CN100493992C - Test device for testing additive center tank (ACT) of aircraft - Google Patents
Test device for testing additive center tank (ACT) of aircraft Download PDFInfo
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- CN100493992C CN100493992C CNB2006100912968A CN200610091296A CN100493992C CN 100493992 C CN100493992 C CN 100493992C CN B2006100912968 A CNB2006100912968 A CN B2006100912968A CN 200610091296 A CN200610091296 A CN 200610091296A CN 100493992 C CN100493992 C CN 100493992C
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Abstract
The invention relates to the testing equipment for ACT system of flying objects. It comprises the AFMC and the ALSCU control device. The equipment comprises at least one part coupling to at least one testing module of the ACT system to replace the control device, with the said testing module composed of device generating one or more testing signals and delivering it ot the ACT system.
Description
Technical field
The present invention relates to be used for the test equipment of the additional central case (ACT) of testing flying vehicle.
Background technology
Modern shipping and passenger aircraft can be provided with additional central case (ACT) system and replenish the main fuel tank system.The ACT system can comprise one or more additional central casees, and they all are arranged in the fuselage of aircraft.Airbus
TMDummy vehicle A319CJ, for example can be equipped with up to six additional central casees.The main fuel tank system typically comprises the central bin in the fuselage of one or more casees in each wing and aircraft.
The ACT system is associated with many valves, and described valve is that delivery of fuel is reached delivery of fuel and needed to the ACT ventilation between ACT to ACT with from the ACT delivery of fuel.The example of such valve is the fuel inlet valve that is used for each additional central case, be used for fuel from the main tank system be fed to the additional central case one or more transmission valves, the one or more fuel valves that are used on the ground the additional central case being filled, be used to control one or more air shut off valve etc. that forced air flows into the additional central case.Structure and operation, the especially Airbus of the ACT system in the general all fam flight devices of those skilled in the art
TMThe structure of model series and operation.
Although can there be such aircraft in the fuel management of ACT system by normal fuel system and ACT system general purpose control device being carried out, being well known that, wherein provide special-purpose control setup to be used for this task.Such model is above-mentioned Airbus
TMA319CJ.Special-purpose ACT control setup can comprise via the supplemental fuel supervisory computer (AFMC) of relay network with subsidiary level sensing control unit (ALSCU) operation.Wherein, AFMC controls ACT fuel to main central bin with from main central bin and the automatic transmission between ACT in the mode that the center of gravity that makes the aircraft balance in the transmittance process and guarantee aircraft remains in the restriction.
Be in the appearance of shortage of the fuel of each level in the horizon sensor sensing case related with ACT.Particularly, the horizontal sensing system of case can be included in the high-level sensor among each ACT, is in high-caliber case content with sensing and also finishes this case fuel up.It can further comprise low level sensor, with the low-level case content of sensing.ALSCU handles measured fuel level, and carries out the comparison of low level sensor wet condition, whether just carry out to monitor the ACT delivery of fuel with correct order, and if not, then trigger the driving compartment alarm.Therefore, ACT horizon sensor and ALSCU relate to the supervision to the ACT delivery of fuel.
ALSCU also can comprise and the logic of forward direction ACT being ventilated and the detection of the damage of fuel up/transfer line and isolation subsequently thereof is associated.
AFMC receives fuel quantity and other information relevant with the main tank system from fuel quantity instruct computer (FQIC) in addition.AFMC uses its information from ALSCU and FQIC reception, to calculate ACT and total aircraft fuel amount, is used for outputing to the centralized aircraft monitors device of electronics (ECAM) and other receptors of driving compartment, and also is used for the control to the automatic fuel up of ACT.
AFMC can be the unit that separates with ALSCU, with the special-purpose plug-in type interface socket of the separation that is connected to the ACT system.Also can imagine AFMC and ALSCU are combined in the single control unit.
