CN110481805A - A kind of aircraft avoids lightning stroke method - Google Patents
A kind of aircraft avoids lightning stroke method Download PDFInfo
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- CN110481805A CN110481805A CN201910703068.9A CN201910703068A CN110481805A CN 110481805 A CN110481805 A CN 110481805A CN 201910703068 A CN201910703068 A CN 201910703068A CN 110481805 A CN110481805 A CN 110481805A
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D45/02—Lightning protectors; Static dischargers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Elimination Of Static Electricity (AREA)
Abstract
The present invention discloses a kind of aircraft and avoids lightning stroke method, the described method comprises the following steps: step 1, carries out lightning stroke adhering zone to aircraft surfaces and demarcates；Step 2 judges whether that being applicable in analogue method divides lightning stroke adhering zone, if applicable, then uses analogue method, if not applicable, first determines guide's adhering zone based on the lightning stroke adhering zone demarcated；Step 3 successively divides lightning stroke adhering zone based on by number of lightning strokes or return stroke times；Step 4 divides aircraft lightning region and carries out simulation calculation, and obtained aircraft surfaces field strength distribution obtains endpoint attachment point and burble point, the injection in aircraft surfaces of further obtaining being struck by lightning, disjoint paths；Step 5 carries out protection design to aircraft in lightning region.This method determines that the place of lightning stroke attachment easily occurs for aircraft surfaces, and determines the region that may pass through when thunder-strike current conducts between a pair of of entry/exit point, and the probability that aircraft is hit in thunderclaps cloud is effectively reduced.
Description
Technical field
The present invention relates to a kind of aircrafts to avoid lightning stroke method, is related to technical field of aerospace.
Background technique
There is thunder cloud in unstable atmospheric environment, atmospheric electrical phenomena therein generates the flight safety of aircraft
It seriously affects.As shown in Figure 1, since it is as a conductor equipotentiality itself, thus can add when aircraft flight is in thunder cloud
The distortion degree in powerful gas medium potential face, so that equipotential surface is bent, field strength increases at aircraft tip, especially it and other bands
Electric field strength between electric object increases, to strong electrical field occur, induces the generation of lightning stroke.
It is struck by lightning and the indirect influence of aircraft is mainly reflected in the influence to electrical/electronic system, be mainly the following
Situation:
(1) to the damage or interference of one or more airborne electronics units, account for about the 10% of lightning stroke incident；
(2) the temporary interference frequently occurred, impacted element can restore normal after lightning stroke；
(3) the provisional loss of electric energy causes the disorder in other systems.
It is generally necessary to be tested by airborne equipment environmental condition and test procedure to protect On-board Electric/Electronic Equipment
Card safety, the main lightning induction transient state susceptibility for verifying equipment and the tolerance to thunder and lightning direct effect.
The main purpose studied aircraft lightning stroke subregion is the place that lightning stroke attachment easily occurs for determining aircraft surfaces, with
And determine the region that may pass through when thunder-strike current conducts between a pair of of entry/exit point.
The characteristic of advanced composite material high specific strength, high specific stiffness, conductivity of composite material can it is poor, when by being struck by lightning
It is difficult to guide in electric current in short time, produces excessively high temperature, so that composite material generates Depth Stratification or serious
Ablation causes structural damage.
Summary of the invention
In order to overcome the above problem, the invention proposes a kind of aircrafts to avoid lightning stroke method, determines that aircraft surfaces easily occur
The place of lightning stroke attachment, and determine the region that may pass through when thunder-strike current conducts between a pair of of entry/exit point, it is effectively reduced
The probability that aircraft is hit in thunderclaps cloud.
The technical solution of the present invention is to provide a kind of aircrafts to avoid lightning stroke method, the described method comprises the following steps:
Step 1 carries out lightning stroke adhering zone to aircraft surfaces and demarcates；
Step 2 judges whether that being applicable in analogue method divides lightning stroke adhering zone, if applicable, then uses analogue method, such as
Fruit is not applicable, then first determines guide's adhering zone based on the lightning stroke adhering zone demarcated；
Step 3 successively divides lightning stroke adhering zone based on by number of lightning strokes or return stroke times；
Step 4 divides aircraft lightning region and carries out simulation calculation, and obtained aircraft surfaces field strength distribution obtains endpoint attachment
Point and burble point, the injection in aircraft surfaces of further obtaining being struck by lightning, disjoint paths；
Step 5 carries out protection design to aircraft in lightning region.
