CN108417096A - A kind of state of flight appraisal procedure and system - Google Patents
A kind of state of flight appraisal procedure and system Download PDFInfo
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- CN108417096A CN108417096A CN201810100039.9A CN201810100039A CN108417096A CN 108417096 A CN108417096 A CN 108417096A CN 201810100039 A CN201810100039 A CN 201810100039A CN 108417096 A CN108417096 A CN 108417096A
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- G—PHYSICS
- G08—SIGNALLING
- G08G—TRAFFIC CONTROL SYSTEMS
- G08G5/00—Traffic control systems for aircraft, e.g. air-traffic control [ATC]
- G08G5/0047—Navigation or guidance aids for a single aircraft
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- G—PHYSICS
- G08—SIGNALLING
- G08G—TRAFFIC CONTROL SYSTEMS
- G08G5/00—Traffic control systems for aircraft, e.g. air-traffic control [ATC]
- G08G5/0095—Aspects of air-traffic control not provided for in the other subgroups of this main group
Abstract
The present invention provides a kind of state of flight appraisal procedure and systems, are related to airmanship field, including acquisition flight initial data；To institute's collected flight initial data decoding, decoding data is obtained；Obtain Standard Flight Data and predetermined deviation value；Based on the predetermined deviation value, the decoding data and the Standard Flight Data are compared and analyzed, and deviation situation of the decoding data relative to the Standard Flight Data is obtained according to the result of comparative analysis；State of flight assessment result is exported based on the deviation situation.To be based on RNP, automatically effective assessment is carried out to the state of flight of aircraft, is conducive to the response performance for promoting aircraft.
Description
Technical field
The present invention relates to airmanship fields, more particularly, to a kind of state of flight appraisal procedure and system.
Background technology
The performance indicator that aerospace applications meet level of security and other needs proposes high requirement.In navigation side
Face, required navigation performance (Required Navigation Performance, abbreviation RNP) have these performance indicators bright
Really regulation.RNP is the new technology flown using aircraft itself Airplane Navigation Equipment and global positioning system vector aircraft.RNP into
One step reduces the weather standard of flight, increases the range of choice in available course line, avoids bad weather condition well
Course line enables aircraft in mountain valley according to RNP programed flights to reduce influence of the landform to flight；It reduces simultaneously
Fuel cost and airport radar equipment cost increase maximum take-off and landing weight, reduce decision height and downslide gradient, improve
Flight natural rate of interest.
Just because of RNP is so important with safety for the steady of flight course, therefore, if the RNP in flight course
There is deviation in operation, is just easy to that the accident of fatal crass occurs.It is therefore desirable to establish a kind of state of flight based on RNP
Appraisal procedure and system.
Invention content
In view of this, the purpose of the present invention is to provide a kind of state of flight appraisal procedure and system, it is right to be based on RNP
The state of flight of aircraft carries out automatically effective assessment, is conducive to the response performance for promoting aircraft.
An embodiment of the present invention provides a kind of state of flight appraisal procedure, which includes：
Acquire flight initial data；
To institute's collected flight initial data decoding, decoding data is obtained；
Obtain Standard Flight Data and predetermined deviation value；
Based on the predetermined deviation value, the decoding data and the Standard Flight Data are compared and analyzed, and root
Deviation situation of the decoding data relative to the Standard Flight Data is obtained according to the result of comparative analysis；
State of flight assessment result is exported based on the deviation situation.
Further, the decoding data includes relative to the deviation situation of the Standard Flight Data：
Lateral deviation situation and vertically to deviation situation, wherein the lateral deviation situation includes at least one straight sides
To deviation situation and at least one camber line lateral deviation situation.
Further, the predetermined deviation value includes level-preset deviation and vertical predetermined deviation value；It is described vertical pre-
If deviation is including vertical boat diameter angle predetermined deviation value and vertically to predetermined deviation value.
Further, the acquisition modes of the straight line lateral deviation situation are as follows：
Based on the Standard Flight Data, the longitude and latitude value, standard of the standardized starting point of a straight line segment are obtained
The longitude and latitude value of terminating point；
Based on the decoding data, each practical flight point of under the same coordinate system, the corresponding straight line segment is obtained
Longitude and latitude value；
Based on the straight line segment and the level-preset deviation, the predetermined deviation range of line correspondence segment is established；
It detects whether each practical flight point is located within the scope of predetermined deviation, establishes the straight line lateral deviation situation.
