharge stopping criterion or descending leader is developed to solution room border.In this process as hit aircraft need record hit position coordinates and each position number of lightning strokes statistics, foundation can be provided for aircraft thunder and lightning subregion.The total number of lightning strokes of this position number of times/aircraft of the lightning strike probability=thunderbolt aircraft of a part.The region that lightning strike probability is large is decided to be 1st district according to master gauge--and be initially struck by lightning attachment region.
Below in conjunction with accompanying drawing, one embodiment of the present invention is described.
The present invention carries out the emulation of thunderbolt attachment point to the simplification F4 aircraft scale model that the such as length shown in Figure 1A ~ Fig. 1 C is 15m.Aircraft is placed in the space of 60m × 60m × 60m, if z=0 plane electromotive force is 0, z=60m plane electromotive force is 2000.Centered by aircraft, about angularly choose thunder and lightning apart from aircraft center more than 25m place and initially position occurs, angle intervals 30 °, because model is symmetrical so only calculate the situation of the initial origination point of thunder and lightning on the right side of aircraft, require each some calculating more than 10 times.The identical thunder and lightning reference position same aircraft attitude lightning leader that method described in the present invention that what Figure 1A ~ Fig. 1 C showed is generates is close to the constitutional diagram of aircraft.Need calculate 10 times illustrated same thunder and lightning reference position thunder and lightning reference position (30,20,60), wherein the simulation result of 3 times is shown in that showing lightning leader respectively shown in Figure 1A ~ Fig. 1 C hits head, hits wing, and does not hit aircraft.Fig. 2 A ~ Fig. 2 C is the constitutional diagram of the different attitude of flight vehicle lightning leaders of different thunder and lightning reference positions close to aircraft of the generation of method described in the present invention.What show respectively in Fig. 2 A ~ Fig. 2 C is wherein 3 thunderbolt states: 30 °, aircraft pitch angle, and roll angle 0 °, hits head; 0 °, aircraft pitch angle, roll angle 30 °, hits vertical tail; 0 °, aircraft pitch angle, roll angle 0 °, hits tailplane.Can see that aircraft runs into the situation of thunderbolt by Figure 1A ~ Fig. 1 C and Fig. 2 A ~ Fig. 2 C at every turn different, and there is certain probability distribution.This example has got 37 thunder and lightning starting points altogether, its coordinate (x, y, z) (30 are set to respectively, 30, 60), (30, 20, 60), (30, 47, 60), (21, 15, 60), (21, 45, 60), (15, 21, 60), (15, 39, 60), (13, 30, 60), (30, 13,-60), (30, 47,-60), (21, 15,-60), (21, 45,-60), (15, 21,-60), (15, 39,-60), (13, 30,-60), (13, 60, 30), (30, 60, 47), (30, 60, 30), (30, 60, 13), (53, 60, 47), (53, 60, 13) (13,-60, 30), (30,-60, 47), (30,-60, 30), (30,-60, 13), (53,-60, 47), (53,-60, 13), (0, 13, 30), (0, 7, 47), (0, 30, 30), (0, 30, 13), (0, 53, 47), (0, 53, 13), (0, 47, 30), (0, 30, 47), (0, 7, 13), (30, 30,-60), each reference position emulates 10 times.Then thunder and lightning starting position coordinates is set to (30,30,60), changes aircraft pitch and gets 37 kinds of situations altogether with rolling angle, (luffing angle, rolling angle):
(30.0,0), (26.6,16.1), (16.1,26.6), (0,30.0), (-16.1,26.6), (-26.6,16.1), (-30.0,0), (60.0,0), (56.3,40.9), (40.9,56.3), (0,60.0), (-40.9,56.3), (-56.3,40.9), (-60.0,0), (90.0,0), (90.0,90.0), (90.0,90.0), (62.7,90.0), (-90.0,90.0), (-90.0,90.0), (-90.0,62.7), (-60.0,180), (-56.3 ,-40.9), (-40.9 ,-56.3), (180 ,-60.0), (40.9 ,-56.3), (56.3 ,-40.9), (60.0,180), (-30.0,180), (-26.6 ,-16.1), (-16.1 ,-26.6), (180 ,-30.0), (16.1 ,-26.6), (26.6 ,-16.1), (30.0,180), (180,180), (0,0) often kind of situation emulates 10 times.
Altogether simulate 740 thunderbolts, wherein hit aircraft 651 times.The attachment point position distribution hitting aircraft according to record: hit head 194 times, hit wing 203 times, hit tailplane 99 times, hit vertical tail 84 times, hit other positions 71 times.With formula: the lightning strike probability=thunderbolt aircraft of a part total number of lightning strokes of this position number of times/aircraft (651 times) calculates the lightning strike probability at each position.