In addition, normally keep in the program process sending in advance the test and ground test need check ACT valve and/or AFMC and/or ALSCU so that proper operation, promptly whether corresponding component suitably reacts for particular condition and/or particular command.Order can comprise the valve order of manually initiating from aircraft cockpit.For example,, must produce cooresponding signal, so that for example certain indicating device in the driving compartment shows that a hand valve activation command provides at an ACT valve in response to the access valve activation command.In addition, when each valve activation command takes place, must check what whether corresponding valve encouraged according to this valve activation command.At last, need to check the ACT valve whether follow to the ACT thrashing (as, for example ACT delivery of fuel fault or the horizontal situation of ACT low fuel) detection and taked predetermined valve position.
Summary of the invention
In view of above-mentioned, an object of the present invention is to provide test equipment, it allows the easy of some aspect at least of aircraft ACT system and actv. test.
For realizing this purpose, the invention provides and be used for the test equipment that the ACT system to aircraft tests, the ACT system comprises the control setup of the function that is configured to carry out supplemental fuel supervisory computer (AFMC) and subsidiary level sensing control unit (ALSCU), wherein said test equipment comprises and is suitable for replacing at least a portion of described control setup and is coupled at least one test module of described ACT system, and described test module comprises the device that is used to produce one or more test signals and described test signal is outputed to described ACT system.
Test module preferably includes switching device, is used for connecting and cutting off one or more test signals.This switching device can be manually operated.In addition or replacedly, test equipment can comprise and be used for the test plan software that carried out by treater, wherein so one or more predetermined testing signals of being exported by test module of configuration so that can realize or generation of one or more predetermined testing signal sequences of this test plan software.
In a simple embodiment, test signal can be high or low electric potential signal, and its low state is corresponding to ground potential, and high state is corresponding to the plus or minus electromotive force that is different from ground potential.Particularly, high potential can be corresponding to the service voltage level of power supply voltage system on the machine of aircraft, but and on the test module slave power supply voltage system obtain high potential.Certainly, test equipment also can comprise its oneself voltage source, and this voltage source is independent of power supply voltage system on the machine.
In one embodiment, described test equipment comprises at least a portion of the control setup that is suitable for replacing carrying out the AFMC function and is coupled to first test module of described ACT system, wherein first test module comprises the device that is used to produce one or more test signals, the order of the one or more ACT valve of described test signal emulation.This embodiment can be used for testing the proper operation of various ACT valves.
The ACT valve order of one or more emulation can specifically comprise:
-with each relevant ACT access valve orders of one or more ACT access valves, and/or
The order of-ACT air shut off valve, and/or
The order of-ACT blow valve, and/or
The order of-ACT fuel up valve.
First test module can further comprise the device that is used to produce one or more test signals, and described test signal carries out emulation to predetermined AFMC transmission faulty condition and at least one of the low-level situation of AFMC of being scheduled to.
First test module also can comprise the device that is used to receive one or more ACT valve status signals, described ACT valve status signals is represented the opening and closing situation of one or more ACT valves, wherein first test module further comprises first indicating device, is used for visually indicating one or more ACT valve situations.
First indicating device can be configured to indication especially:
-with one or more ACT access valves in each relevant ACT access valve situation, and/or
-ACT air shut off valve situation, and/or
-ACT blow valve situation, and/or
-ACT fuel disconnecting valve situation, and/or
-ACT transmits the valve situation, and/or
-ACT ventilation disconnecting valve situation.
Advantageously, first indicating device comprise with one or more ACT valves in each two relevant LED, one of among the LED when being lighted indication open valve position, and another indication closed valve position when being lighted.For example, LED can be green and another is red.
First test module can comprise second indicating device, is used to indicate the generation of one or more ACT valve order, and the order of described ACT valve realizes by the manual operations to one or more valve operating components of providing in the aircraft cockpit.
In another embodiment, this test equipment comprises second test module, be suitable for replacing carrying out the ALSCU function control setup a part and be coupled to the ACT system, carrying out another part of the control setup of AFMC function stays in the ACT system, wherein second test module comprises the device that is used to produce one or more test signals, the one or more ACT fuel level indications of described test signal emulation.Especially, this embodiment can be used for the AFMC suitable function partly of control setup is tested.
