CN101082653B - Flying vehicle power functional failure simulation equipment and method thereof - Google Patents
Flying vehicle power functional failure simulation equipment and method thereof Download PDFInfo
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- CN101082653B CN101082653B CN2006100830879A CN200610083087A CN101082653B CN 101082653 B CN101082653 B CN 101082653B CN 2006100830879 A CN2006100830879 A CN 2006100830879A CN 200610083087 A CN200610083087 A CN 200610083087A CN 101082653 B CN101082653 B CN 101082653B
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Abstract
The invention discloses a checking equipment of at least one flight administration device, which comprises the following parts: first connecting device in the first power indicator line of the first flight administration device, first switch device, wherein the first power indicator line provides to represent the first power signal; the first switch device makes the signal of power indicator of the first flight administration device switched; the switch device is excited to change the signal on the power indicator line, which indicates the supplied power distortion or defect of aircraft and/or other parts; the response of flight administration device can be inactivated and/or activated to test through output signal on the display or aircraft device.
Description
Technical field
The present invention relates to a kind of equipment and method that is used for the power failure of aircraft is carried out emulation.Must display alarm in response to this power failure, the device of aircraft must the deactivation automatically or manually in response to alarm, and/or must forbid their activation automatically.
Background technology
In normal flight operating period, each two generator that are assigned to an aircraft engine produces the electric power that is used for aircraft control device and passenger's comfort device, and wherein this power supply (powersupply) for security reasons is redundant.Under the situation of a generator failure, another generator provides power for whole aerocraft system, but does not provide redundant.Display alarm and can turn-off some electronic installations in the aircraft.Especially, in case the generator failure of an engine, some system of aircraft must be automatically shut down and/or must be prevented and is switched on, as the entertainment systems of aircraft.Turn-off such system and guarantee flight safety,, and turn-off some system and reduced total electric power consumption because the generator failure of an engine has reduced available power.Especially, if redundant power supply is provided, then aircraft is designated as class 3 (category 3).Class 3 allows to march into the arena automatically (approach) and lands.If a generator failure just do not have redundant power to supply with, and correspondingly aircraft is downgraded to class 2.In case the further fault of a system of class 2 indication pilot aircraft, the pilot must the manual drive aircraft.If aircraft is designated as class 2, for security reasons do not allow the pilot to use robot pilot to land automatically, so the pilot must turn-off the robot pilot that is used to land and not allow its connection.All under the situation of fault, auxiliary power is supplied with as extendible outside turbine provides urgent power for aircraft at two generators, display alarm therebetween and can automatically shut down electronic installation nonessential during emergency operation.
Test period on the ground, must be to carrying out emulation by first generator of first driven by engine or by the fault of second generator of second driven by engine and the fault that activates two generators of urgent power supply, so as to verify some aerocraft system such as entertainment systems and kitchen in response to power failure by deactivation and/or can not be activated.The indication pilot in addition, alarm must be shown to the pilot, so that should and/or can not use some system such as robot pilot.
Summary of the invention
An object of the present invention is to provide a kind of method of emulation that is used for the easy operating of test purpose by the power failure of the generator of driven by engine.
Purpose of the present invention is used at least one flight management device and is connected to the method that its wiring verifies realizing by a kind of, and wherein said flight management device is suitable in response to the power condition of at least one power supply in the aircraft outputting alarm, the aircraft device is not worked (disable) and/or forbid the activation of described aircraft device.Described method comprises following steps.Switchgear is arranged in the power indicator line that is connected to the first flight management device, and wherein the power indicator line provides the signal of indicated power state of supply.Revise signal on the power indicator line by the energizing switch device.The response of checking flight management device.
The flight management device can be so-called Flight Management and Guidance Computer or so-called flight vectoring computer.At least one aircraft device of flight management device may command.Whether the aircraft device can be any device in the aircraft, need electric power irrelevant with this device, as aircraft entertainment systems, air-conditioning, kitchen or the like.Can use the adapter connector that switchgear is arranged in the power indicator line.The energizing switch device makes the signal change on the signal index line indicate, i.e. emulation is to the distortion or the fault of the power supply of another parts of flight management system or aircraft.The signal that the response of flight management device is for example exported on display by the flight management device or since the aircraft device by deactivation and/or can not be activated and verify.Selectively, can measure the signal that sends by the flight management device.The power indicator line is any device delivering power in aircraft not.On the contrary, the power indicator line transmits the signal of the power condition of indicated power supply.During operation, flight management system is provided with redundant power supply, does not therefore have the external information flight management system can't the detection power fault.The term wiring can comprise cable bundle (cable harness) and bus-bar (bus bar) and their part.
