CN103472735A - Automatic testing system of avionics system - Google Patents
Automatic testing system of avionics system Download PDFInfo
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- CN103472735A CN103472735A CN 201310438069 CN201310438069A CN103472735A CN 103472735 A CN103472735 A CN 103472735A CN 201310438069 CN201310438069 CN 201310438069 CN 201310438069 A CN201310438069 A CN 201310438069A CN 103472735 A CN103472735 A CN 103472735A
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Abstract
The invention discloses an automatic testing system of an avionics system. The automatic testing system of the avionics system is connected to the tested avionics system (1). The automatic testing system of the avionics system is composed of an aerial carrier flight emulator (2), an external store simulator (3), a conducting exciter (4), a non-avionics system emulator (5), a testing general control platform (6), an each-target simulator (7), an integrated test system (8), a judging and recording system (9) and a prompting system (10). Real-time network connection is conducted on testing auxiliary devices such as the external store simulator, the each-target simulator, the conducting exciter and the aerial carrier flight emulator through the automatic testing system of the avionics system. Each testing auxiliary device is automatically controlled to generate a signal with a strict time series in each inspection step and judgment about data correctness is achieved through a method capable of being called searching type automatic judgment under the control of the testing general control platform so that automatic testing can be achieved. According to the automatic testing system of the avionics system, the efficiency of avionics system testing is effectively improved and the comprehensiveness of automatic testing is improved to a great extent.
Description
Technical field
The present invention relates to structural design and the applied technical field of the test macro of avionics system, a kind of Auto-Test System of avionics system is provided especially.
Background technology
At present in the avionics system integration testing, what the judgement of data stream was adopted is artificial judgment or static automatic decision.Artificial judgment wastes time and energy, and not only delays the product delivery progress, and may produce the situation of the erroneous judgement of failing to judge.And so-called static automatic decision, be exactly after certain checks the step EO, controlling test macro is gathered the data stream on current bus, and the determination methods of correctness as described in patent " Aerial Electronic Equipment function test system " of automatic decision upper all data of this acquisition time, the patent No.: ZL201220652188.4.Although such judgement has improved testing efficiency to a certain extent, to the judgement of a definite time point, if data stream is dynamic change in an operation, just can only judge the correctness of last beat of data due to just, cause judgement not comprehensive.And the operation of each simulator and driver all needs manually to carry out at present, if the sequential unmet demand of operation, or some operate misss are arranged, tending to cause data automatic decision result is mistake, the carrying out of impact test.
People urgently wish to obtain the Auto-Test System of the good avionics system of a kind of technique effect.
Summary of the invention
The Auto-Test System that the purpose of this invention is to provide the good avionics system of a kind of technique effect.
The Auto-Test System of avionics system of the present invention, be connected in tested avionics system 1, it is characterized in that: the Auto-Test System of described avionics system is constructed as follows: carrier aircraft flight simulator 2, store Combinations simulator 3, admittance driver 4, non-avionics system emulator 5, test master control platform 6, each target simulator 7, integrated test system 8, judgement and register system 9, prompt system 10; Wherein:
For providing the carrier aircraft flight simulator 2 of the flight parameter of simulation, avionics system is connected with air data computer with the inertial navigation unit of avionics system, receive the power supply of avionics system, heat, the orders such as store Combinations emission, and the store Combinations simulator 3 of simulating the state of each hanging point store Combinations is connected with avionics system 1, for avionics system provides the radio environment of simulation, as Tacan number of units certificate, the admittance driver 4 of Data-Link information etc. is connected with avionics system 1, the non-avionics system emulator 5 of the Mechatronic Systems of simulated aircraft and flight control system is connected with avionics system, each target simulator 7 is connected with avionics system 1, integrated test system 8 is connected with avionics system 1, control the corresponding data that integrated test system gathers avionics system, and forward these data to judgement and register system, control the automatic decision that it carries out data, and the test master control platform 6 of record data and judged result is connected with integrated test system 8 by the Real-time Network with various original test accessories, automatically control each equipment and produce the data that need, due to the control that is Real-time Network, so these data have sequential accurately, and can not there is the problem of operate miss, simultaneously, test master control platform 6 also sends operation indicating to the avionics system display control apparatus.
Test accessory can be also the combination of a plurality of subsystems; Automatically control each equipment and produce the data that need under current step.Due to the control that is Real-time Network, so these data have sequential accurately, and can not there is the problem of operate miss; The judgement that the data that integrated test system 8 is gathered are carried out automatic decision is connected with test master control platform 6 by Real-time Network with register system 9, and prompt system 10 is connected with test master control platform 6 by Real-time Network.
