CN101988954A - Equipment and method for testing aircraft ground power supply as well as device and method for loading aircraft ground power supply - Google Patents
Equipment and method for testing aircraft ground power supply as well as device and method for loading aircraft ground power supply Download PDFInfo
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- CN101988954A CN101988954A CN2009100556435A CN200910055643A CN101988954A CN 101988954 A CN101988954 A CN 101988954A CN 2009100556435 A CN2009100556435 A CN 2009100556435A CN 200910055643 A CN200910055643 A CN 200910055643A CN 101988954 A CN101988954 A CN 101988954A
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Abstract
According to the invention, testing equipment loads active power and reactive power on an aircraft ground power supply and detects the performance parameters of the aircraft ground power supply aircraft loaded with the active power and the reactive power, such as voltage, current or frequency, thereby judging whether the aircraft ground power supply meets the requirements or not. By adopting the method and equipment provided by the invention, the aircraft ground power supply can be fully tested before being used for supplying power to an aircraft, thereby preventing the unqualified aircraft ground power supply from damaging the equipment on the aircraft, and further better ensuring the safety of life and property of the personnel on the aircraft.
Description
Technical field
The present invention relates to aircraft energizer, relate in particular to and be used for device/Apparatus and method for that aircraft energizer is loaded and tests.
Background technology
Aircraft is under state of flight, and the burning by fuel in the engine converts its part to electric energy, and offers various consumers on the machine, for example airborne communication control, light fixture, pressure conditioning equipment or the like.
But when aircraft on the ground the time, if engine is not started working as yet, these consumers can't be by the be converted acquisition energy of heat energy to electric energy, and for this reason, various aircrafts all are furnished with ground power supply, specialize in the electricity needs of aircraft in this stage.
At home, most of aircraft manufacturing enterprises or airline all directly insert it aircraft and begin to aviation power supply after buying an aircraft energizer.
In some aircraft maintenance factories, whether repaired normally for the aircraft energizer that test is broken down, the tester uses the testing apparatus that has disposed pure resistive loads.
Summary of the invention
The present invention recognizes following unheeded always technical matters:
1. the aircraft energizer of " qualified " or " safety " of after tested and directly supplier not being claimed is used for the surface power supply of aircraft, may threaten the safety of expensive airborne equipment because of the actual conditions of this power supply are undesirable, for example, excessive supply current may burn out the circuit of airborne equipment.
2. airborne equipment comprises inductive or capacitive element toward contact except that comprising resistance element.And these perception or capacitive element and resistance element together influence the feedback of aircraft energizer.
For addressing the above problem, according to a first aspect of the invention, provide a kind of method that is used for the testing airplane ground power supply, wherein, may further comprise the steps: for described aircraft energizer loads active power and reactive power; Detect the performance parameter of described aircraft energizer after having loaded described active power and described reactive power, to obtain testing result.
Wherein, the step for this aircraft energizer loading active power and reactive power comprises: a plurality of phase places that are this aircraft energizer load active power and reactive power.
Preferably, the step for aircraft energizer loading active power and reactive power comprises following substep: an input media is provided; Receive the load relevant information of user by described input media input; According to described load relevant information, for described aircraft energizer loads described active power and described reactive power.
According to a further aspect in the invention, provide a kind of method of aircraft energizer offered load that is, wherein, may further comprise the steps: for described aircraft energizer loads active power and reactive power.
Preferably, described step for this aircraft energizer loading active power and reactive power comprises following substep: an input media is provided; Receive the user by the corresponding respectively load relevant information of described input media each phase place input and described aircraft energizer; According to described load relevant information, for described each phase place loads corresponding active power and reactive power.
Preferably, the input panel of this input media is provided with a plurality of load selector buttons, and wherein each load selector button is corresponding to different active power and/or reactive power value, and identifies by the identification information that is shown on the described input panel.
According to another aspect of the invention, provide a kind of load charger that is used to the aircraft energizer offered load, wherein, having comprised: input media; Treating apparatus is used for the load relevant information imported by described input media based on the user, is that described aircraft energizer loads active power and reactive power.
Preferably, the input panel of described input media is provided with a plurality of load selector buttons, and wherein each load selector button is corresponding to different active power and/or reactive power value, and identifies by the identification information that is shown on the described input panel.
