CN204028691U - Aeromotor hardware is in loop test system - Google Patents
Aeromotor hardware is in loop test system Download PDFInfo
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- CN204028691U CN204028691U CN201420352736.0U CN201420352736U CN204028691U CN 204028691 U CN204028691 U CN 204028691U CN 201420352736 U CN201420352736 U CN 201420352736U CN 204028691 U CN204028691 U CN 204028691U
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Abstract
The utility model provides a kind of aeromotor hardware in loop test system, comprise: for carrying out the electronic controller of engine control, real-time simulation apparatus for simulating engine behavior, for the conditioning of executive signal and the signal condition of collection and harvester, and the fault injection device injecting for carrying out fault, this signal condition and harvester are coupled to this real-time simulation apparatus, this fault injection device is respectively by hardwire and this signal condition and harvester, be connected with this electronic controller, wherein, this aeromotor hardware also comprises in loop test system: ARINC bus board and Ethernet board, this fault injection device is connected with this real-time simulation apparatus by this ARINC bus board, and be connected with this real-time simulation apparatus by this Ethernet board.
Description
Technical field
The utility model relates to the pilot system of aeroengine control system, relates in particular to aeromotor hardware in loop test system.
Background technology
The design of civil aviation engine and manufacture process are extremely complicated, have represented the highest level of Modern Manufacturing Industry.Modern civil aviation engine control system is full powers limit digital engine Electronic Control (FADEC), fuel oil control, health control, starting and the igniting of engine have been comprised, and anti-pushing system, it is very complicated, a crosslinked very high system of degree of coupling, relate to totally pneumatic, structural strength, electric, mechanical-hydraulic, fuel oil and lubricating oil, bleed, and the field of a plurality of subjects such as Airborne Software and bus communication and engineering.At present, be also at home the engine control system of developing first the airliner that possesses seaworthiness.For domestic, this is also the challenge of a long-term technical research.
According to the requirement of complicated mobile system development process (SAE ARP4754A) and seaworthiness checking (CCAR33.28), integrated and the seaworthiness checking of civil aviation engine control system is that a workload is very big, content is very complicated, the crosslinked very high verification experimental verification work of degree of coupling of system.Domestic existing system hardware is at loop verification system, can be at some engineering field, and as electric automobile etc., can completion system integrated verification at circuit platform by building hardware.But in the face of bulky complex like this, high degree of coupling, high reliability and security and relate to the civil aviation engine control system in multidisciplinary field, there is many deficiencies at loop verification platform in domestic existing hardware.
Fig. 1 shows traditional aeromotor hardware at the servo control loop of loop test system.In traditional experiment system architecture, electronic controller is according to controlling target, send servo current signal to control the position of actuator, by cable, current signal harvester etc., collect and in simulator, carry out engine simulation calculating, with simulated engine behavior, for example calculate or simulate the sensing signal of engine actual sensor, displacement sensing signal for example, by displacement signal conditioning module, feed back to electronic controller, thereby form a servo closed control loop.
First, servo current signal, the control bit shifting signal of engine control system are numerous, and therefore, the fault Injection Signal of electronic controller is also numerous, and by fault injection device, on the signal cable on each road, inject fault-signal, thereby can only realize the injection of Single Point of Faliure.Adopt this traditional experiment system, fault injection device cannot carry out the real-time interlock of a plurality of testing equipments such as real-time simulation apparatus, signal regulating device, fault injection device preferably, thereby realizes the multiple combination faults such as servo current signal, control bit shifting signal and power supply
Secondly, the servo current signal of engine control system, control bit shifting signal, throttle platform control signal reach tens of roads.Every road signal has all adopted cable rigid line to connect.If pilot system is longer service time, easily there is the situations such as cable becomes flexible.
And due to the engine control system of different model, the air plug of the signal cable adopting and corresponding stitch are different.Therefore, traditional experiment system architecture adopts cable connected mode, can only be suitable for the engine control system of a certain model.If need the engine control system of applicable another model, just need to carry out manual wiring adjustment to the stube cable of pilot system, very inconvenient.
Therefore, this area needs a kind of improved aeromotor hardware in loop test system.
Utility model content
Below provide the brief overview of one or more aspects so that the basic comprehension to these aspects to be provided.Detailed combine of this not all aspect contemplating of general introduction look at, and neither the also non-scope of attempting to define any or all aspect of the key or decisive key element that is intended to point out out all aspects.Its unique object is the order that some concepts that will provide in simplified form one or more aspects are thought the more detailed description providing after a while.
According to one side of the present utility model, provide a kind of aeromotor hardware in loop test system, comprise: for carrying out the electronic controller of engine control, real-time simulation apparatus for simulating engine behavior, for the conditioning of executive signal and the signal condition of collection and harvester, and the fault injection device injecting for carrying out fault, this signal condition and harvester are coupled to this real-time simulation apparatus, this fault injection device is respectively by hardwire and this signal condition and harvester, be connected with this electronic controller, wherein, this aeromotor hardware also comprises in loop test system: ARINC bus board and Ethernet board, this fault injection device is connected with this real-time simulation apparatus by this ARINC bus board, and be connected with this real-time simulation apparatus by this Ethernet board.
In one example, this fault injection device comprises for receiving and dispatching an ARINC bus transceiver of ARINC bus signals; This real-time simulation apparatus comprises that this ARINC bus board is connected with an ARINC bus transceiver of this fault injection device and the 2nd ARINC bus transceiver of this real-time simulation apparatus respectively for receiving and dispatching the 2nd ARINC bus transceiver of ARINC bus signals.