An advantage of the invention is when the test flight management devices and can continue test during to the reaction of power failure other parts of aircraft.Traditional method of testing switch-off power is supplied with the also response of test flight management devices.The test flight management devices that is used for of invention is only revised the signal on the power indicator line and power supply is not worked the method for power failure response, therefore can be independent of the flight management device to the test of the other parts of aircraft the test of power failure response is continued.
The signal of power indicator line can indicate redundant power to supply with from a plurality of power supplies.If aircraft comprises a plurality of power supplies, then the signal on the power indicator line can be indicated redundant power to supply with and be offered a plurality of flight management devices.If this redundant power is supplied with and offered a plurality of flight management devices, then aircraft is designated as class 3, allows to land automatically.
Signal on the power indicator line can be sent to a plurality of flight management devices.
The step of revising the signal on the power indicator line can comprise the step that interruption such as voltage breakdown (voltage breakdown), short circuit or the overload conditions of power supply are carried out emulation.The step that switchgear is set in the power indicator line can be included in a plurality of power indicator lines that a switchgear are set in a plurality of power indicator lines and/or are being connected to a plurality of flight management devices a plurality of switchgears are set, and the step of the signal on the modification power indicator line comprises the step that a plurality of signals on a plurality of power indicator lines are made amendment.Therefore, can come the correct wiring of aircraft cable bundle of testing complex and the operation of flight management device by the step of carrying out simple and mistake proofing.
Purpose of the present invention also can realize by being suitable at least one flight management device and being connected to the flight management device operation demonstration device that its wiring verifies, the flight management device in wherein using in response to power (supply) fault state outputting alarm, the aircraft device do not worked and/or forbid the activation of described aircraft device.Flight management device operation demonstration device comprises first coupling arrangement, is suitable for being arranged in the first power indicator line of the first flight management device, and the wherein said first power indicator line provides the signal of the situation of indication first power supply; And further comprising first switchgear, it in use connects, and makes signal with the first power indicator line of first flight management device coupling by switch.
As previously mentioned, the flight management device can be so-called Flight Management and Guidance Computer or flight vectoring computer.At least one aircraft device of flight management device may command.Whether the aircraft device can be any device in the aircraft, need electric power irrelevant with this device, as aircraft entertainment systems, air-conditioning, kitchen etc.Coupling arrangement can be the adapter connector, and it can be connected to the suitable connector of aircraft cable bundle and/or the connector of aircraft device.
The energizing switch device causes the signal change on the power indicator line, the power supply distortion or the fault of indication aircraft and/or its part.The response of flight management device can by the signal for example on display, exported by the flight management device or since the aircraft device by deactivation and/or can not be activated and verify.
Flight management device operation demonstration device can comprise the second switch device, and it in use connects, and makes signal with the second power indicator line of second flight management device coupling by switch.The second flight management device can be the flight management device redundancey of the first flight management device, as the condition precedent of aircraft operation as marching into the arena automatically and landing of class 3.
Flight management device operation demonstration device can further comprise: second coupling arrangement, it is suitable for being separately positioned in the third and fourth power indicator line of the first and second flight management devices, and wherein the third and fourth power indicator line provides the signal of the situation of indication second power supply; The 3rd switchgear, it in use connects, and makes signal with the 3rd power indicator line of first flight management device coupling by switch; With the 4th switchgear, it in use connects, and makes signal with the 4th power indicator line of second flight management device coupling by switch.But the situation that the signal indicated power of indication first and/or second power supply is supplied with is as normal running, low-voltage, power failure, overload conditions or the like.During normal running, second power supply provides power to the second flight management device, the redundant power that causes being used for the second flight management device is supplied with, and it is necessary wherein being used for the flight operation that this redundant power of the second flight management device supplies with class 3, as previously mentioned.
Utilize flight management device operation demonstration device, can verify the security system of the aircraft that the redundant power supply is provided.Two power supplies of aircraft and two flight management devices provide two redundant, cause the very complex control apparatus of the bus-bar that is used to be associated and the unusual cable bundle of complexity.Yet flight management device operation demonstration device of the present invention is suitable for verifying the cable bundle, its assembly in aircraft, the bus-bar that is associated of complexity like this and/or to the control of this bus-bar.
