CN110182384A - Electrical system shows simulator and method and aircraft electrical power system integrated test system - Google Patents
Electrical system shows simulator and method and aircraft electrical power system integrated test system Download PDFInfo
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- CN110182384A CN110182384A CN201910445166.7A CN201910445166A CN110182384A CN 110182384 A CN110182384 A CN 110182384A CN 201910445166 A CN201910445166 A CN 201910445166A CN 110182384 A CN110182384 A CN 110182384A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/005—Testing of electric installations on transport means
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Abstract
The present invention provides a kind of electrical system and shows simulator and method and aircraft electrical power system integrated test system, electrical system shows that simulator includes EPS status information receiving unit, the status information of electric system is acquired, and the status information of the electric system is transferred to schematic diagram page display unit；The status information includes the power and output voltage and frequency, busbar voltage and current acquisition fluctuation range of generator；Schematic diagram page display unit passes through logic calculation and generates schematic diagram page form being shown according to the status information of the electric system of EPS status information receiving unit transmission；Unit warning system display unit.The present invention has the beneficial effect that: creating " three birds " joint debugging condition, i.e., only in the presence of electric system, aircraft electrical power system ground test requirement can be completed.
Description
Technical field
It is the invention belongs to the technology that aircraft electrical power system operating status carries out ground test test (MC5), in particular to electric
Gas system shows simulator and method and aircraft electrical power system integrated test system.
Background technique
Previous China's aircraft electrical power system ground test test, is the independent test of electric system, does not need aircraft
The cooperation of other systems, such as the information crosslinking of the systems such as avionics, hydraulic, this is because being set in aviation electric system platform top layer
In meter, conventional airplane is all 3 kinds of hydraulic energy, air pressure and electric energy energy mix modes, and respective isolated operation, electric system is not
It needs to run well under the premise of other systems and meets test request.As " mostly electricity/electric aircraft " technology mentions
Out, hydraulic energy and air pressure service efficiency are low, and reliability and vitality not can guarantee, and electric energy gradually replaces other two kinds of energy
Trend, then caused by the result is that electric system run well must by the systems such as avionics, hydraulic information be crosslinked, that
Using electric system as the test of test center, the cooperation that certainly will will cause aircraft whole system can just be completed, and cause resource
Utilization efficiency is not high, and test progress is slow.
Summary of the invention
The problem to be solved in the present invention is in aircraft electrical power system ground test technology, to power trains such as power generation, distribution
System (i.e. copper bird) is not added practical avionics system (i.e. electric bird), flies control hydraulic system (i.e. iron bird) cooperation when being tested
The technical issues of (signal that information crosslinking, i.e. electric system need to receive electric bird and iron bird).
To solve the problems of the prior art, the present invention provides a kind of electrical system display simulator, incorporates electric bird
Signal monitoring, alarm function are crosslinked information input function to judge electric system test result and electric bird, iron bird and electric system,
Including EPS status information receiving unit, the status information of electric system is acquired, and the status information of the electric system is transmitted
Give schematic diagram page display unit；The status information includes the power and output voltage and frequency, busbar voltage and electric current of generator
Acquire fluctuation range；Schematic diagram page display unit is simulated the signal monitoring function of electric bird, is passed through according to the status information of electric system
It crosses logic calculation and generates schematic diagram page form and shown；Unit warning system display unit simulates the alarm function of electric bird,
The status information threshold value of the status information of the electric system and given electric system is compared, it is true according to comparison result
Surely the rank alerted is shown in the form of text；Signal simulation unit, the signal of simulation avionics system, hydraulic system, uses
Pseudo operation interface is realized by running application software on computers, is closed when being triggered according to the logic that AICD is defined
System calculates operation states of electric power system and is sent to remote power supply management system.
Preferably, further include EPS status information transmission unit, receive the power train of EPS status information receiving unit transmission
The status information of system, and the status information of the electric system is transferred to flight control system.
Preferably, EPS status information receiving unit includes Acquisition Circuit, data collecting plate card；The Acquisition Circuit acquisition
The status information of electric system is carried out logical process by data collecting plate card and is transferred to schematic diagram by the status information of electric system
Page display unit.
Preferably, signal simulation unit includes relay board；Simulate avionics system, the signal of hydraulic system includes simulation
APU control switch, APU prepare load, APU starting enables, left generator fuel-cut, left dynamo ignition switch, right power generation
Machine fuel-cut, right dynamo ignition switch, electromechanical power controller air speed 1, electromechanical power controller air speed 2, power generation
The N2 revolving speed of machine, undercarriage, more than one signals for controlling fire prevention handle state and current air speed, pass through relay board
Give analog signal transmission to the remote power supply management system.
The invention also discloses a kind of aircraft electrical power system integrated test systems, including electric system and remote power supply management
System further includes that mentioned-above electrical system shows simulator, and electrical system shows simulator by operation states of electric power system
It is sent to remote power supply management system, remote power supply management system receives the operation states of electric power system and is translated into control
It instructs and is sent to electric system, electric system is run according to control instruction, and electrical system shows that simulator acquires power train
The status information of system is simultaneously shown in the form of schematic diagram page and text.