In one example, this fault injection device comprises for receiving and dispatching the first ethernet transceiver of ethernet signal; This real-time simulation apparatus comprises that, for receiving and dispatching the second ethernet transceiver of ethernet signal, this Ethernet board is connected with this first ethernet transceiver of this fault injection device and this second ethernet transceiver of this real-time simulation apparatus respectively.
In one example, this signal condition and harvester are coupled to this real-time simulation apparatus and further comprise: between this signal condition and harvester and this real-time simulation apparatus, by bus, be connected.
In one example, this signal condition and harvester comprise signal regulating device and signal pickup assembly, and this signal regulating device comprises the first bus digit signal receiver and the first bus numeral signal projector; This real-time simulation apparatus comprises the second bus numeral signal projector and the second bus digit signal receiver; This of this signal regulating device the first bus digit signal receiver is connected with this second bus numeral signal projector of this real-time simulation apparatus by bus, and this first bus numeral signal projector of this signal pickup assembly is connected with this second bus digit signal receiver of this real-time simulation apparatus by bus.
In one example, this first bus numeral signal projector comprises for simulating signal being converted to the analog to digital converter of digital signal.
In one example, this signal regulating device comprises for digital signal being converted to the digital to analog converter of simulating signal.
In one example, this signal condition comprises at least one in the temperature signal regulation device separately with digital to analog converter, pressure signal conditioning device, frequency signal conditioning device.
In one example, this signal regulating device comprises at least one in switching value input signal conditioning device, switching value output signal harvester.
In one example, this real-time simulation apparatus sends power management echo signal by this ARINC bus board to this fault injection device, and by this Ethernet board, to this fault injection device, send fault and inject instruction, this fault injection device injects instruction according to this fault this power management echo signal is carried out to fault injection.
In one example, this real-time simulation apparatus sends this power management echo signal and this fault injection instruction in real time according to test case and test script.
In one example, this electronic controller is also connected by bus with this fault injection device.
In one example, this real-time simulation apparatus obtains the control signal of being calculated by this electronic controller from this electronic controller by this ARINC bus board, based on this control signal, synchronize with the sensing signal executive signal that self gathers, and after this signal is synchronous, according to test case and test script, send this power management echo signal and inject instruction with this fault.
In one example, this control signal comprises displacement control signal, and this sensing signal comprises displacement sensing signal.
In one example, this control signal also comprises speed controling signal, and this sensing signal comprises speed-frequency sensing signal.
By one side of the present utility model, by the real-time simulation apparatus facilitated by ARINC bus board and Ethernet board and ARINC bus communication and the ethernet communication between fault injection device, the automatic realization of carrying out the combined system Test to Failure of various engines control system according to test case and test script for real-time simulation apparatus provides the foundation.
By on the other hand of the present utility model, the internal bus configuration between real-time simulation apparatus and signal condition and harvester can significantly improve the speed of signal transmission, reduces in large quantities the cable of system signal, thereby improves the reliability of test platform.And, can be applicable to quickly and easily different cable air plugs and the stitch thereof of the engine control system of Multiple Type, and without the stube cable of pilot system being carried out to manual wiring adjustment, thereby increase substantially the progress of model test.
Accompanying drawing explanation
After reading in conjunction with the following drawings the detailed description of embodiment of the present disclosure, can understand better above-mentioned feature and advantage of the present utility model.In the accompanying drawings, each assembly is not necessarily drawn in proportion, and the assembly with similar correlation properties or feature may have identical or close Reference numeral.
Fig. 1 shows traditional aeromotor hardware at the block diagram of the servo control loop of loop test system;
Fig. 2 shows the block diagram in loop test system according to one side aeromotor hardware of the present utility model;
Fig. 3 shows the block diagram at the servo control loop of loop test system according to the aeromotor hardware of an embodiment of the present utility model;
Fig. 4 shows the block diagram that traditional aeromotor hardware is controlled for rotating speed in loop test system; And
Fig. 5 shows the block diagram of controlling for rotating speed in loop test system according to the aeromotor hardware of an embodiment of the present utility model.
Embodiment
Below in conjunction with the drawings and specific embodiments, the utility model is described in detail.Note, the aspects of describing below in conjunction with the drawings and specific embodiments is only exemplary, and should not be understood to protection domain of the present utility model to carry out any restriction.
Fig. 2 shows the block diagram in loop test system 200 according to one side aeromotor hardware of the present utility model.System 200 can comprise the real-time simulation apparatus 210 for simulating engine behavior.Real-time simulation apparatus 210 can be the unify high-performance industrial computer of the simulated environment of supporting MATLAB/SIMULINK of operation real-time oss.
Real-time simulation apparatus 210 receives the control signal that electronic controller 240 transmits, the various models of real time execution, such as aeromotor and airplane digital model, displacement model, temperature model, pressure model, frequency model, switching value model, current model, network communication input/output model etc., calculate the sensing signal of each sensor of engine and aircraft, and by signal condition and harvester 220, send these sensing signals to electronic controller 240 and using and further generate the foundation of control signal as it.As the skilled person easily understood, these all kinds of realistic models that these real-time simulation apparatus 210 move are known in the field.In addition, as readily understood by the skilled person, electronic controller 240 is the subjects of civil aviation engine hardware at loop test.Electronic controller 240 can complete the control of aeromotor fuel oil, health control, starting and ignition function.
