CN102867073B - Flight program design system for performance-based navigation, verification platform and verification method - Google Patents

Abstract

The invention discloses a flight program design system for performance-based navigation (PBN), a verification platform and a verification method, belonging to the field of aerial navigation. The program design system is based on an AIXM (Aeronautical Information Exchange Model) core database; a program protection region can be automatically drawn, an obstacle is evaluated, and a chart is generated; and thus, functions such as seamless connection and the like of the PBN program protection region and the conventional flight program protection region can be realized. According to the system, the chart can be automatically generated according to data finished by the flight program design, customized edition and modification can also be realized according to requirement, and program design and publishing are finished at one time. By using the flight program design system, the verification platform and the verification method, the PBN program can be directly added in a navigation database of the verification platform, and the navigation database can be edited and modified in a verification process. In addition, a visual scene database is increased; the defects and the disadvantages of the program design can be directly discovered according to geomorphology in a visual scene when the PBN flight program is verified; and the program is further modified perfectly.

Description

A kind of mission program design system based on performance navigation and verification platform and verification method

Technical field

The invention belongs to aerial navigation field, be specifically related to a kind of mission program design system based on performance navigation and verification platform and verification method.

Background technology

The high speed development of China's economic facilitates increasing rapidly of Civil Aviation Industry, and since 1978, CAAC's total traffic turnover annual growth is 18%, is about about 2 times of the GCP growth rate same period.Within 2000, CAAC's total traffic turnover is the 9th, the world, within 2003, is the 5th, within 2004, is the 3rd, within 2005, leaps to second place of the world.Remain the position of second in recent years always, become big country of civil aviaton.Although Civil Aviation Transportation System in China entirety remains quick stable development, but the fast development of CAAC also faces lot of challenges, mainly comprises:

(1) special airport is numerous

Special airport refers to that flight environment of vehicle is complicated, airfield support condition is not enough, for ensureing flight safety, needs the airport of taking special counter-measure.China has 38 special airports at present, and high high-altitude aerodrome more than height above sea level 2438 meters (8000 feet) has 8, also has more plateau and complicated airport to build.By the impact of landform and geographical conditions, traditional ground navigational facility in these airports and region is difficult to meet and runs needs, and invests huge, and maintenance cost is high.

(2) the western and eastern's disparate development

Due to the imbalance of China's regional economic development, eastern region has more perfect infrastructure and ground base navigation system, and surveillance radar can realize Multi folds coverage.But the infrastructure in west area and Land Navigation Installation build imperfection, and the quorum sensing inhibitor of guidance station and surveillance radar is incomplete.Along with the fast development of west lags far, the construction of west area civil aviation infrastructure faces a severe challenge.

The signal receiving Land Navigation Installation is utilized during conventional navigation, by realizing the guiding to aircraft to platform and the flight of back of the body platform, its air route and mission program are by the layout of Land Navigation Installation and the restriction of device category, and limited precision, present operation concept and technological means can not solve the problem.Along with the raising of airborne equipment ability and the development of satellite navigation and other advanced technology, concept that International Civil Aviation Organization (ICAO) proposes " navigation (PBN:Performance Based Navigation) based on performance ".The introducing of PBN embodies navigation mode from the transformation navigate to based on sensor based on performance navigation.PBN comparatively traditional program has following advantage:

● accurately guide aircraft, improve flight safety in operation;

● vertical guide is provided, implements the letdown procedure of continous-stable, reduce controlled risk of hitting ground;

● improve round-the-clock running, ensure the safety of Airport Operation with a varied topography;

● realize the flight boat footpath optimized flexibly, increase aircraft industry and carry, reduce the flight time, save fuel oil.

PBN prototype comes from RNAV (area navigation) and RNP (desired properties navigation) concept.Proposing when its concept is the International Civil Aviation Organization's research and development of the nineties initial stage new navigation system (FANS), is the airspace management and the allotment of air traffic interval that are applied in transoceanic flight at first.Along with constantly bringing forth new ideas of airborne airmanship, the definition of PBN and intension are also in continuous change.International Civil Aviation Organization, on the basis integrating existing achievement in research, formally proposes the navigation concepts based on performance in 2008, and specify that RNAV and RNP is two kinds of multi-form PBN, its range of application also opens up each stage extensively having arrived flight.PBN is the heat subject that aviation power is being studied at present, and Ye Shi international airline circle is known as the trend of following navigation development.

What apply PBN technology the earliest is ALASKA AIRLINES INC. of the U.S..After Zhu Nuo airport uses PBN program, achieve with a varied topography and low weather standard run.The current U.S. has the different airport of nearly 10 complexities to employ PBN program, only between ALASKA AIRLINES INC. 2003-2004, to make preparation for dropping 603 flights that make a return voyage through statistics minimizing, and saves 5,000,000 dollars every year.The airline that is applied as based on the airmanship of performance brings high safety reliability and huge economic benefit.In the world except the U.S., Canada, New Zealand, the Australian research and apply also having carried out PBN technology.European Union member countries also in the development of positive regard PBN technology, and are actively promoting the enforcement of these technology in Europe, and one of are supported as the important technology of European sky integration by PBN.

PBN technology ripe day by day and perfect, for quick, the security developments of CAAC provide the approach of effectively dealing with problems.International Civil Aviation Organization's the 36th conference resolution is pointed out: " each contracting party should complete PBN implementation plan in 2009, guaranteed before 2016, and the mode of making peace coordination with global is transitioned into PBN and runs ".Office of CAAC has issued " CAAC is based on performance navigation (PBN) Implementation Roadmap " for this reason, widelys popularize PBN navigation new technology in China.CAAC PBN Implementation Roadmap was also put into effect in 2009.Its implementation strategy will be divided into three phases, i.e. recent (2009-2012), mid-term (2013-2016), (2017-2025) at a specified future date.Recent implementation PBN emphasis application, carries out PBN overall application mid-term, implementation PBN and CNS/ATM at a specified future date system combination.

The complicacy on Lhasa airport allows traditional program encounter the bottleneck being much difficult to overcome, and PBN mission program ideally solves this problem.New page has been opened in the development being applied as CAAC of PBN technology.After Lhasa, domestic at present have Fromlingzhi, tibet, Bamda, Ali, and the Lijing in Yunnan, Hunan the airport such as Zhangjiajie, the Mount Huang in Anhui, the Yanji in Jilin in succession implement PBN program.The application of PBN program solves the drawbacks such as these Airport Operation standards with a varied topography are high, spatial domain is complicated, for airline and airport bring considerable benefit.But designed by the PBN program Dou Shi offshore company that above-mentioned domestic airport is run, core technology still rests in the hand of offshore company.What possess PBN programming capability at present only has Boeing, Air Passenger company and Naverus company of the U.S., offshore company has also had an optimistic view of the great potential of Chinese market, technical blockade is carried out to China, this improves safe operation to CAAC, recommend New technical use, rise to power of civil aviaton by big country of civil aviaton very unfavorable.

At present, only have France and Italy to have the PBN mission program design software designed and developed in worldwide, it comprises:

(1) GITAN (France)

Geotitan mission program design software is that French CAIC Teaching & Administrative (ENAC) drops into data message company of Air France Group CGX the business software researched and developed in calendar year 2001.Software mainly establishes a set of aviation topographic database based on AIXM, and fully integrated ICAO Doc8168-0PS/611 specification, realizes automatic drawing protection, automatic evaluation barrier, automatically makes the function such as chart and establishment report.

(2) FPDAM software (Italy)

FPDAM is mission program design and the airspace management software of a advanced person of Italian IDS company exploitation.Its principal feature is can with the patten's design instrument flight procedure of three-dimensional, and establish a complete aeronautical database platform, the mission program management software not being only it provides platform to provide data, also support radar signal analysis, spatial domain program design etc. provides authentic data to ensure, it provides the interactive environment of program design by conventional navigation information and area navigation concept.

FPDAM is that user job provides following function:

● provide instrument flight procedure design fast for newly-built airports, airport transformation;

● while guarantee interval and MEA/MEL/LSALT confirm, design course line, air route;

● service range is exceeded to flight facilities temporarily, again programme path and redesign course line;

● conditional spatial domain is defined and revised;

● during spatial domain exists military training or other important aerial event, manage there being the region of interim restriction;

● to the assessment of newly-built airports peripheral obstacle and surrounding environment;

● the general planning on airport is analyzed;

● available offline mode checks designed instrument flight procedure.

The domestic system being only applicable to conventional flight program design and analytic function at present, does not also have PBN mission program designed system.

In addition, external aviation flight simulated flight platform comparative maturity and perfect.Serial application has been become to train in each stage of pilot from primary simulator to senior full dynamic simulated machine.But the platform being specifically applied to program verification there is no commercial platform at home and abroad at present.So the checking of current procedure all uses the full dynamic simulated machine of pilot training, this is exactly the problem of proving period time length to program verification existence a subject matter, because program coding is made by FMS navigational route database company, the fabrication cycle of FMS navigational route database is 28 days, if discovery procedure has problem to need amendment after checking, then need next fabrication cycle by the time just can revise, a PBN program design completes more than general needs amendment twice or thrice, often revise and once need to wait 28 days amendment navigational route databases, amendment number of times is more, expend the cycle more, time is oversize.Also also exist simultaneously and use full dynamic simulated machine to verify costly difficulty.

Simultaneously, external large for the analog machine difference in version of PBN program verification, the leap time is long, it not the analog machine scene database that whole analog machine all has verified airport, the analog machine had when PBN program verification can the what comes into a driver's on Installation Validation airport, but what have can not install, when the analog machine having installed checking airport what comes into a driver's is verified, in proof procedure, EGWPS topographic database is once alarm, directly can pinpoint the problems according to airport what comes into a driver's, program is modified, and when there is landform alarm in the analog machine lacking what comes into a driver's data, further investigation discussion is needed to produced problem, reason is determined in multiple authentication flight.

