CN106598032A - Test system of automatic flight control system - Google Patents
Test system of automatic flight control system Download PDFInfo
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Abstract
The invention discloses a test system of an automatic flight control system, and belongs to the aviation engineering test field. The test system is characterized by comprising an automatic flight control signal transmission connecting and disconnecting device for detecting crosslinking signals of an automatic flight control computer, an airborne data bus coupler, an automatic flight control system test interface device, a throttle implementation mechanism, a return actuator, an emulator of a master flight control computer, an air data system emulator, an inertial navigation system emulator, a radio altimeter emulator, a flight management system emulator, a flight state display emulator, an engine parameter system emulator, and test application software. Emulation of crosslinking airborne equipment in an automatic flight control system test can be realized, and a test on the automatic flight control system can be carried out.
Description
Technical field
The present invention relates to a kind of test system of automatic flight control system, the particularly test of automatic flight control system
System and method, belong to aeronautical engineering field tests.
Background technology
Automatic flight control system is aircraft critical function system, replaces pilot to realize automatically controlling aircraft, with
Other function system cooperation of aircraft are to be better carried out aerial mission.Automatic flight control system includes flight automatically
Control device (AFCU), automatic flight-control computer (AFCC), passback actuator device etc., automatic flight-control computer
(AFCC) command information of automatic flight control assemblies (AFCU) is received, and from flight management system, air data system, used
The parameter information synthesis such as guiding systems, Low-altitude Radio altimeter, generate the order of the main flight-control computer (PFC) of control, lead to
Cross data/address bus and be sent to main flight-control computer (PFC), the control to airplane motion attitude is realized, so as to complete to aircraft
The control of flight path, and will the driving cabin control command as corresponding to giving main flight-control computer (PFC) command parameter it is big
Little, control passback actuator motion is in the same size with driving cabin 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
With the parameter information synthesis from engine parameter system, control engine throttle instruction is generated, control accelerator actuating mechanism, it is real
Now to the control of airplane motion attitude, so as to complete the control to aircraft flight path.
In above-mentioned control aircraft in-flight, the parameter such as position, attitude of aircraft flight is by automatic flight-control computer
(AFCC) it is sent to state of flight display to be shown, is easy to pilot's Real Time Observation prison to show position, the attitude of aircraft flight
Deng parameter information.
In the development and design of aircraft, particularly carrying out aircraft critical function system --- automatic flight control system sets
During meter is developed, generally require to carry out a variety of tests, such as：Automatically the component test of flight-control computer, automatically flight
Control system synthesises test, automatic flight control system iron bird integration test etc..In above-mentioned test, it usually needs right according to testing
As --- automatic flight-control computer or automatic flight control system, corresponding experimental test environment is developed, 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 gear ratio
Inspection, work-based logic inspection, system control function inspection, system static and dynamic performance are checked, alert the correlations such as display function inspection
Experiment work.
Above-mentioned experimental test environment is often directed to single subjects --- and automatic flight-control computer flies automatically
Row control system separately designs construction, and design-build of experimental test environment is completed, can only used as overall time.Such as
Automatically during flight-control computer experimental test environment is built, the instrument and equipment for using numerous single functions is needed, such as using letter
Number generator emulation accelerator actuating mechanism, passback actuator signal, using digital multimeter, oscillograph, data acquiring and recording system
The equipment such as system complete to be crosslinked interface analog quantity, digital quantity, the acquisition and recording of on-off model.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,
Once it is only capable of emulating single signal or carries out the single step emulation of pumping signal, is applied in combination the instrument and equipment of numerous single functions,
Operating process is complicated, loaded down with trivial details, inefficiency, and due to being limited by experimental enviroment condition, is only capable of completing part test test
Content.Or automatic flight control system compbined test, automatic flight control system iron bird integration test test environment are built
In, although it is configured with accelerator actuating mechanism, passback actuator, air data system, inertial navigation around automatic flight-control computer
System, Low-altitude Radio altimeter etc., its complex process, enforcement difficulty is big, causes cost also very high, and does not have versatility.
Experimental test process still needs the instrument and equipment for being applied in combination numerous single functions, same complicated, loaded down with trivial details, the efficiency of operating process
Lowly.
The content of the invention
The purpose of the present invention is：It is the test system 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 is emulated, and completes the automatization of automatic flight control system test.
The technical scheme is that:A kind of test system of automatic flight control system, including automatically winged for completing
Row control computer is crosslinked automatic flight control system signal transmission disconnection device [1], the 1553B data/address bus couplings of signal detection
Clutch [2], ARINC-429 data bus couplers [3], automatic flight control system test interface device [4], and throttle are held
Row mechanism simulation device [5], laterally longitudinal direction passback actuator emulator [6], passback actuator emulator [7], course passback start
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 direction passback actuator emulation
Device [6] includes longitudinal direction passback actuator interface signal emulation board and longitudinal direction passback actuator model component, by longitudinally returning start
Device interface signal emulation board emulation longitudinal direction passback actuator interface signal physical characteristics, in longitudinally passback actuator model component
Operation control is lower to produce the feedback signal for meeting longitudinal direction passback actuator interface features and logical relation；
Laterally passback actuator emulator [7] includes laterally passback actuator interface signal emulation board and laterally passback start
Device model component, by the emulation of actuator interface signal emulation board is laterally returned actuator interface signal physical characteristics are laterally returned,
Produce under the operation control of laterally passback actuator model component and meet laterally passback actuator interface features and logical relation
Feedback signal；
Course passback actuator emulator [8] returns actuator interface signal emulation board and course passback start including course
Device model component, by course passback actuator interface signal emulation board emulation course passback actuator interface signal physical characteristics,
Produce under the operation control that course returns actuator model component and meet course passback actuator interface features and logical relation
Feedback signal；
Main flight-control computer emulator [9] includes 1553B data bus interfaces plate and main flight-control computer mould
Type component, by 1553B data bus interfaces plate the communication with automatic flight-control computer AFCC is realized, in main flight control meter
The operation control of calculation machine model component is lower to receive the order that automatic flight-control computer AFCC sends by 1553B data/address bus
Signal, emulates the function and control law algorithm of main flight-control computer, and the status information that would indicate that implementing result passes through 1553B
Data/address bus is returned again to automatic flight-control computer AFCC；
Air data system emulator [10] includes ARINC-429 data bus interfaces plate and air data system model group
Part, arranges air data system state parameter, performs air data system simulation algorithm, write operation control ARINC-429 data
Bus interface board, the air data system state parameter of current setting is sent to fly automatically by ARINC-429 data/address bus
Row control computer AFCC；
Inertial navigation system emulates emulator [11] including ARINC-429 data bus interfaces plate and INS model component,
Inertial system state parameter is set, inertial navigation system simulation algorithm is performed, write operation controls ARINC-429 data bus interface plates,
The inertial system state parameter of current setting is sent to by automatic flight-control computer by ARINC-429 data/address bus
AFCC；
Low-altitude Radio altimeter emulator [12] includes ARINC-429 data bus interfaces plate and Low-altitude Radio height
Table model component, arranges Low-altitude Radio altimeter state parameter, performs Low-altitude Radio altimeter simulation algorithm, write operation control
ARINC-429 data bus interfaces 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 interfaces plate and flight management system model group
Part, arranges flight management system state parameter, performs flight management system simulation algorithm, write operation control ARINC-429 data
Bus interface board, the flight management system state parameter of current setting is sent to fly automatically by ARINC-429 data/address bus
Row control computer AFCC；
Centralized maintenance system emulator [14] includes ARINC-429 data bus interfaces plate and centralized maintenance system model group
Part, receives the data message that automatic flight-control computer AFCC is sent to airborne centralized maintenance system and is shown, or
Airborne centralized maintenance system function is emulated, to automatic flight-control computer AFCC data command is sent；
State of flight shows emulator [15] including ARINC-429 data bus interfaces plate and state of flight display model group
Part, performs state of flight and shows simulation algorithm, and the style and content of simulated flight status display interface receive flight control automatically
Computer AFCC is sent to the data message of onboard flight status displayies, and is shown；
Engine parameter system emulation emulator [16] includes ARINC-429 data bus interfaces plate and engine parameter system
System model component, arranges engine parameter system status parameters, performs engine parameter simulation algorithm, write operation control
ARINC-429 data bus interface plates, are 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 boards [203], 1553B data bus interface plates [204], ARINC-429 data bus interface plate [205] groups
Into automatization test system, it is right that test emulation controller [201] is realized by test instrunment bus or computer bus [202]
The control of above-mentioned all kinds of interface boards；
The advantages of the present invention are：
(1) compact, reliable operation rational in infrastructure, using the interface model of high reliability, through optimization design, modularity,
Standardization and seriation, adapts to be used in harsh electromagnetism and mechanical environment.
(2) excellent extensibility, tailorability and reusability, each simulation unit is 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, functionally equivalent to the function of original multiple special equipments, substantially reduce
Equipment cost.
(4) it is fully functional, easy to use, test efficiency is improve, the test period is shortened, reduce expense.
Description of the drawings
Fig. 1 is present invention composition structure chart；
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 couplers [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 direction passback start
Device emulator [6], laterally passback actuator emulator [7], course passback 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], send out
Motivation parameter system emulator [16].
Specific embodiment
With reference to the accompanying drawings and examples the present invention is described in detail.
The test system and its method of a kind of automatic flight control system, including for completing automatic flight-control computer
Crosslinking automatic flight control system signal transmission disconnection device [1] of signal detection, 1553B data bus couplers [2],
ARINC-429 data bus couplers [3], automatic flight control system test interface device [4], and accelerator actuating mechanism are imitated
True device [5], laterally longitudinal direction passback actuator emulator [6], passback actuator emulator [7], course passback 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, by accelerator actuating mechanism interface signal emulation board accelerator actuating mechanism interface signal physical characteristics are emulated, and are performed in throttle
The operation control of mechanism model component is lower to produce the feedback signal for meeting accelerator actuating mechanism interface features and logical relation.
Longitudinal direction passback actuator emulator [6] includes longitudinal direction passback actuator interface signal emulation board and longitudinal direction passback start
Device model component, by actuator interface signal emulation board emulation longitudinal direction is longitudinally returned actuator interface signal physical characteristics are returned,
Produce under the operation control of longitudinally passback actuator model component and meet longitudinal direction 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 start
Device model component, by the emulation of actuator interface signal emulation board is laterally returned actuator interface signal physical characteristics are laterally returned,
Produce under the operation control of laterally passback actuator model component and meet laterally passback actuator interface features and logical relation
Feedback signal；
Course passback actuator emulator [8] returns actuator interface signal emulation board and course passback start including course
Device model component, by course passback actuator interface signal emulation board emulation course passback actuator interface signal physical characteristics,
Produce under the operation control that course returns actuator model component and meet course passback actuator interface features and logical relation
Feedback signal.
Main flight-control computer emulator [9] includes 1553B data bus interfaces plate and main flight-control computer mould
Type component, by 1553B data bus interfaces plate the communication with automatic flight-control computer (AFCC) is realized, in main flight control
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, and the status information that would indicate that implementing result passes through
1553B data/address bus returns again to give automatic flight-control computer (AFCC).
Air data system emulator [10] includes ARINC-429 data bus interfaces plate and air data system model group
Part, arranges air data system state parameter, performs air data system simulation algorithm, write operation control ARINC-429 data
Bus interface board, the air data system state parameter of current setting is sent to fly automatically by ARINC-429 data/address bus
Row control computer (AFCC)；
Inertial navigation system emulates emulator [11] including ARINC-429 data bus interfaces plate and INS model component,
Inertial system state parameter is set, inertial navigation system simulation algorithm is performed, write operation controls ARINC-429 data bus interface plates,
The inertial system state parameter of current setting is sent to by automatic flight-control computer by ARINC-429 data/address bus
(AFCC)；
Low-altitude Radio altimeter emulator [12] includes ARINC-429 data bus interfaces plate and Low-altitude Radio height
Table model component, arranges Low-altitude Radio altimeter state parameter, performs Low-altitude Radio altimeter simulation algorithm, write operation control
ARINC-429 data bus interfaces 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 interfaces plate and flight management system model group
Part, arranges flight management system state parameter, performs flight management system simulation algorithm, write operation control ARINC-429 data
Bus interface board, the flight management system state parameter of current setting is sent to fly automatically by ARINC-429 data/address bus
Row control computer (AFCC)；
Centralized maintenance system emulator [14] includes ARINC-429 data bus interfaces plate and centralized maintenance system model group
Part, receives the data message that automatic flight-control computer (AFCC) is sent to airborne centralized maintenance system and is shown, or
It is the airborne centralized maintenance system function of emulation, to automatic flight-control computer (AFCC) data command is sent；
State of flight shows emulator [15] including ARINC-429 data bus interfaces plate and state of flight display model group
Part, performs state of flight and shows simulation algorithm, and the style and content of simulated flight status display interface receive flight control automatically
Computer (AFCC) is sent to the data message of onboard flight status displayies, and is shown.
Engine parameter system emulation emulator [16] includes ARINC-429 data bus interfaces plate and engine parameter system
System model component, arranges engine parameter system status parameters, performs engine parameter simulation algorithm, write operation control
ARINC-429 data bus interface plates, are 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 plates [204], ARI NC-429 data/address bus
The automatization test system of interface board [205] composition, test emulation controller [201] is total by test instrunment bus or computer
Line [202] realizes the control to above-mentioned all kinds of interface boards [203] [204] [205].
Fully functional, reliable operation test emulation controller [201] is equipped with, the operation of Simulation Application software is supported, it is complete
In pairs the state of all kinds of emulation interface plates [203] [204] [205] is arranged and operational control, realizes that RVDT (or LVDT) signal is defeated
Enter measurement or simulation data, and on-board data information is received, monitoring or emulation send；
Fully functional, reliable operation RVDT (or LVDT) signal interface board [203] is equipped with, is calculated in flight control automatically
In machine or automatic flight control system test, emulation accelerator actuating mechanism, laterally longitudinal direction passback actuator, passback actuator, boat
The RVDT signals of actuator internal sensor are returned back, to automatic flight-control computer RVDT (or LVDT) signal input is provided
Excitation；
Fully functional, reliable operation 1553B data bus interface plates [204] are equipped with, are realized and flight control meter automatically
The communication of calculation machine, receives the 1553B bus data information that automatic flight-control computer sends output, and to flight control automatically
Computer processed sends 1553B bus data information；
Fully functional, reliable operation ARINC-429 data bus interface plates [205] are equipped with, are realized and flight control automatically
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 message of ARINC-429 buses.
It is equipped with fully functional, reliable operation detection application software, there is provided someone-machine operation interface function, simulation status
With parameter setting function, phantom operation control function, simulation model library and management function, accelerator actuating mechanism emulation work(
Energy, longitudinal passback actuator copying, horizontal passback actuator copying, course return actuator copying, master and fly
Row control computer copying, air data system copying, inertial navigation system copying, Low-altitude Radio altimeter are imitated
True function, flight management system copying, centralized maintenance system copying, state of flight show copying, electromotor
Parameter system copying, correspondence above-mentioned functions develop special software module and realize its function；
People-machine operation interface assembly module [213] provides the mode and means of people-machine operation, by component software bus
[212] scheduling performs simulation status and runs control assembly module [215], imitates with parameter setting assembly module [214], phantom
True mode storehouse 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 show emulation mould
Block, engine parameter system simulation module；
Simulation status realize selection and the parameter setting of simulation status with parameter setting assembly module [214], select emulation
Model state, there is provided each phantom |input paramete；
Simulation model library and management assembly module [215] complete foundation, maintenance, renewal, management of simulation model library etc., just
Each phantom calls execution in phantom runs control assembly module to model library；
Phantom operation control assembly module [216] needs according to automatic flight control system test, calls corresponding
Phantom performs model algorithm, and control emulation interface plate [203] [204] [205] produces simulation excitation signal, or sends out
Send/receiving data bus message；
Accelerator actuating mechanism emulation module [217] needs according to automatic flight control system test, calls throttle to perform machine
Structure phantom performs model algorithm, obtains the RVDT signal magnitudes corresponding to current throttle position, controls RVDT signal simulations
Interface board, produces accelerator actuating mechanism position emulation signal to automatic flight-control computer (AFCC)；
Passback actuator emulation module [218] needs according to automatic flight control system test, calls passback actuator to imitate
True mode performs model algorithm, is currently returned the RVDT signal magnitudes corresponding to position, controls RVDT signal simulation interfaces
Plate, produces passback actuator position emulation signal to automatic flight-control computer (AFCC)；
Main flight-control computer emulation module [219] needs according to automatic flight control system test, calls main flight
Control computer phantom performs model algorithm, and by 1553B data/address bus automatic flight-control computer (AFCC) is received
The command signal of transmission, emulates the function and control law algorithm of main flight-control computer, would indicate that the state letter of implementing result
Breath returns again to give automatic flight-control computer (AFCC) by 1553B data/address bus.
Air data system emulation module [220] needs according to automatic flight control system test, calls atmosphere data system
System phantom performs model algorithm, needs to arrange air data system state parameter, write operation control according to current test
ARINC-429 data bus interface plates, 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] needs according to automatic flight control system test, calls inertial navigation system to emulate mould
Type performs model algorithm, needs to arrange inertial system state parameter according to current test, and write operation control ARINC-429 data are total
Line interface plate, flight control automatically is sent to by ARINC-429 data/address bus by the inertial system state parameter of current setting
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 phantom performs model algorithm, needs to arrange Low-altitude Radio altimeter state parameter according to current test,
Write operation controls ARINC-429 data bus interface plates, 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] needs according to automatic flight control system test, calls flight management system
System phantom performs model algorithm, needs to arrange flight management system state parameter, write operation control according to current test
ARINC-429 data bus interface plates, 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] needs according to automatic flight control system test, emulates airborne central authorities' dimension
Protecting system function, the data message that the automatic flight-control computer (AFCC) of reception is sent to airborne centralized maintenance system is shown
Show, or emulate airborne centralized maintenance system function, to automatic flight-control computer (AFCC) data command is sent；
State of flight shows that emulation component module [225] needs according to automatic flight control system test, simulated flight shape
The style and content of state display interface, receives automatic flight-control computer (AFCC) and is sent to onboard flight status displayies
Data message, and shown.
Engine parameter system simulation module [226] needs according to automatic flight control system test, calls electromotor to join
Number system phantom performs model algorithm, needs to arrange engine parameter system status parameters, write operation according to current test
Control ARINC-429 data bus interface plates, 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 system and its embodiment of the method for a kind of automatic flight control system of the present invention, test emulation controller
[201] using the NI PXI-8108 embedded controllers of NI (National Instruments Inc.) company；
Test instrunment bus ＆ computer bus [202] using PXI buses, from NI (National Instruments
Inc.) company NI PXI-1045 cabinets, support PXI bus functionalitys；
RVDT signal interface boards [203] are using NAI companies NAI (North Atlantic Industries Inc.) 75C3
Board, completes the simulation to RVDT signals, and output produces command signal, feedback signal；
1553B data bus interface plates [204] using Alta Data Technologies companies CPCIC3/6-
1553-1F/2F/3F/4F-T boards, complete the transmission to 1553B bus data information, or complete 1553B bus datas
Information is received；
ARINC-429 data bus interface plates [205] using Alta Data Technologies companies CPCIC3/6-
A429-30-T boards, complete the transmission to ARINC-429 bus data information, or complete ARINC-429 number of buses it is believed that
Breath is received；
Accelerator actuating mechanism adapter [206], laterally longitudinal direction passback actuator adapter [207], passback actuator adaptation
Device [208], course passback actuator adapter [209] are using the component for being configured with multicore aviation socket；
1553B data bus couplers [210] are using 8 mouthfuls of 1553B data bus couplers；
ARINC-429 data bus couplers [211] are adopted and are configured with multicore aviation connector.
The features described above of the present invention can be changed as shown below, but they are all without departing from the essence of the present invention.
Such as, NI PXI-8108 of the control unit [1] using NI (National Instruments Inc.) company is run
Outside embedded controller, it is also possible to select the embedded controller of other model PXI buses of NI companies, it is also an option that other are public
The embedded controller of the PXI buses of department；
RVDT signal interface boards [203] are except using NAI companies NAI (North Atlantic Industries Inc.)
75C3 boards, it is also possible to select NAI companies NAI 75DL1 boards, it is also an option that the RVDT signal simulation boards of other companies；
Further, for the emulation of RVDT signals, except using NAI (North Atlantic Industries Inc.)
75C3 boards, it is also possible to select the NI PXI-7851R boards of NI companies, can adopt existing market supply other models or
The interface models of ATSIM-LVDT 2024 that other type RVDT command signal interface models, such as ATENA companies are provided, North
The Model cPCI-75DL1 3U interface models that Atlantic Industries Inc. companies provide, Axiomatic
The LVDTS-DR-02 interface models that Technologies Corporation companies provide, United Electronic
The DNA/DNR-AI-254 interface models that Industries Inc. companies provide, or other company's productions can also be selected
The RVDT command signal interface models of other models, it is of course also possible to designed, designed develops RVDT command signal interface models.
1553B data bus interface plates [204] is using Alta Data Technologies company CPCIC3/6-1553-
Outside 1F/2F/3F/4F-T boards, it is also possible to select other boards of Alta Data Technologies companies, it is also an option that its
The 1553B data bus interface boards of its company；
ARINC-429 data bus interface plates [204] is using Alta Data Technologies company CPCIC3/6-
Outside A429-30-T boards, it is also possible to other boards of Alta Data Technologies companies are selected, it is also an option that other are public
The ARINC-429 data bus interface boards of department；
Test instrunment bus ＆ computer bus [202] is except using PXI buses, it is also possible to select VXI, LXI instrument controlling total
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 its implementation of the automatic flight control system of the present invention, including it is following in detail
Thin step：
Step 1：System is performed and starts [301], and according to experimental test the completing of the task is needed, initialization test system, if
Put the original state of test system；
Step 2：Perform [302], initializing signal interface board, data bus communication interface plate, each interface board, data are set
The initial output value of bus communication interface plate；
Step 3：Perform [303], read simulation status parameter；
Step 4：Perform [304], the initial parameter of phantom is set；
Step 5：Into each emulation branch [305] [306] [307] [308] [308] [310] [311]；
Perform [305], perform main flight-control computer emulation component, emulate main flight-control computer function and shape
State, according to the requirement of test assignment, arranges main flight-control computer state parameter, is sent to automatic flight-control computer；
Perform [306], air data system emulation component, emulation air data system function and state are performed, according to survey
The requirement of trial business, arranges air data system state parameter, is sent to automatic flight-control computer；
Perform [307], inertial navigation system emulation component, emulation inertial navigation system function and state are performed, according to test assignment
Require, inertial system state parameter is set, be sent to automatic flight-control computer；
Perform [308], perform Low-altitude Radio altimeter emulation component, emulation Low-altitude Radio height table function and shape
State, according to the requirement of test assignment, arranges Low-altitude Radio altimeter state parameter, is sent to automatic flight-control computer；
Perform [309], flight management system emulation component, simulated flight management system function and state are performed, according to survey
The requirement of trial business, arranges flight management system state parameter, is sent to automatic flight-control computer；
Perform [310], perform 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；
Perform [311], centralized maintenance system emulation component, emulation centralized maintenance system function and state are performed, according to survey
The requirement of trial business, arranges centralized maintenance system state parameter, is sent to automatic flight-control computer；
Step 6：Perform [312], according to the requirement of test assignment, by operate knob on automatic flight control assemblies,
Button, arranges automatic flight control system state, parameter；
Step 7：Into each emulation branch [313] [314] [315] [316] [317]；
Perform [313], perform main flight-control computer emulation component, emulate main flight-control computer function and shape
State, reads the director data that automatic flight-control computer sends, according to flight control control law, according to present instruction
Data calculation is accordingly exported, and returns to automatic flight-control computer；
Perform [314], perform accelerator actuating mechanism emulation component, emulation accelerator actuating mechanism function and state, read from
The director data that dynamic flight-control computer sends, according to accelerator actuating mechanism control algolithm, according to present instruction data calculation
Accordingly exported, and returned to automatic flight-control computer；
Perform [315], perform passback actuator emulation component, emulation passback actuator function and state, read and fly automatically
The director data that row control computer sends, according to passback actuator control algolithm, according to present instruction data calculation phase is obtained
Should export, and return to automatic flight-control computer；
Perform [316], the style and content of simulated flight status display interface, receive automatic flight-control computer and send
Flight Condition Data information, and shown according to on-board data presentation of information style, form；
Perform [317], emulate airborne centralized maintenance system function, receive automatic flight-control computer be sent to it is airborne in
The data message of centre maintenance system, and shown according to on-board data presentation of information style, form, or during emulation is airborne
Centre maintenance system function, to automatic flight-control computer data command is sent；
Step 8：Perform [318], read automatic flight control system status parameter；
Step 9：Perform [319], parse automatic flight control system state parameter, show the state parameter after parsing, with
And analytical data result；
Step 10：Perform [320], according to the analysis result that step 9 is obtained, decide whether to continue executing with experimental test, such as
Fruit is then execution step 3, otherwise, execution step 11；
Step 11：Perform [321], terminate to perform.
Claims (1)
1. a kind of test system of automatic flight control system, including for completing automatic flight-control computer signal inspection is crosslinked
Automatic flight control system signal transmission disconnection device [1] of survey, 1553B data bus couplers [2], ARINC-429 data
Bus coupler [3], automatic flight control system test interface device [4], and accelerator actuating mechanism emulator [5], longitudinal direction
Passback 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 direction passback actuator emulator [6] includes longitudinal direction passback actuator
Interface signal emulation board and longitudinal direction passback actuator model component, by actuator interface signal emulation board is longitudinally returned longitudinal direction is emulated
Passback actuator interface signal physical characteristics, the generation under the operation control of longitudinally passback actuator model component meets longitudinal direction and returns
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 actuator interface signal emulation board emulation laterally passback actuator interface signal physical characteristics are laterally returned, in horizontal stroke
The lower generation 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] returns actuator interface signal emulation board and course passback actuator mould including course
Type component, by course passback actuator interface signal emulation board emulation course passback actuator interface signal physical characteristics, in boat
The lower generation 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 interfaces plate and main flight-control computer model group
Part, realizes the communication with automatic flight-control computer AFCC, in main flight-control computer by 1553B data bus interfaces plate
The operation control of model component is lower to receive the order letter that automatic flight-control computer AFCC sends by 1553B data/address bus
Number, the function and control law algorithm of main flight-control computer are emulated, the status information that would indicate that implementing result passes through 1553B numbers
Return again to automatic flight-control computer AFCC according to bus；
Air data system emulator [10] includes ARINC-429 data bus interfaces plate and air data system model component,
Air data system state parameter is set, air data system simulation algorithm, write operation control ARINC-429 data/address bus is performed
Interface board, flight control automatically is sent to by ARINC-429 data/address bus by the air data system state parameter of current setting
Computer AFCC processed；
Inertial navigation system emulation emulator [11] includes ARINC-429 data bus interfaces plate and INS model component, arranges
Inertial system state parameter, performs inertial navigation system simulation algorithm, and write operation control ARINC-429 data bus interface plates pass 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 interfaces plate and Low-altitude Radio altimeter mould
Type component, arranges Low-altitude Radio altimeter state parameter, performs Low-altitude Radio altimeter simulation algorithm, write operation control
ARINC-429 data bus interface plates, 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 interfaces plate and flight management system model component,
Flight management system state parameter is set, flight management system simulation algorithm, write operation control ARINC-429 data/address bus is performed
Interface board, flight control automatically is sent to by ARINC-429 data/address bus by the flight management system state parameter of current setting
Computer AFCC processed；
Centralized maintenance system emulator [14] includes ARINC-429 data bus interfaces plate and centralized maintenance system model component,
Receive the data message that automatic flight-control computer AFCC is sent to airborne centralized maintenance system to be shown, or emulation
Airborne centralized maintenance system function, to automatic flight-control computer AFCC data command is sent；
State of flight shows emulator [15] including ARINC-429 data bus interfaces plate and state of flight display model component,
Perform state of flight and show simulation algorithm, the style and content of simulated flight status display interface receive flight control meter automatically
Calculation machine AFCC is sent to the data message of onboard flight status displayies, and is shown；
Engine parameter system emulation emulator [16] includes ARINC-429 data bus interfaces plate and engine parameter system mould
Type component, arranges engine parameter system status parameters, performs engine parameter simulation algorithm, write operation control 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 boards [203], 1553B data bus interface plates [204], ARINC-429 data bus interface plates [205] compositions
Automatization test system, test emulation controller [201] realized to upper by test instrunment bus or computer bus [202]
State the control of all kinds of interface boards.
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| CN107132773A (en) * | 2017-07-06 | 2017-09-05 | 中国航空工业集团公司西安飞机设计研究所 | A kind of airborne central maintenance application software checking system and method |
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