CN108196141A - A kind of avionics system flexibility test platform and avionics integrated verification method - Google Patents
A kind of avionics system flexibility test platform and avionics integrated verification method Download PDFInfo
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- CN108196141A CN108196141A CN201711075534.0A CN201711075534A CN108196141A CN 108196141 A CN108196141 A CN 108196141A CN 201711075534 A CN201711075534 A CN 201711075534A CN 108196141 A CN108196141 A CN 108196141A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/005—Testing of electric installations on transport means
- G01R31/008—Testing of electric installations on transport means on air- or spacecraft, railway rolling stock or sea-going vessels
Abstract
It is integrated the invention discloses a kind of avionics system, verification method and flexibility test platform, integrated approach：The increment type system integration on Math, verification method：Exciter response formula is verified and dynamic comprehensive verification；Flexibility test platform includes：Turn-key system (101), avionics simulation system (102), configuration intelligence control system (109), turntable (114), dynamoelectric signal simulation system (103), true part cabinet system (108), air excitation system (113), data collecting system (104), virtual cockpit/test stand cabin system (108), electromechanical MIniRIG (112), radio excitation system (111), visual system (105), flight Simulation System (106) and power-supply system (110).Using the present invention, large-scale avionics system can be solved and integrated and validation problem, integrated efficiency is improved, reduce manpower and time cost, improve and verify comprehensive and accuracy, realize the experiment of intelligent automation.
Description
Technical field
The present invention relates to airplane avionics system ground experiment fields more particularly to a kind of avionics system flexibility test to put down
Platform and avionics integrated verification method.
Background technology
Modern aircraft avionics system come into high modularization, synthesization epoch, between each system crosslinking and cooperation close
System is complicated, and participation design, integrated, joint debugging and the personnel of test and unit are more, and technical difficulty and complexity are all very high.Therefore have
The integrated verification method of necessity further investigation avionics system, establishes advanced efficient test platform, to develop avionics system service.
Aspect is integrated in avionics system, it is necessary to using the method for science, to reduce complexity, be improved integrated efficiency, be avoided
It is unnecessary to be iteratively repeated.In terms of avionics system verification, summation function to be needed to describe document according to system, to each avionics point
Whether system and total system are fully examined, accomplished in the various functions requirement of design phase with verification, really
The avionics system finally delivered is protected with initial design to be consistent.
Previous avionics system integrated verification platform mainly include experiment cockpit, a series of emulators of discrete, driver,
Collector and equipment desktop Lian Shitai compositions.There are following features：Equipment is numerous, and information integration degree is low, and control discreteization is serious, no
It can realize Comprehensive Control, the testing crew of needs is more when carrying out large-scale experiment, and concertedness is not strong, and the transformation of avionics network configuration is leaned on
Hand-guided switch or plug-in connector are completed, and intelligent control is realized without the distributing system of intelligence, meanwhile, power-supply system control
Also long-range can not be realized, it is intelligent；Integrated method mostly by the way of direct joint-trial, concentrate by the problem of leading to integrating process
It breaks out in the later stage, rework rate is very high, and risk is larger；In addition, the method for verification is also relatively simple, it is impossible to carry out dynamic comprehensive and test
Card, can not centralized Control, can not comprehensive assessment avionics system function whether meet design requirement.
Invention content
The object of the present invention is to propose a kind of avionics system flexibility test platform and integrated verification method, can solve to navigate
Empty electronic system integrates and validation problem, can drop the complexity of integrated verification significantly, improves accuracy and safety, effectively
Improve test efficiency.
