CN202221566U - Flight programming system and verification platform of performance-based navigation - Google Patents

Abstract

The utility model provides a flight programming system and a verification platform of performance-based navigation, which belongs to the field of airborne navigation. The programming system is based on an airborne information exchange model (AIXM) core data base and can automatically draw a program protection area, evaluate obstacles and generate an aeronautical chart, and can obtain a function of seamless connection between a packet based network (PBN) program protection area and a traditional flight program protection area and the like. The system can generate the aeronautical chart automatically according to data completed by the flight programming and can also edit and revise the aeronautical chart according to requirements of clients so as to finish programming and publishing by one time. The PBN program can be directly added in a navigation data base of the verification platform, and the navigation data base can be edited and revised in a verification process. In addition, a view data base is added, during verification of the PBN flight program, the program can be further revised and improved according to defects of terrain landform visual discover programming in view.

Description

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

Technical field

The utility model belongs to the aerial navigation field, is specifically related to a kind of mission program design system and verification platform based on the performance navigation.

Background technology

The high speed development of China's economic has promoted increasing rapidly of civil aviaton's 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.CAAC's total traffic turnover in 2000 is the 9th in the world, and 2003 is the 5th, and 2004 is the 3rd, leaps to the second place of the world in 2005.Keep second position in recent years always, becoming civil aviaton big country.Though Chinese civil aviation transportation entire system is keeping stable development fast, yet the fast development of CAAC also faces lot of challenges, mainly comprises:

(1) special airport is numerous

Special airport is meant that flight environment of vehicle is complicated, the airport guarantee condition is not enough, for guaranteeing flight safety, the airport that need take special counter-measure.China has 38 special airports at present, and 2438 meters (8000 feet) above high high-altitude aerodromes of height above sea level have 8, also have more plateau and complicated airport to build.Receive the influence of landform and geographical conditions, traditional ground navigational facility in these airports and zone is difficult to satisfy the operation needs, and invests hugely, and maintenance cost is high.

(2) the western and eastern's disparate development

Because the imbalance of China's regional economic development, the eastern region has more perfect infrastructure and ground base navigation system, and surveillance radar can be realized multiple covering.But the infrastructure in west area and Land Navigation Installation are built imperfection, and the signal of guidance station and surveillance radar covers not exclusively.Along with western rapid economy development, the construction of west area civil aviation infrastructure faces a severe challenge.

Utilize the signal that receives Land Navigation Installation during the tradition navigation; Through flight realizes the guiding to aircraft with back of the body platform to platform; Its air route and mission program receive the restriction of the layout and the device category of Land Navigation Installation, and precision is limited, and present operation notion and technological means can not address the above problem.Along with the raising of airborne equipment ability and the continuous development of satellite navigation and other advanced technology, International Civil Aviation Organization (ICAO) has proposed " based on the navigation (PBN:Performance Based Navigation) of performance " notion.The introducing of PBN has embodied the navigation mode from navigate to the transformation based on the performance navigation based on sensor.PBN has following advantage than traditional program:

● accurately guide aircraft, improve the 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 flexibly and the flight of optimizing boat footpath increases aircraft already to carry, reduce the flight time, save fuel oil.

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

Using P BN technology is U.S. ALASKA AIRLINES INC. the earliest., the Zhu Nuo airport realized with a varied topography and low weather standard operation after using the PBN program.The U.S. has nearly 10 different airports of complexity to use the PBN program at present, only in the period of the 2003-2004 of ALASKA AIRLINES INC., reduces 603 flights that make a return voyage of making preparation for dropping through statistics, and practice thrift 5,000,000 dollars every year.The airline that is applied as based on the airmanship of performance has brought high safety reliability and huge economic benefit.Except that the U.S., Canada, New Zealand, Australia have also carried out PBN Study on Technology and application in the world.European Union member countries are also in the development of positive regard PBN technology, and are actively promoting the enforcement of these technology in Europe, and PBN one of is supported as the incorporate important technology of European sky.

PBN technology ripe day by day and perfect, for CAAC fast, security developments provides the approach of effectively dealing with problems.International Civil Aviation Organization's the 36th conference resolution is pointed out: " each contracting party should accomplish the PBN implementation plan in 2009, guaranteed before 2016, carried out the transition to the PBN operation with the whole world one coordinated mode of making peace ".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.The PBN of CAAC 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.Carry out the PBN emphasis in the recent period and use, carry out the PBN overall application mid-term, implementation PBN at a specified future date and CNS/ATM system combination.

The complicacy on Lhasa airport lets traditional program run into much to be difficult to the bottleneck that overcomes, and the PBN mission program has ideally solved this problem.The PBN The Application of Technology is that new page has been opened in the development of CAAC.After Lhasa, at present domestic have Tibet Linzhi, Bamda, Ali, and the Lijing in Yunnan, the Zhangjiajie in Hunan, the Mount Huang in Anhui, the airports such as Yanji in Jilin have been implemented the PBN program in succession.The application of PBN program has solved drawbacks such as these Airport Operation standard height with a varied topography, spatial domain complicacy, for airline and airport having brought considerable benefit.But the PBN program of above-mentioned domestic airport operation all is that offshore company designs, and core technology is still grasped in the hand of company abroad.What possess the PBN programming capability at present has only Boeing, Air Passenger company and U.S. Naverus company; Offshore company has also had an optimistic view of the great potential of Chinese market; China is carried out technical blockade; This improves safe operation to CAAC, recommends new technology to use, and it is very unfavorable to rise to power of civil aviaton by civil aviaton big country.

At present, only have France and Italy that the PBN mission program design software of designing and developing is arranged in the worldwide, it comprises:

(1) GITAN (France)

Geotitan mission program design software is institute of French civil aviaton (ENAC) and the CGX of data message company of Air France Group drop into research and development in calendar year 2001 a business software.Software has mainly been set up the aviation topographic database of a cover based on AIXM, and fully integrated ICAO Doc8168-OPS/611 standard realizes automatic drawing protection, assesses barrier automatically, makes functions such as chart and establishment report automatically.

(2) FPDAM software (Italy)

FPDAM is a advanced person's of Italian IDS company exploitation mission program design and an airspace management software.Its principal feature is to design instrument flight procedure with the mode of three-dimensional; And set up a complete aeronautical database platform; The mission program management software that is not merely it provides platform that data are provided; Also support the radar signal analysis, spatial domain program design etc. provides authentic data to guarantee that it provides the interactive environment of program design with traditional navigation information and area navigation notion.

FPDAM is that user job provides following function:

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

● when guaranteeing that interval and MEA/MEL/LSALT confirm, design course line, air route;

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

● conditional spatial domain is defined and revises;

● the spatial domain exists during military training or other the important aerial incident, and the zone that temporary limit is arranged is managed;

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

● the general planning to the airport is analyzed;

● the available offline mode inspection instrument flight procedure that designs.

The domestic system that only is applicable to traditional mission program design and analysis function does not at present also have PBN mission program designed system.

In addition, external aviation flight simulated flight platform comparative maturity and perfect.Become serial application each stage training in the pilot from primary simulator to senior full dynamic simulated machine.But specialized application does not still have commercial platform at home and abroad at present in the platform of program verification.So the full dynamic simulated machine that the checking of current procedure all uses the pilot training to use, this subject matter to the program verification existence are exactly long problem of proving period time, because program coding is made by FMS navigational route database company; The fabrication cycle of FMS navigational route database is 28 days; If checking back discovery procedure has problem to need to revise, need wait until that then next fabrication cycle just can revise, more than a PBN program design is accomplished and generally needed to revise twice or thrice; Every modification once need wait 28 days and revise navigational route database; It is many more to revise number of times, and it is many more to expend the cycle, and the time is oversize.Also exist simultaneously and use the costly difficulty of full dynamic simulated machine checking.

Simultaneously, the analog machine difference in version that is used for the PBN program verification abroad is big, and the leap time is long; Not the analog machine scene database that whole analog machines all have the airport of verifying, the what comes into a driver's that the analog machine that when the PBN program verification, has can the Installation Validation airport, but can not installing of having; When on the analog machine that checking airport what comes into a driver's has been installed, verifying, the alarm in a single day of EGWPS topographic database can directly be pinpointed the problems according to the airport what comes into a driver's in the proof procedure; Program is made amendment; And the analog machine that lacks the what comes into a driver's data need be furtherd investigate discussion to the problem that occurs when the landform alarm occurring, and multiple authentication flies to confirm reason.