Further, step 1 refers specifically to: a possibility that lightning stroke attachment easily occurs according to aircraft surfaces is cooked aircraft surfaces
It is following to divide:
The area 1A --- region is fought back for the first time；
The area 1B --- long lasting for counterattack region for the first time；
The area 1C --- transition region is fought back for the first time；
The area 2A --- scan lightning region；
The region 2B --- lightning strike area is scanned in attachment for a long time；
3 regions --- not in the region of 1A, 1B, 1C, 2A and 2B.
Further, the region peace in step 3 determines in the following order:
Step 3.1, the region 1A, 1B is positioned,
Step 3.2, the region 1C is positioned,
Step 3.3, the region 2A, 2B is positioned,
Step 3.4, the region 1A, 1B, 2A, 2B, 1C side elongated area is positioned；
Step 3.5,3 regions are positioned；
Step 3.6, consider the division of overlapping region.
As a preference, dividing the method for carrying out simulation calculation to aircraft lightning region includes square in the step 4
Amount method, FInite Element, Finite-Difference Time-Domain Method.
Further, in the step 4, lightning stroke includes following situations in the injection of aircraft surfaces, disjoint paths: head
Enter, fuselage rear goes out；Or head enters, vertical tail goes out.
Further, described that aircraft progress protection design is referred specifically in lightning region in step 5
Compared with prior art, the invention has the following advantages that
Test simulates lightning stroke situation when aircraft engine duct is closed and opened respectively.
According to test result, wherein lightning stroke attachment point occurs twice, occurring the case where appearing on the upside of fuselage middle and back
On wing twice, the vertical fin last time is appeared in.This result has been confirmed the case where attachment point of lightning stroke aboard and has been flown
The feasibility of machine lightning Protection research.This method determines that the place of lightning stroke attachment easily occurs for aircraft surfaces, and determines lightning stroke electricity
The region that may pass through when conducting between a pair of of entry/exit point is flowed, the probability that aircraft is hit in thunderclaps cloud is effectively reduced.
Detailed description of the invention
Fig. 1 be aircraft flight in thunder cloud when equivalent schematic；
Fig. 2 is schematic diagram of the present invention to aircraft lightning stroke subregion；
Fig. 3 is subregion positioning flow figure；
Fig. 4 is the simulated effect figure for carrying out lightning stroke subregion to airliner using the method for the present invention；
Fig. 5, Fig. 6 are injection of the lightning stroke in aircraft surfaces, disjoint paths figure.
Specific embodiment
Below in conjunction with the attached drawing of the embodiment of the present invention, the technical solution of embodiment in the present invention is described.Obviously,
Described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.Based on the implementation in the present invention
Example, every other embodiment obtained by those of ordinary skill in the art without making creative efforts belong to
The scope of protection of the invention.
Embodiment 1
The present embodiment provides a kind of aircrafts to avoid lightning stroke method, the described method comprises the following steps:
Step 1 carries out lightning stroke adhering zone to aircraft surfaces and demarcates；
Step 2 judges whether that being applicable in analogue method divides lightning stroke adhering zone, if applicable, then uses analogue method, such as
Fruit is not applicable, then first determines guide's adhering zone based on the lightning stroke adhering zone demarcated；
Step 3 successively divides lightning stroke adhering zone based on by number of lightning strokes or return stroke times；
Step 4 divides aircraft lightning region and carries out simulation calculation, and obtained aircraft surfaces field strength distribution obtains endpoint attachment
Point and burble point, the injection in aircraft surfaces of further obtaining being struck by lightning, disjoint paths；
Step 5 carries out protection design to aircraft in lightning region.
This method determines that the place of lightning stroke attachment easily occurs for aircraft surfaces, and determines thunder-strike current in a pair of of entry/exit point
Between the region that may pass through when conducting, the probability that aircraft is hit in thunderclaps cloud is effectively reduced.
Embodiment 2
As shown in Fig. 2, step 1 refers specifically to: a possibility that lightning stroke attachment easily occurs according to aircraft surfaces is cooked aircraft surfaces as follows
It divides:
The area 1A --- region is fought back for the first time；
The area 1B --- long lasting for counterattack region for the first time；
The area 1C --- transition region is fought back for the first time；
The area 2A --- scan lightning region；
The region 2B --- lightning strike area is scanned in attachment for a long time；
3 regions --- not in the region of 1A, 1B, 1C, 2A and 2B.