In view of the above problem of the prior art, according to one side disclosed by the invention, the present invention uses following technology
Scheme：
A kind of avionics system flexibility test platform, including：Turn-key system 101, avionics simulation system 102, configuration are intelligently controlled
System 109 processed, turntable 114, dynamoelectric signal simulation system 103, true part cabinet system 108, air excitation system 113, data acquisition
System 104, virtual cockpit/test stand cabin system 107, electromechanics MiniRIG112, radio excitation system 111, visual system
105th, flight Simulation System 106 and power-supply system 110；
Wherein, turn-key system 101 by Ethernet communicably respectively with flight Simulation System 106, visual system 105,
Power-supply system 110, radio excitation system 111, electromechanics MiniRIG112, air excitation system 113, turntable 114, configuration intelligence
Control system 109, avionics simulation system 102, dynamoelectric signal simulation system 103, data collecting system 104 connect, turn-key system
Control, management instruction and state reporting information are completed by Ethernet to transmit；
Flight Simulation System 106 is communicably connect by Ethernet with virtual cockpit/test stand cabin system 107, transmission
Flight parameter, area navigation parameter, aircraft possessed system parameter message：
Virtual cockpit/test stand cabin system 107 by avionics network communicable is connect with true part cabinet system 108, is completed
Instrument display function, and transmit the control information to equipment in true part cabinet system 108：
Power-supply system 110 by supply line respectively to true part cabinet system 108, virtual cockpit/test stand cabin system 107,
Turntable 114 is powered；
Power-supply system 110 is communicably connect by Ethernet with configuration intelligence control system 109, realizes long-range intelligence
Distribution；
Radio excitation system 111 is connect by radio-frequency cable with true part cabinet system 108, is transmitted radio communication navigation and is penetrated
Frequency signal；
Electromechanical MiniRIG112 is connect by avionics network with true part cabinet system 108, transmits aircraft utilities system bus letter
Breath；
Air excitation system 113 is connect by air source pipeline with true part cabinet system 108, air source information is transmitted, for true part cabinet
Air data computer in system 108 resolves；
Turntable 114 is connect by avionics network with configuration intelligence control system 109, transmits inertial navigation, navigation attitude bus data；
Avionics simulation system 102 is connect by avionics bus with configuration intelligence control system 109, is completed avionics network and is cut
It changes；
Dynamoelectric signal simulation system 103 is connect by avionics bus with configuration intelligence control system 109, is completed electromechanical related
Avionics network switching；
Dynamoelectric signal simulation system 103 is connect by avionics network with true part cabinet system 108, transmits aircraft utilities system mould
Intend signal；
Data collecting system 104 is connect by avionics bus with configuration intelligence control system 109, acquires avionics network number
According to；
True part cabinet system 108 by avionics network respectively with configuration intelligence control system 109, virtual cockpit/experiment cockpit
System 107 connects, inside carrying avionics system real equipment；
Virtual cockpit/test stand cabin system 107 is connect by avionics bus with configuration intelligence control system 109；
True part cabinet system 108 and virtual cockpit/test stand cabin system 107 together constitute the avionics system for participating in experiment.
The method integrated using above-mentioned avionics system flexibility test platform progress avionics system, is included the following steps：
1) full digital trigger technique, the reasonability of verification avionics system design；
Avionics simulation system 102 provides inertial navigation emulation part 10201, display processor emulation part 10202, hair and participates in electromechanical ginseng
Number processor emulation part 10203, air data computer emulation part 10204, ultrashort wave radio set emulation part 10205, short-wave radio set
Emulate part 10206, GPS emulation part 10207, comprehensive radio navigation simulation part 10208, radio altimeter emulation part 10209,
Weather radar emulation part 10210, center alert Computer Simulation part 10211, fly ginseng record system emulation part 10212, aerial friendship
Logical anti-collision system emulation part 10213, ground proximity warning system emulation part 10214, range finder emulation part 10215 and telecompass are imitated
True part 10216 forms digital avionics system and carries out emulation testing.
2) the true part of device level replaces emulation part, completes device level and integrates；
It is replaced successively using the single Aerial Electronic Equipment that virtual cockpit/test stand cabin system 107 and true part cabinet system 108 include
Emulation part corresponding to avionics simulation system 102.
3) the true part of subsystem grade replaces emulation part, completes subsystem grade and integrates；
The division principle of avionics system aircraft possessed avionics subsystem is pressed successively, virtual cockpit/test stand cabin system 107
Subsystem is formed with the multiple equipment that true part cabinet system 108 includes, substitutes the emulation part corresponding to avionics simulation system 102.
4) system-level true part replaces emulation part, is finally completed system-level integrated.
After completing subsystem grade and integrating, virtual cockpit/test stand cabin system 107 and true part cabinet system 108 are included
All devices access avionics experimental network, disconnect all emulation parts of avionics simulation system 102, complete system-level formula, with
It completes system-level integrated.
The method that avionics system verification is carried out using above-mentioned avionics system flexibility test platform, is included the following steps：
1) Challenge-response formula is verified；
2) dynamic comprehensive is verified.
It is characterized in that, the Challenge-response formula verification includes the following steps：
1.1) excitation of the setting to individual equipment in avionics system and/or avionics system；
The excitation includes：Tester is in the operation of cockpit, the signal specific from bus interface, from other aircrafts
The alarm signal of system.
1.2) acquisition measures the response of equipment in avionics system and/or avionics system；
1.3) whether the comparison response and the intended response set in turn-key system 101 are consistent, to verify avionics system
And/or whether the corresponding function of equipment is verified in avionics system；
1.4) turn-key system 101 generates the report of Challenge-response formula verification.
It is characterized in that, the intended response described in step 1.3) is according to equipment in avionics system and/or avionics system
Functional requirement describe document obtain its it is described excitation operating mode under response, described in step 1.2) response can cause to be
The variation of certain operations or picture or the output of distinctive signal of system generate special alarm audio or a series of chain reaction.
