CN201757767U - General comprehensive automatic test system of airplane electronic part - Google Patents
General comprehensive automatic test system of airplane electronic part Download PDFInfo
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- CN201757767U CN201757767U CN 200920057467 CN200920057467U CN201757767U CN 201757767 U CN201757767 U CN 201757767U CN 200920057467 CN200920057467 CN 200920057467 CN 200920057467 U CN200920057467 U CN 200920057467U CN 201757767 U CN201757767 U CN 201757767U
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Abstract
Provided is a general comprehensive automatic test system of a civil aviation airliner electronic part. A hardware platform consists of a test controller, a test instrument resource, a switch system and a test signal interface device, the hardware platform adopts an embedded test & control computer, a modularized test & excitation equipment, standard GPIB, VXI and PXI bus control, a eight-road simulation sum switch system structure and a VPC 90 test signal interface device. The combination structure of the system is divided based on the control flow and the control flow direction from the test program (TP) to the unit under test (UUT), five levels of the structure are divided from high to low: a test management level, a test program level, an instrument driving level, an operation system level and a physical hardware level. The general comprehensive automatic test system can automatically complete the excitation, measurement, data processing of the UUT of the airplane electronic part and display as well as output the test result.
Description
Technical field
The utility model relates to a kind of electronic unit Auto-Test System, relates in particular to a kind of civil aviaton airliner electronic unit general integrated automated test system of (comprising airborne computer, Electronic Control Unit, data processing module etc.).
Background technology
At present, the detection of the air environment of airliner all is to be finished by the automatic test equipment (ATE) that SMART (Standard ModularAvionics Repair and Test) standardized module formula avionic device is repaired and tested usually.SMART ATE generally includes microprocessor, program-controlled instrument, four ingredients of MUT module under test adapter and testing software, have abundant measurement and driver resource, switch matrix and bus flexibly can satisfy the test request of civil aviaton's air environment complexity.Its representative has the ATEC6 series of EADS company and the SMART CATS Auto-Test System of Israel RADA company, but invests hugely, and simultaneously, producer can use some special integrated circuit boards to carry out blockade on new techniques, the later maintenance cost height usually.Along with the variation of market or electronic equipment test request, the expansion of hardware configuration and testing software is revised complicated.
The utility model content
The utility model purpose is to provide a kind of cost to hang down expansion easily, reusability of resources is good, the Auto-Test System that the degree of modularity is high.
The purpose of this utility model can realize by following scheme:
A kind of general integrated automated test system of aircraft electronic unit is characterized in that comprising:
Driver resource: be used to tested aircraft electronic unit that the test and excitation signal is provided;
Input resource: be used for gathering and the various signals of measurement from tested aircraft electronic unit;
Power-supply system: for unit under test provides various control AC/DC power supplys able to programme;
Signal interface unit: be used to transmit detection signal and pumping signal, realize that ATE (automatic test equipment) is connected with standard, rapid physical between unit under test;
Switching system: the realization unit under test is with driver resource and detect being connected and the passage switching between resource;
Test controller: be used to control testing process and signal.
Described test controller comprises:
The test and management module is used to control various test patterns;
The test procedure module is used to write down the required program function of test;
The instrument driver module is used to realize the control of test procedure to hardware;
The test operation module is used for carrying out test operation according to upper strata (instrument driver module) module drive order;
The output test control signal is to the instrument driver module behind the trial function of test and management module invokes test procedure module, drive test operation module output function control signal by the instrument driver module, operating control signal is tested the target electronic parts to hardware components by data bus.
Described test and management module comprises test execution administration module and test development administration module, and the test development administration module has comprised command set, parameter list, nail table and allowance table; The test execution administration module uses LABWINDOWS/CVI to write.
Described test procedure module comprises test procedure TP, and each TP (test procedure) comprises autotest program and DEBUG test procedure.
Described data bus comprises GPIB, VXI and PXI bus.