Particularly, signal condition and harvester 220 can comprise signal regulating device 220a and signal pickup assembly 220b.Signal regulating device 220 can carry out suitable conditioning to mail to the sensing signal of electronic controller 240 from real-time simulation apparatus 210, such as signal amplification etc.Signal regulating device 220a can comprise the displacement signal conditioning device 223 of execution displacement sensing signal conditioning, carries out the temperature signal regulation device 224 of temperature sensing signal conditioning, carry out the pressure signal conditioning device 225 of pressure-sensing signal condition and the switching value input signal conditioning device 227 of execution switching value input signal conditioning.
Signal pickup assembly 220b can gather mail to the signal of real-time simulation apparatus 210 from electronic controller 240.Signal pickup assembly 220b can comprise the current signal harvester 228 of carrying out current signal collection and the switching value output signal harvester 229 of carrying out switching value output signal collection.
For in test in the signal transmitting between real-time simulation apparatus 210 and electronic controller 240 such as all kinds of faults of test use, between signal condition and harvester 220 and electronic controller 240, be provided with fault injection device 230 for carrying out fault function of injecting.Fault injection device 230 can pass through respectively hardwire (for example, cable) and be connected with harvester 220 with signal condition with electronic controller 240.
System 200 also comprises power management device 201, remote work station 202, man-machine interaction and engine operation and parameter display equipment 203, power distribution and control device 204 and airborne power supply analogue means 205.
Power management device 201 can be comprised of throttle platform, the Generator Control Switch of emulation, has simulated throttle and the state of engine and has controlled function.
Remote work station 202 can be comprised of station terminal, display and supporting netting twine, and the management of responsible running test and control software.According to the content of test mission book and test program, test management software can complete the demand of engine control system in DOORS platform, mapping to hardware in loop test demand, sets up the test item example of test, and automatically generates the test script of the batch processing of test.
Man-machine interaction can be comprised of station terminal, display and supporting netting twine with engine operation and parameter display equipment 203, complete the control that engine operating parameter and curve show, the artificial engine parameter function of setting, and complete engine control system real time execution parameter and curve demonstration, and the Presentation Function of data readback.
Power distribution and control device 204 can completion system device power and the control function of detection, airborne power supply simulation.Airborne power supply analogue means 205 can simulation electronic controller 240 power supply.
According to one side of the present utility model, between signal condition and harvester 220 and real-time simulation apparatus 210, by bus, be connected.Particularly, as shown in Figure 2, signal regulating device 220a can comprise bus digit signal receiver 221, and signal pickup assembly 220b can comprise bus numeral signal projector 222.Correspondingly, real-time simulation apparatus 210 can comprise bus numeral signal projector 211 and bus digit signal receiver 212.The bus digit signal receiver 221 of signal regulating device 220a can be connected with the bus numeral signal projector 211 of real-time simulation apparatus 210 by bus.The bus numeral signal projector 222 of signal pickup assembly 220b can be connected with the bus digit signal receiver 212 of real-time simulation apparatus 210 by bus.
In this way, between real-time simulation apparatus 210 and real-time simulation apparatus 210, can carry out transceiver bus digital signal by internal bus, but not receive and dispatch simulating signal by hardwire.
The signal obtaining by signals collecting due to signal pickup assembly 220b is actual physics signal, i.e. simulating signal, and therefore, bus numeral signal projector 222 can comprise for simulating signal being converted to the analog to digital converter (not shown) of digital signal.Similarly, because signal regulating device 220a need to fault injection device 230 and then what transmit to electronic controller 240 be actual physics signal, it is simulating signal, therefore, signal regulating device 220a can comprise for digital signal being converted to the digital to analog converter (not shown) of simulating signal.In one example, displacement signal conditioning device 223, temperature signal regulation device 224, pressure signal conditioning device 225 and switching value input signal conditioning device 227 can comprise digital to analog converter separately.
Note, although included displacement signal conditioning device 223, temperature signal regulation device 224, pressure signal conditioning device 225 and the switching value input signal conditioning device 227 of the 220a of signal regulating device shown in Fig. 2 shares a bus digit signal receiver 221, but, as readily understood by the skilled person, these conditioning devices also can have respectively bus digit signal receiver 221 separately.Similarly, current signal harvester 228 and switching value output signal harvester 229 also can be configured to the bus numeral signal projector 222 having respectively separately.
Than transmit the mode of simulating signal between traditional real-time simulation apparatus and signal condition and harvester by hardwire, internal bus configuration between real-time simulation apparatus 210 of the present utility model and signal condition and harvester 220 can significantly improve the speed of signal transmission, reduce in large quantities the cable of system signal, thereby improve the reliability of test platform.On the other hand, can be applicable to quickly and easily different cable air plugs and the stitch thereof of the engine control system of Multiple Type, and without the stube cable of pilot system being carried out to manual wiring adjustment, thereby increased substantially the progress that model is tested.
According on the other hand of the present utility model, system 200 also can comprise ARINC bus board 250 and Ethernet board 260.Fault injection device 230 can be connected with real-time simulation apparatus 210 with Ethernet board 260 by ARINC bus board 250.In this configuration, electronic controller 240 also can be connected by bus with fault injection device 230, as shown in the connecting line of four-headed arrow.