More preferably, described a plurality of load selector buttons comprise many group load selector buttons, and wherein every group of load selector button be corresponding to a phase place of described aircraft energizer, and identify by described identification information.
More preferably, also be provided with a plurality of phase place selector buttons on the input panel of described input media, wherein each phase place selector button is corresponding to a phase place of described aircraft energizer, and identifies by described identification information.
According to another aspect of the invention, provide a kind of testing apparatus that is used for the testing airplane ground power supply, wherein, having comprised: aforesaid load charger; Pick-up unit is used to detect the performance parameter of described aircraft energizer after having loaded described active power and described reactive power, to obtain testing result.
Herein, the ground that is without loss of generality, the load that is carried on the aircraft energizer all embodies with the form of power.Wherein, active power unit is kilowatt (kW), and reactive power is kilovar (kVAR).
Adopt method and apparatus provided by the present invention, can before aircraft energizer is used for aircraft powered, test fully, thereby avoid defective power supply that the safety of airborne equipment is worked the mischief.
In addition, by implementing the present invention, the buyer can the very first time identifies all undesirable aircraft energizers with the cost of minimum, can change to seller requirements subsequently, and can when ground power supply causes actual loss, just this not discovered to some extent, improved efficient.
Another advantage of the present invention is embodied in, check after the power supply maintenance that the tester of aircraft maintenance factory is carried out in can compatible well background technology, because through simple and suitable configuration, at least one embodiment of the present invention can only load active power for aircraft energizer.
Another advantage of the present invention is embodied in, and can come as required one or more phase place is loaded, and for example, measurand only has the situation of a phase place.
Similarly, aircraft energizer manufacturing, maintaining unit also can use technical scheme provided by the invention.
Description of drawings
By reading below in conjunction with the description of accompanying drawing to indefiniteness embodiment, other purpose of the present invention, feature and advantage will become more obvious and outstanding.Wherein, same or analogous Reference numeral is represented same or analogous device or steps characteristic.
Fig. 1 is the test scene synoptic diagram according to the aircraft energizer of a specific embodiment of the present invention;
Fig. 2 a shows an aircraft energizer and according to the testing apparatus block diagram that is used for the testing airplane ground power supply of a specific embodiment of the present invention;
Fig. 2 b is the load charger block diagram that is used to the aircraft energizer offered load according to a specific embodiment of the present invention;
Fig. 2 c is the load charger block diagram that is used to the aircraft energizer offered load according to another specific embodiment of the present invention;
Fig. 2 d is according to the input panel synoptic diagram on the load charger that is used to the aircraft energizer offered load of a specific embodiment of the present invention;
Fig. 3 a is the method flow diagram that is used for the testing airplane ground power supply according to a specific embodiment of the present invention;
Fig. 3 b is the method flow diagram that is used to the aircraft energizer offered load according to a specific embodiment of the present invention.
Embodiment
Exemplified embodiment of the present invention will describe in detail in following content with reference to the accompanying drawings.Under the situation that does not depart from spirit of the present invention and scope, those skilled in the art can implement these or other improvement of the present invention and variation.
May cause the concrete parameter of aircraft energizer there are differences though it will be appreciated by those skilled in the art that the difference of aircraft type, this species diversity can't break away from the core concept of the present invention that hereinafter will discuss in detail.
At first come to be used for the testing airplane ground power supply and to be introduced for the equipment/device of its offered load to provided by the invention in conjunction with Fig. 1 and equipment/device block diagram.Wherein, Fig. 1 is the test scene synoptic diagram according to the aircraft energizer of a specific embodiment of the present invention, shows aircraft energizer to be tested 1 (hereinafter to be referred as power supply 1) and is used for its testing apparatus of testing 2.
According to a specific embodiment of the present invention, the manufacturing plant that mainly carries out the aircraft assembling has purchased a collection of aircraft energizer from the aircraft power supply suppliers, before it is formally come into operation, earlier testing apparatus 2 is connected with power supply 1, to test.Fig. 2 a shows a power supply 1 and according to the block diagram of the testing apparatus that is used for the testing airplane ground power supply 2 of a specific embodiment of the present invention.
