CN104181908A - DFDAU test platform and test method - Google Patents
DFDAU test platform and test method Download PDFInfo
- Publication number
- CN104181908A CN104181908A CN201310191379.4A CN201310191379A CN104181908A CN 104181908 A CN104181908 A CN 104181908A CN 201310191379 A CN201310191379 A CN 201310191379A CN 104181908 A CN104181908 A CN 104181908A
- Authority
- CN
- China
- Prior art keywords
- signal
- data
- generating unit
- test
- dfdau
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Abstract
The invention relates to a test platform and test method for a digital flight data acquisition unit (DFDAU). The aircraft DFDAU test platform includes an input interface which receives test data; a simulation signal generation module which generates simulation signals according to the test data; a wiring extending device used for forming a gateable wiring device, wherein the simulation signals are accessed to a to-be-tested DFDAU through the wiring expansion device; and a comparison module which compares test data which is from the to-be-tested DFDAU and based on the simulation signals and the test data which is input to the input interface.
Description
Technical field
The present invention relates to a kind of aircraft testing apparatus and method of testing, especially, relate to test platform and the method for testing of a kind of digital aircraft flight data securing component DFDAU.
Background technology
The core component that carries out acquisition and processing for aircraft states data or control command data on aircraft is digital aircraft flight data securing component DFDAU(Digital Flight Data Acquisition Unit).DFDAU is a kind of integrated on-board data acquisition and processing system.Aircraft states data or the control command data with relevant device transmission of all the sensors collection are all sent in this device of aircraft DFDAU.
DFDAU comprises data acquisition subsystem and data process subsystem.The data acquisition subsystem of DFDAU is used for gathering from the real-time aircraft states data of each sensor on aircraft or the control command data of control system, and becomes digital signal to store quick access recorder QAR(Quick Access Recorder into the data-switching of obtaining) in.
The data process subsystem of DFDAU, for example aircraft states supervisory system ACMS(Aircraft Condition Monitoring System) can with the data realization of real-time mode collection, to aircraft states, monitor according to DFDAU.When meeting certain triggering logic, ACMS generates the message that comprises accordingly particular aircraft status data or control command data.Message can show by airborne indicator, prints, or be stored in data disks and use after aircraft misses the stop or navigates for navigational matters or flight crew by airborne printing device.Message also can send to ground SITA receiving station by equipment such as very high frequency(VHF), high frequency, satellite receiver through airborne aircraft communication addressing and reporting system (ACARS), is finally sent on the terminal computer of airline.
Although DFDAU is extremely important for aircraft, owing to lacking corresponding DFDAU test platform, DFDAU is but difficult to be found to the fault of aircraft states data or control command data processing.Particularly for some aircraft states data or control command data, it must could export after the processing of DFDAU on display or printer, and DFDAU almost cannot find the fault of these aircraft states data or control command data processing appearance.Therefore, this area needs a kind of test platform and method of testing for DFDAU equipment itself.
Summary of the invention
For the technical matters existing in prior art, according to an aspect of the present invention, the test platform of a kind of aircraft DFDAU is proposed, comprising: input interface, it receives test data; Simulate signal generation module, it produces simulate signal according to described test data; Wiring expansion equipment, it is used for forming gateable termination, and wherein said simulate signal accesses in DFDAU to be tested by described wiring expanding unit; And comparison module, it is the test data based on described simulate signal and the test data that inputs to described input interface from described DFDAU to be tested relatively.
According to another aspect of the present invention, propose a kind of method of on the aircraft DFDAU test platform of the above, DFDAU to be tested being tested, comprising: on described test platform, be written into test data; According to described test data, produce simulate signal; By described simulate signal access wiring expansion equipment; Reception is from the simulate signal of described wiring expansion equipment, and described simulate signal is accessed in DFDAU to be tested; And the relatively test data based on described simulate signal and the test data that is loaded into described test platform from described DFDAU to be tested.
Accompanying drawing explanation
Below, in connection with accompanying drawing, the preferred embodiment of the present invention is described in more detail, wherein:
Fig. 1 is the schematic diagram of DFDAU working condition on aircraft;
Fig. 2 is according to an embodiment of the invention for testing the test platform architecture schematic diagram of DFDAU;
Fig. 3 is simulate signal generation modular structure schematic diagram according to an embodiment of the invention;
Fig. 4 is the structural representation of alternating voltage ratio signal ACVR signal generating unit according to an embodiment of the invention;
Fig. 5 is the structural representation of alternating voltage ratio signal ACVR signal generating unit according to another embodiment of the invention;
Fig. 6 is the structural representation of the synchronous SYNC signal generating unit of alternating voltage according to an embodiment of the invention;
Fig. 7 is the structural representation of the synchronous SYNC signal generating unit of alternating voltage according to another embodiment of the invention;
Fig. 8 is the structural representation of patching panel according to an embodiment of the invention;
Fig. 9 is the schematic diagram of patching panel panel according to an embodiment of the invention;
Figure 10 is the method flow diagram of test DFDAU according to an embodiment of the invention;
Figure 11 is that the test aircraft message on test platform of the present invention triggers the method flow diagram of logic according to one embodiment of present invention.
Embodiment
Fig. 1 is the schematic diagram of aircraft DFDAU working condition.Digital flying quality securing component DFDAU(Digital Flight Data Acquisition Unit) receive aircraft states data or the control command data from airborne sensor or other equipment.The data acquisition subsystem of DFDAU is converted to digital signal by the aircraft states data of obtaining or control command data and broadcasts.Quick access recorder QAR(Quick Access Recorder) receive aircraft states data or the control command data of broadcast and store.Wherein, a part of data are stored in flight data recorder FDR(Flight Data Recorder),, in " black box ", so that after aircraft generation unexpected incidents, for the relevant personnel, investigate and analyse.