It is characterized in that, the dynamic comprehensive verification includes the following steps：
2.1) simulation model is established according to the feature of avionics system aircraft possessed；
2.2) fight environment simulation model is established according to navigational route database, atmospheric environment, Traffic Environment, gravitational field；
2.3) identical flight plan is set respectively in avionics system and flight Simulation System 106；
2.4) operating procedure 2.1) and 2.2) in establish simulation model；
2.5) flight parameter and aircraft system parameter sharing provided flight Simulation System 106 swashs to turntable 114, air
System 113, radio excitation system 111, dynamoelectric signal simulation system 103, electromechanics MiniRIG112 are encouraged to complete tested avionics
The dynamic exciting of system；
2.6) turntable 114, air excitation system 113, radio excitation system 111, dynamoelectric signal simulation system 103, machine
Corresponding Aerial Electronic Equipment in electric MiniRIG112 excitations avionics system；
2.7) dynamic response of dynamic acquisition and observation avionics system, it is fixed in document to be described with the functional requirement of avionics system
The avionics system operation characteristic of justice compares, and whether the function of avionics system and performance, which meet, when performing aerial mission so as to verify sets
Meter requirement.
Advantageous effect：
The flexibility test platform of the present invention, it can be ensured that the integrated verification method is preferably implemented, and reduces integrated difficulty
Degree and complexity improve integrated efficiency, ensure the correctness and integrality of avionics verification, preferably support grinding for avionics system
System.The advantages of using multiple step format incremental integration method：Integrated focus is gradually transferred to entirety by device level demand each time
Sexual function demand；Entire integrating process fully expose different levels the problem of, it is ensured that final overall system integration it is smooth complete
Into so as to reduce the complexity of overall system integration.The specific aim of Challenge-response formula verification method is very strong, meets very much avionics
The verification demand of system action logic.Dynamic comprehensive verification can situation of the ground validation avionics system in practical flight task,
The efficiency of examination avionics system can be integrated.
Description of the drawings
Fig. 1 is the architecture principle figure of flexibility test platform of the present invention；
Fig. 2 is avionics system integrated approach of the present invention；
Fig. 3 is Challenge-response formula verification method of the present invention；
Fig. 4 is dynamic comprehensive verification method of the present invention；
Fig. 5 is the avionics simulation system schematic diagram of flexibility test platform of the present invention；
Fig. 6 is the dynamoelectric signal simulation system schematic diagram of flexibility test platform of the present invention；
Fig. 7 is the true part cabinet system schematic of flexibility test platform of the present invention；
Fig. 8 is virtual cockpit/test stand cabin system schematic diagram of flexibility test platform of the present invention；
Fig. 9 is the electromechanical MiniRIG schematic diagrames of flexibility test platform of the present invention, and MiniRIG is driver and experiment
The experiment subsystem of part composition；
Figure 10 is the radio excitation system schematic diagram of flexibility test platform of the present invention；
Figure 11 is the visual system schematic diagram of flexibility test platform of the present invention；
Figure 12 is the flight Simulation System schematic diagram of flexibility test platform of the present invention；
Figure 13 is the power-supply system schematic diagram of flexibility test platform of the present invention.
Specific embodiment
The present invention is described in further detail, but the implementation of the present invention is not limited to this with reference to embodiment.
As shown in attached drawing 1, the avionics system flexibility test platform, including turn-key system 101, avionics simulation system 102,
Configuration intelligence control system 109, turntable 114, dynamoelectric signal simulation system 103, true part cabinet system 108, air excitation system
113rd, data collecting system 104, virtual cockpit/test stand cabin system 107, electromechanics MiniRIG112, radio excitation system
111st, visual system 105, flight Simulation System 106 and power-supply system 110.
Turn-key system 101 by Ethernet communicably respectively with flight Simulation System 106, visual system 105, power supply system
System 110, radio excitation system 111, electromechanics MiniRIG112, air excitation system 113, turntable 114, configuration intelligent control system
System 109, avionics simulation system 102, dynamoelectric signal simulation system 103, data collecting system 104 connect.
Turn-key system is completed following control, management instruction and state reporting information by Ethernet and is transmitted：
Initialization, flight plan to flight simulation create, navigational route database loading, topographic database loading, hand in the air
The control and management of the functions such as logical environment setting, flight profile, mission profile setting, offline mode control, fault simulation；
Flight simulation flight parameter and operating status return；
The controls such as initialization, view angle switch of visual system management instructs；
Visual system health status is returned；
Power-supply system distribution instructs and state reporting；
The setting of the communication radio station excitation parameters, navigation system excitation parameters of radio excitation system；
The return such as health status, the working condition of radio excitation system；
The excitation control of electromechanical MiniRIG, output monitoring, health monitoring；
Stagnation pressure, static pressure, total temperature equal excitation parameter and the working condition return of air data system；
Three axial excitation parameter settings and the working condition return of turntable；
The avionics such as A429, RS422 and discrete magnitude of configuration intelligence control system bus wiring instructs, wiring work state；
The distribution instruction of configuration intelligence control system and power supply state；
True/imitative part state instruction of configuration intelligence control system and resource health monitoring；
Simulation model setting, startup, stopping and the status information of avionics simulation system；
The electromechanical parameters setting of dynamoelectric signal simulation system and status information；
Acquisition, storage, monitoring and the playback controls of data collecting system.
