CN114236284B - Electrical testing device for aircraft - Google Patents
Electrical testing device for aircraft Download PDFInfo
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- CN114236284B CN114236284B CN202111542394.XA CN202111542394A CN114236284B CN 114236284 B CN114236284 B CN 114236284B CN 202111542394 A CN202111542394 A CN 202111542394A CN 114236284 B CN114236284 B CN 114236284B
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- 238000012360 testing method Methods 0.000 title claims abstract description 133
- 239000002360 explosive Substances 0.000 claims abstract description 47
- 230000000977 initiatory effect Effects 0.000 claims abstract description 47
- 238000011990 functional testing Methods 0.000 claims abstract description 6
- 230000004913 activation Effects 0.000 claims description 5
- 238000010304 firing Methods 0.000 claims description 2
- 230000006870 function Effects 0.000 description 14
- 238000000034 method Methods 0.000 description 14
- 230000008569 process Effects 0.000 description 13
- 238000004088 simulation Methods 0.000 description 4
- 238000005259 measurement Methods 0.000 description 3
- 238000007689 inspection Methods 0.000 description 2
- 238000003860 storage Methods 0.000 description 2
- 230000002159 abnormal effect Effects 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004590 computer program Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000013024 troubleshooting Methods 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Electric Properties And Detecting Electric Faults (AREA)
Abstract
The application relates to an aircraft electrical testing device, belongs to the technical field of aircraft electrical systems, and aims to solve the problem that the testing device of the existing aircraft electrical system is high in cost. An aircraft electrical test device, the device comprising: a power supply module, and a plurality of functional test modules; each functional test module is used for receiving corresponding functional signals in the aircraft electrical system and electrically testing the received functional signals; the power supply module is used for supplying power to each function test module; the function test module comprises an initiating explosive device ignition test module, a simulated thermal battery test module and a fuse insurance state check module.
Description
Technical Field
The application relates to the technical field of aircraft electrical systems, in particular to an aircraft electrical testing device.
Background
There are many important signals in the aircraft electrical system, such as power supply and distribution signals, and signals related to initiating explosive devices, etc., which directly affect the safety of the aircraft system.
The conventional electrical test device is arranged in an aircraft, namely, the test process is completed in the aircraft: and collecting the whole flow signal of the working process of the aircraft, and detecting the whole flow signal.
This approach has the following disadvantages:
(1) The cost of the testing device is high;
(2) The testing process is very complex and takes a long time;
(3) The electric testing device arranged in the aircraft occupies the volume, the weight and the like in the aircraft, so that the overall performance index of the aircraft is influenced, and the cost of the aircraft is greatly increased particularly for mass-production aircraft.
Disclosure of Invention
In view of the above analysis, an embodiment of the present application is directed to an electrical testing device for an aircraft, so as to solve the problem of high cost of the testing device existing in the electrical system of the existing aircraft.
The embodiment of the application discloses an aircraft electrical testing device, which comprises: a power supply module, and a plurality of functional test modules; wherein,,
each function test module is used for receiving corresponding function signals in the aircraft electrical system and electrically testing the received function signals;
the power supply module is used for supplying power to each function test module;
the function test module comprises an initiating explosive device ignition test module, a simulated thermal battery test module and a fuse insurance state check module.
Based on the scheme, the application also makes the following improvements:
further, the initiating explosive device ignition test module is a relay closed-loop control circuit;
the relay closed-loop control circuit consists of a relay, diodes D1-D2, a resistor R1 and an indicator light LED1, wherein the relay is provided with a normally open switch; wherein,,
one end of a normally open switch of the relay is connected with the positive output end of the power supply module, and the other end of the normally open switch, the negative electrode of the diode D1 and one end of the resistor R1 are all connected with the control end of the relay; the anode of the diode D1 is a signal input end of a relay closed-loop control circuit; the other end of the resistor R1 is connected with the positive electrode of the indicator light LED1, and the negative electrode of the indicator light LED1 and the output end of the relay are both connected with the negative output end of the power supply module;
a diode D2 is also reversely connected between the control end and the output end of the relay;
in the initiating explosive device ignition test module, a signal input end of a relay closed-loop control circuit is used as a signal input end of the initiating explosive device ignition test module and used for receiving an initiating explosive device ignition signal output by an aircraft electrical system.
