CN114217599B - An aircraft ground energy console - Google Patents

Abstract

The invention discloses an aircraft ground energy console, which belongs to the technical field of aircraft electrical systems and solves the problems of high cost and poor intuitive control of existing aircraft ground energy consoles. The aircraft ground energy console includes a signal detection-control module and a power supply module; the signal detection-control module includes: a simulated thermal battery signal detection and control sub-module, used to issue an instruction detection when the simulated thermal battery activation signal is detected To simulate the continuous response of the thermal battery signal, and simulate the thermal battery to power the aircraft; the pyrotechnics ignition signal detection sub-module is used to send out a continuous response indicating that the pyrotechnics ignition signal is detected when the pyrotechnics ignition signal is detected ; The flight zero signal detection sub-module is used to send a continuous response indicating that the flight zero signal is detected when the flight zero signal is detected; the power supply module is used to supply power to the signal detection-control module.

Description

An aircraft ground energy console

Technical field

The present invention relates to the technical field of aircraft electrical systems, and in particular to an aircraft ground energy console.

Background technique

During the ground joint debugging stage, the aircraft electrical system requires multiple launch control and test processes for verification. This process involves power supply and distribution signals, pyrotechnics, flight zero-point signals, simulated battery activation signals, etc. The detection process of these signals directly affects to the verification of the entire aircraft process system.

Since the above signals are distributed at different stages during the operation of the aircraft electrical system, how to facilitate technicians to intuitively and quickly determine whether the above signals are detected and at the same time reduce the cost of the detection console is an urgent technical problem that needs to be solved.

Contents of the invention

In view of the above analysis, embodiments of the present invention aim to provide an aircraft ground energy console to solve the problems of high cost and poor intuitive control of existing aircraft ground energy consoles.

An embodiment of the present invention discloses an aircraft ground energy console, which includes a signal detection-control module and a power supply module; wherein,

The signal detection-control module includes:

The simulated hot battery signal detection and control submodule is used to send a continuous response indicating that the simulated hot battery signal is detected when the simulated hot battery activation signal is detected, and to simulate the hot battery to power the aircraft;

The pyrotechnics ignition signal detection submodule is used to send a continuous response indicating that the pyrotechnics ignition signal is detected when the pyrotechnics ignition signal is detected;

The flight zero signal detection submodule is used to send a continuous response indicating that the flight zero signal is detected when the flight zero signal is detected;

The power supply module is used to supply power to the signal detection-control module.

On the basis of the above solution, the present invention also makes the following improvements:

Further, the aircraft ground energy console includes one or more of the signal detection and control modules.

Further, the method of indicating the continuous response is continuous lighting of the indicator light.

Further, the flight zero signal detection sub-module includes a resistor RD1 and an indicator light LEDD1; where,

The signal input end of the flight zero signal detection sub-module is connected to one end of the resistor RD1, the other end of the resistor RD1 is connected to the positive pole of the indicator LEDD1, and the negative pole of the indicator LEDD1 is connected to the negative output end of the power supply module;

The signal input end of the flight zero signal detection submodule is used to receive the flight zero signal output by the aircraft electrical system.

Further, the pyrotechnics ignition signal detection sub-module is a relay closed-loop control circuit;

The relay closed-loop control circuit is composed of a relay, diodes V1-V2, resistor R1 and indicator light LED1, and the relay has a normally open switch; wherein,

One end of the normally open switch of the relay is connected to the positive output end of the power supply module. The other end of the normally open switch, the cathode of the diode V1 and one end of the resistor R1 are all connected to the control end of the relay; the anode of the diode V1 is the signal input end; the resistor R1 The other end is connected to the positive pole of the indicator light LED1, and the negative pole of the indicator light LED1 and the output end of the relay are connected to the negative output end of the power supply module;

A diode V2 is also connected in reverse between the control terminal and the output terminal of the relay;

The signal input end of the pyrotechnics ignition signal detection submodule is used to receive the pyrotechnics ignition signal output from the aircraft electrical system.

Further, the simulated thermal battery signal detection and control sub-module includes: another relay closed-loop control circuit with the same structure as the relay closed-loop control circuit in the pyrotechnics ignition test module, and a simulated thermal battery power supply circuit; wherein,

The simulated hot battery power supply loop is composed of switch SB1, resistor RB1 and indicator light LEDB1;

One end of the switch SB1 is connected to the other end of the normally open switch, the other end of the switch SB1 is connected to one end of the resistor RB1, the other end of the resistor RB1 is connected to the positive electrode of the indicator light LEDB1, and the negative electrode of the indicator light LEDB1 is grounded;

The other end of the switch SB1 also serves as the positive electrode of the simulated thermal battery power supply, and the negative output end of the power supply module serves as the negative electrode of the simulated thermal battery power supply; the positive and negative electrodes of the simulated thermal battery power supply are connected in parallel with both ends of the thermal battery in the aircraft electrical system to simulate Thermal batteries power the aircraft;

The signal input end of the analog hot battery signal detection and control submodule is used to receive the simulated hot battery activation signal output from the aircraft electrical system.