Summary of the invention

The object of the invention is to solve the difficult problem existed in above-mentioned prior art, there is provided a kind of based on performance navigation PBN mission program design system and verification platform, solve the difficult problems such as the accuracy of way point in PBN programming procedure, the accuracy of database coding, the rationality of program design and program verification excessive cycle, meet the demand that domestic air mail market increases fast, meet ICAO and civil aviaton of China to the operation demand of PBN program, reduce the application cost of design cost and airline.

The present invention is achieved by the following technical solutions:

It is a kind of that based on performance navigation PBN mission program design system, described system comprises three layers: bottom, middle layer and the superiors, wherein:

Described bottom is the core database layer based on AIXM, and it have collected various database, comprises AIPs and NOTAM;

Described middle layer is SUPERMAP component layer, and it carries out two-way interactive by database engine and bottom;

The described the superiors are application layer;

Described application layer comprises:

1) PBN mission program Computer Aided Design application module, the data of its process from this locality and the data of outside central database, carry out two-way interactive by middle layer and database engine; Local data refer to the data that Supermap SDB document form stores;

2) chart application module, and it, according to standard chart template generation chart, carries out two-way interactive by middle layer and database engine;

3) ARINC424 coding exports application module, comprises and encoding to basic data and mission program data; The process of encoding to basic data generates data form sequentially to data to export, and encoding to mission program data, is extract key message, and to key message rearrangement, finally generates data form file in order; Data are sent to ARINC424 coding and export application module by database engine;

This module provides three partial functions: A, carries out according to the part basis data in mission program plan document and mission program front pre-service of encoding; B, provides user again to edit content after pre-service; C, derives design automatic coding function.

4) SUPERMAP DESKPRO (desktop software of hypergraph company) browses chart application module or map file, SUPERMAP DESKPRO is utilized to browse chart module, utilize the function of desktop software on maps processing to process the chart designed, complete the function that program development software can not complete;

Data are sent to SUPERMAP DESKPRO and browse chart application module or map file by database engine;

5) based on the reporting modules of template and data, its data sent according to database engine, by the template of design, generate report file automatically.

Whether described PBN mission program Computer Aided Design application module self-verifying design meets PBN mission program way point sequence rules, and generates nominal flight path and protected location; Simultaneously regularly fragmented storage, is convenient to the Segment evaluation of protected location; Realize the seamless link of RNAV or RNP protected location and conventional I LS protected location; Cultural obstacle and DEM barrier are identified; Automatically march into the arena, leave the theatre, near, non-precision approach is entered in Initial Approach, centre, each stage of ILS-OAS, APV-BARO OAS and visual barrier assessment, provide referential suggestion.

Described PBN mission program Computer Aided Design application module comprises three layers:

(1) display layer and optimum configurations interface: described display layer is used for each program design element of visual Layering manifestation PBN mission program design, and described program design element comprises runway, guidance station, protected location; Described optimum configurations interface is used for the parameter of graphical setting program design element;

(2) Business Logic: the core layer being this module, it is responsible for carrying out alternately with described display layer and optimum configurations interface, and carries out alternately, completing calling of algorithm with the database of bottom simultaneously;

(3) data storage layer: comprise local profile, local SUPERMAP data source and the central database based on AIXM; Described local profile is undertaken alternately by XML parser and Business Logic; Described local SUPERMAP data source is undertaken alternately by SUPERMAP SDX+ engine and engine and Business Logic; The described central database based on AIXM is undertaken by SQLSERVER database engine and Business Logic alternately.

For the verification platform verified described mission program design system of navigating based on performance, described verification platform comprises flight dynamics system, flight management and guidance system, flight control system, engine system, atmosphere data and Inertial Platform System, central monitoring system, control system, instrument system and visual system; Described engine system comprises fuel system;

Described flight dynamics system comprises Aerodynamic Coefficient module and equation of motion module, described Aerodynamic Coefficient module be rise under the various condition of aircraft, the set of resistance and moment coefficient, in computation process, obtain the various Aerodynamic Coefficient value of aircraft this moment by real-time query.It is by receiving aircraft rudder surface, the flap configuration of control system, and relevant flight parameter, utilizes these parameter query Aerodynamic Coefficients, and recycling Aerodynamic Coefficient calculates flight force and moment, and result of calculation is transported to equation of motion module;

Described equation of motion module receives the flight force and moment of Aerodynamic Coefficient module, and the thrust magnitude of engine system, fuel weight and center of gravity of airplane position, and normal atmosphere data, utilize these conditions and aircraft initial value, resolve the non-linear full dose equation of motion of aircraft six degree of freedom, obtain the attitude of aircraft, speed, grade, position and other flight parameter, and these parameters are fed back to pneumatic system module again, again inquiry obtains go forward side by side promoting the circulation of qi power and aerodynamic moment of Aerodynamic Coefficient and calculates, pass to equation of motion module again, go round and begin again and repeat above-mentioned computation process, realize flight dynamics to calculate,

Described flight management and guidance system, self is with navigational route database, aircraft performance database and aerodynamic data and engine data storehouse, realizes flight management and guides two parts function with flight; Described flight management part, by man-machine interface input take off initial parameter and leave the theatre and march into the arena, approach flight program, undertaken leaving the theatre, landing by this mission program to make aircraft;

Described flight leader, receive the information of aircraft dynamics system and flight control system transmission, with the flight planning comparison in database, calculate current speed, course and course error, pass to flight control system and engine system again, realize speed, the control of course and course-line deviation, afterwards, the fresh information calculated is fed back to flight management and guidance system by aircraft dynamics system and flight control system again, calculation deviation controlling again, go round and begin again repetition said process, complete navigation procedure, make aircraft by expection track flight.Meanwhile, flight management and guidance system calculate the precision of navigation sources and positional precision, and report to the police when precision is undesirable;

Described flight control system, the current flight path that reception flight management and guidance system send and course deviation, utilize the control rate designed in advance, calculate and revise aircraft rudder surface required for deviation and flap control amount, manipulated variable data are delivered to aerofoil steering wheel, executable operations, makes aircraft change attitude and course, according to the track flight of expection;

Described engine system, the present speed that reception flight management and guidance system send and height tolerance, utilize the engine throttle control rate designed in advance, calculate and revise fuel flow required for deviation and auto-throttle manipulated variable, manipulated variable data are delivered to engine system, executable operations, make engine change thrust, thus change the flight parameter such as speed, height, reach the airmark of expection;

Described atmosphere data and Inertial Platform System, comprise atmosphere data processing section and inertial platform part, described atmosphere data processing section obtains the dynamic pressure of air, static pressure, stagnation pressure, these basic parameters of atmospheric temperature by sensor, calculates current air basic parameter and barometer altitude, air speed information; Described inertial platform part obtains aircraft acceleration information by three axes accelerometers, is obtained the velocity information of three axles by integration, and integration obtains three dimensional local information again, utilize the air speed information of atmosphere data, calculate current wind speed, utilize air pressure signal, obtain barometric-corrected altitude;

Described central monitoring system, receives from other systematic data, monitors each working state of system and data, once there is data over run and abnormal state, will report to the police with audio frequency and video information, reminds unit to note;

Described control system provides the equipment of unit manual control aircraft, comprise deflecting roller, jociey stick, throttle lever and pedal, control command is directly sent to flight control system, aerofoil steering wheel, engine system by these equipment by unit, taking off, land and traffic adjustment, control order time manually handle, also can manual control aircraft when thrashing, burst are unexpected;

Described instrument system comprises primary flight display, navigation indicator; Described instrument system receives the parameter from atmosphere data and inertia system, flight management and guidance system, flight dynamics system and flight control system, to current flight attitude, speed, grade, Mach number, highly, flight path, navigation information, terrain information, atmosphere data, flight plan data show, check for unit, to understand current state of flight;

Described visual system receive current flight attitude, speed, grade, Mach number, highly, flight path, navigation information, utilize the three dimensional topographic data storehouse carried, aloft virtual three-dimensional scene is provided, comprises dimensional topography, three-dimensional atmospheric environment, airport and terminal area environment, three-dimensional model aircraft; There is provided the acoustics in engine and extraneous physical environment, for unit simulated flight provides 3D vision true to nature and auditory information.

Described visual system comprises flying quality interface, scheduling memory module, buffer management module, what comes into a driver's cutting module, plays up output module;

The described flying quality interface temporally flying quality that produces of sequential reception analog machine in real time, and the relevant information extracting aircraft is to drive what comes into a driver's;

Described scheduling memory module is according to the scope in the viewpoint position obtained in airplane data interface and the visual field, the scope that calculating need read in internal storage data ensures that the data area in internal memory can meet and plays up needs in following a period of time, and upgrades the data in internal memory according to the change of viewpoint;

The function of described buffer management module is data dispatching, simplified model; When observing viewpoint and roaming in Virtual Terrain scene, according to the scope of viewpoint and look migration to, the interior data that come into view are called in buffer zone by system from internal memory; Described buffer zone comprises Render Buffer and data buffer; Render Buffer refers to according to active user's field range, a visual range of delimiting, and the landform fallen within the scope of this must be played up, and is responsible for the renewal of data buffer by data management system; Described Render Buffer shows as the pointer list of all data cells in current Render Buffer, is responsible for the renewal of buffer zone by scene manager; Scheduling due to data needs to spend the regular hour, therefore, needs before data block comes into view, needs those data blocks that may come into view very soon of forward scheduling;

Described what comes into a driver's cutting module: the image that screen shows is two-dimentional scenery perpendicular to the projection in the two-dimensional imaging plane of direction of visual lines, must judge the relative position of object and view body before playing up output, then be handled as follows by then described what comes into a driver's cutting module: if to be positioned at view completely external for object, then discard; If object is positioned at view body completely, then it is transformed to screen coordinate system and play up; If object is crossing with view body, then with view body, cutting is carried out to object, then play up the part be positioned within view body;

Describedly play up output module: play up output module and carry out playing up output according to the pointer list of data cells all in current Render Buffer; When viewpoint moves, scene manager is responsible for according to real-time the upgrading unit in Render Buffer of viewpoint parameter, the new unit pointer entering Render Buffer is added pointer list, and delete the pointer that those have shifted out Render Buffer unit, meanwhile, use polling mechanism, whether the data of constantly inquiring in current Render Buffer to scene manager are ready to, as being ready to just to proceed to play up, what realize circulation like this plays up what comes into a driver's.