The invention also discloses a kind of test methods, applied to mentioned-above electrical system display simulator, including with
Lower step:
Receive user operation instruction trigger signal simulation unit, the logical relation that the emulation signal of generation is defined according to AICD
It calculates operation states of electric power system and is sent to remote power supply management system；
The status information of electric system is acquired, the status information of the electric system includes the power and output electricity of generator
Pressure and frequency, busbar voltage and current acquisition fluctuation range；
The status information of electric system is passed through logic calculation and generates schematic diagram page form and is shown；
The status information threshold value of the status information of the electric system and given electric system is compared, according to than
Relatively result determines that the rank of warning generates textual form and shown.
Preferably, operation states of electric power system includes: generator starting state and starting state, the generator do not include
Left generator, right generator, APU generator.
Preferably, logic calculation is defined as follows:
When electrical system shows that generator starting state is sent to remote power supply management system by simulator, if electrical system
The status information fluctuation range 3% of the electric system of system display simulator acquisition is hereinafter, the then status information of corresponding electric system
For normal mode；
When electrical system shows that generator starting state is sent to remote power supply management system by simulator, if electrical system
System shows 3% or more the status information fluctuation range of the electric system of simulator acquisition, then the status information of corresponding electric system
For fault mode；
Or when electrical system show simulator by generator starting state is not sent to remote power supply management system when, if
Electrical system shows that the power of the generator of simulator acquisition and output voltage and frequency have feedback information, then corresponding generator
Power and output voltage and frequency are fault mode；
When electrical system show simulator by generator starting state is not sent to remote power supply management system when, if electrically
The power and output voltage and frequency that system shows the generator of simulator acquisition are without feedback information, then the power of corresponding generator
And output voltage and frequency, busbar voltage and electric current are not start-up mode；
The status information of electric system includes the power and output voltage and frequency, the temperature of battery and voltage of generator
With electric current, the output voltage of vertoro and electric current and busbar voltage and electric current.
Preferably, the status information of electric system and the status information threshold value of given electric system are compared, according to
Comparison result determines that the rank of warning generates textual form and show
When comparison result is the power of given generator and output voltage and frequency have a signal, the power of generator and defeated
Voltage and frequency are zero out, determine that the rank of corresponding generator warning is that highest warning generation textual form is shown；
When comparison result is the power and output voltage and frequency no signal of given generator, the power of generator and defeated
Voltage and frequency have feedback information out, determine that the rank of corresponding generator warning is that highest warning generation textual form is shown
Show；
When comparison result is that the power of given generator and output voltage and frequency have signal, the state letter of electric system
Breath acquisition fluctuation range determines that the rank of the status information warning of corresponding electric system is that middle rank warning generates at 5% or more
Textual form is shown；
When comparison result is that the power of given generator and output voltage and frequency have signal, the state letter of electric system
When breath acquisition fluctuation range 3%~5%, determine that the rank of the status information warning of corresponding electric system is that rudimentary warning generates text
This form is shown；
When comparison result is that the power of given generator and output voltage and frequency have signal, the state letter of electric system
When breath 3% or less fluctuation range of acquisition, determine that the rank of the status information warning of corresponding electric system is that normal mode generates text
This form is shown；
When comparison result is the power of given generator and output voltage and frequency do not have signal, the power of generator
And output voltage and frequency do not have feedback information, determine that the rank of corresponding generator warning is that start-up mode does not generate textual form
It is shown；
The status information of electric system includes the power and output voltage and frequency, the temperature of battery and voltage of generator
With electric current, the output voltage of vertoro and electric current and busbar voltage and electric current；
The rudimentary warning > normal mode > of > not text of the start-up mode to display is alerted according to superlative degree warning > middle rank
Form is ranked up.
The present invention has the effect that
(1) in aircraft electrical power system ground test technology, the electric system such as power generation, distribution (i.e. copper bird) are tests pair
As, but the cooperation (information that the normal operation of electric system needs avionics system (i.e. electric bird), flies control hydraulic system (i.e. iron bird)
Crosslinking, i.e. electric system need to receive the signal of electric bird and iron bird) it could normally run, this just needs to test electric system
" copper bird ", avionics system test " electric bird " and fly control hydraulic system iron bird carry out information crosslinking, to form " three birds
Analysis, verifying, the debugging of the power train irrespective of size of joint debugging "；The system that signal simulation unit serves as " electric bird " " iron bird ", gives electric power
Signal required for system (i.e. " copper bird ") operates normally creates conditions for the normal operation of " copper bird ", realizes " three birds " joint debugging,
It does not need actually to build avionics system and flies control hydraulic system, i.e., only in the presence of electric system, complete aricraft electrical power
System ground test request.
(2) true schematic diagram page display unit is substituted, it is (main to summarize the relevant status information of aircraft electrical power system (EPS)
Power and output voltage and frequency, busbar voltage and electric current including generator and power circuit topology) etc. information, with schematic diagram
Page formal intuition is shown, and ground monitoring personnel can monitor the operating status of electric system by schematic diagram page.
(3) true avionics unit warning system is substituted, and the fault point in electric system is subjected to centralized displaying simultaneously
Refresh in real time, alarm level is ranked up, prompt alarm function is played.
(4) present invention is convenient for human-computer interaction, the performance of quick and convenient test electric system.