Further, the analog thermal battery test module includes: the relay closed-loop control circuit has the same structure as the relay closed-loop control circuit of the initiating explosive device ignition test module, and simulates a thermal battery power supply circuit; wherein,,
the simulated thermal battery power supply loop consists of a switch SB1, a resistor RB1 and an indicator lamp LEDB 1;
one end of the switch SB1 is connected with the other end of the normally open switch, the other end of the switch SB1 is connected with one end of the resistor RB1, the other end of the resistor RB1 is connected with the positive pole of the indicator lamp LEDB1, and the negative pole of the indicator lamp LEDB1 is grounded;
the other end of the switch SB1 is also used as a power supply anode of the simulated thermal battery, and the negative output end of the power supply module is used as a power supply cathode of the simulated thermal battery; the positive electrode and the negative electrode of the power supply of the simulated thermal battery are connected with the two ends of the thermal battery in the electric system of the aircraft in parallel;
in the analog thermal battery test module, the signal input end of the other relay closed-loop control circuit is used as the signal input end of the analog thermal battery test module and is used for receiving the analog thermal battery activation signal output by the aircraft electrical system.
Further, the fuse insurance state checking module comprises a resistor RE1 and an indicator lamp LEDE1; wherein,,
the signal input end of the fuse insurance state checking module is connected to the negative electrode of the indicator lamp LEDE1, the positive electrode of the indicator lamp LEDE1 is connected with one end of a resistor RE1, and the other end of the resistor RE1 is connected with the positive output end of the power supply module;
the signal input end of the fuse insurance state checking module is used for receiving a fuse insurance state checking signal output by the electric system of the aircraft.
Further, the power supply module includes: fuse FA1, switches SA1-SA2, resistors RA1-RA2 and indicator lights LEDA1-LEDA 2; wherein,,
the positive input end of the power supply module is sequentially connected with a fuse FA1 and a switch SA1 in series, and then is connected with one end of a switch SA2, and the other end of the switch SA2 is used as the positive output end of the power supply module; the negative input end of the power supply module is used as the negative output end of the power supply module; one end of the switch SA1 connected with the switch SA2 is also connected with one end of a resistor RA1, the other end of the resistor RA1 is connected with the positive electrode of an indicator lamp LEDA1, and the negative electrode of the indicator lamp LEDA1 is connected with the negative input end of the power supply module; the other end of the switch SA2 is also connected with one end of a resistor RA2, the other end of the resistor RA2 is connected with the positive electrode of an indicator lamp LEDA2, and the negative electrode of the indicator lamp LEDA2 is connected with the negative input end of the power supply module.
Further, an ammeter is connected in series between the switch SA2 and the switch SA 3;
and a voltmeter is also connected in parallel between one end of the switch SA2 connected with the switch SA3 and the negative input end of the power supply module.
Further, the device also comprises a power supply test module for executing auxiliary voltage test on the positive output end and the negative input end of the power supply module.
Further, the auxiliary voltage test includes a ground signal test.
Further, the device comprises a plurality of initiating explosive device ignition test modules; each initiating explosive device ignition test module is used for receiving corresponding initiating explosive device ignition signals.
Further, the firing signal emission time is different for each initiating explosive device.
Further, the indicator lamp is an LED lamp.
Compared with the prior art, the application has at least one of the following beneficial effects:
the aircraft electrical testing device disclosed by the application has the following advantages:
(1) The test of main functional signals such as aircraft simulation thermal battery power supply, initiating explosive device signal acquisition, fuse insurance state inspection and the like can be realized. The electric testing device is simple to realize, mainly comprises hardware such as a resistor, a switch, an indicator light, a relay and the like, has low cost, and can effectively measure important electric signals of the aircraft;
(2) The test process is simple, and the passing of the test process can be determined by the lighting of the indicator lamp;
(3) Meanwhile, the electrical testing device is convenient to use, can be directly integrated in the whole system test of the aircraft for measurement, and does not need to be installed in the aircraft;
(4) The connection relation with the electric system of the aircraft is simple, the disassembly is convenient, and the carrying is convenient; the cost of electrical testing of large batches of aircraft is reduced.
In the application, the technical schemes can be mutually combined to realize more preferable combination schemes. Additional features and advantages of the application will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the application. The objectives and other advantages of the application may be realized and attained by the structure particularly pointed out in the written description and drawings.
