CN206975428U - A kind of flight control system experimental rig - Google Patents
A kind of flight control system experimental rig Download PDFInfo
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- CN206975428U CN206975428U CN201720047541.9U CN201720047541U CN206975428U CN 206975428 U CN206975428 U CN 206975428U CN 201720047541 U CN201720047541 U CN 201720047541U CN 206975428 U CN206975428 U CN 206975428U
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Abstract
The utility model discloses a kind of fly-by-wire flight control system experimental rig based on virtual instrument technique.The experimental rig is made up of hardware system and software systems two parts, its hardware system is made up of slave computer and host computer two parts, slave computer includes the modules such as pumping signal output hardware module, rudder face response signal acquisition hardware module, sensor response signal acquisition hardware module, data transmission bus and the next machine controller, main to complete the functions such as digital stimulus signal produces, response signal gathers, signal analysis resolves；Host computer includes trystate communication hardware module and man-machine interaction computer, realizes human-computer interaction function.The utility model advantage is directly to be crosslinked using redundance number bus between experimental rig and flight control computer, the problems such as avoiding signal amplitude decay, wave distortion, improves the accuracy of result of the test.
Description
Technical field
Patent of the present invention is related to a kind of vehicle flight control system experimental rig, is a kind of be based on virtually specifically
The experimental rig that can be used for the time domain response of aircraft fly-by-wire flight control system and frequency response test of technical device.
Background technology
Fly-by-wire flight control system time domain response and frequency response test are customary ground experiments before aircraft is taken a flight test, including
Ground time domain response experiment, Steady settlement experiment etc., it is main to measure each loop dynamic characteristic of flight control system, so as to according to examination
Data are tested to assess the dynamic characteristic of flight control system.
At present, fly-by-wire flight control system time domain and frequency response test produce flight using frequency response analyzer mostly
Control system swept frequency excitation signal, and the response signal of flight control system is gathered simultaneously, resolved by frequency response analyzer
Obtain the dynamic characteristic numerical value of flight control system.System tester, analog/digital conversion device sum are needed during experiment
Word/Simulation Conversion Assembly etc. realizes the interconnection of signals of frequency response analyzer and flight control computer, causes cable between experimental rig
Connect more complicated, cause signal attenuation, wave distortion and signal noise, reduce the signal to noise ratio of experiment process collection signal, make
Into result of the test accuracy.
The content of the invention
(1) goal of the invention
The present invention proposes a kind of fly-by-wire flight control system experimental rig based on virtual instrument technique, avoids using existing
There are frequency response analyzer, system tester, analog/digital conversion device, D/A conversion device and test cable to cause
Signal amplitude decay, wave distortion the problems such as, improve the standard of fly-by-wire flight control system time domain and frequency domain response result of the test
True property.
(2) inventive technique scheme
Fly-by-wire flight control system experimental rig proposed by the present invention includes two parts of hardware system and software systems, leads to
Cross the collaborative work of hardware system and software systems, realize flight control system time domain and frequency domain response attribute testing, analysis with
Evaluation.
The experimental rig hardware system structure as shown in figure 1, the experimental rig by host computer and slave computer two parts group
Into.Wherein slave computer includes pumping signal output hardware module 11, rudder face response signal acquisition hardware module 12, sensor response
Signal acquisition hardware module 13, flight control system state acquisition hardware module 14, data transmission bus 15 and the next machine controller 16,
It is main to complete the functions such as digital stimulus signal produces, response signal gathers, signal analysis resolves.Host computer leads to including trystate
Hardware module 17 and man-machine interaction computer 18 are interrogated, realizes human interface function, there is provided man machine operation interface, receives user's input
State of flight point information, pumping signal information, control command etc., and the information such as display data result graph curve realizes people
Machine interactive function.