Especially, second test module can comprise with one or more additional central Fuel Tanks in each two relevant-position, switch is to produce one or more test signals of the wet and dried Fuel Tank situation of emulation.
Second test module also can comprise the device that is used to produce one or more test signals, described test signal emulation:
-be used for the valve order that first servomotor to the fuel disconnecting valve encourages, and/or
-be used for the valve order that second servomotor to the fuel disconnecting valve encourages, and/or
-be used for the valve order that first servomotor to the ventilation disconnecting valve encourages, and/or
One is used for the valve order that second servomotor to the ventilation disconnecting valve encourages.
Consider the above, should be appreciated that, typically at least some in many valves of in the ACT system, finding available two independently servo actuator (servomotor) implement so that provide redundant.The fuel up valve can be an exception, and it only equips single servo actuator usually.
Further, second test module can comprise the device that is used to produce one or more test signals, described test signal emulation:
-pipeline damages indication, and/or
The order of-alarm line closing of circuit, and/or
-predetermined ACT transmits faulty condition.
Second test module also can comprise indicating device, be used to indicate the alarm line circuit whether the urgent power supply of closure and/or aircraft whether work.
Description of drawings
Referring now to accompanying drawing the present invention is described in further detail, wherein:
Fig. 1 is the schematic plan view of additional central case fuel system in the aircraft,
Figure 2 shows that to be used for the front panel that the testing cassete of emulation is carried out in to ACT valve order, and
Figure 3 shows that the front panel that is used for the ALSCU signal is carried out the testing cassete of emulation.
The specific embodiment
Figure 1 shows that schematic plan view according to the overall setting of fuel tank system in the commercial passenger traffic of an one exemplary embodiment or the cargo aircraft.This fuel tank system comprises main tank system and additional central case system (ACT system).The general in the drawings label of this ACT system is 10.The main tank system can comprise left wing's case 12, right flank case 14 and central bin 15.
In the embodiment shown, aircraft is equipped with 6 ACT, is designated as 16,18,20,22,24 and 26.ACT 16-26 is positioned at the cargo area of aircraft fuselage and is connected to each other via fuel line 28.They further are connected to main wing case 12,14 and central bin 15 via fuel line 30.Fuel line 30 is main fuel up/go fuel lines.
Each additional central case (ACT) 16-26 is provided with fuel inlet valve 32,34,36,38,40,42 respectively.
Fuel up valve 44 allows to give ACT system fuel up.During fuel up, fuel up valve 44 is set to open position and will cuts out in the every other time.
ACT transmits petrolift 46 and ACT transmits valve 48 is provided for transmitting fuel between main tank system and ACT system 10 mechanism.This delivery of fuel does not occur over just during the fuel up, also occurs in the fuel that loads when aircraft during the flight and burns down gradually and bring into use in the ACT fuel.For this reason, ACT fuel can be that the mode of sky is delivered to main central bin 15 sequentially to make ACT via fuel line 30 one by one.
In order to allow the ventilation of ACT system, provide the ventilating duct 50 that is connected to all additional central case 16-26 and is coupled to central bin breathing line 52.Unshowned blow valve allows the selectivity of additional central case 16-26 to ventilate among Fig. 1.
When fuel when additional central case 16-26 drains out, forced air is fed in the additional central case, to prevent forming potential explosive gas mixture in the additional central case.Forced air is sent in additional central case 16 and 22 via the air shut off valve 54 that is arranged in the air pressurized line 56.Because all ACT 16-26 are via ventilating duct 50 fluid communication with each other, the forced air that is fed in ACT 16 and 22 also will be fed in residual A CT 18,20,24 and 26.
The control of ACT system 10 realizes by the supplemental fuel supervisory computer (AFMC) of working with the subsidiary level sensing control unit (ALSCU) that does not illustrate in the drawings.Before new aircraft is submitted to client, and in the periodical maintenance process, should the whole ACT system 10 that comprise its valve and AFMC be tested, to guarantee the normal running of this system.