Shown testing apparatus 2 comprises a load charger 20, be used for being power supply 1 offered load by connecting 30 at test process, pick-up unit 21 then is used for detecting the performance parameter that is embodied after power supply 1 offered load by connecting 31, for example: voltage, electric current or frequency.
In an exemplary embodiment of the present invention, the inner structure of load charger 20 is shown in Fig. 2 b, comprising treating apparatus 201 and a load device set 202, this load device set 202 comprises a plurality of active power loads such as resistor and a plurality of reactive power load such as capacitor and/or inductor.Those skilled in the art can realize load device set in this example according to the disclosed content of this instructions equally.
According to present embodiment, in dispatching from the factory, this treating apparatus 201 just has been set to automatically and has realized multiple predetermined active power and reactive power load mode by this load device set 202, has three phase places with power supply 1 and is example, and is as shown in table 1:
By table 1 as seen, by being a plurality of active power values of each phase settings and a plurality of reactive power value in advance, treating apparatus 201 can come automatically to come that by load device set 202 power supply 1 is carried out load in test process according to predetermined rule and load.Wherein, though in the table 1 active power value default on each phase place and reactive power value all are designated as N, but those skilled in the art understand, active power value number default on the out of phase can be identical, reactive power value default on the out of phase can be identical, and the active power value on the same phase place and the number of reactive power value also needn't be identical.In addition, it will be understood by those skilled in the art that active power and reactive power with corresponding footnote can be used for the load loading in couples, also can be not limited.
According to table 1, in an example of the present invention, active power and reactive power that treating apparatus 201 can be put down in writing in first comes for A, B, C phase place difference load table 1 constantly by loading device set 202, and in second moment after this, according to the active power and the reactive power that are loaded on these three phase places of table 1 change.Wherein, first constantly and second the interval between constantly can preestablish by the technician, the duration that loads on after the loading also can preestablish.
In the work of aircraft distribution, often make three phase places share power supply pressure relatively fifty-fifty, that is to say that when aircraft during in operate as normal, the load in the time of most on three phase places is about equally, the balanced load that this just it has often been said.The associative list 1 described embodiment according to the present invention, when load charger 20 is that three phase places are when all loading active power and reactive power respectively, can carry out balanced loaded loading, whether up to standard with testing power supply 1 in the performance parameter that aircraft is in general work state following time; Distinguishingly, the load charger 20 in this example can also load nonequilibrium load for three phase places, also, wherein has at least a load (for example active power and reactive power) on the phase place to be different from the load on other arbitrary phase place.Like this, advantageously whether testing power supply is up to standard in the performance parameter that aircraft is in particular job state following time.
It will be appreciated by those skilled in the art that in general example the above-mentioned AC load that is loaded on the A of power supply 1, B, the C phase place is identical, perhaps have more limited difference, this mainly is impaired in test process in order to prevent power supply 1.Certainly, if do not consider whether power supply 1 is impaired in test process, and just in order to test the performance of similar power supply under unusual condition, then mentioned above principle also can be inapplicable.
Certainly, in above-mentioned load loading procedure, pick-up unit 21 should monitor the performance parameter of power supply 1, for example voltage, electric current or frequency etc. all the time.After the performance parameter that detects power supply 1, it can be stored simply or shows by man-machine interface, so that consulting with the artificially, the technician pinpoints the problems (as existing).Perhaps, pick-up unit 21 can automatically compare detected parameters and predefined standard value, when the gap between a certain parameter and the respective standard value surpasses predetermined threshold, judge that promptly there is potential safety hazard in power supply 1, shall not be applied to the surface power supply of aircraft.Alternatively, the present invention also provides an alarm device (not shown) that is complementary for pick-up unit 21, after pick-up unit 21 judges that there is potential safety hazard in power supply 1, can alarm to the technician in modes such as flashing light, buzzings by alarm device.
As another kind of selection the of the present invention, can when test come by the technician by man-machine interface to load charger 20 active power and the reactive power on the power supply that is carried in 1 dispose flexibly, be explained below in conjunction with accompanying drawing more specifically.
Fig. 2 c shows the load charger block diagram that is used to the aircraft energizer offered load according to another specific embodiment of the present invention, wherein, shown in the treating apparatus 201 that in comprising Fig. 2 b, illustrated of load charger 20 and the load device set 202, also comprise an input media 200, be used for when testing, importing the active power and the reactive power value of desired loading by man-machine interaction for the technician.And those skilled in the art can realize this load device set 202 according to the disclosed content of this instructions.