As shown in figure 3, the region peace in step 3 determines in the following order:
It is struck by lightning the determination of initial guide's adhering zone
The first step of positioning lightning region is to determine that the initial guide that is struck by lightning may adhere to the region of aircraft.It can be with there are many kinds of method
Complete this task, such as similarity method, test, analysis (i.e. spin analytic approach, EFM).Its result, which has to comply with, previously to be had
The aircraft of the experience flight lightning stroke of similar geometry shape body, or meet the known attachment phenomenon that is struck by lightning.Typical initial attachment
Area includes end, such as head, wing, empennage wing tip, rotor end, some engine nacelles, cockpit window frame, Yi Jiqi
Its apparent protrusion.
Find in the first step when lightning electric arc cannot surface is scanned farther along airflow direction from there when, be in rear
Initial guide's adhering zone may bear most or all of lightnings.Therefore when these initial adhering zones subject long
Between uninterrupted conducting lightning currents, also therefore be defined positioned at the area 1B.
2) 1A and 1B
The second step of the positioning positioning lightning strike area in area is to determine the more multizone fought back may reach for the first time.Mainly include
The area 1A, 1B and 1C.When guide, which reaches ground (or other charge areas) triggering, to be fought back for the first time, aircraft flies before generally remaining,
From front, initial attachment point is rearwardly scanned by lightning and guide.The distance that aircraft is flown over this period determine the region 1A from
The distance that initial attachment point rearwardly extends.This section of distance depend on air speed, aircraft terrain clearance (cloud-ground lightning), with
And guide's rate.The area 1A starting point should be the end of initial adhering zone.In 1B lightning adhering zone, initial guide
The lightning channel of attachment region has to last for its whole life cycle.
3) positioning in the region 1C
The area 1C is selected in the region aircraft surfaces 1A rear portion, and flying height is in 1500m(5000ft herein) arrive 3000m
It is the place scanning guide and capable of reaching between (10000ft).
4) positioning in the region 2A and 2B
Due to being struck by lightning lasting 1,2 second in, all aircrafts can fly over its own whole length, the region 1C tail portion to
Residual surface afterwards should consider to be located at the area 2A.The rear edge surface of the region 2A tail portion backward should consider to remove in the region 2B
It is non-they be positioned in the area 1B.
5) 1A, 1B, 1C, 2A and 2B region extends laterally
Determining arc or sweepback or wing and the affiliated region 1A and 1B of empennage wing tip surface region with winglet
When, it is proposed that it determines the horizontal point of contact of wing tip curvature, then the area 1A and 1B inwardly extends 0.5m.In addition, it is contemplated that
Since wing and the region empennage wing tip 1A and 1B are inside, a possibility that low intensive lightning stroke is directly adhered to lower, lightning drops
The lateral movement in channel is smaller, so the inside 0.5m in the region 1A and 1B should consider in the region 2A and 2B.
Because lightning channel lateral movement is smaller, it has been determined that the region 1A, 1C, 1B, 2A, 2B, along wing root, the wing is hung
Engine and horizontal and vertical fixed wing root are to the table within respective edge (i.e. outer boundary or inner boundary) 0.5m(18in)
Face should be also taken into account within identical region.
6) positioning in region 3
Those are not in the region 1A, 1B, 1C, 2A, 2B, and any lightning channel is all less likely surface consideration of attachment
In 3 regions.3 regions contain the surface portion below other regions, and are directly adhering to or scanning channel adhering zone
Between conduct conducting lightning currents region.
7) overlapping region
In the surface region Ye2A in the area 1A and 1C, it is likely to occur in as fighting back for the first time sometimes close to initial first
It leads attachment point (such as head or hood entrance), subsequent counterattack occurs in the remaining place in the region 1A.3rd area also exist
Within other all areas.Design protection should be the worst based on situation area.
8) subregion is carried out with similitude
It can be used for a type aircraft with the aircraft analogy authenticated or derive from the basis of aircraft subregion.Do similarity assessment
When be considered as the following: the geometric shape of the aircraft and type aircraft that had authenticated without significant difference, such as: curvature half
The angle of sweep of diameter, structure size or wing；Configuration.Such as engine quantity, empennage form, shoulder wing or the low wing；
Big protrusion.Such as blade antenna, pneumatic barrier or fuel outlet；The aircraft of military service is struck by lightning experience have shown that subregion positioning does not have
It is necessary to change.
Aircraft surfaces electric conductivity does not have great variation.Such as aluminum alloy surface is taken with nonconducting fiberglass surfacing
Generation.
Flight characteristics is without significant change.Such as air speed and height envelope.