Detailed description of the invention
Fig. 1 is the structural schematic diagram that the electrical system that one embodiment of the invention provides shows simulator；
Fig. 2 be another embodiment of the present invention provides electrical system show simulator structural schematic diagram；
Fig. 3 be another embodiment of the present invention provides electrical system show simulator structural schematic diagram；
Fig. 4 is the structural schematic diagram for the aircraft electrical power system integrated test system that one embodiment of the invention provides；
Fig. 5 is the structural schematic diagram for the EPS status information receiving unit that one embodiment of the invention provides；
Fig. 6 is that the electrical system that one embodiment of the invention provides shows simulator human-computer interaction interface；
Fig. 7 is that the simple page figure of Fig. 6 shows the enlarged drawing of the page；
Fig. 8 is that the unit warning information of Fig. 6 shows the enlarged drawing of the page；
Wherein, 1.EPS status information receiving unit；2. schematic diagram page display unit；3. unit warning system display unit；4.
Signal simulation unit；5.EPS status information transmission unit；6. flight control system；7. electric system；8. remote power supply management system
System.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.Attached drawing
Only for illustration, expression is only schematic diagram, rather than pictorial diagram, should not be understood as the limitation to this patent, in order to more
Illustrate a specific embodiment of the invention well, the certain components of attached drawing have omission, zoom in or out, and do not represent actual product
Size, it will be understood by those skilled in the art that the omitting of some known structures and their instructions in the attached drawings are understandable, base
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts it is all its
His embodiment, shall fall within the protection scope of the present invention.
In the description of the present invention, it is also necessary to which explanation is unless specifically defined or limited otherwise, term " setting ",
" connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or be integrally connected；It can be
Mechanical connection, is also possible to be electrically connected；It can be directly connected, two can also be can be indirectly connected through an intermediary
Connection inside element.For the ordinary skill in the art, above-mentioned term can be understood at this as the case may be
Concrete meaning in invention.
As shown in Figure 1, a kind of electrical system shows simulator, including
EPS status information receiving unit 1 acquires the status information of electric system 7, and by the state of the electric system 7
Information is transferred to schematic diagram page display unit 2；The status information includes the power and output voltage and frequency, bus electricity of generator
Pressure and current acquisition fluctuation range；
The status information of schematic diagram page display unit 2, the electric system 7 transmitted according to EPS status information receiving unit 1 is passed through
Logic calculation simultaneously generates schematic diagram page form and is shown；
Unit warning system display unit 3, by the shape of the status information of the electric system 7 and given electric system 7
State information threshold is compared, and determines that the rank of warning is shown in the form of text according to comparison result；
Signal simulation unit 4, the signal of simulation avionics system, hydraulic system, using pseudo operation interface, by operating in
Application software on computer realizes, calculates 7 operating status of electric system according to the logical relation that AICD is defined when triggering
Remote power supply management system 8 is sent to by built-in relay board.
Fig. 2 is another structural schematic diagram that electrical system shows simulator, for unit warning system display unit 3,
It can both conform to the principle of simplicity as shown in Figure 1 map sheet display unit 2 obtain electric system 7 status information, can also as shown in Figure 2 from
The status information of electric system 7 is obtained in EPS status information receiving unit 1 (i.e. 7 status information receiving unit of electric system).
In the embodiment, electrical system shows simulator, and hardware is mainly by the work of data collecting card, ethernet communication interface
Industry controls computer composition, is carried out to the status information of electric system 7 with schematic diagram page and unit warning system (CAS) message form
It has been shown that, and show that electric system 7 and other systems such as avionics, hydraulic are crosslinked bus message by signal simulation unit 4.
The realization of software is completed by LabVIEW exploitation environment, and software section is mainly data communication and logic calculation.?
In aircraft operational process, avionics system and winged control hydraulic system need to send control instruction, as ensure that electric system 7 is normally transported
Row needs avionics system and flies the status signal that control hydraulic system provides it aircraft other systems, such as APU control switch, APU
Prepare load, APU starting enables, left generator fuel-cut, left dynamo ignition switch, right generator fuel-cut, right hair
Motor ignition switch, electromechanical power controller air speed 1, electromechanical power controller air speed 2, generator N2 tach signal,
The signals such as undercarriage, left and right fire prevention handle state, current air speed, it is meant that, the signal of simulation avionics system, hydraulic system
I.e. simulation APU control switch, APU prepare load, APU starting enables, left generator fuel-cut, left dynamo ignition switch,
Right generator fuel-cut, right dynamo ignition switch, electromechanical power controller air speed 1, electromechanical power controller air speed
2, the N2 revolving speed of generator, undercarriage, more than one signals for controlling fire prevention handle state and current air speed.These signals
All be directly related to electric system 7 work in which kind of state, operation whether normal and its working condition conversion.Therefore originally
Invention needs according to current specific test requirements document and 7 actual operating state of electric system simulation avionics system and flies control hydraulic pressure system
The working condition of system, and electric system 7 is sent to by bus in real time according to the period demand of each signal respectively, these letters
Signal simulation unit 4 number through the invention generates, and 7 operating status of electric system (i.e. control signal) of needs is passed through relay
Device board is sent to remote power supply management system 8 (" RPDU pilot system " described briefly below), to control the fortune of electric system 7
Row.