Should be appreciated that to be used to realize that described input media 200 adoptable forms of the present invention are more, hereinafter mainly this form of input panel that is provided with button is introduced, but this does not represent the input media of other form of spirit eliminating employing of the present invention.
Fig. 2 d is according to the input panel synoptic diagram on the load charger that is used to the aircraft energizer offered load of a specific embodiment of the present invention, typically, this input panel belongs to the housing parts of input media 200, its with treating apparatus 201 between exist and to be used to transmit being connected of signal, which button makes treating apparatus 201 know has be pressed on it.
Shown in Fig. 2 d, wherein, the input panel of input media 200 is provided with many group load selector buttons, represents with the circle that has mark among the figure, for example button S4, S7, S32 etc.Wherein every group of load selector button be corresponding to a phase place of power supply 1, and wait and identify by the identification information on the panel " A is meritorious mutually ", " B is mutually idle ".Wherein, each load selector button of " A is meritorious mutually " delegation promptly is used to the A phase place to load active power, and the rest may be inferred for other.
In addition, each load selector button is also specifically corresponding to different active power or reactive power value, and identify by the identification information that is shown on the input panel, this identification information for example with the corresponding 0.66kW of button S7, promptly expression is when only pressing this button, and the A phase place that is expressed as power supply 1 has loaded the active power of 0.66kW.Dash area can be used to be provided for identifying the pairing reactive power value of the corresponding button among the figure, and this paper does not make for example its concrete value, but this does not influence abundant disclosing of the present invention.Make that the pairing reactive power of button S25 is m kilovar, then by pressing the button S4 and button S25, can realize the A phase place is loaded the active power of 0.33kW and m kilovar reactive power, if in addition also supress button S8, S18, S21 and S45, can realize A, B, C three-phase are all loaded numerical value active power and reactive power as can be known.
Wherein, a plurality of buttons are pressed and can also be used to load bigger performance number, for example, press these two buttons of S16 and S19, promptly can be the active power that the A phase place loads 6.66kW, and other situation also can by parity of reasoning.
Because the technician can be known the pairing performance number of each button by the identification information on the panel, therefore, can come to the load of three phase place load balance by suitably pressing some buttons.Wherein, so-called balanced load is meant that the active power and the reactive power that are loaded on three phase places all equate.Certainly, for testing power supply 1 performance under special circumstances, can also come to load unbalance load by pressing some buttons to three phase places.
Example shown in Fig. 2 d can be applicable to the loading to the meritorious and reactive power of any a plurality of phase places in A, B, three phase places of C well.
In the example shown in Fig. 2 d, set in advance on the input panel and be used to identify the identification information of respectively organizing the pairing phase place of load selector button.In the variation example of this example, some phase place selector buttons can be set on panel, wherein each phase place selector button is corresponding to a phase place of aircraft energizer to be tested, and identifies by corresponding identification information.
This changes in example, and each load selector button no longer equally divides into groups shown in the image pattern 2d with corresponding to different phase places, and the button of pressing specifically is will depend on that for the loading which phase place is done load which phase place selector button is pressed.Therefore, this variation example can be used for being single phase place offered load more.
Change in the example at another, the power supply that may need to test only has a phase place, then Ci Shi input panel then can be so complicated unlike Fig. 2 d, also do not need the phase place selector button described in the last variation example, the input panel of this moment will only dispose some and the corresponding load selector button of active power and some and the corresponding load selector button of reactive power.
As another optional scheme, load selector button on the input panel on the input media 200 can be unlike Fig. 2 d or separately corresponding to active power or separately corresponding to reactive power, but simultaneously corresponding to active power and reactive power, also be, after by next such button, just be equivalent to load a kilowatt active power and b kilovar reactive power to power supply 1.
Below be according to the part technical parameter of the load of embodiment more specifically of the present invention:
Capacity: m kVA;
Voltage: three-phase 115V/220V, 400Hz;
Active power resolution: 1kW;
Reactive power resolution can be set according to actual conditions by the technician;
Three phases active power: each stepping 30kW;
Three phase reactive power: each stepping can be set according to actual conditions by the technician.
