CN110488630A - A kind of control increases steady flight control computer test macro and test method - Google Patents
A kind of control increases steady flight control computer test macro and test method Download PDFInfo
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- CN110488630A CN110488630A CN201910635610.1A CN201910635610A CN110488630A CN 110488630 A CN110488630 A CN 110488630A CN 201910635610 A CN201910635610 A CN 201910635610A CN 110488630 A CN110488630 A CN 110488630A
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- G—PHYSICS
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- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B17/00—Systems involving the use of models or simulators of said systems
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- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P90/00—Enabling technologies with a potential contribution to greenhouse gas [GHG] emissions mitigation
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Abstract
The invention discloses a kind of controls to increase steady flight control computer test macro and test method, it includes complete machine comprehensive test platform and functional test module, test platform should have emulation aircraft bus module, it is mainly used for all kinds of bus signals that emulation increases steady flight control computer crosslinking with control, bus signals are converted to by using GJB289A and ARINC429 bus board, it is sent to control and increases steady flight control computer, and by software emulation bus failure mode, carry out the test of system bus signal；Increase steady computer closed-loop dynamic working method, the frequency response of analogue back-up function, the emulation of various kinds of sensors signal dynamics and all kinds of execution unit model dynamic hardware assemblage on-orbits for real simulation control.By the way that by method for fault-injection test, solving the problems, such as previous conventional test device, fault location is difficult during the test, ensure that the practicability of testing scheme.
Description
Technical field
The present invention relates to a kind of aircraft control system testing field, especially a kind of flight control computer test macro belongs to
The inspection of control system or surveillance technology field.
Background technique
Control increases the core that steady flight control computer is entire flight control system, carries out redundance using high speed parallel bus
Architecture Design, information is carried out by high-speed figure differential signal between remaining and is mutually passed, structure and function is complicated, inside/outside
Portion is crosslinked more relationship, reliability, testability, fault diagnosis/Support and requires high, be on active service period length and technology upgrading ability
By force.Its integrated application modern electronic technology, microelectric technique, digital technology, bussing technique, computer technology, SERVO CONTROL
The product of the advanced technologies such as technology and network technology.The control of certain model increases steady flight control computer external interface signals up to more than 1000
Road, and signal kinds are more (containing function signals such as fault detection, fault management, fault alarm, artificial and automatic switchover logics), essence
Degree requires height, if it is low that there are test coverages using traditional manual test test equipment, executing agency's model accuracy is poor,
It is big that control increases steady flight control computer integration test deviation.It is mentioned to increase steady flight control computer comprehensive performance verification and testing to control
For the environment of operation, test platform and test method that control increases steady flight control computer interface and functional module need to be designed, still,
Existing means of testing is unable to meet demand, it is necessary to develop a kind of dedicated comprehensive survey of the steady flight control computer of type aircraft control increasing
Test system and test method.
Summary of the invention
It is an object of the invention to provide operation to increase steady flight control computer comprehensive performance verification and testing to control
Environment provides a kind of test macro of control increasing steady flight control computer interface and functional module, increases for type aircraft control steady
The dedicated integration test of flight control computer and test method.
Problem of the present invention is realized with following technical proposals:
A kind of steady flight control computer test macro of control increasing, it includes complete machine comprehensive test platform and functional test module, test
Platform should have emulation aircraft bus module, be mainly used for all kinds of buses that emulation increases steady flight control computer crosslinking with control and believe
Number, bus signals are converted to by using GJB289A and ARINC429 bus board, control is sent to and increases steady flight control computer,
And by software emulation bus failure mode, the test of system bus signal is carried out；
The functional module part of detecting includes that PXI cabinet, adapter and industrial personal computer software test module, the adapter are used for
Unit under test is connected, the PXI cabinet includes ACE simulation electronic test module, DCE digital and electronic test module, avionics bus
Test module, distinctive signal emulation module, interface and power supply system.
Each analog channel configures the independent excitation/measuring instrument of muti-piece: High Speed Analog input/output and dynamic waveform are compiled
Collect device, Dynamic Signal simulation analysis instrument, high-precision embedded signal analyzer.