Flight management device operation demonstration device can further comprise: the 3rd coupling arrangement, it is suitable for being separately positioned between the 5th and the 6th power indicator line of the first and second flight management devices, and wherein the 5th and the 6th power indicator line provides the signal of the situation of indication the 3rd power supply; The 5th switchgear, it in use connects, and makes signal with the 5th power indicator line of first flight management device coupling by switch; With the 6th switchgear, it in use connects, and makes signal with the 6th power indicator line of second flight management device coupling by switch.First power supply can be first generator that is driven by first aircraft engine, second power supply can be second generator that is driven by second aircraft engine, and the 3rd power supply can be the urgent power supply that is used for aircraft, as battery or extendible auxiliary turbines, it all is activated respectively during fault and expands at two generators.The term power supply also can comprise bus-bar and part thereof.
When first and second power supplies all during the emergent power fault, the flight management device can make aircraft comfort system such as air-conditioning, aircraft entertainment systems etc. not work, to save the power of battery of aircraft battery.Necessary in addition display alarm, as previously mentioned.
It will be understood by those skilled in the art that the cable bundle of supporting so complicated redundancy and poor efficiency strategy and the bus-bar that is associated are complicated in design.Yet foregoing, flight management device operation demonstration device can be verified so complicated cable bundle and power flow concentration bar.Flight management device operation demonstration device easy operating and therefore be not easy very much to occur operating mistake.
Equipment above-mentioned can be used for verifying flight management device, cable bundle and/or bus-bar.Flight management device operation demonstration device can be power failure simulator apparatus and any power failure situation that can be used to the simulated flight device.
Description of drawings
The present invention will obtain more detailed description with reference to the accompanying drawings, wherein
Fig. 1 is the synoptic diagram according to flight management device operation demonstration device of the present invention;
Fig. 2 is the exemplary schematic representation that the redundant power of two flight management devices in the aircraft is supplied with; And
Fig. 3 is the synoptic diagram of flight management device operation demonstration device of the present invention.
Embodiment
Fig. 1 illustrates the flight management device operation demonstration device 1 that comprises six switches 14,16,18,20,22,24.First coupling arrangement comprises that public connector 2 and female connectors 4, the second coupling arrangements comprise public connector 8 and female connectors 6, and the 3rd coupling arrangement comprises public connector 12 and female connectors 10.Flight management device operation demonstration device 1 further comprises the cable 26 that is used for connecting a plurality of connectors and switch.
With reference to figure 2.Aircraft comprises first generator 30, second generator 34 and urgent current source 32, and described urgent current source can be battery or extendible outside turbine.The first flight management device 36 and/or the second flight management device 38 display message and can selectively control air-conditioning 42 and entertainment systems 68 on display 40.Power flow concentration bar 46 will be from the power division of first generator 30, urgent power supply 32 and second generator 34 to the first flight management device 36 and/or the second flight management device 38, and this depends on the situation of power supply 30,32,34.Bus-bar control 48 is by the operating conditions of a plurality of line 50 sensings first generators 30, urgent power supply 32 and second generator 34.Bus-bar control 48 passes the signal to the first flight management device 36 and the second flight management device 38 respectively on a plurality of power indicator lines 52,54.
In normal flight operating period, first generator 30 provides power for the first flight management device 36, and second generator 34 provides power for the second flight management device 38 similarly.If detect power failure by bus-bar control 48 in first generator 30, then bus-bar is controlled 48 cut-off switch 56 and Closing Switch 58, makes second generator 34 provide power for the first flight management device 36 and the second flight management device 38.Yet, in this case, does not have redundant power to supply with and offer the first and second flight management devices 36,38, and aircraft is downgraded to class 2 from class 3.In class 2, it is unallowed landing automatically, and in addition, for security reason, must turn-off some device as entertainment systems 68.Correspondingly, flight management device 36,38 display alarm and can selectively turn-off entertainment systems 68 and/or forbid that entertainment systems 68 is activated on display 40.
In case detect different power failures, bus-bar control 46 can with foregoing switch 56,58 similar mode switches at second generator 34 and/or the urgent other switch 60,62,64,66 in the bus-bar of power supply 32, there not being providing power redundantly to the first and second flight management devices 36,38, and can be with the power failure type via a plurality of power indicator lines 52 with the signalisation first flight management device 36 with via crossing a plurality of power indicator lines 54 with the signalisation second flight management device 38.Yet Fig. 2 is just in order to explain the synoptic diagram of simplification of the present invention.The cable bundle of aircraft, bus-bar and bus-bar control is very complicated and is distributed in whole aircraft, therefore tests and verifies that correct allomeric function is complicated task.