Further, the acquisition modes of the camber line lateral deviation situation include：
Based on the Standard Flight Data, the standard center of circle of a camber line segment, the warp of standard radius, standardized starting point are obtained
The longitude and latitude value of angle value and latitude value, standard termination point；
Based on the decoding data, the practical turning path of under the same coordinate system, the corresponding camber line segment is obtained；
Based on the camber line segment and the level-preset deviation, the predetermined deviation range of corresponding camber line segment is established,
The predetermined deviation is ranging from using the standard center of circle as the fan ring in the center of circle；
Detect the predetermined deviation model whether each practical flight point on the practical turning path is located at the camber line segment
In enclosing, the camber line lateral deviation situation is established.
Further, described to include to the acquisition modes of deviation situation vertically when aircraft is flat to fly：
Based on the Standard Flight Data, the Standard Flight height in a flat flight section is obtained；
It based on the decoding data, obtains under the same coordinate system, the practical flight height of the corresponding flat flight section；
The height difference for obtaining the Standard Flight height and the practical flight height, as the first fiducial value；
Obtain it is described vertically to predetermined deviation value, as the second fiducial value；
Compare the magnitude relationship between first fiducial value and second fiducial value, as described vertically to deviation feelings
Condition.
Further, described to include to the acquisition modes of deviation situation vertically when aircraft rises or falls on the way：
Based on the Standard Flight Data, a standard vertical boat diameter angle for rising or falling segment is obtained；
Based on the decoding data, obtain it is under the same coordinate system, corresponding described in rise or fall the reality of segment and hang down
Sail through to diameter angle；
The angle difference for obtaining standard vertical boat diameter angle diameter angle of navigating vertical with the reality, as the first fiducial value；
The vertical boat diameter angle predetermined deviation value is obtained, as the second fiducial value；
The magnitude relationship for comparing first fiducial value and second fiducial value, as described vertically to deviation situation.
Further, which further includes：
Based on the lateral deviation situation, judge whether the event of transfiniting, the event that transfinites be practical flight point not
Entirely fall within the situation within the scope of corresponding predetermined deviation.
Further, which further includes：
Based on described vertically to deviation situation, judge whether that the event of transfiniting, the event that transfinites are first ratio
The case where being more than second fiducial value compared with value.
The embodiment of the present invention brings following advantageous effect：The present invention provides a kind of state of flight appraisal procedure, we
Method is based on RNP, and flight initial data and Standard Flight Data that practical flight obtains are compared and analyzed, aircraft can be obtained and exist
Deviation situation under each stage, and state of flight assessment result is obtained based on the deviation situation.Be conducive to staff's understanding
The operating condition of RNP, and adjusted in time, ensure having a smooth flight and safety for the aircraft based on RNP.
On the other hand, the present invention provides a kind of state of flight assessment system, including memory, processor and it is stored in institute
The computer program that can be run on memory and on the processor is stated, the processor executes real when the computer program
Existing following methods：
Acquire flight initial data；
To institute's collected flight initial data decoding, decoding data is obtained；
Obtain Standard Flight Data and predetermined deviation value；
Based on the predetermined deviation value, the decoding data and the Standard Flight Data are compared and analyzed, and root
Deviation situation of the decoding data relative to the Standard Flight Data is obtained according to the result of comparative analysis；
State of flight assessment result is exported based on the deviation situation.
Other features and advantages of the present invention will illustrate in the following description, also, partly become from specification
It obtains it is clear that understand through the implementation of the invention.The purpose of the present invention and other advantages are in specification, claims
And specifically noted structure is realized and is obtained in attached drawing.
To enable the above objects, features and advantages of the present invention to be clearer and more comprehensible, preferred embodiment cited below particularly, and coordinate
Appended attached drawing, is described in detail below.
Description of the drawings
It is required in being described below to embodiment for the clearer technical solution illustrated in the embodiment of the present invention
Attached drawing does simple introduction：
Fig. 1 is the flow diagram one of state of flight appraisal procedure provided in an embodiment of the present invention；
Fig. 2 is the flow diagram two of state of flight appraisal procedure provided in an embodiment of the present invention；
Fig. 3 is the straight line boat diameter schematic diagram of aircraft；
Fig. 4 is the flow diagram three of state of flight appraisal procedure provided in an embodiment of the present invention；
Fig. 5 is the camber line boat diameter schematic diagram of aircraft；
Fig. 6 is the flow diagram four of state of flight appraisal procedure provided in an embodiment of the present invention；
Fig. 7 is the flow diagram five of state of flight appraisal procedure provided in an embodiment of the present invention；
Fig. 8 is the structural schematic diagram of state of flight assessment system provided in an embodiment of the present invention.