Described carrier aircraft flight simulator 2 adopts computing machine that the form of board 21 is installed, comprise board 21 and real-time network interface card 14, the carrier aircraft flight parameter that wherein board 21 generates computing module in the carrier aircraft flight simulator by the board passage sends to inertial navigation set 11 and the air data computer 12 in tested avionics system 1; Network interface card 14 is connected with Real-time Network switch 13 by optical-fibre channel in real time, thereby be connected in Auto-Test System, realize receiving the carrier aircraft original state parameter of test master control platform 6 transmissions and change and control, carry out accordingly the calculating of carrier aircraft flight parameter, flight parameter result of calculation is sent to tested avionics system 1; Simultaneously, carrier aircraft flight simulator 2 receives target original state parameter and the variation control that test master control platform 6 sends, and carries out accordingly the flight simulation of target, and the real-time flight parameter of target is returned to test master control platform 1, to be transmitted to each target simulator 7;
Described board 21 is specially the ARINC429 board.
Described store Combinations simulator 3 emulation aircrafts are joined control response logic and the function of the various store Combinations of extension, gather and/or receive all information that in tested avionics system, plug-in property management reason subsystem is exported to store Combinations, simultaneously by true store Combinations steering logic loopback information, real-time network interface card 14 is installed in the store Combinations simulator, on the Real-time Network switch 13 that is connected to Auto-Test System, receive the store Combinations setting state control parameter that test master control platform 6 sends, to complete the simulation of store Combinations.
The radio environment that described admittance driver 4 simulation avionics systems receive, and the mode of injecting by radio frequency is given the admittance equipment of tested avionics system; The combination in any that admittance driver 4 is the subsystems such as compass driver, Tacan driver, Data-Link information incentive device or one of them;
Referring to accompanying drawing 5, the control module 41 of admittance driver 4 realizes the system control of driver, and the excitation control of analog radio-frequency signal, data processing and signal are processed, and being connected by real-time network interface card 14 and Real-time Network switch 13, realize and test being connected of master control platform 6 in test environment, receive the control of test master control platform 6, and the status information of loopback self.
Non-avionics system emulator 5 adopts open industrial computer to add extended housing, and configure on this basis analog output interface circuit plate, discrete magnitude output interface plate, synchronous tolerance output interface plate, frequency quantity output interface plate, universal serial bus RS-422 interface board, the ARINC429 interface board main body as the avionics system emulator, by cable butting on the machine of transit cable box and tested avionics system, realize the test to each system.And by being connected of real-time network interface card and Real-time Network switch, realize with test environment in test master control platform mutual, receive the non-avionics setup parameter that test master control platform sends, produce non-avionics signal with simulation.
The form that test master control platform 6 is installed real-time network interface card with computing machine exists, wherein network interface card 14 is connected on the Real-time Network switch 13 of Auto-Test System by optical-fibre channel in real time, send the original state parameter of carrier aircraft and target and change to carrier aircraft flight simulator 2 and control, and receive the target of carrier aircraft flight simulator loopback; Send the store Combinations setting state to store Combinations simulator 3 and control parameter; Send admittance excitation correlation behavior setup parameter to admittance driver 4; Forward to each target simulator 7 target component that the carrier aircraft flight simulator calculates in real time; Send non-avionics setup parameter to non-avionics system emulator 5; Send starting record and stopping record order of each step to integrated test system 8, and receive the test data that test master control platform returns; The test data that test master control platform is returned sends to judgement and register system 9, and reception judges and register system is returned automatic decision result and corresponding data; Send to prompt system 10 operation indicating that each step should be carried out.The parameter that above test master control platform 6 sends all can send automatically according to corresponding testing procedure.
Described each target simulator 7 is a plurality of target simulators, comprises the combination in any of radar simulator, light thunder target simulator, electronic warfare target simulator etc. or one of them; Each simulator is equipped with real-time network interface card 14, be connected on the Real-time Network switch 13 of Auto-Test System, receive the target flight parameter that Auto-Test System forwards from carrier aircraft flight simulator 2, to complete the generation of respective objects signal, and finally with mode or the radiation mode of radio frequency injection, give tested avionics system corresponding sensor device;
Referring to accompanying drawing 6, each target simulator be a kind of typical connected mode: radar simulator 71, light thunder target simulator 72, electronic warfare target simulator 73 all are connected with Real-time Network switch 13 by optical-fibre channel, receive the real-time target component of calculating of carrier aircraft flight simulator 2 that test master control platform 6 forwards, thereby each target simulator completes the generation of respective objects signal, send to 76 3 subsystems of radar 74, light thunder 75, electronic warfare of tested avionics system in the mode of radio frequency injection or radiation.