Aircraft states supervisory system ACMS(Aircraft Condition Monitoring System) also from the data acquisition subsystem of DFDAU, receive aircraft states data or the control command data of broadcast.ACMS monitors, collects, and records aircraft states data or control command data, and under certain trigger condition, exports predetermined aircraft states data or control command data, for navigational matters and the daily monitoring aircraft states of flight crew and performance.Because its data content and form can be changed by user, so be called message.
ACMS message is controlled and is produced by integrated application software.Message is by the threshold value of particular aircraft state parameter or the combinational logic of multinomial particular aircraft state parameter, and specific message triggering logic triggers.The ACMS message that manufacturer's design of ACMS and the message of test trigger logic generation is called basic message.A lot of basic messages have become civil aviation administrative authority specified standard.The Boeing-737 NG aircraft of take is example, and the basic message of ACMS of its use approximately has more than 20.
Fig. 2 is according to an embodiment of the invention for testing the test platform architecture schematic diagram of DFDAU.According to one embodiment of present invention, the DFDAU that DFDAU test platform can be tested comprises the 2233000-8XX type that Teledyne company produces, the 967-0212-XXX type that HoneyWell company produces, or the 261303879-XXXX type of Sagem company production, wherein X.. represents concrete model.It will be appreciated by those skilled in the art that above model is only for giving an example.Test platform of the present invention also can be applied to the test of other DFDAU.
As shown in the figure, test platform of the present invention comprises input interface, is used for inputting aircraft states data or control command data.According to one embodiment of the present invention, input interface is wired network interface, USB interface, radio network interface, blue tooth interface etc.It will be appreciated by those skilled in the art that the implementation of any data input all can be used for the configuration of the input interface of test platform.
For the signal environment on accurate reproduction aircraft, the DFDAU of test platform of the present invention is input as the simulate signal producing from simulate signal generation module.The data that the aircraft signal of the type of these simulate signals and characteristic and the collection of aircraft sensor and other aircraft states assembly transmit are in full accord.
According to one embodiment of present invention, the Data Source of the simulate signal of signal generating module, it is test data, comprise two kinds: a kind of is the aircraft running status emulated data of writing according to aircraft data standard, and another kind is aircraft states data or the control command data being stored on airborne quick access recorder QAR.
The generation that all kinds of events were simulated and reproduced to the aircraft running status emulated data that use is write according to aircraft data standard better.Because aircraft operation is very high to reliability requirement, aircraft is in operation and occurs that the probability of a certain particular event is unpredictable, by use, according to aircraft data standard, write voluntarily emulated data and can provide any value of arbitrary signal and the combination between arbitrary signal, the generation of manual control particular event, thus testing efficiency greatly improved.
Use is stored in the true environment that the True Data of aircraft states on airborne quick access recorder QAR or the True Data of control command can complete reproduction aircrafts, the situation during generation that can reproduce better fault.
According to one embodiment of present invention, the simulate signal of inputting DFDAU on test platform of the present invention relates to a plurality of systems on aircraft, comprise: housing construction, engine, avionics system, Mechatronic Systems, hydraulic pressure, fuel oil, ring control, and control system etc.The signal kinds relating to is a lot, comprising: simulating signal, discrete signal and aviation private bus signal etc.; And these signals have the correlativity on time and value.
According to one embodiment of present invention, test data via input interface by being connected to signal generating module based on data highway system.These data buss comprise but are not limited to PXI bus, pci bus, PCIE bus, vxi bus etc.
According to one embodiment of present invention, test platform further comprises signal condition adapter.The simulate signal that signal condition adapter produces the signal generating module based on data highway system is further nursed one's health, such as means such as amplification or decay, isolation, multipath conversion, to guarantee quality and the stability of signal, meet for the high requirement of aircraft states aircraft data-signal precision.
According to one embodiment of present invention, test platform further comprises wiring expansion equipment.The signal of process conditioning, before inputing to DFDAU, strengthens the alternative of input by wiring expansion equipment, form the optional termination connecing that leads to.According to one embodiment of present invention, wiring expansion equipment comprises different subregions, and each subregion is for a kind of signal type.Thus, in wiring expansion equipment, the importing joint of various signals is very clear, and both convenient management, also conveniently realized the logical combination of various signals.
The simulate signal that signal generating module generates, after conditioning, is input in wiring expansion equipment, then enters in DFDAU, realizes the simulation of the working environment of DFDAU in aircraft operational process.
According to one embodiment of the present invention, receive aircraft states data or the control command data of the broadcast of DFDAU data acquisition subsystem, again itself and the raw data of input are compared, just can determine that whether DFDAU is working properly, thereby realize the test to DFDAU.
According to one embodiment of present invention, test platform comprises a comparison module, compare the aircraft states data of input interface or aircraft states data or the control command data of control command data and the broadcast of described DFDAU data acquisition subsystem from test platform, and export comparative result.According to one embodiment of present invention, when existing multinomial aircraft states data or control command data to compare, comparison module can complete aircraft states data corresponding in the aircraft states data of every input interface or control command data and described message or the comparison of control command data automatically, and exports the two different aircraft states data or control command data.
According to another embodiment of the invention, directly do not receive the digital signal of DFDAU broadcast, and the message that can issue by parsing DFDAU obtains the output data of DFDAU.By writing voluntarily ACMS message triggering logic, can produce customization message.Customization message can be so that those skilled in the art be no longer limited by the restriction of parameter in basic message, and can directly face tens thousand of aircraft states parameters.
For the test of DFDAU, according to one embodiment of present invention, for DFDAU, process the parameter that may go wrong and write customization message triggering logic.After obtaining corresponding message, aircraft states data or the control command data of the aircraft states data in message or control command data and input are contrasted, just can determine that whether DFDAU is correct to the processing of these aircraft states data or control command data.