The utility model content

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

The utility model is realized through following technical scheme:

A kind of based on performance navigation PBN mission program design system, said system comprises three layers: bottom, middle layer and the superiors, wherein:

Said bottom is the core database layer based on AIXM, and it has collected various databases, comprises AIPs and NOTAM;

Said middle layer is the SUPERMAP component layer, and it carries out two-way interactive through database engine and bottom;

The said the superiors are application layer;

Said application layer comprises:

1) PBN mission program Aided Design application module, it handles data and outer center data of database from this locality, carries out two-way interactive through middle layer and database engine; Local data are meant the data of Supermap SDB document form storage;

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

3) ARINC424 coding output application module comprises basic data and mission program data is encoded; The process that basic data is encoded is that data are generated data form output sequentially, and it then is to extract key message that the mission program data are encoded, and to the key message rearrangement, generates the data form file at last in order; Database engine sends data to ARINC424 coding output application module;

This module provides three partial functions: A, according to the preceding pre-service of encoding of the part basic data in the mission program scheme file and mission program; B, provide the user to pre-service after content edit once more; C derives design automatic coding function.

4) SUPERMAP DESKPRO (desktop software of hypergraph company) browses chart application module or map file; Utilize SUPERMAP DESKPRO to browse the chart module; Utilize the function of desktop software on map treatment that the chart that designs is processed, accomplish the function that program development software can not be accomplished;

Database engine sends data to SUPERMAP DESKPRO and browses chart application module or map file;

5) based on the reporting modules of template and data, the data that it sends according to database engine by designing template, generate report file automatically.

Whether said PBN mission program Aided Design application module self-verifying design meets PBN mission program way point sequence rules, and generates nominal flight path and protected location; By regular fragmented storage, be convenient to the segmentation assessment of protected location simultaneously; Realize the seamless link of RNAV or RNP protected location and conventional I LS protected location; Cultural obstacle and DEM barrier are discerned; Automatically march into the arena, leave the theatre, Initial Approach, centre advance near, non-precision approach, ILS-OAS, each stage of APV-BARO OAS and visual barrier assessment, provide with reference to the property suggestion.

Said PBN mission program Aided Design application module comprises three layers:

(1) display layer and parameter are provided with the interface: said display layer is used for each program design element that visual layering shows the design of PBN mission program, and said program design element comprises runway, guidance station, protected location; Said parameter is provided with the interface and is used for graphical setting program design element parameters needed;

(2) Business Logic: be the core layer of this module, it is responsible for said display layer and parameter the interface being set and carries out alternately, and carries out accomplishing calling of algorithm simultaneously alternately with the database of bottom;

(3) data storage layer: comprise local profile, local SUPERMAP data source and based on the central database of AIXM; Said local profile carries out alternately through XML resolver and Business Logic; Said local SUPERMAP data source is carried out alternately through SUPERMAP SDX+ engine and engine and Business Logic; Said central database based on AIXM carries out through SQLSERVER database engine and Business Logic alternately.

A kind of verification platform of verifying based on the mission program design system of performance navigation said of being used for, said 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; Said engine system comprises fuel system;

Said flight dynamics system comprises pneumatic coefficient module and equation of motion module; Said pneumatic coefficient module be rise under the various conditions of aircraft, the set of resistance and moment coefficient, in computation process, obtain the various pneumatic coefficient values of aircraft this moment through inquiry in real time.It is through aircraft rudder surface, the flap configuration of reception control system, and relevant flight parameter, utilizes the pneumatic coefficient of these parameter queries, utilizes pneumatic coefficient calculations aerodynamic force and moment again, and result of calculation is transported to equation of motion module;

Said equation of motion module receives the aerodynamic force of pneumatic coefficient module and thrust magnitude, fuel weight and center of gravity of airplane position and the normal atmosphere data of moment and engine system; Utilize these conditions and aircraft initial value; Resolve the non-linear full dose equation of motion of aircraft six degree of freedom, obtain attitude, speed, grade, position and other flight parameter of aircraft, and these parameters are fed back to the pneumatic system module again; Again inquiry is obtained go forward side by side promoting the circulation of qi power and aerodynamic moment of pneumatic coefficient and is calculated; Pass to equation of motion module again, the repetition aforementioned calculation of going round and beginning again process realizes flight dynamics calculating;

Said flight management and guidance system self have navigational route database, aircraft performance database and aerodynamic data and engine data storehouse, realize flight management and flight guiding two parts function; Said flight management part, through man-machine interface input take off initial parameter and leave the theatre and march into the arena, the approach flight program so that aircraft is left the theatre, is landed by this mission program;

Said flight leader receives the information that aircraft dynamics system and flight control system transmit, with the flight planning comparison in the database; Calculate current speed, course and course error, pass to flight control system and engine system again, realize control speed, course and course-line deviation; Afterwards; Aircraft dynamics system and flight control system feed back to flight management and guidance system with the fresh information that calculates again, calculation deviation and controlling once more, and the repetition said process goes round and begins again; Accomplish navigation procedure, make aircraft by the expection track flight.Simultaneously, flight management and guidance system calculate the precision and the positional precision of navigation sources, and when precision is undesirable, report to the police;

Said flight control system; Receive current flight path and course deviation that flight management and guidance system send, utilize the control rate of design in advance, calculate needed aircraft rudder surface of deviation and the flap control amount revised; The manipulated variable data transfer is arrived the aerofoil steering wheel; Executable operations makes aircraft change attitude and course, according to the track flight of expection;

Said engine system receives present speed and height tolerance that flight management and guidance system send, utilizes the engine throttle control rate of design in advance; Calculate and revise needed fuel flow of deviation and auto-throttle manipulated variable; To engine system, executable operations makes engine change thrust with the manipulated variable data transfer; Thereby flight parameters such as change speed, height reach the airmark of expection;

Said atmosphere data and Inertial Platform System; Comprise atmosphere data processing section and inertial platform part; Current atmosphere basic parameter and barometer altitude, air speed information are calculated through dynamic pressure, static pressure, stagnation pressure, these basic parameters of atmospheric temperature of sensor acquisition atmosphere in said atmosphere data processing section; Said inertial platform part obtains the aircraft acceleration information through three axial acceleration meters, obtains three velocity information through integration, and integration obtains three dimensional local information once more; Utilize the air speed information of atmosphere data; Calculate current wind speed, utilize air pressure signal, obtain barometric-corrected altitude;

Said central monitoring system receives the data from other all systems, and each working state of system and data are monitored, in case occur that data transfinite and abnormal state, will report to the police with audio frequency and video information, and the prompting unit is noted;

Said control system provides the equipment of unit manual control aircraft; Comprise deflecting roller, jociey stick, throttle lever and pedal; Unit directly sends to flight control system, aerofoil steering wheel, engine system with control command through these equipment; Take off, manual work is handled when the adjustment of landing and traffic, control order, thrashing, also can the manual control aircraft when burst is unexpected;

Said instrument system comprises primary flight display, navigation indicator; Said 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; The confession unit is checked, to understand present state of flight;

Said visual system receive current flight attitude, speed, grade, Mach number, highly, flight path, navigation information; The dimensional topography database that utilization carries; Aloft virtual three-dimensional scene is provided, comprises dimensional topography, three-dimensional atmospheric environment, airport terminal district environment, three-dimensional model aircraft; Acoustics in engine and the extraneous physical environment is provided, for the unit simulated flight provides 3D vision and auditory information true to nature.