Fig. 3 is the synoptic diagram of the flight management device operation demonstration device 1 when for example being connected to the first flight management device 36 and the second flight management device 38 via bus-bar, cable bundle or the like during test pattern.In order to be easy to explain that the bus-bar 46 and the cable bundle of aircraft do not have shown in Figure 3.As previously mentioned, flight management device operation demonstration device 1 comprises switch 14,20,16,22,18,24.Each switch comprises by main switchgear of alphabetical " a " indication and the inferior switchgear of being indicated by letter " b ", wherein in case encourage corresponding switch, two switchgear while switches.
For the emulation normal running, the closed first switchgear 14a, second switch device 20a, the 3rd switchgear 18a, the 4th switchgear 24a, the 5th switchgear 16a and the 6th switchgear 22a, so that signal Vnorm is applied to the first flight management device 36 and the second flight management device 38, be available thereby supply with from the above-mentioned redundant power of first power supply 30 and second power supply 34 with signalisation.To there be alarm information by 36,38 outputs of the first and second flight management devices.Vnorm normally ground voltage and indication does not have the power failure situation will be with signalisation.In case energizing switch 14, the first switchgear 14a disconnect and do not have signal Vnorm to be applied to the first power indicator line 74, and correspondingly with unusual power condition with signalisation to the first flight management device 36.The first flight management device 36 with display alarm, aircraft device such as entertainment systems 68 are not worked and/or will forbid the activation of aircraft device.In case excitation second switch 20, then second switch device 20a disconnects and does not have signal Vnorm to be applied on the second power indicator line 76, cause unusual power condition with signalisation to the second flight management device 38.The second flight management device 38 also with display alarm, the aircraft device do not worked and/or forbid the activation of aircraft device.
In case encourage the 3rd switch 18, the 3rd switchgear 18a disconnects and does not correspondingly have signal Vnorm to be applied to the 3rd power indicator line 82, and therefore unusual power condition to the first flight management device 36, causes the above-mentioned response of the first flight management device 36 with signalisation.If encourage the 4th switch 24, then the 4th switchgear 24a disconnect and do not have signal Vnorm on the 4th power indicator line 84 with signalisation to the second flight management device 38, cause the above-mentioned response of the second flight management device 38.
In case encourage the 5th switch 16, the five switchgear 16a disconnection and therefore do not have signal Vnorm to be applied to the 5th power indicator line 82,, cause the above-mentioned response of the first flight management device 36 to the unusual power condition of the first flight management device, 36 indications.In case encourage the 6th switch 24, then the 6th switchgear 22a disconnects, and does not correspondingly have signal Vnorm to be applied to the 6th power indicator line 80.Correspondingly, to the second flight management device 38, it will be as described above in response to described situation with signalisation for unusual power condition.
First switch 14 and second switch 20 emulation are by the mistake in first generator of first driven by engine.The 3rd switch 18 and 24 emulation of the 4th switch are by the mistake in second generator of second driven by engine.The urgent power supply of the 5th switch 16 and 22 emulation of the 6th switch such as battery or extendible auxiliary supply is activated.The first flight management device 36 and the second flight management device 38 have a plurality of power indicator lines 74,78,82 and 76,80,84 that are connected to it respectively.Yet, it will be understood by those skilled in the art that the signal of a plurality of erroneous condition of indication can transmit on single power indicator line.
In normal flight operation, first and second switches 14 and 20 function realize by first relay, and third and fourth switch 18 and 24 function are realized by second relay, and the function of the 5th and the 6th switch 16 and 22 is realized by the 3rd relay.If the power failure situation takes place during the normal flight situation, then will power up first, second and the 3rd relay so that with the power failure situation with signalisation to the first and second flight management devices 36,38.Therefore, if only will not apply Vnorm to the first flight management device 36 or the second flight management device 38 one of in the signal meter (SM) line 74,76,78,80,82,84, then message will be presented on the display 40, and aircraft device such as entertainment systems 68 will be turned off.Such somewhat complex design that test has a plurality of redundancies is complicated and error-prone task.
If be fed in the system of generating pusher side in the power rub-out signal of test period with emulation, then first, second will be powered with the 3rd relay, and because a plurality of redundancies, test will be impossible fully.