The type of attachment that inner Real-time Network switch 81 is core be take in described integrated test system 8 inside, referring to accompanying drawing 7, to gather and control computing machine 85, collecting computer 82 is connected on inner Real-time Network switch 81, collecting computer quantity can increase and decrease to some extent according to testing requirement, wherein collecting computer 82 completes collection to be measured in tested avionics system, for example: switching value, analog quantity, frequency quantity, synchronous tolerance, the RS-422 signal, the ARINC429 signal, the collection of GJB289A bus signals and video pictures, storage, and according to the unified control that gathers control computing machine 85, corresponding institute image data is sent to gather and controls computing machine 85, gathering and controlling computing machine 85 is that collecting computer is broadcasted unified timestamp by Real-time Network, and will be controlled by self and the image data received mails to test master control platform 6 by Real-time Network switch 13, and receive starting that test master control platform sends and gather and stop acquisition, complete the data acquisition of a certain process to control corresponding collecting computer.
The form that judgement and register system 9 are installed real-time network interface card 14 and mass storage device with computing machine exists, wherein network interface card 14 is connected on the Real-time Network switch 13 of Auto-Test System in real time, receive the judgement control command of test master control platform 6, and receive the process data that the integrated test system that forwards from test master control platform 6 collects, so that these data are carried out to automatic decision, and judged result and corresponding data are recorded in the mass storage device of self, and judged result and corresponding data are returned to test master control platform 6 to show.
The form that prompt system 10 is installed real-time network interface card 14 with computing machine exists, wherein network interface card 14 is connected on the Real-time Network switch 13 of Auto-Test System in real time, usually this prompt system is positioned over to the place that need to carry out test operation, the operation that each testing procedure that reception test master control platform 6 sends should carry out, to point out the test operation personnel.
Described carrier aircraft flight simulator 2 is connected with avionics system by the HB6069 bus, described store Combinations simulator 3 is connected with avionics system 1 by bus and/or discrete magnitude cable, non-avionics system emulator 5 is connected with avionics system by the RS-422 bus, and non-avionics system emulator 5 comprises RS-422 bus, analog quantity, discrete magnitude, frequency quantity etc. with being connected of avionics system; Integrated test system 8 is connected with avionics system 1 with non-bus by bus,
Automatic testing process to certain step is as follows:
Be provided with " starting record " and " end record " button on test master control platform 6, control beginning and the end of record and automatic decision, when meeting record and automatic decision condition, now each test accessory has been ready to and has provided the signal that step starts front needs, and the display control apparatus of avionics system 1 has completed the beamhouse operation in early stage, click " starting record " button, now by test master control platform 6, control all test accessories and produce the emulation of agreement in advance, simulation, pumping signal, the operation of relevant device is carried out in the prompting that the display control apparatus operating personnel produce according to test master control platform, when step completes, click " end record " button, order and control the test that whole test macro completes this step according to the tester by test master control platform 6, stop the transmission of corresponding test auxiliary signal, and the data retransmission that integrated test system 8 is collected is given judgement and register system 9, judgement and register system 9 complete the automatic decision of data correctness, and record data and judged result.
The mode that script is loaded in the interior employing of integrated test system 8, stipulate the data block that each testing procedure need to gather.Each data block comprises one group of data that band is free.
Judgement and register system 9 are carried out automatic decision to these data;
The process of data automatic decision is as follows:
To each testing procedure, comprise a plurality of determining steps, each determining step comprises again the judgement of one or more data item; The script that each data item comprises comprises following information:
1 retrieval type: as be 0, be illustrated in after time reference adds delay time and retrieve the data that meet value conditions; As be 1, mean to extract first data after time reference adds delay time, to carry out the judgement of respective value;
2 data types: comprise meaning type, integer, floating type;
Data value judgement number: number, as be 0, means not need to carry out the judgement of data value, is generally at this moment only need to carry out the judgement poor with last process time, or only as the time reference of next process, and is indifferent to the occurrence of data; Number is as be other value, the number of the correct situation of presentation data value;
3 value=a and error range or b and error range ... comprising the how many kinds of situation is determined by top " data value judgement number ";
4 supervision time are poor: whether the Yes/No regulation checks the mistiming with last process; For first process, this entry is invalid;
5 mistiming scopes: only having a upper entry is "Yes", and this entry is just effective; The allowed band of the mistiming of regulation and a upper corresponding time of process;
6 time references: if this value is 0, mean it is not the time reference of next process; Non-zero numerical value if, mean in next process that identical therewith " a upper time benchmark " take this item number is time reference according to the corresponding current time, starts to retrieve corresponding data after adding time delay between at this moment; Identical data that if this process comprises multinomial " time reference ", corresponding time reference is times the latest corresponding to these data.For last process, this entry is invalid;
A time benchmark on 7: with this, obtain time the latest corresponding to this time reference in a upper process.For first process, this entry is invalid;
8 time delays: as the compensation of time reference, such as some equipment needs certain hour after in stable condition, just can export the numerical value of regulation, extract such data and just need to after time reference, add certain time delay.