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

The flying quality that said flying quality interface produces by time sequential reception analog machine in real time, and the relevant information of extraction aircraft drives what comes into a driver's;

Said scheduling memory module is according to the scope in the viewpoint position that obtains in the airplane data interface and the visual field; The scope that calculating need be read in internal storage data guarantees that the data area in the internal memory can satisfy the needs of playing up in following a period of time, and according to the data in the variation updating memory of viewpoint;

The function of said buffer management module is data dispatching, simplified model; When observing viewpoint when in virtual landform scene, roaming, according to the scope of viewpoint with look migration to, the data in system will come into view are called in buffer zone from internal memory; Said buffer zone comprises plays up buffer zone and data buffer; Play up buffer zone and refer to field range according to the active user, a visual range of being delimited, the landform that falls in this scope must be played up, and is responsible for the renewal of data buffer by data management system; The said buffer zone of playing up shows as the current pointer list of playing up all data cells in the buffer zone, is responsible for the renewal of buffer zone by the scene management device; Because the scheduling of data need spend the regular hour, therefore, need be before data block comes into view, those possibly get into the data block in the visual field very soon to need forward scheduling;

Said what comes into a driver's cutting module: images displayed is two-dimentional scenery perpendicular to the projection on the two-dimensional imaging plane of direction of visual lines on the screen; Must judge the relative position of object and view body before playing up output; Handle as follows by said what comes into a driver's cutting module then then: external if object is positioned at view fully, then discard; If object is positioned at the view body fully, then transforms to screen coordinate system to it and play up; If object and view body intersect, then object is carried out cutting with the view body, play up then and be positioned at that part of within the view body;

The said output module of playing up: play up output module and play up output according to the current pointer list of all data cells of playing up in the buffer zone; When viewpoint moves, the scene management device be responsible for according to viewpoint parameter real-time each unit upgrades in the buffer zone to playing up, the unit pointer of new entering being played up buffer zone adds pointer list; And delete those and shifted out the pointer of playing up buffer location; Simultaneously, use polling mechanism, constantly whether be ready to the current data of playing up in the buffer zone of scene management device inquiry; As be ready to just proceed to play up, realize that like this round-robin plays up what comes into a driver's.

What said visual system adopted is the scene database of real landform, texture, the generation of airport data;

Said visual system adopts single video card and special-purpose split screen hardware; Said special-purpose split screen hardware using figure expansion module technology; To being three road signals, and let Windows 2000/XP operating system picture signal outputed to display screen one road VGA signal allocation of input according to suitable ratio.

Compared with prior art, the beneficial effect of the utility model is:

(1) created the aeronautical data interaction models first, this model can effectively provide basic data for program design with airport, three-dimensional data landform, barrier data and the automatic hinge of navigational intelligence data together.

(2) realized the design of PBN Automatic Program.The utility model can according to regulations and the standard of ICAO and FAA, be assessed barrier automatically according to the basic data in the aeronautical data storehouse, the route that advances to leave the theatre of choosing optimum of intelligence, and can generate the navigational intelligence document fast.Improved the efficient of program design greatly.

(3) mission program navigational route database integrity verification.FPCAD can according to the software format data demand, accomplish the process integrity checking automatically to the mission program of having accomplished.Mainly comprise the whether compliant requirement etc. of way point, program height, leg, a kind of means of check are provided for the safety of flight.

(4) the PBN program only needs on the program verification platform of the utility model, to carry out flight validation; 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, can directly add the PBN program in the navigational route database of verification platform, can edit and revise navigational route database in the proof procedure; Modification of program need not wait 28 day cycle, and the real time modifying navigational route database can be verified once more.After modification of program is improved, submit to FMS navigational route database company (Smith company and Honeywell company) again and accomplish coding, paying airline can put into operation.

Description of drawings

Fig. 1 is the block architecture diagram of the utility model based on performance navigation PBN mission program design system.

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

Fig. 3 is the block architecture diagram of the verification platform of the utility model.

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

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

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

Fig. 7 is the displayed map of assessment result on map of Fig. 6.

Fig. 8 is that the utility model generates the interface automatically based on the chart in the performance navigation PBN mission program design system.

Fig. 9 is the construction module figure of the visual system in the utility model.

Embodiment

Below in conjunction with accompanying drawing the utility model is described in further detail:

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

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

AIPs, NOTAM and other data have been collected;

In the mission program design, can relate to such as the airport guidance station; How mass data such as mission program, barrier realizes that these data are beneficial to preservation, check, are a major issue alternately, to this problem; The utility model adopts international airline exchanges data model AIXM to set up database; Integrate the aeronautical data resource, realize unified management aviation information, for the PBN program design with verification system provides accurately, reliable data support.

Real guidance station, related datas such as course line, airport, landform are the bases that guarantees mission program planning, assessment drawing, coding.Adopt the independent database service mechanism, could guarantee safety of data, reduce data redudancy, the validity of data management and the reliability of data are to realize the key of the utility model.Employing is based on AIXM (aviation information exchange model) model creation database; Adopt data-centered operational mode; From data acquisition; Program design program verification to the end all is to be produced by unique data source, reduces mistake and error that data occur in transmittance process, guarantees program quality.

The purpose of AIXM modelling is through satisfying ICAO annex 15 described data demands to aviation field, supports the AIS demand data.Along with the application of Area navigation (RNAV), required navigation performance (RNP) and airborne computer navigational system, great change has taken place in the role and the importance of aeronautical data/information.The damage of aviation information or wrong to navigation safety formation potential threat.In order to satisfy required unitarity and the compatible requirement of navigational information in providing of airborne computer navigational system operation, contracting party should avoid adopting international standard and the program of using outside the regulation as far as possible.

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

2, the middle layer is SUPERMAP component layer (being SUPERMAP OBJECT among Fig. 1)

Carry out two-way interactive through database engine and bottom;

3, the superiors are application layer

Wherein, Application layer comprise PBN mission program Aided Design application module, drawing application module, ARINC424 coding output application module, SUPERMAP DESKPRO browse the chart application module, based on reporting modules and traditional mission program design application module of template and data, specific as follows:

1) PBN mission program Aided Design application module is handled data and outer center data of database from this locality, integrates the service logics such as mission program, protected location, assessment of complicacy, and is mutual through SUPERMAP OBJECT and system bidirectional; Whether the self-verifying design meets PBN mission program way point sequence rules, and generates nominal flight path and protected location.By regular fragmented storage, be convenient to the segmentation assessment of protected location simultaneously, realize the seamless link of RNAV/RNP protected location and conventional I LS protected location etc.To cultural obstacle and the identification of DEM barrier; Automatically march into the arena, leave the theatre, Initial Approach, centre advance near, non-precision approach, ILS-OAS, APV-BARO OAS, etc. each stage and visual barrier assessment; Provide with reference to the property suggestion, programming efficiency improves than manual work greatly.

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

(1) display layer and parameter are provided with the interface

(2) Business Logic: be the core layer of this module, be responsible for the interface being set and carry out alternately, and carry out accomplishing calling of algorithm simultaneously alternately with the data of three kinds of separate sources of bottom with display layer and parameter.

(3) data storage layer

Comprise local profile, local SUPERMAP data source and based on the central database of AIXM.Mission program store three kinds; Generally when design, get business datum from SQLSEVER earlier, import configuration data from the XML file; Design is preserved three types of data after accomplishing again; Preserve the XML configuration file in this locality, local SUPERMAP (SDX among Fig. 2 is a database engine) data source, the server data end is kept in the SQLSEVER.Database engine among Fig. 1 has comprised SQLSEVER database engine and SUPERMAP SDX+ engine among Fig. 2 etc.

2) the drawing application module promptly generates chart according to standard chart template, carries out two-way interactive through SUPERMAP OBJECT and database engine;

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

The purpose of coding is for digital coding company can mission program deviser's theory be expressed accurately like (Corinth, Honeywell etc.) in the mission program design.Just reaching digital coding company with reference to ARINC424 standard design can recognition coding, reaches the versatility of coding, how to guarantee that accuracy, the reliability of encoding are the focuses that we pay close attention to.PBN mission program design software can be automatically converted to the ARINC424 coding with the mission program that designs accurately; Simultaneously analog machine can its coding of Direct Recognition; Automatically transform to be loaded in the navigational route database and verify, pinpoint the problems, make amendment from the mission program design software; Program design and checking personnel do not participate in the direct modification to coded data, reduce the error that manually-operated brings.

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

The ARINC424 authority data also is a prerequisite of implementing aviation new standard and new technology.See that from whole CAAC what lack is not the navigational intelligence navigation data, do not form navigation data but press cannonical format.The navigation data of current CAAC is only applicable to the product of domestic publication and distribution, for example: and NAIP, Flight Information compilation, AIP, enroute chart etc., and can not be generalized in world's application apparatus or the software.Especially domestic not open navigation data part can't be generalized in the middle of the foreign system of the current use of domestic operator, and for example, the use of empty company of domestic three key airline companies is by the SOC system of U.S.'s exploitation, the FMC that is mainly provided by external production firm etc.And the ARINC424 authority data optimal path expanded of navigation data just.Only combine the actual conditions of present CA to see, ordered JEPPESEN " whole world " data (ARINC424 authority data) do not comprise domestic externally not open navigation data, and these data just are one of the most used navigation datas of domestic operator.The utility model can generate the ARINC424 authority data of domestic navigation data, and the domestic part of replacement or additional JEPPESEN " whole world " data realizes complete worldwide navigation database, supplies domestic operator to use.

