CN106598032B - A kind of test macro of automatic flight control system - Google Patents
A kind of test macro of automatic flight control system Download PDFInfo
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Abstract
The invention discloses a kind of test macros of automatic flight control system, belong to aeronautical engineering test field.It is characterized by comprising the automatic flight control signal transmission disconnection devices for completing automatic flight-control computer crosslinking signal detection, airborne databus coupler, automatic flight control system test interface device, and accelerator actuating mechanism, return actuator, the emulator and air data system of main flight-control computer, inertial navigation system, radio altimeter, flight management system, state of flight is shown, engine parameter system simulator etc. and test application software form, realize the emulation that airborne equipment is crosslinked in automatic flight control system test, it completes to test automatic flight control system.
Description
Technical field
The present invention relates to the tests of a kind of test macro of automatic flight control system, especially automatic flight control system
System and method belong to aeronautical engineering testing field.
Background technique
Automatic flight control system is aircraft critical function system, realizes the automatic control to aircraft instead of pilot, with
Other function system cooperations of aircraft are to be better carried out aerial mission.Automatic flight control system includes automatic flight
Control device (AFCU), automatic flight-control computer (AFCC), passback actuator device etc., automatic flight-control computer
(AFCC) command information for receiving automatic flight control assemblies (AFCU), and from flight management system, air data system, used
The parameter informations such as guiding systems, Low-altitude Radio altimeter are comprehensive, generate the order for controlling main flight-control computer (PFC), lead to
It crosses data/address bus to be sent to main flight-control computer (PFC), realizes the control to airplane motion posture, to complete to aircraft
The control of flight path, and will be big by cockpit control command corresponding to main flight-control computer (PFC) command parameter is given
Small, control passback actuator movement is in the same size with cockpit control command amplitude to control aircraft flight attitude.
Equally, automatic flight-control computer (AFCC) receives the command information of automatic flight control assemblies (AFCU), also
It is comprehensive with the parameter information from engine parameter system, control engine throttle instruction is generated, accelerator actuating mechanism is controlled, it is real
Now to the control of airplane motion posture, to complete the control to aircraft flight path.
Above-mentioned control aircraft in-flight, the parameters such as position, posture of aircraft flight are by automatic flight-control computer
(AFCC) it is sent to state of flight display to be shown, observes position, posture that prison shows aircraft flight in real time convenient for pilot
Equal parameter informations.
In the development and design of aircraft, especially in progress, aircraft critical function system --- automatic flight control system is set
Meter generally requires to carry out a variety of different tests in developing, such as: the component test of automatic flight-control computer, automatic flight
Control system synthesis test, automatic flight control system iron bird integration test etc..In above-mentioned test, it usually needs according to test pair
As --- automatic flight-control computer or automatic flight control system develop corresponding experimental test environment, according to examination
Test tries the contents of a project, carries out automatic flight-control computer or automatic flight control system interface check, polarity and transmission ratio
The correlations such as inspection, work-based logic inspection, system control function inspection, the inspection of system static and dynamic performance, alarm display function inspection
Experiment work.
Above-mentioned experimental test environment is often directed to single subjects --- and automatic flight-control computer is automatic winged
Row control system separately designs construction, and design-build of experimental test environment is completed, can only be used as overall time.Such as
During automatic flight-control computer experimental test environment is built, need using numerous instrument and equipments having a single function, such as using letter
Number generator emulation accelerator actuating mechanism, passback actuator signal, use digital multimeter, oscillograph, data acquiring and recording system
System etc. equipment complete crosslinking interface analog quantity, digital quantity, on-off model acquisition and recording.Using data/address bus emulator,
Data/address bus monitoring device completes the transmission of data/address bus information, receives analysis etc., experimental test according to the needs of content of the test,
It is once only capable of emulation single signal or carries out the single step emulation of pumping signal, numerous instrument and equipments having a single function are applied in combination,
Operating process complexity, cumbersome, inefficiency, and due to being limited by experimental enviroment condition, it is only capable of completing part test test
Content.Either automatic flight control system compbined test, automatic flight control system iron bird integration test test environment are built
In, although being configured with accelerator actuating mechanism, passback actuator, air data system, inertial navigation around automatic flight-control computer
System, Low-altitude Radio altimeter etc., complex process, enforcement difficulty is big, causes cost also very high, and does not have versatility.
There is still a need for numerous instrument and equipments having a single function, same complicated, cumbersome, the efficiency of operating process is applied in combination for experimental test process
Lowly.