According to one embodiment of present invention, test platform comprises a comparison module, relatively from the aircraft states data of the input interface of test platform or aircraft states data or the control command data in control command data and described message, and export comparative result.According to one embodiment of present invention, when existing multinomial aircraft states data or control command data to compare, comparison module can complete aircraft states data corresponding in the aircraft states data of every input interface or control command data and described message or the comparison of control command data automatically.
According to one embodiment of present invention, test platform comprises printer and/or display.Printer and/or display receive the output of DFDAU, by the output to DFDAU, decode, the message of DFDAU output is printed and/or is shown, for operating personnel's inspection and.According to one embodiment of present invention, the printer of test platform is virtual printer.
According to one embodiment of present invention, test platform further comprises general printing and/or display device, the result of its demonstration or the output of printing comparison module.
According to one embodiment of present invention, there is part and part of detecting and respectively comprise that a power supply is used to and provide the various piece of test platform that power supply is provided in the simulate signal of test platform.For example, 115V400Hz AC power.
Fig. 3 is simulate signal generation modular structure schematic diagram according to an embodiment of the invention.As shown in Figure 3, in the present embodiment, simulate signal generation module integration a plurality of simulate signal generating units.According to one embodiment of present invention, test data is inputted by the test data input interface of test platform, is connected to each simulate signal generating unit of simulate signal generation module under the control of bus controller by data bus.
According to one embodiment of present invention, utilize the data acquisition processing system of PXI bus Open architecture, by various interface plate, on the platform of bussing technique, realize obtaining and controlling of signal.Wherein, PXI bus is opening, the modular instrument bus of a kind of high-performance low price of American National instrument company (NI) issue.It will be appreciated by those skilled in the art that PXI bus is only introduced and illustrated as an optional example.The data bus of other types also can be applied in the solution of the present invention.
According to one embodiment of present invention, the simulate signal generating unit of simulate signal generation module integration comprises discrete signal generating unit, voltage signal generating unit, simulating signal generating unit and bus signals generating unit.
According to one embodiment of present invention, discrete signal generating unit comprises switching value signal generating unit; Simulating signal generating unit comprises: alternating voltage ratio signal ACVR generating unit, and synchronizing signal SYNC generating unit; Bus signals generating unit comprises ARINC429 bus signals generating unit, and ARINC619 bus signals generating unit.
According to one embodiment of present invention, switching value generating unit comprises high density general-purpose relay matrix, and it is configured to the switching value signal of the hundreds of passages of emulation, and for example the general hilted broadsword list of high density is put relay card.According to one embodiment of present invention, switching value generating unit comprises digital switch array.
According to one embodiment of present invention, voltage signal generating unit comprises quiescent voltage output board card, emulation low-voltage direct LLDC(Low Level Direct Current) signal.According to one embodiment of present invention, the PXI-6704 multifunctional static Voltage-output board that voltage signal generating unit can WeiNI company be produced.
According to one embodiment of present invention, the substandard digital signal generating unit of ARINC429 comprises 429 bus boards.According to one embodiment of present invention, the ACX429 board that 429 bus boards can WeiAIM company be produced.
According to one embodiment of present invention, the substandard digital signal generating unit of ARINC619 comprises 619 bus boards.According to one embodiment of present invention, the ACX619 board that 619 bus boards can WeiAIM company be produced.
Fig. 4 is the structural representation of alternating voltage ratio signal ACVR signal generating unit according to an embodiment of the invention.As shown in Figure 4, ACVR signal generating unit 400 comprises ac voltage signal converting unit 401, and it is connected to power supply and the ac voltage signal of 115V400Hz is converted to the reference ac voltage signal of 26V400Hz; Digital signal branch road 402, it receives the digital signal from bus system; Modulator 403, it receives this ac voltage signal and digital signal, and this digital signal is converted to alternating voltage ratio signal; And output transformer 404, the alternating voltage ratio signal that its output generates.According to one embodiment of the present invention, ac voltage signal converting unit 401 is carried out frequency conversion and/or transformation by the ac voltage signal that power supply is provided, and produces needed with reference to ac voltage signal.According to one embodiment of present invention, ACVR signal generating unit is that a digital signal is to the D/A converting unit of alternating voltage ratio signal.
Fig. 5 is the structural representation of alternating voltage ratio signal ACVR signal generating unit according to another embodiment of the invention.As shown in Figure 5, ACVR signal generating unit 500 comprises ac voltage signal converting unit 501, and it produces 26V400Hz ac voltage signal by the ac voltage signal of power supply is carried out to frequency conversion and/or transformation.
ACVR signal generating unit 500 also comprises digital signal branch road 502, modulator 503, and output transformer 504.Digital signal branch road 502 further comprises bus adapter 5021, bus driving circuits 5022 and level shifting circuit 5023.Bus adapter 5021 is connected with external bus system, for obtaining the digital signal from external bus.Bus driving circuits 5022 is used for driving this digital signal.Level shifting circuit 5023 is adjusted into the required level of modulator 503 by the level of this digital signal.Modulator 503 receives with reference to ac voltage signal from ac voltage signal converting unit 501, according to the digital signal from data bus of being inputted by digital signal branch road, to carry out amplitude modulation with reference to ac voltage signal, generates corresponding alternating voltage ratio signal.
Output transformer 504 these alternating voltage ratio signals of output.
For example, on aircraft redundant hydraulic force value by alternating voltage ratio signal indication.In order to realize the emulation to this signal, modulator 503 completes the modulation to reference voltage signal according to following formula:
Up（AC）=26（-0.49E-5Pressure+0.5985）；
Wherein, the effective value that Up(AC) represents ac voltage signal; Pressure represents the force value of input, and its value is 0-4000PSI.Thus, by ACVR signal generating unit 500, just can simulate redundant hydraulic force value alternating voltage ratio signal on the aircraft within the scope of 0-4000PSI.