Particularly, fault injection device 230 can comprise ARINC bus transceiver 231, and correspondingly, real-time simulation apparatus 210 can comprise ARINC bus transceiver 213.ARINC bus board 250 can be connected with the ARINC bus transceiver 231 of fault injection device 230 and the ARINC bus transceiver 213 of real-time simulation apparatus 210 respectively.
Fault injection device 230 also can comprise ethernet transceiver 232, and correspondingly, real-time simulation apparatus 210 also can comprise ethernet transceiver 214.Ethernet board 260 can be connected with the ethernet transceiver 232 of fault injection device 230 and the ethernet transceiver 214 of real-time simulation apparatus 210 respectively.
In this way, can between real-time simulation apparatus 210 and fault injection device, transmit in real time ARINC bus signals and ethernet signal.More preferably, real-time simulation apparatus 210 can send power management echo signal to fault injection device 230 by ARINC bus board 250, and by Ethernet board 260, to fault injection device 230, sends fault and inject instruction.Fault injection device 230 can inject instruction according to fault thus power management echo signal is carried out to fault injection.
Than traditional fault, inject, in the utility model, by the real-time simulation apparatus 210 facilitated by ARINC bus board 250 and Ethernet board 260 and ARINC bus communication and the ethernet communication between fault injection device 230, the automatic realization of carrying out the combined system Test to Failure of various engines control system according to test case and test script for real-time simulation apparatus provides the foundation.This advantage is below being described in detail in conjunction with specific embodiments.
Fig. 3 shows the block diagram at the servo control loop of loop test system 300 according to the aeromotor hardware of an embodiment of the present utility model.The system 300 of Fig. 3 is used to illustrate servocontrol as understood by a person skilled in the art, and therefore, some parts of system 300 are not all illustrated in Fig. 3.
In Fig. 3, current signal harvester 328 can comprise bus numeral signal projector 322, and correspondingly, real-time simulation apparatus 310 can comprise bus digit signal receiver 312.The bus numeral signal projector 322 of current signal harvester 328 can be connected with the bus digit signal receiver 312 of real-time simulation apparatus 310 by bus.Displacement signal conditioning device 323 can comprise bus digit signal receiver 321, and correspondingly, real-time simulation apparatus 310 can comprise bus numeral signal projector 311.The bus digit signal receiver 321 of displacement signal conditioning device 323 can be connected with the bus numeral signal projector 311 of real-time simulation apparatus 310 by bus.Bus numeral signal projector 322 can comprise for simulating signal being converted to the analog to digital converter (not shown) of digital signal.Displacement signal conditioning device 323 can comprise for digital signal being converted to the digital to analog converter (not shown) of simulating signal.
On the other hand, fault injection device 330 can comprise ethernet transceiver 332 and ARINC bus transceiver 331, and correspondingly, real-time simulation apparatus 310 can comprise ethernet transceiver 314 and ARINC bus transceiver 313.Ethernet board 360 can be connected with the ethernet transceiver 332 of fault injection device 330 and the ethernet transceiver 314 of real-time simulation apparatus 310 by ethernet line respectively.ARINC bus board 350 can be connected with the ARINC bus transceiver 331 of fault injection device 330 and the ARINC bus transceiver 313 of real-time simulation apparatus 310 by ARINC bus respectively.Electronic controller 340 also can be connected to carry out bus connection with fault injection device 330 by bus, shown in electronic controller 340 and the four-headed arrow connecting line between fault injection device 330 as shown in Figure 3.
The multipath servo current signal that electronic controller 340 sends, by current signal harvester 328, carry out signals collecting, and by the analog to digital converter of its bus numeral signal projector 322, simulating signal is converted to after digital signal, the send to real-time simulation apparatus 310 real-time by internal bus carries out computing.Real-time simulation apparatus 310 receives the digital signal of servo current by its bus digit signal receiver 310.In real-time resolving, go out after multichannel displacement control signal, by its bus numeral signal projector 311 by the digital signal of the multichannel displacement control signal calculating, by internal bus, send successively in real time the bus digit signal receiver 321 of displacement signal conditioning device 323 to, displacement signal conditioning device 323 converts the displacement control simulation signal of controlling displacement to after receiving displacement control figure signal, by hardwire (for example, signal cable) feed back to electronic controller 340, thereby form a servo closed control loop.
With respect to traditional pilot system framework, system of the present utility model has adopted the connected mode of internal bus, the numerous servocontrol displacement sensing signal of anti-motor control system that real-time simulation apparatus 310 is resolved, sends to displacement signal conditioning device 323 by internal bus; Meanwhile, the digital quantity of the servocontrol electric current that reaches tens of roads that current signal harvester 328 is sent, sends to real-time simulation apparatus 310 by internal bus.And the power management echo signals such as the throttle lever that throttle platform 301 is sent, fuel cock, send to electronic controller 340 by ARINC bus board 350 by ARINC bus.For the numerous engine control system of system signal, can save the wire harness that a large amount of cables connects, reduced the probability that occurs the situations such as cable is loosening, improved the reliability of test platform.
Another advantage of system of the present utility model is, air plug and the corresponding stitch of the signal cable adopting due to the engine control system of different model are all different.As shown in Figure 3, if need be applicable to the engine control system of another model, only need adjust according to the interface control document of this model engine control system (ICD) sequencing of internal bus and ARINC bus transmitt or receive signal, can be applicable to quickly and easily the engine control system of another model, and without the stube cable of test platform being carried out to manual wiring adjustment, thereby increased substantially the progress that model is tested.