In addition, if first relay is by switch during test pattern, then the power failure signal is sent to the first and second flight management devices 36 and 38 via the first power indicator line 74 and the second power indicator line 76. Flight management system 36,38 the two all with display alarm and the aircraft device is not worked.Because redundant layout, because the second power indicator line 76 can not be applied to Vnorm the second flight management device 38, the mistake of the wrong and/or first flight management device 6 on the first power indicator line 74 can not be detected, and therefore the second flight management device 38 will be on display 40 display alarm and/or with entertainment systems 68 deactivations.Vnorm is ground voltage normally.If the first power indicator line 74 cursorily is connected to ground, then the first power indicator line 74 can not be with the power failure situation with signalisation to the first flight management device 36.
Do not having under the situation of apparatus and method of the present invention, multilevel redundancy of the present invention is only by by line continuous review and the signal of indicated power fault state is applied directly to the first and second flight management devices 36,38 verifies.
The flight management device operation demonstration device (1) of invention is easy to be connected to bus-bar and/or the cable bundle in the commercial large-scale cabin aircraft, because it only comprises several connectors.In addition, the complicated power division that comprises a plurality of redundancies can utilize wieldy flight management device validator to test.Because the flight management device operation demonstration device (1) of invention only comprises six switches, so be not easy to take place operating mistake.At above-mentioned test period, there is not power supply by deactivation, therefore do not interrupt other test to aircraft.
Claims (10)
1. one kind is used at least one flight management device (36,38) and be connected to the method that its wiring is verified, wherein said flight management device (36,38) be suitable in response at least one power supply (30 in the aircraft, 32,34) power condition and outputting alarm, make aircraft device (42,44) not work and/or forbid said method comprising the steps of the activation of described aircraft device:
The power indicator line (74,76,78,80,82,84 that is being connected to the first flight management device (36,38); 52,54) be provided with in switchgear (14a, 16a, 18a, 20a, 22a, 24a), wherein said power indicator line (74,76,78,80,82,84; 52,54) provide the signal of the situation of indicated power supply (30,32,34);
By encourage described switchgear (14a, 16a, 18a, 20a, 22a 24a) revises described power indicator line (74,76,78,80,82,84; 52,54) signal on; And
Verify the response of described flight management device (36,38);
Wherein, at power indicator line (74,76,78,80,82,84; Switchgear (14a, 16a, 18a, 20a are set 52,54), 22a, step 24a) is included in and a switchgear is set in a plurality of power indicator lines and/or is being connected to a plurality of power indicator lines (74,76 of a plurality of flight management devices (36,38), 78,80,82,84; 52,54) be provided with in a plurality of switchgears (14a, 16a, 18a, 20a, 22a 24a), and revises described power indicator line (74,76,78,80,82,84; The step of the signal 52,54) comprises a plurality of power indicator lines (74,76,78,80,82,84; 52,54) step that a plurality of signals on are made amendment.
2. method according to claim 1, wherein said power indicator line (74,76,78,80,82,84; 52,54) signal on indicates the redundant power in a plurality of power supplies to supply with.
3. method according to claim 1 and 2, wherein said power indicator line (74,76,78,80,82,84; 52,54) signal on sends to a plurality of flight management devices (36,38).
4. method according to claim 1 and 2 is wherein revised described power indicator line (74,76,78,80,82,84; The step of the signal 52,54) comprises the step that the interruption of power supply (30,32,34) or overload conditions are carried out emulation.
5. one kind is suitable at least one flight management device (36,38) and be connected to the flight management device operation demonstration device (1) that its wiring is verified, described flight management device (36 in wherein using, 38) in response to the power failure situation outputting alarm, make aircraft device (42,44) do not work and/or forbid the activation of described aircraft device, wherein said flight management device operation demonstration device (1) comprising:
First coupling arrangement (2,4) is suitable for being arranged in the first power indicator line (74) that is connected to the first flight management device (36), and the wherein said first power indicator line (74) provides the signal of the situation of indication first power supply (30);
First switchgear (14a) in use is connected, and the signal of the described first power indicator line (74) of the feasible and described first flight management device (36) coupling is by switch; And
Second switch device (20) in use is connected, and makes signal with the second power indicator line (76) of the second flight management device (38) coupling by switch.