AICD (Avionics Interface Control Document) i.e. avionics interface controls file
AICD is respectively 1Hz, 5Hz, 10Hz and 20Hz as the data frequency that industry standard standard defines bus transmission,
So between avionics system and electric system 7 information send minimum period 50ms in realize all functions (data acquisition,
The functions such as analysis, preservation, EPS schematic diagram and the update of CAS information state), to meet requirement of the system to real-time.
Status information (power, output voltage and the frequency of engine, busbar voltage and the electric current of electric system 7 (EPS)
Deng), in real time by monitoring bus, monitoring bus from 429 buses and pci bus collected initial data (EPS information) according to
The journal of time is got off, later by collected data carry out logical process, i.e., data decompose and logic calculation, this two
The code requirement for requiring to provide in strict accordance with AICD is divided to carry out, any one data or the minor error calculated can all cause
The serious distortion for determining result causes currently to determine 7 state of electric system insincere.
As shown in figure 5, EPS status information receiving unit 1 includes Acquisition Circuit, data collecting plate card；The Acquisition Circuit
The status information of electric system 7 is carried out logical process transmission by data collecting plate card by the status information for acquiring electric system 7
To schematic diagram page display unit 2.Electric system 7 operates after obtaining corresponding control instruction, the status information of electric system 7
(i.e. the power of generator and output voltage and frequency, busbar voltage and electric current and power circuit topology) by Acquisition Circuit into
Enter data collecting plate card (as exemplary illustration, such as NI company PCI6224 data collecting plate card) acquisition, by electric system 7
Status information gets off to carry out according to the journal of time logical process and is transferred to schematic diagram page display unit 2 to be shown, schematic diagram
The working principle of page display unit 2 is Labview by writing dynamic link library (DLL) file for the status information of electric system 7
It is stored in Labview reading data memory, by calling Labview waveform chart, the state of reading electric system 7 is believed
Breath is graphically shown on PC display in real time.Wherein, the signal of acquisition according to type be divided into analog signal and from
Scattered signal, analog signal enter back into the acquisition of PCI6224 data after signal acquisition circuit (filtering, amplification, difference etc. are adjusted)
Board guarantees the stability and reliability of collected signal.
As shown in figure 3, on the basis of the above embodiments, electrical system shows that simulator further includes EPS status information hair
It send unit 5, receives the status information for the electric system 7 that EPS status information receiving unit 1 is transmitted, and by the electric system 7
Status information is transferred to flight control system 6.
The status information of electric system 7 will be sent to flight control system 6 by EPS status information transmission unit 5, fly
Row control system 6 is the information fusion center of aircraft.
As shown in figure 4, a kind of 7 integrated test system of aircraft electrical power system, including electric system 7 and remote power supply management system
System 8 further includes that electrical system recited above shows simulator, and electrical system shows simulator by 7 operating status of electric system
It is sent to remote power supply management system 8, remote power supply management system 8 receives 7 operating status of electric system and is translated into
Control instruction is sent to electric system 7, and electric system 7 is run according to control instruction, and electrical system shows simulator acquisition
The status information of electric system 7 is simultaneously shown in the form of schematic diagram page and text.
Electrical system recited above shows the test method of simulator, includes the following steps:
Receive user operation instruction trigger signal simulation unit 4, the emulation signal of generation is closed according to the logic that AICD is defined
System calculates 7 operating status of electric system and is sent to remote power supply management system 8；
The status information of electric system 7 is acquired, the status information of the electric system 7 includes power and the output of generator
Voltage and frequency, the temperature of battery and voltage and current, the output voltage of vertoro and electric current and busbar voltage and electricity
Stream acquisition fluctuation range；
The status information of electric system 7 is passed through logic calculation and generates schematic diagram page form and is shown；
The status information threshold value of the status information of the electric system 7 and given electric system 7 is compared, according to
Comparison result determines that the rank of warning generates textual form and shown.
As exemplary illustration, 7 operating status of electric system includes: generator starting state and not starting state, described
Generator includes left generator, right generator, APU generator.
As exemplary illustration, logic calculation is defined as follows: when electrical system shows simulator by generator starting state
When being sent to remote power supply management system 8, if electrical system shows that the status information of the electric system of simulator acquisition fluctuates model
3% is enclosed hereinafter, then the status information of corresponding electric system is normal mode；
When electrical system shows that generator starting state is sent to remote power supply management system 8 by simulator, if electrically
System shows 3% or more the status information fluctuation range of the electric system of simulator acquisition, then the state letter of corresponding electric system
Breath is fault mode；
When electrical system show simulator by generator starting state is not sent to remote power supply management system 8 when, if electric
The power and output voltage and frequency of the generator of gas system display simulator acquisition have feedback information, then the function of corresponding generator
Rate and output voltage and frequency are fault mode；
When electrical system show simulator by generator starting state is not sent to remote power supply management system 8 when, if electric
The power and output voltage and frequency that gas system shows the generator of simulator acquisition are without feedback information, then the function of corresponding generator
Rate and output voltage and frequency are not start-up mode；
The status information of electric system includes the power and output voltage and frequency, the temperature of battery and voltage of generator
With electric current, the output voltage of vertoro and electric current and busbar voltage and electric current, the status information of certain electric system is not only
It is limited to this, may also comprise converter, only enumerate.