Drawings
The drawings are only for purposes of illustrating particular embodiments and are not to be construed as limiting the application, like reference numerals being used to refer to like parts throughout the several views.
Fig. 1 is a schematic structural diagram of an aircraft electrical testing apparatus according to an embodiment of the present application.
Detailed Description
The following detailed description of preferred embodiments of the application is made in connection with the accompanying drawings, which form a part hereof, and together with the description of the embodiments of the application, are used to explain the principles of the application and are not intended to limit the scope of the application.
In one embodiment of the present application, an electrical test device for an aircraft is disclosed, the schematic structure of which is shown in fig. 1, the device comprising: a power supply module, and a plurality of functional test modules; wherein,,
each function test module is used for receiving corresponding function signals in the aircraft electrical system and electrically testing the received function signals;
the power supply module is used for supplying power to each function test module;
the function test module comprises an initiating explosive device ignition test module, a simulated thermal battery test module and a fuse insurance state check module.
Compared with the prior art, the aircraft electrical testing device provided by the embodiment does not need to be installed inside an aircraft, and can realize testing only by receiving corresponding functional signals in an aircraft electrical system. Typically, functional signals in an aircraft electrical system may be led through wires into a test device to perform electrical testing of the signals. Therefore, the aircraft electrical testing device disclosed by the embodiment can test the aircraft electrical index outside the aircraft, and has important application value for reducing cost for batch development of the aircraft.
Preferably, the initiating explosive device ignition test module is a relay closed-loop control circuit; the relay closed-loop control circuit consists of a relay, diodes D1 and D2, a resistor R1 and an indicator light LED1, wherein the relay is provided with a normally open switch; wherein,,
one end of a normally open switch of the relay is connected with the positive output end of the power supply module, and the other end of the normally open switch, the negative electrode of the diode D1 and one end of the resistor R1 are all connected with the control end of the relay; the anode of the diode D1 is a signal input end of a relay closed-loop control circuit; the other end of the resistor R1 is connected with the positive electrode of the indicator light LED1, and the negative electrode of the indicator light LED1 and the output end of the relay are both connected with the negative output end of the power supply module;
a diode D2 is also reversely connected between the control end and the output end of the relay;
in the initiating explosive device ignition test module, a signal input end of a relay closed-loop control circuit is used as a signal input end of the initiating explosive device ignition test module and used for receiving an initiating explosive device ignition signal output by an aircraft electrical system.
In fig. 1, since the initiating explosive device ignition test module C and the analog thermal battery test module B each include a relay closed-loop control circuit with the same structure, the symbols representing the hardware used in the relay closed-loop control circuit are common symbols. However, when the hardware components in the respective parts are identified by different reference numerals in fig. 1, the correspondence relationship can be confirmed by fig. 1:
illustratively, in the initiating explosive device ignition test module C, the diode D1 is expressed as DC1, and is obtained by adding the identification of the module C and adjusting the sign on the basis of the original D1; the resistor is RC1, namely the mark of the module C is increased on the basis of the original R1.
Here, under the condition that the power supply module works normally, the test process of the initiating explosive device ignition test module C is described as follows:
when an ignition signal of the initiating explosive device 1 is received (the voltage of the signal is larger than the conduction voltage of the diode DC 1), the indicator lamp LEDC1 is lightened so as to remind relevant staff that the ignition signal test of the initiating explosive device 1 is passed; meanwhile, the coil of the relay KC is powered on, and the control end of the relay KC is connected with the output end; at this time, the normally open switch of the relay KC is closed, and the voltages at the terminals C1, C2, C3, and C4 in fig. 1 are all clamped to the voltage at the positive output terminal of the power supply module, so that the indicator lamp LEDC1 will maintain a normally on state. Therefore, although the initiating explosive device ignition signal is a short-time instant signal, based on the setting of the initiating explosive device ignition test module in this embodiment, the indicator lamp LEDC1 can be in a normally-on state to represent that the initiating explosive device 1 ignition signal is tested.
In addition, it should be noted that, in the present embodiment, the diode DC1 is mainly used for reverse cut-off; the diode DC2 has the reverse cut-off function and simultaneously has the function of releasing the electromotive force of the relay coil when the power is off.