Summary of the invention
The purpose of the present invention is: it is the test macro and its method for designing a kind of automatic flight control system, realizes automatic
In all kinds of tests of flight-control computer or automatic flight control system with automatic flight-control computer cross-linking apparatus from
Dynamicization emulation, completes the automation of automatic flight control system test.
The technical scheme is that a kind of test macro of automatic flight control system, including for completing to fly automatically
The automatic flight control system signal of row control computer crosslinking signal detection transmits disconnection device [1], 1553B data/address bus coupling
Clutch [2], ARINC-429 data bus coupler [3], automatic flight control system test interface device [4] and throttle are held
Row mechanism simulation device [5], longitudinal passback actuator emulator [6], laterally passback actuator emulator [7], course return actuation
Device emulator [8], main flight-control computer emulator [9], air data system emulator [10], inertial navigation system emulator
[11], Low-altitude Radio altimeter emulator [12], flight management system emulator [13], centralized maintenance system emulator
[14], state of flight shows emulator [15], engine parameter system simulator [16], wherein longitudinal passback actuator emulation
Device [6] includes longitudinal passback actuator interface signal emulation board and longitudinal passback actuator model component, by longitudinally returning actuation
The longitudinal passback actuator interface signal physical characteristic of device interface signal emulation board emulation, in longitudinally passback actuator model component
Operation control is lower to generate the feedback signal for meeting longitudinal passback actuator interface features and logical relation；
Laterally passback actuator emulator [7] includes laterally passback actuator interface signal emulation board and laterally passback actuation
Device model component, by laterally returning actuator interface signal emulation board emulation laterally passback actuator interface signal physical characteristic,
It is generated under the operation control of laterally passback actuator model component and meets laterally passback actuator interface features and logical relation
Feedback signal；
Course passback actuator emulator [8] includes course passback actuator interface signal emulation board and course passback actuation
Device model component returns actuator interface signal physical characteristic by course passback actuator interface signal emulation board emulation course,
It is generated under the operation control of course passback actuator model component and meets course passback actuator interface features and logical relation
Feedback signal；
Main flight-control computer emulator [9] includes 1553B data bus interface plate and main flight-control computer mould
Type component realizes the communication with automatic flight-control computer AFCC by 1553B data bus interface plate, controls and count in main flight
The operation control of calculation machine model component is lower to receive the order that automatic flight-control computer AFCC is sent by 1553B data/address bus
Signal emulates the function and control law algorithm of main flight-control computer, the status information for indicating implementing result is passed through 1553B
Data/address bus is returned again to automatic flight-control computer AFCC；
Air data system emulator [10] includes ARINC-429 data bus interface plate and air data system model group
Air data system state parameter is arranged in part, executes air data system simulation algorithm, and write operation controls ARINC-429 data
The air data system state parameter of current setting is sent to automatic fly by ARINC-429 data/address bus by bus interface board
Row control computer AFCC；
Inertial navigation system emulation emulator [11] includes ARINC-429 data bus interface plate and INS model component,
Inertial system state parameter is set, inertial navigation system simulation algorithm is executed, write operation controls ARINC-429 data bus interface plate,
The inertial system state parameter of current setting is sent to automatic flight-control computer by ARINC-429 data/address bus
AFCC；
Low-altitude Radio altimeter emulator [12] includes ARINC-429 data bus interface plate and Low-altitude Radio height
Low-altitude Radio altimeter state parameter is arranged in table model component, executes Low-altitude Radio altimeter simulation algorithm, write operation control
ARINC-429 data bus interface plate processed, by ARINC-429 data/address bus by the Low-altitude Radio height table-like of current setting
State parameter is sent to automatic flight-control computer AFCC；
Flight management system emulator [13] includes ARINC-429 data bus interface plate and flight management system model group
Flight management system state parameter is arranged in part, executes flight management system simulation algorithm, and write operation controls ARINC-429 data
The flight management system state parameter of current setting is sent to automatic fly by ARINC-429 data/address bus by bus interface board
Row control computer AFCC；
Centralized maintenance system emulator [14] includes ARINC-429 data bus interface plate and centralized maintenance system model group
Part receives the data information that automatic flight-control computer AFCC is sent to airborne centralized maintenance system and is shown, either
Airborne centralized maintenance system function is emulated, Xiang Zidong flight-control computer AFCC sends data command；
State of flight shows that emulator [15] include ARINC-429 data bus interface plate and state of flight display model group
Part executes state of flight and shows simulation algorithm, and the style and content of simulated flight status display interface receive automatic flight control
Computer AFCC is sent to the data information of onboard flight status displays, and is shown；
Engine parameter system emulation emulator [16] includes ARINC-429 data bus interface plate and engine parameter system
System model component, is arranged engine parameter system status parameters, executes engine parameter simulation algorithm, write operation control
ARINC-429 data bus interface plate is joined the engine parameter system mode of current setting by ARINC-429 data/address bus
Number is sent to automatic flight-control computer AFCC；
It is equipped with based on testing and control bus or computer bus [202], by test emulation controller [201], RVDT
Or LVDT signal interface board [203], 1553B data bus interface plate [204], ARINC-429 data bus interface plate [205] group
At automatization test system, test emulation controller [201] realized pair by test equipment bus or computer bus [202]
The control of above-mentioned all kinds of interface boards；
The advantages of the present invention are:
(1) structurally reasonable compact, reliable operation, the interface model using high reliability, by optimization design, modularization,
Standardization and seriation adapts to use in harsh electromagnetism and mechanical environment.