In this embodiment, can between real-time simulation apparatus 310 and fault injection device 340, transmit in real time ARINC bus signals and ethernet signal.More preferably, real-time simulation apparatus 310 can send various power management echo signals to fault injection device 230 by ARINC bus board 350, and by Ethernet board 360, to fault injection device 330, sends fault and inject instruction.Fault injection device 330 can inject instruction according to fault thus power management echo signal is carried out to fault injection.In the example shown in Fig. 3, fault injection device 330 can comprise signal synthesizer 333, for resultant fault, injects instruction and power management echo signal, carries out fault injection.In one example, real-time simulation apparatus 310 can send power management echo signal and fault injection instruction in real time according to for example test case and the test script from remote work station 302.
More preferably, by the framework of system 300, real-time simulation apparatus 310 can obtain from electronic controller 340 control signal of being calculated by electronic controller 340 by ARINC bus board 350, thereby can synchronize with the sensing signal executive signal that self gathers based on this control signal, and according to test case and test script, send power management echo signal and described fault injection instruction after this signal is synchronous.
Than traditional fault, inject, in the utility model, by the real-time simulation apparatus 310 facilitated by ARINC bus board 350 and Ethernet board 360 and ARINC bus communication and the ethernet communication between fault injection device 330, the automatic realization of carrying out the combined system Test to Failure of various engines control system according to test case and test script for real-time simulation apparatus provides the foundation.
For example, system 300 based on Fig. 3, the test case that real-time simulation apparatus 310 can send according to remote work station 302 and test script, according to the sequential of test case regulation, send in real time throttle platform by ARINC bus and control echo signal, displacement target signal; And the moment of stipulating in test case, by Ethernet, send the fault of throttle lever signal, displacement target signal is injected to instruction, and by fault injection device 340 realize multichannel unlike signal fault separately regulation the moment occur, thereby realize the injection of combined fault, complete the more difficult combined fault system test completing of traditional experiment platform.
A kind of typical engine fuel control servo loop fault test of take is example, this fault test requires: when the displacement sensing signal of displacement transducer collection, and the threshold value that surpasses regulation between the displacement control signal of electronic controller 340 interior real-time calculating, and continue the specific time, can cut off the signal of current acquisition.
Traditional test platform, just be difficult to the displacement sensing signal that guarantees that displacement transducer gathers, with synchronizeing on system operation time between the displacement control signal of electronic controller 340 interior real-time calculating, thereby more difficult this class control loop combined fault of realizing, also difficulty tests out the lasting time of combined fault exactly.Adopt the system 300 of Fig. 3, real-time simulation apparatus 310 not only can be real-time the displacement sensing signal of collection displacement transducer, and can pass through the displacement control signal of ARINC bus Real-time Obtaining electronic controller 340 interior real-time calculating, thereby can make these two signals take the real-time clock of real-time simulation apparatus, as standard, carry out signal transmission, signal is synchronous.On this basis, the test case that real-time simulation apparatus 310 sends according to remote work station 302 again and test script, according to the sequential of test case regulation, send throttle platform control signal, displacement target signal in real time; And the moment of stipulating in test case, by Ethernet, send by the fault for displacement target signal of test case appointment and inject instruction, and by fault injection device 330 realize designated displacement echo signal fault regulation the moment occur, thereby realize the injection of combined fault, to reach the object of test.
Fig. 4 shows the block diagram that traditional aeromotor hardware is controlled for rotating speed in loop test system.In this traditional experiment system architecture, electronic controller according to rotary speed instruction (, manipulation of objects signal) with the speed-frequency sensing signal receiving, calculate servo current signal (, control signal) control output fuel flow, to reach the rotating speed of appointment, thereby form a close loop control circuit, its shortcoming is with the traditional experiment system architecture shown in Fig. 2.
Fig. 5 shows the block diagram of controlling for rotating speed in loop test system 500 according to the aeromotor hardware of an embodiment of the present utility model.The system 500 of Fig. 5 is used to illustrate rotating speed control as understood by a person skilled in the art, and therefore, some parts of system 500 are not all illustrated in Fig. 5.
In Fig. 5, current signal harvester 528 can comprise bus numeral signal projector 522, and correspondingly, real-time simulation apparatus 510 can comprise bus digit signal receiver 512.The bus numeral signal projector 522 of current signal harvester 528 can be connected with the bus digit signal receiver 512 of real-time simulation apparatus 510 by bus.Displacement signal conditioning device 523 can comprise bus digit signal receiver 521a, and correspondingly, real-time simulation apparatus 510 can comprise bus numeral signal projector 511a.The bus digit signal receiver 521a of displacement signal conditioning device 523 can be connected with the bus numeral signal projector 511a of real-time simulation apparatus 510 by bus.Speed-frequency signal regulating device 526 can comprise bus digit signal receiver 521b, and correspondingly, real-time simulation apparatus 510 can comprise bus numeral signal projector 511b.The bus digit signal receiver 521b of speed-frequency signal regulating device 526 can be connected with the bus numeral signal projector 511b of real-time simulation apparatus 510 by bus.Bus numeral signal projector 522 can comprise for simulating signal being converted to the analog to digital converter (not shown) of digital signal.Displacement signal conditioning device 523 and speed-frequency signal regulating device 526 can comprise separately for digital signal being converted to the digital to analog converter (not shown) of simulating signal.