Specific implementation mode
In order to make the object, technical scheme and advantages of the embodiment of the invention clearer, below in conjunction with attached drawing to the present invention
Technical solution be clearly and completely described, it is clear that described embodiments are some of the embodiments of the present invention, rather than
Whole embodiments.Based on the embodiments of the present invention, those of ordinary skill in the art are not making creative work premise
Lower obtained every other embodiment, shall fall within the protection scope of the present invention.
Unless specifically stated otherwise, the opposite step of the component and step that otherwise illustrate in the examples below, digital table
It is not limit the scope of the invention up to formula and numerical value.
At present because RNP is extremely important for the steady of flight course and safety, therefore, if the RNP in flight course
Operation there is deviation, be just easy to occur fatal crass accident.It is therefore desirable to establish a kind of flight shape based on RNP
State appraisal procedure and system.Based on this, a kind of state of flight appraisal procedure and system provided in an embodiment of the present invention can be based on
RNP carries out automatically effective assessment to the state of flight of aircraft, is conducive to the response performance for promoting aircraft.
For ease of understanding the present embodiment, first to a kind of state of flight assessment side disclosed in the embodiment of the present invention
Method describes in detail, as shown in Figure 1, the state of flight appraisal procedure includes：
Step S101, flight initial data is acquired.
In the embodiment of the present invention, collected flight initial data is with quick access recorder (Quick access
Recorder, abbreviation QAR) the form of file stored.
QAR refers in particular to the onboard flight data recording equipment with protective device, and recording capacity is usually 128MB, can be continuous
The time is recorded up to 600 hours, hundreds of data can be acquired simultaneously, the data acquired cover aircraft flight handling quality prison
Most parameters of control.The QAR equipment that domestic operator uses at present is all generally magneto-optic disk or personal computer memory card
International association (Personal Computer Memory Card International Association, abbreviation PCMCIA)
The storage mediums types such as card need to change storage medium by maintenance personnel after flying daily, then transfer to decoding department into
Row decoding is analyzed.
Step S102, the collected flight initial data of institute is decoded, obtains decoding data.
It is defined according to reference record, establishes decoding parameter library.Flight initial data is translated using the decoding parameter library
Code, will be converted to engineering Value Data, and these engineering Value Datas are stored in for the flight initial data of binary data format
Assessment system database.
Step S103, Standard Flight Data and predetermined deviation value are obtained.
First, course line, way point and the airport reference point etc. in RNP Standard Flight programs are obtained using navigational route database
Relevant parameters, as Standard Flight Data.Later, these Standard Flight Datas are stored in volatile data base and are made
To calculate lateral deviation situation, vertical missing situation, can also be used to as the assessment foundation for defining the event of transfiniting.
Next, in order to calculate lateral deviation situation and vertical missing situation, and the event of transfiniting is defined, the present invention is implemented
In example, it is also necessary to obtain predetermined deviation value, which can pre-set and be stored in volatile data base, Huo Zheyou
Staff is arranged temporarily, and it is not limited by the embodiments of the present invention.
Step S104, it is based on predetermined deviation value, decoding data and Standard Flight Data are compared and analyzed, and according to right
Result than analysis obtains deviation situation of the decoding data relative to Standard Flight Data.
By the decoding data after decoding, by the identification of outlier, rejecting, amendment, filtering and smooth etc. reason, can be used
Practical flight parameter and volatile data base in point different segments RNP Standard Flight Data it is unified to the same coordinate system, then
Using practical flight flight path and planning flight path, establish laterally and vertically to deviation mathematical model.
Wherein, in embodiments of the present invention, the longitude of the flight path way point in Standard Flight Data, latitude are in WGS-84
Coordinate system (World Geodetic System-1984 Coordinate System).A kind of geocentric coordinates used in the world
System.Coordinate origin is earth centroid, and the Z axis of the earth's core rectangular coordinate system in space is directed toward international time service organization to be determined in 1984
The agreement earth extreme direction of justice, X-axis are directed toward the intersection point of zero meridian plane and the equator CTP of BIH 1984.0, and Y-axis is hung down with Z axis, X-axis
Straight to constitute right-handed coordinate system, referred to as World Geodesic Coordinate System 1984 is united.
