CN105116877A - Testing system of power supply control management processor and method - Google Patents
Testing system of power supply control management processor and method Download PDFInfo
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- CN105116877A CN105116877A CN201510493196.7A CN201510493196A CN105116877A CN 105116877 A CN105116877 A CN 105116877A CN 201510493196 A CN201510493196 A CN 201510493196A CN 105116877 A CN105116877 A CN 105116877A
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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
- G05B23/00—Testing or monitoring of control systems or parts thereof
- G05B23/02—Electric testing or monitoring
- G05B23/0205—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults
- G05B23/0208—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults characterized by the configuration of the monitoring system
- G05B23/0213—Modular or universal configuration of the monitoring system, e.g. monitoring system having modules that may be combined to build monitoring program; monitoring system that can be applied to legacy systems; adaptable monitoring system; using different communication protocols
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Abstract
The present invention provides a testing system of a power supply control management processor and a method. The system comprises a testing signal generating device for generating an excitation signal in a power supply control management processor test and a test processing device which tests whether the function of the power supply control management processor is correct or not according to the output of the power supply control management processor, wherein the excitation signal is used for simulating the working mode and working process of at least one equipment which is connected to the power supply control management processor in an aircraft, and the output of the power supply control management processor is generated according to the excitation signal. According to the power supply control management processor and the method, the problems of time consuming and labor consuming of testing a power supply control management processor in the related technology are solved, and the system and the method have the effects of cost saving and time saving.
Description
Technical field
The present invention relates to power supply control administrative processor validation test technical field, in particular to a kind of test macro and method of power supply control administrative processor.
Background technology
Power supply control management system is the important component part of electric power system, completes the critical functions such as the informix of electric power system, system reconfiguration, load management and fault warning.Along with the development of computer technology and bussing technique, power supply control management system is more and more important in modern aircraft design process.Therefore, need to carry out comprehensive, detailed checking in the ground experiment stage to power supply control management system.
In the demonstration test of power supply control management system, all power supply control administrative processor is relevant for most of Verification Project, and carries out around this power supply control administrative processor.Therefore first validation test should be carried out to the power supply control administrative processor of core.
There is no the test environment and method verified power supply control administrative processor specially at present, the test of power supply control administrative processor is all complete in the test of electric power system ground model.Therefore must build a whole set of electric power system experimental enviroment, environmental structure difficulty is large, the cycle is long, pinpoints the problems and also needs to position faulty equipment, cause test to be wasted time and energy in test.And the functional performance index of power supply control administrative processor self cannot be verified completely.
In order to ensure the cycle of aircraft development, accelerate electric power system and test progress and the difficulty reducing electric power system test, must set up and a kind ofly specially carry out the test macro tested and method of testing for power supply control administrative processor, before electric power system test, power supply control administrative processor comprehensively be tested.
Summary of the invention
The invention provides a kind of test macro of power supply control administrative processor, at least to solve in correlation technique, the problem that test power supply control administrative processor is wasted time and energy.
According to an aspect of the present invention, provide a kind of test macro of power supply control administrative processor, comprise: test signal generation device, for generation of the pumping signal in the validation test of described power supply control administrative processor, wherein, the mode of operation of one of at least equipment that is connected with described power supply control administrative processor on simulated aircraft of described pumping signal and the course of work; Test processes device, according to the output of described power supply control administrative processor, whether the function of testing described power supply control administrative processor is correct, and wherein, the output of described power supply control administrative processor produces according to described pumping signal.
Preferably, described test signal generation device comprise following one of at least: engine controller emulation module, for simulating the work of the engine controller of described aircraft, exports the pumping signal of described engine controller to described power supply control administrative processor; DC power control protector emulation module, for simulating the work of the DC power control protector of described aircraft, exports the pumping signal of described DC power control protector to described power supply control administrative processor; Flying control storage battery charger emulation module, for simulating the work flying control storage battery charger of described aircraft, flying the pumping signal of control storage battery charger described in output to described power supply control administrative processor; External power source watch-dog emulation module, for simulating the work of the external power source watch-dog of described aircraft, exports the pumping signal of described external power source watch-dog to described power supply control administrative processor; AC power control enclosure emulation module, for simulating the work of the AC power control enclosure of described aircraft, exports the pumping signal of described AC power control enclosure to described power supply control administrative processor; AC distribution box emulation module, for simulating the work of the AC distribution box control enclosure of described aircraft, exports the pumping signal of described AC distribution box to described power supply control administrative processor; DC power distribution unit (PDU) emulation module, for simulating the work of the DC power distribution unit (PDU) control enclosure of described aircraft, exports the pumping signal of described DC power distribution unit (PDU) to described power supply control administrative processor; Storage Battery Simulation module, for simulating the work of the accumulator of described aircraft, exports the pumping signal of described accumulator to described power supply control administrative processor; Landing Gear System emulation module, for simulating the work of the Landing Gear System of described aircraft, exports the pumping signal of described Landing Gear System to described power supply control administrative processor.
Preferably, described system also comprises signal process box, described signal process box for receive and nurse one's health described power supply control administrative processor input analog signals, described analog signals is converted into multiple digital signal, and described digital signal is input to described test processes device, use for described test processes device to test.
Preferably, described system also comprises signal measurement panel, and described measurement panel is provided with multiple measured hole, for controlling the break-make of the cable between described test macro and described power supply control administrative processor.
Preferably, described system also comprise industrial control computer and following one of at least: combined type cabinet-type air conditioner, direct supply, alternating current-direct current signal source, display, power control switch, signal measurement panel and stube cable, wherein, described test signal generation device and described test processes device are arranged in described industrial control computer.
Preferably, described direct supply, is connected to the power input interface of described power supply control administrative processor by stube cable, for simulating the 28V direct supply needed for the work of described power supply control administrative processor.
Preferably, described alternating current-direct current signal source, signal input interface corresponding to described power supply control administrative processor is connected to, for generation of the 28V DC analogue quantity signal gathered required for described power supply control administrative processor and 115V/400Hz ac analog signal by stube cable.
According to also one side of the present invention, provide a kind of method of testing of power supply control administrative processor, comprise: produce the pumping signal in the validation test of described power supply control administrative processor, wherein, the mode of operation of one of at least equipment that is connected with described power supply control administrative processor on simulated aircraft of described pumping signal and the course of work; According to the output of described power supply control administrative processor, whether the function of testing described power supply control administrative processor is correct, and wherein, the output of described power supply control administrative processor produces according to described pumping signal.
Preferably, described pumping signal comprise following one of at least: the pumping signal of described engine controller simulating the work of the engine controller of described aircraft, output; Simulate the pumping signal of described DC power control protector of the work of the DC power control protector of described aircraft, output; Simulate the pumping signal flying control storage battery charger described in the work flying control storage battery charger of described aircraft, output; Simulate the pumping signal of described external power source watch-dog of the work of the external power source watch-dog of described aircraft, output; Simulate the pumping signal of described AC power control enclosure of the work of the AC power control enclosure of described aircraft, output; Simulate the pumping signal of the work of the AC distribution box control enclosure of described aircraft, the described AC distribution box of output; Simulate the pumping signal of the work of the DC power distribution unit (PDU) control enclosure of described aircraft, the described DC power distribution unit (PDU) of output; Simulate the pumping signal of described accumulator of the work of the accumulator of described aircraft, output; Simulate the pumping signal of described Landing Gear System of the work of the Landing Gear System of described aircraft, output.
Preferably, described method also comprises: the break-make controlling the output signal of described power supply control administrative processor by arranging multiple measured hole.
Pass through the present invention, adopt test signal generation device, for generation of the pumping signal in the validation test of described power supply control administrative processor, wherein, the mode of operation of one of at least equipment that is connected with described power supply control administrative processor on simulated aircraft of described pumping signal and the course of work; Test processes device, according to the output of described power supply control administrative processor, whether the function of testing described power supply control administrative processor is correct, wherein, the output of described power supply control administrative processor produces according to described pumping signal, solve in correlation technique the problem of testing power supply control administrative processor and wasting time and energy, thus there is saving cost, time saving effect.
Accompanying drawing explanation
Accompanying drawing described herein is used to provide a further understanding of the present invention, and form a application's part, schematic description and description of the present invention, for explaining the present invention, does not form inappropriate limitation of the present invention.In the accompanying drawings:
Fig. 1 is the structural representation of the test macro of power supply control administrative processor according to the embodiment of the present invention;
Fig. 2 is the process flow diagram of the APS APS condition processing method according to the embodiment of the present invention;
Fig. 3 is the structural representation of the test macro of power supply control administrative processor according to the preferred embodiment of the invention.
Embodiment
Hereinafter also describe the present invention in detail with reference to accompanying drawing in conjunction with the embodiments.It should be noted that, when not conflicting, the embodiment in the application and the feature in embodiment can combine mutually.
As used below, term " module " can realize the software of predetermined function and/or the combination of hardware.Although the device described by following examples preferably realizes with software, hardware, or the realization of the combination of software and hardware also may and conceived.
Provide a kind of test macro of power supply control administrative processor in the present embodiment, Fig. 1 is the structural representation of the test macro of power supply control administrative processor according to the embodiment of the present invention, and as shown in Figure 1, this system comprises:
Test signal generation device 12, for generation of the pumping signal in this power supply control administrative processor validation test, wherein, the mode of operation of one of at least equipment that pumping signal is connected with this power supply control administrative processor on simulated aircraft and the course of work;
Test processes device 14, according to the output of this power supply control administrative processor, whether the function of testing this power supply control administrative processor is correct, and wherein, the output of this power supply control administrative processor produces according to this pumping signal.
By said structure, solve in correlation technique the problem of testing power supply control administrative processor and wasting time and energy, thus there is saving cost, time saving effect.
In one embodiment, described test signal generation device 12 can also comprise following one of at least: engine controller emulation module, for simulating the work of the engine controller of described aircraft, export the pumping signal of described engine controller to described power supply control administrative processor; DC power control protector emulation module, for simulating the work of the DC power control protector of described aircraft, exports the pumping signal of described DC power control protector to described power supply control administrative processor; Flying control storage battery charger emulation module, for simulating the work flying control storage battery charger of described aircraft, flying the pumping signal of control storage battery charger described in output to described power supply control administrative processor; External power source watch-dog emulation module, for simulating the work of the external power source watch-dog of described aircraft, exports the pumping signal of described external power source watch-dog to described power supply control administrative processor; AC power control enclosure emulation module, for simulating the work of the AC power control enclosure of described aircraft, exports the pumping signal of described AC power control enclosure to described power supply control administrative processor; AC distribution box emulation module, for simulating the work of the AC distribution box control enclosure of described aircraft, exports the pumping signal of described AC distribution box to described power supply control administrative processor; DC power distribution unit (PDU) emulation module, for simulating the work of the DC power distribution unit (PDU) control enclosure of described aircraft, exports the pumping signal of described DC power distribution unit (PDU) to described power supply control administrative processor; Storage Battery Simulation module, for simulating the work of the accumulator of described aircraft, exports the pumping signal of described accumulator to described power supply control administrative processor; Landing Gear System emulation module, for simulating the work of the Landing Gear System of described aircraft, exports the pumping signal of described Landing Gear System to described power supply control administrative processor.
In another embodiment, described system can also comprise signal process box, described signal process box for receive and nurse one's health described power supply control administrative processor input analog signals, described analog signals is converted into multiple digital signal, and described digital signal is input to described test processes device, use for described test processes device to test.
In yet another embodiment, described system also comprises signal measurement panel, and described measurement panel is provided with multiple measured hole, for controlling the break-make of the cable between described test macro and described power supply control administrative processor.
In a preferred embodiment, described system also comprise industrial control computer and following one of at least: combined type cabinet-type air conditioner, direct supply, alternating current-direct current signal source, display, power control switch, signal measurement panel and stube cable, wherein, described test signal generation device and described test processes device are arranged in described industrial control computer.Wherein, described direct supply, is connected to the power input interface of described power supply control administrative processor by stube cable, for simulating the 28V direct supply needed for the work of described power supply control administrative processor; Described alternating current-direct current signal source, signal input interface corresponding to described power supply control administrative processor is connected to, for generation of the 28V DC analogue quantity signal gathered required for described power supply control administrative processor and 115V/400Hz ac analog signal by stube cable.
The embodiment of the present invention additionally provides a kind of method of testing of power supply control administrative processor, and Fig. 2 is the process flow diagram of the method for testing of power supply control administrative processor according to the embodiment of the present invention, and the method comprises the following steps:
Step S202, produces the pumping signal in the validation test of described power supply control administrative processor, wherein, and the mode of operation of one of at least equipment that described pumping signal is connected with described power supply control administrative processor on simulated aircraft and the course of work;
Step S204, according to the output of described power supply control administrative processor, whether the function of testing described power supply control administrative processor is correct, and wherein, the output of described power supply control administrative processor produces according to described pumping signal.
Preferably, described pumping signal comprise following one of at least: the pumping signal of described engine controller simulating the work of the engine controller of described aircraft, output; Simulate the pumping signal of described DC power control protector of the work of the DC power control protector of described aircraft, output; Simulate the pumping signal flying control storage battery charger described in the work flying control storage battery charger of described aircraft, output; Simulate the pumping signal of described external power source watch-dog of the work of the external power source watch-dog of described aircraft, output; Simulate the pumping signal of described AC power control enclosure of the work of the AC power control enclosure of described aircraft, output; Simulate the pumping signal of the work of the AC distribution box control enclosure of described aircraft, the described AC distribution box of output; Simulate the pumping signal of the work of the DC power distribution unit (PDU) control enclosure of described aircraft, the described DC power distribution unit (PDU) of output; Simulate the pumping signal of described accumulator of the work of the accumulator of described aircraft, output; Simulate the pumping signal of described Landing Gear System of the work of the Landing Gear System of described aircraft, output.
Below in conjunction with preferred embodiment, technical scheme provided by the invention is described in detail.
The object of the invention is the test macro and the method for testing thereof that design a kind of power supply control administrative processor, the various mode of operation of the airborne equipment that simulation and power supply control administrative processor are cross-linked and the course of work, to test the functional performance index of power supply control administrative processor, thus power supply control administrative processor is evaluated.
Technical scheme provided by the invention is as follows: a kind of test macro of power supply control administrative processor, comprise combined type rack, direct supply, alternating current-direct current signal source, industrial control computer, display, signal process box, power control switch, signal measurement panel and stube cable, the mode of operation of other airborne equipments that industrial control computer build-in test software simulation and power supply control administrative processor are cross-linked and the course of work, produce the pumping signal in the validation test of power supply control administrative processor and information.
Direct supply, alternating current-direct current signal source, industrial control computer, display, signal process box, power control switch, signal measurement panel are carried out combination and install by combined type rack, are connected with power supply control administrative processor by stube cable.
The 28V direct supply needed for the work of power supply control administrative processor on direct supply simulated aircraft, is connected to the power input interface of power supply control administrative processor by stube cable.
Alternating current-direct current signal source produces the 28V DC analogue quantity signal and 115V/400Hz ac analog signal that on aircraft, power supply control administrative processor gathers, and is connected to signal input interface corresponding to power supply control administrative processor by stube cable.
Industrial control computer build-in test software mainly comprises engine controller emulation module, DC power control protector emulation module, flies control storage battery charger emulation module, external power source watch-dog emulation module, AC power control enclosure emulation module, AC distribution box emulation module, DC power distribution unit (PDU) emulation module, Storage Battery Simulation module, electromechanical simulation module, Landing Gear System emulation module, accident record device emulation module; Simulation produces relative configuration and the malfunction of electric power system under aircraft various state, and receives the data message of relevant electric power system state that power supply control administrative processor sends and fault, carries out display translation.
Each emulator in display display industrial control computer build-in test software arranges interface and output display interface.
The analog signals that signal process box conditioning power supply control administrative processor exports, and output to industrial control computer.
Power control switch mainly comprises master switch, DC power supply switch, signal source switch and computer switch, master switch controls the power-on and power-off of whole test macro, DC power supply switch controls the power-on and power-off of direct supply, the power-on and power-off of signal source switch control rule alternating current-direct current signal source, computer switch controls the power-on and power-off of industrial control computer.
The break-make of signal measurement panel control linkage cable, has measured hole simultaneously on measurement panel.
Lower surface analysis shows principle in fact:
On functional realiey, all devices of the present invention is by unit equipment cabinet combination integrative installation technology, power control switch realizes the switch control rule of each equipment, direct supply provides the working power of power supply control administrative processor, the 28V DC analogue quantity signal that alternating current-direct current signal source provides power supply control administrative processor to gather and 115V/400Hz ac analog signal, the engine controller that industrial control computer simulation is crosslinked with power supply control administrative processor, DC power control protector, fly control storage battery charger, external power source watch-dog, AC power control enclosure, AC distribution box, DC power distribution unit (PDU), accumulator, the various mode of operation of the airborne equipment such as Mechatronic Systems and Landing Gear System and the course of work, be connected with power supply control administrative processor by stube cable, by display interfaces, the various types of signal in the power supply control administrative processor course of work is set, send power supply control administrative processor to.
After the work of power supply control administrative processor, resolve according to the various signals that test macro is arranged, send to Mechano-Electronic System Simulation device in industrial control computer and accident record equipment simulator by resolving rear information, display shows corresponding information;
Synchronous signal measures panel can the break-make of control linkage cable easily, and under cable connected state, measured each road signal of cable by measured hole.
In above-mentioned process of the test, industrial control computer build-in test software carries out logic according to the current setting state of display interface and resolves, and each airborne equipment crosslinked with power supply control administrative processor is emulated, control each road signaling interface simultaneously and output to power supply control administrative processor;
Signal process box gathers the analog signals that power supply control administrative processor sends, industrial control computer is sent to after conditioning, the analog signals through conditioning of bus signals and signal process box transmission that industrial control computer gathers the transmission of power supply control administrative processor carries out overall treatment, and shown by display, complete the validation test of power supply control administrative processor;
In test process, signal measurement panel can the break-make of control linkage cable easily, and under cable connected state, measured each road signal of cable by measured hole.Satisfactory reporting the result can be generated as required simultaneously.
Fig. 3 is a kind of according to the preferred embodiment of the invention test system structure schematic diagram of power supply control administrative processor, as shown in Figure 3, this system comprises combined type rack 1, direct supply 2, alternating current-direct current signal source 3, industrial control computer 4, display 5, signal process box 6, power control switch 7, signal measurement panel 8 and stube cable 9, whole test macro cooperating, the course of work of the airborne equipment that simulation and power supply control administrative processor are cross-linked, produce the pumping signal in the validation test of power supply control administrative processor and gather the output signal of power supply control administrative processor.
Direct supply 2, alternating current-direct current signal source 3, industrial control computer 4, display 5, signal process box 6, power control switch 7, signal measurement panel 8 are carried out combination and install by combined type rack 1, are connected with power supply control administrative processor by stube cable 9.
The 28V direct supply needed for the work of power supply control administrative processor on direct supply 2 simulated aircraft, is connected to the power input interface of power supply control administrative processor by stube cable 9.
Alternating current-direct current signal source 3 produces the 28V DC analogue quantity signal and 115V/400Hz ac analog signal that on aircraft, power supply control administrative processor gathers, and is connected to signal input interface corresponding to power supply control administrative processor by stube cable 9.
Industrial control computer 4 includes testing software, mainly comprises engine controller emulation module, DC power control protector emulation module, flies control storage battery charger emulation module, external power source watch-dog emulation module, AC power control enclosure emulation module, AC distribution box emulation module, DC power distribution unit (PDU) emulation module, Storage Battery Simulation module, electromechanical simulation module, Landing Gear System emulation module, accident record device emulation module; Simulation produces relative configuration and the malfunction of electric power system under aircraft various state, and receives the data message of relevant electric power system state that power supply control administrative processor sends and fault.
Each emulator that display 5 shows industrial control computer 4 build-in test software arranges interface and output display interface.
Signal process box 6 nurses one's health the analog signals that power supply control administrative processor exports, and outputs to industrial control computer 4.Power control switch 7 mainly comprises master switch, DC power supply switch, signal source switch and computer switch, master switch controls the power-on and power-off of whole test macro, DC power supply switch controls the power-on and power-off of direct supply 2, the power-on and power-off of signal source switch control rule alternating current-direct current signal source [3], computer switch controls the power-on and power-off of industrial control computer 4.
The break-make of signal measurement panel 8 control linkage cable 9, has measured hole simultaneously on measurement panel.
The preferred embodiment of the present invention additionally provides a kind of method of testing of power supply control administrative processor, and the method comprises following detailed step:
(1) system connect, before system does not work on power by all cables by test macro and power supply control administrative processor exact connect ion;
(2) system electrification and configuration, master switch in the gauge tap that switches on power successively [7], DC power supply switch, signal source switch and computer switch, output voltage and the protective current of direct supply [2] are set, run the testing software of industrial control computer [4];
(3) engine controller emulation module, DC power control protector emulation module in testing software are set in the upper correspondence of display [5] successively according to test assignment, fly control storage battery charger emulation module, external power source watch-dog emulation module, AC power control enclosure emulation module, AC distribution box emulation module, DC power distribution unit (PDU) emulation module, Storage Battery Simulation module, electromechanical simulation module, Landing Gear System emulation module, accident record device emulation module, power supply control administrative processor is tested accordingly;
(4) step (3) is repeated, until complete the test job of current task defined;
(5) record is carried out to test result, save as WORD form, then utilize the printing function of WORD, carry out printout, generate report, complete a complete validation test.
The present invention has following beneficial effect:
(1) the present invention is a kind of test macro of power supply control administrative processor, simulate the operational process of electric power system configuration information and power supply control administrative processor, to solved logic, the interface features of power supply control administrative processor, and the correctness of output signal is verified, function is complete.
(2) rational in infrastructure compact, reliable operation, system emulation degree are high, Test coverage is comprehensive, test accuracy is high.
(3) excellent extensibility and portability, each equipment adopts module-integrated design, and cabinet combination is installed, and is with good expansibility and portability.
(4) man-machine interface is friendly, convenient operation.
(5) shorten the cycle of system integration test, reduce the difficulty of system integration test.
Along with the development of technology and market, the test macro of power supply control administrative processor will have good promotional value.
Obviously, those skilled in the art should be understood that, above-mentioned of the present invention each module or each step can realize with general calculation element, they can concentrate on single calculation element, or be distributed on network that multiple calculation element forms, alternatively, they can realize with the executable program code of calculation element, thus, they can be stored and be performed by calculation element in the storage device, and in some cases, step shown or described by can performing with the order be different from herein, or they are made into each integrated circuit modules respectively, or the multiple module in them or step are made into single integrated circuit module to realize.Like this, the present invention is not restricted to any specific hardware and software combination.
The foregoing is only the preferred embodiments of the present invention, be not limited to the present invention, for a person skilled in the art, the present invention can have various modifications and variations.Within the spirit and principles in the present invention all, any amendment done, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (10)
1. a test macro for power supply control administrative processor, is characterized in that, comprises
Test signal generation device, for generation of the pumping signal in the validation test of described power supply control administrative processor, wherein, the mode of operation of one of at least equipment that is connected with described power supply control administrative processor on simulated aircraft of described pumping signal and the course of work;
Test processes device, according to the output of described power supply control administrative processor, whether the function of testing described power supply control administrative processor is correct, and wherein, the output of described power supply control administrative processor produces according to described pumping signal.
2. system according to claim 1, is characterized in that, described test signal generation device comprise following one of at least:
Engine controller emulation module, for simulating the work of the engine controller of described aircraft, exports the pumping signal of described engine controller to described power supply control administrative processor;
DC power control protector emulation module, for simulating the work of the DC power control protector of described aircraft, exports the pumping signal of described DC power control protector to described power supply control administrative processor;
Flying control storage battery charger emulation module, for simulating the work flying control storage battery charger of described aircraft, flying the pumping signal of control storage battery charger described in output to described power supply control administrative processor;
External power source watch-dog emulation module, for simulating the work of the external power source watch-dog of described aircraft, exports the pumping signal of described external power source watch-dog to described power supply control administrative processor;
AC power control enclosure emulation module, for simulating the work of the AC power control enclosure of described aircraft, exports the pumping signal of described AC power control enclosure to described power supply control administrative processor;
AC distribution box emulation module, for simulating the work of the AC distribution box control enclosure of described aircraft, exports the pumping signal of described AC distribution box to described power supply control administrative processor;
DC power distribution unit (PDU) emulation module, for simulating the work of the DC power distribution unit (PDU) control enclosure of described aircraft, exports the pumping signal of described DC power distribution unit (PDU) to described power supply control administrative processor;
Storage Battery Simulation module, for simulating the work of the accumulator of described aircraft, exports the pumping signal of described accumulator to described power supply control administrative processor;
Landing Gear System emulation module, for simulating the work of the Landing Gear System of described aircraft, exports the pumping signal of described Landing Gear System to described power supply control administrative processor.
3. according to right system according to claim 2, it is characterized in that, described system also comprises signal process box, described signal process box for receive and nurse one's health described power supply control administrative processor input analog signals, described analog signals is converted into multiple digital signal, and described digital signal is input to described test processes device, use for described test processes device to test.
4. according to right system according to claim 2, it is characterized in that, described system also comprises signal measurement panel, and described measurement panel is provided with multiple measured hole, for controlling the break-make of the cable between described test macro and described power supply control administrative processor.
5. system according to any one of claim 1 to 3, it is characterized in that, described system also comprise industrial control computer and following one of at least: combined type cabinet-type air conditioner, direct supply, alternating current-direct current signal source, display, power control switch, signal measurement panel and stube cable, wherein, described test signal generation device and described test processes device are arranged in described industrial control computer.
6. system according to claim 4, is characterized in that, described direct supply, is connected to the power input interface of described power supply control administrative processor by stube cable, for simulating the 28V direct supply needed for the work of described power supply control administrative processor.
7. system according to claim 4, it is characterized in that, described alternating current-direct current signal source, signal input interface corresponding to described power supply control administrative processor is connected to, for generation of the 28V DC analogue quantity signal gathered required for described power supply control administrative processor and 115V/400Hz ac analog signal by stube cable.
8. a method of testing for power supply control administrative processor, is characterized in that, comprising:
Produce the pumping signal in the validation test of described power supply control administrative processor, wherein, the mode of operation of one of at least equipment that described pumping signal is connected with described power supply control administrative processor on simulated aircraft and the course of work;
According to the output of described power supply control administrative processor, whether the function of testing described power supply control administrative processor is correct, and wherein, the output of described power supply control administrative processor produces according to described pumping signal.
9. method according to claim 8, is characterized in that, described pumping signal comprise following one of at least:
Simulate the pumping signal of described engine controller of the work of the engine controller of described aircraft, output;
Simulate the pumping signal of described DC power control protector of the work of the DC power control protector of described aircraft, output;
Simulate the pumping signal flying control storage battery charger described in the work flying control storage battery charger of described aircraft, output;
Simulate the pumping signal of described external power source watch-dog of the work of the external power source watch-dog of described aircraft, output;
Simulate the pumping signal of described AC power control enclosure of the work of the AC power control enclosure of described aircraft, output;
Simulate the pumping signal of the work of the AC distribution box control enclosure of described aircraft, the described AC distribution box of output;
Simulate the pumping signal of the work of the DC power distribution unit (PDU) control enclosure of described aircraft, the described DC power distribution unit (PDU) of output;
Simulate the pumping signal of described accumulator of the work of the accumulator of described aircraft, output;
Simulate the pumping signal of described Landing Gear System of the work of the Landing Gear System of described aircraft, output.
10. method according to claim 8 or claim 9, it is characterized in that, described method also comprises: the break-make controlling the output signal of described power supply control administrative processor by arranging multiple measured hole.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510493196.7A CN105116877A (en) | 2015-08-11 | 2015-08-11 | Testing system of power supply control management processor and method |
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| CN201510493196.7A CN105116877A (en) | 2015-08-11 | 2015-08-11 | Testing system of power supply control management processor and method |
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| CN106093676A (en) * | 2016-06-07 | 2016-11-09 | 中国南方航空工业(集团)有限公司 | Outfield fault detection and diagnosis equipment |
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Application publication date: 20151202 |