CN107578145B - A kind of aircraft scene operation state impact evaluation method - Google Patents
A kind of aircraft scene operation state impact evaluation method Download PDFInfo
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Abstract
The invention discloses a kind of aircraft scene operation state impact evaluation methods, on the basis of obtaining airdrome scene essential characteristic and aircraft model information, according to the microcosmic running track for the aircraft slide path computing aircraft landing gear collected, and from undercarriage to road face and aircraft wing, engine to two, the dynamic effects region of peripheral space in terms of judge influence that aircraft scene slides.
Description
Technical field
Present invention relates particularly to a kind of aircraft scene operation state impact evaluation methods.
Background technique
In nearest 20 years, aircraft industry is grown rapidly, and aerodrome traffic is increasingly busy, to airfield extension and newly-built need
Growth is asked, the type type of Airport Operation is further abundant, taxi circuit more sophisticated.At the same time, since what airport fell behind sets
Arrange it is standby, blank pipe or operation controllers new architecture is unfamiliar with, a variety of factors exacerbate airdrome scene accident generation wind
Danger.Such as once repeatedly reported that generation staff sucked murderous event and White Cloud Airport aircraft by engine
The event etc. of engines tail blowing roadside Sign Board.These events have reflected the seriousness of scene operational safety problem.
Being directed to the research of airdrome scene safety both at home and abroad at present is mainly aircraft scene conflict Resolution, and less consideration is slided
When influence of the aircraft to peripheral facility and people, this problem primary focus is aircraft itself in scene running track and right
The research of the influence area on periphery.The country is also fewer for the research of these two aspects or more unilateral.
In conjunction with aircraft scene running track, the influence area of aircraft scene operation is assessed, is conducive to evade potential
Risk of collision has stronger reference value, but its research is still at present blank, therefore the aircraft scene operation state zone of influence
Domain research is to need to carry out.
Summary of the invention
It is an object of the invention to overcome deficiency in the prior art, provides a kind of aircraft scene operation coasting-flight phase and deposit
In the judgment method of security risk, realizing aircraft, in scene operation, influence area is determining and security risk is assessed.
In order to solve the above technical problems, the present invention provides a kind of aircraft scene operation state impact evaluation method,
It is characterized in, comprising the following steps:
Step S1 establishes airdrome scene structure chart, determines the position coordinates of scene inner taxiway section parameter and item to be assessed
Information；
Step S2, the sliding path data according to aircraft in scene, the cunning that the acquisition aircraft slide stage successively passes through
The running track of trade section and its geometric center；
Step S3 determines the fortune of the aircraft landing gear in the taxiway section passed through according to the running track of aircraft
Row track；
Step S4 calculates aircraft landing gear to the dynamic effects area in road face according to the running track of aircraft landing gear
Domain；
Step S5 calculates aircraft to the dynamic effects region of peripheral space according to the running track of aircraft landing gear；
Step S6, assessment aircraft slide stage whether there is security risk in each taxiway section: first according in step S4
The aircraft landing gear of acquisition is to the taxiway section parameter obtained in the dynamic effects region in road face and step S1, and assessment is when advancing slip
Trade section whether there is security risk；Again according to the aircraft obtained in step S5 to the dynamic effects region of peripheral space and step
Current taxiway section is assessed with the presence or absence of security risk in the item position to be assessed determined in rapid S1；It is both not present when aforementioned
When security risk, then security risk is not present when this taxiway section is run for aircraft.
Further, in the step S1, taxiway section includes line sliding section and taxiing turn section two types, directly
Line coasting-flight phase parameter includes starting point coordinate, terminating point coordinate, length and width；Taxiing turn section parameter includes that starting point is sat
Mark, terminating point coordinate, width, turning radius and turning degree.