Further, the signal detection-control module also includes a backup signal detection sub-module, which includes a resistor RF1 and an indicator light LEDF1; wherein,

The backup signal port XF1 is connected to one end of the resistor RF1, the other end of the resistor RF1 is connected to the positive pole of the indicator LEDF1, and the negative pole of the indicator LEDF1 is connected to the backup signal port XF2;

According to the high and low level properties of the backup signal, determine the connection relationship between the output terminal of the backup signal, the ground terminal of the backup signal, the backup signal port XF1, and the backup signal port XF2, so that when the backup signal is received, the indicator LEDF1 is Light up.

Further, the power supply module includes: fuse FA1, switches SA1-SA2, resistors RA1-RA2, and indicator lights LEDA1-LEDA2; wherein,

The positive input end of the power supply module is connected in series with fuse FA1 and switch SA1, and then connected to one end of switch SA2. The other end of switch SA2 serves as the positive output end of the power supply module; the negative input end of the power supply module serves as the negative output end of the power supply module. ;

One end of the switch SA1 and the switch SA2 is also connected to one end of the resistor RA1, the other end of the resistor RA1 is connected to the positive pole of the indicator LEDA1, and the negative pole of the indicator LEDA1 is connected to the negative input end of the power supply module;

The other end of the switch SA2 is also connected to one end of the resistor RA2, the other end of the resistor RA2 is connected to the positive electrode of the indicator LEDA2, and the negative electrode of the indicator LEDA2 is connected to the negative input terminal of the power supply module.

Furthermore, an ammeter is connected in series between switch SA1 and switch SA2;

A voltmeter is also connected in parallel between one end of the switch SA1 and the switch SA2 and the negative input end of the power supply module.

Further, the console also includes a power supply test module for performing auxiliary voltage testing on the positive output terminal and negative input terminal of the power supply module.

Compared with the prior art, the present invention can achieve at least one of the following beneficial effects:

The aircraft ground energy control console disclosed by the present invention has the following advantages:

(1) Able to realize real-time detection of aircraft simulated thermal battery activation signals, pyrotechnics ignition signals and flight zero-point signals, and achieve signal detection result indication through continuous response;

(2) The aircraft ground energy console is simple to implement. It is mainly composed of some resistors, switches, indicator lights, relays and other hardware. It is low-cost, but can effectively detect and indicate important electrical signals of the aircraft; in addition, the console is easy to disassemble. , highly portable.

(3) The working process of the console is simple. It can be confirmed that the relevant signal has been detected by the continuous lighting of the indicator light.

In the present invention, the above technical solutions can also be combined with each other to achieve more preferred combination solutions. Additional features and advantages of the invention will be set forth in the description which follows, and in part, some advantages will be apparent from the description, or may be learned by practice of the invention. The objectives and other advantages of the invention may be realized and obtained by the disclosure particularly pointed out in the description and drawings.

Description of the drawings

The drawings are for the purpose of illustrating specific embodiments only and are not to be construed as limitations of the invention. Throughout the drawings, the same reference characters represent the same components.

Figure 1 is a schematic structural diagram of an aircraft ground energy control console disclosed in an embodiment of the present invention;

Figure 2 is a schematic structural diagram of another aircraft ground energy control console disclosed in an embodiment of the present invention;

Figure 3 is a schematic diagram of an operation panel disclosed in an embodiment of the present invention.

Detailed ways

The preferred embodiments of the present invention will be described in detail below with reference to the accompanying drawings. The drawings constitute a part of this application and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not intended to limit the scope of the present invention.

A specific embodiment of the present invention discloses an aircraft ground energy console. The structural schematic diagram is shown in Figures 1 and 2. The console includes a signal detection-control module and a power supply module; wherein,

The signal detection-control module includes:

The simulated hot battery signal detection and control submodule is used to send a continuous response indicating that the simulated hot battery signal is detected when the simulated hot battery activation signal is detected, and to simulate the hot battery to power the aircraft;

The pyrotechnics ignition signal detection submodule is used to send a continuous response indicating that the pyrotechnics ignition signal is detected when the pyrotechnics ignition signal is detected;

The flight zero signal detection submodule is used to send a continuous response indicating that the flight zero signal is detected when the flight zero signal is detected;

The power supply module is used to supply power to the signal detection-control module.

Preferably, one or more of the signal detection and control modules are included in the aircraft ground energy console. When the aircraft ground energy console contains multiple signal detection and control modules, it can detect related signals of multiple aircraft at the same time, which can effectively improve the control efficiency of the console. However, in order to ensure the quality of control, a maximum of four signal detection-control modules are generally set up.