In addition, the number of the initiating explosive device ignition signals of the aircraft may be multiple, so in the testing device in this embodiment, a plurality of initiating explosive device ignition testing modules may be included, and each initiating explosive device ignition testing module is configured to receive a corresponding initiating explosive device ignition signal; since the aircraft electrical system cannot emit a plurality of initiating explosive device ignition signals simultaneously, in this embodiment, the emission time of each initiating explosive device ignition signal is different. The initiating explosive device ignition test module D in fig. 1 is another initiating explosive device ignition test module corresponding to the initiating explosive device ignition signal.
Preferably, the analog thermal battery test module includes: the relay closed-loop control circuit has the same structure as the relay closed-loop control circuit of the initiating explosive device ignition test module, and simulates a thermal battery power supply circuit; wherein,,
the simulated thermal battery power supply loop consists of a switch SB1, a resistor RB1 and an indicator lamp LEDB 1;
one end of the switch SB1 is connected with the other end of the normally open switch, the other end of the switch SB1 is connected with one end of the resistor RB1, the other end of the resistor RB1 is connected with the positive pole of the indicator lamp LEDB1, and the negative pole of the indicator lamp LEDB1 is grounded;
the other end of the switch SB1 is also used as a power supply anode of the simulated thermal battery, and the negative output end of the power supply module is used as a power supply cathode of the simulated thermal battery; the positive electrode and the negative electrode of the power supply of the simulated thermal battery are connected with the two ends of the thermal battery in the electric system of the aircraft in parallel;
in the analog thermal battery test module, the signal input end of the other relay closed-loop control circuit is used as the signal input end of the analog thermal battery test module and is used for receiving the analog thermal battery activation signal output by the aircraft electrical system.
In fig. 1, the analog thermal battery test module B completes the analog thermal battery power supply output function. Because the thermal battery is a disposable product, in the normal test of the aircraft, the thermal battery cannot be integrated into the whole aircraft loop for testing, and the function of the simulated thermal battery must exist.
Here, under the condition that the power supply module works normally, the test process of the analog thermal battery test module B is described as follows:
when receiving the analog thermal battery activation signal (the voltage of the signal is greater than the on voltage of the diode DC 1), the indicator lamp LEDB2 is kept continuously on based on the operation of the relay closed-loop control circuit described above, so that the analog thermal battery activation signal is tested.
In addition, in order to be more fit with the actual working process of the aircraft electrical system, in the simulated thermal battery test module B, a switch SB1 can be closed, at this time, the voltage of the power supply anode of the simulated thermal battery is the voltage at the endpoint B5, and the voltage of the power supply cathode of the simulated thermal battery is the same as the voltage of the negative output end of the power supply module; at this time, the positive electrode and the negative electrode of the power supply of the simulation thermal battery are connected with two ends of the thermal battery in parallel in the electric system of the aircraft, and are used for simulating the working process of continuously supplying power for replacing the thermal battery, and the indicator lamp LEDB1 can be used for indicating the power supply indication of the simulation main battery so as to represent the replacement process.
Preferably, the fuse insurance status checking module comprises a resistor RE1 and an indicator lamp LEDE1; the signal input end of the fuse insurance state checking module is connected to the negative electrode of the indicator lamp LEDE1, the positive electrode of the indicator lamp LEDE1 is connected with one end of a resistor RE1, and the other end of the resistor RE1 is connected with the positive output end of the power supply module; the signal input end of the fuse insurance state checking module is used for receiving a fuse insurance state checking signal output by the electric system of the aircraft.
In fig. 1, a fuse cutout state checking module E is configured to complete fuse cutout state checking measurement, and the fuse cutout state checking signal is a low level signal. The endpoint E1 is a high level signal, the resistances of the indicator lamp LERE1 and RE1 are designed between the endpoint E1 and the endpoint E1, when the fuse safety state check signal XE1 comes, a forward voltage drop is formed between the endpoint E1 and the endpoint E1, and the indicator lamp LERE1 is lightened to indicate that the fuse safety state signal is normal.