The relative prior art advantage of the utility model is: system hardware is core with the computing machine, control each quasi-instrument, equipment by communication patterns such as PXI, VXI and GPIB, automatically finish excitation, measurement, data processing to measurand aircraft electronic unit UUT, and show and to output test result, print test report.This integrated automated test system message transmission rate height, data throughout is big, system buildup is flexible, expansion easily, reusability of resources is good, standardization, degree of modularity height.
Description of drawings
Fig. 1 is the integrated general principles block diagram of hardware of the present utility model;
Fig. 2 is the integrated specific implementation block diagram of hardware of the present utility model;
Fig. 3 resource module switch matrix structure;
Fig. 4 signal converting module switch matrix structure;
Fig. 5 is the composition structural drawing of embodiment of the present utility model.
Embodiment
Extremely shown in Figure 5 as Fig. 1, native system hardware is core with the computing machine, communicates by letter with GPIB etc. by PXI, VXI and controls each quasi-instrument, equipment, finishes excitation, measurement, data processing to measurand aircraft electronic unit UUT automatically, and show and to output test result, print test report.System has the message transmission rate height, data throughout is big, system buildup is flexible, and expansion is easy, and reusability of resources is good, standardization, numerous advantages such as degree of modularity height.The composition structure of system is divided to the control flow and the control flow direction of tested object UUT according to test procedure TP, is divided into five-layer structure from high to low: test and management layer, test procedure layer, instrument Drive Layer, operating system layer, physical hardware layer.The test and management layer is divided into the test program development platform and test procedure is carried out platform, the developing instrument that the test program development platform facilitates for the user, the inside comprises command set, parameter list, nail table, the allowance table that various device is used, the user only needs input simple and clear programming instruction, data and parameter in the process of exploitation, just can finish the operation that each equipment is measured and encouraged.Test procedure is carried out the platform friendly interface, and easy operating is user-friendly to.
Concrete technical scheme is as follows:
One) hardware is integrated
Hardware is formed and is comprised: test controller, testing tool resource, switching system and test signal interface arrangement.Test controller is realized various driver resource in the Auto-Test System, is detected the configuration of resource and switching system, and determines its working method, state, function and parameter, the channel selecting and the switching of control test signal.The interconnection of signals of test macro and unit under test then is to realize by signal interface unit.
1. test controller
Test controller is the core of system.Testing software moves on test controller, realizes the control to test process, and that system selects for use is the embedded controller PXI-8187 of the NI of American National instrument company, is equipped with external units such as CRT monitor, keyboard, printer simultaneously.The work of test controller also has the support of corresponding operating system software.
2. testing tool resource
The system testing instrument resource comprises: input resource, driver resource, power-supply system etc.The input resource is made up of various program control test surveying instruments, is used for gathering and the various signals of measurement, as multimeter, oscillograph, Timer, ARINC 429 receivers, angle position indicator, phase voltage table etc.Driver resource provides necessary test and excitation signal for unit under test work, as AWG (Arbitrary Waveform Generator), D/A converter, ARINC429 generator, RS-232/422/485 communication etc.Power-supply system provides various control AC/DC power supplys able to programme for unit under test.Detect with driver resource and adopt module to draw design, and use PXI, VXI, the control of STD bus such as GPIB.
3. switching system
Switching system realizes switching being connected with passage between unit under test interface and test resource in system.By switching system, system can make full use of limited test resource and satisfy unit under test test signal completeness demand, reduces the cost of whole test system.Testing tool can be realized the ATE (automatic test equipment) self-test function easily by the connection of switching system.Through the switching system cascade, can also realize the expansion of test macro and reconfigure.The switching system of system is the unique texture of complete autonomous Design, use 13 groove signal condition cabinet SCXI-1001 of American National instrument, use 5 SCXI-1129 matrix switch modules to realize being connected of resource and measured signal, use 4 SCXI-1166 universal switch modules to realize the general connection of signal by 8 emulation buss.
4. signal interface unit
System selects for use the 25 mould receivers of VPC90 as signal interface unit, realizes that ATE (automatic test equipment) is connected with standard, rapid physical between unit under test.Interface arrangement also comprises: the signal receiver in the ATE (automatic test equipment) (Receiver) reaches and the supporting test fixture (Fixture) of unit under test, is connected and fixed device and various test cables etc. as test interface adapter, unit under test.