Fig. 2 illustrates an exemplary and nonrestrictive embodiment of the front panel 58 of testing cassete, and it is suitable for the order of emulation ACT valve.Testing cassete replaces AFMC.In other words, in order to make the testing cassete place in operation, AFMC must at first disconnect from ACT system 10 and connecting.Then, use and the identical electric coupler interface of connection AMFC, testing cassete can be connected to ACT system 10.
Shown in the upper left of front panel 58, vertically six of row can manually operated, two-position (on/off) switch 60,62,64,66,68,70 to provide one.Certainly, switch 60 is used for carrying out emulation to the ACT access valve order of the fuel inlet valve 32 related with ACT 16, and switch 62 is used for carrying out emulation to the ACT access valve order of the fuel inlet valve 34 related with ACT 18, and the rest may be inferred.Switch 60-70 encourages so that its control lever moves to right positions as shown in Figure 2, corresponding to the emulation of " opening (open) " order, the order that the ACT access valve is removed.On the other hand, the switching manipulation bar is moved to leftward position among Fig. 2, corresponding with emulation to " closing (close) " order of ACT access valve.
On the right of switch 60-70, in front on the plate 58, provide the vertical LED 72-82 of row, with the order of indication ACT access valve when the valve command panel from aircraft cockpit (not shown herein) manually boot.Therefore, in order to test the ACT access valve, the tester has two options, and one is that the switch 60-70 of the testing cassete by using Fig. 2 comes emulation is carried out in the valve order, and another is by handling on the valve command panel in driving compartment.The access valve order that so produces from driving compartment valve command panel is routed to testing cassete via the AUI of above-mentioned ACT system 10.
In order to verify that easily whether ACT access valve order (no matter from testing cassete or from driving compartment valve command panel) has made corresponding ACT access valve take the desired position, on the capable the right of LED 72-82, provides two LED that vertically go.The opening and closing access valve situation of these two vertical row indication access valve 32-42.The first row LED 84-94 is made up of 6 red LED, when it is lighted, indicates corresponding access valve to be in the position of closing.The second row LED 96-106 is made up of 6 green LED, when it is lighted, indicates corresponding access valve to be in the position of opening.
Below this row switch 60-70, being provided with another group 5 in one vertically goes can manually operated, two-position (on/off) switch 108-116.These can be used for emulation: air shut off valve order (switch 108), blow valve order (switch 110), fuel up valve order (switch 112), AFMC transmit faulty condition (switch 114) and the horizontal situation of ACT low fuel (switch 116).Switch 108 is operated in the mode identical with switch 60-70 with 112, and switch 110 is then opposite, and the order of promptly " opening (open) " is corresponding to the left position of switching manipulation bar, and " closing (close) " order is corresponding to the location right of switching manipulation bar.
The right hand of switch 108-116, have but two vertically the LED of row be positioned on the front panel 58, it indicates the valve position of following valve: ACT to transmit valve 48, air shut off valve 54, blow valve, fuel disconnecting valve and ventilation disconnecting valve with the above-mentioned similar manner with being relevant to LED 72-82 and LED 84-94.
When by switch 114 is set to its location right come emulation AFMC transmit faulty condition (as, can be caused by the fault of transmitting petrolift 46 and/or transmitting valve 48) time, at least a portion of the ACT valve shown on the front panel 58 should move to specific desired location automatically.By checking that among each LED on the front panel 58 which lighted, can verify to reach these predetermined valve positions whether.
Fig. 3 shows an exemplary and nonrestrictive embodiment of the front panel 58 of testing cassete, and it is suitable for emulation ALSCU signal.This testing cassete replaces ALSCU.In other words, enter use in order to make testing cassete, ALSCU must at first disconnect from ACT system 10 and connecting.Then, use and the identical electric coupler interface of connection ALSCU, testing cassete can be connected to ACT system 10.