And longitude, the latitude of practical flight flight path are indicated using geographical coordinate.Geographical coordinate is to indicate ground with latitude, longitude
The spherical coordinate of millet cake position.For geographic coordinate system using the earth's axis as polar axis, all planes by earth south poles are referred to as meridian
Face.Geographical coordinate exactly indicates the spherical coordinate of ground point with longitude and latitude.
Since the data of Standard Flight Data and practical flight in different coordinates can not be handled, need
Both data to be converted under the same coordinate system first.The embodiment of the present invention is converted using Mercator projection.Mo Ka
Support projection is positive axis cylindrical equal-angle projection, also known as cylindrical equal-angle projection, one kind of conic projection, by Dutch map scholar Mercator
(G.Mercator) quasi- in wound in 1569.It is maximum to be influenced in map projection's method.
Imagine a cylinder consistent with ground axis direction to be cut in or cut in the earth, graticules is projected into circle by conformal projection
On cylinder, cylindrical surface is opened up after plane, to obtain plane geographic mesh.Through line it is one group of vertical equidistant straight parallel after projection
Line, weft are perpendicular to one group of parallel lines of warp.Each adjacent weft interval is increased from equator to the two poles of the earth.Where any takes up an official post
To length ratio be equal, i.e., no angular distortion, and area distortion is notable increases with far from benchmark weft.The projection has
There is loxodrome to be expressed straight characteristic, therefore is widely used in establishment nautical chart and aerial chart etc..
According to RNP standards, and the RNP programming criterion for combining China's RNP flight tests and operating experience to formulate obtain
The evaluation criteria of RNP, further according to what is occurred in the standard value of each flight parameter as defined in RNP standardization programs and flight course
Alert message, whether flight parameter is beyond limitation during judging practical flight, if flight parameter is beyond the standard value limited
Or there is alert message, then it is demarcated as the event that transfinites.
It is counted according to the occurrence number for the event of transfiniting, if the event that transfinites repeats in same position, is needed
The event of transfiniting is analyzed, identifies the security risk.
Specifically, assessing the flight of aircraft to deviation situation by lateral deviation situation and vertically in the embodiment of the present invention
Quality defines the event of transfiniting.Wherein, lateral deviation situation includes at least one straight line lateral deviation situation and at least one camber line
Lateral deviation situation.
Since aircraft has the actions such as flat winged, rise/fall, turning during flight, in order to be moved to various aircrafts
It is all compared, assesses, decoding data includes relative to the deviation situation of Standard Flight Data in the embodiment of the present invention：
Lateral deviation situation and vertically to deviation situation, wherein lateral deviation situation includes that at least one straight line is laterally inclined
Poor situation and at least one camber line lateral deviation situation.
Hereinafter, the acquisition modes of lateral deviation situation in the embodiment of the present invention are discussed in detail：
As shown in Fig. 2, the acquisition modes of the straight line lateral deviation situation in lateral deviation situation are as follows：
Step S201, be based on Standard Flight Data, obtain a straight line segment standardized starting point longitude and latitude value,
The longitude and latitude value of standard termination point.
As shown in figure 3, for the straight line segment, standardized starting point is point a, and standard termination point is point b, then obtains
Take longitude, the latitude value of standardized starting point a and standard termination point b.
Step S202, it is based on decoding data, obtains under the same coordinate system, line correspondence segment each practical flight point
Longitude and latitude value.
Step S203, it is based on straight line segment and level-preset deviation, establishes the predetermined deviation range of line correspondence segment.
As shown in figure 3, the level-preset deviation in the embodiment of the present invention could be provided as d, then this straight line of a-b is corresponded to
Region between the predetermined deviation of segment ranging from two dotted lines of Fig. 3.
Specifically, level-preset deviation d is being determined in air route, spatial domain or region, the maximum of aircraft lateral deviation is limited.
According to desired difference, the value of level-preset deviation d can be 1.0 nautical miles, 4.0 nautical miles, 12.6 nautical miles, 20.0 nautical miles etc. and take
Value.
Step S204, it detects whether each practical flight point is located within the scope of predetermined deviation, establishes straight line lateral deviation situation.