A kind of steady flight control computer test method of control increasing includes the following steps:
Step 1: power supply system is supplied to control and increases the power supply of steady flight control computer three-way power on analog machine, and can independent control its
On-off is monitored power supply and protects；
Step 2: acquisition control increases the out-put supply signal of steady flight control computer；
Step 3: communication being carried out with the steady flight control computer of control increasing by RS422 communication interface and data are crosslinked；
Step 4: simulation control increases the discrete input of steady flight control computer, output signal, and input, output signal include that 28V/ opens letter
Number, 15V/ON signal；
Step 5: emulation HB6096 bus and GJB289A bus signals complete the bus for increasing steady flight control computer with control to be measured
Communication and detection；
Step 6: completing various kinds of sensors signal simulation, include dynamic and static pressure, yaw angle, the left and right angle of attack, the exchanges such as angular displacement biography
Sensor and acceleration, the emulation of the direct current transducers such as angular speed；
Step 7: completing all kinds of horizontal tails, aileron, rudder steering engine signal simulation, include horizontal tail, the limit, the front part of a Chinese robe or jacket, flaperon, direction
The emulation of the signals such as rudder；
Step 8: achievable control increases the given of steady flight control computer analog signal, and can collecting computer analog signal in real time
Output.
Above-mentioned test method completes product test to be measured and record, incoming/outgoing management and channel failure logic, bus
Transmit/receive test, CCDL transmission.
Above-mentioned test method realizes that, to left/right horizontal tail steering engine, left/right flaperon steering engine, direction steering engine, left/right servo is put
Synchronous and signal cross transmits control test, the voting of remaining signal and monitoring and tests, is real between big loop simulation test, channel
Existing system control logic is comprehensive to be tested with control mode conversion.
The beneficial effects of the present invention are:
The present invention has autorun, and High Precision Automatic analysis test result is surveyed according to product tolerance demand automatic comparison
Test result, the artificial test bring error of removal, increases the requirement of steady flight control computer to control, and the test of 95% or more satisfaction is covered
Lid rate, measuring accuracy is high, is fitted all kinds of steering engines and all kinds of emulation modules of sensor parameters completely.
Control can be achieved to increase outside steady flight control computer containing fault detection, fault management, fault alarm, artificial and cut automatically
Change the test of the function signals interface such as logic.
It may be implemented to test complete machine and functional module, increase steady computer closed-loop dynamic work side for real simulation control
Formula, the frequency response of analogue back-up function, the emulation of various kinds of sensors signal dynamics and all kinds of execution unit model dynamic hardwares exist
Ring emulation.By by method for fault-injection test, solving previous conventional test device, fault location is difficult during the test
Problem, it can be determined that whether equipment is in normal operating conditions.It solves the problems, such as that communication failure tracking is not compiled, ensure that test
The practicability of scheme, while avoiding because of the shortcomings that conventional detection multichannel excitation acquisition signal is easy " false-alarm ".
Detailed description of the invention
The present invention will be further explained below with reference to the attached drawings.
Fig. 1 is the functional block diagram that present invention control increases steady flight control computer comprehensive test platform test and verifying；
Fig. 2 is that control increases steady computer testing algorithm operational flow diagram；
Each list of reference numerals in figure are as follows: 1, the steady flight control computer comprehensive test platform of control increasing, 1-1, industrial personal computer (test software), 1-
2, PXI cabinet, 1-3, adapter, 2, unit under test, 3, software test platform.
Specific embodiment
Referring to Fig. 1, the present invention is that a kind of control increases steady flight control computer test macro, it includes complete machine comprehensive test platform
With functional test module, test platform should have emulation aircraft bus module, be mainly used for emulating and control the steady winged control calculating of increasing
All kinds of bus signals of machine crosslinking, are converted to bus signals by using GJB289A and ARINC429 bus board, are sent to control
System increases steady flight control computer, and by software emulation bus failure mode, carries out the test of system bus signal；
The functional module part of detecting includes that PXI cabinet, adapter and industrial personal computer software test module, the adapter are used for
Unit under test is connected, the PXI cabinet includes ACE simulation electronic test module, DCE digital and electronic test module, avionics bus
Test module, distinctive signal emulation module, interface and power supply system.
Each analog channel configures the independent excitation/measuring instrument of muti-piece: High Speed Analog input/output and dynamic waveform are compiled
Collect device, Dynamic Signal simulation analysis instrument, high-precision embedded signal analyzer.
Firstly, equipment mainly includes complete machine integration test and functional module tests two parts, system is carried out before device power
Each test board, power supply are tested in self-test.Simulation electronic test will be successively detected after device power according to each call instruction
Module, digital and electronic test module, avionics bus test module, cabinet and power supply system, distinctive signal emulation module, and unroll
Direct fault location test, to realize real-time acquisition of the host computer to product.