In the top of plate 138, be provided with LED 140 in front, when it was lighted, indication was delivered to the urgent power supply of testing cassete just in normal operation with predetermined voltage.Urgent power supply (not shown) comprises timer-relay (timer-relay), and it can be set to the schedule time, as 20 seconds.If this timer-relay normally plays a role, then LED140 should light 20 seconds, and disconnects then.
In addition, a horizontal line can be used for the intended fuel level indicative signal that is used for each ACT is carried out emulation by manually operated switch 146-156.Switch 146-156 is two-position (on/off) switch, with emulation " wet (wet) " and " doing (dry) " horizontal situation of ACT.Use switch 14-156, might check whether AFMC correctly works, and promptly whether causes predetermined reaction, wherein AFMC stays in the ACT system between the used life of the alternative testing cassete of ALSCU.For example, can require AFMC on cockpit display panel, to cause the vision indication of fuel level.
Below the switch 146-156 of horizontal line, provide two-position (on/off) switch 158-170 that vertically goes in front on the plate 138.If be set to " on ", then switch 158 emulation are used for being positioned at the activation command of first servomotor of the disconnecting valve of fuel line.If be set to " on ", then switch 160 emulation are used for the activation command of first servomotor of blow valve.If be set to " on ", then switch 162 emulation are used for the activation command of second servomotor of fuel disconnecting valve, and switch 164 can be used to the activation command that emulation is used for second servomotor of blow valve.Then, can check whether AFMC has caused that cooresponding driving compartment shows, and whether corresponding valve has been taked and the cooresponding position of this activation command.
If be set to " on ", the ventilating duct that damages of switch 166 emulation then.Can check then whether AFMC has caused that cooresponding driving compartment shows.If be set to " on ", switch 168 emulation ALSCU output signals then, this signal indication is as the fault of delivery of fuel pump 46.Therefore can check whether AFMC has caused that cooresponding driving compartment shows.
If be set to " on ", switch 170 emulation close commands then, with closed alarm line circuit, this circuit is arranged to detect the ventilating duct of damage.LED 172 is arranged on the right of switch 170, if the success of alarm line circuit is closed, then it is lighted.
Claims (15)
1. test equipment that additional central case (ACT) system that is used for aircraft tests, described ACT system comprises the control setup of the function that is configured to carry out supplemental fuel supervisory computer (AFMC) and subsidiary level sensing control unit (ALSCU), wherein said test equipment comprises and is suitable for replacing at least a portion of described control setup and is coupled at least one test module of described ACT system, described test module comprises and is used to produce one or more test signals and described test signal is outputed to the device of described ACT system, wherein said at least one test module comprise with in the lower module one of at least:
First test module, its be suitable for replacing described control setup execution AFMC function a part and be coupled to described ACT system, wherein said first test module comprises the device of the one or more test signals that are used to produce the order of the one or more ACT valve of emulation; And
Second test module, its be suitable for replacing described control setup execution ALSCU function a part and be coupled to described ACT system, another part of the execution AFMC function of wherein said control setup is stayed in the described ACT system, and wherein said second test module comprises the device of the one or more test signals that are used to produce the one or more ACT fuel levels indications of emulation.
2. test equipment according to claim 1 is used for the switching device that described one or more test signals are connected and cut off comprising one of at least in wherein said first test module and second test module.
3. test equipment according to claim 2, but wherein said switching device M/C.
4. according to each the described test equipment in the claim 1 to 3, wherein one or more are comprised by the ACT valve order of emulation:
-with each relevant ACT access valve order in one or more ACT access valves, and/or
The order of-ACT air shut off valve, and/or
The order of-ACT blow valve, and/or
The order of-ACT fuel up valve.
5. according to each the described test equipment in the claim 1 to 3, wherein said first test module comprises that being used for producing at least one that predetermined AFMC is transmitted faulty condition and the low-level situation of predetermined AFMC carries out the device of one or more test signals of emulation.