Further, in step S3, determine that running track detailed process of the aircraft landing gear in taxiway section includes:
Step S31, when aircraft is located at line sliding section, the sliding trajectory of aircraft is located at the center line of taxiway,
Front-wheel and main landing gear center follow center line linear running track；
Step S32, when aircraft is located at taxiing turn section, aircraft front-wheel is travelled along taxi way center line, and master rises and falls
Frame center follows turnaround section circular arc running track, and arc radius is current taxiing turn section turning radius Rj, total radian for turning over
For current taxiing turn section turning degree θj；
When the front-wheel S of aircraft moves to certain point on circular arc, angle corresponding with circle center line connecting is θS, according to aircraft base
Standard length d andWith auxiliary formulaDetermine the steering angle under current time
β, and foundationDetermine that two main wheel center U of undercarriage are inscribed and center line in steering angle β
Offset λ.
Further, aircraft landing gear is calculated in step S4 includes: to the dynamic effects region process in road face
Step S41, when aircraft is located at line sliding section, aircraft landing gear is taxiway to the influence area in road face
The distance range of each half main wheel track of center line or so；
Step S42, when aircraft is located at taxiing turn section, aircraft landing gear is in taxiway to the influence area in road face
Heart line leans on half main wheel track on the inside of taxiway by the distance range and taxi way center line of half main wheel track on the outside of taxiway
Distance is plus curve inner side main wheel and guides existing maximum offset range.
Further, aircraft includes that wing and engine are right respectively to the dynamic effects region of peripheral space in step S5
The dynamic effects region of peripheral space.
Further, determine aircraft wing to the dynamic effects region of peripheral space:
Step S51, when aircraft is located at line sliding section, wing is taxiway to the dynamic effects region of peripheral space
Straight line portion center line two sides half span regional scope；
Step S52, when aircraft is located at taxiing turn section, wing turns the dynamic effects region of peripheral space for taxiway
On the outside of bight portion center line half spanwise length region and inside half spanwise length plus curve inner side main wheel with
The maximum offset regional scope of leading line；
Further, engine includes that air intake duct influence area and tail spray influence area two to the coverage of peripheral space
A part；
Step S53, engine inlets influence area be using the midpoint of part before engine as the semicircular area in the center of circle,
According to the distance between two outboard engines, the center location of engine inlets influence area is determined, according to engine charge
Road zone of influence radius determines semicircle engine inlets influence area；
Step S54, engines tail spray influence area include intermediate rectangular part and rectangle part two sides apex angle be 15 ° etc.
Lumbar triangle shape, the side length of intermediate rectangular part and wing line level be between two outboard engines at a distance from, it is vertical with wing line
Partial side length is that tail spray influences distance, and a length of tail spray of the waist of left and right isosceles triangle influences distance；This engine coverage
Perpendicular bisector about two main wheel line of undercarriage is symmetrical, i.e., engine coverage can be right by its with respect to aircraft running track
Claim line explanation；
Influence model is determined according to aircraft engine coverage determined above, and according to the coast period being presently in
Enclose the position of relative motion track:
When aircraft is located at line sliding section, the middle line of the coverage is overlapped with taxiway middle line；
When aircraft is located at taxiing turn section, the middle line of the coverage is parallel with taxiway middle line and close to taxiway
The line of offset inboard is overlapped, i.e., whole using taxiway middle line as reference line, toward taxiway offset inboard maximum offset distance.
Further, the dynamic effects region and taxiway section parameter according to aircraft landing gear to road face, assessment are current
Taxiway section includes: with the presence or absence of the detailed process of security risk
When line sliding section, taxiway straight line portion width should be not less than the straightway coverage that step S41 is determined；
When taxiing turn section, turn fractions taxiway width should not less than step S42 determine turnaround section section coverage with
The sum of taxiway roadside personal distance.
If meeting above-mentioned condition, undercarriage is on road face without influence.