Flight Simulation System 106 is communicably connect by Ethernet with virtual cockpit/test stand cabin system 107, transmission
Following information：
The navigation station such as voll, range finder, Non Direction Beason, marker beacon, instrument landing needed for radio excitation system
Information；
Air traffic Anticollision information, radio altitude information, GPS position information, aircraft needed for radio excitation system
Radio communication frequency information, meteorological radar sounding target information；
Fuel oil parameter, engine parameter, undercarriage parameter, manipulated parameter needed for dynamoelectric signal simulation system etc.；
The flight parameters information such as visual system desired position, height, speed；
Aircraft system information needed for electromechanical MiniRIG；
The information such as pressure altitude, air speed, lifting speed, temperature needed for air excitation system；
The information such as pitching, roll, course needed for turntable.
Virtual cockpit/test stand cabin system 107 by avionics network communicable is connect with true part cabinet system 108, is passed through
The following information of avionics network prevailing transmission：
Weather radar video information, air traffic anti-collision system video etc.；
The control panels information such as Distal promoter, weather radar, air traffic anticollision；
Audio-frequency information.
Power-supply system 110 by supply line respectively with true part cabinet system 108, virtual cockpit/test stand cabin system 107,
Turntable 114 connects, and realizes the power supply of following equipment respectively：
True part cabinet system Aerial Electronic Equipment；
Virtual cockpit/test stand cabin system Aerial Electronic Equipment；
Inertial navigation, navigation attitude in turntable.
Power-supply system 110 is communicably connect by Ethernet with configuration intelligence control system 109, realizes long-range intelligence
Distribution；
Radio excitation system 111 is connect by radio-frequency cable with true part cabinet system 108, is transmitted radio communication navigation and is penetrated
Frequency signal；
Electromechanical MiniRIG112 is connect by avionics network with true part cabinet system 108, transmits Mechatronic Systems bus message；
Air excitation system 113 is connect by air source pipeline with true part cabinet system 108, air source information is transmitted, for big destiny
According to computer-solution；
Turntable 114 is connect by avionics network with configuration intelligence control system 109, transmits inertial navigation, navigation attitude bus data；
Avionics simulation system 102 is connect by avionics bus with configuration intelligence control system 109, is completed avionics network and is become
It changes；
Dynamoelectric signal simulation system 103 is connect by avionics bus with configuration intelligence control system 109, is completed electromechanical related
Avionics network transformation；
Dynamoelectric signal simulation system 103 is connect by avionics network with true part cabinet system 108, transmission Mechatronic Systems simulation letter
Number；
Data collecting system 104 is connect by avionics bus with configuration intelligence control system 109, acquires avionics network number
According to；
True part cabinet system 108 by avionics network respectively with configuration intelligence control system 109, virtual cockpit/experiment cockpit
System 107 connects；
Virtual cockpit/test stand cabin system 107 is connect by avionics bus with configuration intelligence control system 109.
102 principle of avionics simulation system as shown in Figure 5, including：Inertial navigation emulation part 10201, display processor are imitated
True part 10202 generates participation electromechanical parameters processor emulation part 10203, air data computer emulation part 10204, ultrashort wave electricity
Platform emulation part 10205, short-wave radio set emulation part 10206, GPS emulation part 10207, comprehensive radio navigation simulation part 10208, nothing
Line electrical height table emulation part 10209, center alarm Computer Simulation part 10211, flies ginseng record at weather radar emulation part 10210
System emulation part 10212, air traffic anti-collision system emulation part 10213, ground proximity warning system emulation part 10214, range finder are imitated
True part 10215, telecompass emulation part 10216.It is each to emulate the corresponding Aerial Electronic Equipment emulation of part complete independently, it can be according to user's need
The multiple examples of operation are sought, and realize the automatic numbering of example.
103 principle of dynamoelectric signal simulation system as shown in Figure 6, including：Fuel oil signal imitation 10301, hydraulic pressure letter
Number simulation 10302, undercarriage signal imitation 10303, manipulation signal simulation 10304, engine signal simulation 10305, hatch door letter
Number simulation 10306, AIR COND SIG Air Conditioner Singnal simulation 10307, fire prevention signal imitation 10308, anti-deicing signal imitation 10309 totally 9 modules.