In the embodiment, generator includes left generator, right generator, APU generator, and bus includes: left exchange confluence
Item, right AC bus bar, Zuo Zhiliu busbar, right direct current busbar, Zuo Zhiliu essential bus, right direct current essential bus, direct current
Convert essential bus, 3 phases exchange essential bus, single phase ac essential bus, flight control direct current busbar etc., battery packet
Main storage battery, flight control battery and APU battery are included, wherein vertoro includes that left vertoro, middle transformation are whole
Device, right vertoro are flowed, there are three types of the warning levels of these status informations, for convenience of monitoring, can correspond to three kinds of colors
Display, for example, such as green represents normal mode, yellow representing fault failure mode (and can be subdivided into highest warning,
Middle rank warning and rudimentary warning), white represents not start-up mode.
With L AC BUS (left AC bus bar) for example, if L AC BUS shows yellow, then it represents that L AC BUS is (left
AC bus bar) be malfunction and failure mode: if L AC BUS display green, then it represents that L AC BUS (left AC bus bar) is just
Norm formula.
As exemplary illustration, by the status information threshold of the status information of the electric system 7 and given electric system 7
Value is compared, and determines that the rank of warning carries out display in the form of text and includes: according to comparison result
When comparison result is the power of given generator and output voltage and frequency have a signal, the power of generator and defeated
Voltage and frequency are zero out, determine that the rank of corresponding generator warning is that highest warning generation textual form is shown；
When comparison result is the power and output voltage and frequency no signal of given generator, the power of generator and defeated
Voltage and frequency have feedback information out, determine that the rank of corresponding generator warning is that highest warning generation textual form is shown
Show；
When comparison result is that the power of given generator and output voltage and frequency have signal, the state letter of electric system
Breath acquisition fluctuation range determines that the rank of the status information warning of corresponding electric system is that middle rank warning generates at 5% or more
Textual form is shown；
When comparison result is that the power of given generator and output voltage and frequency have signal, the state letter of electric system
When breath acquisition fluctuation range 3%~5%, determine that the rank of the status information warning of corresponding electric system is that rudimentary warning generates text
This form is shown；
When comparison result is that the power of given generator and output voltage and frequency have signal, the state letter of electric system
When breath 3% or less fluctuation range of acquisition, determine that the rank of the status information warning of corresponding electric system is that normal mode generates text
This form is shown；
When comparison result is the power of given generator and output voltage and frequency do not have signal, the power of generator
And output voltage and frequency do not have feedback information, determine that the rank of corresponding generator warning is that start-up mode does not generate textual form
It is shown；
The status information of electric system includes the power and output voltage and frequency, the temperature of battery and voltage of generator
With electric current, the output voltage of vertoro and electric current and busbar voltage and electric current；
The rudimentary warning > normal mode > of > not text of the start-up mode to display is alerted according to superlative degree warning > middle rank
Form is ranked up.
For example with left generator test, if the power and output voltage and frequency of given left generator have signal,
The power and output voltage and frequency of the generator of acquisition are zero, determine that the rank of left generator warning is that highest warning generates
Textual form is shown.When comparison result is the power and output voltage and frequency no signal of given left generator, Zuo Fa
The power and output voltage and frequency of motor have feedback information (being not zero), determine that the rank of left generator warning is highest police
Generation textual form is accused to be shown；When comparison result is that the power of given left generator and output voltage and frequency have letter
Number, if the power and output voltage and frequency collection fluctuation range of the left generator of acquisition determine left generator at 5% or more
The rank of warning is that middle rank warning generation textual form is shown, if the power and output voltage and frequency of the left generator of acquisition
When rate acquires fluctuation range between 3%-5%, determine the warning of left generator rank be rudimentary warning generate textual form into
Row display determines left hair if the power and output voltage and frequency collection fluctuation range of the left generator of acquisition are below 3%
The rank of motor warning is that normal mode generation textual form is shown, if the temperature of the battery of acquisition and voltage and electric current
And/or the output voltage of vertoro and electric current and/or busbar voltage current acquisition fluctuation range be at 5% or more,
The rank for determining battery and/or vertoro and/or bus warning is that middle rank warning generation textual form is shown
Show, if the output voltage and electric current and/or mother of the temperature of the battery of acquisition and voltage and electric current and/or vertoro
When line voltage current acquisition fluctuation range is between 3%-5%, battery and/or vertoro and/or bus are determined
The rank of warning is that middle rank warning generates textual form and shown, if the temperature of the battery of acquisition and voltage and electric current and/
Or the output voltage of vertoro and electric current and/or busbar voltage current acquisition fluctuation range below 3% when, determine
Battery and/or the rank of vertoro and/or bus warning are that middle rank warning generation textual form is shown.It is right
Generator, APU generator test are similarly.
The POWER SYSTEM STATE information fluctuation range 3%, 5% of above-mentioned acquisition can also need to redefine according to actual test
Numerical value.Such as 4%, 8% etc..
As exemplary illustration, electrical system shows that the human-computer interaction interface of simulator can be as shown in Figure 6.