Fig. 6 is the schematic diagram of synchronous SYNC signal generating unit according to an embodiment of the invention.Synchronous SYNC signal is also referred to as shaft angle signal.As shown in Figure 6, SYNC signal generating unit comprises an ac voltage signal converting unit 601, the ac voltage signal that it is connected to power supply provides be converted to required two groups with reference to alternating voltage synchronizing signal; Digital signal branch road 602, it receives the digital signal from bus system; Modulator 603, it receives this alternating voltage synchronizing signal and digital signal, and this digital signal is converted to alternating voltage synchronizing signal; And output transformer 604, the synchronizing signal that its output generates.According to one embodiment of present invention, SYNC signal generating unit is that a digital signal is to the D/A converting unit of alternating voltage synchronizing signal.
Fig. 7 is the structural representation of the synchronous SYNC signal generating unit of alternating voltage according to another embodiment of the invention.As shown in Figure 7, SYNC signal generating unit 700 comprises ac voltage signal converting unit 701, and it is connected to power supply and the ac voltage signal of 115V400Hz is converted to the reference ac voltage signal of two groups of 28V400Hz.
SYNC signal generating unit 700 also comprises digital signal branch road 702 and modulator 703.Digital signal branch road 702 comprises bus adapter 7021, bus driving circuits 7022 and level shifting circuit 7023.Bus adapter 7021 is connected with external bus system, for obtaining the digital signal from external bus.Bus driving circuits 7022 is used for driving this digital signal.Level shifting circuit 7023 is adjusted into the required level of modulator 703 by the level of this digital signal.
The modulator 703 of SYNC signal generating unit comprises quadrant switch 7031, sin multiplier 7032 and cos multiplier 7033.Two groups of ac voltage signals enter respectively in sin multiplier 7032 and cos multiplier 7033 after quadrant switch 7031.From 2 bit representation of the digital signal of external bus the quadrant of angle, remainder represents the angle value of a 0-90 degree.Thus, the angle value that represents 0-360 degree.2 of digital signal are input in quadrant switch 7031, and remainder is input in sin multiplier 7032 and cos multiplier 7033.After sin multiplier 7032 and cos multiplier 7033, the phase differential between two groups of ac voltage signals has just represented this angle value.
SYNC signal generating unit 700 further comprises amplifier 7041 and 7042, and the output signal of sin multiplier 7032 and cos multiplier 7033 is carried out to power amplification; And output transformer 705, be used for exporting this synchronizing signal.Thus, realized the simulation of shaft angle signal.
According to one embodiment of present invention, said modulator can realize by four-quadrant multiplier.
According to one embodiment of present invention, the wiring expansion equipment of test platform part of detecting comprises patching panel.Fig. 8 is the structural representation of patching panel according to an embodiment of the invention.As shown in the figure, patching panel 800 comprises: patching panel panel 801 and a plurality of output interface 802-804 etc.According to one embodiment of present invention, patching panel 801 comprises a plurality of plug wire holes, the aircraft signal transmission apparatus that each plug wire hole can certain type communication of pegging graft.Each output interface, corresponding to the signal of a type, is connected respectively to the input interface of the corresponding types of DFDAU.Each output interface comprises a plurality of lead-out terminals, and each lead-out terminal is corresponding with a plug wire hole of patching panel 801.
Fig. 9 is the schematic diagram of patching panel panel according to an embodiment of the invention.As shown in Figure 9, patching panel panel comprises a plurality of regions: aircraft type designator is selected region 901, simulating signal region 902 and bus signals region 903.Alternatively, patching panel panel comprises switching value signal area.Aircraft type designator selects region 901 to be used to refer to the type of aircraft.
By dissimilar signal is placed into respectively in different regions, facilitate tester to manage test signal.And by patching panel, tester can complete the logical combination of the test signal of number of different types as required, the collection situation of aircraft states data or control command data signal under emulation true environment.Patching panel panel further comprises power supply access region 904 and ground wire access region 905.
According to one embodiment of present invention, alternatively, patching panel comprises automatic switching module.From the input signal of patching panel panel 801, be linked into the input end of automatic switching module, the output terminal of automatic switching module is connected to a plurality of output interface 802-804.Automatic switching module is realized the automatic switchover between patching panel panel 801Ge road input signal and each lead-out terminal of a plurality of output interface 802-804.Utilize automatic switching module, the switching that operating personnel needn't be between each road signal of patching panel panel 801 manual operations, can greatly facilitate test operation.
According to another embodiment of the invention, wiring expansion equipment comprises automatic switching module, input interface and output interface.This input interface comprises a plurality of input terminals, and each input terminal can be connected communication with the aircraft signal transmission apparatus of certain type.This output interface comprises a plurality of lead-out terminals, and each lead-out terminal is corresponding with an input terminal of described input interface.The automatic switching module of wiring expansion equipment, the automatic switchover being used between described patching panel panel Shang Ge road input signal and each lead-out terminal of described a plurality of output interfaces.
According to one embodiment of present invention, automatic switching module can comprise the switch matrix being arranged in rows and columns.All input signals form each row and all each row of lead-out terminal formation.A switch is set on the point of crossing of each row and row, thereby forms switch matrix.By these switches in gauge tap matrix, just can realize the automatic switchover between input signal and lead-out terminal.
According to one embodiment of present invention, alternatively, patching panel comprises multimeter module and line scanning module.Because patching panel has comprised the connection line of the One's name is legion between input and output terminal, these connection lines may lose efficacy due to a variety of causes.And be loaded down with trivial details and a require great effort job for the inspection of inefficacy circuit.Whether multimeter module, by measuring electric current and the voltage of connection line, can check connection line to lose efficacy.Line scanning module can automatically switch between each connection line, thereby multimeter module is connected in different connection lines.By multimeter module and line scanning module, can realize easily " self check ", check out all inefficacy circuits.