Further, according to aircraft to the dynamic effects region and item position to be assessed of peripheral space, assessment is when advancing slip
Trade section includes: with the presence or absence of the detailed process of security risk
Step S61, dynamic effects region and item location information to be assessed according to aircraft wing to peripheral space, assessment
Current taxiway section whether there is the detailed process of security risk are as follows:
When line sliding section, aircraft machine is lower than in taxiway straight line portion center line two sides half span regional scope
If someone or item to be assessed, are determined as danger in the peripheral space region of wing height and position；
When taxiing turn section, half spanwise length region and inside two on the outside of taxiway turn segment centerline/
One spanwise length is lower than aircraft wing height and position plus the maximum offset regional scope of curve inner side main wheel and leading line is interior
If peripheral space region in someone or item to be assessed, be determined as danger；
If not being determined as danger above, wing is on peripheral space without influence；
Step S62, dynamic effects region and item location information to be assessed according to aircraft engine to peripheral space, is commented
Estimating current taxiway section whether there is the detailed process of security risk are as follows:
When line sliding section, the middle line of influence area is overlapped with taxiway middle line, when item to be assessed is located at influence area
Within the scope of when, it is possible that by engine suck or spray reclamation tail gas burning, be determined as danger；
When taxiing turn section, the middle line of influence area is parallel with taxiway middle line and close to peak excursion on the inside of taxiway
Line be overlapped, when object is located within the scope of influence area, it is possible that by engine sucking or ejection reclamation tail gas burning, sentence
It is set to danger；
If not being determined as danger above, engine is on peripheral space without influence.
Compared with prior art, the beneficial effects obtained by the present invention are as follows being: the principle of the invention is simple, compensates for the country to boat
The blank of pocket scene operation state influence area assessment of risks, from the microcosmic running track of aircraft landing gear calculates aircraft
The road Luo Jiadui face, aircraft slide influence judgement, while the present invention to the dynamic effects region of peripheral space and aircraft scene
Also by scene and aircraft running track information data, future can be according to the visual zone of influence of real time data the Realization of Simulation
Domain views make it have universality.
Detailed description of the invention
Fig. 1 is the flow chart of the method for the present invention；
Fig. 2 is the microcosmic running track calculation flow chart of aircraft landing gear；
The microcosmic running track of undercarriage aids in illustrating figure when Fig. 3 is the line sliding stage；
The microcosmic running track of undercarriage aids in illustrating figure when Fig. 4 is taxiing turn section；
Fig. 5 is dynamic effects region calculation flow chart of the aircraft landing gear to road face；
Fig. 6 is dynamic effects region calculation flow chart of the aircraft to peripheral space；
Fig. 7 is that the coverage of engine aids in illustrating figure；
Fig. 8 is that aircraft scene slides influence decision flow chart.
Specific embodiment
The invention will be further described below in conjunction with the accompanying drawings.Following embodiment is only used for clearly illustrating the present invention
Technical solution, and not intended to limit the protection scope of the present invention.
As shown in Figure 1, a kind of aircraft scene operation state impact evaluation method of the invention, comprising the following steps:
Step S1 establishes airdrome scene structure chart, determines the position coordinates of scene inner taxiway section parameter and item to be assessed
Information.
Detailed process is as follows for it:
(1.1) using airport reference point as coordinate origin, due east direction is positive direction of the x-axis, and direct north is positive direction of the y-axis,
Establish rectangular coordinate system；
(1.2) according to the structure of the runway on airport and taxiway, the connection crosspoint of runway and taxiway everywhere is obtained
(because the end of taxiway is also runway of ining succession, being also required to consider runway point), and according to runway point { R1, R2, R3...,
Ri... and taxiway point { T1, T2, T3..., Ti... crosspoint is sorted out, each crosspoint is obtained according to the coordinate system established
Coordinate；Label facility, equipment in airport etc. are the items to be assessed whether influenced in aircraft slide, for convenience, this
These facilities, equipment are known as item to be assessed in invention, obtain item coordinate to be assessed according to the coordinate system established.
(1.3) crosspoint sorted out according to step (1.2), all taxiway sections that successively logging machine place is split are sliding
Trade section is made of starting endpoint and termination end points, and all points belong to the runway point or taxiway point set of (1.2) classification.