The function of ELECTRICAL SYSTEM SYNOPTIC (simple page figure shows the page) this part: being exactly that state is aobvious in fact
The function of showing shows 7 current state of electric system in the form of simple page figure via data acquisition, after data processing,
Intuitively show the operating status of 7 each section of electric system.Specifically status information is shown as shown in fig. 7, Fig. 7 explanation of nouns: L
AC BUS: left AC bus bar；R AC BUS: right AC bus bar；TRU:Transformer Rectifier Unit, transformation
Rectifier；L E R TRU: it is left in right TRU；BUS: Zuo Zhiliu busbar of L DC；R DC BUS: right direct current busbar；L DC
BUS: Zuo Zhiliu essential bus of ESS；R DC ESS BUS: right direct current essential bus；DC ESS XFER BUS: direct current conversion master
Busbar；3PH AC ESS BUS:3 phase exchanges essential bus；1PH AC BUS: single phase ac essential bus；INV: converter；
MAIN BATT: main storage battery；FC BATT: flight control battery；FC DC BUS: flight control direct current busbar；APU
BATT:APU battery；Yellow representing fault failure mode, white represent not start-up mode；Green represents normal condition, Fig. 7
In, left hair malfunction and failure mode (display yellow)；APU not start-up mode (being displayed in white)；(display is green for right hair normal startup mode
Color)；Other component (removing generator) such as E TRU, R DC ESS BUS, MAINBATT value of feedback be not in normal fluctuation range
(3%) in (display yellow), since Fig. 7 is black and white therefore can not find out.
The status information of electric system 7 carries out CAS warning function by unit warning system display unit 3, when schematic diagram page
Certain status informations of middle electric system 7 show yellow this means that these status informations break down, and unit warning system is aobvious
Show that unit 3 will extract trouble unit information, the parameter of trouble unit and given threshold value are compared, shown by following classification
The alert message of EPS three grades: Warning, Caution and Advisory, to form unit warning system in interface
(CAS) information is shown, warning information play the role of remind ground monitoring personnel, here Warning, Caution and
Advisory is belonged to " warning ", and the degree level relation of warning is Warning > Caution > Advisory.Generator without
Method, which normally starts, belongs to highest warning (Warning), the power and output voltage and frequency of left generator, the function of right generator
Rate and output voltage and frequency, the power of APU generator and output voltage and frequency, the temperature of battery and voltage and current,
The above are middle ranks to alert 5% for the output voltage and electric current and busbar voltage and current acquisition fluctuation range of vertoro
(Caution), 3%~5% the above are rudimentary warning (Advisory).CAS, that is, unit warning information shows the page such as Fig. 8 institute
Show, the high CAS information arrangement of alert level above the page, alert level it is low be arranged in lower section.Explanation of nouns in Fig. 8: L
GEN FAULT: left hair failure；MAIN BATT FAULT: main storage battery failure；E TRU FAULT: middle vertoro failure；
APU GEN FAULT:APU sends out failure；R GEN FAULT: right hair failure；L GEN is in malfunction and failure mode in Fig. 8, belongs to
Superlative degree warning, therefore it is in top, show Warning；MAIN BATT and E TRU fluctuation range is in 5% or more
Middle rank warning, successively sorts, and shows Caution；L DC BUS fluctuation range is fluctuated 3% or more, shows Advisory.
Signal simulation unit 4 is the systems such as simulation avionics system, hydraulic system, is provided required for electric system normal operation
Normal signal, electric system 7 here refers to copper bird, and avionics system refers to electric bird, and hydraulic system refers to iron bird, this
Sample shows that simulator is easy to only realize " three birds " joint-trial in the presence of electric system 7 by electrical system.
Signal simulation unit 4 can provide signal required for electric system i.e. " copper bird " runs well, thus to winged
The ground test of electromechanical Force system 7 provides a kind of effective means.It is simulated by signal simulation unit 4 in electric system 7
The source of trouble (because the normal operation of electric system 7 requires to carry out output signal from signal simulation unit 4), electric system 7 obtains
Some necessary CRANK PULSES are obtained, can be run according to artificial control, while electric system 7 is operated according to instruction,
Sensor will acquire the operating status situation of each component (all status informations shown in schematic diagram page) in real time, and in letter
It is intuitively shown in map sheet, while electrical system shows that simulator will be by the malfunction coefficient of electric system 7 in the CAS page.
Electrical system display simulation implement body test mode is as follows:
It is now assumed that simulation test: left hair (L GEN) is in malfunction and failure mode (yellow representative), and APU, which is in, not to be started
Mode (white represents), right hair (R GEN) are in normal condition (green represents).Under such artificial facilities, so that it may
To realize the failure proof to electric system 7, thus the electric power normality of test macro.
(electrical system shows that simulator can carry out emulation signal to signal simulation here, can mould by the signal of needs
Draw up come) in include that signal has:
APU Master Switch:APU control switch；APU RTL:APU prepares load；
APU Start Enable:APU starting is enabled；
L Engine fuel cutoff: Left Hand Engine fuel-cut；L Engine fire switch: Left Hand Engine point
Fire switch；
R Engine fuel cutoff: right engine fuel cutting；R Engine fire switch: right engine point
Fire switch；
CAL_AIRSPEED1_EMPC (≤80knots): electromechanical power controller air speed 1 (is less than or equal to 80 sections)
CAL_AIRSPEED2_EMPC (> 170knots): electromechanical power controller air speed 2 (is greater than 170 sections)
The main function of signal simulation is the signal for simulating avionics system and hydraulic system etc., and the signal of emulation is as control
Instruction, normal in order to ensure electric system 7, operation needs other systems to provide it the state of aircraft other systems, such as sends out
The N2 tach signal of motivation, undercarriage, left and right fire prevention handle state, current air speed etc., using LabVIEW develop environment into
Row signal simulation, belongs to the prior art, repeats no more.These signals be all directly related to electric system 7 work in which kind of state,
Operation whether normal and its working condition conversion.In 7 ground test technology of aircraft electrical power system, signal simulation unit 4
Signal, the function of control 7 state of electric system, and the logical relation that signal here is defined according to AICD can be completed
Calculate 7 operating status situation of electric system.