The scene database of what described visual system adopted is real landform, texture, airport data genaration;

Described visual system adopts single video card and special split screen hardware, described special split screen hardware adopts graphic extension building block technique, being assigned to by one road VGA signal of input is three road signals, and allows Windows 2000/XP operating system, according to suitable ratio, picture signal is outputted to display screen.

Use described verification platform to carry out the method verified, said method comprising the steps of:

(1) typing navigational route database: by upgrading navigational route database interface, start navigational route database editing system, the information type that flight validation personnel selection will input, the various data that input is corresponding, after input data, generate database, restart flight validation platform;

(2) arrange flight parameter, carry out ground validation: checking personnel pass through tarmac, parameters, personnel are according to Standard Flight program in checking, carry out pre-flight various operation;

(3) verify in laggard line space of taking off: checking personnel carry out the various operations of taking off according to the mission program of standard;

(4) nearly phase authentication is entered: when aircraft was in into the nearly stage, navigational system is according to predetermined Gradient Descent to the speed of program design, and automatic vector aircraft to DH+50 height, is not relied on instrument landing system (ILS) by vertical guidance system, under GPS PRIMARY pattern, realize automatic Landing.

Compared with prior art, the invention has the beneficial effects as follows:

(1) create aeronautical data interaction models first, this model can effectively by airport, three-dimensional data landform, barrier data and navigational intelligence data automatic hinge together for program design provides basic data.

(2) PBN program Automated Design is achieved.The present invention can according to the basic data in aeronautical data storehouse, and according to regulations and the specification of ICAO and FAA, automatic evaluation barrier, intelligent chooses the optimum route that enters to leave the theatre, and can generate navigational intelligence document fast.Greatly improve the efficiency of program design.

(3) mission program navigational route database integrity verification.FPCAD to the mission program completed, according to software format data demand, can complete process integrity checking automatically.Mainly comprise way point, whether program height, leg meet code requirement etc., the safety for flight provides a kind of means of inspection.

(4) PBN program only need carry out flight validation on program verification platform of the present invention, cost is obviously low than full dynamic simulated machine, the program verification initial stage does not need FMS navigational route database company to make coding, directly can carry out interpolation PBN program in the navigational route database of verification platform, can edit navigational route database and revise in proof procedure, modification of program does not need to wait 28 day cycle, and real time modifying navigational route database can be verified again.Until after modification of program improves, then submit to FMS navigational route database company (Smith company and Honeywell company) and complete coding, paying airline can put into operation.

Accompanying drawing explanation

Fig. 1 is the block architecture diagram that the present invention is based on performance navigation PBN mission program design system.

Fig. 2 is the structured flowchart of the PBN mission program Computer Aided Design application module in Fig. 1.

Fig. 3 is the block architecture diagram of verification platform of the present invention.

Fig. 4 the present invention is based on the protected location figure that performance navigation PBN mission program design system generates connection automatically.

Fig. 5 the present invention is based on the APV-BARO VNAV barrier evaluate parameter inputting interface in performance navigation PBN mission program design system.

Fig. 6 the present invention is based on the APV-BARO VNAV barrier assessment result figure in performance navigation PBN mission program design system.

Fig. 7 is the display figure of assessment result on map of Fig. 6.

Fig. 8 is that the chart that the present invention is based in performance navigation PBN mission program design system generates interface automatically.

Fig. 9 is the construction module figure of the visual system in the present invention.

Embodiment

Below in conjunction with accompanying drawing, the present invention is described in further detail:

As shown in Figure 1, a kind of based on performance navigation PBN mission program design system, described system comprises three layers: bottom, middle layer and the superiors, wherein:

1, bottom is the core database layer based on AIXM:

Have collected AIPs, NOTAM and other data;

In mission program design, such as airport can be related to, guidance station, how the mass data such as mission program, barrier, realize these data and be beneficial to preservation, check, be a major issue alternately, for this problem, the present invention adopts international airline Data Exchange Model AIXM building database, integrate aeronautical data resource, realize the unified management to aviation information, for PBN program design and verification system provide accurately, reliable Data support.

Real guidance station, the related datas such as course line, airport, landform are the bases ensureing mission program planning, assessment drawing, coding.Adopt independently database service mechanism, the security of guarantee data, reduce data redudancy, the validity of data management and the reliability of data realize key of the present invention.Adopt based on AIXM (aviation information exchange model) model creation database, adopt data-centered operational mode, from data acquisition, program design is all produced by unique data source to final program checking, the mistake that minimizing data occur in transmittance process and error, ensure program quality.

The object that AIXM model is set up is at the data demand to aviation field by meeting described by ICAO annex 15, supports AIS demand data.Along with the application of area navigation (RNAV), required navigation performance (RNP) and airborne computer navigational system, role and the importance of aeronautical data/information there occurs great change.Damage or the mistake of aviation information/data form potential threat to navigation safety.In order to meet airborne computer navigational system run needed for the unitarity of navigational information in providing and compliance, contracting party should avoid as far as possible adopting and internationally use standard outside regulation and program.

The foundation of AIXM model to be included in AIPs based on International Civil Aviation Organization's (ICAO) standard and suggestion and measure (SARPS) but not by the concept data industrial standard that ICAO and SARPS is contained, as ARINC 424 (being mainly used in instrument approach and departure procedure coding).

2, middle layer is SUPERMAP component layer (i.e. SUPERMAP OBJECT in Fig. 1)

Two-way interactive is carried out by database engine and bottom;

3, the superiors are application layer

Wherein, application layer comprises PBN mission program Computer Aided Design application module, drawing application module, ARINC424 coding export application module, SUPERMAP DESKPRO browse chart application module, based on the reporting modules of template and data and conventional flight program design application module, specific as follows:

1) PBN mission program Computer Aided Design application module, processes the data of data from this locality and outside central database, integrates the complicated service logic such as mission program, protected location, assessment, by SUPERMAP OBJECT and system bidirectional mutual; Whether self-verifying design meets PBN mission program way point sequence rules, and generates nominal flight path and protected location.Simultaneously regularly fragmented storage, is convenient to the Segment evaluation of protected location, realizes the seamless link etc. of RNAV/RNP protected location and conventional I LS protected location.To cultural obstacle and DEM obstacle recognition, automatically march into the arena, leave the theatre, near, non-precision approach is entered in Initial Approach, centre, ILS-OAS, APV-BARO OAS, etc. each stage and visual barrier assessment, provide referential suggestion, programming efficiency comparatively manual work improves greatly.

As shown in Figure 2, PBN mission program Computer Aided Design application module comprises three layers:

(1) display layer, and optimum configurations interface

(2) Business Logic: the core layer being this module, is responsible for carrying out alternately with display layer and optimum configurations interface, and carries out alternately, completing calling of algorithm with the data of bottom three kinds of separate sources simultaneously.

(3) data storage layer

Comprise local profile, local SUPERMAP data source and the central database based on AIXM.Mission program store three kinds, generally when designing, first get business datum from SQLSEVER, configuration data is imported from XML file, three class data are preserved again after having designed, preserve XML configuration file in this locality, local SUPERMAP (SDX in Fig. 2 is database engine) data source, server data end is kept in SQLSEVER.Database engine in Fig. 1 includes SQLSEVER database engine and SUPERMAP SDX+ engine etc. in Fig. 2.

2) chart application module, namely according to standard chart template generation chart, carries out two-way interactive by SUPERMAP OBJECT and database engine;

3) ARINC424 coding exports application module, carries out one-way interaction with database engine;

In mission program design, the object of coding is in order to data encoding company such as (Corinth, Honeywell etc.) theory of mission program deviser can be expressed accurately.Just reaching data encoding company with reference to ARINC424 Specification Design can recognition coding, reaches the versatility of coding, and the accuracy how ensureing to encode, reliability are the focuses that we pay close attention to.The mission program of design can be automatically converted to ARINC424 coding by PBN mission program design software accurately, simultaneously analog machine can its coding of Direct Recognition, automatic conversion is loaded in navigational route database to be verified, pinpoint the problems, modify from mission program design software, program design and checking personnel do not participate in the direct amendment to coded data, reduce the error that manual operation brings.

The international widely used navigation data standard format of ARINC424 authority data Shi Bei, it is also the basis of FMC (FlightManagement Computer) contained on-board navigation data.For domestic operator, the aeronautical data of nearly 2/3 can not get effective utilization in FMC, causes great inconvenience to flight and aviation management personnel.In addition, correctly and effectively can not use domestic navigation data, be also a kind of huge waste to domestic air mail data simultaneously.

ARINC424 authority data is also the prerequisite implementing aviation new standard and new technology.From whole CAAC, what lack is not navigational intelligence navigation data, but does not press cannonical format formation navigation data.The navigation data of China civil aviaton is only applicable to the product of domestic publication and distribution, such as: NAIP, Flight Information compilation, AIP, enroute chart etc., and can not be generalized in world's application apparatus or software.Especially domestic open navigational data portion, in the middle of the foreign system that cannot be generalized to the current use of domestic operator, such as, empty company of domestic three key airline companies use the SOC system developed by the U.S., primarily of the FMC etc. that external production firm provides.And ARINC424 authority data just navigation data expand optimal path.Actual conditions only in conjunction with current CA are seen, ordered JEPPESEN " whole world " data (ARINC424 authority data) do not comprise domestic externally not open navigation data, and one of these the most used navigation datas of data Qia Shi domestic operator.The present invention can generate the ARINC424 authority data of domestic navigation data, and the Some Domestic of replacement or supplementary JEPPESEN " whole world " data, realizes complete worldwide navigation database, for domestic operator.