6. according to each the described test equipment in the claim 1 to 3, wherein said first test module comprises and is used for device that one or more ACT valve status signals are received, described ACT valve status signals is represented the opening and closing situation of one or more ACT valves, and wherein said first test module further comprises first indicating device that is used for visually indicating one or more ACT valve situations.
7. test equipment according to claim 6, wherein said first indicating device are configured to indication:
-with each relevant ACT access valve situation in one or more ACT access valves, and/or
-ACT air shut off valve situation, and/or
-ACT blow valve situation, and/or
-ACT fuel disconnecting valve situation, and/or
-ACT transmits the valve situation, and/or
-ACT ventilation disconnecting valve situation.
8. test equipment according to claim 6, wherein said first indicating device comprises and each two relevant LED in one or more ACT valves, a LED among the described LED indicates when lighting and opens valve position, and another LED indicates closed valve position when lighting.
9. test equipment according to claim 8, a wherein said LED are green and another LED is red.
10. according to each the described test equipment in the claim 1 to 3, wherein said first test module comprises second indicating device, be used to indicate the generation of one or more ACT valve order, the order of described one or more ACT valve realizes by the M/C to one or more valve operating components of being provided in the aircraft cockpit.
11. according to each the described test equipment in the claim 1 to 3, wherein said second test equipment comprise with one or more additional central Fuel Tanks in each relevant two position switch so that produce one or more test signals that wet and dried Fuel Tank situation are carried out emulation.
12. according to each the described test equipment in the claim 1 to 3, wherein said second test module comprises and is used to produce the device that the following is carried out one or more test signals of emulation:
-be used for the valve order that first servomotor to the fuel disconnecting valve encourages, and/or
-be used for the valve order that second servomotor to described fuel disconnecting valve encourages, and/or
-be used for the valve order that first servomotor to the ventilation disconnecting valve encourages, and/or
-be used for the valve order that second servomotor to described ventilation disconnecting valve encourages.
13. according to each the described test equipment in the claim 1 to 3, wherein said second test module comprises and is used to produce the device that the following is carried out one or more test signals of emulation:
-pipeline damages indication, and/or
The order of-alarm line closing of circuit, and/or
-predetermined ACT transmits faulty condition.
14. whether closed test equipment according to claim 13, wherein said second test module comprise the indicating device that is used to indicate described alarm line circuit.
15. according to each the described test equipment in the claim 1 to 3, wherein said second test module comprises the indicating device whether urgent power supply that is used to indicate aircraft works.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2006100912968A CN100493992C (en) | 2006-06-11 | 2006-06-11 | Test device for testing additive center tank (ACT) of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2006100912968A CN100493992C (en) | 2006-06-11 | 2006-06-11 | Test device for testing additive center tank (ACT) of aircraft |
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| Publication Number | Publication Date |
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| CN101085645A CN101085645A (en) | 2007-12-12 |
| CN100493992C true CN100493992C (en) | 2009-06-03 |
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| CNB2006100912968A Expired - Fee Related CN100493992C (en) | 2006-06-11 | 2006-06-11 | Test device for testing additive center tank (ACT) of aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103112599A (en) * | 2013-01-28 | 2013-05-22 | 南京航空航天大学 | Air bag type plane auxiliary fuel oil system air pressure transfusion fuel oil testing system and method |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109878760B (en) * | 2019-04-15 | 2022-05-03 | 中国民航大学 | Universal aviation aircraft fault remote assistance platform and repairing method |
| WO2021072414A2 (en) * | 2019-08-06 | 2021-04-15 | Telles Angel | Cabin pressure sensor (cps) system for pressurized-cabin aircraft and associated methods |
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2006
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103112599A (en) * | 2013-01-28 | 2013-05-22 | 南京航空航天大学 | Air bag type plane auxiliary fuel oil system air pressure transfusion fuel oil testing system and method |
| CN103112599B (en) * | 2013-01-28 | 2015-01-14 | 南京航空航天大学 | Air bag type plane auxiliary fuel oil system air pressure transfusion fuel oil testing system and method |
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| CN101085645A (en) | 2007-12-12 |
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