(2) excellent extensibility, tailorability and reusability, each simulation unit are designed using modular assembly, can root
According to optional component module is needed, the unitization combination of system is realized.
(3) due to realizing General design, it is functionally equivalent to the function of original multiple special equipments, is substantially reduced
Equipment cost.
(4) fully functional, easy to use, test efficiency is improved, the test period is shortened, reduces expense.
Detailed description of the invention
Fig. 1 is composite structural diagram of the present invention；
Fig. 2 is one embodiment of the invention theory of constitution figure；
Fig. 3 is test software flow chart of the present invention.
Wherein, signal transmission disconnection device [1], 1553B data bus coupler [2], the coupling of ARINC-429 data/address bus
Device [3], automatic flight control system test interface device [4] and accelerator actuating mechanism emulator [5], longitudinal passback actuation
Device emulator [6], laterally passback actuator emulator [7], course return actuator emulator [8], main flight-control computer
Emulator [9], air data system emulator [10], inertial navigation system emulator [11], Low-altitude Radio altimeter emulator
[12], flight management system emulator [13], centralized maintenance system emulator [14], state of flight show emulator [15], hair
Motivation parameter system emulator [16].
Specific embodiment
The present invention is described in detail with reference to the accompanying drawings and examples.
A kind of test macro and its method of automatic flight control system, including for completing automatic flight-control computer
Be crosslinked signal detection automatic flight control system signal transmission disconnection device [1], 1553B data bus coupler [2],
ARINC-429 data bus coupler [3], automatic flight control system test interface device [4] and accelerator actuating mechanism are imitative
True device [5], longitudinal passback actuator emulator [6], laterally passback actuator emulator [7], course return actuator emulator
[8], main flight-control computer emulator [9], air data system emulator [10], inertial navigation system emulator [11], low latitude
Radio altimeter emulator [12], flight management system emulator [13], centralized maintenance system emulator [14], state of flight
Show emulator [15], engine parameter system simulator [16].
Accelerator actuating mechanism emulator [5] includes accelerator actuating mechanism interface signal emulation board and accelerator actuating mechanism model
Component emulates accelerator actuating mechanism interface signal physical characteristic by accelerator actuating mechanism interface signal emulation board, executes in throttle
The operation control of mechanism model component is lower to generate the feedback signal for meeting accelerator actuating mechanism interface features and logical relation.
Longitudinal passback actuator emulator [6] includes longitudinal passback actuator interface signal emulation board and longitudinal passback actuation
Device model component, by longitudinally returning the longitudinal passback actuator interface signal physical characteristic of actuator interface signal emulation board emulation,
It is generated under the operation control of longitudinally passback actuator model component and meets longitudinal passback actuator interface features and logical relation
Feedback signal；
Laterally passback actuator emulator [7] includes laterally passback actuator interface signal emulation board and laterally passback actuation
Device model component, by laterally returning actuator interface signal emulation board emulation laterally passback actuator interface signal physical characteristic,
It is generated under the operation control of laterally passback actuator model component and meets laterally passback actuator interface features and logical relation
Feedback signal；
Course passback actuator emulator [8] includes course passback actuator interface signal emulation board and course passback actuation
Device model component returns actuator interface signal physical characteristic by course passback actuator interface signal emulation board emulation course,
It is generated under the operation control of course passback actuator model component and meets course passback actuator interface features and logical relation
Feedback signal.