4) SUPERMAP DESKPRO browses chart application module, or map file, with database engine one-way interaction;

5) based on the reporting modules of template and data, namely according to data such as mission programs known in system, by the template of design, automatic report file, with database engine one-way interaction;

6) conventional flight program design application module, adds, with database engine one-way interaction after this application module expands future represented by dashed line on the basis of this framework.

Due to bottom employing is the database that aviation information exchange model is set up, so application layer has very strong extensibility.This framework is centered by independently database, and application extension is guiding, is convenient to carry out integrations utilization to the resource such as data and application.

Of the present inventionly achieve following functions based on performance navigation PBN mission program design system:

A, mission program designs:

Select after way point, the navigational facility that the present invention selects according to mission program and navigation specification, enter the automatic data processings such as nearly type, aircraft type, specific as follows:

● check whether way point meets PBN mission program way point sequence rules;

● automatically calculate ATT, the XTT of way point, BV, half-breadth AW value;

● self-verifying calculates the shortest stabilizing distance when changing, and checks whether the constraint rule meeting the shortest stabilizing distance;

● automatically generate nominal flight path.

According to ICAO OPANS 8168 DOC, the present invention completes conventional mission program, marches into the arena, and leaves the theatre, and waits for, ILS, and RNAV " T " or " Y " program design.

B, automatic drawing protection

In mission program design, maximum workload is drawing protection, but drawing process is a process repeatedly revising adjustment, merely by hand or CAD not only can consume a large amount of energy of designer, and inaccurate being easy to is made mistakes.In the present invention, with reference to ICAO PAN-OPS 8168 and FAA specification, utilize geographical information platform, adopt the automatic drawing protection of parameterized mode, alleviate the workload of programmer, ensure the quality of mission program.

The invention provides parametrization, connection procedure is drawn in intelligentized protected location, makes complicated service logic process become simple, greatly improves work efficiency.Major embodiment is several aspect below;

1, the generation of straight line protected location;

2, the generation of turning protected location, and fragmented storage, be convenient to the Segment evaluation of protected location;

3, the seamless link of RNAV/RNP protected location and conventional I LS protected location;

4, the conversion between protected location only need regulate a parameter for another way point, and such as, MAP meets DF and meet TF after MAP is turned after turning, and only need change the more lower flight path termination code of MAP.

5, the intellectuality prompting in the generative process of protected location.If the parameter arranged does not meet the rule generating protected location, software provides information and advisory information immediately.

Protected location paint type in the present invention is mainly as shown in table 1, and the protected location figure automatically generated as shown in Figure 4.

Sequence number	Protected location type	Corresponding programme section
			1	DF is met after leaping turning (Fly-Over)	Mission program section is turned

2	Fly-by turns (Fly-By)	Mission program section is turned
			3	Specified altitude assignment of leaving the theatre meets DF after turning	To leave the theatre turning
4	Specified altitude assignment of going around is turned	To go around turning
			5	DF is met after MAP is turned	To go around turning
6	Specify semidiameter turn (RF)	Mission program section is turned
			7	TF is met after leaping turning (Fly-OVER)	Mission program section is turned
8	Specified altitude assignment of leaving the theatre meets CF after turning	Mission program section is turned
			9	TF is met after MAP is turned	Mission program section is turned
10	CF is met after MAP is turned	Mission program section is turned
			11	ILS	Closely the most laggard
12	ILS	Go around
			13	RNP waits for	Wait for
14	APV I/II procedures—GBAS	Closely the most laggard
			15	APV I/II procedures—GBAS	Go around

Table 1

C, barrier is assessed

An important step of mission program design is exactly barrier assessment, directly concerns the success or failure of program, concerns flight safety.Two classes are mainly divided into by the source of barrier, i.e. cultural obstacle and the data (as electronics altitude figures DEM) from electronic chart, and electronic map data amount is large, such as, usually reach hundreds of thousands for the location point on the electronic chart of APV-BARO VNAV program, the data processing is like this more difficult, the parameter that the present invention inputs according to user and the parameter that system automatically calculates or obtains, according to mission program barrier Rules of Assessment, realize barrier assessment robotization.

The present invention can to RNAV, RNP standard program carries out carrying out cultural obstacle and DEM obstacle recognition, visual and non-visual obstacle clearance analysis and barrier assessment according to ICAO annex, CAAC regulations, finally accurately draw the parameter such as barrier place obstacle clearance surface and obstacle clearance height, provide referential suggestion, hand over assessment result to show on two-dimension GIS map simultaneously.Barrier assessment kind comprises:

● APV-BARO VNAV barrier is assessed, as shown in Fig. 5, Fig. 6 and Fig. 7;

● the segmentation barrier assessment of Standard Approach, departure procedure;

● ILS-OAS barrier is assessed;

● non-precision approach barrier assessment;

● Initial Approach section barrier is assessed;

● the assessment of nearly section barrier is entered in centre.

D, the present invention's application aviation information exchange model (AIXM) specification, exports and adopts ARINC424 coded format, so partial data can be shared with flight simulator, and intercourses, for setting up airport scene database, flying quality etc.The data shared comprise:

● electronic map data

● mission program data

● airport, runway data

● location point data

● barrier data

E, standard chart generates robotization

One of net result of mission program design is exactly issue chart, automatically generates the electronic stencil of the chart importantly production standard meeting international standard or China's standard, then utilizes the data in SUPERMAP data source to add mold filling plate, generate standard chart.Only need amendment some areas wherein, as adjustment labeling position, namely become the chart that can issue.

The present invention according to standard chart template generation chart, as shown in Figure 8.Mainly contain and generate lower several chart:

● RNAV Standard Approach figure

● RNP Standard Approach figure

● RNAV standard is left the theatre figure

● RNAV instrument approach figure

● RNP instrument approach figure

F, based on the intelligent editing function of business rule, specific as follows:

A, based on the visual edit function of business rule, comprising:

● according to the sequence of all types of way point of program, catch by the operation of drawing and mouse the way point forming (containing near) program of leaving the theatre/march into the arena;

● operations such as according to the sequence of all types of way point of program, being added forward by the way point of operation to program of drawing and mouse, add backward, middlely to add, delete, remove;

B, based on the automatic Verification assist edit function of business rule, comprising:

● according to the way point sequence of Program Type, the connection of each way point of automatic discrimination, and point out the connection type of next way point;

● calculating feedback automatically leaps, the shortest stabilizing distance of fly-by turns;

● automatically judge the feasibility that flight path is turned;

● automatically calculate the radii fixus that feedback RF turns;

● automatically identify leg type by way point type and some sequence;

● according to the indicated airspeed that leg type automatic acquisition ICAO specifies, the gradient, the data such as reaction time; C, based on the mission program interface editing function of parameter, comprising:

● drawing program type is determined in the selection by the Program Type entering to leave the theatre;

● the selection by entering nearly type is determined near mode;

● the mission program analysis and designation parameter used that the ICAO such as XTT, ATT, half-breadth specify is determined in the selection by navigational facility, navigation specification and aircraft type;

● support leaps, the selection of fly-by turns, straight-forward program;

● support the selection that specified altitude assignment and radii fixus are turned;

● support that TF, DF turn;

● support the amendment of the data such as indicated airspeed, the gradient, wind speed, temperature variable, pilot reaction time.

Of the present inventionly meet ICAO and civil aviaton of China to the operation demand of PBN program based on performance navigation PBN mission program design system, break the monopoly position of external procedure service provider in this field, develop PBN mission program software first at home, important basis is laid for CAAC carries forward vigorously PBN mission program, provide indispensable means, to the PBN program designed in guarantee flight safety, improve operational efficiency aspect significant, have significant economic and social benefit.

Based on performance Navigator verification platform:

PBN mission program, after design completes, needs to carry out reliability, the integrality that simulated flight checking ensures the program after having designed, then carries out real Flight.The method of traditional simulated flight checking the program designed is given navigational route database manufacturing company companies such as () thalous, honeywell to be made into every navigational route database once upgraded for 28 days, then utilizes full dynamic simulated machine (FFS) or solid model (FTD) to load navigational route database and carry out simulated flight checking.This verification method is in each program design or all need the renewal waiting for navigational route database after upgrading, and the cycle causing mission program to design is long, and efficiency is low, cannot meet the demand of domestic a large amount of RNP program design, be unfavorable for design and the popularization of RNP program.In order to improve the efficiency of checking, sooner, better RNP mission program is verified, the present invention devise can efficiently, the verification platform of accurate validation RNP mission program---based on performance Navigator verification platform.

As shown in Figure 3, described verification platform comprises flight dynamics system, flight management and guidance system (FMGS), flight control system, engine system (comprising fuel system), atmosphere data (ADC) and Inertial Platform System (IRS), central monitoring system (ECAM), control system, instrument system and visual system.

Described flight dynamics system comprises Aerodynamic Coefficient module and equation of motion module, described Aerodynamic Coefficient module be rise under the various condition of aircraft, the set of resistance and moment coefficient, in computation process, obtain the various Aerodynamic Coefficient value of aircraft this moment by real-time query.It is by receiving aircraft rudder surface, the flap configuration of control system, and landing gear position, with relevant flight parameters such as flying speed, Mach number, grade, attitudes, utilize these parameter query Aerodynamic Coefficients, recycling Aerodynamic Coefficient calculates flight force and moment, and result of calculation is transported to equation of motion module.

Described equation of motion module receives the flight force and moment of Aerodynamic Coefficient module, and the thrust magnitude of engine system, fuel weight and center of gravity of airplane position, and normal atmosphere data, utilize these conditions and aircraft initial value, resolve the non-linear full dose equation of motion of aircraft six degree of freedom, obtain the attitude of aircraft, speed, grade, position and other flight parameter, and these parameters are fed back to pneumatic system module again, again inquiry obtains go forward side by side promoting the circulation of qi power and aerodynamic moment of Aerodynamic Coefficient and calculates, pass to equation of motion module again, go round and begin again and repeat above-mentioned computation process, realize flight dynamics to calculate.