Consider that the load device set may produce more heat, therefore, the present invention has been for it provides a plurality of heat abstractor (not shown)s, is used for the higher heat that produces on the course of work of load charger 20 is drained it, thereby reduces the influence of temperature variation to electron device.By adopting for example a plurality of small blast fans of a plurality of heat abstractors separate and that disperse, compare and use single large blower can reduce noise.
Come again below method provided by the invention to be done, therefore to conform to the principle of simplicity owing to above done comparatively detailed description for the corresponding device/equipment of this method to introduce in conjunction with process flow diagram.
Fig. 3 a is the method flow diagram that is used for the testing airplane ground power supply according to a specific embodiment of the present invention.This method starts from step S20, and wherein, testing apparatus 2 shown in Figure 1 is that aircraft energizer 1 loads active power and reactive power.Also promptly, in step S20, a load charger 20 by mentioned earlier loads active power and reactive power to power supply 1.The structure of load charger 20 wherein can be with reference to the associated description in Fig. 2 b and 2c and the instructions.
Wherein, when step S20 was realized by the load charger 20 shown in Fig. 2 c, the inside refinement flow process of step S20 had wherein at length described to be the idiographic flow of aircraft energizer offered load shown in Fig. 3 b.
Particularly, by an input media is provided, the input media shown in Fig. 3 c 200 for example, can come the input load relevant information for the technician, also be that he wants the active power and the reactive power value that load, thereby performing step S201 among the step S202 after this, loads corresponding active power and reactive power by load device set 202 to power supply 1 by treating apparatus 201.
According to a specific embodiment of the present invention, the inside idiographic flow of step S20 as shown in Figure 3.
More than the specific embodiment of the present invention is described.Need to prove that the present invention is not limited to above-mentioned specific implementations, those skilled in the art can make various modification or modification within the scope of the appended claims.
Claims (16)
1. method that is used for the testing airplane ground power supply wherein, may further comprise the steps:
A. be that described aircraft energizer loads active power and reactive power;
B. detect the performance parameter of described aircraft energizer after having loaded described active power and described reactive power, to obtain testing result.
2. method according to claim 1, wherein, described step a comprises:
-load active power and reactive power respectively in a plurality of phase places of described aircraft energizer.
3. method according to claim 1, wherein, described step a comprises:
A1., an input media is provided;
A2. receive the load relevant information of user by described input media input;
A3. according to described load relevant information, for described aircraft energizer loads described active power and described reactive power.
4. method according to claim 3, wherein, the input panel of described input media is provided with a plurality of load selector buttons, and wherein each load selector button is corresponding to different active power and/or reactive power value, and identifies by the identification information that is shown on the described input panel.
5. according to each described method in the claim 1 to 4, wherein, after described step a, further comprising the steps of:
-come described active load and described reactive load are carried out distributed heat radiation by a plurality of heat abstractors.
6. one kind is the method for aircraft energizer offered load, wherein, may further comprise the steps:
A. be that described aircraft energizer loads active power and reactive power.
7. method according to claim 6, wherein, described steps A comprises:
-be that one or more phase places in a plurality of phase places of described aircraft energizer load active power and reactive power.
8. method according to claim 7, wherein, described step a comprises:
-input media is provided;
-receive the user by the corresponding respectively load relevant information of described input media each phase place input and described aircraft energizer;
-according to described load relevant information, for described each phase place loads corresponding active power and reactive power.
9. method according to claim 8, wherein, the input panel of described input media is provided with a plurality of load selector buttons, and wherein each load selector button is corresponding to different active power and/or reactive power value, and identifies by the identification information that is shown on the described input panel.
10. load charger that is used to the aircraft energizer offered load wherein, comprising:
A load device set is comprising at least one active power device and at least one reactive power device;
Treating apparatus is used for gathering to come by described load device being that described aircraft energizer loads active power and reactive power.
11. load charger according to claim 10 wherein, also comprises:
An input media is used to receive the load loading relevant information that the user imports;
Described treating apparatus also is used for, and based on described load loading relevant information, gathering to come by described load device is that described aircraft energizer loads active power and reactive power.
12. load charger according to claim 11, wherein, the input panel of described input media is provided with a plurality of load selector buttons, wherein each load selector button is corresponding to different active power and/or reactive power value, and identifies by the identification information that is shown on the described input panel.