Main flight-control computer emulator [9] includes 1553B data bus interface plate and main flight-control computer mould
Type component realizes the communication with automatic flight-control computer (AFCC) by 1553B data bus interface plate, controls in main flight
The operation control of computer model component is lower to receive what automatic flight-control computer (AFCC) sent by 1553B data/address bus
Command signal emulates the function and control law algorithm of main flight-control computer, the status information for indicating implementing result is passed through
1553B data/address bus, which returns again to, gives automatic flight-control computer (AFCC).
Air data system emulator [10] includes ARINC-429 data bus interface plate and air data system model group
Air data system state parameter is arranged in part, executes air data system simulation algorithm, and write operation controls ARINC-429 data
The air data system state parameter of current setting is sent to automatic fly by ARINC-429 data/address bus by bus interface board
Row control computer (AFCC)；
Inertial navigation system emulation emulator [11] includes ARINC-429 data bus interface plate and INS model component,
Inertial system state parameter is set, inertial navigation system simulation algorithm is executed, write operation controls ARINC-429 data bus interface plate,
The inertial system state parameter of current setting is sent to automatic flight-control computer by ARINC-429 data/address bus
(AFCC)；
Low-altitude Radio altimeter emulator [12] includes ARINC-429 data bus interface plate and Low-altitude Radio height
Low-altitude Radio altimeter state parameter is arranged in table model component, executes Low-altitude Radio altimeter simulation algorithm, write operation control
ARINC-429 data bus interface plate processed, by ARINC-429 data/address bus by the Low-altitude Radio height table-like of current setting
State parameter is sent to automatic flight-control computer (AFCC)；
Flight management system emulator [13] includes ARINC-429 data bus interface plate and flight management system model group
Flight management system state parameter is arranged in part, executes flight management system simulation algorithm, and write operation controls ARINC-429 data
The flight management system state parameter of current setting is sent to automatic fly by ARINC-429 data/address bus by bus interface board
Row control computer (AFCC)；
Centralized maintenance system emulator [14] includes ARINC-429 data bus interface plate and centralized maintenance system model group
Part, receives automatic flight-control computer (AFCC) and is sent to the data information of airborne centralized maintenance system and shown, or
It is the airborne centralized maintenance system function of emulation, Xiang Zidong flight-control computer (AFCC) sends data command；
State of flight shows that emulator [15] include ARINC-429 data bus interface plate and state of flight display model group
Part executes state of flight and shows simulation algorithm, and the style and content of simulated flight status display interface receive automatic flight control
Computer (AFCC) is sent to the data information of onboard flight status displays, and is shown.
Engine parameter system emulation emulator [16] includes ARINC-429 data bus interface plate and engine parameter system
System model component, is arranged engine parameter system status parameters, executes engine parameter simulation algorithm, write operation control
ARINC-429 data bus interface plate is joined the engine parameter system mode of current setting by ARINC-429 data/address bus
Number is sent to automatic flight-control computer (AFCC).
Fig. 2 is one embodiment of the invention theory of constitution figure.
In embodiment, it is equipped with based on testing and control bus or computer bus [202], by test emulation controller
[201], RVDT (or LVDT) signal interface board [203], 1553B data bus interface plate [204], ARI NC-429 data/address bus
The automatization test system of interface board [205] composition, test emulation controller [201] are total by test equipment bus or computer
Line [202] realizes the control to above-mentioned all kinds of interface boards [203] [204] [205].
It is equipped with fully functional, reliable operation test emulation controller [201], supports the operation of Simulation Application software, it is complete
The state setting and operation control of pairs of all kinds of emulation interface plates [203] [204] [205], realize that RVDT (or LVDT) signal is defeated
Enter measurement or simulation data and on-board data information receives, monitoring or emulation are sent；
It is equipped with fully functional, reliable operation RVDT (or LVDT) signal interface board [203], is calculated in automatic flight control
In machine or automatic flight control system test, emulation accelerator actuating mechanism, longitudinal passback actuator, laterally passback actuator, boat
The RVDT signal of actuator internal sensor is returned back, Xiang Zidong flight-control computer provides the input of RVDT (or LVDT) signal
Excitation；
It is equipped with fully functional, reliable operation 1553B data bus interface plate [204], is realized and automatic flight control meter
The communication of calculation machine receives the 1553B bus data information that automatic flight-control computer sends output, and controls to automatic flight
Computer processed sends 1553B bus data information；
It is equipped with fully functional, reliable operation ARINC-429 data bus interface plate [205], realizes and is controlled with automatic flight
The communication of computer processed receives the ARINC-429 bus data information that automatic flight-control computer sends output, flies to automatic
Row control computer sends the data information of ARINC-429 bus.