Simultaneously for each taxiway section, taxiway parameter is recorded, includes taxiway point belonging to the starting of taxiway section, terminating point
TiOr runway point RiCorresponding coordinate, the type (line sliding section or taxiing turn section) of taxiway section.Line sliding section simultaneously
Also need record length Li, width Wi, taxiing turn section also need record width Wi, turning radius RjAnd turning degree θj。
Step S2, the sliding path data according to aircraft in scene, the cunning that the acquisition aircraft slide stage successively passes through
The running track of trade section and its geometric center.
(2.1) the sliding path data according to the aircraft of collection in scene, the cunning on the airport in conjunction with described in step (1.3)
Trade section, sorts out all taxiway sections that the aircraft slide stage successively passes throughWherein according to the class of taxiway section
Type is different,It include line sliding sectionWith taxiing turn section
(2.2) the aircraft slide road section obtained according to (2.1)In conjunction with sliding in (1.3)
Road section parameter can obtain the track that aircraft geometric center is passed through.
It is also related with aircraft concrete type when determining aircraft scene operation state impact evaluation, therefore according to boat
Pocket type obtains aircraft information from aircraft handbook.The specific geometric center comprising aircraft, spanwise length b, chord-length
Spend the structural informations such as c；Datum length (distance of the front-wheel of undercarriage to main landing gear center) d, main wheel track (two main wheel of undercarriage
Between distance) the undercarriages information such as D；Distance D between two outboard engines1, engine width LP, engine inlets shadow
Ring area's radius Rpower, tail spray influence distance X1Equal engine informations.
Since each composition portion of aircraft is relatively fixed, the track that geometric center described in foundation aircraft is passed through,
With above-mentioned aircraft model information, is converted by distance, can determine undercarriage, the machine in track any time aircraft
The wing, engine relative position.
Step S3 determines the fortune of the aircraft landing gear in the taxiway section passed through according to the running track of aircraft
Row track.
Fig. 2 is the microcosmic running track calculation flow chart of aircraft landing gear, the corresponding step S3 include it is following step by step:
(3.1) according to aircraft running track, coast period locating for aircraft is judged one by one；
(3.2) when aircraft is located at the line sliding stage, the sliding trajectory of aircraft is located at the middle line of taxiway, front-wheel
Linear running track is followed with main landing gear center, as shown in Figure 3；
(3.3) when aircraft is located at taxiing turn section, aircraft front-wheel is travelled along taxi way center line (i.e. guide line),
Main landing gear center follows circular arc running track as shown in figure 4, arc radius is current taxiing turn section turning radius Rj, turn over
Total radian be current taxiing turn section turn degree θj。
When the front-wheel S of aircraft moves to certain point on circular arc, angle corresponding with circle center line connecting is θS, according to aircraft base
Standard length d andWith auxiliary formulaDetermine the steering angle under current time
β, and foundationDetermine that two main wheel center U of undercarriage are inscribed and guide line in steering angle β
Offset λ.
Step S4 calculates aircraft landing gear to the dynamic effects area in road face according to the running track of aircraft landing gear
Domain；
Fig. 5 is aircraft landing gear to the dynamic effects region calculation flow chart in road face, the corresponding step (4) include with
Under step by step:
(4.1) judge the coast period that aircraft is presently in；
(4.2) according to coast period locating for aircraft, in conjunction with the step (3) aircraft microscopic motion track,
Determine aircraft undercarriage track under locating coast period.
(4.3) since undercarriage is relatively fixed with respect to the centroid position of aircraft, and the front-wheel edge of coast period undercarriage
Taxiway traveling, aircraft landing gear is mainly reflected in the region that two main wheels streak to the influence area of scene.