13. load charger according to claim 12, wherein, described a plurality of load selector button comprises many group load selector buttons, and wherein every group of load selector button be corresponding to a phase place of described aircraft energizer, and identifies by described identification information.
14. load charger according to claim 12, wherein, also be provided with a plurality of phase place selector buttons on the input panel of described input media, wherein each phase place selector button is corresponding to a phase place of described aircraft energizer, and identifies by described identification information.
15. a testing apparatus that is used for the testing airplane ground power supply wherein, comprising:
According to each described load charger among the claim 10-14;
Pick-up unit is used to detect the performance parameter of described aircraft energizer after having loaded described active power and described reactive power, to obtain testing result.
16. testing apparatus according to claim 16 also comprises a plurality of heat dissipation equipments, is used for described active load and described reactive load are carried out distributed heat radiation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009100556435A CN101988954A (en) | 2009-07-30 | 2009-07-30 | Equipment and method for testing aircraft ground power supply as well as device and method for loading aircraft ground power supply |
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| Application Number | Priority Date | Filing Date | Title |
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| CN2009100556435A CN101988954A (en) | 2009-07-30 | 2009-07-30 | Equipment and method for testing aircraft ground power supply as well as device and method for loading aircraft ground power supply |
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| CN101988954A true CN101988954A (en) | 2011-03-23 |
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| CN2009100556435A Pending CN101988954A (en) | 2009-07-30 | 2009-07-30 | Equipment and method for testing aircraft ground power supply as well as device and method for loading aircraft ground power supply |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103308868A (en) * | 2013-07-09 | 2013-09-18 | 南昌航空大学 | Airplane power source system control and protection experiment device |
| CN103983921A (en) * | 2013-12-27 | 2014-08-13 | 天津三星电子有限公司 | Power strip detection method and device |
| CN108037469A (en) * | 2017-10-23 | 2018-05-15 | 上海科梁信息工程股份有限公司 | Aircraft power supply characteristic test system and method |
| CN109799410A (en) * | 2019-03-19 | 2019-05-24 | 西北工业大学 | Flight profile, mission profile control device, aircraft electrical power system integrated test system and method |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2069025U (en) * | 1990-03-26 | 1991-01-09 | 成都飞机工业公司 | Electric appliance faulting detector in starting system of plane engine |
| CN2645320Y (en) * | 2003-09-11 | 2004-09-29 | 威海广泰空港设备股份有限公司 | Electric power unit for airplane |
| CN101135910A (en) * | 2007-09-29 | 2008-03-05 | 中国石油天然气股份有限公司 | oil pumping with lever system ground facilities efficiency evaluate method |
-
2009
- 2009-07-30 CN CN2009100556435A patent/CN101988954A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2069025U (en) * | 1990-03-26 | 1991-01-09 | 成都飞机工业公司 | Electric appliance faulting detector in starting system of plane engine |
| CN2645320Y (en) * | 2003-09-11 | 2004-09-29 | 威海广泰空港设备股份有限公司 | Electric power unit for airplane |
| CN101135910A (en) * | 2007-09-29 | 2008-03-05 | 中国石油天然气股份有限公司 | oil pumping with lever system ground facilities efficiency evaluate method |
Non-Patent Citations (2)
| Title |
|---|
| 周杰等: "一种航空地面电源检测仪的设计与实现", 《现代雷达》 * |
| 孟军红等: "基于LabVIEW的飞机电源地面试验测试系统", 《计测技术》 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103308868A (en) * | 2013-07-09 | 2013-09-18 | 南昌航空大学 | Airplane power source system control and protection experiment device |
| CN103308868B (en) * | 2013-07-09 | 2015-09-16 | 南昌航空大学 | Aircraft power system control and protection experimental provision |
| CN103983921A (en) * | 2013-12-27 | 2014-08-13 | 天津三星电子有限公司 | Power strip detection method and device |
| CN108037469A (en) * | 2017-10-23 | 2018-05-15 | 上海科梁信息工程股份有限公司 | Aircraft power supply characteristic test system and method |
| 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 |
| CN109799410A (en) * | 2019-03-19 | 2019-05-24 | 西北工业大学 | Flight profile, mission profile control device, aircraft electrical power system integrated test system and method |
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Application publication date: 20110323 |