Figure 10 is the method flow diagram of test DFDAU according to an embodiment of the invention.As shown in the figure, in method of testing 1000, in step 1010, by input interface, on test platform, be written into as the aircraft states data of writing voluntarily according to air communications standard of test data or control command data or from aircraft states data or the control command data of QAR.In step 1020, according to being written into test data, by simulate signal generation module, generate the simulate signal of simulation aircraft real running environment.In step 1030, the simulate signal of generation is inputted to DFDAU to be tested.According to some specific embodiment of the present invention, this step may further include the conditioning of simulate signal and adaptation.According to some specific embodiment of the present invention, this step may further include the various signals of manual wiring configuration input DFDAU.In step 1040, whether consistent with the test data being written into by the data of comparison module DFDAU broadcast more to be tested.Or in step 1050, whether the data in the message issuing by comparison module DFDAU more to be tested are consistent with the test data being written into.In step 1060, according to comparative result, draw test result.
Figure 11 is the method flow diagram of the test DFDAU on test platform of the present invention according to one embodiment of present invention.As shown in figure 11, in method of testing 1100, in step 1110, on patching panel, select aircraft type designator, and by required simulating signal, bus signals lead-in wire access patching panel.In step 1120, import the aircraft states data write voluntarily or control command data or from aircraft states data or the control command data of QAR.In step 1130, bus controller reads in aircraft states data or control command data from input interface, and is occurred to each signal generating unit in simulate signal generation module, produces respective switch amount signal, simulating signal and/or bus signals.In step 1140, the signal that each signal generating unit produces, after the conditioning of conditioning adapter, through patching panel, is inputted DFDAU to be tested.
In step 1150, DFDAU to be tested receives after signal, is translated into digital signal outwards broadcast.In step 1160, obtain aircraft states data or the control command data of DFDAU to be tested broadcast, the aircraft states data of DFDAU broadcast more to be tested or control command data are consistent with the whether aircraft states data or the control command data that are written into.If obtain consistent result, enter step 1170, show that DFDAU to be tested is by the result of this test; If do not obtain, in step 1180, the corresponding failure message of output DFDAU.
In step 1151, DFDAU to be tested receives after signal, and its inner ACMS system triggers logic according to the message that obtains particular aircraft status data or control command data, generates the message that comprises corresponding aircraft states data or control command data.In step 1161, comparison module receives, analytic message, and judges that the aircraft states data obtained in message or control command data are consistent with the whether aircraft states data or the control command data that are written into.If obtain consistent result, enter step 1170, show that DFDAU to be tested is by the result of this test; If do not obtain, in step 1180, the corresponding failure message of output DFDAU.
Test platform of the present invention is complete has reproduced the data environment on aircraft.On test platform of the present invention, carrying out test result is on all four with the test result of carrying out on actual aircraft.Therefore, DFDAU completes after test on test platform of the present invention, can directly apply in aircraft.Test platform of the present invention and method of testing have realized the test fast and accurately of DFDAU.Thus, operating personnel can monitor the state of aircraft more accurately, guarantee the safety of flight.
Above-described embodiment is used for illustrative purposes only, and be not limitation of the present invention, the those of ordinary skill in relevant technologies field, without departing from the present invention, can also make a variety of changes and modification, therefore, all technical schemes that are equal to also should belong to category disclosed by the invention.
Claims (30)
1. a test platform of aircraft DFDAU, comprising:
Input interface, it receives test data;
Simulate signal generation module, it produces simulate signal according to described test data;
Wiring expansion equipment, it is used for forming gateable termination, and wherein said simulate signal accesses in DFDAU to be tested by described wiring expanding unit; And
Comparison module, it is the test data based on described simulate signal and the test data that inputs to described input interface from described DFDAU to be tested relatively.
2. test platform according to claim 1, wherein said aircraft states data or control command data comprise aircraft states data or the control command data of writing according to air communications standard.
3. test platform according to claim 1, wherein said aircraft states data or control command data comprise aircraft states data or the control command data from aircraft quick access recorder QAR.
4. according to the test platform described in claim 2 or 3, whether the test data based on described simulate signal of the more described DFDAU broadcast to be tested of wherein said comparison module is consistent with the test data that inputs to described input interface, and exports inconsistent aircraft states data or control command data.
5. test platform according to claim 1, test data and the test data that inputs to described input interface based on described simulate signal in the message that the more described DFDAU to be tested of wherein said comparison module produces.
6. test platform according to claim 1, wherein simulate signal generation module comprises discrete signal generating unit, voltage signal generating unit, simulating signal generating unit and/or bus signals generating unit; Wherein said input interface is connected to various discrete signal generating unit, voltage signal generating unit, simulating signal generating unit and/or bus signals generating unit by bus system.
7. test platform according to claim 6, wherein discrete signal generating unit comprises switching value signal generating unit; Wherein said switching value signal generating unit comprises relay array.
8. test platform according to claim 6, wherein discrete signal generating unit comprises switching value signal generating unit; Wherein said switching value signal generating unit comprises switch arrays.
9. test platform according to claim 6, wherein simulating signal generating unit comprises alternating voltage ratio signal ACVR generating unit, described ACVR signal generating unit comprises ac voltage signal converting unit, and it is connected to power supply and produces the ac voltage signal with required effective value and frequency; Digital signal branch road, it receives the digital signal from described bus system; Modulator, it receives described ac voltage signal and digital signal, and described digital signal is converted to alternating voltage ratio signal; And output transformer, it exports described alternating voltage ratio signal.