After filtering off outlier, each practical flight point should be able to be linked to be a more straight straight line, if the straight line is a certain
Section is located at except predetermined deviation range, that is, has practical flight point to be located at except predetermined deviation range, then illustrate that the segment is deposited at this time
In the event of transfiniting, event of transfiniting to this is needed to be recorded, and be shown to staff.
When aircraft turn, the calculating of camber line deviation situation can be carried out by similar methods, is obtained.Similar, such as Fig. 4
Shown, the acquisition modes of camber line lateral deviation situation include：
Step S301, Standard Flight Data, the standard center of circle of one camber line segment of acquisition, standard radius, standard starting are based on
The longitude and latitude value of the longitude and latitude value, standard termination point of point.
Step S302, it is based on decoding data, obtains the practical turning road of under the same coordinate system, corresponding camber line segment
Diameter.
Step S303, it is based on camber line segment and level-preset deviation, establishes the predetermined deviation range of corresponding camber line segment,
Predetermined deviation is ranging from using the standard center of circle as the fan ring in the center of circle.
Step S304, the predetermined deviation model whether each practical flight point on practical turning path is located at camber line segment is detected
In enclosing, camber line lateral deviation situation is established.
As shown in figure 5, the common segment segments type RF in RNP mission programs, are the boats with radii fixus to anchor point
Segment type.The type segment is using radius r as constant value, in the circular arc segment that an anchor point terminating point is turning center o.RF navigates
Section can be used to control ground track or the gradient of turning.Curve segment is in the end anchor point (leaping a little) for being tangential to previous segment
Start at a and (leaps a little) b in the Initial fix for being tangential to next section of segment and terminate.
It is that radiuses is waited to turn to realize that the deviation of the segments the RF flight path of aircraft in the horizontal direction carries out assessment and the segments RF
Curved segment has carried out algorithm design using the range formula of point to camber line.First by the longitude and latitude of each point in QAR decoding datas into
Row coordinate is converted, and is then shown using correspond to the starting point of segment, terminal, turning radius, left/right rotation dactylogryposis in gold database, utilization
Center of circle extraction algorithm obtains the center of circle of the segments RF, finally acquires the distance between each practical way point and center of circle and turning radius
Difference is the deviation of each practical way point in the segments RF.
False coordinate conversion after practical air route point coordinates be (x1, y1), the corresponding central coordinate of circle in the segments RF be (x0,
Y0), turning radius r, then the camber line lateral deviation value D of the practical way pointRFFor：
If the camber line lateral deviation value D of the practical way pointRFMore than horizontal forecast deviation d, i.e., as shown in figure 5, the reality
Border way point is located at except the predetermined deviation range that dotted line limit comes out, then occurs the event of transfiniting at this time, should be recorded simultaneously
Show staff.Conversely, being then normal condition.
In the vertical direction, aircraft has flat winged and up and down operations, then correspondingly, vertical predetermined deviation value packet
Include vertical boat diameter angle predetermined deviation value and vertically to predetermined deviation value.
When aircraft is flat to fly, as shown in fig. 6, including to the acquisition modes of deviation situation vertically：
Step S401, it is based on Standard Flight Data, obtains the Standard Flight height in a flat flight section.
Step S402, it is based on decoding data, is obtained under the same coordinate system, the practical flight of corresponding flat flight section is high
Degree.
Step S403, the height difference for obtaining Standard Flight height and practical flight height, as the first fiducial value.
Step S404, it obtains vertically to predetermined deviation value, as the second fiducial value.
Step S405, compare the magnitude relationship between the first fiducial value and the second fiducial value, as vertically to deviation situation.
And as shown in fig. 7, when aircraft rises or falls on the way, include to the acquisition modes of deviation situation vertically：
Step S501, it is based on Standard Flight Data, obtains a standard vertical boat diameter angle for rising or falling segment.
Step S502, it is based on decoding data, under the same coordinate system, the corresponding reality for rising or falling segment is obtained and hangs down
Sail through to diameter angle.
Step S503, the angle difference for obtaining standard vertical boat diameter angle and practical vertical boat diameter angle, as the first fiducial value.
Step S504, vertical boat diameter angle predetermined deviation value is obtained, as the second fiducial value.
Step S505, the magnitude relationship for comparing the first fiducial value and the second fiducial value, as vertically to deviation situation.