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

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

6) traditional mission program design application module, this application module dots and on the basis of this framework, expands the back adding in the future, with the database engine one-way interaction.

Because what bottom adopted is the database that the aviation information exchange model is set up, so application layer has very strong extensibility.This framework is the center with the independent database, and application extension is convenient to resources such as data and application are integrated utilization for guiding.

The utility model realized following function based on performance navigation PBN mission program design system:

A, the mission program design:

After selecting way point, navigational facility and navigation specification that the utility model is selected according to mission program advance automatic data processings such as nearly type, aircraft type, and be specific as follows:

● whether the inspection way point meets PBN mission program way point sequence rules;

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

● the shortest stabilizing distance when self-verifying calculate to change, and whether inspection meets the constraint rule of short stabilizing distance;

● generate the nominal flight path automatically.

According to ICAO OPANS 8168 DOC, the utility model has been accomplished mission program commonly used, marches into the arena, and leaves the theatre, and waits for ILS, and RNAV " T " or " Y " program design.

B, drawing protection automatically

Maximum workload is drawing protection in the mission program design, but drawing process is a process of revising adjustment repeatedly, lean on craft or CAD not only can consume a large amount of energy of designer merely, and inaccurate being easy to is made mistakes.In the utility model, with reference to ICAO PAN-OPS 8168 and FAA standard, utilize geographical information platform, adopt the automatic drawing protection of parameterized mode, alleviated programmer's workload, guarantee the quality of mission program.

The utility model provides parametrization, and connection procedure is drawn in intelligentized protected location, and the complicated service logical process is become simply, has improved work efficiency greatly.Be mainly reflected in following several aspect;

1, the generation of straight line protected location;

2, the segmentation assessment of protected location is convenient in the generation of turning protected location, and fragmented storage;

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

4, the conversion between the protected location only need be regulated the parameter of other way point, for example, meets DF after MAP is turned and after MAP is turned, meets TF, and the more following flight path termination that only needs to change MAP yard gets final product.

5, the prompting of the intellectuality in the generative process of protected location.If the parameter that is provided with does not meet the rule that generates the protected location, software provides information and advisory information immediately.

Protected location paint type in the utility model is mainly as shown in table 1, and the protected location figure that generates automatically is as shown in Figure 4.

Sequence number	The protected location type	The corresponding programme section
			1	Meet DF after leaping turning (Fly-Over)	The mission program section is turned
2	Fly-by turns (Fly-By)	The mission program section is turned
			3	The specified altitude assignment of leaving the theatre meets DF after turning	The turning of leaving the theatre
4	The specified altitude assignment of going around is turned	The turning of going around
			5	, MAP meets DF after turning	The turning of going around
6	Specify semidiameter turn (RF)	The mission program section is turned
			7	Meet TF after leaping turning (Fly-OVER)	The mission program section is turned

8	The specified altitude assignment of leaving the theatre meets CF after turning	The mission program section is turned
			9	, MAP meets TF after turning	The mission program section is turned
10	, MAP meets CF after turning	The mission program section is turned
			11	ILS	The most laggard near
12	ILS	Go around
			13	RNP waits for	Wait for
14	APV?I/II?procedures-GBAS	The most laggard near
			15	APV?I/II?procedures-GBAS	Go around

Table 1

C, the barrier assessment

An important step of mission program design is exactly the barrier assessment, directly concerns the success or failure of program, concerns flight safety.Source by barrier mainly is divided into two types, i.e. cultural obstacle and from the data (like electronics altitude figures DEM) of electronic chart, and the electronic map data amount is big; Such as; Usually it is individual to reach hundreds of thousands for the location point on the electronic chart of APV-BARO VNAV program, and many like this data processing are difficulty relatively, the parameter that the utility model calculates automatically or obtains according to the parameter and the system of user's input; According to mission program barrier Rules of Assessment, realize barrier assessment robotization.

The utility model can be to RNAV; The RNP standard program carries out carrying out the identification of cultural obstacle and DEM barrier, visual and non-visual ultra barrier analyzed and the barrier assessment according to ICAO annex, CAAC regulations; Accurately draw ultra barrier face in barrier place and the high parameter of ultra barrier at last; Provide with reference to the property suggestion, hand over assessment result on the two-dimension GIS map, to show simultaneously.Barrier assessment kind comprises:

● the assessment of APV-BARO VNAV barrier, like Fig. 5, Fig. 6 and shown in Figure 7;

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

● the assessment of ILS-OAS barrier;

● non-precision approach barrier assessment;

● the assessment of Initial Approach section barrier;

● near section barrier assessment advanced in the centre.

D, the utility model is used aviation information exchange model (AIXM) standard, and the ARINC424 coded format is adopted in output, so partial data can be shared with flight simulator, and intercourse, is used to set up airport scene database, flying quality etc.The data of sharing comprise:

● electronic map data

● the mission program data

● airport, runway data

● the location point data

● the barrier data

E, the standard chart generates robotization

One of net result of mission program design is exactly to issue chart, generates the chart electronic stencil of production standardization importantly that meets international standard or China's standard automatically, utilizes data in the SUPERMAP data source to add then and fills template, generates the standard chart.Only need to revise some areas wherein,, promptly become the chart that to issue like the adjustment labeling position.

The utility model generates chart according to standard chart template, and is as shown in Figure 8.Mainly contain and generate following several kinds of charts:

● RNAV Standard Approach figure

● RNP Standard Approach figure

● the RNAV standard figure that leaves the theatre

● RNAV instrument approach figure

● RNP instrument approach figure

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

A, the visual edit function based on business rule comprises:

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

● according to the sequence of all types of way points of program, the operation through drawing and mouse is added forward, is added backward, middlely operation such as adds, deletes, removes the way point of program;

B based on the auxiliary editting function of the automatic verification of business rule, comprising:

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

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

● judge the feasibility that flight path is turned automatically;

● calculate the radii fixus that feedback RF turns automatically;

● discern the leg type automatically through way point type and some preface;

● obtain the indicated airspeed that ICAO stipulates, the gradient, data such as reaction time automatically according to the leg type;

C, the mission program interface editing function based on parameter comprises:

● can confirm the drawing program type through the selection of the Program Type that advances to leave the theatre;

● can confirm near mode through the selection of advancing nearly type;

● the mission program analysis designing institute that can confirm ICAO regulations such as XTT, ATT, half-breadth through the selection of navigational facility, navigation specification and aircraft type is used parameter;

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

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

● support TF, DF turns;

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

The utility model satisfied ICAO and China civil aviaton operation demand based on performance navigation PBN mission program design system to the PBN program; Broken the monopoly position of external procedure service provider in this field; Develop PBN mission program software first at home; Lay important basis for CAAC carries forward vigorously the PBN mission program, indispensable means are provided, the PBN program of designing is being guaranteed flight safety; It is significant to improve the operational efficiency aspect, and remarkable economical and social benefit are arranged.

Based on performance Navigator verification platform:

The PBN mission program need carry out simulated flight and verify reliability, the integrality that guarantees to design the program after the completion after design is accomplished, and carries out the real checking of taking a flight test then.The method of conventional analogue flight validation is to give navigational route database manufacturing company (companies such as thalous, honeywell) with the program that designs to be made into the navigational route database of once upgrading in per 28 days, utilizes full dynamic simulated machine (FFS) or solid model (FTD) to load navigational route database then and carries out the simulated flight checking.This verification method all need be waited for the renewal of navigational route database in each program design or after upgrading, cause the cycle of mission program design long, and efficient is low, can't satisfy the demand of domestic a large amount of RNP program design, is unfavorable for the design and the popularization of RNP program.In order to improve the efficient of checking, sooner, better the RNP mission program is verified that the utility model has designed the verification platform that can efficiently, accurately verify the RNP mission program---based on performance Navigator verification platform.

As shown in Figure 3, said 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.

Said flight dynamics system comprises pneumatic coefficient module and equation of motion module; Said pneumatic coefficient module be rise under the various conditions of aircraft, the set of resistance and moment coefficient, in computation process, obtain the various pneumatic coefficient values of aircraft this moment through inquiry in real time.It is through receiving aircraft rudder surface, the flap configuration of control system; And undercarriage position; With relevant flight parameters such as flying speed, Mach number, grade, attitudes; Utilize the pneumatic coefficient of these parameter queries, utilize pneumatic coefficient calculations aerodynamic force and moment again, and result of calculation is transported to equation of motion module.