Table 1 aircraft each position lightning strike probability results contrast
Table 1 is that the method for the invention simulates the simulation result of the present embodiment and the actual comparison sheet passing through the thunderstruck probability statistics result in each position of aircraft in the flight test that thunderstorm belt carries out of U.S.'s F-4 aircraft.The thunderbolt attachment point that analog simulation of the present invention obtains mainly is distributed in the higher position of the electric field intensity such as tip and head of wing, tailplane and vertical tail.This is consistent with existing theoretical analysis, because when lightning leader approaches aircraft, always induces very strong electric field at these positions, the ionization that its ambient air produces, and attracts lightning leader to adhere at these positions.And as can be seen from Table 1, the present invention emulates the lightning strike probability distribution results that obtains compared with the measured result of F-4 flight test, the maximum difference of probability distribution is 3.2%, and the goodness of fit is higher, describe use the present invention to carry out thunderbolt attachment point to carry out simulated experiment be feasible.
Claims (2)
1. generate aircraft to be initially struck by lightning the method for attachment point, it is characterized in that, comprise the following steps:
The first step, selected simulated domain, setting thunder and lightning reference position and position of aircraft, adopt the electromotive force in method of finite difference calculating simulation region; Described simulated domain gets the square air cartridge submodel that length, width and height are more than or equal to aircraft full-size more than 3 times, the setting reference position of thunder and lightning and initial breakdown point are positioned at described air cartridge submodel top center, and below the reference position that aircraft is positioned at thunder and lightning, the reference position of distance thunder and lightning is aircraft full-size 1.5 times place;
Electromotive force in described simulated domain
meet Laplace's equation, delivery is intended area outer and is jointly formed Dirichlet boundary conditions by the Potential Distributing on the inner boundary that discharge channel is formed, and described Laplace's equation is:
Wherein
for the border of simulated domain Ω, x, y, z are the coordinate of any point in simulated domain, x ', y ', z ' is the coordinate of any point on simulated domain border,
for the electromotive force of simulated domain any point, and f (x ', y ', z ') be border
potential function;
Second step, calculates the Probability p of the point of discharge development that may develop to each
i:
Wherein,
for the field intensity between the point of discharge that may develop and current breakdown point,
for the point of discharge electromotive force that may develop in discharge channel,
for the breakdown point electromotive force be connected with the point of discharge that may develop, wherein Δ l is the point of discharge and current breakdown point spacing that may develop accordingly; E
thbe discharge threshold electric field intensity, η is the Intrusion Index of atmospheric environment to discharge channel, and obtain next breakdown point i direction by wheel disc robin according to development probability function Stochastic choice, lightning channel guide develops a step; The electromotive force of the point of discharge that may develop in described discharge channel is
atmospheric environment represents with Σ Δ l the distance along discharge channel between electric discharge initial breakdown point and the point of discharge that may develop, and this point of discharge that may develop is the next point of lightning channel guide development, completes a step electric discharge; Wherein, E
infor discharge channel axis is to internal electric field,
for the reference potential of initial breakdown point;
3rd step, calculates the electromotive force selecting the next breakdown point i obtained;
4th step, the boundary condition of the electromotive force adjustment simulated domain of the point of discharge that may develop calculated according to the 3rd step, repeats the first step ~ the 3rd step, until meet lightning channel to hit aircraft or descending leader is developed to solution room border;
5th step, repeats the first step ~ the 4th step, and record thunder and lightning hits the number of times a of aircraft and hits the number of times a of the some position j of aircraft respectively
j, wherein j is the label of aircraft position j;
6th step, hits the several a in j time, aircraft a certain position according to thunder and lightning
jhit the number of times a of aircraft with thunder and lightning, obtain the lightning strike probability a at each position
j/ a.
2. a kind of aircraft that generates according to claim 1 is initially struck by lightning the method for attachment point, it is characterized in that: the Intrusion Index η value of described atmospheric environment to discharge channel is 0 ~ 5.
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| FR3051442B1 (en) * | 2016-05-20 | 2021-07-16 | Airbus Operations Sas | ON-BOARD SYSTEM FOR EVALUATING THE SEVERITY OF A LIGHTNING STRIKE |
| CN106407501B (en) * | 2016-08-18 | 2019-10-18 | 广州供电局有限公司 | High pressure gas breaker break performance appraisal procedure and system |
| CN108052702B (en) * | 2017-11-23 | 2021-07-20 | 上海无线电设备研究所 | Lightning partitioning method based on lightning shortest path space geometric topology principle |
| CN114146428A (en) * | 2021-10-25 | 2022-03-08 | 中航通飞华南飞机工业有限公司 | Method for manufacturing lightning partition test model of amphibious aircraft |
| CN114812698B (en) * | 2022-07-01 | 2022-09-30 | 江西信息应用职业技术学院 | Lightning protection monitoring method and device, readable storage medium and electronic equipment |
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