Obviously, when the first fiducial value is more than the second fiducial value, illustrate that aircraft is in transfiniting state-event at this time, need pair
This is recorded.Certainly, if the first fiducial value is less than the second fiducial value, illustrate that aircraft traveling is normal, similarly need to carry out
Record, remains subsequent staff and analyzes aircraft, handles.
In embodiments of the present invention, vertically to the calculating of deviation mainly for landing phases.According to the tool of aircraft landing
Body process, this system will vertically be calculated to deviation situation using FAF points as line of demarcation.March into the arena, Initial Approach and it is intermediate into
The nearly stage, respectively according to each way point elevation design vertical missing algorithm in gold database；And the most laggard nearly stage according to
Vertical boat diameter angle VPA carries out algorithm design to vertical missing.
Segment march into the arena to decline from the Route reform stage excessively to enlightening into the segment of nearly anchor point (IAF), is mainly used for
It makes the relationship between air route and Airport Operation course line in order, improves on-road efficiency, safeguard air traffic order, ensure aerial smooth.
Since Initial Approach anchor point (IAF), into nearly anchor point (IF) or reversed course line program, straight is completed to intermediate
After the program of line course line, it is cut into the segment until any of intermediate segment.
Centre is into nearly segment for from centre into nearly anchor point (IF) to the end into nearly anchor point/most laggard near point (FAF/
FAP the segment between), it is Initial Approach to the end into close changeover portion, is mainly used for adjusting aircraft configuration, speed and position,
And stablize and complete to be aligned most laggard nearly flight path on machine of being expert at, entrance is most laggard close.
Most laggard nearly segment is to complete flight path to the segment just with decline landing.
Later, this method can be counted based on the deviation situation carried out for different situations, be analyzed, and such as Fig. 1 institutes
Show have：
Step S105, it is based on deviation situation and exports state of flight assessment result.
For user or staff, they can be searched by carrying the human-computer interaction interface of the system of this method
The relevant Flight Information of rope type, shows relevant information according to the line of flight and event, and flight path is linked according to search result
Playback, the analysis and assessment of practical flight data.
During the flight path of certain flight is played back, according to the demand of staff, by the selected secondary flight
Flight path progress animation is shown and curve is shown stage by stage in different colors by the parameter chosen, including each event of display
The state that time of origin, display are transfinited.
Certain segment practical flight data of certain flight are analyzed, and are checked to some parameter according to demand and review it
All acquired original data, and shown in a manner of curve.It transfinites event finally by assessment flight path and statistical analysis
Display systems assessment result.
The present invention assesses RNP operating conditions well, finds the possible factor for leading to deviation, and generation transfinite event and
When occurring repeatedly similar event, identify that non-compliant operation, the safety such as RNP standardization programs of existing defects are hidden as soon as possible
Suffer from, control event development trend, data and Informational support is provided for the system and implementation of the following corrective measure, to realization pair
The research of RNP safety increases the advantages of pilot is to the degree of belief of RNP.
Further, the present invention provides a kind of state of flight assessment system, including memory, processor and it is stored in institute
The computer program that can be run on memory and on the processor is stated, processor realizes above-mentioned side when executing computer program
Method.
The input interface of the state of flight assessment system is made of CD, USB interface etc..QAR data source carriers source is
CD, USB, TF (Trans-flash Card) card and the forms such as wifi, state of flight assessment system can be by USB interface outside
Connect it is omnipotent extension card slot, wifi module or CD form, by QAR data with document form be stored in assessment system running software
Platform has been compatible with the lead-in mode of various machine type datas.
Similar, RNP flight quality assessment system output interfaces are made of network interface, USB interface.Assessment result can pass through net
Mouth or the external wifi module of USB interface are transferred to next stage user.
The technique effect of the state of flight assessment system that the embodiment of the present invention is provided, realization principle and generation and aforementioned
Embodiment of the method is identical, and to briefly describe, device embodiment part does not refer to place, can refer to corresponding in preceding method embodiment
Content.
It is apparent to those skilled in the art that for convenience and simplicity of description, the system of foregoing description
It with the specific work process of device, can refer to corresponding processes in the foregoing method embodiment, details are not described herein.
The flight assessment system can behave as device 100 as shown in Figure 8, including：Processor 40, memory 41, bus
42 and communication interface 43, the processor 40, communication interface 43 and memory 41 connected by bus 42；Processor 40 is for holding
The executable module stored in line storage 41, such as computer program.