10. test platform according to claim 9, wherein said digital signal branch road comprises bus adapter, it is connected with described portion bus system, for obtaining the digital signal from external bus; Bus driving circuits, it is used for driving described digital signal; And level shifting circuit, its level by this digital signal is adjusted into the required level of described modulator.
11. test platforms according to claim 9, wherein said modulator, according to the digital signal from described bus system by described digital signal branch road input, is modulated and is generated corresponding alternating voltage ratio signal the effective value of described ac voltage signal.
12. test platforms according to claim 6, wherein simulating signal generating unit comprises synchronizing signal SYNC generating unit, described SYNC signal generating unit comprises ac voltage signal converting unit, and it is connected to power supply and produces the ac voltage signal of required effective value and frequency; Digital signal branch road, it receives the digital signal from bus system; Modulator, it receives this ac voltage signal and digital signal, and this digital signal is converted to alternating voltage synchronizing signal; And output transformer, it exports described alternating voltage synchronizing signal.
13. test platforms according to claim 6, wherein simulating signal generating unit comprises synchronizing signal SYNC generating unit, described synchronizing signal SYNC signal generating unit comprises:
Ac voltage signal converting unit, it is connected to power supply and produces two groups of ac voltage signals;
Digital signal branch road, it comprises:
Bus adapter, it is connected with external bus system, for obtaining the digital signal from external bus;
Bus driving circuits, it is used for driving this digital signal; And
Level shifting circuit, its level by this digital signal is adjusted into required level;
Modulator, it comprises:
Quadrant switch;
Sin multiplier; And
Cos multiplier,
Wherein said two groups of ac voltage signals enter respectively described sin multiplier and described cos multiplier after described quadrant switch, and this digital signal is converted to two groups of ac voltage signals that differ a phase bit;
The first amplifier and the second amplifier, it is used for the output signal of sin multiplier and cos multiplier to carry out power amplification; And
Output transformer, it is used for exporting described two groups of ac voltage signals that differ a phase bit.
14. test platforms according to claim 6, wherein said bus signals generating unit comprises ARINC429 bus signals generating unit and ARINC629 bus signals generating unit.
15. test platforms according to claim 6, further comprise signal condition adapter, and the simulate signal that described signal generating module is produced is nursed one's health.
16. test platforms according to claim 1, described wiring expansion equipment comprises patching panel, described patching panel comprises: patching panel panel; And a plurality of output interfaces;
Wherein, patching panel panel comprises a plurality of plug wire holes, and each plug wire hole can be pegged graft and communicate by letter with described simulate signal generation module Yi road output signal;
Wherein, each output interface, corresponding to the signal of a type, is connected respectively to the input interface of the corresponding types of DFDAU;
Wherein, each output interface comprises a plurality of lead-out terminals, and each lead-out terminal is corresponding with a plug wire hole of described patching panel panel.
17. test platforms according to claim 16, described patching panel panel comprises: simulating signal region, bus signals region, power supply access region and ground wire access region.
18. test platforms according to claim 16, described patching panel comprises automatic switching module, it is used for the automatic switchover between described patching panel panel Shang Ge road input signal and each lead-out terminal of described a plurality of output interfaces.
19. test platforms according to claim 1, wherein said wiring expansion equipment comprises input interface and output interface; Described input interface comprises a plurality of input terminals, and each input terminal can be pegged graft and communicate by letter with described simulate signal generation module Yi road output signal; Described output interface comprises a plurality of lead-out terminals, and each lead-out terminal is corresponding with a plug wire hole of described patching panel panel;
Described wiring expansion equipment comprises automatic switching module, and it is used for the automatic switchover between each input terminal of described input interface and each lead-out terminal of described a plurality of output interfaces.
20. according to the test platform described in claim 18 or 19, and wherein said automatic switching module comprises the switch matrix being arranged in rows and columns.
21. test platforms according to claim 1, wherein said wiring expansion equipment comprises multimeter module and line scanning module; Whether wherein said multimeter module, by measuring electric current and the voltage of connection line, can check connection line to lose efficacy; Wherein said line scanning module can automatically switch between each connection line, thereby multimeter module is connected in different connection lines.
22. 1 kinds of methods of on the aircraft DFDAU test platform as described in claim 1-21, DFDAU to be tested being tested, comprising:
On described test platform, be written into test data;
According to described test data, produce simulate signal;
By described simulate signal access wiring expansion equipment;
Reception is from the simulate signal of described wiring expansion equipment, and described simulate signal is accessed in DFDAU to be tested; And
Compare the test data based on described simulate signal and the test data that is loaded into described test platform from described DFDAU to be tested.
23. method of testings according to claim 22, wherein said test data comprises aircraft states data or the control command data of writing according to air communications standard.
24. method of testings according to claim 22, wherein said test data comprises aircraft states data or the control command data from aircraft quick access recorder QAR.
25. according to the method for testing described in claim 23 and 24, and wherein said DFDAU to be tested is converted to aircraft states data or control command data or control command data broadcast by the simulate signal from described wiring expansion equipment; Wherein said comparison step comprises: relatively input to the described test data of input interface and aircraft states data or the control command data of DFDAU broadcast.
26. according to the method for testing described in claim 23 and 24, further comprises: wherein said DFDAU to be tested is converted to the simulate signal from described wiring expansion equipment aircraft states data or control command data or control command data and triggers logic according to message and generates the message relevant with aircraft signal transmission apparatus to be tested; Wherein said comparison step comprises aircraft states data or the control command data relatively inputing in the described test data of the input interface message relevant with aircraft signal transmission apparatus described and to be tested.
27. method of testings according to claim 22, further comprise: adjust this message and trigger logic.
28. method of testings according to claim 22, further comprise: for particular aircraft status data or control command data on aircraft, determine in the message that comprises described particular aircraft status data or control command data and the message of this message triggering logic.