It is equipped with fully functional, reliable operation detection application software, someone-machine operation interface function, simulation status is provided
Function is emulated with parameter setting function, simulation model operation control function, simulation model library and management function, accelerator actuating mechanism
Energy, longitudinal direction passback actuator copying, lateral passback actuator copying, course returns actuator copying, master flies
Row control Computer Simulation function, air data system copying, inertial navigation system copying, Low-altitude Radio altimeter are imitative
True function, flight management system copying, centralized maintenance system copying, state of flight show copying, engine
Parameter system copying, corresponding above-mentioned function, develops special software module and realizes its function；
People-machine operation interface assembly module [213] provides people-machine operation mode and means, passes through component software bus
[212] scheduling executes simulation status and parameter setting assembly module [214], simulation model run control assembly module [215], imitate
True mode library and management assembly module [216], accelerator actuating mechanism emulation module [217], passback actuator emulation module
[218], main flight-control computer emulation module, air data system emulation module, inertial navigation system emulation module, low latitude is wireless
Electrical height table emulation module, flight management system emulation module, centralized maintenance system emulation module, state of flight display emulation mould
Block, engine parameter system simulation module；
The selection and parameter setting of simulation status, selection emulation are realized in simulation status and parameter setting assembly module [214]
Model state provides each simulation model input parameter；
Simulation model library and management assembly module [215] complete foundation, maintenance, update, the management etc. of simulation model library, just
It is executed in calling of the simulation model operation control assembly module to simulation model each in model library；
Simulation model, which runs control assembly module [216] and tests according to automatic flight control system, to be needed, and is called corresponding
Simulation model executes model algorithm, controls emulation interface plate [203] [204] [205], generates simulation excitation signal, or hair
Send/receive data/address bus information；
Accelerator actuating mechanism emulation module [217] is tested according to automatic flight control system to be needed, and throttle is called to execute machine
Structure simulation model executes model algorithm, obtains RVDT signal magnitude corresponding to current throttle position, controls RVDT signal simulation
Interface board generates accelerator actuating mechanism position emulation signal to automatic flight-control computer (AFCC)；
It returns actuator emulation module [218] and is tested according to automatic flight control system and needed, call passback actuator imitative
True mode executes model algorithm, obtains currently returning RVDT signal magnitude corresponding to position, controls RVDT signal simulation interface
Plate generates passback actuator position emulation signal to automatic flight-control computer (AFCC)；
Main flight-control computer emulation module [219] is tested according to automatic flight control system to be needed, and main flight is called
It controls computer simulation model and executes model algorithm, automatic flight-control computer (AFCC) is received by 1553B data/address bus
The command signal of transmission emulates the function and control law algorithm of main flight-control computer, and the state for indicating implementing result is believed
Breath is returned again to by 1553B data/address bus gives automatic flight-control computer (AFCC).
Air data system emulation module [220] is tested according to automatic flight control system to be needed, and atmosphere data system is called
Simulation model of uniting executes model algorithm, needs to be arranged air data system state parameter, write operation control according to current test
ARINC-429 data bus interface plate, by ARINC-429 data/address bus by the air data system state parameter of current setting
It is sent to automatic flight-control computer (AFCC)；
Inertial navigation system emulation module [221] is tested according to automatic flight control system to be needed, and inertial navigation system is called to emulate mould
Type executes model algorithm, needs to be arranged inertial system state parameter according to current test, it is total that write operation controls ARINC-429 data
The inertial system state parameter of current setting is sent to automatic flight control by ARINC-429 data/address bus by line interface plate
Computer (AFCC)；
Low-altitude Radio altimeter emulation module [222] according to automatic flight control system test need, call low latitude without
Line electrical height table simulation model executes model algorithm, needs to be arranged Low-altitude Radio altimeter state parameter according to current test,
Write operation controls ARINC-429 data bus interface plate, by ARINC-429 data/address bus by the Low-altitude Radio of current setting
Altimeter state parameter is sent to automatic flight-control computer (AFCC)；
Flight management system emulation module [223] is tested according to automatic flight control system to be needed, and flight management system is called
Simulation model of uniting executes model algorithm, needs to be arranged flight management system state parameter, write operation control according to current test
ARINC-429 data bus interface plate, by ARINC-429 data/address bus by the flight management system state parameter of current setting
It is sent to automatic flight-control computer (AFCC)；
Centralized maintenance system assembly module [224] is tested according to automatic flight control system to be needed, and airborne center dimension is emulated
Protecting system function, receives automatic flight-control computer (AFCC) and is sent to the data information of airborne centralized maintenance system and shown
Show, or the airborne centralized maintenance system function of emulation, Xiang Zidong flight-control computer (AFCC) send data command；
State of flight shows that emulation component module [225] test needs, simulated flight shape according to automatic flight control system
The style and content of state display interface receive automatic flight-control computer (AFCC) and are sent to onboard flight status displays
Data information, and shown.