Wherein, memory 41 may include high-speed random access memory (RAM, Random Access Memory),
May further include non-labile memory (non-volatile memory), for example, at least a magnetic disk storage.By extremely
A few communication interface 43 (can be wired or wireless) is realized logical between the system network element and at least one other network element
Letter connection can use internet, wide area network, local network, Metropolitan Area Network (MAN) etc..
Bus 42 can be isa bus, pci bus or eisa bus etc..The bus can be divided into address bus, data
Bus, controlling bus etc..Only indicated with a four-headed arrow for ease of indicating, in Fig. 7, it is not intended that an only bus or
A type of bus.
Wherein, memory 41 is for storing program 401, and the processor 40 is after receiving and executing instruction, described in execution
Program 401, the method performed by device that the stream process that aforementioned any embodiment of the embodiment of the present invention discloses defines can be applied
It is realized in processor 40, or by processor 40.
Processor 40 may be a kind of IC chip, the processing capacity with signal.During realization, above-mentioned side
Each step of method can be completed by the integrated logic circuit of the hardware in processor 40 or the instruction of software form.Above-mentioned
Processor 40 can be general processor, including central processing unit (Central Processing Unit, abbreviation CPU), network
Processor (Network Processor, abbreviation NP) etc.；It can also be digital signal processor (Digital Signal
Processing, abbreviation DSP), application-specific integrated circuit (Application Specific Integrated Circuit, referred to as
ASIC), ready-made programmable gate array (Field-Programmable Gate Array, abbreviation FPGA) or other are programmable
Logical device, discrete gate or transistor logic, discrete hardware components.It may be implemented or execute in the embodiment of the present invention
Disclosed each method, step and logic diagram.General processor can be microprocessor or the processor can also be to appoint
What conventional processor etc..The step of method in conjunction with disclosed in the embodiment of the present invention, can be embodied directly in hardware decoding processing
Device executes completion, or in decoding processor hardware and software module combination execute completion.Software module can be located at
Machine memory, flash memory, read-only memory, programmable read only memory or electrically erasable programmable memory, register etc. are originally
In the storage medium of field maturation.The storage medium is located at memory 41, and processor 40 reads the information in memory 41, in conjunction with
Its hardware completes the step of above method.
Flow chart and block diagram in attached drawing show system according to an embodiment of the invention, method and computer program production
The architecture, function and operation in the cards of product.In this regard, each box in flowchart or block diagram can represent one
A part for a part for a module, section or code, the module, section or code includes one or more is used in fact
The executable instruction of logic function as defined in existing.It should also be noted that in some implementations as replacements, being marked in box
Function can also occur in a different order than that indicated in the drawings.For example, two continuous boxes can essentially substantially simultaneously
It executes capablely, they can also be executed in the opposite order sometimes, this is depended on the functions involved.It is also noted that frame
The combination of figure and/or each box in flow chart and the box in block diagram and or flow chart can be used as defined in executing
Function or the dedicated hardware based system of action are realized, or can be come using a combination of dedicated hardware and computer instructions
It realizes.
It is apparent to those skilled in the art that for convenience and simplicity of description, the system of foregoing description
Specific work process, can refer to corresponding processes in the foregoing method embodiment, details are not described herein.
Finally it should be noted that：Embodiment described above, only specific implementation mode of the invention, to illustrate the present invention
Technical solution, rather than its limitations, scope of protection of the present invention is not limited thereto, although with reference to the foregoing embodiments to this hair
It is bright to be described in detail, it will be understood by those of ordinary skill in the art that：Any one skilled in the art
In the technical scope disclosed by the present invention, it can still modify to the technical solution recorded in previous embodiment or can be light
It is readily conceivable that variation or equivalent replacement of some of the technical features；And these modifications, variation or replacement, do not make
The essence of corresponding technical solution is detached from the spirit and scope of technical solution of the embodiment of the present invention, should all cover the protection in the present invention
Within the scope of.Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (10)
1. a kind of state of flight appraisal procedure, which is characterized in that including：
Acquire flight initial data；
To institute's collected flight initial data decoding, decoding data is obtained；
Obtain Standard Flight Data and predetermined deviation value；
Based on the predetermined deviation value, the decoding data and the Standard Flight Data are compared and analyzed, and according to right
Deviation situation of the decoding data relative to the Standard Flight Data is obtained than the result of analysis；
State of flight assessment result is exported based on the deviation situation.