Preferably, the power supply module a includes: fuse FA1, switches SA1-SA2, resistors RA1-RA2 and indicator lights LEDA1-LEDA 2; the positive input end of the power supply module is sequentially connected with a fuse FA1 and a switch SA1 in series, and then is connected with one end of a switch SA2, and the other end of the switch SA2 is used as the positive output end of the power supply module; the negative input end of the power supply module is used as the negative output end of the power supply module; one end of the switch SA1 connected with the switch SA2 is also connected with one end of a resistor RA1, the other end of the resistor RA1 is connected with the positive electrode of an indicator lamp LEDA1, and the negative electrode of the indicator lamp LEDA1 is connected with the negative input end of the power supply module; the other end of the switch SA2 is also connected with one end of a resistor RA2, the other end of the resistor RA2 is connected with the positive electrode of an indicator lamp LEDA2, and the negative electrode of the indicator lamp LEDA2 is connected with the negative input end of the power supply module.
Preferably, an ammeter is also connected in series between the switch SA2 and the switch SA 3; and a voltmeter is also connected in parallel between one end of the switch SA2 connected with the switch SA3 and the negative input end of the power supply module. It should be noted that, the voltmeter and the ammeter are designed herein, so that when the signal test is performed, especially when the analog thermal battery activates the signal test, the ammeter and the voltmeter can be checked to more clearly understand the current and voltage information in the current test process, so as to more fully understand the current test situation.
When the power supply module a is used for supplying power, the switches SA1 and SA2 are turned off, and at this time, the indicator lamps LEDA1 and LEDA2 are turned on to indicate that the power supply module works normally. Meanwhile, by sequentially designing the fuse FA1 and the switch SA1 between XA1 and A1, the high current burn-out test device can be prevented.
Preferably, the device further comprises a power supply test module for performing an auxiliary voltage test on the positive output terminal and the negative input terminal of the power supply module. Illustratively, the power test module F draws power +out to XF1 and power-out to XF2 of the test equipment as an electrical test equipment auxiliary checkpoint to improve the inspectability of the test equipment. The auxiliary voltage test may include a ground signal test, for example. For example, after switches SA1, SA2 are both closed, when the sensing voltmeter shows abnormal voltage, the multimeter can be used to measure the voltage of module F for verification and troubleshooting.
The indicator light in the device of the embodiment may be an LED light. In addition, in this embodiment, the resistors are all used in series with the indicator lamp, so that a matched resistor model can be selected according to parameters and power supply voltage of the indicator lamp.
In summary, the aircraft electrical testing device provided in this embodiment has the following advantages:
(1) The test of main functional signals such as aircraft simulation thermal battery power supply, initiating explosive device signal acquisition, fuse insurance state inspection and the like can be realized. The electric testing device is simple to realize, mainly comprises hardware such as a resistor, a switch, an indicator light, a relay and the like, has low cost, and can effectively measure important electric signals of the aircraft;
(2) The test process is simple, and the passing of the test process can be determined by the on-off of the indicator lamp;
(3) The electrical testing device is convenient to use, can be directly integrated in the whole system test of the aircraft for measurement, and does not need to be installed in the aircraft;
(4) The connection relation with the electric system of the aircraft is simple, the disassembly is convenient, and the carrying is convenient; the cost of electrical testing of large batches of aircraft is reduced.
Those skilled in the art will appreciate that all or part of the flow of the methods of the embodiments described above may be accomplished by way of a computer program to instruct associated hardware, where the program may be stored on a computer readable storage medium. Wherein the computer readable storage medium is a magnetic disk, an optical disk, a read-only memory or a random access memory, etc.
The present application is not limited to the above-mentioned embodiments, and any changes or substitutions that can be easily understood by those skilled in the art within the technical scope of the present application are intended to be included in the scope of the present application.