(4.3.1) is located at line sliding section when aircraftWhen, aircraft landing gear is to the influence area in road face
The distance range (D/2) of each half main wheel track of taxi way center line or so；
(4.3.2) aircraft is located at taxiing turn sectionWhen, aircraft landing gear is to slide to the influence area in road face
Trade center line leans on one on the inside of taxiway by the distance range (D/2) and taxi way center line of half main wheel track on the outside of taxiway
The distance of half main wheel track is plus curve inner side main wheel and guides existing maximum offset range (D/2+ λ).
Step S5 calculates aircraft to the dynamic effects region of peripheral space according to the running track of aircraft landing gear；
Fig. 6 is dynamic effects region calculation flow chart of the aircraft to peripheral space, and the corresponding step (5) includes following
Step by step:
(5.1) aircraft described in includes wing and engine respectively to periphery sky to the dynamic effects region of peripheral space
Between dynamic effects region；
(5.2) judge the coast period that aircraft is presently in；
(5.3) according to coast period locating for aircraft, in conjunction with the step (3) aircraft microscopic motion track,
Determine aircraft under locating coast period undercarriage track (calculate undercarriage track be because using undercarriage as referential,
Two main wheels of undercarriage are square under the wings of an airplane)；
(5.4) since the main wheel of tricycle landing gear aircraft is all mounted on substantially below wing, with wing relative position
It is fixed, main wheel track is determined according to the step (5.3) aircraft landing gear track, in conjunction with by obtaining in the step (2.2)
Main wheel and the positional relationship and spanwise length b of wing determine aircraft wing to the dynamic effects region of peripheral space.
(5.4.1) is located at line sliding section when aircraftWhen, wing is to the dynamic effects region of peripheral space
Taxiway straight line portion center line the two sides half span (b/2) regional scope；
(5.4.2) aircraft is located at taxiing turn sectionWhen, wing is to slide to the dynamic effects region of peripheral space
The half span region (b/2) and the inside half span add curve inner side main wheel on the outside of the turn fractions center line of trade
With maximum offset (b/2+ λ) regional scope of leading line.
(5.5) since first three point type engine location is relatively fixed in main landing gear position, according to the step (5.3) institute
It states and combines engine coverage of the aircraft under current sliding state true in specific coast period aircraft landing gear position
Aircraft engine is determined to the dynamic effects region of peripheral space.
The coverage of engine described in (5.5.1) is as shown in fig. 7, spray the zone of influence comprising air intake duct influence area and tail
Two, domain part.
(5.5.1.1) engine inlets influence area is the semicircle area using the midpoint of part before engine as the center of circle
Domain, according to the distance D between two outboard engines1, determine the center location of engine inlets influence area, i.e., in wing line
Point or so each D1/ 2 distances, according to engine inlets zone of influence radius RpowerDetermine the semicircle engine inlets zone of influence
Domain；
It is irregular area as shown in Figure 7 that (5.5.1.2) engines tail, which sprays influence area, includes intermediate rectangular part
The isosceles triangle for being 15 ° with rectangle part two sides apex angle, according to the distance D between two outboard engines1With tail spray influence away from
From X1, determine that the side length of intermediate rectangular part and wing line level is D1, the side length with wing line vertical component is X1, left and right etc.
The a length of X of the waist of lumbar triangle shape1；
The engine coverage that foundation step (5.5.1.1) described in (5.5.1.3) and (5.5.1.2) are determined is about rising
The perpendicular bisector for falling two main wheel line of frame is symmetrical, i.e., engine coverage can be added with respect to aircraft running track by its line of symmetry
Upper effect of irregular region is illustrated；
(5.5.2) according to described in (5.5.1) determines aircraft engine coverage, and slides rank according to what is be presently in
Section determines the position of coverage relative motion track；
(5.5.2.1) is located at line sliding section when aircraftWhen, the middle line and taxiway middle line of the coverage
It is overlapped；
(5.5.2.2) is located at taxiing turn section when aircraftWhen, the middle line and taxiway middle line of the coverage
Parallel and line close to taxiway offset inboard is overlapped, i.e., whole using taxiway middle line as reference line, the lateral deviation in taxiway
Move λ distance.