Engine parameter system simulation module [226] is tested according to automatic flight control system to be needed, and engine ginseng is called
Number system simulation model executes model algorithm, needs to be arranged engine parameter system status parameters, write operation according to current test
ARINC-429 data bus interface plate is controlled, by ARINC-429 data/address bus by the engine parameter system shape of current setting
State parameter is sent to automatic flight-control computer (AFCC).
In the test macro and its embodiment of the method for a kind of automatic flight control system of the invention, test emulation controller
[201] the NI PXI-8108 embedded controller of NI (National Instruments Inc.) company is used；
Test equipment bus & computer bus [202] uses PXI bus, selects NI (National Instruments
Inc.) company NI PXI-1045 cabinet supports PXI bus functionality；
RVDT signal interface board [203] uses NAI company NAI (North Atlantic Industries Inc.) 75C3
Board, completes the simulation to RVDT signal, and output generates command signal, feedback signal；
1553B data bus interface plate [204] uses the CPCIC3/6- of Alta Data Technologies company
1553-1F/2F/3F/4F-T board completes the transmission to 1553B bus data information, or completes 1553B bus data
Information receives；
ARINC-429 data bus interface plate [205] uses the CPCIC3/6- of Alta Data Technologies company
A429-30-T board completes transmission to ARINC-429 bus data information, or complete ARINC-429 number of buses it is believed that
Breath receives；
Accelerator actuating mechanism adapter [206], longitudinal passback actuator adapter [207], laterally passback actuator adaptation
Device [208], course passback actuator adapter [209] are using the component for being configured with multicore aviation socket；
1553B data bus coupler [210] uses 8 mouthfuls of 1553B data bus couplers；
ARINC-429 data bus coupler [211] is using configured with multicore aviation connector.
Features described above of the invention can change as shown below, but they are all without departing from essence of the invention.
Such as, operation control unit [1] uses the NI PXI-8108 of NI (National Instruments Inc.) company
Outside embedded controller, the embedded controller of the other model PXI buses of NI company also can choose, it is also an option that other public affairs
The embedded controller of the PXI bus of department；
RVDT signal interface board [203], which removes, uses NAI company NAI (North Atlantic Industries Inc.)
75C3 board also can choose NAI company NAI 75DL1 board, it is also an option that the RVDT signal simulation board of other companies；
Further, for the emulation of RVDT signal, except using NAI (North Atlantic Industries Inc.)
75C3 board also can choose the NI PXI-7851R board of NI company, can using existing market supply other models or
Other type RVDT command signal interface models, such as 2024 interface model of ATSIM-LVDT that ATENA company provides, North
The Model cPCI-75DL1 3U interface model that Atlantic Industries Inc. company provides, Axiomatic
The LVDTS-DR-02 interface model that Technologies Corporation company provides, United Electronic
The DNA/DNR-AI-254 interface model that Industries Inc. company provides, or also can choose other company's productions
The RVDT command signal interface model of other models, it is of course also possible to which designed, designed develops RVDT command signal interface model.
1553B data bus interface plate [204] uses Alta Data Technologies company CPCIC3/6-1553-
Outside 1F/2F/3F/4F-T board, it also can choose the other boards of Alta Data Technologies company, it is also an option that its
The 1553B data bus interface board of its company；
ARINC-429 data bus interface plate [204] uses Alta Data Technologies company CPCIC3/6-
Outside A429-30-T board, it also can choose the other boards of Alta Data Technologies company, it is also an option that other public affairs
The ARINC-429 data bus interface board of department；
Test equipment bus & computer bus [202], which removes, uses PXI bus, and it is total also to can choose VXI, LXI instrument controlling
Line, it is also an option that the microcomputer bus such as PCI, VME.