It is guided after industrial personal computer is powered up or reset by jump instruction and enters startup procedure, when the first subsynchronous i.e. booting
After synchronizing successfully, 50 m s task runs being entered later and are synchronized, the synchronous time waited is 50 m s.Software completes computer
Initialization management, the initialization of redundancy management；If not receiving synchronization signal in the synchronous waiting time, system delay one is clapped
Starting is synchronous to restore, and carries out computer power-up BIT test, and the synchronous time restored is 51m s, is greater than minimum monitoring 50 m of period
s；It is successfully recovered if synchronizing, enters 50 m s tasks, and wait next subsynchronous.If synchronous restore also to fail, record is same
Permanent fault is walked, which stops output, into endless loop.If occurring synchronization failure again, binary channels enters simultaneously to be synchronized
Restore, and then the OFF signal that has according to input, carries out functional module conversion testing.
Referring to Fig. 2, direct fault location entirety implementation flow chart of the invention, the specific steps are as follows: first after device power, on
A certain channel power source falls in position organ, i.e., the channel crystal oscillator is in off position, checks that other channel computers have inerrancy letter
Number, if it has not, it is high level that setting function, which decides by vote output, local variable is initialized, according to communications protocol, executes and tests quilt
Default execution number is arranged in survey each function of computer, detects whether each channel computer operation has exception, when execution cycle detection
Process kind notes abnormalities, and detected value DIA sets height in each hardware module of computer, then shows that corresponding test point is abnormal.
Successively to rest channels DIA value, channel computer address is simultaneously put to the vote where retaining mistake, when a failure,
It then can proceed with work, take vote value as control instruction, control executing agency.
When DIA value and rest channels not be 1, then start the track algorithm inside test equipment, built-in synchro indicator
Work is carried out while being acquired to related sensor input channel, and each channel computer carries out Cross transfer, software by CCDL
Redundancy management is carried out, takes vote value as control instruction, controls test macro operation.
In the present invention, a kind of steady flight control computer test method of control increasing includes the following steps:
Step 1: power supply system is supplied to control and increases the power supply of steady flight control computer three-way power on analog machine, and can independent control its
On-off is monitored power supply and protects；
Step 2: acquisition control increases the out-put supply signal of steady flight control computer；
Step 3: communication being carried out with the steady flight control computer of control increasing by RS422 communication interface and data are crosslinked；
Step 4: simulation control increases the discrete input of steady flight control computer, output signal, and input, output signal include that 28V/ opens letter
Number, 15V/ON signal；
Step 5: emulation HB6096 bus and GJB289A bus signals complete the bus for increasing steady flight control computer with control to be measured
Communication and detection；
Step 6: completing various kinds of sensors signal simulation, include dynamic and static pressure, yaw angle, the left and right angle of attack, the exchanges such as angular displacement biography
Sensor and acceleration, the emulation of the direct current transducers such as angular speed；
Step 7: completing all kinds of horizontal tails, aileron, rudder steering engine signal simulation, include horizontal tail, the limit, the front part of a Chinese robe or jacket, flaperon, direction
The emulation of the signals such as rudder；
Step 8: achievable control increases the given of steady flight control computer analog signal, and can collecting computer analog signal in real time
Output.
Above-mentioned test method completes product test to be measured and record, incoming/outgoing management and channel failure logic, bus
Transmit/receive test, CCDL transmission.
Above-mentioned test method realizes that, to left/right horizontal tail steering engine, left/right flaperon steering engine, direction steering engine, left/right servo is put
Synchronous and signal cross transmits control test, the voting of remaining signal and monitoring and tests, is real between big loop simulation test, channel
Existing system control logic is comprehensive to be tested with control mode conversion.
Claims (5)
1. a kind of control increases steady flight control computer test macro, it includes complete machine comprehensive test platform and functional test module, is surveyed
Examination platform should have emulation aircraft bus module, be mainly used for all kinds of buses that emulation increases steady flight control computer crosslinking with control and believe
Number, bus signals are converted to by using GJB289A and ARINC429 bus board, control is sent to and increases steady flight control computer,
And by software emulation bus failure mode, the test of system bus signal is carried out；
The functional module part of detecting includes that PXI cabinet, adapter and industrial personal computer software test module, the adapter are used for
Unit under test is connected, the PXI cabinet includes ACE simulation electronic test module, DCE digital and electronic test module, avionics bus
Test module, distinctive signal emulation module, interface and power supply system.