Each module can complete independently corresponding system signal imitation, and can realize static and dynamic analog.Static simulation refers to try
The output of personnel's manual static setting analog signal is tested, dynamic analog refers to that dynamoelectric signal simulation system is received by Ethernet and flies
The analog signal of aircraft system state modulator output that row analogue system is shared, realizes the dynamic mapping of signal.
True 108 principle of part cabinet system as shown in Figure 7, including：Cabinet 10801, supplies adjustable wire connection terminal 10802
Electric Special wiring row 10803, Aerial Electronic Equipment 10804 of participating in the experiment.There is partition board, Aerial Electronic Equipment mounting bracket of participating in the experiment on partition board in cabinet
And connector.Adjustable wire connection terminal is mechanically connected by bottom plate and cabinet；Participate in the experiment Aerial Electronic Equipment by mounting bracket and cabinet every
Plate is mechanically connected；The Special wiring row that powers is mechanically connected by its bottom plate and cabinet；Participate in the experiment Aerial Electronic Equipment by aviation wire with
Adjustable wire connection terminal is communicatively coupled；Power supply Special wiring row is connect by aviation wire with Aerial Electronic Equipment of participating in the experiment, and is supplied for it
Electricity.Adjustable wire connection terminal is adapted to the more wheel changes of avionics system design to realize that the flexibility of Aerial Electronic Equipment wiring designs.
The virtual cockpit/107 principle of test stand cabin system as shown in Figure 8, including：Virtual cockpit 10701, test stand
Cabin 10702, cockpit are participated in the experiment the special power supply line bank 10704 of equipment 10703, cockpit, cockpit is adjustable wire connection terminal 10705.Virtually
Cockpit provides cockpit instrument, control panel, switch of emulation etc., is tested for full digital trigger technique；Cockpit participate in the experiment equipment pass through it is tight
Firmware and experiment cockpit mechanical connection；The special power supply line bank of cockpit is mechanically connected by its bottom plate and experiment cockpit；Cockpit can
Wire connection terminal is adjusted to be mechanically connected by its terminal block bottom plate and experiment cockpit；Cockpit it is special power supply line bank by aviation wire with
Cockpit participate in the experiment equipment connection, power for it；Cockpit is adjustable, and wire connection terminal participates in the experiment equipment communicably by aviation wire and cockpit
Connection.Adjustable wire connection terminal in similar true part cabinet system, cockpit is adjustable, and wire connection terminal is also suitable for avionics change in design, reaches
The purpose of flexibility design.
The electromechanics MiniRIG112 principles as shown in Figure 9, including：Fuel oil computer MiniRIG11201, wing flap control
Computer MiniRIG11202 processed, flight control computer MiniRIG11203, undercarriage control control computer MiniRIG11204,
Rudder restriction controller MiniRIG11205, water rudder control computer MiniRIG11206, stall protection control calculate
Machine MiniRIG11207, fireproofing controller MiniRIG11208, propeller temperature adding controller MiniRIG11209, Nose Wheel Steering control
Computer MiniRIG11210 processed, air-conditioner controller MiniRIG11211.These modules are respectively completed：
Avionics system is verified with the crosslinking of fuel system bus；
Avionics system is verified with the crosslinking of wing flap control system bus；
Avionics system is verified with the crosslinking of autoflight system bus；
Avionics system is verified with the crosslinking of Landing Gear System bus；
Avionics system is verified with the crosslinking of water rudder control system bus；
Avionics system is verified with the crosslinking of stall protection system bus；
Avionics system is verified with the crosslinking of fire prevention system bus；
Avionics system is verified with the crosslinking of propeller heating system bus；
Avionics system is verified with the crosslinking of Nose Wheel Steering system bus；
Avionics system is verified with the crosslinking of air-conditioning system bus.
111 principle of radio excitation system as shown in Figure 10, including：No.1 short-wave radio set encourages 11101, No. two
Short-wave radio set excitation 11102, No.1 ultrashort wave radio set encourage 11103, No. two ultrashort wave radio set excitations 11104, No.1 voll to swash
Encourage 11105, No. two voll excitations 11106, No.1 range finder encourages 11107, No. two range finder excitations 11108, telecompasses
Excitation 11109, No.1 blank pipe answering machine encourage 11110, No. two blank pipe answering machine excitations 11111, air traffic anticollision excitation
11112nd, No.1 radio altimeter encourages 11113, No. two radio altimeter excitations 11114, No.1 GPS excitations 11115, two
Number GPS excitation 11116, No.1 instrument landing encourage 11117, No. two instrument landings excitations 11118, marker beacon excitation 11119,
Weather radar target simulator 11120.Each excitation module can independent operating, can static stimulation dynamic excitation again.
The system simulates corresponding electromagnetic environment when aircraft performs aerial mission, completes swashing for aircraft radio communication navigation equipment
It encourages.