On the other hand, fault injection device 530 can comprise ethernet transceiver 532 and ARINC bus transceiver 531, and correspondingly, real-time simulation apparatus 510 can comprise ethernet transceiver 514 and ARINC bus transceiver 513.Ethernet board 560 can be connected with the ethernet transceiver 532 of fault injection device 530 and the ethernet transceiver 514 of real-time simulation apparatus 510 by ethernet line respectively.ARINC bus board 550 can be connected with the ARINC bus transceiver 531 of fault injection device 530 and the ARINC bus transceiver 513 of real-time simulation apparatus 510 by ARINC bus respectively.Electronic controller 540 also can be connected to carry out bus connection with fault injection device 530 by bus, shown in electronic controller 540 and the four-headed arrow connecting line between fault injection device 530 as shown in Figure 5.
The throttle lever that real-time simulation apparatus 510 comprehensively sends from remote work station 502, throttle platform 501, fuel cock etc. are controlled echo signal, send to the ARINC bus transceiver 531 of fault injection device 530 by ARINC bus board 560.Meanwhile, the fail-safe control instruction that the ethernet transceiver 532 of fault injection device 530 receives from real-time simulation apparatus 510.Fault injection device 530, be signal synthesizer 533 wherein in one example, the information of its ARINC bus transceiver 531, ethernet transceiver 532 is carried out comprehensively, realization is injected control signal and the fault-signals thereof such as throttle lever, fuel cock in specific sequential, and sends to electronic controller 540.The rotary speed instruction that electronic controller 540 sends according to ARINC bus board 550, the speed-frequency sensing signal sending with speed-frequency signal regulating device 526, calculate servo current signal, and by current signal harvester 528, send to real-time simulation apparatus 510 and control output fuel flow, to reach the appointment rotating speed being sent by ARINC bus, thereby form a speed closed loop control loop.
With respect to traditional pilot system framework, system of the present utility model has adopted the connected mode of internal bus, numerous servocontrol displacement sensing signal, the speed-frequency sensing signal of anti-motor control system that real-time simulation apparatus 510 is resolved, sends to displacement signal conditioning device 523 and speed-frequency signal regulating device 526 by internal bus.Meanwhile, the digital quantity of the servocontrol electric current that reaches tens of roads that current signal harvester 528 is sent, sends to real-time simulation apparatus 510 by internal bus.And the power management echo signals such as the throttle lever that throttle platform 501 is sent, fuel cock, send to electronic controller 540 by ARINC bus board 550 by ARINC bus.For the numerous engine control system of system signal, can save the wire harness that a large amount of cables connects, reduced the probability that occurs the situations such as cable is loosening, improved the reliability of test platform.
Another advantage of system of the present utility model is, air plug and the corresponding stitch of the signal cable adopting due to the engine control system of different model are all different.As shown in Figure 5, if need be applicable to the engine control system of another model, only need adjust according to the interface control document of this model engine control system (ICD) sequencing of internal bus and ARINC bus transmitt or receive signal, can be applicable to quickly and easily the engine control system of another model, and without the stube cable of test platform being carried out to manual wiring adjustment, thereby increased substantially the progress that model is tested.
In this embodiment, can between real-time simulation apparatus 510 and fault injection device 540, transmit in real time ARINC bus signals and ethernet signal.More preferably, real-time simulation apparatus 510 can send various power management echo signals to fault injection device 230 by ARINC bus board 550, and by Ethernet board 560, to fault injection device 530, sends fault and inject instruction.Fault injection device 530 can inject instruction according to fault thus power management echo signal is carried out to fault injection.In the example shown in Fig. 5, fault injection device 530 can comprise signal synthesizer 533, for resultant fault, injects instruction and power management echo signal, carries out fault injection.In one example, real-time simulation apparatus 510 can send power management echo signal and fault injection instruction in real time according to for example test case and the test script from remote work station 502.
More preferably, by the framework of system 500, real-time simulation apparatus 510 can obtain from electronic controller 540 control signal of being calculated by electronic controller 540 by ARINC bus board 550, thereby can synchronize with the sensing signal executive signal that self gathers based on this control signal, and according to test case and test script, send power management echo signal and described fault injection instruction after this signal is synchronous.
Than traditional fault, inject, in the utility model, by the real-time simulation apparatus 510 facilitated by ARINC bus board 550 and Ethernet board 560 and ARINC bus communication and the ethernet communication between fault injection device 530, the automatic realization of carrying out the combined system Test to Failure of various engines control system according to test case and test script for real-time simulation apparatus provides the foundation.
For example, system 500 based on Fig. 5, the test case that real-time simulation apparatus 510 can send according to remote work station 502 and test script, according to the sequential of test case regulation, send in real time throttle platform by ARINC bus and control echo signal, displacement target signal, speed-frequency echo signal; And the moment of stipulating in test case, by Ethernet, send the fault of throttle lever signal, displacement target signal, speed-frequency echo signal is injected to instruction, and by fault injection device 540 realize multichannel unlike signal fault separately regulation the moment occur, thereby realize the injection of combined fault, complete the more difficult combined fault system test completing of traditional experiment platform.
A kind of typical engine start control system fault test of take is example, and this fault test requires: according to the three phases of engine start different rotating speeds, inject successively the rotating speed deviation fault of different numerical value.Traditional test platform, more difficult rotating speed echo signal and the Complete Synchronization of fault Injection Signal within the same standard time realized.