Step S6, according to coasting-flight phase locating for aircraft, the aircraft landing gear in conjunction with described in step S4 is to road face and step S1
The taxiway section parameter of middle determination, and the aircraft in conjunction with described in step S5 is in the dynamic effects region and step S1 of peripheral space
Current coasting-flight phase is assessed with the presence or absence of security risk in determining item position to be assessed；
Fig. 8 is that aircraft scene slides influence decision flow chart, the corresponding step (6) include it is following step by step:
(6.1) the aircraft scene described in slides the influence and wing influenced judgement comprising undercarriage to road face and starts
The influence two parts of machine to peripheral space；
(6.2) any time slided for aircraft in scene determines coasting-flight phase locating for aircraft, and according to described
The parameter information of the coasting-flight phase determined in step (2) and the more specific location information of this section of item to be assessed；
(6.3) undercarriage determining according to the step (4) judges that taxiway width is to the dynamic effects region in road face
(6.3.1) described in no satisfaction and (6.3.2) requirement, the moment undercarriage is on road face without influence if meeting；
(6.3.1) taxiway straight line portion width should determine straightway coverage not less than step (4.3.1)；
It is no less than at a distance from roadside between the safety of taxiway roadside on the outside of the aircraft main wheel of (6.3.2) taxiway turn part
Every main wheel deviates inwardly when due to turning, and turn fractions taxiway width should determine turnaround section section not less than step (4.3.2)
The sum of coverage and taxiway roadside personal distance；The taxiway roadside personal distance is true by Flying Area in Airport index
It is fixed.
(6.4) aircraft wing is determined to the dynamic effects region of peripheral space, in conjunction with aircraft according to the step (5)
Locating taxiway part item location information to be assessed, the judgment rule of (6.4.1) and (6.4.2) according to described in, if not determining
For danger, then the moment wing is on peripheral space without influence；
It is lower than aircraft machine in (6.4.1) taxiway straight line portion center line the two sides half span (b/2) regional scope
If someone or other items to be assessed, are determined as danger in the peripheral space region of wing height and position；
The half span region (b/2) and the inside half wing on the outside of (6.4.2) taxiway turn segment centerline
Exhibition is plus the maximum offset (b/2+ λ) of curve inner side main wheel and leading line if the interior someone in region or other items to be assessed are set
It applies, is then determined as danger；
(6.5) aircraft engine is determined to the dynamic effects region of peripheral space, in conjunction with aviation according to the step (5)
The item location information to be assessed of taxiway part locating for device, the judgment rule of (6.5.1) and (6.5.2) according to described in, if not sentencing
It is set to danger, then the moment engine is on peripheral space without influence；
(6.5.1) taxiway straight line portion coverage is irregular figure as shown in Figure 7, wherein in irregular figure
Line is overlapped with taxiway middle line, when item to be assessed is located within the scope of influence area, it is possible that being sucked or being sprayed by engine
Reclamation tail gas burning out, is determined as danger；
(6.5.2) taxiway turn some effects range is irregular figure as shown in Figure 7, wherein in irregular figure
Line it is parallel with taxiway middle line and close to taxiway offset inboard λ line be overlapped, when item to be assessed be located at influence area range it
When interior, it is possible that the reclamation tail gas burning for being sucked or being sprayed by engine, is determined as danger；
(6.6) when (6.3) to (6.5) are determined as no danger, i.e., it is believed that current coast period is not present
Security risk.
Step S7 carries out security risk to entire coasting-flight phase and comments according to the determination flow that step S6 aircraft slide influences
Estimate.
Microcosmic running track of the present invention according to the aircraft slide path computing aircraft landing gear collected, and from rising and falling
The road Jia Dui face and aircraft wing, engine judge that aircraft scene slides to two, the dynamic effects region aspect of peripheral space
Influence, be conducive to evade potential undercarriage and destroy road face, wing and the collision of scene object and engine sucking or spray
The kinds of risks such as scene people/item to be assessed equipment are damaged, there is stronger reference value.