Flight management and guidance system (FMGS), self is with navigational route database, aircraft performance database and aerodynamic data and engine data storehouse, realizes flight management and guides two parts function with flight.Realize navigation management (calculating of inertia, satellite and foundation navigation signal, automatically select), flight planning, performance prediction and optimization and automatic Pilot manages, flight director instruction, auto-throttle instruction.In flight management part, can pass through man-machine interface (MCDU) input take off initial parameter and leave the theatre and march into the arena, approach flight program, undertaken leaving the theatre, landing by this mission program to make aircraft.

The flight leader of FMGS, receive the position of aircraft dynamics module and flight control system transmission, the information such as speed, with the flight planning comparison in database, calculate current speed, course and course error, pass to flight again to control and engine system, realize speed, the control of course and course-line deviation, afterwards, the new position that dynamics module and flight control system will calculate again, the information feed back such as speed are to FMGS, calculation deviation controlling again, go round and begin again repetition said process, complete navigation procedure, make aircraft by expection track flight.Meanwhile, it can also calculate the precision of navigation sources and positional precision, and reports to the police when precision is undesirable.

Flight control system, current flight path, course deviation that reception flight management and guidance system send, utilize the control rate designed in advance, calculate and revise aircraft rudder surface required for deviation and flap control amount, manipulated variable data are delivered to aerofoil steering wheel, executable operations, makes aircraft change attitude and course, according to the track flight of expection.

Present speed, height tolerance that engine system (comprising fuel system), same reception flight management and guidance system send, utilize the engine throttle control rate designed in advance, calculate and revise fuel flow required for deviation and auto-throttle manipulated variable, manipulated variable data are delivered to engine system, executable operations, make engine change thrust, thus change the flight parameter such as speed, height, reach the airmark of expection.

Atmosphere data (ADC) is with Inertial Platform System (IRS), atmospheric treatment machine part obtains the basic parameter such as dynamic pressure, static pressure, stagnation pressure, atmospheric temperature of air by sensor, calculate current air basic parameter, and the information such as barometer altitude, air speed.Simultaneously, inertial platform part obtains aircraft acceleration information by three axes accelerometers, the velocity information of three axles is obtained by integration, integration obtains three dimensional local information again, utilize the air speed information of atmosphere data, current wind speed can be calculated, utilize air pressure signal, obtain barometric-corrected altitude.

Central monitoring system (ECAM), receive the data from atmosphere data and inertia system, flight management and guidance system and flight dynamics system, flight control system, engine system etc., each working state of system and data are monitored, once there is data over run and abnormal state, to report to the police with audio frequency and video information, and remind unit to note.

Control system, provide the equipment of unit manual control aircraft, comprise deflecting roller, jociey stick, throttle lever and pedal, control command is directly sent to flight control system, aerofoil steering wheel, engine system etc. by these equipment by unit, serve the function of override flight management system, taking off, land and traffic adjustment, control order time manually handle, also can manual control aircraft when thrashing, burst are unexpected.

Instrument system, mainly comprises primary flight display, navigation indicator etc.Receive the parameter from atmosphere data and inertia system, flight management and guidance system and flight dynamics system, flight control system, to current flight attitude, speed, grade, Mach number, highly, the data such as flight path, navigation information, terrain information, atmosphere data, flight planning show, check for unit, understand current state of flight.

Visual system, same reception current flight attitude, speed, grade, Mach number, highly, flight path, the information such as navigation, utilize the three dimensional topographic data storehouse carried, aloft virtual three-dimensional scene is provided, comprise dimensional topography, three-dimensional atmospheric environment, airport and terminal area environment, three-dimensional model aircraft etc., additionally provide the acoustics in engine and extraneous physical environment, for unit simulated flight provides 3D vision true to nature and auditory information, flight environment of vehicle has stronger infiltration sense.

This system possesses the function of reproduction airflight environment, can take off, land, climb, turn, maneuvering flight simulation to pilot, also can analyze and research to aeroplane performance, handling quality, mobile system performance simultaneously.The aircraft system realistic model of this verification platform comprises flight dynamics model, engine system models, control system model, Navigation System Model, flight management system model etc., and the various logic control planning between model is consistent with true aircraft.The function of each subsystem of aircraft and performance simulation are accurately, can run, and operating personnel equally on true aircraft with them can operate these systems.

In order to better complete the checking of mission program, the true environment of better simulated flight proof procedure, the flight course that reduction is actual, is necessary for checking flight and provides what comes into a driver's.Flight scene is the important component part of flight validation system, and can be program verification personnel provides lasting, stable visually parameter to examine, and is the actual position entering closely to provide runway of flight.Such as, in program design, whether the height of last several anchor point can land smoothly to aircraft, plays conclusive effect.After program design completes, carry out checking flight by what comes into a driver's and in conjunction with the performance of aircraft, can the setting of height of the last anchor point of extraordinary judgement whether reasonable, feasible.Can be program staff in addition and barrier and terrain information be provided, can by Flight scene experience intuitively the design of the flight obstacle clearance of aircraft and protected location whether rationally, meet specification.

As shown in Figure 9, comprising of described flight scene system: flying quality interface, scheduling memory module, buffer management module, what comes into a driver's cutting module, output module is played up.

Flying quality interface: the flying quality that real-time temporally sequential reception analog machine produces also extracts the relevant informations such as the six degree of freedom parameter of aircraft, drives what comes into a driver's.

Scheduling memory module: due to the magnanimity feature of airport visual system terrain data, and the restriction of image processing hardware condition, be difficult in all data of the disposable loading of terrain scene establishment stage.In the present system, scheduling memory module according to the scope in the viewpoint position obtained in airplane data interface and the visual field, can control the scope of required rendering image, and the data of correspondence is read in internal memory in real time.

Buffer management module: the function of this module is data dispatching, simplified model.When observing viewpoint and roaming in Virtual Terrain scene, according to the scope of viewpoint and look migration to prediction, the system interior data that will come into view call in buffer zone from database; Described buffer zone comprises Render Buffer and to data buffer.When observing viewpoint and roaming in Virtual Terrain scene, according to the scope of viewpoint, the data entering viewpoint must be played up, meanwhile, because calling in of data needs a process with modeling, according to the prediction moved towards viewpoint control.System also needs from database, call in data for those interior blocks that will come into view and carry out modeling.In order to address this problem, for current view point establishes Render Buffer and data buffer, be responsible for playing up and dispatching of data respectively.

Render Buffer and data buffer.Render Buffer refers to according to active user's field range, and its roaming mode adopted, a visual range of delimiting, and the landform fallen within the scope of this must be played up, otherwise user will see an incomplete scene.The size and shape of Render Buffer not only needs the viewpoint parameter considering user, as distance, visual angle etc., also needs to consider current adopted roaming mode.Can set up fan-shaped buffer zone for flight roaming, fan-shaped radius is relevant with the length of sighting distance, and fan-shaped angle is then decided by visual angle.The radius of buffer zone determines primarily of pilot's sighting distance.

Scheduling due to data needs to spend the regular hour, therefore, needs before data block comes into view, needs those data blocks that may come into view very soon of forward scheduling.By setting up data buffer around Render Buffer, before data render, potential visible data can be called in, and then carry out modeling and play up.The delimitation of the scope of data buffer is the same with Render Buffer, also needs the roaming mode adopted based on active user to carry out.

The data management of buffer zone and playing up.When real time roaming, each frame all needs before playing up to judge the unit in Render Buffer and data buffer, with the data determining the data that current needs carry out playing up and be loaded into from secondary storage as required.Here usage data manager and scene manager are responsible for the scheduling of data and playing up of scene respectively.In scene manager, the information such as the position to current view point, direction and roam speed of being responsible for are followed the tracks of, and determine the scope of Render Buffer and data buffer with this, and safeguard a pointer pointing to Render Buffer.Render Buffer shows as the pointer list of all data cells in current Render Buffer, when viewpoint moves, scene manager is responsible for, according to real-time the upgrading unit in Render Buffer of viewpoint parameter, the new unit pointer entering Render Buffer being added pointer list.And delete the pointer that those have shifted out Render Buffer unit.Meanwhile, scene rendering management uses a kind of " poll " mechanism.Whether the data of constantly inquiring in current Render Buffer to data management system are ready to, when data buffer is reasonable in design, those data entering Render Buffer should be ready, and namely should always to obtain answering of affirmative mad in this inquiry.Scene manager, after being confirmed, is played up the data block in Render Buffer.

In buffer zone, the management of data is responsible for primarily of data management system, safeguards the information of secondary storage database and a list of pointers friend of current data buffer zone in data management system simultaneously.Data management system enters the sequencing of data buffer according to data block, calls in the data of each resolution from Law of DEM Data storehouse, backstage.Meanwhile, the scheduling receiving data from scene manager confirms request, and sends corresponding confirmation to scene manager.

Data dispatch, the multithreading realization simplifying and play up.Data are called in from database, modeling simplifies and even play up the certain process of needs.Meanwhile, the continuity that scene must be able to be kept to show is played up and roamed to real-time virtual scene requirement to scene.Therefore, desirable state is that the scheduling of data and playing up of scene can be carried out simultaneously, keeps the continuity of data between scheduling with display.In the large-scale virtual environment of multi-CPU architecture, scene can be carried out piecemeal according to the region on screen, each piecemeal uses an independent CPU to carry out modeling and Graphics Processing, and multiple CPU parallel computation obtains the real-time virtual image of whole scene.This is a kind of horizontal parallel processing algorithm, is adapted at the reality environment that the computer network platform of concentrating type is set up.And on the microcomputer of uniprocessor, then can realize based on the multithreading support of system.Here, what responsible data dispatch and the data management system of simplification and the scene manager of responsible scene rendering are placed on respectively two threads asks realization, by the scheduling of event notice coordination data with play up between thread.