105 principle of visual system as shown in Figure 11, including：What comes into a driver's computer 10501 and display system 10502.
What comes into a driver's computer is communicably connect by vision cable with display system, and driving display system shows Flight scene image.Depending on
The initialization of scape system and view angle switch can control in turn-key system.
106 principle of flight Simulation System as shown in Figure 12, including：Aircraft aerodynamic model emulation 10601, aircraft system
System emulation 10602, fight environment simulation 10603, navigational route database 10604, topographic database 10605.
The related flight parameter information of aircraft aerodynamic model the Realization of Simulation aircraft flight six degree of freedom simulates the manipulation of aircraft
Response characteristic etc.；
Aircraft system emulation mainly includes：The status information of aircraft avionics system and each equipment of Mechatronic Systems, running parameter
Information etc. is used for each excitation system.
Fight environment simulation, including：The natural environments such as wind, rain, cloud；Air traffic situation.
Navigational route database, including obtaining near current location：Airport information, radionavigation station information, course line letter
Breath etc.；
Topographic database, including obtaining current terrain data information, to emulate ground proximity warning system function.
110 principle of power-supply system as shown in Figure 13, including：28V direct current supplys 11001,115V Alternating Current Power Supplies
11002,28V direct current supplys and the 115V Alternating Current Power Supplies participated in the experiment needed for equipment are realized respectively, support the long-distance intelligent of turn-key system
Distribution.
Integrated avionic system scale is big, and the crosslinking and cooperation relation between each system are complicated.In order to improve the effect of the system integration
Rate reduces manpower and time cost, it is necessary to using the method for science, to reduce integrated complexity.
The Integrated Strategy of system integration generally use increment type, the present invention integrates beginning using slave device, followed by divides and be
Irrespective of size, it is system-level, integrated to final aircraft-level.The strategy that this substep integrates causes the focus slave device integrated each time
The demand of grade is gradually transferred to final globality functional requirement so that fully exposes asking for different levels in entire integrating process
Topic, it is ensured that final overall system integration smoothly completes, so as to reduce the complexity of overall system integration.
In order to support this substep Integrated Strategy well, it is desirable to provide the simulation capacity of good each subsystem equipment with
And convenient interface fillip.Based on the emulation of model in addition to that can be that the demand of system and global design are carried in the development stage
Except verification means, mechanism is automatically generated by real-time target, also provides good test for follow-up system integration testing
Basis.In addition, simulation stage formed test specification and use-case, also integrated for subsequent substep provide perfect test will
It asks.By such method so that the model and test case of design phase can be iteratively applied to subsequent system collection
Into in test, so as to improve the efficiency of system development, the consistency of test ensure that, the final quality for improving product.
As can be seen from the above analysis, ideal system integrated approach is：The achievement of inheritance system Digital Simulation, and by its
It is transformed into the Real-Time Model (emulation part) for having actual physical interface, lays the first stone for the subsequent system integration.True
After real equipment (true part) is developed, by the replacement one by one between true part and emulation part, it is gradually completing entire avionics system
Integrated work.For the ease of the flexible replacement between true part and emulation part, testing stand needs to provide flexible configuration configuration, this can
To improve the avionics real-time performance of wiring mechanism by having.Avionics system is realized by the method for the step S101 ￣ S104 of attached drawing 2
System is integrated.
In the design phase of avionics system, designer can propose avionics system according to model totality and pilot total
Body requirement carries out demand analysis, and show that detailed avionics system function describes document, to instruct subsequent detailed design and divide
System realizes work.In the system integration and Qualify Phase, document is described according to the demand analysis and function of system, to each avionics
Whether subsystem and total system are fully examined, accomplished in the various functions requirement of design phase with verification,
Ensure that the avionics system finally delivered is consistent with initial design.
When planning to the verification work of avionics system, it is referred to demand analysis and function describes document, according to
The requirement of overall wherein to system and each subsystem designs the test case of Challenge-response formula one by one.So-called Challenge-response
Formula is verified, is to show equipment to be measured or system to provide a pumping signal, and trigger a series of its internal operation, state is cut
It changes or internal data transfer, the result finally responsed to which is acquired or measures, and be compared with desired response, with
Obtain the conclusion of verification.All it is greatly condition trigger-type due to having in the behavior of avionics system, so exciter response
Formula verification is the important verification method of avionics system.
The case designing of exciter response formula verification can be divided into two parts, i.e. pumping signal and expected response result.Excitation
Mode can be that once-through operation that pilot is present on on-deck plate or the signal specific to Devices to test input, can also
It is simulation under l-G simulation test environment to the change of external environment or to certain fault mode etc..Desired response results may
It is the output of certain signal specific or variation that avionics picture occurs, also or a series of chain reaction in caused system
Action.