Said equation of motion module receives the aerodynamic force of pneumatic coefficient module and thrust magnitude, fuel weight and center of gravity of airplane position and the normal atmosphere data of moment and engine system; Utilize these conditions and aircraft initial value; Resolve the non-linear full dose equation of motion of aircraft six degree of freedom, obtain attitude, speed, grade, position and other flight parameter of aircraft, and these parameters are fed back to the pneumatic system module again; Again inquiry is obtained go forward side by side promoting the circulation of qi power and aerodynamic moment of pneumatic coefficient and is calculated; Pass to equation of motion module again, the repetition aforementioned calculation of going round and beginning again process realizes flight dynamics calculating.

Flight management and guidance system (FMGS) self have navigational route database, aircraft performance database and aerodynamic data and engine data storehouse, realize flight management and flight guiding two parts function.Realize navigation management (calculating of inertia, satellite and ground base navigation signal, selection automatically), flight planning, performance prediction and optimization and drive management, flight director instruction, auto-throttle instruction automatically.In the flight management part, can through man-machine interface (MCDU) input take off initial parameter and leave the theatre and march into the arena, the approach flight program so that aircraft is left the theatre, is landed by this mission program.

The flight leader of FMGS, information such as the position that reception aircraft dynamics module and flight control system transmit, speed are with the flight planning comparison in the database; Calculate current speed, course and course error, pass to flight control and engine system again, realize control speed, course and course-line deviation; Afterwards; Information feedback such as the new position that dynamics module and flight control system will calculate again, speed are given FMGS, calculation deviation and controlling once more, and the repetition said process goes round and begins again; Accomplish navigation procedure, make aircraft by the expection track flight.Simultaneously, it can also calculate the precision and the positional precision of navigation sources, and when precision is undesirable, reports to the police.

Flight control system; Receive current flight path, course deviation that flight management and guidance system send, utilize the control rate of design in advance, calculate needed aircraft rudder surface of deviation and the flap control amount revised; The manipulated variable data transfer is arrived the aerofoil steering wheel; Executable operations makes aircraft change attitude and course, according to the track flight of expection.

Engine system (comprising fuel system), receive present speed, the height tolerance that flight management and guidance system send equally; Utilize the engine throttle control rate of design in advance, calculate and revise needed fuel flow of deviation and auto-throttle manipulated variable, with the manipulated variable data transfer to engine system; Executable operations; Make engine change thrust, thereby flight parameters such as change speed, height reach the airmark of expection.

In atmosphere data (ADC) and the Inertial Platform System (IRS), the atmospheric treatment machine partly obtains the basic parameters such as dynamic pressure, static pressure, stagnation pressure, atmospheric temperature of atmosphere through sensor, calculate current atmosphere basic parameter, and information such as barometer altitude, air speed.Simultaneously; The inertial platform part obtains the aircraft acceleration information through three axial acceleration meters, obtains three velocity information through integration, and integration obtains three dimensional local information once more; Utilize the air speed information of atmosphere data; Can calculate current wind speed, utilize air pressure signal, obtain barometric-corrected altitude.

Central monitoring system (ECAM); Reception is from the data of 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; In case occur that data transfinite and abnormal state, will report to the police with audio frequency and video information, remind unit to note.

Control system; The equipment of unit manual control aircraft is provided; Comprise deflecting roller, jociey stick, throttle lever and pedal, unit directly sends to flight control system, aerofoil steering wheel, engine system etc. with control command through these equipment, has played the function of override flight management system; Take off, manual work is handled when the adjustment of landing and traffic, control order, thrashing, also can the manual control aircraft when burst is unexpected.

Instrument system mainly comprises primary flight display, navigation indicator etc.Reception is from the parameter of 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, data such as flight path, navigation information, terrain information, atmosphere data, flight planning show; The confession unit is checked, understands present state of flight.

Visual system; Same receive current flight attitude, speed, grade, Mach number, highly, information such as flight path, navigation; The dimensional topography database that utilization carries; Aloft virtual three-dimensional scene is provided, comprises dimensional topography, three-dimensional atmospheric environment, airport terminal district environment, three-dimensional model aircraft etc., the acoustics in engine and the extraneous physical environment also is provided; For the unit simulated flight provides 3D vision and auditory information true to nature, flight environment of vehicle has stronger infiltration sense.

This system possesses the function of reproduction airflight environment, can take off to the pilot, lands, climbs, turning, maneuvering flight simulation, 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, navigational system model, flight management system model etc., and the various logic control relation between model is consistent with true aircraft.The function of each subsystem of aircraft and performance simulation are accurately, can move, operating personnel can with their the same these systems of operating on true aircraft.

For the better checking of accomplishing mission program, the true environment of better simulated flight proof procedure, the flight course that reduction is actual is necessary for and verifies that flight provides what comes into a driver's.The flight what comes into a driver's is the important component part of flight validation system, can be the program verification personnel lasting, stable visual landform reference is provided, and is the actual position that advances closely to provide runway of flight.Such as, whether the height of last several anchor points can land decisive role smoothly to aircraft in program design.After program design was accomplished, through what comes into a driver's and combine the performance of aircraft to verify flight, whether the setting of height that can the last anchor point of extraordinary judgement was reasonable, feasible.Can be the program personnel in addition barrier and terrain information are provided, can experience design whether reasonable, the compliant of the ultra barrier of flight and the protected location of aircraft intuitively through the flight what comes into a driver's.

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

The flying quality interface: real-time flying quality that produces by time sequential reception analog machine and the relevant informations such as six degree of freedom parameter of extracting aircraft drive what comes into a driver's.

The scheduling memory module: because the magnanimity characteristic of airport visual system terrain data, and the restriction of Flame Image Process hardware condition, be difficult in disposable all data that are written into of landform scene establishment stage.In native system, the scheduling memory module can be controlled the scope of required rendering image in real time according to the scope in the viewpoint position that obtains in the airplane data interface and the visual field, and the data of correspondence are read in internal memory.

The buffer management module: the function of this module is data dispatching, simplified model.When observing viewpoint when in virtual landform scene, roaming, according to the scope of viewpoint with look migration to prediction, the data in system will come into view are called in buffer zone from database; Said buffer zone comprises plays up buffer zone and to the data buffer zone.When observing viewpoint when in virtual landform scene, roaming, according to the scope of viewpoint, the data that get into viewpoint must be played up, simultaneously since data call in and modeling needs a process, according to prediction to viewpoint roaming trend.System also need call in data and carry out modeling for those interior pieces that will come into view from database.In order to address this problem, set up for current view point and to have played up buffer zone and data buffer, be responsible for playing up and dispatching of data respectively.

Play up buffer zone and data buffer.Play up buffer zone and refer to field range according to the active user, with and the roaming mode that adopts, a visual range of being delimited, the landform that falls in this scope must be played up, otherwise the user will see an incomplete scene.Play up the size of buffer zone and the viewpoint parameter that shape not only need be considered the user,, also need consider the current roaming mode that adopts like distance, visual angle etc.Can set up fan-shaped buffer zone for the flight roaming, fan-shaped radius is relevant with the length of sighting distance, and fan-shaped angle is then decided by the visual angle.The radius of buffer zone is mainly determined by pilot's sighting distance.

Because the scheduling of data need spend the regular hour, therefore, need be before data block comes into view, those possibly get into the data block in the visual field very soon to need forward scheduling.Through setting up the data buffer around the buffer zone playing up, can before data are played up, call in potential visible data, and then carry out modeling and play up.The delimitation of the scope of data buffer also need be carried out based on the roaming mode that the active user adopted with to play up buffer zone the same.

The data management of buffer zone and playing up.When real time roaming, each frame all need be judged each unit of playing up in buffer zone and the data buffer before playing up, to confirm data that current needs are played up and the data that from secondary storage, are written into as required.Here use data management system and scene management device to come to be responsible for respectively the scheduling of data and playing up of scene.In the scene manager, be responsible for the information such as position, direction and roam speed of current view point are followed the tracks of, confirm to play up the scope of buffer zone and data buffer with this, and safeguard that a sensing plays up the pointer of buffer zone.Play up buffer zone and show as the current pointer list of playing up all data cells in the buffer zone; When viewpoint moves; The scene management device be responsible for according to viewpoint parameter real-time each unit upgrades in the buffer zone to playing up, the unit pointer of new entering being played up buffer zone adds pointer list.And delete those and shifted out the pointer of playing up buffer location.Simultaneously, a kind of " poll " mechanism is used in the scene rendering management.Constantly whether be ready to the current data of playing up in the buffer zone of data management system inquiry; Under the situation reasonable in design of data buffer; The data of buffer zone are played up in those entering should be ready, i.e. this inquiry should always obtain sure answer mad.The scene management device is played up the data block of playing up in the buffer zone after obtaining affirmation.