Two) the composition structure of system
System software is the core of system's operation, and it has described the testing requirement that varies, and has represented the Test Application at various types of measurands.Security, the reliability of the advance of the completeness of this testing software, ease for use, software configuration, extensibility and software systems operation reduce tester's labour intensity to greatest extent, increase work efficiency the stability of enhanced system operation.
System divides to the control flow and the control flow direction of tested object UUT according to test procedure TP, is divided into five-layer structure from high to low: test and management layer, test procedure layer, instrument Drive Layer, operating system layer, physical hardware layer.
1) test and management layer
The test and management layer is the control dispatching center of system, and this layer is positioned at the top layer of software systems of IATS2000, is the interface of man-machine interaction, has friendly interface, the characteristics of easy operating.The test and management layer is made up of test execution management platform and test development management platform.The test program development platform uses Microsoft VB and OFFICE2003 to write, the developing instrument that facilitates for the user, the inside comprises command set, parameter list, nail table, the allowance table that various device is used, the user only needs input simple and clear programming instruction, data and parameter in the process of exploitation, just can finish the operation that each equipment is measured and encouraged.Test procedure is carried out platform and is used LABWINDOWS/CVI to write, friendly interface, and easy operating is user-friendly to.
2) test procedure layer
This layer contains all test procedure TP of IATS2000, and each TP comprises autotest program and DEBUG test procedure two parts.Test procedure is realized the test to UUT by the modularity function control system resource of calling system platform.
3) instrument Drive Layer
It is one of important component part in the system software architecture that instrument drives, and its instrument Drive Layer between test procedure and operating system layer realizes that by the transmission of operating system test procedure is to control of hardware resources.
4) operating system layer
Operating system is accepted the order from the instrument driving, is delivered to GPIB by computing machine, VXI, PXI bus, the final automatic and manual test of realizing UUT.
5) physical hardware layer
Physical hardware layer system resource and adapter are the hardware components of test and maintenance detection system.
Fig. 1 is the integrated general principles block diagram of system hardware, test controller is the core of system, and testing software moves on test controller, realizes the control to test process, the system testing instrument resource comprises: input resource, driver resource, power-supply system etc.The input resource is made up of various program control test surveying instruments, is used for gathering and the various signals of measurement, and driver resource provides necessary test and excitation signal for unit under test work.Switching system realizes switching being connected with passage between unit under test interface and test resource in system.Signal interface unit realizes that ATE (automatic test equipment) is connected with standard, rapid physical between unit under test.
Fig. 2 is the integrated specific implementation block diagram of system hardware, and the PXI-8187 that adopts NI company is as test controller; The input driver resource comprises: the PXI-4072 DMM of NI company, the PXI-5122 DSO of NI company, the PXI-8423RS-422/484 of NI company, the PXI-6259 DI/O of NI company, the PXI-5421 of NI company, 41-429D ARINC 429 transceivers of PICKERING company, the 40-295D programmable resistance card of PICKERING company, the 41-650 of PICKERING company becomes gain amplifier; Power-supply system is used 501SL single phase alternating current power supply, 6654 and 6032 direct supplys able to programme of AGILENT, the self-control fixed power source case FBS-2000 of ELGAR; Switching system is the 13 groove signal condition cabinets of the SCXI-1001 of NI company, forms the structure of 8 tunnel emulation buss by 5 SCXI-1129 switch matrix cards, and 4 SCXI-1166 form the universal switch structures.
Fig. 3 is the resource module switch matrix structure, by the SCXI-1334 connection terminal, allows a SCXI-1129 form the switch matrix structure of the 32*8 of 2 lines, can realize 32 pipeline equipments are transferred to the function of 8 tunnel emulation buss.