29. method of testings according to claim 22, further comprise: utilize bus controller from input interface, to read in aircraft states data or control command data or control command data, and send it to each signal generating unit in described simulate signal generation module, produce respective switch amount signal, simulating signal and/or bus signals.
30. method of testings according to claim 29, further comprise: switching value signal, simulating signal and/or the bus signals that each signal generating unit is produced is through the conditioning of conditioning adapter.
Priority Applications (10)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310191379.4A CN104181908B (en) | 2013-05-22 | 2013-05-22 | A kind of DFDAU test platform and method of testing |
| CA2852080A CA2852080C (en) | 2013-05-22 | 2014-05-21 | Test apparatus and test method based on dfdau |
| US14/284,017 US9639997B2 (en) | 2013-05-22 | 2014-05-21 | Test apparatus and test method based on DFDAU |
| JP2014106166A JP6223277B2 (en) | 2013-05-22 | 2014-05-22 | Test apparatus and test method based on DFDAU |
| TW103117845A TWI616377B (en) | 2013-05-22 | 2014-05-22 | Test appartus based on digital flight data acquisition unit (dfdau) |
| KR1020140061831A KR102052219B1 (en) | 2013-05-22 | 2014-05-22 | Test apparatus and test method based on dfdau |
| EP14169533.8A EP2818953B1 (en) | 2013-05-22 | 2014-05-22 | Test apparatus and test method based on DFDAU |
| AU2014202810A AU2014202810B2 (en) | 2013-05-22 | 2014-05-22 | Test apparatus and test method based on dfdau |
| SG10201402576SA SG10201402576SA (en) | 2013-05-22 | 2014-05-22 | Test Apparatus and Test Method based on DFDAU |
| HK15100979.8A HK1200546A1 (en) | 2013-05-22 | 2015-01-28 | Test apparatus and test method based on dfdau dfdau |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310191379.4A CN104181908B (en) | 2013-05-22 | 2013-05-22 | A kind of DFDAU test platform and method of testing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104181908A true CN104181908A (en) | 2014-12-03 |
| CN104181908B CN104181908B (en) | 2017-12-01 |
Family
ID=51963046
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310191379.4A Active CN104181908B (en) | 2013-05-22 | 2013-05-22 | A kind of DFDAU test platform and method of testing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104181908B (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104965143A (en) * | 2015-07-13 | 2015-10-07 | 北京博曼迪汽车科技有限公司 | Combustion gas ECU test system |
| CN105159141A (en) * | 2015-08-11 | 2015-12-16 | 中国航空工业集团公司西安飞机设计研究所 | Fax control law transmission ratio verification method and apparatus |
| CN107450013A (en) * | 2017-09-15 | 2017-12-08 | 北京锐视康科技发展有限公司 | A kind of circuit board functional completeness test platform and method of testing |
| CN111071481A (en) * | 2020-01-02 | 2020-04-28 | 北京航天测控技术有限公司 | Universal test platform integration method and system |
| CN111210668A (en) * | 2019-12-30 | 2020-05-29 | 四川函钛科技有限公司 | Landing stage flight trajectory offset correction method based on time sequence QAR parameter |
| CN112441255A (en) * | 2020-11-10 | 2021-03-05 | 山东盖特航空科技有限公司 | Automatic testing device and method for flight parameter quick-taking recording system |
| CN112498736A (en) * | 2019-09-16 | 2021-03-16 | 上海飞机制造有限公司 | Universal bus test system suitable for AFDX bus |
| CN113885392A (en) * | 2021-10-18 | 2022-01-04 | 卡斯柯信号有限公司 | Fuse-free discrete output safety state escape protection system for safety output |
| CN114002590A (en) * | 2020-07-28 | 2022-02-01 | 北京机械设备研究所 | Travel switch detection method and system |
| CN114217599A (en) * | 2021-12-14 | 2022-03-22 | 北京机电工程研究所 | Aircraft ground energy control platform |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4470116A (en) * | 1982-08-02 | 1984-09-04 | United Technologies Corporation | Digital flight data recording system |
| US5023791A (en) * | 1990-02-12 | 1991-06-11 | The Boeing Company | Automated test apparatus for aircraft flight controls |
| US20040160340A1 (en) * | 2003-02-17 | 2004-08-19 | Thomson Deane A. | Methods and apparatus for transportation vehicle security monitoring |
| CN1736043A (en) * | 2002-11-11 | 2006-02-15 | 航空力学服务有限公司 | Aircraft flight data management system |
| CN101023589A (en) * | 2004-09-16 | 2007-08-22 | 哈里公司 | System and method of transmitting data from an aircraft |
| CN102033494A (en) * | 2010-12-14 | 2011-04-27 | 西北工业大学 | Signal conditioning device orienting flight control simulation |
| CN102092477A (en) * | 2010-11-30 | 2011-06-15 | 中国民航大学 | Device and method for automatic test and fault diagnosis of plane audio integrated system |
| CN202677183U (en) * | 2012-03-02 | 2013-01-16 | 昌河飞机工业（集团）有限责任公司 | Integrated test equipment of flight control system |
| CN102915029A (en) * | 2012-10-15 | 2013-02-06 | 中国运载火箭技术研究院 | Avionics system automatic test platform based on reusable spacecraft |
| CN103065022A (en) * | 2013-01-24 | 2013-04-24 | 无锡华航电子科技有限责任公司 | Incentive model simulation platform for aerocraft electronic system |
-
2013
- 2013-05-22 CN CN201310191379.4A patent/CN104181908B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4470116A (en) * | 1982-08-02 | 1984-09-04 | United Technologies Corporation | Digital flight data recording system |
| US5023791A (en) * | 1990-02-12 | 1991-06-11 | The Boeing Company | Automated test apparatus for aircraft flight controls |