The above is only a preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, without departing from the technical principles of the invention, several improvements and modifications, these improvements and modifications can also be made
Also it should be regarded as protection scope of the present invention.
Claims (9)
1. a kind of aircraft scene operation state impact evaluation method, characterized in that the following steps are included:
Step S1 establishes airdrome scene structure chart, determines the location coordinate information of scene inner taxiway section parameter and item to be assessed；
Step S2, the sliding path data according to aircraft in scene, the taxiway that the acquisition aircraft slide stage successively passes through
The running track of section and its geometric center；
Step S3 determines the operation rail of the aircraft landing gear in the taxiway section passed through according to the running track of aircraft
Mark；
Step S4 calculates aircraft landing gear to the dynamic effects region in road face according to the running track of aircraft landing gear；
Step S5 calculates aircraft to the dynamic effects region of peripheral space according to the running track of aircraft landing gear；
Step S6, assessment aircraft slide stage whether there is security risk in each taxiway section:
First slided according to the aircraft landing gear obtained in step S4 to what is obtained in the dynamic effects region in road face and step S1
Road section parameter assesses current taxiway section with the presence or absence of security risk；
It is to be assessed to what is determined in the dynamic effects region of peripheral space and step S1 according to the aircraft obtained in step S5 again
Current taxiway section is assessed with the presence or absence of security risk in item position；
When aforementioned both there is no when security risk, then security risk is not present when this taxiway section is run for aircraft.
2. a kind of aircraft scene operation state impact evaluation method according to claim 1, characterized in that in the step
In rapid S1, taxiway section includes line sliding section and taxiing turn section two types, and line sliding section parameter includes that starting point is sat
Mark, terminating point coordinate, length and width；Taxiing turn section parameter includes starting point coordinate, terminating point coordinate, width, turning half
Diameter and turning degree.
3. a kind of aircraft scene operation state impact evaluation method according to claim 2, characterized in that step S3
In, determine that running track detailed process of the aircraft landing gear in taxiway section includes:
Step S31, when aircraft is located at line sliding section, the sliding trajectory of aircraft is located at the center line of taxiway, front-wheel
Center line linear running track is followed with main landing gear center；
Step S32, when aircraft is located at taxiing turn section, aircraft front-wheel is travelled along taxi way center line, in main landing gear
The heart follows turnaround section circular arc running track, and arc radius is current taxiing turn section turning radius Rj, the total radian turned over is to work as
Before slide turnaround section turning degree θj；
When the front-wheel S of aircraft moves to certain point on circular arc, angle corresponding with circle center line connecting is θS, long according to aircraft reference
Spend d andWith auxiliary formulaDetermine the steering angle β under current time, and according to
According toDetermine that two main wheel center U of undercarriage inscribe the offset with center line in steering angle β
λ。
4. a kind of aircraft scene operation state impact evaluation method according to claim 3, characterized in that in step S4
Calculate aircraft landing gear includes: to the dynamic effects region process in road face
Step S41, when aircraft is located at line sliding section, aircraft landing gear is taxiway center to the influence area in road face
The distance range of each half main wheel track of line or so；
Step S42, when aircraft is located at taxiing turn section, aircraft landing gear is taxi way center line to the influence area in road face
Distance of the distance range and taxi way center line of half main wheel track by half main wheel track on the inside of taxiway on the outside of taxiway
In addition the maximum offset range of curve inner side main wheel and guide line.
5. a kind of aircraft scene operation state impact evaluation method according to claim 3, characterized in that in step S5
Aircraft includes wing and engine respectively to the dynamic effects region of peripheral space to the dynamic effects region of peripheral space.