In order to facilitate technicians to more intuitively understand that the relevant signal has been detected, preferably, this embodiment provides a way of indicating the continuous response: continuous lighting of an indicator light. Of course, other response methods can also realize the reminder function, such as buzzers, etc. The indicator light is the most intuitive.

Preferably, in this embodiment, the pyrotechnics ignition signal detection sub-module is a relay closed-loop control circuit; the relay closed-loop control circuit is composed of a relay, diodes V1-V2, resistor R1 and indicator light LED1. The relay It has a normally open switch; one end of the normally open switch of the relay is connected to the positive output end of the power supply module, the other end of the normally open switch, the cathode of the diode V1 and one end of the resistor R1 are all connected to the control end of the relay; the diode V1 The positive terminal is the signal input terminal; the other end of the resistor R1 is connected to the positive terminal of the indicator LED1, the negative terminal of the indicator LED1 and the output terminal of the relay are both connected to the negative output terminal of the power supply module; there is also an inverse reaction between the control terminal and the output terminal of the relay. Connect diode V2; the signal input end of the pyrotechnics ignition signal detection submodule is used to receive the pyrotechnics ignition signal output from the aircraft electrical system.

In Figure 2, since the pyrotechnics ignition signal detection sub-module C and the analog thermal battery signal detection and control sub-module B both contain relay closed-loop control circuits, the above describes the representation of each hardware used in the relay closed-loop control circuit. Symbols are universal representation symbols. However, when implemented in Figure 2, in order to easily distinguish the hardware components in each part, they are distinguished by different numbers. The corresponding relationship can be confirmed through Figure 2:

For example, in the pyrotechnics ignition signal detection sub-module C, the diode is represented as DC1, which is obtained by adding the identification of module C on the basis of the original V1 and adjusting the symbol; the resistor is RC1, which is added on the basis of the original R1 Identification of module C.

Here, when the power supply module is working normally, the test process of pyrotechnics ignition signal detection sub-module C is explained as follows:

When the ignition signal of pyrotechnic product 1 is detected (the voltage of this signal is greater than the conduction voltage of diode DC1), the indicator light LEDC1 is lit to remind the relevant staff that the ignition signal of pyrotechnic product 1 has passed the test; at the same time, the relay KC The coil is energized, and the control terminal of the relay KC is connected to the output terminal; at this time, the normally open switch of the relay KC is closed, and the voltages of endpoints C1, C2, C3, and C4 in Figure 2 are all clamped to the voltage of the positive output terminal of the power supply module. , therefore, the indicator LEDC1 will remain on. Therefore, although the ignition signal of the pyrotechnic product is a short-term instantaneous signal, based on the settings of the ignition signal detection sub-module of the pyrotechnic product in this embodiment, the indicator light LEDC1 can be kept in a constant light state to represent the ignition signal test of the pyrotechnic product 1 complete.

In addition, it should be noted that in this embodiment, the diode DC1 is mainly used for reverse blocking; the diode DC2 not only has the reverse blocking function, but also has the function of releasing the electromotive force of the relay coil when the power is turned off.

Preferably, the simulated hot battery signal detection and control sub-module includes: the relay closed-loop control circuit, and a simulated hot battery power supply circuit; wherein,

The simulated hot battery power supply loop is composed of switch SB1, resistor RB1 and indicator light LEDB1;

One end of the switch SB1 is connected to the other end of the normally open switch, the other end of the switch SB1 is connected to one end of the resistor RB1, the other end of the resistor RB1 is connected to the positive electrode of the indicator light LEDB1, and the negative electrode of the indicator light LEDB1 is grounded;

The other end of the switch SB1 also serves as the positive electrode of the simulated thermal battery power supply, and the negative output end of the power supply module serves as the negative electrode of the simulated thermal battery power supply; the positive and negative electrodes of the simulated thermal battery power supply are connected in parallel with both ends of the thermal battery in the aircraft electrical system;

The signal input end of the analog hot battery signal detection and control submodule is used to receive the simulated hot battery activation signal output from the aircraft electrical system.

In Figure 2, the analog thermal battery signal detection and control submodule B completes the analog thermal battery power supply output function. Since the thermal battery is a one-time use product, during normal aircraft testing, the thermal battery cannot be incorporated into the entire aircraft circuit for testing, and the simulated thermal battery function must exist.

Here, when the power supply module is working normally, the test process of simulated hot battery signal detection and control sub-module B is explained as follows:

When the simulated hot battery activation signal is detected (the voltage of this signal is greater than the conduction voltage of diode DC1), based on the working process of the relay closed-loop control circuit introduced previously, the indicator light LEDB2 remains continuously lit to simulate a hot battery. The activation signal test is completed.