Citing: (logical relation that AICD is defined)
The APU start-up mode logical relation that 1 AICD of table is defined
Table 1 illustrates: APU auxiliary power unit is usually before taking off, and is 7 output power of aircraft electrical power system, institute
Under the premise of saying that working as APU Master Switch, APU RTL, APU Start Enable opens, and CAL_
AIRSPEED1_EMPC (≤80knots) is that 1, CAL_AIRSPEED2_EMPC (> 170knots) is 0 (it is small to represent the aircraft speed of a ship or plane
In being equal to 80 sections), such APU is in start-up mode, remaining state is not start-up mode.
The left hair start-up mode logical relation that 2 AICD of table is defined
Table 2 illustrates: it is 7 output power of aircraft electrical power system that left hair, which is after taking off, thus as L Engine
Under the premise of fuel cutoff, L Engine fire switch are opening, and CAL_AIRSPEED1_EMPC (≤
80knots) be 0, CAL_AIRSPEED2_EMPC (> 170knots) be 0 or 1 (representing the aircraft speed of a ship or plane greater than 80 sections), in this way
Left hair is in start-up mode, remaining state is in not start-up mode.
The right hair start-up mode logical relation that 3 AICD of table is defined
Table 3 illustrates: it is 7 output power of aircraft electrical power system that right hair, which is after taking off, thus as R Engine
Under the premise of fuel cutoff, R Engine fire switch are opening, and CAL_AIRSPEED1_EMPC (≤
80knots) be 0, CAL_AIRSPEED2_EMPC (> 170knots) be 0 or 1 (representing the aircraft speed of a ship or plane greater than 80 sections), in this way
Right hair is in start-up mode, remaining state is in not start-up mode.
Signal simulation function is sent to RPDU (Remote Power for signal (i.e. the operating status of electric system 7) is controlled
Distribution Unit) pilot system, i.e. remote power supply management system 8, the generator operation of RPDU control electric system 7
State (starts or not start-up mode).
Aircraft electrical power system 7 is run according to control instruction, and analog quantity and digital quantity Real-time Feedback are returned schematic diagram page and shown
Show unit 2, carries out AICD logic calculation and shown that the method for calculating: green represents normal operation；White, which represents, does not start mould
Formula；The AICD calculating of the failure of yellow representing fault, malfunction and failure refers under normal activation state that (signal simulation unit 4 controls
Generator starting), 7 operating condition lower sensor of practical power systems returns to abnormality (generator does not start)；Or it is other
Component fluctuation range not in normal fluctuation range (3%), remind by display yellow.
Aircraft electrical power supply system is run according to control instruction, and analog quantity and digital quantity Real-time Feedback are returned electrical system and shown
Show the schematic diagram page display unit of simulator, is shown wherein being also intended to progress AICD logic calculation, the method for calculating: green generation
Table normal operation；White represents not start-up mode；The AICD calculating of the failure of yellow representing fault, malfunction and failure refers to normally opening
Under dynamic state (signal simulation unit controls generator starting), actual power running situation lower sensor returns to abnormality
(generator does not start)；Or other component nominal values not in normal fluctuation range (3%), remind by display yellow.
It although an embodiment of the present invention has been shown and described, for the ordinary skill in the art, can be with
A variety of variations, modification, replacement can be carried out to these embodiments without departing from the principles and spirit of the present invention by understanding
And modification, the scope of the present invention is defined by the appended.
Claims (9)
1. a kind of electrical system shows simulator, it is characterised in that: including
EPS status information receiving unit acquires the status information of electric system, and the status information of the electric system is transmitted
Give schematic diagram page display unit；The status information includes the power and output voltage and frequency, busbar voltage and electric current of generator
Acquire fluctuation range；
Schematic diagram page display unit passes through logic calculation and generates schematic diagram page form being shown according to the status information of electric system
Show；
Unit warning system display unit, by the status information threshold of the status information of the electric system and given electric system
Value is compared, and determines that the rank of warning is shown in the form of text according to comparison result；
Signal simulation unit, the signal of simulation avionics system, hydraulic system are calculated using pseudo operation interface by operating in
Application software on machine is realized, is calculated operation states of electric power system according to the logical relation that AICD is defined when being triggered and is sent
Give remote power supply management system.
2. electrical system shows simulator according to claim 1, it is characterised in that: further include that EPS status information sends list
Member receives the status information of the electric system of EPS status information receiving unit transmission, and by the status information of the electric system
It is transferred to flight control system.