Adopt the system 500 of Fig. 5, real-time simulation apparatus 510 not only can gather the displacement sensing signal of displacement transducer and the fast frequency sensing signal that speed probe turns in real time, and can pass through displacement control signal and the speed controling signal of the 540 interior real-time calculating of ARINC bus Real-time Obtaining electronic controller, thereby can make these two pairs of signals take the real-time clock of real-time simulation apparatus, as standard, carry out signal transmission, signal is synchronous.On this basis, the test case that real-time simulation apparatus 510 sends according to remote work station 502 again and test script, according to the sequential of test case regulation, send throttle platform control signal, displacement target signal, rotating speed echo signal in real time; And the moment of stipulating in test case, by Ethernet, send by the fault for rotating speed echo signal of test case appointment and inject instruction, and realize and specify rotating speed echo signal fault to occur in the moment of regulation by fault injection device 530, thereby realize the injection of rotating speed deviation fault, to reach the object of test.
By one side of the present utility model, by the real-time simulation apparatus facilitated by ARINC bus board and Ethernet board and ARINC bus communication and the ethernet communication between fault injection device, the automatic realization of carrying out the combined system Test to Failure of various engines control system according to test case and test script for real-time simulation apparatus provides the foundation.
By on the other hand of the present utility model, the internal bus configuration between real-time simulation apparatus and signal condition and harvester can significantly improve the speed of signal transmission, reduces in large quantities the cable of system signal, thereby improves the reliability of test platform.And, can be applicable to quickly and easily different cable air plugs and the stitch thereof of the engine control system of Multiple Type, and without the stube cable of pilot system being carried out to manual wiring adjustment, thereby increase substantially the progress of model test.
Providing previous description of the present disclosure is for making any person skilled in the art all can make or use the disclosure.To various modifications of the present disclosure, will be all apparent for a person skilled in the art, and generic principles as defined herein can be applied to other variants and can not depart from spirit or scope of the present disclosure.Thus, the disclosure is not intended to be defined to example described herein and design, but should be awarded the widest scope consistent with principle disclosed herein and novel features.
Claims (15)
1. aeromotor hardware, in a loop test system, comprising:
For carrying out the electronic controller of engine control, real-time simulation apparatus for simulating engine behavior, for the conditioning of executive signal and the signal condition of collection and harvester, and the fault injection device injecting for carrying out fault, described signal condition and harvester are coupled to described real-time simulation apparatus, described fault injection device is connected with described electronic controller with harvester with described signal condition by hardwire respectively
It is characterized in that, described aeromotor hardware also comprises in loop test system:
ARINC bus board and Ethernet board, described fault injection device is connected with described real-time simulation apparatus by described ARINC bus board, and is connected with described real-time simulation apparatus by described Ethernet board.
2. aeromotor hardware as claimed in claim 1, in loop test system, is characterized in that,
Described fault injection device comprises for receiving and dispatching an ARINC bus transceiver of ARINC bus signals;
Described real-time simulation apparatus comprises for receiving and dispatching the 2nd ARINC bus transceiver of ARINC bus signals,
Described ARINC bus board is connected with a described ARINC bus transceiver of described fault injection device and described the 2nd ARINC bus transceiver of described real-time simulation apparatus respectively.
3. aeromotor hardware as claimed in claim 1, in loop test system, is characterized in that,
Described fault injection device comprises for receiving and dispatching the first ethernet transceiver of ethernet signal;
Described real-time simulation apparatus comprises for receiving and dispatching the second ethernet transceiver of ethernet signal,
Described Ethernet board is connected with described first ethernet transceiver of described fault injection device and described second ethernet transceiver of described real-time simulation apparatus respectively.
4. aeromotor hardware as claimed in claim 1, in loop test system, is characterized in that, described signal condition and harvester are coupled to described real-time simulation apparatus and further comprise:
Between described signal condition and harvester and described real-time simulation apparatus, by bus, be connected.
5. aeromotor hardware as claimed in claim 4, in loop test system, is characterized in that,
Described signal condition and harvester comprise signal regulating device and signal pickup assembly, and described signal regulating device comprises the first bus digit signal receiver and the first bus numeral signal projector;
Described real-time simulation apparatus comprises the second bus numeral signal projector and the second bus digit signal receiver;
The described first bus digit signal receiver of described signal regulating device is connected with the described second bus numeral signal projector of described real-time simulation apparatus by bus, and the described first bus numeral signal projector of described signal pickup assembly is connected with the described second bus digit signal receiver of described real-time simulation apparatus by bus.
6. aeromotor hardware as claimed in claim 5, in loop test system, is characterized in that,
Described the first bus numeral signal projector comprises for simulating signal being converted to the analog to digital converter of digital signal.
7. aeromotor hardware as claimed in claim 5, in loop test system, is characterized in that, described signal regulating device comprises for digital signal being converted to the digital to analog converter of simulating signal.
8. aeromotor hardware as claimed in claim 7 is in loop test system, it is characterized in that, described signal condition comprises at least one in the temperature signal regulation device separately with digital to analog converter, pressure signal conditioning device, frequency signal conditioning device.
9. aeromotor hardware as claimed in claim 5, in loop test system, is characterized in that, described signal regulating device comprises at least one in switching value input signal conditioning device, switching value output signal harvester.