In entire verification process, the Challenge-response verification sequence of avionics system can be by multiple execution repeatedly：
1) it in the full digital trigger technique stage, needs through the execution to whole checking cases, simulation model and verification is used
Example is confirmed；
2) it in cockpit joint-trial or subsystem Qualify Phase, needs to perform aobvious control or the relevant checking case of the subsystem；
3) it in total system Qualify Phase, needs to perform all checking cases from the beginning to the end, and one by one confirm；
4) when verification is pinpointed the problems, whether exclude to confirm for the positioning for carrying out failure or to failure, it is also desirable to
Relevant checking case is performed repeatedly.
Verification for subsystem is general using static Challenge-response formula verification method.The step of by attached drawing 3
The method of S201 ￣ S204 realizes the verification of Challenge-response formula.
In order to investigate working condition of the avionics system under practical flight task environment comprehensively, need to test using dynamic comprehensive
Card method, i.e., based on real-time flight simulation, the verification for avionics system provides data stimuli source.Flying simulation model should be able to
The emulation of whole envelope is carried out, and manually and automatically two kinds of offline mode are provided.During experiment, flying simulation model will resolve
The flight parameter gone out shares to avionics simulation model, various excitation systems and visual system etc., and entire experimental enviroment is made to coordinate system
One.In addition, it should also contain all kinds of simulation models with the crosslinked non-avionics system of avionics system in flying simulation model and fly control
System model, to support the joint-trial of each system.In dynamic comprehensive verification process, it can be injected and failure mould by various data
The means of plan, investigate whether avionics system can correctly handle all kinds of fault modes.
Before dynamic comprehensive verification is carried out, it is also desirable to experiment process rationally be planned, to the scene and task of experiment
Environment is set, and chooses suitable flight profile, mission profile, and determine the content mainly investigated during the secondary flight test and
Method.During experiment, need the acquisition by data and monitoring tools, to the test data before and after failure carry out record and
Analysis.The method that dynamic comprehensive is verified the step S301-S307 of attached drawing 4 is realized.
The basic principle of aircraft avionics system flexibility test platform is：On the basis of avionics system emulation, pass through true part
To emulating the replacement one by one of part, the integrated of avionics system, joint debugging and test verification is done step-by-step.Thus, it is possible to reference to existing hard
The framework of part, software technology design avionics system flexibility test platform.
Claims (6)
1. a kind of avionics system flexibility test platform, including：Turn-key system (101), avionics simulation system (102), configuration intelligence
Control system (109), turntable (114), dynamoelectric signal simulation system (103), true part cabinet system (108), air excitation system
(113), data collecting system (104), virtual cockpit/test stand cabin system (107), electromechanics MiniRIG (112), wireless electric shock
Encourage system (111), visual system (105), flight Simulation System (106) and power-supply system (110)；
Wherein, turn-key system (101) by Ethernet communicably respectively with flight Simulation System (106), visual system
(105), power-supply system (110), radio excitation system (111), electromechanics MiniRIG (112), air excitation system (113), turn
Platform (114), configuration intelligence control system (109), avionics simulation system (102), dynamoelectric signal simulation system (103), data are adopted
Collecting system (104) connects, and turn-key system is completed control, management instruction and state reporting information by Ethernet and transmitted；
Flight Simulation System (106) is communicably connect by Ethernet with virtual cockpit/test stand cabin system (107), transmission
Flight parameter, area navigation parameter, aircraft possessed system parameter message：
Virtual cockpit/test stand cabin system (107) by avionics network communicable is connect with true part cabinet system (108), is completed
Instrument display function, and transmit the control information to equipment in true part cabinet system (108)：
Power-supply system (110) is by supply line respectively to true part cabinet system (108), virtual cockpit/test stand cabin system
(107), turntable (114) equipment is powered；
Power-supply system (110) is communicably connect by Ethernet with configuration intelligence control system (109), realizes long-range intelligence
Distribution；
Radio excitation system (111) is connect by radio-frequency cable with true part cabinet system (108), is transmitted radio communication navigation and is penetrated
Frequency signal；
Electromechanical MiniRIG (112) is connect by avionics network with true part cabinet system (108), transmits aircraft utilities system bus letter
Breath；
Air excitation system (113) is connect by air source pipeline with true part cabinet system (108), air source information is transmitted, for true part cabinet
Air data computer in system (108) resolves；
Turntable (114) is connect by avionics network with configuration intelligence control system (109), transmits inertial navigation, navigation attitude bus data；
Avionics simulation system (102) is connect by avionics bus with configuration intelligence control system (109), is completed avionics network and is cut
It changes；
Dynamoelectric signal simulation system (103) is connect by avionics bus with configuration intelligence control system (109), is completed electromechanical related
Avionics network switching；
Dynamoelectric signal simulation system (103) is connect by avionics network with true part cabinet system (108), transmits aircraft utilities system mould
Intend signal；
Data collecting system (104) is connect by avionics bus with configuration intelligence control system (109), acquires avionics network number
According to；
True part cabinet system (108) by avionics network respectively with configuration intelligence control system (109), virtual cockpit/experiment cockpit
System (107) connects, inside carrying avionics system real equipment；
Virtual cockpit/test stand cabin system (107) is connect by avionics bus with configuration intelligence control system (109)；
True part cabinet system (108) and virtual cockpit/test stand cabin system (107) together constitute the avionics system for participating in experiment.