3. electrical system shows simulator according to claim 1, it is characterised in that: the EPS status information receiving unit
Including Acquisition Circuit, data collecting plate card；The status information of the Acquisition Circuit acquisition electric system, passes through data collecting plate card
The status information of electric system is subjected to logical process and is transferred to schematic diagram page display unit.
4. electrical system shows simulator according to claim 1, it is characterised in that: the signal simulation unit includes relay
Device board；It is described simulation avionics system, hydraulic system signal include simulation APU control switch, APU prepare load, APU starting
Enabled, left generator fuel-cut, left dynamo ignition switch, right generator fuel-cut, right dynamo ignition switch, electromechanics
Formula power controller air speed 1, electromechanical power controller air speed 2, the N2 revolving speed of generator, undercarriage, left and right fire prevention hand
More than one signals of handle state and current air speed give analog signal transmission to the remote power supply management by relay board
System.
5. a kind of aircraft electrical power system integrated test system, including electric system and remote power supply management system, it is characterised in that:
It further include the electrical system display simulator as described in claim 1-4 is any, electrical system shows simulator by electric system
Operating status is sent to remote power supply management system, and remote power supply management system receives the operation states of electric power system for its turn
It turns to control instruction to send to electric system, electric system is run according to control instruction, and electrical system shows that simulator is adopted
Collect the status information of electric system and is shown in the form of schematic diagram page and text.
6. a kind of test method shows simulator applied to any electrical system of claim 1-5, which is characterized in that
The following steps are included:
Receive user operation instruction trigger signal simulation unit, the emulation signal of generation is calculated according to the logical relation that AICD is defined
Operation states of electric power system is sent to remote power supply management system out；
Acquire electric system status information, the status information of the electric system include generator power and output voltage and
Frequency, the temperature of battery and voltage and current, the output voltage of vertoro and electric current and busbar voltage and current acquisition
Fluctuation range；
The status information of electric system is passed through logic calculation and generates schematic diagram page form and is shown；
The status information threshold value of the status information of the electric system and given electric system is compared, is tied according to comparing
Fruit determines that the rank of warning generates textual form and shown.
7. test method as claimed in claim 6, it is characterised in that: the operation states of electric power system includes: that generator opens
Dynamic state and starting state, the generator do not include left generator, right generator, APU generator.
8. test method as claimed in claim 6, it is characterised in that: the logic calculation is defined as follows:
When electrical system shows that generator starting state is sent to remote power supply management system by simulator, if electrical system is aobvious
Show the status information fluctuation range 3% of the electric system of simulator acquisition hereinafter, then the status information of corresponding electric system is positive
Norm formula；
When electrical system shows that generator starting state is sent to remote power supply management system by simulator, if electrical system is aobvious
Show 3% or more the status information fluctuation range of the electric system of simulator acquisition, then the status information of corresponding electric system is event
Barrier mode；
When electrical system show simulator by generator starting state is not sent to remote power supply management system when, if electrical system
The power and output voltage and frequency of the generator of display simulator acquisition have feedback information, then the power of corresponding generator and defeated
Voltage and frequency are fault mode out；
When electrical system show simulator by generator starting state is not sent to remote power supply management system when, if electrical system
The power and output voltage and frequency for showing the generator of simulator acquisition are without feedback information, then the power of corresponding generator and defeated
Voltage and frequency, busbar voltage and electric current are not start-up mode out；
The status information of electric system includes the power and output voltage and frequency, the temperature of battery and voltage and electricity of generator
Stream, the output voltage of vertoro and electric current and busbar voltage and electric current.
9. test method as claimed in claim 6, it is characterised in that: the status information of the electric system and given electric power
The status information threshold value of system is compared, and determines that the rank of warning generates textual form and carries out display packet according to comparison result
It includes:
When comparison result is that the power of given generator and output voltage and frequency have signal, the power and output electricity of generator
It presses and frequency is zero, determine that the rank of corresponding generator warning is that highest warning generation textual form is shown；
When comparison result is the power and output voltage and frequency no signal of given generator, the power and output electricity of generator
It presses and frequency has feedback information, determine that the rank of corresponding generator warning is that highest warning generation textual form is shown；
When comparison result is that the power of given generator and output voltage and frequency have signal, the status information of electric system is adopted
Collect fluctuation range at 5% or more, determines that the rank of the status information warning of corresponding electric system is that middle rank warning generates text
Form is shown；
When comparison result is that the power of given generator and output voltage and frequency have signal, the status information of electric system is adopted
When collecting fluctuation range 3%~5%, determine that the rank of the status information warning of corresponding electric system is that rudimentary warning generates text shape
Formula is shown；
When comparison result is that the power of given generator and output voltage and frequency have signal, the status information of electric system is adopted
When collecting 3% or less fluctuation range, determine that the rank of the status information warning of corresponding electric system is that normal mode generates text shape
Formula is shown；
When comparison result is the power of given generator and output voltage and frequency do not have signal, the power of generator and defeated
Voltage and frequency do not have feedback information out, determine that the rank of corresponding generator warning is that start-up mode does not generate textual form progress
Display；
The status information of electric system includes the power and output voltage and frequency, the temperature of battery and voltage and electricity of generator
Stream, the output voltage of vertoro and electric current and busbar voltage and electric current；
The rudimentary warning > normal mode > of > not textual form of the start-up mode to display is alerted according to superlative degree warning > middle rank
It is ranked up.
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