If aircraft only has, certain parts are similar to the aircraft authenticated, and similar portion can carry out subregion with analogue method,
It should be by above-mentioned step subregion without similar portion.For example, a frame transporter head, cockpit, the geometric shape of wing and
The aircraft of certification is similar, but fuselage is longer than the aircraft authenticated, it can carry out subregion based on the aircraft authenticated completely.
In the step 4, to aircraft lightning region divide carry out simulation calculation method include moment method, FInite Element,
Finite-Difference Time-Domain Method, as shown in figure 4, being struck by lightning using the electromagnetic simulation software operating room CST EM based on FInite Element to aircraft
Adhering zone, which divides, carries out simulation calculation, obtained aircraft surfaces field intensity map.
Further, as shown in Figure 5, Figure 6, in the step 4, lightning stroke includes in the injection of aircraft surfaces, disjoint paths
Following situations:
Path A: head enters, and fuselage rear goes out；Lightning stroke attachment point and burble point are distributed in head, empennage, wing, engine really
And vertical fin, the positions such as engine and vertical fin.
Path B head enters, and vertical tail goes out.Thunder-strike current is injected from attachment point, is then connected in burble point with conductor.It is imitative
True result meets the regulation of SAE-ARP5414A standard.
Based on above-mentioned lightning protection method, the present invention provides the lightning test for being directed to large aircraft composite material, experiment condition: examination
The instrument used is tested to become for impulse voltage generator SJTU-3000, DC voltage generator ZL-600, without partial discharge industrial frequency experiment
Depressor YDTCW800/2*400, impulse current generator IGC-100.Test simulate respectively aircraft engine duct close and
Lightning stroke situation when unlatching.
According to test result, wherein lightning stroke attachment point occurs twice, occurring the case where appearing on the upside of fuselage middle and back
On wing twice, the vertical fin last time is appeared in.
This result has confirmed the case where attachment point of lightning stroke aboard to a certain extent and aircraft lightning Protection is ground
The feasibility studied carefully.
Composite material electric conductivity itself is poor, can not in time guide the electrostatic charge of surface aggregation when being struck by lightning, from
And cause the destruction of aircaft configuration.In order to improve the lightning resistance energy of a large amount of aircrafts using composite material, need to take
Measure is protected, more common way when on the surface of composite material increase by one layer of conductive functional layers, can in time by
The electrostatic charge of material surface guides the safety to protect structure, and the way for increasing conductive functional layers includes composite material surface flame
Spray aluminized coating, bonded metal net and bonding aluminium foil etc..
Spray aluminium
Flame-spraying and plasma spraying are the methods of common two kinds of sprayings aluminium, and the two has similar protection effect.Usually
Hole sealing agent can be sprayed to enhance it in the fitting intensity of composite material surface on spraying aluminium, the specific scheme is that
Sprayed on composite product surface 0.1016mm thickness one layer of spraying aluminium (for region I, spray coating with a thickness of
0.1524mm), it is amenable to the lightning discharge of region II and composite material is not damaged.But the deposited aluminum near lightning discharge point
It is evaporated, and the deposited aluminum in other regions will appear fracture.In use regular inspection should be carried out simultaneously to spraying aluminium surface
Repairing in time.
During composite material manufacture, it can be manufactured in this way in one layer of glass cloth of surface laying of carbon fiber laying
Composite material surface out carries out the operation of deposited aluminum again, and anti-lightning strike effect can greatly increase, it can be incited somebody to action first
The isolation of product and charge is opened, and can also sprayed protection aluminium layer not by couple corrosion.
Wire mesh
Metal twine, which refers to, is made into knitwear for wire by standard textile technique.It is multiple that aluminium wire netting can be easily made shape
Miscellaneous curved surface, and can simply by matrices of composite material as adhesive and part by one-step solidified forming, and can with compared with
Small weight transmits the higher quantity of electric charge, so it is high-quality, efficient lightning Protection layer.According to simulation lightning test as a result,
Specific anti-lightning strike scheme are as follows:
(1) for 1st area of aircraft lightning region, the surface protecting layer of composite material parts can be made of the aluminium wire netting of 97.7g/m2.Aluminium
The mesh count of silk screen is 20 × 40 holes/(in) 2, and aluminium wire diameter is 0.14mm.
(2) for 2nd area of aircraft lightning region, the surfacecti proteon of composite material parts can be made of the aluminium wire netting of 48.8g/m2
Layer.The mesh count of aluminium wire netting is also 20 × 40 holes/(in) 2, and aluminium wire diameter is 0.1mm.