2. carry out the method that integrates of avionics system using avionics system flexibility test platform as described in claim 1, including with
Lower step：
1) full digital trigger technique, the reasonability of verification avionics system design；
Avionics simulation system (102) provides inertial navigation emulation part (10201), display processor emulates part (10202), hair participation is electromechanical
Parameter processing machine emulation part (10203), air data computer emulate part (10204), ultrashort wave radio set emulates part (10205),
Short-wave radio set emulation part (10206), GPS emulation parts (10207), comprehensive radio navigation simulation part (10208), radio altitude
Table emulation part (10209), center alarm Computer Simulation part (10211), flies ginseng record system at weather radar emulation part (10210)
System emulation part (10212), air traffic anti-collision system emulation part (10213), ground proximity warning system emulation part (10214), ranging
Machine emulation part (10215) and telecompass emulation part (10216) form digital avionics system and carry out emulation testing.
2) the true part of device level replaces emulation part, completes device level and integrates；
It is replaced successively using the single Aerial Electronic Equipment that virtual cockpit/test stand cabin system (107) and true part cabinet system (108) include
Emulation part corresponding to avionics simulation system (102).
3) the true part of subsystem grade replaces emulation part, completes subsystem grade and integrates；
Press the division principle of avionics system aircraft possessed avionics subsystem successively, virtual cockpit/test stand cabin system (107) and
The multiple equipment composition subsystem that true part cabinet system (108) includes, substitutes the emulation part corresponding to avionics simulation system (102).
4) system-level true part replaces emulation part, is finally completed system-level integrated.
After completing subsystem grade and integrating, virtual cockpit/test stand cabin system (107) and true part cabinet system (108) are included
All devices access avionics experimental network, disconnect all emulation parts of avionics simulation system (102), complete system-level formula,
It is system-level integrated to complete.
3. using avionics system flexibility test platform as described in claim 1 carry out avionics system verification method, including with
Lower step：
1) Challenge-response formula is verified；
2) dynamic comprehensive is verified.
4. the method for avionics system verification as claimed in claim 3, which is characterized in that the Challenge-response formula verification includes
Following steps：
1.1) excitation of the setting to individual equipment in avionics system and/or avionics system；
The excitation includes：Tester is in the operation of cockpit, the signal specific from bus interface, from other aircraft systems
Alarm signal.
1.2) acquisition measures the response of equipment in avionics system and/or avionics system；
1.3) compare it is described response with turn-key system (101) in set intended response it is whether consistent, come verify avionics system with/
Or whether the corresponding function of equipment is verified in avionics system；
1.4) report of turn-key system (101) generation Challenge-response formula verification.
5. the method for avionics system verification as claimed in claim 4, which is characterized in that the intended response described in step 1.3)
It is to describe document according to the functional requirement of equipment in avionics system and/or avionics system to obtain its sound under the excitation operating mode
Should, described in step 1.2) response can be cause system certain operations or picture variation or distinctive signal output or generation
Special alarm audio or a series of chain reaction.
6. the method for avionics system verification as claimed in claim 3, which is characterized in that the dynamic comprehensive verification includes following
Step：
2.1) simulation model is established according to the feature of avionics system aircraft possessed；
2.2) fight environment simulation model is established according to navigational route database, atmospheric environment, Traffic Environment, gravitational field；
2.3) identical flight plan is set respectively in avionics system and flight Simulation System (106)；
2.4) operating procedure 2.1) and 2.2) in establish simulation model；
2.5) flight parameter and aircraft system parameter sharing provided flight Simulation System (106) swashs to turntable (114), air
System (113), radio excitation system (111), dynamoelectric signal simulation system (103), electromechanics MiniRIG (112) are encouraged to complete
The dynamic exciting of tested avionics system；
2.6) turntable (114), air excitation system (113), radio excitation system (111), dynamoelectric signal simulation system
(103), electromechanics MiniRIG (112) encourages corresponding Aerial Electronic Equipment in avionics system；
2.7) dynamic response of dynamic acquisition and observation avionics system, describes with the functional requirement of avionics system defined in document
Avionics system operation characteristic compares, and whether the function of avionics system and performance meet design and want when performing aerial mission so as to verify
It asks.
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