Fig. 4 is a signal converting module switch matrix structure, by the SCXI-1135 connection terminal, allows 4 SCXI-1129 form the switch matrix structure of the 64*4 of 2 lines, can realize 64 drive test trial signals are transferred to the function of 4 tunnel emulation buss.
Fig. 5 is the composition structure of system.Test procedure TP flows to division to control flow and the control of tested object UUT, is divided into five-layer structure from high to low: test and management layer, test procedure layer, instrument Drive Layer, operating system layer, physical hardware layer.
Claims (3)
1. the general integrated automated test system of an aircraft electronic unit is characterized in that comprising:
Driver resource: be used to tested aircraft electronic unit that the test and excitation signal is provided;
Input resource: be used for gathering and the various signals of measurement from tested aircraft electronic unit;
Power-supply system: for unit under test provides various control AC/DC power supplys able to programme;
Signal interface unit: be used to transmit detection signal and pumping signal, realize that ATE (automatic test equipment) is connected with standard, rapid physical between unit under test;
Switching system: realization unit under test signal is with driver resource and detect being connected and the passage switching between resource;
Test controller: be used to control testing process and signal;
Test controller is realized various driver resource in the Auto-Test System, is detected the configuration of resource and switching system, and determines its working method, state, function and parameter, the channel selecting and the switching of control test signal; The interconnection of signals of test macro and unit under test realizes by signal interface unit.
2. the general integrated automated test system of aircraft electronic unit according to claim 1 is characterized in that: described test controller comprises:
The test and management module is used to control various test patterns;
The test procedure module is used to write down the required program function of test;
The instrument driver module is used to realize the control of test procedure to hardware;
The test operation module is used for driving order according to the instrument driver module and carries out test operation;
The output test control signal is to the instrument driver module behind the trial function of test and management module invokes test procedure module, drive test operation module output function control signal by the instrument driver module, operating control signal is tested the target electronic parts to hardware components by data bus.
53. the general integrated automated test system of any aircraft electronic unit according to claim 1 and 2, it is characterized in that: described switching system is by the SCXI-1334 connection terminal, allow a SCXI-1129 form the switch matrix structure of the 32*8 of 2 lines, realization is transferred to 32 pipeline equipments the function of 8 tunnel emulation buss, by the SCXI-1135 connection terminal, allow 4 SCXI-1129 form the switch matrix structure of the 64*4 of 2 lines, realization is transferred to the function of 4 tunnel emulation buss with 64 drive test trial signals, and uses 4 SCXI-1166 to form the universal switch structure.
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| CN103116287A (en) * | 2013-01-22 | 2013-05-22 | 中国民航大学 | Avionics equipment running environment dynamic simulating device and method |
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| CN103336194A (en) * | 2013-06-09 | 2013-10-02 | 广州飞机维修工程有限公司 | Integrated automatic test system of on-board computer of civilian airliner |
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| CN111208770A (en) * | 2020-03-02 | 2020-05-29 | 北京华力智飞科技有限公司 | Signal acquisition and test system and test method |
| CN111208770B (en) * | 2020-03-02 | 2021-03-23 | 北京华力智飞科技有限公司 | Signal acquisition and test system and test method |
| CN111813072A (en) * | 2020-06-11 | 2020-10-23 | 中车唐山机车车辆有限公司 | Detection system for input and output functions of electronic equipment |
| CN112130009A (en) * | 2020-08-14 | 2020-12-25 | 陕西千山航空电子有限责任公司 | Flying parameter time-sharing test system |
| CN112882457A (en) * | 2021-01-19 | 2021-06-01 | 国营芜湖机械厂 | Automatic testing device and method for flight control box |
| CN113865446A (en) * | 2021-08-18 | 2021-12-31 | 上海机电工程研究所 | Missile testing and remote measuring integrated testing system and testing method thereof |
| CN114003453A (en) * | 2021-10-29 | 2022-02-01 | 哲库科技(北京)有限公司 | Test method, electronic equipment, system and computer storage medium |
| CN116540681A (en) * | 2023-07-04 | 2023-08-04 | 合众新能源汽车股份有限公司 | Controller interface function test system and test method |
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