Claims (9)
1. An aircraft electrical test device, the device comprising: a power supply module, and a plurality of functional test modules; wherein,,
each functional test module is used for receiving corresponding functional signals in the aircraft electrical system and electrically testing the received functional signals;
the power supply module is used for supplying power to each function test module;
the function test module comprises an initiating explosive device ignition test module, a simulated thermal battery test module and a fuse insurance state check module;
the initiating explosive device ignition test module is a relay closed-loop control circuit;
the relay closed-loop control circuit consists of a relay, diodes D1 and D2, a resistor R1 and an indicator light LED1, wherein the relay is provided with a normally open switch; wherein,,
one end of a normally open switch of the relay is connected with the positive output end of the power supply module, and the other end of the normally open switch, the negative electrode of the diode D1 and one end of the resistor R1 are all connected with the control end of the relay; the anode of the diode D1 is a signal input end of a relay closed-loop control circuit; the other end of the resistor R1 is connected with the positive electrode of the indicator light LED1, and the negative electrode of the indicator light LED1 and the output end of the relay are both connected with the negative output end of the power supply module;
a diode D2 is also reversely connected between the control end and the output end of the relay;
in the initiating explosive device ignition test module, a signal input end of a relay closed-loop control circuit is used as a signal input end of the initiating explosive device ignition test module and used for receiving an initiating explosive device ignition signal output by an aircraft electrical system.
2. The aircraft electrical test device of claim 1, wherein the analog thermal battery test module comprises: the relay closed-loop control circuit has the same structure as the relay closed-loop control circuit of the initiating explosive device ignition test module, and simulates a thermal battery power supply circuit; wherein,,
the simulated thermal battery power supply loop consists of a switch SB1, a resistor RB1 and an indicator lamp LEDB 1;
one end of the switch SB1 is connected with the other end of the normally open switch, the other end of the switch SB1 is connected with one end of the resistor RB1, the other end of the resistor RB1 is connected with the positive pole of the indicator lamp LEDB1, and the negative pole of the indicator lamp LEDB1 is grounded;
the other end of the switch SB1 is also used as a power supply anode of the simulated thermal battery, and the negative output end of the power supply module is used as a power supply cathode of the simulated thermal battery; the positive electrode and the negative electrode of the power supply of the simulated thermal battery are connected with the two ends of the thermal battery in the electric system of the aircraft in parallel;
in the analog thermal battery test module, the signal input end of the other relay closed-loop control circuit is used as the signal input end of the analog thermal battery test module and is used for receiving the analog thermal battery activation signal output by the aircraft electrical system.
3. The aircraft electrical test device of claim 2, wherein the fuse cutout module comprises a resistor RE1 and an indicator lamp LEDE1; wherein,,
the signal input end of the fuse insurance state checking module is connected to the negative electrode of the indicator lamp LEDE1, the positive electrode of the indicator lamp LEDE1 is connected with one end of a resistor RE1, and the other end of the resistor RE1 is connected with the positive output end of the power supply module;
the signal input end of the fuse insurance state checking module is used for receiving a fuse insurance state checking signal output by the electric system of the aircraft.
4. An aircraft electrical test device according to any one of claims 1-3, wherein the power supply module comprises: fuse FA1, switches SA1-SA2, resistors RA1-RA2 and indicator lights LEDA1-LEDA 2; wherein,,
the positive input end of the power supply module is sequentially connected with a fuse FA1 and a switch SA1 in series, and then is connected with one end of a switch SA2, and the other end of the switch SA2 is used as the positive output end of the power supply module; the negative input end of the power supply module is used as the negative output end of the power supply module;
one end of the switch SA1 connected with the switch SA2 is also connected with one end of a resistor RA1, the other end of the resistor RA1 is connected with the positive electrode of an indicator lamp LEDA1, and the negative electrode of the indicator lamp LEDA1 is connected with the negative input end of the power supply module;
the other end of the switch SA2 is also connected with one end of a resistor RA2, the other end of the resistor RA2 is connected with the positive electrode of an indicator lamp LEDA2, and the negative electrode of the indicator lamp LEDA2 is connected with the negative input end of the power supply module.
5. The aircraft electrical test device according to claim 4, wherein,
an ammeter is also connected in series between the switch SA2 and the switch SA 3;
and a voltmeter is also connected in parallel between one end of the switch SA2 connected with the switch SA3 and the negative input end of the power supply module.
6. The aircraft electrical test device of claim 5, further comprising a power test module for performing auxiliary voltage testing on a positive output, a negative input of the power supply module.
7. The aircraft electrical test device of claim 6, wherein the auxiliary voltage test comprises a ground signal test.
8. The aircraft electrical test device of claim 1, wherein the device comprises a number of initiating explosive device ignition test modules; each initiating explosive device ignition test module is used for receiving corresponding initiating explosive device ignition signals.
9. The aircraft electrical test device of claim 8, wherein the firing signal is emitted at different times for each initiating explosive device.
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