2. each analog channel configures the independent excitation/measuring instrument of muti-piece: High Speed Analog input/output and dynamic waveform editor
Device, Dynamic Signal simulation analysis instrument, high-precision embedded signal analyzer.
Include the following steps: 3. a kind of control increases steady flight control computer test method
Step 1: power supply system is supplied to control and increases the power supply of steady flight control computer three-way power on analog machine, and can independent control its
On-off is monitored power supply and protects；
Step 2: acquisition control increases the out-put supply signal of steady flight control computer；
Step 3: communication being carried out with the steady flight control computer of control increasing by RS422 communication interface and data are crosslinked；
Step 4: simulation control increases the discrete input of steady flight control computer, output signal, and input, output signal include that 28V/ opens letter
Number, 15V/ON signal；
Step 5: emulation HB6096 bus and GJB289A bus signals complete the bus for increasing steady flight control computer with control to be measured
Communication and detection；
Step 6: completing various kinds of sensors signal simulation, include dynamic and static pressure, yaw angle, the left and right angle of attack, the exchanges such as angular displacement biography
Sensor and acceleration, the emulation of the direct current transducers such as angular speed；
Step 7: completing all kinds of horizontal tails, aileron, rudder steering engine signal simulation, include horizontal tail, the limit, the front part of a Chinese robe or jacket, flaperon, direction
The emulation of the signals such as rudder；
Step 8: achievable control increases the given of steady flight control computer analog signal, and can collecting computer analog signal in real time
Output.
4. test method according to claim 3 completes product test to be measured and record, incoming/outgoing management and channel
Fault logic, bus transmit/receive test, CCDL transmission.
5. test method according to claim 3, above-mentioned test method are realized to left/right horizontal tail steering engine, left/right flap pair
Wing steering engine, direction steering engine, synchronous between the emulation testing of left/right servo amplifying return circuit, channel and signal cross transmission control test,
System control logic synthesis and control mode conversion test are realized in the voting and monitoring test of remaining signal.
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| CN201910635610.1A CN110488630B (en) | 2019-07-15 | 2019-07-15 | Test system and test method for controlling stability-increasing flight control computer |
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| CN201910635610.1A CN110488630B (en) | 2019-07-15 | 2019-07-15 | Test system and test method for controlling stability-increasing flight control computer |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112115552A (en) * | 2020-09-16 | 2020-12-22 | 天津津航计算技术研究所 | Airborne flight data recharging method and device |
| CN112346331A (en) * | 2020-11-18 | 2021-02-09 | 西安爱生技术集团公司 | Channel selection method of three-redundancy flight control computer |
| CN112596539A (en) * | 2020-12-04 | 2021-04-02 | 中国航空工业集团公司成都飞机设计研究所 | Differential extraction, construction and synchronization method for flight control stability augmentation controlled variable |
| CN113448784A (en) * | 2021-05-27 | 2021-09-28 | 中国航空工业集团公司沈阳飞机设计研究所 | Computer BIT system and method thereof |
| CN113703419A (en) * | 2021-08-08 | 2021-11-26 | 中国航空工业集团公司沈阳飞机设计研究所 | Automatic testing method and device for redundancy management algorithm of flight control system |
| CN114200909A (en) * | 2021-11-08 | 2022-03-18 | 陕西千山航空电子有限责任公司 | Analog quantity module test platform and test method based on PXI bus |
| CN114348291A (en) * | 2021-12-17 | 2022-04-15 | 国营芜湖机械厂 | Flight fault diagnosis method based on flight parameter data and simulation |
| CN114721358A (en) * | 2022-05-10 | 2022-07-08 | 中国民航大学 | Technology for testing ground function of flight control system and switching device |
| CN115755866A (en) * | 2022-12-21 | 2023-03-07 | 杭州牧星科技有限公司 | Unmanned aerial vehicle flies to control computer test system |
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| CN114348291A (en) * | 2021-12-17 | 2022-04-15 | 国营芜湖机械厂 | Flight fault diagnosis method based on flight parameter data and simulation |
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| CN114721358A (en) * | 2022-05-10 | 2022-07-08 | 中国民航大学 | Technology for testing ground function of flight control system and switching device |
| CN114721358B (en) * | 2022-05-10 | 2022-08-23 | 中国民航大学 | Switching device for ground function test of flight control system |
| CN115755866A (en) * | 2022-12-21 | 2023-03-07 | 杭州牧星科技有限公司 | Unmanned aerial vehicle flies to control computer test system |
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