6. flight management device operation demonstration device according to claim 5 (1) further comprises:
Second coupling arrangement (10,12) is suitable for being separately positioned on the first and second flight management devices (36,38) the third and fourth power indicator line (82,84) in, the wherein said third and fourth power indicator line (82,84) provides the signal of the situation of indication second power supply (34);
The 3rd switchgear (18a) in use is connected, and the signal of described the 3rd power indicator line (82) of the feasible and described first flight management device (36) coupling is by switch; And
The 4th switchgear (24a) in use is connected, and the signal of described the 4th power indicator line (84) of the feasible and described second flight management device (38) coupling is by switch.
7. flight management device operation demonstration device according to claim 6 (1) further comprises:
The 3rd coupling arrangement (6,8) is suitable for being separately positioned on the first and second flight management devices (36,38) the 5th and the 6th power indicator line (78,80) between, the wherein said the 5th and the 6th power indicator line (78,80) provides the signal of the situation of indication the 3rd power supply (32);
The 5th switchgear (16a) in use is connected, and the signal of described the 5th power indicator line (78) of the feasible and described first flight management device (36) coupling is by switch; And
The 6th switchgear (22a) in use is connected, and the signal of described the 6th power indicator line (80) of the feasible and described second flight management device (38) coupling is by switch.
8. flight management device operation demonstration device according to claim 5 (1), wherein said first power supply are first generators (30) that is driven by first aircraft engine.
9. flight management device operation demonstration device according to claim 6 (1), wherein said second power supply are second generators (34) that is driven by second aircraft engine.
10. flight management device operation demonstration device according to claim 7 (1), wherein said the 3rd power supply (32) are the urgent power supplies that is used for aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2006100830879A CN101082653B (en) | 2006-05-31 | 2006-05-31 | Flying vehicle power functional failure simulation equipment and method thereof |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2006100830879A CN101082653B (en) | 2006-05-31 | 2006-05-31 | Flying vehicle power functional failure simulation equipment and method thereof |
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| Publication Number | Publication Date |
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| CN101082653A CN101082653A (en) | 2007-12-05 |
| CN101082653B true CN101082653B (en) | 2011-04-13 |
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| CN2006100830879A Expired - Fee Related CN101082653B (en) | 2006-05-31 | 2006-05-31 | Flying vehicle power functional failure simulation equipment and method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US9794131B2 (en) * | 2014-04-30 | 2017-10-17 | The Boeing Company | File, command, and airplane data transfer tool |
| FR3049095B1 (en) * | 2016-03-15 | 2019-10-25 | Airbus Operations (S.A.S.) | FLIGHT MANAGEMENT ASSISTANCE CENTER FOR A PLURALITY OF AIRCRAFT |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4002972A (en) * | 1975-03-18 | 1977-01-11 | General Electric Company | Electric vehicle control analyzer |
| US4015201A (en) * | 1974-10-31 | 1977-03-29 | Mono-Probe Corporation | Electrical continuity and voltage testing device |
| US4118664A (en) * | 1976-04-06 | 1978-10-03 | Paul Fields | Electrical trouble finding apparatus |
| US4251765A (en) * | 1979-02-07 | 1981-02-17 | The United States Of America As Represented By The Secretary Of The Air Force | Aircraft electrical system tester |
| US4870347A (en) * | 1988-02-22 | 1989-09-26 | Arnold Cicerone | Universal master breakout unit for testing avionic systems |
| EP1037061A2 (en) * | 1999-02-16 | 2000-09-20 | SUMITOMO WIRING SYSTEMS, Ltd. | Method for testing on-vehicle electronic unit |
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2006
- 2006-05-31 CN CN2006100830879A patent/CN101082653B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4015201A (en) * | 1974-10-31 | 1977-03-29 | Mono-Probe Corporation | Electrical continuity and voltage testing device |
| US4002972A (en) * | 1975-03-18 | 1977-01-11 | General Electric Company | Electric vehicle control analyzer |
| US4118664A (en) * | 1976-04-06 | 1978-10-03 | Paul Fields | Electrical trouble finding apparatus |
| US4251765A (en) * | 1979-02-07 | 1981-02-17 | The United States Of America As Represented By The Secretary Of The Air Force | Aircraft electrical system tester |
| US4870347A (en) * | 1988-02-22 | 1989-09-26 | Arnold Cicerone | Universal master breakout unit for testing avionic systems |
| EP1037061A2 (en) * | 1999-02-16 | 2000-09-20 | SUMITOMO WIRING SYSTEMS, Ltd. | Method for testing on-vehicle electronic unit |
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| CN101082653A (en) | 2007-12-05 |
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