2. state of flight appraisal procedure according to claim 1, which is characterized in that the decoding data is relative to the mark
The deviation situation of quasi- flying quality includes：
Lateral deviation situation and vertically to deviation situation, wherein the lateral deviation situation includes that at least one straight line is laterally inclined
Poor situation and at least one camber line lateral deviation situation.
3. state of flight appraisal procedure according to claim 2, which is characterized in that the predetermined deviation value includes horizontal pre-
If deviation and vertical predetermined deviation value；The vertical predetermined deviation value is including vertical boat diameter angle predetermined deviation value and vertically to pre-
If deviation.
4. state of flight appraisal procedure according to claim 3, which is characterized in that the straight line lateral deviation situation obtains
Take mode as follows：
Based on the Standard Flight Data, the longitude and latitude value, standard termination of the standardized starting point of a straight line segment are obtained
The longitude and latitude value of point；
Based on the decoding data, the warp of each practical flight point of under the same coordinate system, the corresponding straight line segment is obtained
Angle value and latitude value；
Based on the straight line segment and the level-preset deviation, the predetermined deviation range of line correspondence segment is established；
It detects whether each practical flight point is located within the scope of predetermined deviation, establishes the straight line lateral deviation situation.
5. state of flight appraisal procedure according to claim 3, which is characterized in that the camber line lateral deviation situation obtains
The mode is taken to include：
Based on the Standard Flight Data, the standard center of circle of one camber line segment of acquisition, standard radius, the longitude of standardized starting point
With the longitude and latitude value of latitude value, standard termination point；
Based on the decoding data, the practical turning path of under the same coordinate system, the corresponding camber line segment is obtained；
Based on the camber line segment and the level-preset deviation, the predetermined deviation range of corresponding camber line segment is established, it is described
Predetermined deviation is ranging from using the standard center of circle as the fan ring in the center of circle；
Detect whether each practical flight point on the practical turning path is located within the scope of the predetermined deviation of the camber line segment,
Establish the camber line lateral deviation situation.
6. state of flight appraisal procedure according to claim 3, which is characterized in that when aircraft is flat to fly, it is described vertically to
The acquisition modes of deviation situation include：
Based on the Standard Flight Data, the Standard Flight height in a flat flight section is obtained；
It based on the decoding data, obtains under the same coordinate system, the practical flight height of the corresponding flat flight section；
The height difference for obtaining the Standard Flight height and the practical flight height, as the first fiducial value；
Obtain it is described vertically to predetermined deviation value, as the second fiducial value；
Compare the magnitude relationship between first fiducial value and second fiducial value, as described vertically to deviation situation.
7. state of flight appraisal procedure according to claim 3, which is characterized in that when aircraft rises or falls on the way, institute
It states and includes to the acquisition modes of deviation situation vertically：
Based on the Standard Flight Data, a standard vertical boat diameter angle for rising or falling segment is obtained；
Based on the decoding data, obtain it is under the same coordinate system, corresponding described in rise or fall the practical vertical boat of segment
Diameter angle；
The angle difference for obtaining standard vertical boat diameter angle diameter angle of navigating vertical with the reality, as the first fiducial value；
The vertical boat diameter angle predetermined deviation value is obtained, as the second fiducial value；
The magnitude relationship for comparing first fiducial value and second fiducial value, as described vertically to deviation situation.
8. state of flight appraisal procedure according to claim 4 or 5, which is characterized in that further include：
Based on the lateral deviation situation, the event of transfiniting is judged whether, the event that transfinites is that practical flight point is incomplete
Fall the situation within the scope of corresponding predetermined deviation.
9. the state of flight appraisal procedure described according to claim 6 or 7, which is characterized in that further include：
Based on described vertically to deviation situation, the event of transfiniting is judged whether, the event that transfinites is first fiducial value
The case where more than second fiducial value.
10. a kind of state of flight assessment system, including memory, processor and it is stored on the memory and can be at the place
The computer program run on reason device, which is characterized in that the processor realizes following methods when executing the computer program：
Acquire flight initial data；
To institute's collected flight initial data decoding, decoding data is obtained；
Obtain Standard Flight Data and predetermined deviation value；
Based on the predetermined deviation value, the decoding data and the Standard Flight Data are compared and analyzed, and according to right
Deviation situation of the decoding data relative to the Standard Flight Data is obtained than the result of analysis；
State of flight assessment result is exported based on the deviation situation.
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