The management of data mainly is responsible for by data management system in the buffer zone, in data management system, safeguards the information of secondary storage database and a list of pointers friend of current data buffer zone simultaneously.Data management system is called in the data of each resolution according to the sequencing of data block entering data buffer from the digital elevation model database of backstage.Simultaneously, request is confirmed in the scheduling that from the scene management device, receives data, and sends corresponding confirmation to the scene management device.

Data dispatch, the multithreading realization of simplifying and playing up.Data are called in from database, modeling is simplified and even play up the certain process of needs.Simultaneously, the real-time virtual scene requires scene played up and roam the continuity that must can keep the scene demonstration.Therefore, desirable state is that the scheduling and the playing up of scene of data can be carried out simultaneously, keeps the continuity of data between scheduling and demonstration.In the large-scale virtual environment of multi-CPU architecture, can scene be carried out piecemeal according to the zone on the screen, each piecemeal uses an independent CPU to carry out modeling and display process, and a plurality of CPU parallel computations obtain the real-time virtual image of whole scene.This is a kind of horizontal parallel processing algorithm, is adapted at the reality environment of setting up on the computer network platform of concentrating type.And on the microcomputer of uniprocessor, then can realize based on the multithreading support of system.Here, the scene management device of the data management system of being responsible for data dispatch and simplification and responsible scene rendering is placed on the realization of asking of two threads respectively, the scheduling through the event notice coordination data between the thread and playing up.

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

In eye coordinates system, the relation of given object and view can be divided into following several types:

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

● object is positioned at the view body fully, transforms to it screen coordinate system and plays up.

● object and view body intersect, and need carry out cutting to object with the view body, play up then to be positioned at that part of within the view body.

Judge the relation of an object and view body, confirm that promptly this object whether in current what comes into a driver's, at first will confirm the equation on six cutting planes of view, the distance between computing object and each cutting plane is judged by these distances then.

Play up output module: play up buffer zone and show as the current pointer list of playing up all data cells in the buffer zone; When viewpoint moves; The scene management device be responsible for according to viewpoint parameter real-time each unit upgrades in the buffer zone to playing up, the unit pointer of new entering being played up buffer zone adds pointer list.And delete those and shifted out the pointer of playing up buffer location.Simultaneously, a kind of " poll " mechanism is used in the scene rendering management.Constantly whether be ready to, then the data block of playing up in the buffer zone played up to the current data of playing up in the buffer zone of data management system inquiry.

The manufacturing process of said what comes into a driver's is: data processing, visual fusion, the modeling of flight scene database, flight simulation visual system and show based on the flight simulation what comes into a driver's of microcomputer; First three part is the process that the what comes into a driver's Data Processing is generated the what comes into a driver's data, and back two parts are playing up of image and show.Original photo, landform, vector data etc. generate scene database at last through this processing, play up through microcomputer and generate the flight what comes into a driver's.

The scene database that visual system adopts real landform, texture, airport data to generate;

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

The airport image comprises near landform, the landforms the airport, cultural traits, the runway in the airport and taxiway and terminal etc.;

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

What comes into a driver's image and aerodynamic program design coupling, and the accurate ambient image relevant with attitude is provided.

The visual system of the utility model has adopted the solution based on the hardware of PC and TV screen, the requirement of considered frame speed in the selection of PC graphic display card and select the high-performance video card for use.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-purpose split screen hardware.Special-purpose split screen hardware using figure expansion module (GXM) technology, to being three road signals, and let Windows 2000/XP operating system picture signal outputed to display screen one road VGA signal allocation of input according to suitable ratio.The concrete configuration environment is following:

1)CPU：AMD?Athlon(tm)64?X2?Dual?Core?Processor?3800+；

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

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

To be that the visual system of core is integrated with the flight validation system that is core mutually with flight management guiding analogue system with the vision rendering system; Set up both sides' communications protocol; Realize flying quality; The communication of control data and visual system makes the demonstration of visual system accurately corresponding relevant with the flight operation of aircraft.

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

Verification system and visual system are combined, and the core of design is from the seasonal effect in time series flying quality, to extract relevant information, drives scene database.And be the six degree of freedom parameter of aircraft: with respect to the three dimensional space coordinate of airport and landform with respect to three attitude angle (head, roll, pitch) of body as the main information in the flying quality of key.Through the information of these 6 parameters, state of flight that just can unique definite a certain moment of aircraft, program real-time 6DOF information is presented on the screen in the function design.

The verification platform of the utility model has been realized following function:

1; The emulation of flight management guidance system (FMGS): FMGS receives the input that comes from air data computer, inertial reference system, navigational route database, Mult1purpose Coutrols (MCDU) and flight control assembly systems such as (FCU), shows that (PFD), navigation show that (ND) and duty control desk provide signal for after treatment automatic driving, auto-throttle, main flight.The navigational route database that FMGS can use user oneself to provide.The flight management guidance system is exactly a Flight Management Computer System in itself, and it is a multiple processor system, comprises navigation processing machine, performance processor and I/O processor three parts.Numerical data transmits and adopts the ARINC-429 form.Through analysis to related datas such as aeroplane characteristic handbook, flight airmanships; Framework goes out the flow chart of flight management guidance system; Realization is to the emulation of FMGS; Wherein navigation processing machine module receive atmospheric parameter from the air data computer module input, take off location parameter, inertial reference system input best guidance station apart from the direction parameter of direction parameter and radio navigation system etc.; Through optimizing these data, calculate aircraft current location and flight parameter, and output to related systems such as autoflight system, EFIS then; The performance processor module is then determined the optimum flight profile, mission profile under a certain performance index according to current atmospheric conditions.

1) emulation of Mult1purpose Coutrols (MCDU): MCDU is the vitals that FMGS gets into people/machine dialogue; Realize calculating air route and performance parameter to the required flight of Flight Management Computer (FMC) input through imitation multi-functional control display module (MCDU), it provides packing into of true, accurate and complete flight planning and shows.Through utilizing the graph processing technique of real-time simulation technology, network communications technology and computing machine; The involved various key issues such as data transmission, electronic page generation and tissue, page switching, fault handling and real time execution of MCDU have been solved; Realized emulation to MCDU; And adopt touch-screen to drive simulating keyboard as input media, accomplished the input function of the assortment of keys of MCDU.

2) realization of flight (Auto Flight) automatically: according to the composition and the function of aircraft autoflight system; Whole autoflight system is divided into interface module, logic module, pitch control subsystem rate module, roll control rate module, yawdamper module and engine system module six major parts; The interface input quantity that the main emulation autoflight system of interface module is important, and adopt the collection of main iteration speed and monitor the variation of these input signals; Logic module receives from switching value, sign amount and autoflight system pitching, roll control module, auto-throttle module, Flight Management Computer and the relevant subsystem module of interface module current various quantity of states and sign amount; Mode of operation under various connection logics of emulation autoflight system and the various flying method; And attitude guides appearance, autopilot operation and these sign amounts transported to flying method annunciator (FMA) go up and show, also delivers to flight control assembly (FCU) simultaneously and goes up and drive corresponding pilot lamp and caution signal; Pitch control subsystem rate modular simulation flight director sys tem and autopilot system pitch control subsystem return circuit; The attitude of completion under pitching mode all working pattern guided the appearance control rate; Calculate and generate the command signal and the emulation robot pilot control rate that drive attitude guide appearance pitch demand bar, generate the command signal that drives elevating rudder; Roll control rate modular simulation flight director sys tem and autopilot system roll control loop function, the control rate of accomplishing under the various mode of operations is calculated, and generates roll command bar drive signal and aileron drift angle control command signal; Yawdamper modular simulation flight control system yawdamper function; When the pitching of autoflight system engage the autopilot, when the roll passage is worked, yawdamper must be connected, and receives the calibrated airspeed of aircraft yaw rate signal, air data computer output; Calculate the yaw rudder steering order; Reach the stability that goes as course, the vibration that the damping Dutch roll causes provides functions such as coordinate turn; Engine system modular simulation auto-throttle control system function may operate under the mode of operation of coordinating with the pitching flying method, obtains and keeps required throttle lever position.The message exchange of each intermodule realizes that through local public data area the message exchange between autoflight system and other subsystems is through overall public data area transmission in the autoflight system.