6. a kind of aircraft scene operation state impact evaluation method according to claim 5, characterized in that determine aviation
Dynamic effects region of the device wing to peripheral space:
Step S51, when aircraft is located at line sliding section, wing is taxiway straight line to the dynamic effects region of peripheral space
Segment centerline two sides half span regional scope；
Step S52, when aircraft is located at taxiing turn section, wing is taxiway turn portion to the dynamic effects region of peripheral space
Half spanwise length region and inside half spanwise length are plus curve inner side main wheel and guiding on the outside of the line of branch center
The maximum offset regional scope of line；
7. a kind of aircraft scene operation state impact evaluation method according to claim 6, characterized in that engine pair
The coverage of peripheral space includes that air intake duct influence area and tail spray the part of influence area two；
Step S53, engine inlets influence area are using the midpoint of part before engine as the semicircular area in the center of circle, foundation
Distance between two outboard engines determines the center location of engine inlets influence area, according to engine inlets shadow
It rings area's radius and determines semicircle engine inlets influence area；
Step S54, engines tail spray the isosceles three that influence area includes intermediate rectangular part and rectangle part two sides apex angle is 15 °
It is angular, the side length of intermediate rectangular part and wing line level be between two outboard engines at a distance from, with wing line vertical component
Side length be that tail spray influences distance, a length of tail spray of the waist of left and right isosceles triangle influences distance；This engine coverage about
The perpendicular bisector of two main wheel line of undercarriage is symmetrical, i.e., engine coverage can be by its line of symmetry with respect to aircraft running track
Explanation；
Coverage phase is determined according to aircraft engine coverage determined above, and according to the coast period being presently in
To the position of running track:
When aircraft is located at line sliding section, the middle line of the coverage is overlapped with taxiway middle line；
When aircraft is located at taxiing turn section, the middle line of the coverage is parallel with taxiway middle line and on the inside of taxiway
The line of offset is overlapped, i.e., whole using taxiway middle line as reference line, toward taxiway offset inboard maximum offset distance.
8. a kind of aircraft scene operation state impact evaluation method according to claim 4, characterized in that according to aviation
Current taxiway section is assessed with the presence or absence of security risk in dynamic effects region and taxiway section parameter of the device undercarriage to road face
Detailed process includes:
When line sliding section, taxiway straight line portion width should be not less than determining straightway coverage；
When taxiing turn section, turn fractions taxiway width should pacify not less than turnaround section section coverage and taxiway roadside is determined
The sum of full interval；
If meeting above-mentioned condition, undercarriage is on road face without influence.
9. a kind of aircraft scene operation state impact evaluation method according to claim 7, characterized in that according to aviation
For device to the dynamic effects region and item position to be assessed of peripheral space, assessing current taxiway section whether there is the tool of security risk
Body process includes:
Step S61, dynamic effects region and item location information to be assessed according to aircraft wing to peripheral space, assessment are current
Taxiway section whether there is the detailed process of security risk are as follows:
It is high lower than aircraft wing in the taxiway straight line portion center line two sides half span regional scope when line sliding section
If spending someone or item to be assessed in the peripheral space region of position, it is determined as danger；
When taxiing turn section, divide on the outside of taxiway turn segment centerline plus the region of half spanwise length and inside two
If one of the interior someone or item to be assessed of spanwise length plus the region of curve inner side main wheel and leading line maximum offset, sentence
It is set to danger；
If not being determined as danger above, wing is on peripheral space without influence；
Step S62 works as the dynamic effects region of peripheral space and item location information to be assessed, assessment according to aircraft engine
Preceding taxiway section whether there is the detailed process of security risk are as follows:
When line sliding section, the middle line of influence area is overlapped with taxiway middle line, when item to be assessed is located at influence area range
Within when, it is possible that by engine suck or spray reclamation tail gas burning, be determined as danger；
When taxiing turn section, the line of peak excursion on the inside of parallel with the taxiway middle line and close taxiway of the middle line of influence area
It is overlapped, when object is located within the scope of influence area, it is possible that the reclamation tail gas burning for being sucked or being sprayed by engine, is determined as
It is dangerous；
If not being determined as danger above, engine is on peripheral space without influence.
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