| CN1736043A (en) * | 2002-11-11 | 2006-02-15 | 航空力学服务有限公司 | Aircraft flight data management system |
| US20040160340A1 (en) * | 2003-02-17 | 2004-08-19 | Thomson Deane A. | Methods and apparatus for transportation vehicle security monitoring |
| CN101023589A (en) * | 2004-09-16 | 2007-08-22 | 哈里公司 | System and method of transmitting data from an aircraft |
| CN102092477A (en) * | 2010-11-30 | 2011-06-15 | 中国民航大学 | Device and method for automatic test and fault diagnosis of plane audio integrated system |
| CN102033494A (en) * | 2010-12-14 | 2011-04-27 | 西北工业大学 | Signal conditioning device orienting flight control simulation |
| CN202677183U (en) * | 2012-03-02 | 2013-01-16 | 昌河飞机工业（集团）有限责任公司 | Integrated test equipment of flight control system |
| CN102915029A (en) * | 2012-10-15 | 2013-02-06 | 中国运载火箭技术研究院 | Avionics system automatic test platform based on reusable spacecraft |
| CN103065022A (en) * | 2013-01-24 | 2013-04-24 | 无锡华航电子科技有限责任公司 | Incentive model simulation platform for aerocraft electronic system |
Non-Patent Citations (3)
| Title |
|---|
| 尚华，等: "飞行控制系统信号模拟器的设计", 《测控技术》 * |
| 王国华，等: "飞行数据采集器通用自动测试软件", 《测试技术学报》 * |
| 田建学，等: "直流电压比率信号变换ARINC429数据信号的方案研究", 《飞行设计》 * |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104965143A (en) * | 2015-07-13 | 2015-10-07 | 北京博曼迪汽车科技有限公司 | Combustion gas ECU test system |
| CN105159141A (en) * | 2015-08-11 | 2015-12-16 | 中国航空工业集团公司西安飞机设计研究所 | Fax control law transmission ratio verification method and apparatus |
| CN107450013A (en) * | 2017-09-15 | 2017-12-08 | 北京锐视康科技发展有限公司 | A kind of circuit board functional completeness test platform and method of testing |
| CN107450013B (en) * | 2017-09-15 | 2023-05-12 | 北京锐视康科技发展有限公司 | Circuit board functional integrity test platform and test method |
| CN112498736B (en) * | 2019-09-16 | 2022-09-09 | 上海飞机制造有限公司 | Universal bus test system suitable for AFDX bus |
| CN112498736A (en) * | 2019-09-16 | 2021-03-16 | 上海飞机制造有限公司 | Universal bus test system suitable for AFDX bus |
| CN111210668A (en) * | 2019-12-30 | 2020-05-29 | 四川函钛科技有限公司 | Landing stage flight trajectory offset correction method based on time sequence QAR parameter |
| CN111071481A (en) * | 2020-01-02 | 2020-04-28 | 北京航天测控技术有限公司 | Universal test platform integration method and system |
| CN111071481B (en) * | 2020-01-02 | 2021-06-01 | 北京航天测控技术有限公司 | Universal test platform integration method and system |
| CN114002590A (en) * | 2020-07-28 | 2022-02-01 | 北京机械设备研究所 | Travel switch detection method and system |
| CN114002590B (en) * | 2020-07-28 | 2024-01-30 | 北京机械设备研究所 | Travel switch detection method and system |
| CN112441255A (en) * | 2020-11-10 | 2021-03-05 | 山东盖特航空科技有限公司 | Automatic testing device and method for flight parameter quick-taking recording system |
| CN113885392A (en) * | 2021-10-18 | 2022-01-04 | 卡斯柯信号有限公司 | Fuse-free discrete output safety state escape protection system for safety output |
| CN114217599A (en) * | 2021-12-14 | 2022-03-22 | 北京机电工程研究所 | Aircraft ground energy control platform |
| CN114217599B (en) * | 2021-12-14 | 2023-10-17 | 北京机电工程研究所 | Aircraft ground energy control console |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104181908B (en) | 2017-12-01 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104184758B (en) | A kind of test platform and method of testing of airborne vehicle message triggering logic | |
| CN104181908A (en) | DFDAU test platform and test method | |
| KR102052219B1 (en) | Test apparatus and test method based on dfdau | |
| CN109855651B (en) | Ground test system and test method for modern aircraft radio communication navigation system | |
| CN104184525A (en) | Digital-flight-data-acquisition-unit-based test platform and test method of signal transmission device | |
| CN103116287B (en) | Avionics equipment running environment dynamic simulating device and method | |
| CN101620800A (en) | 500 KV substation analog simulation training system | |
| CN204065697U (en) | A kind of automatic testing equipment of avionics system | |
| CN114018591A (en) | Vehicle hardware simulation test system, method, vehicle and storage medium | |
| CN107776911B (en) | PXI bus-based flight parameter system test platform and method | |
| CN103475522A (en) | Device and method for airplane centralized maintenance system simulation | |
| CN111025046B (en) | Test system, method for controlling matrix switch and storage medium | |
| CN102880173A (en) | Simulation testing method, equipment and system | |
| CN103064790A (en) | Testing method for main control computer | |
| CN113050583A (en) | Flight control system ground test platform and test method thereof | |
| CN112193436B (en) | Integrated verification test environment system for civil passenger plane cabin system | |
| CN218213833U (en) | Signal board of suspension interface box board card | |
| KR20230102281A (en) | Test management system using data set and method therefor | |
| CN117193249A (en) | Complex avionics system test and integrated verification platform | |
| CN114661029A (en) | Airworthiness identification test system and method for civil aircraft flight control system | |
| CN102445942A (en) | Dispatching automation simulated plant station system | |
| CN110532712A (en) | Analog detecting method and system, electronic equipment, computer readable storage medium | |
| Ananda | General aviation Light Transport Aircraft avionics: Integration and system tests |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |