CN102062833B - Programmable airplane power supply characteristic comprehensive test apparatus - Google Patents
Programmable airplane power supply characteristic comprehensive test apparatus Download PDFInfo
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- CN102062833B CN102062833B CN201010528995.0A CN201010528995A CN102062833B CN 102062833 B CN102062833 B CN 102062833B CN 201010528995 A CN201010528995 A CN 201010528995A CN 102062833 B CN102062833 B CN 102062833B
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Abstract
The invention relates to the field of aviation and provides a programmable automatic tester which can simulate various surges probably produced in the actual operational process of an airplane power supply system and can carry out comprehensive reliability testing on various airplane-mounted electronic devices in strict accordance with parameters and sequences specified in the standards of 'Airplane Power Supply Characteristics', namely GJB181-1986 and GJB181A-2003. The tester comprises an EMI (electro-magnetic interference) circuit, a PFC (power factor correction) circuit, a 28VDC (voltage-to-digital converter) circuit, an 80VDC circuit, an 8VDC circuit, a +600VDC circuit, a manual mode control keyboard, a program control mode control keyboard, a microprocessor control circuit, an LCD display screen and an output control and switching circuit; and the tester has two functions of manual control and program control. The information in the programming and testing process can be displayed on the LCD display screen, and the tester has the advantages that test types are complete, automation of the test is fully, operation is simple, anti-jamming capability is strong and reliability is high.
Description
Technical field
The present invention relates to aerospace field, specifically refer to a kind of equipment being used for various air environment being carried out to surge simulation test.
Background technology
Aviation observation and control technology is one of developing important foundation technology of aeronautical technology, aviation observation and control technology has service object and technical development field widely,, strength test pneumatic from aircraft, quiet, the dynamic test of the various parameter of engine, to the experimental test etc. of various airborne equipment, observation and control technology all has very important effect: it is directly connected to performance, the reliability and security of product.Can find out from the overall process of aeronautical product development: from basic technology beforehand research, Project R&D, production definition of taking a flight test, all need to provide first and then reliable experimental test means, whether this experimental test advanced technology directly affects advance and the reliability of aeronautical product, plays key effect to the lead time of product simultaneously.Increasing along with the kind of airborne electronic equipment, quantity and function, the reliability of air environment, security more and more receive the concern of people, are therefore again the most important thing of aviation observation and control technology to the reliability testing of electronic equipment various on aircraft.
The important indicator weighing various aircraft airborne electronic equipment performance especially reliability sees whether these air environments can bear various surges that aircraft electrical power supply system produces in operational process as the voltage fluctuation, current fluctuation etc. of moment.It is whole that aircraft electrical power supply system contains from power supply to consumer input end, is usually divided into power-supply system and distribution system two parts.Power-supply system is the part that power supply arrives between power bars, and distribution system is the part from power bars to consumer input end.Aircraft power system is made up of AC power supply system and DC power system, and AC power supply system provides 115/200V to AC network on machine, 400Hz three-phase alternating current.DC power system provides 28V low-voltage DC to direct current networking on machine.Aircraft electrical supply parameters test is exactly generate the various abnormal electrical power supply situations that produce in actual moving process of aircraft electrical power supply system by testing apparatus simulation to carry out various short circuit, open circuit, overvoltage, the surge test such as under-voltage to air environment, be without prejudice to verify in the surge whether these air environments can produce at aircraft electrical power supply system and can normally work.The kind, method, order etc. of aircraft electrical supply parameters test have been included in national military standard GJB181-1986 and GJB181A-2003 " aircraft electrical supply parameters ".
In the prior art, most of aircraft electrical supply parameters testing apparatus is all manual operation or needs to rely on computing machine realization programming, control etc.Manual test functions of the equipments are single, complex operation, and computer-controlled testing apparatus volume is comparatively large, be not easy to carry, and equipment interface many, couple together complexity, not easy to operate.
Present invention provides a can issuable various surge in simulated aircraft electric power system actual moving process, the Automatic Test Equipment able to programme of overall reliability test can be carried out to various aircraft airborne electronic equipment in strict accordance with the parameter specified in GJB181-1986 and GJB181A-2003 " aircraft electrical supply parameters " standard and order, have test approaches complete, test full-automation, simple to operate, strong interference immunity, high reliability.It comprises: EMI circuit, pfc circuit, 28VDC circuit, 80VDC circuit, 8VDC circuit ,+600VDC circuit, manual mode supervisory keyboard, Program Mode supervisory keyboard, microprocessor control circuit, LCD display, output control and commutation circuit.Wherein, EMI circuit adopts topological structure, by common mode interference filter inductance L
cMwith differential mode interference filter inductance L
dMseries connection, can effectively suppress the common and different mode in circuit to disturb.And 28VDC circuit, 80VDC circuit, 8VDC circuit and+600VDC circuit adopt identical circuit topological structure, output circuit and internal circuit realize isolating by transformer, thus substantially increase the antijamming capability of whole test macro.-600V pulse is realized, also without the need to changing external cabling by the polarity switching+600V pulse in inside.All functions exporting control and commutation circuit control are achieved by relay and MOSFET element.Device panel is made up of LCD display, power light, power switch, 28V voltage-regulation button, equipment output end, Program Mode supervisory keyboard, manual mode supervisory keyboard and start button, is well integrated with the functions such as output, input, programming, adjustment, display.Non-follow control keyboard can control to export single 80V, 8V, 0V ,+600V and-600V pulse in a manual mode.Program control supervisory keyboard realizes the function such as programming, program storage by microprocessor control circuit, can the shock pulse of the various needs of automatic output such as pulse kind, number, interval sequentially, between pulse that specify of opertaing device follow procedure.LCD display can the information such as display translation voltage, pulse pattern, number.
Summary of the invention
A kind of aircraft electrical supply parameters integral test system able to programme, it comprises: EMI circuit, pfc circuit, 28VDC circuit, 80VDC circuit, 8VDC circuit ,+600VDC circuit, Non-follow control keyboard, Program Mode supervisory keyboard, microprocessor control circuit, LCD display, output control and commutation circuit.It is characterized in that: EMI circuit is connected with pfc circuit, pfc circuit is connected with 28VDC circuit, 80VDC circuit, 8VDC circuit ,+600VDC circuit respectively, 28VDC circuit, 80VDC circuit, 8VDC circuit ,+600VDC circuit jointly control with output and commutation circuit is connected, export and to control and commutation circuit, Non-follow control keyboard, Program Mode supervisory keyboard, LCD display are connected with microprocessor control circuit respectively, LCD display to control and commutation circuit is put on device panel by same with exporting.Wherein, EMI circuit adopts topological structure, by common mode interference filter inductance L
cMwith differential mode interference filter inductance L
dMseries connection, can effectively suppress the common and different mode in circuit to disturb; Pfc circuit is made up of active power factor controlling chip, inductance L and power MOSFET device Q; 28VDC circuit, 80VDC circuit, 8VDC circuit and+600VDC circuit adopt identical circuit topological structure, and output circuit and internal circuit realize isolating by transformer, thus substantially increase the antijamming capability of whole test macro;-600V pulse is realized, without the need to changing external cabling by the polarity switching+600V pulse in inside.Table 1 lists output type of the present invention and parameter.
Table 1
All output controls and commutation circuit control by exporting, and wherein output switching is realized by relay and MOSFET element.And device panel is made up of LCD display, power light, power switch, 28V voltage-regulation button, equipment output end, Program Mode supervisory keyboard, manual mode supervisory keyboard and start button.Wherein, Non-follow control keyboard can control to export single 80V, 8V, 0V ,+600V and-600V pulse in a manual mode; Program control supervisory keyboard realizes the function such as programming, program storage by microprocessor control circuit, can control the shock pulse of the various needs of automatic output such as pulse kind that tester follow procedure specify, number, interval sequentially, between pulse; LCD display can the information such as display translation voltage, pulse pattern, number.
Accompanying drawing explanation
Fig. 1 is the circuit theory diagrams of aircraft electrical supply parameters testing apparatus
Fig. 2 is the EMI circuit diagram of aircraft electrical supply parameters testing apparatus
Fig. 3 is the pfc circuit figure of aircraft electrical supply parameters testing apparatus
Fig. 4 is the half-bridge circuit figure of aircraft electrical supply parameters testing apparatus
Fig. 5 is the workflow diagram of aircraft electrical supply parameters testing apparatus
Fig. 6 is the monnolithic case figure of aircraft electrical supply parameters testing apparatus
In Fig. 1,1:EMI circuit; 2:PFC circuit; 3:28VDC circuit; 4:80VDC circuit; 5:8VDC circuit; 6:+600VDC circuit; 7: Non-follow control keyboard; 8: microprocessor control circuit; 9: Program Mode supervisory keyboard; 10:LCD display screen; 11: export and control and commutation circuit.
In Fig. 6,1-1: power light; 1-2: power switch; 1-3:28V voltage-regulation knob; 1-4: lead-out terminal; 1-5: start button; 1-6: manual mode supervisory keyboard; 1-7: Program Mode supervisory keyboard; 1-8:LCD display screen; 1-9: equipment cabinets.
Embodiment
Just by reference to the accompanying drawings following description is done to the specific embodiment of the present invention below:
See Fig. 1, the present invention is made up of EMI circuit 1, pfc circuit 2,28VDC circuit 3,80VDC circuit 4,8VDC circuit 5 ,+600VDC circuit 6, Non-follow control keyboard 7, microprocessor control circuit 8, Program Mode supervisory keyboard 9, LCD display 10, output control and commutation circuit 11.Described EMI circuit 1 is connected with power supply.
See Fig. 2, described EMI circuit adopts topological structure, by common mode interference filter inductance L
cMwith differential mode interference filter inductance L
dMseries connection, effectively inhibit the common and different mode in circuit to disturb.
See Fig. 3, described pfc circuit is made up of active power factor controlling chip, inductance L and power MOSFET device Q.
See Fig. 4, described 28VDC circuit, 80VDC circuit, 8VDC circuit and+600VDC circuit adopt identical circuit topological structure, and output circuit and internal circuit realize isolating by transformer, thus substantially increase the antijamming capability of whole test macro.
See Fig. 6,1-9 is the outside cabinet of described equipment, and described Non-follow control keyboard 1-6, Program Mode supervisory keyboard 1-7, LCD display 1-8 are placed on device panel together with power light 1-1, power switch 1-2,28V voltage-regulation knob 1-3, the sub-1-4 of equipment output end and start button 1-5.Get back to Fig. 1, output controls and commutation circuit 11 is connected with the sub-1-4 of equipment output end described in Fig. 6, and the sub-1-4 of described equipment output end is connected with Devices to test.
See Fig. 6 and Fig. 1, workflow of the present invention is: the setting value (between+25VDC ~+31VDC) regulating 28V voltage-regulation knob 1-3 to need to user on device panel as shown in Figure 6, and voltage and current value is shown in LCD liquid crystal display screen 10 by microprocessor control circuit 8 as shown in fig. 1.In Program Mode supervisory keyboard 1-7 as shown in Figure 6, carry out programming operation, the program compiled can be processed by described microprocessor control circuit 8, and shows in LCD display 10.After programming terminates, press the start button 1-5 on device panel as shown in Figure 6, order can by exporting control and commutation circuit 11 carries out executable operations as shown in fig. 1.The information such as output voltage, pulse pattern, number also can control via described output simultaneously and commutation circuit 11 shows in described LCD display 10.The topological structure that adopts of EMI circuit 1 as shown in fig. 1 in test process is by common mode interference filter inductance L
cMwith differential mode interference filter inductance L
dM, can effectively suppress the common and different mode in circuit to disturb.Each power circuit adopts identical half-bridge circuit topology, and output circuit and internal circuit realize isolating by isolating transformer, also improve the antijamming capability of test macro.
Respectively operation of the present invention is described further for " program control " pattern and " manually " pattern below:
See Fig. 6 and Fig. 5, turn on the power switch 1-2 and open tester, power light 1-1 brightens.Regulate 28V voltage-regulation knob 1-3 can the numerical value of regulation output voltage, magnitude of voltage shows in LCD display 1-8.Devices to test is connected with tester by lead-out terminal 1-4.In Program Mode supervisory keyboard 1-7, such as, press " program control " key and enter Program Mode, press " programming starts " key and enter programming, user carries out output pulse protocol as required and writes.LCD display 1-8 can simultaneous display user programme.Such as LCD display 1-8 first row display translation pulse voltage amplitude V, secondary series display translation pulse number n, the 3rd row display translation recurrent interval Δ t during programming.Such as input: 80V, 5,30s (programming data of certain a line), represent and export 5 80V 50ms pulse continuously, between every two pulses, the time interval is 30s.Switch between row and row and such as controlled by down arrows button, switch between the column and the column and such as controlled by left and right arrow key.The data modification at cursor dwell place such as by+,-button increases and decreases.By " programming terminates " bond bundle programming in described Program Mode supervisory keyboard 1-7 after programming terminates.Devices to test or load are wired to of the present invention+,-lead-out terminal 1-4, start executive routine by start button 1-5.LCD display 1-8 can show the information such as the kind exporting pulse in implementation and number automatically.
After performing identical start and attended operation, manually supervisory keyboard 1-6 can carry out the single pulse test operation under manual mode, i.e. pulse shown in the exportable button of one-touch.The test of this single pulse can carry out reliability testing in strict accordance with the parameter of the normal output specified in GJB181-1986 and GJB181A-2003 " aircraft electrical supply parameters " standard, overvoltage, under-voltage, spike, power down test and order to various aircraft airborne electronic equipment.Such as, after Non-follow control keyboard 1-6 presses " manually " key, manual ringing can reach to export by microprocessor control circuit 8 as shown in fig. 1 and to control and commutation circuit 11 carries out blocked operation, press " 8V " key on Non-follow control keyboard 1-6, press start button 1-5 again, then export order to be controlled and commutation circuit 11 control 8V power circuit to export the+8V pulse of a 50ms from lead-out terminal 1-4 by described output, LCD display 1-8 can indication example as " having exported a 8V pulse ".
See table 1, in a manual mode manually supervisory keyboard 1-6 respectively by the exportable different surge of key control, principle of operation is identical.
Claims (10)
1. an equipment for simulated aircraft electric power system output characteristics test air environment, it comprises: EMI circuit, pfc circuit, 28VDC circuit, 80VDC circuit, 8VDC circuit ,+600VDC circuit, Non-follow control keyboard, Program Mode supervisory keyboard, microprocessor control circuit, LCD display, output control and commutation circuit; It is characterized in that: EMI circuit is connected with pfc circuit, pfc circuit is connected with 28VDC circuit, 80VDC circuit, 8VDC circuit ,+600VDC circuit respectively, 28VDC circuit, 80VDC circuit, 8VDC circuit ,+600VDC circuit jointly control with output and commutation circuit is connected, export and to control and commutation circuit, Non-follow control keyboard, Program Mode supervisory keyboard, LCD display are connected with microprocessor control circuit respectively, LCD display to control and commutation circuit is put on device panel by same with exporting.
2. equipment according to claim 1, is characterized in that: described EMI circuit adopts topological structure, by common mode interference filter inductance L
cMwith differential mode interference filter inductance L
dM, can effectively suppress the common and different mode in circuit to disturb.
3. equipment according to claim 1, is characterized in that: described pfc circuit is made up of active power factor controlling chip, inductance and power MOSFET device.
4. equipment according to claim 1, is characterized in that: described 28VDC circuit, 80VDC circuit, 8VDC circuit and+600VDC circuit adopt identical circuit topological structure, and output circuit and internal circuit realize isolating by isolating transformer.
5. equipment according to claim 1, is characterized in that: described+600VDC circuit changes-600VDC pulse into by inner switch polarity, without the need to changing external cabling.
6. equipment according to claim 1, is characterized in that: described 28VDC circuit, 80VDC circuit, 8VDC circuit ,+600VDC circuit, and it exports and controls and commutation circuit realization by exporting, and wherein output switching is realized by relay and MOSFET element.
7. equipment according to claim 1, is characterized in that: described device panel is made up of LCD display, power light, power switch, 28VDC voltage-regulation button, equipment output end, Program Mode supervisory keyboard, Non-follow control keyboard and start button.
8. equipment according to claim 7, is characterized in that: described Non-follow control keyboard controls to export single 80VDC, 8VDC, 0VDC ,+600VDC and-600VDC pulse in a manual mode.
9. equipment according to claim 7, it is characterized in that: described Program Mode supervisory keyboard realizes programming, program memory function by microprocessor control circuit, the pulse kind that opertaing device follow procedure specifies, number, interval sequentially, between pulse, export the shock pulse needed automatically.
10. equipment according to claim 7, is characterized in that: described LCD display display translation information of voltage, current information, pulse pattern information and number information.
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| CN201010528995.0A CN102062833B (en) | 2010-12-03 | 2010-12-03 | Programmable airplane power supply characteristic comprehensive test apparatus |
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| CN201010528995.0A CN102062833B (en) | 2010-12-03 | 2010-12-03 | Programmable airplane power supply characteristic comprehensive test apparatus |
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| CN102062833B true CN102062833B (en) | 2015-05-20 |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102508437B (en) * | 2011-09-14 | 2014-04-16 | 中国航空工业集团公司西安飞机设计研究所 | Multifunctional electromechanical system simulation method for simulation of airplane power supply control management system |
| CN103616560A (en) * | 2013-11-29 | 2014-03-05 | 中国航空无线电电子研究所 | Automatic power consumption parameter testing device and method applied to avionics device |
| CN104122421A (en) * | 2014-04-17 | 2014-10-29 | 航天长峰朝阳电源有限公司 | Single chip microcomputer based voltage impact test simulator |
| CN105991041A (en) * | 2015-02-27 | 2016-10-05 | 乐金电子研发中心(上海)有限公司 | Indirect matrix converter |
| CN108037469B (en) * | 2017-10-23 | 2020-06-16 | 上海科梁信息工程股份有限公司 | Airplane power supply characteristic testing system and method |
| CN109637893B (en) * | 2018-11-16 | 2020-04-03 | 北京遥感设备研究所 | Magnetic latching relay control system and magnetic latching relay system |
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