Fig. 3 is test software flow chart of the present invention.
A kind of test software process description of automatic flight control system of the invention its implementation, including it is following in detail
Thin step:
Step 1: system execution starts [301], needs the completing of the task according to experimental test, initialization test system, if
Set the original state of test macro；
Step 2: executing [302], each interface board, data is arranged in initializing signal interface board, data bus communication interface plate
The initial output value of bus communication interface plate；
Step 3: executing [303], read simulation status parameter；
Step 4: executing [304], the initial parameter of simulation model is set；
Step 5: entering each emulation branch [305] [306] [307] [308] [308] [310] [311]；
It executes [305], executes main flight-control computer emulation component, emulate main flight-control computer function and shape
State is arranged main flight-control computer state parameter, is sent to automatic flight-control computer according to the requirement of test assignment；
It executes [306], executes air data system emulation component, air data system function and state are emulated, according to survey
The requirement of trial business, is arranged air data system state parameter, is sent to automatic flight-control computer；
It executes [307], executes inertial navigation system emulation component, inertial navigation system function and state are emulated, according to test assignment
It is required that setting inertial system state parameter, is sent to automatic flight-control computer；
It executes [308], executes Low-altitude Radio altimeter emulation component, emulate Low-altitude Radio height table function and shape
State is arranged Low-altitude Radio altimeter state parameter, is sent to automatic flight-control computer according to the requirement of test assignment；
It executes [309], flight management system emulation component, simulated flight management system function and state is executed, according to survey
The requirement of trial business, is arranged flight management system state parameter, is sent to automatic flight-control computer；
It executes [310], executes engine parameter system emulation component, simulating engine parameter system function and state, press
According to the requirement of test assignment, engine parameter system status parameters are set, automatic flight-control computer is sent to；
It executes [311], executes centralized maintenance system emulation component, centralized maintenance system function and state are emulated, according to survey
The requirement of trial business, is arranged centralized maintenance system state parameter, is sent to automatic flight-control computer；
Step 6: execute [312], according to the requirement of test assignment, by operate the knob on automatic flight control assemblies,
Automatic flight control system state, parameter is arranged in key；
Step 7: entering each emulation branch [313] [314] [315] [316] [317]；
It executes [313], executes main flight-control computer emulation component, emulate main flight-control computer function and shape
State reads the director data that automatic flight-control computer is sent, according to flight control control law, according to present instruction
Data calculation is accordingly exported, and returns to automatic flight-control computer；
It executes [314], executes accelerator actuating mechanism emulation component, emulate accelerator actuating mechanism function and state, read from
The director data that dynamic flight-control computer is sent, according to accelerator actuating mechanism control algolithm, according to present instruction data calculation
It is accordingly exported, and returns to automatic flight-control computer；
It executes [315], executes passback actuator emulation component, emulation passback actuator function and state, read automatic fly
The director data that row control computer is sent obtains phase according to present instruction data calculation according to passback actuator control algolithm
It should export, and return to automatic flight-control computer；
It executes [316], the style and content of simulated flight status display interface, receives automatic flight-control computer and send
Flight Condition Data information, and shown according to on-board data information display styles, format；
It executes [317], emulates airborne centralized maintenance system function, receive automatic flight-control computer and be sent in airborne
The data information of maintenance system is entreated, and is shown according to on-board data information display styles, format, or is emulated in airborne
Maintenance system function is entreated, Xiang Zidong flight-control computer sends data command；
Step 8: executing [318], read automatic flight control system status parameter；
Step 9: it executes [319], parses automatic flight control system state parameter, the state parameter after showing parsing, with
And analysis data result；
Step 10: executing [320], the analysis obtained according to step 9 is as a result, decide whether to continue to execute experimental test, such as
Fruit is to then follow the steps 3, otherwise, executes step 11；
Step 11: executing [321], terminate to execute.