For the test of each step, one or more data item are carried out to continuous acquisition, the collection result of certain data item may be not adopt data, or collects many beat of data, each beat of data has comprised corresponding time and data value.
While being defined in judgement, one group of data value of arranging in advance of retrieval in one group of data item of arranging in advance, perhaps after certain delay time, directly extract one group of data of regulation, if do not look for the data value of full regulation, directly judge this step mistake, if look for complete and judge that all direct extraction data are for correct, continue in the data item of current or the prior agreement of another group, from one group of corresponding concluding time of data or add after certain time delay and retrieve another group data value of agreement in advance, or directly extract another and organize data, judge whether all to retrieve, and directly extract data for correct, as required simultaneously, to mistiming of the judgement of indivedual data and last process corresponding data whether at the appointed time within, if all pass through, proceed the retrieval of next process and extract judgement, the like, until retrieve and extracted the data value of all prior agreements, thereby complete the judgement of one group of process.Also can judge as required many groups process.
Take as mentioned above constantly the mode of a plurality of data item settings of retrieval to carry out the Auto-Test System of the judgement of paired data stream transmission procedure.
Test accessory in the avionics system test environment is connected by Real-time Network, and, under unified control of test master control platform, each testing procedure is produced automatically to simulation, emulation, the pumping signal needed.
The Auto-Test System used in avionics system test of the present invention, this system is passed through the store Combinations simulator, each target simulator, the admittance driver, the test accessories such as carrier aircraft flight simulator carry out the connection of Real-time Network, automatically control each test accessory and check that at each step produces the signal with strict sequential order, and under the control of test master control platform, by a kind of method that can be called as the retrieval type automatic decision, complete the judgement of data correctness, thereby complete automatic test, by this invention, effectively improved the efficiency of avionics system test, and improved to a great extent the comprehensive of automatic test.
The accompanying drawing explanation
Below in conjunction with drawings and the embodiments, the present invention is further detailed explanation:
The Auto-Test System theory diagram that Fig. 1 is avionics system;
A kind of crosslinked graph of a relation of the Auto-Test System that Fig. 2 is avionics system and tested avionics system;
A kind of data flow diagram that Fig. 3 is tested avionics system;
Fig. 4 is carrier aircraft flight simulator theory diagram;
Fig. 5 is admittance driver theory diagram;
Fig. 6 is each target simulator theory diagram;
Fig. 7 is the integrated test system theory diagram;
Embodiment
The Auto-Test System of the described avionics system of the present embodiment, be connected in tested avionics system 1, it is characterized in that: the Auto-Test System of described avionics system is constructed as follows: carrier aircraft flight simulator 2, store Combinations simulator 3, admittance driver 4, non-avionics system emulator 5, test master control platform 6, each target simulator 7, integrated test system 8, judgement and register system 9, prompt system 10; Wherein:
For providing the carrier aircraft flight simulator 2 of the flight parameter of simulation, avionics system is connected with air data computer with the inertial navigation unit of avionics system, receive the power supply of avionics system, heat, the orders such as store Combinations emission, and the store Combinations simulator 3 of simulating the state of each hanging point store Combinations is connected with avionics system 1, for avionics system provides the radio environment of simulation, as Tacan number of units certificate, the admittance driver 4 of Data-Link information etc. is connected with avionics system 1, the non-avionics system emulator 5 of the Mechatronic Systems of simulated aircraft and flight control system is connected with avionics system, each target simulator 7 is connected with avionics system 1, integrated test system 8 is connected with avionics system 1, control the corresponding data that integrated test system gathers avionics system, and forward these data to judgement and register system, control the automatic decision that it carries out data, and the test master control platform 6 of record data and judged result is connected with integrated test system 8 by the Real-time Network with various original test accessories, automatically control each equipment and produce the data that need, due to the control that is Real-time Network, so these data have sequential accurately, and can not there is the problem of operate miss, simultaneously, test master control platform 6 also sends operation indicating to the avionics system display control apparatus.
Test accessory can be also the combination of a plurality of subsystems; Automatically control each equipment and produce the data that need under current step.Due to the control that is Real-time Network, so these data have sequential accurately, and can not there is the problem of operate miss; The judgement that the data that integrated test system 8 is gathered are carried out automatic decision is connected with test master control platform 6 by Real-time Network with register system 9, and prompt system 10 is connected with test master control platform 6 by Real-time Network.
Described carrier aircraft flight simulator 2 adopts computing machine that the form of board 21 is installed, comprise board 21 and real-time network interface card 14, the carrier aircraft flight parameter that wherein board 21 generates computing module in the carrier aircraft flight simulator by the board passage sends to inertial navigation set 11 and the air data computer 12 in tested avionics system 1; Network interface card 14 is connected with Real-time Network switch 13 by optical-fibre channel in real time, thereby be connected in Auto-Test System, realize receiving the carrier aircraft original state parameter of test master control platform 6 transmissions and change and control, carry out accordingly the calculating of carrier aircraft flight parameter, flight parameter result of calculation is sent to tested avionics system 1; Simultaneously, carrier aircraft flight simulator 2 receives target original state parameter and the variation control that test master control platform 6 sends, and carries out accordingly the flight simulation of target, and the real-time flight parameter of target is returned to test master control platform 1, to be transmitted to each target simulator 7;
Described board 21 is specially the ARINC429 board.
Described store Combinations simulator 3 emulation aircrafts are joined control response logic and the function of the various store Combinations of extension, gather and/or receive all information that in tested avionics system, plug-in property management reason subsystem is exported to store Combinations, simultaneously by true store Combinations steering logic loopback information, real-time network interface card 14 is installed in the store Combinations simulator, on the Real-time Network switch 13 that is connected to Auto-Test System, receive the store Combinations setting state control parameter that test master control platform 6 sends, to complete the simulation of store Combinations.
The radio environment that described admittance driver 4 simulation avionics systems receive, and the mode of injecting by radio frequency is given the admittance equipment of tested avionics system; The combination in any that admittance driver 4 is the subsystems such as compass driver, Tacan driver, Data-Link information incentive device or one of them;
Referring to accompanying drawing 5, the control module 41 of admittance driver 4 realizes the system control of driver, and the excitation control of analog radio-frequency signal, data processing and signal are processed, and being connected by real-time network interface card 14 and Real-time Network switch 13, realize and test being connected of master control platform 6 in test environment, receive the control of test master control platform 6, and the status information of loopback self.
Non-avionics system emulator 5 adopts open industrial computer to add extended housing, and configure on this basis analog output interface circuit plate, discrete magnitude output interface plate, synchronous tolerance output interface plate, frequency quantity output interface plate, universal serial bus RS-422 interface board, the ARINC429 interface board main body day as the avionics system emulator, by cable butting on the machine of transit cable box and tested avionics system, realize the test to each system.And by being connected of real-time network interface card and Real-time Network switch, realize with test environment in test master control platform mutual, receive the non-avionics setup parameter that test master control platform sends, produce non-avionics signal with simulation.
The form that test master control platform 6 is installed real-time network interface card with computing machine exists, wherein network interface card 14 is connected on the Real-time Network switch 13 of Auto-Test System by optical-fibre channel in real time, send the original state parameter of carrier aircraft and target and change to carrier aircraft flight simulator 2 and control, and receive the target of carrier aircraft flight simulator loopback; Send the store Combinations setting state to store Combinations simulator 3 and control parameter; Send admittance excitation correlation behavior setup parameter to admittance driver 4; Forward to each target simulator 7 target component that the carrier aircraft flight simulator calculates in real time; Send non-avionics setup parameter to non-avionics system emulator 5; Send starting record and stopping record order of each step to integrated test system 8, and receive the test data that test master control platform returns; The test data that test master control platform is returned sends to judgement and register system 9, and reception judges and register system is returned automatic decision result and corresponding data; Send to prompt system 10 operation indicating that each step should be carried out.The parameter that above test master control platform 6 sends all can send automatically according to corresponding testing procedure.
Described each target simulator 7 is a plurality of target simulators, comprises the combination in any of radar simulator, light thunder target simulator, electronic warfare target simulator etc. or one of them; Each simulator is equipped with real-time network interface card 14, be connected on the Real-time Network switch 13 of Auto-Test System, receive the target flight parameter that Auto-Test System forwards from carrier aircraft flight simulator 2, to complete the generation of respective objects signal, and finally with mode or the radiation mode of radio frequency injection, give tested avionics system corresponding sensor device;
Referring to accompanying drawing 6, each target simulator be a kind of typical connected mode: radar simulator 71, light thunder target simulator 72, electronic warfare target simulator 73 all are connected with Real-time Network switch 13 by optical-fibre channel, receive the real-time target component of calculating of carrier aircraft flight simulator 2 that test master control platform 6 forwards, thereby each target simulator completes the generation of respective objects signal, send to 76 3 subsystems of radar 74, light thunder 75, electronic warfare of tested avionics system in the mode of radio frequency injection or radiation.
The type of attachment that inner Real-time Network switch 81 is core be take in described integrated test system 8 inside, referring to accompanying drawing 7, to gather and control computing machine 85, collecting computer 82 is connected on inner Real-time Network switch 81, collecting computer quantity can increase and decrease to some extent according to testing requirement, , wherein collecting computer 82 completes collection to be measured in tested avionics system, for example: switching value, analog quantity, frequency quantity, synchronous tolerance, the RS-422 signal, the ARINC429 signal, the collection of GJB289A bus signals and video pictures, storage, and according to the unified control that gathers control computing machine 85, corresponding institute image data is sent to gather and controls computing machine 85, gathering and controlling computing machine 85 is that collecting computer is broadcasted unified timestamp by Real-time Network, and will be controlled by self and the image data received mails to test master control platform 6 by Real-time Network switch 13, and receive starting that test master control platform sends and gather and stop acquisition, complete the data acquisition of a certain process to control corresponding collecting computer.
The form that judgement and register system 9 are installed real-time network interface card 14 and mass storage device with computing machine exists, wherein network interface card 14 is connected on the Real-time Network switch 13 of Auto-Test System in real time, receive the judgement control command of test master control platform 6, and receive the process data that the integrated test system that forwards from test master control platform 6 collects, so that these data are carried out to automatic decision, and judged result and corresponding data are recorded in the mass storage device of self, and judged result and corresponding data are returned to test master control platform 6 to show.
The form that prompt system 10 is installed real-time network interface card 14 with computing machine exists, wherein network interface card 14 is connected on the Real-time Network switch 13 of Auto-Test System in real time, usually this prompt system is positioned over to the place that need to carry out test operation, the operation that each testing procedure that reception test master control platform 6 sends should carry out, to point out the test operation personnel.
Described carrier aircraft flight simulator 2 is connected with avionics system by the HB6069 bus, described store Combinations simulator 3 is connected with avionics system 1 by bus and/or discrete magnitude cable, non-avionics system emulator 5 is connected with avionics system by the RS-422 bus, and non-avionics system emulator 5 comprises RS-422 bus, analog quantity, discrete magnitude, frequency quantity etc. with being connected of avionics system; Integrated test system 8 is connected with avionics system 1 with non-bus by bus,
Automatic testing process to certain step is as follows:
Be provided with " starting record " and " end record " button on test master control platform 6, control beginning and the end of record and automatic decision, when meeting record and automatic decision condition, now each test accessory has been ready to and has provided the signal that step starts front needs, and the display control apparatus of avionics system 1 has completed the beamhouse operation in early stage, click " starting record " button, now by test master control platform 6, control all test accessories and produce the emulation of agreement in advance, simulation, pumping signal, the operation of relevant device is carried out in the prompting that the display control apparatus operating personnel produce according to test master control platform, when step completes, click " end record " button, order and control the test that whole test macro completes this step according to the tester by test master control platform 6, stop the transmission of corresponding test auxiliary signal, and the data retransmission that integrated test system 8 is collected is given judgement and register system 9, judgement and register system 9 complete the automatic decision of data correctness, and record data and judged result.
The mode that script is loaded in the interior employing of integrated test system 8, stipulate the data block that each testing procedure need to gather.Each data block comprises one group of data that band is free.
Judgement and register system 9 are carried out automatic decision to these data;
The process of data automatic decision is as follows:
To each testing procedure, comprise a plurality of determining steps, each determining step comprises again the judgement of one or more data item; The script that each data item comprises comprises following information:
1 retrieval type: as be 0, be illustrated in after time reference adds delay time and retrieve the data that meet value conditions; As be 1, mean to extract first data after time reference adds delay time, to carry out the judgement of respective value;
2 data types: comprise meaning type, integer, floating type;
Data value judgement number: number, as be 0, means not need to carry out the judgement of data value, is generally at this moment only need to carry out the judgement poor with last process time, or only as the time reference of next process, and is indifferent to the occurrence of data; Number is as be other value, the number of the correct situation of presentation data value;
3 value=a and error range or b and error range ... comprising the how many kinds of situation is determined by top " data value judgement number ";
4 supervision time are poor: whether the Yes/No regulation checks the mistiming with last process; For first process, this entry is invalid;
5 mistiming scopes: only having a upper entry is "Yes", and this entry is just effective; The allowed band of the mistiming of regulation and a upper corresponding time of process;
6 time references: if this value is 0, mean it is not the time reference of next process; Non-zero numerical value if, mean in next process that identical therewith " a upper time benchmark " take this item number is time reference according to the corresponding current time, starts to retrieve corresponding data after adding time delay between at this moment; Identical data that if this process comprises multinomial " time reference ", corresponding time reference is times the latest corresponding to these data.For last process, this entry is invalid;
A time benchmark on 7: with this, obtain time the latest corresponding to this time reference in a upper process.For first process, this entry is invalid;
8 time delays: as the compensation of time reference, such as some equipment needs certain hour after in stable condition, just can export the numerical value of regulation, extract such data and just need to after time reference, add certain time delay.
For the test of each step, one or more data item are carried out to continuous acquisition, the collection result of certain data item may be not adopt data, or collects many beat of data, each beat of data has comprised corresponding time and data value.
While being defined in judgement, one group of data value of arranging in advance of retrieval in one group of data item of arranging in advance, perhaps after certain delay time, directly extract one group of data of regulation, if do not look for the data value of full regulation, directly judge this step mistake, if look for complete and judge that all direct extraction data are for correct, continue in the data item of current or the prior agreement of another group, from one group of corresponding concluding time of data or add after certain time delay and retrieve another group data value of agreement in advance, or directly extract another and organize data, judge whether all to retrieve, and directly extract data for correct, as required simultaneously, to mistiming of the judgement of indivedual data and last process corresponding data whether at the appointed time within, if all pass through, proceed the retrieval of next process and extract judgement, the like, until retrieve and extracted the data value of all prior agreements, thereby complete the judgement of one group of process.Also can judge as required many groups process.
Take as mentioned above constantly the mode of a plurality of data item settings of retrieval to carry out the Auto-Test System of the judgement of paired data stream transmission procedure.
Test accessory in the avionics system test environment is connected by Real-time Network, and, under unified control of test master control platform, each testing procedure is produced automatically to simulation, emulation, the pumping signal needed.
The Auto-Test System used in the described avionics system test of the present embodiment, this system is passed through the store Combinations simulator, each target simulator, the admittance driver, the test accessories such as carrier aircraft flight simulator carry out the connection of Real-time Network, automatically control each test accessory and check that at each step produces the signal with strict sequential order, and under the control of test master control platform, by a kind of method that can be called as the retrieval type automatic decision, complete the judgement of data correctness, thereby complete automatic test, by this embodiment, effectively improved the efficiency of avionics system test, and improved to a great extent the comprehensive of automatic test.
Referring to accompanying drawing 2, tested avionics system 1 comprises control system, remote terminal 1, remote terminal 2.Radar simulator is connected by radio-frequency cable with remote terminal 2; For remote terminal 2 provides the target data of simulation; The carrier aircraft flight simulator is connected with remote terminal 1 by the ARINC429 bus and connects, for remote terminal 1 provides the carrier aircraft flight parameter of simulation; Remote terminal 1, remote terminal 2 and control are connected by bus with integrated test system, make integrated test system gather the data of tested avionics system; Simultaneously, radar simulator, carrier aircraft flight simulator 2, judgement and register system 9, integrated test system 8, test master control platform 6, prompt system 10 are connected with Real-time Network switch 13 by optical-fibre channel, realize that whole Auto-Test System completes test under unified control of test master control platform.
In this testing procedure, in tested avionics system, the data stream transmitting of control system, remote terminal 1 and remote terminal 2 is as follows: control system sends order to remote terminal 1 by data item 1, by data item 2, sends order to remote terminal 2; After two remote terminals receive orders, respectively by data item 3 and data item 4 return states, the state returned for remote terminal 1 comprises that two kinds is all correct, but require the response time in 100ms, remote terminal 1 sends the stable data before many bats are different from 300ms to remote terminal 2 by data item 5 after 300ms simultaneously, requires mistiming corresponding to many beat of data should be less than 200ms.
Respective stream of data is illustrated as follows:
The script edit that this testing procedure is corresponding is as follows:
Process 1:
1 data item 1: retrieval type=0, data type=meaning type, numerical value judgement number=1, value=a, the supervision time is poor=no, time reference=1, time delay=0
2 data item 2, retrieval type=0, data type=meaning type, numerical value judgement number=1, value=b, the supervision time is poor=no, time reference=2, time delay=0
Process 2:
1 data item 3: retrieval type=0, data type=meaning type, numerical value judgement number=2, value=c or h, the supervision time is poor=be mistiming scope=100ms, time reference=0, a upper time benchmark=1, time delay=0
2 data item 4: retrieval type=0, data type=meaning type, numerical value judgement number=1, value=data d, the supervision time is poor=no, time reference=0, a upper time benchmark=2, time delay=0
3 data item 5: retrieval type=1, data type=floating type, numerical value judgement number=1, value=data e, the supervision time is poor=no, time reference=1, a upper time benchmark=1, time delay=300ms
Process 3:
1 data item 6: retrieval type=1, data type=floating type, numerical value judgement number=0, the supervision time is poor=be mistiming scope=200ms, time reference=0, a upper time benchmark=1
Utilize above-mentioned script to be judged:
At first in data item 1 and data item 2, retrieve data a and data b, corresponding time hypothesis is respectively time 1 and time 2; Afterwards, in data item 3 at rear retrieve data c of time 1 or h, in data 4 at rear retrieve data d of time 2, suppose that the c and the d time of occurrence that retrieve are respectively time 3 and time 4, the judgement time 3 is less than or equal to 100ms with the difference of time 1, in data item 5, extracts data after time 1 time delay 300ms simultaneously, judge that these data should be e, the corresponding time is assumed to be the time 5; Finally, in data item 5, after the time 5, extract data, judge that the time of these data should differ in 200ms with the time 5.
If it is complete that above-mentioned deterministic process can be carried out, the judgement of this testing procedure is correct.
Claims (8)
1. the Auto-Test System of an avionics system, be connected in tested avionics system (1), it is characterized in that: the Auto-Test System of described avionics system is constructed as follows: carrier aircraft flight simulator (2), store Combinations simulator (3), admittance driver (4), non-avionics system emulator (5), test master control platform (6), each target simulator (7), integrated test system (8), judgement and register system (9), prompt system (10); Wherein:
Carrier aircraft flight simulator (2) is connected with air data computer with the inertial navigation unit of avionics system, and store Combinations simulator (3), admittance driver (4), non-avionics system emulator (5), each target simulator (7), integrated test system (8) are connected with avionics system (1) respectively; Carrier aircraft flight simulator (2), store Combinations simulator (3), admittance driver (4), non-avionics system emulator (5), each target simulator (7), integrated test system (8), judgement and register system (9), prompt system (10) are connected with test master control platform (6) by Real-time Network respectively.
2. according to the Auto-Test System of the described avionics system of claim 1, it is characterized in that: described carrier aircraft flight simulator (2) adopts computing machine that the form of board (21) is installed, carrier aircraft flight simulator (2) comprises board (21) and real-time network interface card (14), and the carrier aircraft flight parameter that wherein board (21) generates computing module in the carrier aircraft flight simulator by the board passage sends to inertial navigation set (11) and the air data computer (12) in tested avionics system (1); Network interface card (14) is connected with Real-time Network switch (13) by optical-fibre channel in real time, thereby be connected in Auto-Test System, realize receiving the carrier aircraft original state parameter of test master control platform (6) transmission and change and control, carry out accordingly the calculating of carrier aircraft flight parameter, flight parameter result of calculation is sent to tested avionics system (1); Simultaneously, carrier aircraft flight simulator (2) receives target original state parameter and the variation control that test master control platform (6) sends, carry out accordingly the flight simulation of target, and the real-time flight parameter of target is returned to test master control platform (1), to be transmitted to each target simulator (7).
3. according to the Auto-Test System of the described avionics system of claim 2, it is characterized in that: the radio environment that described admittance driver (4) simulation avionics system receives, and the mode of injecting by radio frequency is given the admittance equipment of tested avionics system.
4. according to the Auto-Test System of the described avionics system of claim 3, it is characterized in that: described each target simulator (7) is a plurality of target simulators, each simulator is equipped with real-time network interface card (14), be connected on the Real-time Network switch (13) of Auto-Test System, receive the target flight parameter that Auto-Test System forwards from carrier aircraft flight simulator (2), to complete the generation of respective objects signal, and finally with mode or the radiation mode of radio frequency injection, give tested avionics system corresponding sensor device.
5. according to the Auto-Test System of the described avionics system of claim 4, it is characterized in that: described integrated test system (8) is inner take the type of attachment that inner Real-time Network switch (81) is core, to gather and control computing machine (85), collecting computer (82) is connected on inner Real-time Network switch (81), wherein collecting computer (82) completes collection to be measured in tested avionics system, and according to the unified control that gathers control computing machine (85), corresponding institute image data is sent to gather and controls computing machine (85); Gathering and controlling computing machine (85) is that collecting computer is broadcasted unified timestamp by Real-time Network, and will be controlled by self and the image data received mails to by Real-time Network switch (13) and tests master control platform (6), and receive starting that test master control platform sends and gather and stop acquisition, complete the data acquisition of a certain process to control corresponding collecting computer.
6. according to the Auto-Test System of the described avionics system of claim 5, it is characterized in that: described board (21) is specially the ARINC429 board.
7. according to the Auto-Test System of the described avionics system of claim 6, it is characterized in that: described carrier aircraft flight simulator (2) is connected with avionics system by the HB6069 bus, described store Combinations simulator (3) is connected with avionics system (1) by bus and/or discrete magnitude cable, non-avionics system emulator (5) is connected with avionics system by the RS-422 bus, and integrated test system (8) is connected with avionics system with non-bus by bus.
8. according to the Auto-Test System of the described avionics system of claim 7, it is characterized in that: load script in described integrated test system (8).
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| CN 201310438069 CN103472735A (en) | 2013-09-24 | 2013-09-24 | Automatic testing system of avionics system |
| CN201410007750.1A CN103760439B (en) | 2013-09-24 | 2014-01-07 | A kind of Auto-Test System of avionics system |
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| CN103760439A (en) | 2014-04-30 |
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