10. aeromotor hardware as claimed in claim 1 is in loop test system, it is characterized in that, described real-time simulation apparatus sends power management echo signal by described ARINC bus board to described fault injection device, and by described Ethernet board, to described fault injection device, send fault and inject instruction, described fault injection device injects instruction according to described fault described power management echo signal is carried out to fault injection.
11. aeromotor hardware as claimed in claim 10, in loop test system, is characterized in that, described real-time simulation apparatus is according to test case and test script sends in real time described power management echo signal and described fault is injected instruction.
12. aeromotor hardware as claimed in claim 10, in loop test system, is characterized in that, described electronic controller is also connected by bus with described fault injection device.
13. aeromotor hardware as claimed in claim 12 are in loop test system, it is characterized in that, described real-time simulation apparatus obtains the control signal of being calculated by described electronic controller from described electronic controller by described ARINC bus board, based on described control signal, synchronize with the sensing signal executive signal that self gathers, and according to test case and test script, send described power management echo signal and described fault injection instruction after described signal is synchronous.
14. aeromotor hardware as claimed in claim 13, in loop test system, is characterized in that, described control signal comprises displacement control signal, and described sensing signal comprises displacement sensing signal.
15. aeromotor hardware as claimed in claim 14, in loop test system, is characterized in that, described control signal also comprises speed controling signal, and described sensing signal comprises speed-frequency sensing signal.
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105626271A (en) * | 2015-12-29 | 2016-06-01 | 中国航空工业集团公司沈阳发动机设计研究所 | Combined fault logic treatment method for aircraft engine control system |
| CN106020166A (en) * | 2016-06-07 | 2016-10-12 | 中国南方航空工业(集团)有限公司 | Aeroengine control system detection device |
| CN110443084A (en) * | 2018-05-03 | 2019-11-12 | 中国航发商用航空发动机有限责任公司 | Aero-engine closed-loop simulation method and system, emulation platform and its construction device |
| CN110879584A (en) * | 2019-09-29 | 2020-03-13 | 北京动力机械研究所 | Turbofan engine comprehensive simulation test and fault injection platform for unmanned aerial vehicle |
| CN111191336A (en) * | 2018-11-13 | 2020-05-22 | 中国航发商用航空发动机有限责任公司 | Closed-loop simulation method and system for control prototype of aircraft engine and storage medium |
| CN111238817A (en) * | 2020-01-02 | 2020-06-05 | 北京航天测控技术有限公司 | Fault injection method and system |
| CN111290289A (en) * | 2018-12-10 | 2020-06-16 | 中国科学院沈阳自动化研究所 | Engine hardware-in-loop simulation system |
| CN111505964A (en) * | 2020-05-27 | 2020-08-07 | 西安交通大学 | Full-real information source semi-physical simulation system and test method for aircraft engine |
| CN114115168A (en) * | 2020-09-01 | 2022-03-01 | 上汽通用汽车有限公司 | Fault injection test system |
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- 2014-06-27 CN CN201420352736.0U patent/CN204028691U/en not_active Expired - Lifetime
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105626271A (en) * | 2015-12-29 | 2016-06-01 | 中国航空工业集团公司沈阳发动机设计研究所 | Combined fault logic treatment method for aircraft engine control system |
| CN106020166A (en) * | 2016-06-07 | 2016-10-12 | 中国南方航空工业(集团)有限公司 | Aeroengine control system detection device |
| CN110443084A (en) * | 2018-05-03 | 2019-11-12 | 中国航发商用航空发动机有限责任公司 | Aero-engine closed-loop simulation method and system, emulation platform and its construction device |
| CN110443084B (en) * | 2018-05-03 | 2023-07-18 | 中国航发商用航空发动机有限责任公司 | Aeroengine closed-loop simulation method and system, simulation platform and construction device thereof |
| CN111191336A (en) * | 2018-11-13 | 2020-05-22 | 中国航发商用航空发动机有限责任公司 | Closed-loop simulation method and system for control prototype of aircraft engine and storage medium |
| CN111191336B (en) * | 2018-11-13 | 2023-11-03 | 中国航发商用航空发动机有限责任公司 | Aeroengine control prototype closed-loop simulation method and system and storage medium |
| CN111290289A (en) * | 2018-12-10 | 2020-06-16 | 中国科学院沈阳自动化研究所 | Engine hardware-in-loop simulation system |
| CN110879584A (en) * | 2019-09-29 | 2020-03-13 | 北京动力机械研究所 | Turbofan engine comprehensive simulation test and fault injection platform for unmanned aerial vehicle |
| CN111238817A (en) * | 2020-01-02 | 2020-06-05 | 北京航天测控技术有限公司 | Fault injection method and system |
| CN111505964A (en) * | 2020-05-27 | 2020-08-07 | 西安交通大学 | Full-real information source semi-physical simulation system and test method for aircraft engine |
| CN111505964B (en) * | 2020-05-27 | 2023-03-21 | 西安交通大学 | Full-real information source semi-physical simulation system and test method for aircraft engine |
| CN114115168A (en) * | 2020-09-01 | 2022-03-01 | 上汽通用汽车有限公司 | Fault injection test system |
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Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee after: AECC COMMERCIAL AIRCRAFT ENGINE Co.,Ltd. Address before: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee before: AVIC Commercial Aircraft Engine Co.,Ltd. |
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Granted publication date: 20141217 |