Claims (1)
1. a kind of test macro of automatic flight control system, including for completing automatic flight-control computer crosslinking signal inspection
The automatic flight control system signal of survey transmits disconnection device (1), 1553B data bus coupler (2), ARINC-429 data
Bus coupler (3), automatic flight control system test interface device (4) and accelerator actuating mechanism emulator (5), longitudinal direction
Return actuator emulator (6), laterally passback actuator emulator (7), course passback actuator emulator (8), main flight control
Computer simulator (9) processed, air data system emulator (10), inertial navigation system emulator (11), Low-altitude Radio altimeter
Emulator (12), flight management system emulator (13), centralized maintenance system emulator (14), state of flight show emulator
(15), engine parameter system simulator (16), wherein longitudinal passback actuator emulator (6) includes longitudinal passback actuator
Interface signal emulation board and longitudinal passback actuator model component, it is longitudinal by longitudinally returning the emulation of actuator interface signal emulation board
Actuator interface signal physical characteristic is returned, is generated under the operation control of longitudinally passback actuator model component and meets longitudinal return
Pass the feedback signal of actuator interface features and logical relation；
Laterally passback actuator emulator (7) includes laterally passback actuator interface signal emulation board and laterally passback actuator mould
Type component, by laterally returning actuator interface signal emulation board emulation laterally passback actuator interface signal physical characteristic, in cross
Lower generate of operation control for returning back actuator model component meets the anti-of laterally passback actuator interface features and logical relation
Feedback signal；
Course passback actuator emulator (8) includes course passback actuator interface signal emulation board and course passback actuator mould
Type component returns actuator interface signal physical characteristic by course passback actuator interface signal emulation board emulation course, is navigating
Lower generate of operation control for returning back actuator model component meets the anti-of course passback actuator interface features and logical relation
Feedback signal；
Main flight-control computer emulator (9) includes 1553B data bus interface plate and main flight-control computer model group
Part realizes the communication with automatic flight-control computer AFCC by 1553B data bus interface plate, in main flight-control computer
The operation control of model component is lower to receive the order letter that automatic flight-control computer AFCC is sent by 1553B data/address bus
Number, the function and control law algorithm of main flight-control computer are emulated, the status information for indicating implementing result is passed through into 1553B number
It returns again to according to bus to automatic flight-control computer AFCC；
Air data system emulator (10) includes ARINC-429 data bus interface plate and air data system model component,
Air data system state parameter is set, air data system simulation algorithm is executed, write operation controls ARINC-429 data/address bus
The air data system state parameter of current setting is sent to automatic flight control by ARINC-429 data/address bus by interface board
Computer AFCC processed；
Inertial navigation system emulation emulator (11) includes ARINC-429 data bus interface plate and INS model component, setting
Inertial system state parameter, executes inertial navigation system simulation algorithm, and write operation controls ARINC-429 data bus interface plate, passes through
The inertial system state parameter of current setting is sent to automatic flight-control computer AFCC by ARINC-429 data/address bus；
Low-altitude Radio altimeter emulator (12) includes ARINC-429 data bus interface plate and Low-altitude Radio altimeter mould
Low-altitude Radio altimeter state parameter is arranged in type component, executes Low-altitude Radio altimeter simulation algorithm, write operation control
ARINC-429 data bus interface plate, by ARINC-429 data/address bus by the Low-altitude Radio height table status of current setting
Parameter is sent to automatic flight-control computer AFCC；
Flight management system emulator (13) includes ARINC-429 data bus interface plate and flight management system model component,
Flight management system state parameter is set, flight management system simulation algorithm is executed, write operation controls ARINC-429 data/address bus
The flight management system state parameter of current setting is sent to automatic flight control by ARINC-429 data/address bus by interface board
Computer AFCC processed；
Centralized maintenance system emulator (14) includes ARINC-429 data bus interface plate and centralized maintenance system model component,
It receives the data information that automatic flight-control computer AFCC is sent to airborne centralized maintenance system to be shown, or emulation
Airborne centralized maintenance system function, Xiang Zidong flight-control computer AFCC send data command；
State of flight shows that emulator (15) include ARINC-429 data bus interface plate and state of flight display model component,
It executes state of flight and shows simulation algorithm, the style and content of simulated flight status display interface receive automatic flight control meter
Calculation machine AFCC is sent to the data information of onboard flight status displays, and is shown；
Engine parameter system emulation emulator (16) includes ARINC-429 data bus interface plate and engine parameter system mould
Engine parameter system status parameters are arranged in type component, execute engine parameter simulation algorithm, and write operation controls ARINC-
429 data bus interface plates are sent the engine parameter system status parameters of current setting by ARINC-429 data/address bus
To automatic flight-control computer AFCC；
Be equipped with based on testing and control bus or computer bus (202), by test emulation controller (201), RVDT or
LVDT signal interface board (203), 1553B data bus interface plate (204), ARINC-429 data bus interface plate (205) composition
Automatization test system, test emulation controller (201) realized by test equipment bus or computer bus (202) to upper
State the control of all kinds of interface boards.
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