Wherein, pumping signal output hardware module 11, rudder face response signal acquisition hardware module 12, sensor response signal
Acquisition hardware module 13 and the redundant configurations identical with experiment flight control system holding of flight control system state acquisition hardware module 14.Excitation
Signal output hardware module 11 is connected using digital communication bus with flight control computer, is that flight control system time domain and frequency domain response try
Test and be injected separately into square wave and sine wave numeral swept frequency excitation signal.Rudder face response signal acquisition hardware module 12 uses digital communication
Bus is connected with flight control computer, completes the collection of flight control system rudder face response signal.Sensor response signal acquisition hardware mould
Block 13 is connected using digital communication bus with flight control computer, completes the collection of the sensor response signals such as gyro, accelerometer.Fly
Control system mode acquisition hardware module 14 is connected with flight control computer, completes flight control system alarm failure status information capture.Under
Position machine controller 16 is rung by the data transmission bus 15 of slave computer cabinet mainboard with pumping signal output hardware module 11, rudder face
Induction signal acquisition hardware module 12, sensor response signal acquisition hardware module 13, flight control system state acquisition hardware module 14
Communication.Trystate communication hardware module 17 and the comprehensive control replicating machine of iron bird testing stand are connected, and realize pilot fight state
The setting of information.Man-machine interaction computer 18 realizes the functions such as man-machine interaction, test data analyzer and storage.
The pumping signal output hardware module 11, rudder face response signal acquisition hardware module 12, sensor response signal
Acquisition hardware module 13 and the redundant configurations identical with experiment flight control system holding of flight control system state acquisition hardware module 14.More than
The signal of each module output and collection is redundance digital signal, by effectively can be rejected after remaining voting process in signal
Singular value, improve result of the test accuracy.
The pumping signal output hardware module 11 is the digital pumping signal needed for flight control system experiment injection.Excitation
Signal can choose different waveforms according to pilot project, choose square wave digital stimulus signal during the response test of city when carrying out, enter
Sine wave digital stimulus signal is chosen when line frequency domain response is tested.
The pumping signal and rudder face response signal acquisition hardware module 12 that the pumping signal output hardware module 11 exports
The response signal gathered with sensor response signal acquisition hardware module 13 is digital signal, effectively prevent to be put to the test and sets
Caused by standby and live electromagnetic interference the problems such as signal amplitude decay, wave distortion, so as to improve the accuracy of result of the test.
The present invention software system structure as shown in Fig. 2 including:Pumping signal produces software module 21, rudder face response letter
Number acquisition software module 22, sensor response signal acquisition software module 23, flight control system status monitoring software module 24, experiment
State sets software module 25, trystate bitcom module 26, Process flowchart software module 27, signal remaining voting software
Module 28, test data analyzer software module 29 and experimental data base 30.Wherein pumping signal generation software module 21 passes through people
Machine interactive interface selectes each state of flight point pumping signal type (time domain response experiment selection square-wave signal, frequency by testing crew
Sine wave signal is chosen in rate response test), and the parameters such as amplitude, frequency range, frequency sweep time, caused numeral are set
Formula pumping signal, flight control computer will be directly injected into by digital bus.Rudder face response signal acquisition software module 22 is completed
Flight control system rudder face response signal gathers, and call signal remaining voting software module 28 rejects the singular value in signal, carries out
Smoothing processing.Sensor response signal acquisition software module 23 completes pitch rate, Rolling Velocity Aerocraft, yaw speed, normal g-load
Etc. signal acquisition, and call signal remaining voting software module 28 rejects the singular value in signal, is smoothed.Fly control system
System status monitoring software module 24 is monitored to flight control system alarm failure state, abort during malfunction.Test shape
State sets software module 25 to complete the parameter settings such as each state of flight height, Mach number, static pressure, dynamic pressure, configuration.Process flowchart is soft
Part module 27 presets information by testing crew, controls each software module to run, realizes the automatic continuous of more state of flight points
Experiment.Test data analyzer software module 29 completes rudder face response and sensor response signal resolves, drawing system time domain or frequency
Rate resonse characteristic.Test data and analysis result for measuring etc. are stored in experimental data base 30, are converged for experiment post analysis
Always.
The experimental rig software systems are based on Development of Virtual Instrument, using current ripe Virtual Instrument Development system
Unified editing journey, the open system framework of ripe Virtual Instrument Development system is fully inherited, is easy to safeguard, is easy to upgrade, had good
Good Universal and scalability.
The trystate sets software module 25 to be drawn by man-machine interaction circle by testing crew in flight envelope model
Interior preselect multiple pilot fight state points are enclosed, and each state of flight point height, Mach number, static pressure, dynamic pressure, aircraft are set
The parameters such as configuration.Experimental rig will automatically continuously complete each state of flight experimental tests, whole under flight control system normal condition
Individual experiment process does not need testing crew intervention.