3) emulation of flight control assembly (FCU): the driver is provided with automatic driving and auto-throttle through FCU; And through FCU can the preliminary election height, the input information of FMGS such as speed/Mach number, course, flight path, these parameters are reference datas that pitching, roll, control law are calculated.

4) emulation of EFIS (EFIS): flying instruments is aeroplane performance parameter and navigational parameter window displayed, to the pilot visual information in the passenger cabin is provided.We adopt computer real-time graph image technology on terminal, to generate digital graphical meter; On the extra-sight of these emulating instruments, indicating mode and the function all with true aircraft on instrument consistent; Flight parameter, navigational parameter, electrical system parameter, engine parameter etc. are shown in real time and offer the driver, satisfy the needs of flight training.Realizing the function of Electronic Flight Instrument symbol generator, is that main flight shows that (PFD) and navigation show that (ND) provides symbol output.The Electronic Flight Instrument symbol generator is handled the input information that comes from each subsystem of aircraft and parts, produces formative by the employed signal of EFIS (EFIS).

2, do not realize all relevant flight section purpose training under the situation in kind having

Utilize split screen display card, serial card, touch-screen to realize operation, realize all relevant flight section purpose training under the situation in kind not having.

3, accomplished the development of following simulation hardware, make the pilot in environment more true to nature, to train:

1) simulation hardware of accomplishing side lever, throttle lever and turning handwheel is developed;

2) simulation hardware of accomplishing flight control assembly FCU is developed;

3) simulation hardware of accomplishing Mult1purpose Coutrols MCDU is developed.

4, visual system has following technological breakthrough:

1) the Using geographic information system technology is handled landform vector data and dem data, merges the real terrain data of calibration back reduction, guarantees virtual emulation environment availability, reliability.

2) collection of texture and treatment technology utilize remote sensing image preconditioning technique (geometric correction, radiation correcting, information strengthen), texture integration technology, handle multiple image data, make texture can keep more information, make what comes into a driver's more approach real flight environment of vehicle.

3) constructing technology of three-dimensional model is set up the 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, 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 that validity is high, can render the scene of approaching the Live Flying environment; Adopt that case technology, external reference technology, texture are technological, level of detail (LOD), child node technology etc. have carried out optimization process to model.Improve the efficient that scene database moves in the what comes into a driver's real-time rendering system based on PC.

The method of using verification platform to verify may further comprise the steps:

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

(2) flight parameter is set, carries out ground validation: the checking personnel are provided with parameter through tarmac, and the checking personnel carry out the various operations of flight cavity according to the standard mission program;

(3) take off and verify in the laggard line space: the various operations that the checking personnel take off according to the mission program of standard;

(4) advance the checking of nearly stage: when aircraft is in near stage; Navigational system drops to the speed of program design according to predetermined gradient, and the vertical guidance system with automatic vector aircraft to DH+50 does not highly rely on instrument landing system (ILS); Under GPS PRIMARY pattern, realize landing automatically.

The mission program design system and the verification platform of the utility model have following innovation:

1, must fly automatically with the WGS84 coordinate input aircraft navigation database of encoding to the PBN mission program; And China's topomap all is Beijing 1954 coordinate systems; Map reference and program coordinate system mismatch problem; The utility model adopts GIS-Geographic Information System to carry out conceptual design, realizes the mutual conversion of WGS84 coordinate system and Beijing 1954 coordinate systems, has solved the problem that goes up design PBN mission program (WGS84 coordinate) coordinate and precision at China's topomap (Beijing 1954 coordinates).

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

3, to after the mission program completion design; Need repaint chart according to Program path and publish, workload is big, easy error; Revise the problem of length consuming time back and forth; This system can generate chart automatically according to the data that the mission program design is accomplished, and also can and revise according to demand customization editor, accomplishes program design, publishes once and accomplish.

4, use the problem that full dynamic simulated machine cost is high, the navigational route database fabrication cycle is long to external PBN program verification; The program verification platform of the utility model does not need FMS navigational route database company to make coding at the checking initial stage; Can directly add the PBN program in the navigational route database of verification platform; Can edit and revise navigational route database in the proof procedure, modification of program need not wait 28 day cycle, and the real time modifying navigational route database can be verified once more.After modification of program was improved, net result was submitted to FMS navigational route database company (Smith company and Honeywell company) and is accomplished coding, and paying airline can put into operation.

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

In a word, the utility model can be in the program design working environment disposable completion program design, coding, checking and iteration optimization process thereof.Improved the application level of China's navigation new technology greatly in the civil aviation field.

The utility model can be applicable to:

Airline

1) accurately guides aircraft, improve the security of operation

Compare with traditional mission program, the precision navigation of PBN can fly along favourable landform by vector aircraft, and the easy degree of the predictability of its flight path, accuracy and operation all is far superior to traditional program.As: in service at high-altitude aerodrome, the aircraft true air speed is big, and maneuverability is poor, and speedup is slow with deceleration, and flight operation is obviously blunt than Plain airport.In addition, the easy anoxic of highlands pilot, reaction capacity descends, and psychological pressure is big.The track and the requirement for height of PBN program are clear and definite, and basic dependence automatically flown, and pilot's main task is the monitoring state of flight, and operational load reduces greatly.In addition, PBN advances closely generally to take the mode that descends continuously (Continue Descend Approach CDA), reduces the most laggard near downward gradient of aircraft, and the pilot controls throttle and Speed of Approach easily, has improved and has advanced near stability.

2) increasing airline already carries

The tradition mission program considers that the scope of barrier is bigger, and the take-off climb or the gradient of going around are had relatively high expectations.At high-altitude aerodrome, airline often has to satisfy the aeroplane performance requirement through reducing already to carry.Use the PBN technology, then can make full use of lineament, dwindle the barrier scope, reduce the 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, the flight time is shortened in the flight boat footpath of realizing optimization flexibly, saves fuel oil, evades the noise sensitizing range, and the minimizing discharging improves Environmental Protection Level.

4) program design takes into full account the flight emergency measure

The concrete property (like navigation performance, aerodynamic quality etc.) of some aircraft is not considered in the design of tradition mission program, does not consider special circumstances (like power failure, guidance station dropout etc.) yet.The RNP program then is airborne equipment ability and the aeroplane performance according to institute's aircraft type; And considered various special circumstances, for example: take off, advance power failure near and the process of going around, lose navigation signal (losing efficacy) like GPS; Autoflight system lost efficacy, flight management system inefficacy etc.Also formulate the corresponding prediction scheme of disposing on this basis, assess and analyze the general safety level to all special circumstances.

5) give full play to the airborne homing capability of aircraft

The RNP program makes full use of the airborne equipment of aircraft, and the ability of performance aircraft is to improve the security and the economy of operation.Compare with traditional instrument approach procedure, IAP and departure procedure, the RNP operation has very remarkable advantages, and is particularly suitable for receiving the airport and the zone of restrictions such as landform, flight facilities and spatial domain.

Blank pipe

1) level and longitudinal separation between aircraft improve the service efficiency in spatial domain, increase airspace capacity; Because the PBN technology is used the notion of degree of containing; Required spatial domain is less, so just might in limited spatial domain scope, arrange more course line, reduces the lateral separation between the course line.Because the accuracy of PBN navigation can realize the design of course line " viaduct " formula of into leaving the theatre, thereby make the separation of into leaving the theatre, and avoids the course line to converge, and alleviates controller's burden, under the premise that security is guaranteed, promotes airspace capacity effectively.

2) reduce controller's working load

The tradition mission program needs controller and pilot frequently to converse; Carry out the flight path guiding, the PBN program has existed in the aircraft FMS navigational route database, and flight path is accurate; Can realize that aircraft flies automatically; Be convenient to commander, reduce controller and pilot's empty voice communication in land and radar vectoring demand, reduce working load;

The airport

1) normality of improvement Airport Operation

China's high-altitude aerodrome is owing to limited by landform, and Airport Operation weather standard is higher.Wherein, basically all to require be visual flight to the actual motion of most of high high-altitude aerodromes.The airport is subject to weather effect, and operation normality is low.Use the PBN program, because flight path precise control property is high, the protected location that needs is little, can reduce the take-off and landing standard, thereby reduces the influence of weather to flight, has improved the normality of Airport Operation.

2) reduce investment outlay expense and operating cost

PBN technology is main uses satellite navigation, and precision height, good reliability, operating cost are low, can reduce the dependence to flight facilities, save build, expenses such as on duty, maintenance and verification, the day-to-day operation cost on reduction airport.In addition, PBN also can reduce the obstacle free airspace treatment requirement, has to utilize protection ring border and the earthwork disposal cost that reduces airport construction.

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

System succeeds in developing the implementation plan according to the PBN of CAAC Implementation Roadmap for China civil aviaton; The important techniques guarantee is provided; The development of system has been successfully applied to the PBN operation on Guyuan airport, proves that the mission program that is designed can be used for actual motion.Air China has signed the PBN mission program cooperation agreement on 25 airports with peace skill center, quicken application and development that the PBN mission program operates in China.

Domestic operator will participate in the international airline competition comprehensively; The international development process of airline; And airline faces increasing cost pressure, the automatic flight that the PBN mission program that needs to use the native system design to accomplish is realized flexibly, optimized, and the increase aircraft already carries; Reduce the flight time, save fuel oil; Avoid the noise sensitizing range, improve Environmental Protection Level.

Along with the fast development of CAAC, the spatial domain resource is nervous, causes air traffic to be blocked up, and the operation on some airports is near state of saturation, and existing operation notion and technological means can not satisfy the demand that the magnitude of traffic flow increases fast fully.The PBN mission program that utilizes native system to accomplish can be implemented parallel air route and increase the air route anchor point that advances, leaves the theatre in the termination environment, improves 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 controller and pilot's working load.

Technique scheme is a kind of embodiment of the utility model; For those skilled in the art; On the basis that the utility model discloses application process and principle, be easy to make various types of improvement or distortion, and be not limited only to the described method of the above-mentioned embodiment of the utility model; Therefore the mode of front description is just preferred, and does not have restrictive meaning.

Claims (3)

1. verification platform to verifying based on the mission program design system of performance navigation is characterized in that:

Said 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; Said engine system comprises fuel system;

Said flight dynamics system comprises pneumatic coefficient module and equation of motion module; Said pneumatic coefficient module be rise under the various conditions of aircraft, the set of resistance and moment coefficient, in computation process, obtain the various pneumatic coefficient values of aircraft this moment through inquiry in real time; It is through aircraft rudder surface, the flap configuration of reception control system, and relevant flight parameter, utilizes the pneumatic coefficient of these parameter queries, utilizes pneumatic coefficient calculations aerodynamic force and moment again, and result of calculation is transported to equation of motion module;

Said equation of motion module receives the aerodynamic force of pneumatic coefficient module and thrust magnitude, fuel weight and center of gravity of airplane position and the normal atmosphere data of moment and engine system; Utilize these conditions and aircraft initial value; Resolve the non-linear full dose equation of motion of aircraft six degree of freedom, obtain attitude, speed, grade, position and other flight parameter of aircraft, and these parameters are fed back to the pneumatic system module again; Again inquiry is obtained go forward side by side promoting the circulation of qi power and aerodynamic moment of pneumatic coefficient and is calculated; Pass to equation of motion module again, the repetition aforementioned calculation of going round and beginning again process realizes flight dynamics calculating;

Said flight management and guidance system self have navigational route database, aircraft performance database and aerodynamic data and engine data storehouse, realize flight management and flight guiding two parts function; Said flight management part, through man-machine interface input take off initial parameter and leave the theatre and march into the arena, the approach flight program so that aircraft is left the theatre, is landed by this mission program;

Said flight leader receives the information that aircraft dynamics system and flight control system transmit, with the flight planning comparison in the database; Calculate current speed, course and course error, pass to flight control system and engine system again, realize control speed, course and course-line deviation; Afterwards; Aircraft dynamics system and flight control system feed back to flight management and guidance system with the fresh information that calculates again, calculation deviation and controlling once more, and the repetition said process goes round and begins again; Accomplish navigation procedure, make aircraft by the expection track flight.Simultaneously, flight management and guidance system calculate the precision and the positional precision of navigation sources, and when precision is undesirable, report to the police;

Said flight control system; Receive current flight path and course deviation that flight management and guidance system send, utilize the control rate of design in advance, calculate needed aircraft rudder surface of deviation and the flap control amount revised; The manipulated variable data transfer is arrived the aerofoil steering wheel; Executable operations makes aircraft change attitude and course, according to the track flight of expection;

Said engine system receives present speed and height tolerance that flight management and guidance system send, utilizes the engine throttle control rate of design in advance; Calculate and revise needed fuel flow of deviation and auto-throttle manipulated variable; To engine system, executable operations makes engine change thrust with the manipulated variable data transfer; Thereby flight parameters such as change speed, height reach the airmark of expection;

Said atmosphere data and Inertial Platform System; Comprise atmosphere data processing section and inertial platform part; Current atmosphere basic parameter and barometer altitude, air speed information are calculated through dynamic pressure, static pressure, stagnation pressure, these basic parameters of atmospheric temperature of sensor acquisition atmosphere in said atmosphere data processing section; Said inertial platform part obtains the aircraft acceleration information through three axial acceleration meters, obtains three velocity information through integration, and integration obtains three dimensional local information once more; Utilize the air speed information of atmosphere data; Calculate current wind speed, utilize air pressure signal, obtain barometric-corrected altitude;

Said central monitoring system receives the data from other all systems, and each working state of system and data are monitored, in case occur that data transfinite and abnormal state, will report to the police with audio frequency and video information, and the prompting unit is noted;

Said control system provides the equipment of unit manual control aircraft; Comprise deflecting roller, jociey stick, throttle lever and pedal; Unit directly sends to flight control system, aerofoil steering wheel, engine system with control command through these equipment; Take off, manual work is handled when the adjustment of landing and traffic, control order, thrashing, also can the manual control aircraft when burst is unexpected;

Said instrument system comprises primary flight display, navigation indicator; Said 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; The confession unit is checked, to understand present state of flight;

Said visual system receive current flight attitude, speed, grade, Mach number, highly, flight path, navigation information; The dimensional topography database that utilization carries; Aloft virtual three-dimensional scene is provided, comprises dimensional topography, three-dimensional atmospheric environment, airport terminal district environment, three-dimensional model aircraft; Acoustics in engine and the extraneous physical environment is provided, for the unit simulated flight provides 3D vision and auditory information true to nature.

2. verification platform according to claim 1 is characterized in that:

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

The flying quality that said flying quality interface produces by time sequential reception analog machine in real time, and the relevant information of extraction aircraft drives what comes into a driver's;

Said scheduling memory module is according to the scope in the viewpoint position that obtains in the airplane data interface and the visual field; The scope that calculating need be read in internal storage data guarantees that the data area in the internal memory can satisfy the needs of playing up in following a period of time, and according to the data in the variation updating memory of viewpoint;

The function of said buffer management module is data dispatching, simplified model; When observing viewpoint when in virtual landform scene, roaming, according to the scope of viewpoint with look migration to, the data in system will come into view are called in buffer zone from internal memory; Said buffer zone comprises plays up buffer zone and data buffer; Play up buffer zone and refer to field range according to the active user, a visual range of being delimited, the landform that falls in this scope must be played up, and is responsible for the renewal of data buffer by data management system; The said buffer zone of playing up shows as the current pointer list of playing up all data cells in the buffer zone, is responsible for the renewal of buffer zone by the scene management device;

Said what comes into a driver's cutting module: images displayed is two-dimentional scenery perpendicular to the projection on the two-dimensional imaging plane of direction of visual lines on the screen; Must judge the relative position of object and view body before playing up output; Handle as follows by said what comes into a driver's cutting module then then: external if object is positioned at view fully, then discard; If object is positioned at the view body fully, then transforms to screen coordinate system to it and play up; If object and view body intersect, then object is carried out cutting with the view body, play up then and be positioned at that part of within the view body;

The said output module of playing up: play up output module and play up output according to the current pointer list of all data cells of playing up in the buffer zone; When viewpoint moves, the scene management device be responsible for according to viewpoint parameter real-time each unit upgrades in the buffer zone to playing up, the unit pointer of new entering being played up buffer zone adds pointer list; And delete those and shifted out the pointer of playing up buffer location; Simultaneously, use polling mechanism, constantly whether be ready to the current data of playing up in the buffer zone of scene management device inquiry; As be ready to just proceed to play up, realize that like this round-robin plays up what comes into a driver's.

3. verification platform according to claim 2 is characterized in that:

Said visual system adopts single video card and special-purpose split screen hardware.

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