What comes into a driver's cutting module: two-dimensional geometry to as if set up in object coordinates system, but the image that screen shows is just under given viewpoint and direction of visual lines, and two-dimentional scenery is perpendicular to the projection in the two-dimensional imaging plane (screen) of direction of visual lines.After scenery in scene has been transformed into eye coordinate from object coordinates system, ensuing work is will the coordinate conversion in eye coordinate in screen coordinate system, before this, must test the relative position of object and view body, this test is necessary, because carry out perspective transform or orthogonal transformation is skimble-skamble to being positioned at the external object of view, and external at view, and the definition of screen space conversion is ill.

In eye coordinate, the relation of a given object and view can be divided into following a few class:

● it is external that object is positioned at view completely, can discard at once.

● object is positioned at view body completely, it is transformed to screen coordinate system and plays up.

● object is crossing with view body, needs to carry out cutting with view body to object, then plays up the part be positioned within view body.

Judge the relation of an object and view body, namely determine this object whether in current what comes into a driver's, first will determine the equation of view six cutting planes, then calculate the distance between object and each cutting plane, judge by these distances.

Play up output module: Render Buffer shows as the pointer list of all data cells in current Render Buffer, when viewpoint moves, scene manager is responsible for, according to real-time the upgrading unit in Render Buffer of viewpoint parameter, the new unit pointer entering Render Buffer being added pointer list.And delete the pointer that those have shifted out Render Buffer unit.Meanwhile, scene rendering management uses a kind of " poll " mechanism.Whether the data of constantly inquiring in current Render Buffer to data management system are ready to, and then play up the data block in Render Buffer.

The manufacturing process of described what comes into a driver's is: data processing, visual fusion, Flight scene Database Modeling, flight simulation visual system and the flight simulation visual display based on microcomputer, first three part is the process process of what comes into a driver's data being generated to what comes into a driver's data, and rear two parts are playing up of image and show.Original photo, landform, vector data etc. finally generate scene database by this process, play up generation Flight scene by microcomputer.

Visual system adopts the scene database of real landform, texture, airport data genaration;

For checking personnel provide continuous print large-scale landform what comes into a driver's;

Airport Images comprises landform, the landforms of near airports, cultural traits, the runway in airport and taxiway and terminal etc.;

Controlled weather system, cloud base are high, visibility, runway visual range and airfield light;

Scenery picture mates with aerodynamic program design, and provides the exact circumstances image relevant with attitude.

Visual system of the present invention have employed the solution of the hardware of Based PC and TV screen, the selection of PC graphic display card is considered the requirement of frame rate and selects high performance video cards.In the selection of three screen viewing hardwares, do not adopt common multi-display card technology, but adopt the design of single video card+special split screen hardware.Special split screen hardware have employed graphic extension module (GXM) technology, and being assigned to by a road VGA signal of input is three road signals, and allows Windows 2000/XP operating system, according to suitable ratio, picture signal is outputted to display screen.Concrete configuration environment is as follows:

1)CPU：AMD Athlon(tm)64X2Dual Core Processor 3800+；

2) internal memory/hard disk: 4G/500G;

3) display card/video memory: GeForce 7600GS/256M

The visual system being core with vision rendering system is integrated mutually with the flight validation system guiding analogue system to be core with flight management, set up the communications protocol of both sides, realize flying quality, the communication of control data and visual system, makes the display of visual system and the flight of aircraft run accurately corresponding relevant.

Communications protocol between verification system and visual system is the customization communication standard be based upon in TCP/IP transmission control protocol, is used for transmitting the position of flight, attitude, manipulation and performance parameter.

Verification system and visual system are combined, the core of design extracts relevant information from seasonal effect in time series flying quality, drives scene database.And be the six degree of freedom parameter of aircraft as the main information in the flying quality of key: relative to airport and the three dimensional space coordinate of landform and three attitude angle (head, roll, pitch) relative to body.By the information of these 6 parameters, just uniquely can determine the state of flight in aircraft a certain moment, program on Functional Design real-time by 6DOF information displaying on screen.

Verification platform of the present invention achieves following function:

1, the emulation of flight management guidance system (FMGS): FMGS receives the input coming from the systems such as air data computer, inertial reference system, navigational route database, Mult1purpose Coutrols & Display Unit (MCDU) and flight Control Component (FCU), provides signal to after treatment automatic Pilot, auto-throttle, main flight display (PFD), navigation display (ND) and working state control platform.The navigational route database that FMGS can use user oneself to provide.Flight management guidance system is exactly a Flight Management Computer System in itself, and it is multiple processor system, comprises navigation processor, performance processor and I/O processor three part.Numerical data transmits and adopts ARINC-429 form.By to aeroplane characteristic handbook, the analysis of the related datas such as flight airmanship, framework goes out the flow chart of flight management guidance system, realize the emulation to FMGS, processor module of wherein navigating receives the atmospheric parameter from air data computer module input, take off location parameter, the distance direction parameter of best guidance station of inertial reference system input and the direction parameter etc. of radio navigation system, then by optimizing these data, calculate aircraft current location and flight parameter, and output to automatic mission program design system, the related systems such as EFIS, performance processor module is then according to the optimum flight profile, mission profile that current atmospheric conditions are determined under a certain performance index.

1) emulation of Mult1purpose Coutrols & Display Unit (MCDU): MCDU is the vitals that FMGS enters man/machine dialogue, realize calculating air route and performance parameter to the flight needed for Flight Management Computer (FMC) input by imitation multi-functional Control Items (MCDU), it provides loading and the display of true, accurate and complete flight planning.By utilizing the graph processing technique of Real-time Simulation Technology, network communications technology and computing machine, solve the various key issues such as the data transmission involved by MCDU, electronic page generation and tissue, page layout switch, fault handling and real time execution, achieve the emulation to MCDU, and adopt touch-screen to drive simulating keyboard as input media, complete the input function of the assortment of keys of MCDU.

2) realization of flight (Auto Flight) automatically: according to composition and the function of the automatic mission program design system of aircraft, whole automatic mission program design system is divided into interface module, logic module, pitch control subsystem rate module, control of sideward roll rate module, yawdamper module and engine system module six major part, interface module mainly emulates the important interface input quantity of automatic mission program design system, and adopts the change of main these input signals of iterative rate collection and monitor, logic module receives the switching value from interface module, mark amount and the pitching of automatic mission program design system, control of sideward roll module, auto-throttle module, Flight Management Computer and about the current various quantity of state of subsystem module and mark amount, emulate the mode of operation under automatic mission program design system various connection logic and various flying method, and attitude director, these mark amounts are also transported to the upper display of flying method annunciator (FMA) by autopilot operation, also deliver to flight Control Component (FCU) the corresponding pilot lamp of upper driving and caution signal simultaneously, pitch control subsystem rate modular simulation flight director sys tem and autopilot system pitch control subsystem return circuit, complete the attitude director control rate under pitching mode all working pattern, calculate and generate the command signal and emulation robot pilot control rate that drive attitude director pitch demand bar, generating the command signal driving elevating rudder, control of sideward roll rate modular simulation flight director sys tem and autopilot system control of sideward roll return circuit, the control rate completed under various mode of operation calculates, and generates roll command bar drive singal and aileron drift angle steering order signal, yawdamper modular simulation flight control system yawdamper function, when pitching, the roll channels operation of automatic mission program design system engagement the autopilot, yawdamper must be connected, receive the calibrated airspeed of aircraft yaw rate signal, air data computer output, calculate yaw rudder steering order, reach the stability that goes as course, the vibration that damping Dutch roll causes, the functions such as coordinate turn are provided, engine system modular simulation auto-throttle control system function, under may operate at the mode of operation coordinated with pitching flying mode, obtains and throttle lever position needed for keeping.In automatic mission program design system, the message exchange of each intermodule is realized by local public data area, and the message exchange between automatic mission program design system and other subsystems is by overall common data block transitive.

3) emulation of flight Control Component (FCU): driver arranges automatic Pilot and auto-throttle by FCU, and can the input information of the FMGS such as pre-selected height, speed/Mach number, course, flight path by FCU, the reference data that these parameters are pitching, roll, control law calculate.

4) emulation of EFIS (EFIS): flying instruments is the window of aeroplane performance parameter and navigational parameter display, provides the visual information in passenger cabin to pilot.We adopt computing machine real-time graphic image technology to generate digital graphical meter on computer terminals, these simulation instrument at outward appearance, indicating mode with functionally all consistent with the instrument on true aircraft, flight parameter, navigational parameter, electrical system parameter, engine parameter etc. are shown and are supplied to driver in real time, meets the needs of flight training.Realizing the function of Electronic Flight Instrument symbol generator, is that main flight display (PFD) and navigation display (ND) provide symbol to export.The process of Electronic Flight Instrument symbol generator comes from the input information of each subsystem of aircraft and parts, produce format the signal that uses by EFIS (EFIS).

2, the object training of all relevant flight sections is realized when nothing is in kind

Utilize split screen display card, serial card, touch-screen to realize operation, realize the object training of all relevant flight sections when nothing is in kind.

3, complete the development of following simulation hardware, pilot can be trained in environment more true to nature:

1) the simulation hardware development of side lever, throttle lever and turning handwheel is completed;

2) the simulation hardware development of flight Control Component FCU is completed;

3) the simulation hardware development of Mult1purpose Coutrols & Display Unit MCDU is completed.

4, visual system has technological breakthrough below:

1) applied geography information systems technology, process landform vector data and dem data, merge the terrain data of the rear rediscover of calibration, ensure virtual simulation environment availability, reliability.

2) the acquisition and processing technology of texture, utilize remote sensing image preconditioning technique (geometric correction, radiation correcting, information enhancement), grain table technology, process multiple image data, make texture can retain more information, make the flight environment of vehicle of what comes into a driver's more approaching to reality.

3) constructing technology of three-dimensional model, sets up method and the flow process of airport and termination environment what comes into a driver's stereoscopic model modeling, the foundation of airport and termination environment buildings stereoscopic model, the stereoscopic models such as airport direction board and light.

4) adopt virtual reality technology and Computerized three-dimensional emulation technology, exploitation vision rendering system, realizes validity high, can render the scene of approaching to reality flight environment of vehicle; Case technology, external reference technology, mapping technology, level of detail (LOD), child node technology etc. is adopted to be optimized process to model.Improve the efficiency of scene database at the what comes into a driver's real-time rendering system cloud gray model of Based PC.

Use verification platform to carry out the method verified, comprise the following steps:

(1) typing navigational route database: by upgrading navigational route database interface, start navigational route database editing system, the information type that flight validation personnel selection will input, the various data that input is corresponding, after input data, generate database, restart flight validation platform;

(2) arrange flight parameter, carry out ground validation: checking personnel pass through tarmac, parameters, personnel are according to Standard Flight program in checking, carry out the various operations of flight cavity;

(3) verify in laggard line space of taking off: checking personnel carry out the various operations of taking off according to the mission program of standard;

(4) nearly phase authentication is entered: when aircraft was in into the nearly stage, navigational system is according to predetermined Gradient Descent to the speed of program design, and automatic vector aircraft to DH+50 height, is not relied on instrument landing system (ILS) by vertical guidance system, under GPS PRIMARY pattern, realize automatic Landing.

Mission program design system of the present invention and verification platform have following innovation:

1, coding input aircraft navigation database must be carried out with WGS84 coordinate for PBN mission program automatically to fly, and China's topomap is all Beijing 1954 coordinate system, map reference and program coordinate system mismatch problem, the present invention adopts Geographic Information System to carry out conceptual design, realize the mutual conversion of WGS84 coordinate system and Beijing 1954 coordinate system, solve the problem at China's topomap (Beijing 1954 coordinate) upper design PBN mission program (WGS84 coordinate) coordinate and precision.

2, high for PBN program precision prescribed; hand-designed program efficiency is low; the problem of accurate rate variance; this system is according to the programming discipline of ICAO and CAAC; can according to the automatic drawing program protected locations of attribute such as way point, program height, leg type, assessment barrier, generation chart; the functions such as the seamless link in PBN programmed protection district and conventional flight programmed protection district can be realized, increase work efficiency, reduce mistake.

3, for after mission program complete design, need to repaint chart according to Program path to publish, workload is large, easily make mistakes, revise the problem of length consuming time back and forth, the data that this system can design according to mission program generate chart automatically, also can according to demand customization editor and amendment, accomplish program design, publish once complete.

4, use for external PBN program verification the problem that full dynamic simulated machine cost is high, navigational route database fabrication cycle is long, program verification platform of the present invention does not need FMS navigational route database company to make coding at the checking initial stage, directly can carry out interpolation PBN program in the navigational route database of verification platform, can edit navigational route database and revise in proof procedure, modification of program does not need to wait 28 day cycle, and real time modifying navigational route database can be verified again.Until modification of program improve after, net result is submitted to FMS navigational route database company (Smith company and Honeywell company) and is completed coding, pay airline can put into operation.

5, PBN mission program verification platform adds scene database, when verifying PBN mission program, can the defect of the discovery procedure directly perceived design according to the topography and geomorphology in what comes into a driver's and deficiency, and to the further modification and perfection of program.

In a word, the present invention disposablely in programming effort environment can complete program design, coding, checking and iterative optimization procedure thereof.Greatly improve the application level of China's navigation new technology in civil aviation field.

The present invention can be applicable to:

Airline

1) accurately guide aircraft, improve the security run

Compared with conventional flight program, the precision navigation of PBN can vector aircraft along the flight of favourable landform, the easy degree of the predictability of its flight path, accuracy and operation is all far superior to traditional program.As: in high-altitude aerodrome runs, aircraft true air speed is large, and maneuverability is poor, and slowly, flight operation is obviously blunt than Plain airport for speedup and deceleration.In addition, the easy anoxic of highlands pilot, reaction capacity declines, and psychological pressure is large.Clearly, basic dependence is flown automatically for the track of PBN program and requirement for height, and the main task of pilot monitors state of flight, and operational load reduces greatly.In addition, PBN enters and closely generally takes the mode that declines continuously (Continue Descend Approach, CDA), and reduce the most laggard near downward gradient of aircraft, pilot easily controls throttle and Speed of Approach, improves near stability.

2) increase airline's industry to carry

Conventional flight program considers that the scope of barrier is larger, requires higher to take-off climb or gradient of going around.At high-altitude aerodrome, airline often has to be carried by minimizing industry meet aeroplane performance requirement.Use PBN technology, then can make full use of lineament, reduce barrier scope, reduce gradient of climb requirement, effectively increase industry and carry, promote the on-road efficiency of airline.

3) reduce the flight time, save fuel oil

Do not rely on the laying of Land Navigation Installation, point-to-point direct flight, realize the flight boat footpath optimized flexibly, shorten the flight time, save fuel oil, evade noise-sensitive district, emissions reduction improves Environmental Protection Level.

4) program design takes into full account flight emergency measure

The concrete property (as navigation performance, aerodynamic quality etc.) of some aircraft is not considered in conventional flight program design, does not consider special circumstances (as power failure, guidance station dropout etc.) yet.RNP program is then airborne equipment ability according to institute's airplane-type and aeroplane performance, and consider various special circumstances, such as: take off, enter a power failure near and process of going around, lose navigation signal (as GPS lost efficacy), automatic mission program design system lost efficacy, flight management system inefficacy etc.Also formulate corresponding Response project for all special circumstances on this basis, assessment and analysis general safety level.

5) the airborne homing capability of aircraft is given full play to

RNP program makes full use of the airborne equipment of aircraft, plays the ability of aircraft, to improve security and the economy of operation.Compare with departure procedure with traditional instrument approach procedure, IAP, RNP runs has obviously advantage, and the airport be particularly suitable for by restrictions such as landform, flight facilities and spatial domains and region.

Blank pipe

1) level and longitudinal separation between aircraft, improves the service efficiency in spatial domain, increases airspace capacity, because PBN technology uses the concept of degree of containing, required spatial domain is less, so just likely within the scope of limited spatial domain, arranges more course line, reduces the lateral separation between course line.Due to the accuracy of PBN navigation, the design into course line of leaving the theatre " viaduct " formula can be realized, thus make, into separation of leaving the theatre, to avoid course line to converge, alleviate controller's burden, under the premise that security is guaranteed, effectively promote airspace capacity.

2) ATC controller workload is reduced

Conventional flight program needs controller and pilot frequently to converse, carry out flight path guiding, PBN program has existed in aircraft FMS navigational route database, flight path is accurate, aircraft can be realized automatically fly, be convenient to commander, reduce the empty voice communication in land and the radar vectoring demand of controller and pilot, reduce working load;

Airport

1) normality of Airport Operation is improved

China's high-altitude aerodrome is owing to limiting by landform, and Airport Operation weather standard is higher.Wherein, the actual motion of most of high high-altitude aerodrome substantially all requires it is visual flight.Airport is subject to weather effect, and normal operation is low.Use PBN program, because flight tracking control accuracy is high, the protected location of needs is little, can reduce take-off and landing standard, thus reduces weather to the impact of flight, improves the normality of Airport Operation.

2) expense of reducing investment outlay and operating cost

PBN technology mainly uses satellite navigation, and precision is high, good reliability, operating cost are low, can reduce the dependence to flight facilities, save build, on duty, safeguard and the expense such as verification, reduce the day-to-day operation cost on airport.In addition, PBN also can reduce the requirement to obstacle free airspace process, has the earthwork disposal cost utilizing protection of the environment and reduce airport construction.

PBN runs can obtain above-mentioned operation benefit, but its core is that PBN mission program designs.This system is realize the design of PBN mission program and solid foundation has been laid in checking, accelerates PBN program applying at home.

System succeed in developing as civil aviaton of China is according to the implementation plan of CAAC PBN Implementation Roadmap, provide important technical guarantee, the development of system has been successfully applied to the PBN operation on Guyuan airport, and the mission program designed by proving can be used for actual motion.Air China Yi Yuanji has signed at center the PBN mission program cooperation agreement on 25 airports, accelerates the application & development that PBN mission program operates in China.

Domestic operator will participate in international airline competition comprehensively, the international development process of airline, and airline faces increasing cost pressure, need the automatic flight that the PBN mission program using native system to design realizes flexibly, optimizes, increase aircraft industry to carry, reduce the flight time, save fuel oil; Avoid noise-sensitive district, improve Environmental Protection Level.

Along with the fast development of CAAC, spatial domain resource is nervous, and cause air traffic to be blocked up, the operation on some airports is close to state of saturation, and existing operation concept and technological means can not meet the demand that the magnitude of traffic flow increases fast completely.The PBN mission program utilizing native system to complete, parallel routes can be implemented and increase in termination environment, air route anchor point of leaving the theatre, improve the magnitude of traffic flow; Reduce level and longitudinal separation between aircraft, increase airspace capacity; Reduce earth-space communication and radar vectoring demand, be convenient to commander, reduce the working load of controller and pilot.

Technique scheme is one embodiment of the present invention, for those skilled in the art, on the basis that the invention discloses application process and principle, be easy to make various types of improvement or distortion, and the method be not limited only to described by the above-mentioned embodiment of the present invention, therefore previously described mode is just preferred, and does not have restrictive meaning.

Claims (6)

1. the verification platform for verifying the mission program design system of navigating based on performance, is characterized in that:

Described verification platform comprises flight dynamics system, flight management and guidance system, flight control system, engine system, atmosphere data and Inertial Platform System, central monitoring system, control system, instrument system and visual system; Described engine system comprises fuel system;

Described flight dynamics system comprises Aerodynamic Coefficient module and equation of motion module, described Aerodynamic Coefficient module be rise under the various condition of aircraft, the set of resistance and moment coefficient, in computation process, obtain the various Aerodynamic Coefficient value of aircraft this moment by real-time query; It is by receiving aircraft rudder surface, the flap configuration of control system, and relevant flight parameter, utilizes these parameter query Aerodynamic Coefficients, and recycling Aerodynamic Coefficient calculates flight force and moment, and result of calculation is transported to equation of motion module;

Described equation of motion module receives the flight force and moment of Aerodynamic Coefficient module, and the thrust magnitude of engine system, fuel weight and center of gravity of airplane position, and normal atmosphere data, utilize these conditions and aircraft initial value, resolve the non-linear full dose equation of motion of aircraft six degree of freedom, obtain the attitude of aircraft, speed, grade, position and other flight parameter, and these parameters are fed back to pneumatic system module again, again inquiry obtains go forward side by side promoting the circulation of qi power and aerodynamic moment of Aerodynamic Coefficient and calculates, pass to equation of motion module again, go round and begin again and repeat above-mentioned computation process, realize flight dynamics to calculate,

Described flight management and guidance system, self is with navigational route database, aircraft performance database and aerodynamic data and engine data storehouse, realizes flight management and guides two parts function with flight; Described flight management part, by man-machine interface input take off initial parameter and leave the theatre and march into the arena, approach flight, undertaken leaving the theatre, landing by this flight to make aircraft;

Described flight leader, receive the information of aircraft dynamics system and flight control system transmission, with the flight planning comparison in database, calculate current speed, course and course error, pass to flight control system and engine system again, realize speed, the control of course and course-line deviation, afterwards, the fresh information calculated is fed back to flight management and guidance system by aircraft dynamics system and flight control system again, calculation deviation controlling again, go round and begin again repetition said process, complete navigation procedure, make aircraft by expection track flight, meanwhile, flight management and guidance system calculate the precision of navigation sources and positional precision, and report to the police when precision is undesirable,

Described flight control system, the current flight path that reception flight management and guidance system send and course deviation, utilize the control rate designed in advance, calculate and revise aircraft rudder surface required for deviation and flap control amount, manipulated variable data are delivered to aerofoil steering wheel, executable operations, makes aircraft change attitude and course, according to the track flight of expection;

Described engine system, the present speed that reception flight management and guidance system send and height tolerance, utilize the engine throttle control rate designed in advance, calculate and revise fuel flow required for deviation and auto-throttle manipulated variable, manipulated variable data are delivered to engine system, executable operations, make engine change thrust, thus change the flight parameter such as speed, height, reach the airmark of expection;

Described atmosphere data and Inertial Platform System, comprise atmosphere data processing section and inertial platform part, described atmosphere data processing section obtains the dynamic pressure of air, static pressure, stagnation pressure, these basic parameters of atmospheric temperature by sensor, calculates current air basic parameter and barometer altitude, air speed information; Described inertial platform part obtains aircraft acceleration information by three axes accelerometers, is obtained the velocity information of three axles by integration, and integration obtains three dimensional local information again, utilize the air speed information of atmosphere data, calculate current wind speed, utilize air pressure signal, obtain barometric-corrected altitude;

Described central monitoring system, receives from other systematic data, monitors each working state of system and data, once there is data over run and abnormal state, will report to the police with audio frequency and video information, reminds unit to note;

Described control system provides the equipment of unit manual control aircraft, comprise deflecting roller, jociey stick, throttle lever and pedal, control command is directly sent to flight control system, aerofoil steering wheel, engine system by these equipment by unit, taking off, land and traffic adjustment, control order time manually handle, also can manual control aircraft when thrashing, burst are unexpected;

Described instrument system comprises primary flight display, navigation indicator; Described instrument system receives the parameter from atmosphere data and inertia system, flight management and guidance system, flight dynamics system and flight control system, to current flight attitude, speed, grade, Mach number, highly, flight path, navigation information, terrain information, atmosphere data, flight plan data show, check for unit, to understand current state of flight;

Described visual system receive current flight attitude, speed, grade, Mach number, highly, flight path, navigation information, utilize the three dimensional topographic data storehouse carried, aloft virtual three-dimensional scene is provided, comprises dimensional topography, three-dimensional atmospheric environment, airport and terminal area environment, three-dimensional model aircraft; There is provided the acoustics in engine and extraneous physical environment, for unit simulated flight provides 3D vision true to nature and auditory information;

The described mission program design system based on performance navigation comprises three layers: bottom, middle layer and the superiors, wherein: described bottom is the core database layer based on AIXM, and it have collected various database, comprises AIPs and NOTAM;

Described middle layer is SUPERMAP component layer, and it carries out two-way interactive by database engine and bottom;

The described the superiors are application layer;

Described application layer comprises:

1) PBN flight Computer Aided Design application module, the data of its process from this locality and the data of outside central database, carry out two-way interactive by middle layer and database engine; Local data refer to the data that Supermap SDB document form stores;

2) chart application module, and it, according to standard chart template generation chart, carries out two-way interactive by middle layer and database engine;

3) ARINC424 coding exports application module, comprises and encoding to basic data and flying quality; The process of encoding to basic data generates data form sequentially to data to export, and encoding to flying quality, is extract key message, and to key message rearrangement, finally generates data form file in order; Data are sent to ARINC424 coding and export application module by database engine;

4) SUPERMAP DESKPRO browses chart application module or map file, SUPERMAP DESKPRO is utilized to browse chart module, the function of desktop software on maps processing is utilized to process the chart designed, the function that complete design software can not complete; Data are sent to SUPERMAP DESKPRO and browse chart application module or map file by database engine;

5) based on the reporting modules of template and data, its data sent according to database engine, by the template of design, generate report file automatically.

2. verification platform according to claim 1, is characterized in that: whether described PBN flight Computer Aided Design application module self-verifying design meets PBN flight route point sequence rule, and generates nominal flight path and protected location; Simultaneously regularly fragmented storage, is convenient to the Segment evaluation of protected location; Realize the seamless link of RNAV or RNP protected location and conventional I LS protected location; Cultural obstacle and DEM barrier are identified; Automatically march into the arena, leave the theatre, near, non-precision approach is entered in Initial Approach, centre, each stage of ILS-OAS, APV-BARO OAS and visual barrier assessment, provide referential suggestion.

3. verification platform according to claim 2, is characterized in that: described PBN flight Computer Aided Design application module comprises three layers:

(1) display layer and optimum configurations interface: described display layer is used for each design element that visual Layering manifestation PBN flies, and described design element comprises runway, guidance station, protected location; Described optimum configurations interface is used for the parameter graphically arranging design element;

(2) Business Logic: the core layer being this module, it is responsible for carrying out alternately with described display layer and optimum configurations interface, and carries out alternately, completing calling of algorithm with the database of bottom simultaneously;

(3) data storage layer: comprise local profile, local SUPERMAP data source and the central database based on AIXM; Described local profile is undertaken alternately by XML parser and Business Logic; Described local SUPERMAP data source is undertaken alternately by SUPERMAP SDX+ engine and engine and Business Logic; The described central database based on AIXM is undertaken by SQLSERVER database engine and Business Logic alternately.

4. verification platform according to claim 3, is characterized in that:

Described visual system comprises flying quality interface, scheduling memory module, buffer management module, what comes into a driver's cutting module, plays up output module;

The described flying quality interface temporally flying quality that produces of sequential reception analog machine in real time, and the relevant information extracting aircraft is to drive what comes into a driver's;

Described scheduling memory module is according to the scope in the viewpoint position obtained in airplane data interface and the visual field, the scope that calculating need read in internal storage data ensures that the data area in internal memory can meet and plays up needs in following a period of time, and upgrades the data in internal memory according to the change of viewpoint;

The function of described buffer management module is data dispatching, simplified model; When observing viewpoint and roaming in Virtual Terrain scene, according to the scope of viewpoint and look migration to, the interior data that come into view are called in buffer zone by system from internal memory; Described buffer zone comprises Render Buffer and data buffer; Render Buffer refers to according to active user's field range, a visual range of delimiting, and the landform fallen within the scope of this must be played up, and is responsible for the renewal of data buffer by data management system; Described Render Buffer shows as the pointer list of all data cells in current Render Buffer, is responsible for the renewal of buffer zone by scene manager;

Described what comes into a driver's cutting module: the image that screen shows is two-dimentional scenery perpendicular to the projection in the two-dimensional imaging plane of direction of visual lines, must judge the relative position of object and view body before playing up output, then be handled as follows by then described what comes into a driver's cutting module: if to be positioned at view completely external for object, then discard; If object is positioned at view body completely, then it is transformed to screen coordinate system and play up; If object is crossing with view body, then with view body, cutting is carried out to object, then play up the part be positioned within view body;

Describedly play up output module: play up output module and carry out playing up output according to the pointer list of data cells all in current Render Buffer; When viewpoint moves, scene manager is responsible for according to real-time the upgrading unit in Render Buffer of viewpoint parameter, the new unit pointer entering Render Buffer is added pointer list, and delete the pointer that those have shifted out Render Buffer unit, meanwhile, use polling mechanism, whether the data of constantly inquiring in current Render Buffer to scene manager are ready to, as being ready to just to proceed to play up, what realize circulation like this plays up what comes into a driver's.

5. verification platform according to claim 4, is characterized in that:

The scene database of what described visual system adopted is real landform, texture, airport data genaration;

Described visual system adopts single video card and special split screen hardware, described special split screen hardware adopts graphic extension building block technique, being assigned to by one road VGA signal of input is three road signals, and allows Windows 2000/XP operating system, according to suitable ratio, picture signal is outputted to display screen.

6. use the verification platform described in claim 5 to carry out the method verified, it is characterized in that:

Said method comprising the steps of:

(1) typing navigational route database: first by upgrading navigational route database interface, start navigational route database editing system, the information type that flight validation personnel selection will input, the various data that input is corresponding, after input data, generate database, restart verification platform;

(2) arrange flight parameter, carry out ground validation: checking personnel pass through tarmac, parameters, personnel are according to Standard Flight in checking, carry out the various operations of flight cavity;

(3) verify in laggard line space of taking off: checking personnel carry out the various operations of taking off according to the flight of standard;

(4) nearly phase authentication is entered: when aircraft was in into the nearly stage, navigational system is according to predetermined Gradient Descent to the speed designed, and automatic vector aircraft to DH+50 height, is not relied on instrument landing system (ILS) by vertical guidance system, under GPS PRIMARY pattern, realize automatic Landing.