The pumping signal produces software module 21 and realizes digital pumping signal generation, and the module is opened using virtual instrument
The ripe control exploitation of hair system.Generating control by waveform first, (square wave, frequency response are selected in time domain experiment according to pumping signal type
Sine wave is selected in experiment), amplitude frequency, sample frequency generate digital pumping signal, then successively by each sampled point real-value
Integer type numerical value is converted into according to engineer's scale, and according to number bus communication format interpolation data block build byte, byte number
Byte, sample rate byte, excitation steering wheel sequence number byte, code and byte etc. form standard digital bus communication data block, and lead to
Cross digital communication bus and be sent to flight control computer.
The signal remaining voting software module 28 is responsible for carrying out redundance voting to multichannel test data, decides by vote process
In first in elimination test data greatly and minimum, it is then determined that (triplex redundance test data chooses median conduct to vote value
Vote value, four remaining test datas determine vote value by the average value of remaining two medians), with this elimination test data
Singular value.
The test data analyzer software module 29 is analyzed and processed to test data, and (time domain experiment carries out time domain point
Analysis, frequency response test carry out frequency-domain analysis), wherein frequency-domain analysis is handled from discrete Fourier transform DFT algorithms, is obtained
To winged each passage dynamic characteristic result of control.
(3) beneficial effect of invention
Beneficial effects of the present invention include:
1. by introducing a set of flight control system experimental rig based on virtual instrument, substitute in experiment at present using frequency
Rate response analyzer, system tester, analog/digital conversion device, D/A conversion device etc., realize experimental rig with
The redundance numeral of flight control computer is directly crosslinked, and avoids the signal amplitude brought using existing experimental rig and test cable
The problems such as decay, wave distortion, improve the accuracy of result of the test.
2. selection and the parameter setting of pilot fight state point can be carried out by software interface, more pilot fight states are realized
Point, multichannel continuous and automatic testing, mitigate the workload of testing crew.
3. experimental rig software systems are based on Development of Virtual Instrument, ripe Virtual Instrument Development system is fully inherited
Open system framework, versatility and scalability are preferable, are easy to promote, and have good application prospect.
Brief description of the drawings
Fig. 1 is the hardware structure diagram of flight control system experimental rig of the present invention.
Wherein：11 be pumping signal output hardware module, and 12 be rudder face response signal acquisition hardware module, and 13 be sensor
Response signal acquisition hardware module, 14 be flight control system state acquisition hardware module, and 15 be data transmission bus, and 16 be slave computer
Controller, 17 be trystate communication hardware module, and 18 be man-machine interactive computer.
Fig. 2 is the software architecture diagram of flight control system experimental rig of the present invention.
Wherein：21 be that pumping signal produces software module, and 22 be rudder face response signal acquisition software module, and 23 be sensor
Response signal acquisition software module, 24 be flight control system status monitoring software module, and 25 be that trystate sets software module, 26
It is Process flowchart software module for trystate bitcom module, 27,28 be that signal remaining decides by vote software module, and 29 be experiment
DAS module, 30 be experimental data base.
Embodiment
One embodiment of the invention hardware system structure as shown in figure 1, the experimental rig by host computer and slave computer two
It is grouped into.Wherein slave computer uses and is based on PXI data transmission bus system frameworks, pumping signal output hardware module 11, rudder face
Response signal acquisition hardware module 12, sensor response signal acquisition hardware module 13, flight control system state acquisition hardware module
14 realize 4 redundant configurations using NI companies of U.S. PXI-8431/8 boards, and data transmission bus 15 uses PXI data transfers total
Line, the next machine controller 16 is using NI companies of U.S. PXIe-8840 controller modules, and slave computer cabinet is using NI companies of the U.S.
PXIe-1082 cabinets.Pumping signal output hardware module 11, rudder face response signal acquisition hardware module 12, sensor response letter
Number acquisition hardware module 13 and flight control system state acquisition hardware module 14 are installed in slave computer cabinet, and pass through cabinet master
The PXI data transmission bus of plate communicates with the next machine controller 16.Slave computer mainly completes digital stimulus signal and produces, responds letter
Number collection, signal analysis resolve etc. function.
Host computer includes trystate communication hardware module 17 and man-machine interaction computer 18, realizes human interface function,
Man machine operation interface is provided, receives state of flight point information, pumping signal information, control command of the input of user etc., and show
Registration realizes experiment human-computer interaction function according to information such as result graph curves.Trystate communication hardware module 17 uses MOXA
CP-132 boards, man-machine interaction computer 18 is using general business computer either industrial computer, trystate communication
Hardware module 17 is arranged on the cabinet mainboard of man-machine interaction computer 18.Man-machine interaction computer 18 passes through Ethernet and bottom
Machine communicates.
The present embodiment software system structure is as shown in Fig. 2 the system is developed using virtual instrument technique programming mode is based on
System selects the Chinese editions of LabVIEW 2013, ensures that software systems have good Universal and scalability.The software systems
Software module 21, rudder face response signal acquisition software module 22, sensor response signal acquisition software are produced including pumping signal
Module 23, flight control system status monitoring software module 24, trystate set software module 25, trystate bitcom module
26th, Process flowchart software module 27, signal remaining voting software module 28, test data analyzer software module 29 and test data
Storehouse 30.
The pumping signal produces software module 21 and realizes digital pumping signal generation, and the module is opened using virtual instrument
The ripe control exploitation of hair system.Basic function generator module foundation in plate is selected to swash using LabVIEW waveforms generation first
Encourage signal type（Time domain experiment select square wave, sine wave is selected in frequency response test), amplitude, frequency, sample frequency（The present embodiment is write from memory
Think 1000Hz) the digital pumping signal of generation, each sampled point real-value is then converted into integer according to engineer's scale successively
Type Value (byte of length 2), and according to RS422 serial communication form interpolation data block builds byte, byte number byte, sampling
Rate byte excitation steering wheel sequence number byte, code and byte etc. form standard serial port communication data block, and are exported by pumping signal
The RS422 serial ports of hardware module 11 is sent to flight control computer.Flight control computer passes through solution after digital pumping signal is received
Calculate and export analog pumping signal driving steering wheel motion development experiment.
The rudder face response signal acquisition software module 22 and sensor response signal acquisition software module 23, are each responsible for
Gather redundance digital rudder face instruction that flight control computer sends and sensor response signal (pitch rate, Rolling Velocity Aerocraft, partially
Speed of a ship or plane rate, normal g-load etc.).The winged control of serial ports reading control collection in plate is selected to calculate using LabVIEW serial communication first
The redundance digital signal that machine is sent, then generate the digital rudder of redundance according to preset RS422 serial communications form
Face instructs and each sensor response signal.
The flight control system status monitoring software module 24 is responsible for being monitored flight control system alarm failure state, first
Select serial ports reading control collection flight control computer in plate to send status signal using LabVIEW serial communication, then press
Flight control system alarm state information is generated according to preset RS422 serial communications form, and alarm state information is sent to process
Software model 27.When flight control system breaks down, Process flowchart software module 27 sends interrupt instruction, stops experiment,
Warning message is concurrently sent to man-machine interface.
The trystate sets software module 25 to be developed using LabVIEW ripe control, there is provided man-machine interaction circle
Face can realize the parameter settings such as more state of flight point height, Mach number, static pressure, dynamic pressure, aircraft configurations.Default each flight shape
State point information with the process of experiment passes through trystate bitcom module 26 under being controlled in Process flowchart software module 27
It is sent to one by one in the integration test replicating machine of iron bird testing stand, realizes that each state of flight point is automatically continuously tested.
The signal remaining voting software module 28 is responsible for carrying out redundance voting to multichannel test data, decides by vote process
In reject first in redundance test data greatly and minimum, it is then determined that vote value (among triplex redundance flight control system chooses
Value is used as vote value, and four remaining flight control systems determine vote value by the average value of remaining two medians), with this elimination test number
Singular value in.
The test data analyzer software module 29 analyzes and processes according to test type to data, and the module uses
LabVIEW signal analysis selects the ripe control of plate, and time-domain analysis and frequency-domain analysis are carried out to test data.Wherein, frequency domain
Discrete Fourier transform DFT algorithm process is selected in analysis, and is output to man-machine interface by images outputting class control, while will examination
Test in the experimental data base 30 that data and result preserve.Current ripe data base management system can be selected in experimental data base 30,
Such as SQL Server, Oracle.
Above example is the further description carried out to technical scheme, is not intended to limit the present invention
Protection domain, within the spirit and principles of the invention, any modification, equivalent substitution and improvements done etc., all should include
Within protection scope of the present invention.
Claims (5)
1. a kind of fly-by-wire flight control system experimental rig based on virtual instrument technique, it is characterized in that：Hardware system is by bottom
Machine and host computer two parts composition, slave computer include pumping signal output hardware module, rudder face response signal acquisition hardware module,
Sensor response signal acquisition hardware module, flight control system state acquisition hardware module, data transmission bus and slave computer control
Device, it is main to complete digital stimulus signal generation, response signal collection and signal analysis resolving function；Host computer includes trystate
Communication hardware module and man-machine interaction computer, there is provided man machine operation interface, realize human-computer interaction function.
2. fly-by-wire flight control system experimental rig according to claim 1, it is characterized in that：The pumping signal output hardware
Module, rudder face response signal acquisition hardware module, sensor response signal acquisition hardware module and flight control system state acquisition are hard
Part module redundant configurations identical with experiment flight control system holding；Pumping signal output hardware module is using digital communication bus with flying
Control computer is connected, and square wave and sine wave numeral swept frequency excitation letter are injected separately into for flight control system time domain and frequency domain response experiment
Number；Rudder face response signal acquisition hardware module is connected using digital communication bus with flight control computer, completes flight control system rudder face
The collection of response signal；Sensor response signal acquisition hardware module is connected using digital communication bus with flight control computer, complete
Gathered into gyro and acceierometer sensor response signal；Flight control system state acquisition hardware module is connected with flight control computer,
Complete flight control system alarm failure status information capture；The data transmission bus that the next machine controller passes through slave computer cabinet mainboard
With pumping signal output hardware module, rudder face response signal acquisition hardware module, sensor response signal acquisition hardware module, fly
Control system mode acquisition hardware module communication；Trystate communication hardware module and the comprehensive control replicating machine phase of iron bird testing stand
Connection, realizes the setting of trystate information, man-machine interaction computer realizes man-machine interaction, test data analyzer and store function.
3. fly-by-wire flight control system experimental rig according to claim 1, it is characterized in that：The pumping signal output hardware
Module, rudder face response signal acquisition hardware module, sensor response signal acquisition hardware module and flight control system state acquisition are hard
Part module redundant configurations identical with experiment flight control system holding, and the signal of the output of each module and collection is redundance numeral
Formula signal, by can effectively reject the singular value in signal after remaining voting process, improve result of the test accuracy.
4. fly-by-wire flight control system experimental rig according to claim 1, it is characterized in that：The pumping signal output hardware
Module is the digital pumping signal needed for flight control system experiment injection, and pumping signal can choose different ripples according to pilot project
Shape, square wave digital stimulus signal is chosen during the response test of city when carrying out, carry out injecting sine wave numeral during frequency domain response experiment
Pumping signal.
5. fly-by-wire flight control system experimental rig according to claim 1, it is characterized in that：The pumping signal output hardware
The pumping signal and rudder face response signal acquisition hardware module of module output and the collection of sensor response signal acquisition hardware module
Response signal be digital signal, effectively prevent the signal amplitude that is put to the test caused by equipment and live electromagnetic interference and decay
With wave distortion problem, the accuracy of result of the test is improved.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109703780A (en) * | 2018-10-26 | 2019-05-03 | 中国飞行试验研究院 | A kind of fax airplane in transportation category flight test rudder face card resistance implementation method |
| CN116296345A (en) * | 2023-05-11 | 2023-06-23 | 西安晟昕科技股份有限公司 | Steering engine performance test method |
-
2017
- 2017-01-16 CN CN201720047541.9U patent/CN206975428U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109703780A (en) * | 2018-10-26 | 2019-05-03 | 中国飞行试验研究院 | A kind of fax airplane in transportation category flight test rudder face card resistance implementation method |
| CN109703780B (en) * | 2018-10-26 | 2022-04-19 | 中国飞行试验研究院 | Method for realizing control surface jamming in fly test of telex transport type airplane |
| CN116296345A (en) * | 2023-05-11 | 2023-06-23 | 西安晟昕科技股份有限公司 | Steering engine performance test method |
| CN116296345B (en) * | 2023-05-11 | 2023-08-15 | 西安晟昕科技股份有限公司 | Steering engine performance test method |
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