Early stage studying lightning Protection layer, attempt to that conductive paint is used to prove as lightning Protection layer, but through lightning test:
Aluminium, copper, graphite or carbon black filled conductive paint are invalid to the lightning Protection of advanced composite material.With the silver of 0.0762mm thickness
The highest thunder-strike current for filling the conductive paint protection injury-free permission of advanced composite material is 50 kA.Conductive paint is seldom used at present
Lightning Protection layer as advanced composite structure.
Metal foil
Lightning Protection can be carried out with aluminium foil or aluminum foil strip to the polymer matrix composites of boron fibre, fibre reinforced.Concrete scheme
Are as follows:
(1) it is glued on the outer surface of component with the aluminium foil of 0.0762mm thick (to the aluminium foil of 0.1524mm thickness of region 1), shape
At the conductive layer for lightning Protection.It is amenable to the simulation lightning test in region 2 and not damaged.But lightning discharge attachment point is attached
Close aluminium foil is evaporated, and the size of evaporating area is between 16mm × 21mm~29mm × 33mm.To prevent matrices of composite material quilt
It burns or evaporates, while increasing its anti-lightning strike ability, it will usually the laying high insulation between aluminium foil and composite material.But make
With this protective layer to the more demanding of aircaft configuration surface inspection, needs to repair aluminium foil in time and be evaporated place, and this office
Repair general relatively difficult in portion.
(2) with the chaff (to the chaff of the thickness 0.1524mm thickness of region 1) of width 25mm, thickness 0.0762mm, spacing
50mm is configured on composite product surface along perpendicular to airflow direction, is confirmed through simulation lightning test, with aluminium foil all standing
It compares in composite material surface with protection effect relatively, but the electric arc when being struck by lightning, between adjacent chaff
A degree of destruction can be generated to matrix, need often to carry out examination and maintenance.
Discharge brush
The electrostatic of aircraft is discharged into the atmosphere by the discharge brush of plane airfoil rear, so as to avoid the electrostatic of accumulation
In aircraft surfaces, aircraft is caused to damage.
Discharge brush itself is unable to lightning protection, the electrostatic charge on its effect mainly discharge aircraft, so that aircraft be protected to power on
The radio interference of sub- equipment.Discharge brush is made of brush holder support and pedestal, pedestal and aerofoil metal structure fastener and adhesive
Connection.The top of discharge brush has filled the metal needle of a very little, and due to the effect of electromagnetic field in atmosphere, band point charge all collects
In on the metal needle on discharge brush top, since charge buildup is on very small syringe needle, be not necessarily to very high electricity
It will lead to the disruptive discharge in air or cloud layer between hydrone in the state of lotus energy accumulation, cause putting for the small energy in part
Electric (appellation point discharge) (if the electric current of discharge brush is with ampere meter, the electric current being struck by lightning will be in terms of kilo-ampere).Discharge brush
It is separately mounted to the outside rear of the big wing and horizontal stabilizer, the top rear edge of vertical tail.
Application mode described in the invention can be adjusted according to the actual situation, be not for limiting invention wound
It makes.Technical solution provided by the present invention is described in detail above；The explanation of the present embodiment is merely used to help understand
Method of the invention.Application mode of the present invention can be adjusted according to the actual situation, be not for limiting the present invention.
Claims (8)
1. a kind of aircraft avoids lightning stroke method, which is characterized in that the described method comprises the following steps:
Step 1 carries out lightning stroke adhering zone to aircraft surfaces and demarcates；
Step 2 judges whether that being applicable in analogue method divides lightning stroke adhering zone, if applicable, then uses analogue method, such as
Fruit is not applicable, then first determines initial guide's adhering zone based on the lightning stroke adhering zone demarcated；
Step 3 successively divides lightning stroke adhering zone based on by number of lightning strokes or return stroke times；
Step 4 divides aircraft lightning region and carries out simulation calculation, and obtained aircraft surfaces field strength distribution obtains endpoint attachment
Point and burble point, the injection in aircraft surfaces of further obtaining being struck by lightning, disjoint paths；
Step 5 carries out protection design to aircraft in lightning region.
2. aircraft according to claim 1 avoids lightning stroke method, which is characterized in that step 1 refers specifically to: according to aircraft table
Face easily occurs a possibility that lightning stroke attachment and aircraft surfaces is done following division:
The area 1A --- region is fought back for the first time；
The area 1B --- long lasting for counterattack region for the first time；
The area 1C --- transition region is fought back for the first time；
The area 2A --- scan lightning region；
The region 2B --- lightning strike area is scanned in attachment for a long time；
3 regions --- not in the region of 1A, 1B, 1C, 2A and 2B.
3. aircraft according to claim 2 avoids lightning stroke method, which is characterized in that pacify according to following in the region in step 3
Sequence determines:
Step 3.1, the region 1A, 1B is positioned,
Step 3.2, the region 1C is positioned,
Step 3.3, the region 2A, 2B is positioned,
Step 3.4, the region 1A, 1B, 2A, 2B, 1C side elongated area is positioned；
Step 3.5,3 regions are positioned；
Step 3.6, consider the division of overlapping region.
4. aircraft according to claim 2 avoids lightning stroke method, which is characterized in that in the step 4, be struck by lightning to aircraft
The method that region division carries out simulation calculation includes moment method, FInite Element, Finite-Difference Time-Domain Method.
5. aircraft according to claim 2 avoids lightning stroke method, which is characterized in that in the step 4, be struck by lightning in aircraft
The injection on surface, disjoint paths include following situations: head enters, and fuselage rear goes out；Or head enters, vertical tail goes out.
6. aircraft according to any one of claims 1 to 5 avoids lightning stroke method, which is characterized in that described in step 5
Protection design is carried out to aircraft in lightning region to refer specifically to carry out lightning-arrest design to aircraft surfaces using following several ways:
1) aluminium is sprayed, 2) add wire mesh, 3) reinforced using chaff, 4) implemented by discharge brush to aircraft surfaces
Electric discharge.
7. aircraft according to claim 6 avoids lightning stroke method, which is characterized in that the detailed process of the step 3 are as follows:
Step 3.1, the area 1A and 1B is positioned,
The second step of positioning lightning strike area is to determine the more multizone fought back may reach for the first time, including the area 1A, 1B, when guide reaches
Ground or other charge areas, triggering is when fighting back for the first time, and the distance that aircraft is flown over this period determines the region 1A from initial
The distance that attachment point rearwardly extends；The area 1A starting point is the end of initial guide's adhering zone, in 1B lightning adhering zone,
The lightning channel of initial guide's attachment region continues its whole life cycle；
Step 3.2, the area 1C is positioned,
The area 1C is selected in the region aircraft surfaces 1A rear portion, and flying height is to scan guide's energy between 1500m to 3000m herein
Get at the place reached；
Step 3.3, the positioning in the region 2A and 2B,
The surface of the region 1C tail portion backward is the starting point in the area 2A, and the rear edge surface of the region 2A tail portion backward is the area 2B
The starting point in domain；
Step 3.4,1A, 1B, 1C, 2A and 2B region extends laterally,
Determining arc or sweepback or wing and the affiliated region 1A and 1B of empennage wing tip surface region with winglet
When, it determines the horizontal point of contact of wing tip curvature, then the area 1A and 1B inwardly extends 0.5m；In addition, the area 1A and 1B
The inside 0.5m in domain is in the region 2A and 2B；
And, it has been determined that the region 1A, 1C, 1B, 2A, 2B, along wing root, the wing hangs engine and horizontal and vertical solid
Wing root is determined to the surface within respective edge 0.5m, is also considered within identical region；
Step 3.5, the positioning in region 3,
Those are not in the region 1A, 1B, 1C, 2A, 2B, and the surface that any lightning channel is impossible to adhere to is divided in 3
Region；3 regions contain the surface portion below other regions, and are directly adhering to or scanning between the adhering zone of channel
Conduct the region of conducting lightning currents；
Step 3.6, overlapping region,
Sometimes it fights back and is likely to occur in close to initial guide's attachment point for the first time, the surface area Ye 2A in the area 1A and 1C
In domain, subsequent counterattack occurs in the remaining place in the region 1A, and 3rd area are also within other all areas.
8. aircraft according to claim 7 avoids lightning stroke method, which is characterized in that described based on the lightning stroke demarcated attachment
Region first determine guide's adhering zone be specially
Step 3.0, it is struck by lightning the determination of initial guide's adhering zone,
Using similarity method, test or analytic approach, i.e. spin analytic approach, EFM, determine that the initial guide that is struck by lightning may adhere to aircraft
Region；Typical initial attachment region includes end, and such as head, wing, empennage wing tip, rotor end, some engines are short
Cabin, cockpit window frame and other apparent protrusions.
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| CN112464361A (en) * | 2020-11-05 | 2021-03-09 | 陕西飞机工业（集团）有限公司 | Lightning partition dividing method |
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