In addition, in order to better fit the actual working process of the aircraft electrical system, in the simulated thermal battery signal detection and control sub-module B, the switch SB1 can also be closed. At this time, the positive voltage of the simulated thermal battery power supply is the voltage at end point B5, and the analog The voltage of the negative electrode of the thermal battery power supply is the same as the voltage of the negative output terminal of the power supply module; at this time, the positive and negative electrodes of the simulated thermal battery power supply are connected in parallel with both ends of the thermal battery in the aircraft electrical system to simulate the working process of continuing to provide power in place of the thermal battery. The indicator light LEDB1 can be used to indicate the simulated main battery power supply indication to characterize the replacement process here.

Preferably, the flight zero signal detection sub-module includes a resistor RD1 and an indicator light LEDD1; wherein, the signal input end of the flight zero signal detection sub-module is connected to one end of the resistor RD1, and the other end of the resistor RD1 is connected to the positive electrode of the indicator light LEDD1, The negative pole of the indicator LEDD1 is connected to the negative output terminal of the power supply module; the signal input terminal of the flight zero signal detection sub-module is used to receive the flight zero signal output by the aircraft electrical system.

In Figure 2, the flight zero signal detection sub-module D is used to complete the detection and continuous response of the flight zero signal. The flight zero signal is a high level signal. Endpoint D1 is a low-level signal. Design indicator LEDD1 and RD1 resistors between XD1 and endpoint D1. When the flight zero signal XD1 comes, a forward voltage drop is formed between D1 and XD1, and the indicator light LERD1 lights up , to indicate that the flight zero signal is detected.

Preferably, the power supply module A includes: a fuse FA1, switches SA1-SA2, resistors RA1-RA2, and indicator lights LEDA1-LEDA2; wherein, the positive input end of the power supply module is connected in series with the fuse FA1, the switch SA1, and then the switch. One end of SA2 and the other end of switch SA2 serve as the positive output end of the power supply module; the negative input end of the power supply module serves as the negative output end of the power supply module; the end connected to switch SA1 and switch SA2 is also connected to one end of resistor RA1, resistor RA1 The other end of the switch SA2 is also connected to one end of the resistor RA2, and the other end of the resistor RA2 is connected to the positive electrode of the indicator LEDA2. The indicator light The negative pole of LEDA2 is connected to the negative input terminal of the power supply module.

Preferably, an ammeter is connected in series between the switch SA1 and the switch SA2; and a voltmeter is connected in parallel between one end of the switch SA1 and the switch SA2 and the negative input terminal of the power supply module. It should be noted that the purpose of designing the voltmeter and ammeter here is that when performing a signal test, especially during the simulated hot battery activation signal test, you can have a clearer understanding of the current test by viewing the ammeter and voltmeter. Current and voltage information during the process to have a more comprehensive understanding of the current test situation.

When the power supply module A is used for power supply, turn off the switches SA1 and SA2. At this time, the indicator lights LEDA1 and LEDA2 are lit to indicate that the power supply module is working normally. At the same time, by designing the fuse FA1 and the switch SA1 in sequence between XA1 and A1, it can prevent the test device from burning out due to high current.

Preferably, the device further includes a power supply test module E for performing auxiliary voltage testing on the positive output terminal and negative input terminal of the power supply module. For example, the power supply test module E leads the power supply + of the test equipment to XE1 and the power supply - to XE2 as an auxiliary check point of the electrical test equipment to improve the checkability of the test equipment. For example, the auxiliary voltage test may include a ground signal test. For example, when switches SA1 and SA2 are both closed and the voltmeter displays an abnormal voltage, you can use a multimeter to measure the voltage of module E for verification and troubleshooting.

In addition, in order to increase the number of controllable signals of the console, in this embodiment, the signal detection-control module also includes a backup signal detection sub-module, and the backup signal detection sub-module includes a resistor RF1 and an indicator light LEDF1; where , the backup signal port The connection relationship between the ground terminal of the backup signal and the backup signal port XF1 and the backup signal port XF2 is to realize that when the backup signal is received, the indicator LEDF1 is lit.

For example, in the design process of different aircraft, the standby signal fire status check signal may be active at high level or low level; at this time, it can be determined based on the high and low level properties of the fire status check signal. Specific connection relationships; for example,

When the high level of the fuse status check signal is active, connect the output end of the backup signal to the backup signal port XF1, and connect the ground end of the backup signal to the backup signal port XF2. At this time, when the high level fuse status is received When checking the signal, the indicator LEDF1 is lit;

When the fuse status check signal is active at low level, connect the output end of the backup signal to the backup signal port XF2, and connect the ground end of the backup signal to the backup signal port XF1. At this time, when a low level fuse is received When the status check signal is detected, the indicator LEDF1 is lit.

Through the above methods, the use scope of the console can be effectively expanded. It should also be noted that the ground terminal of the backup signal and the negative output terminal of the power supply module may not be the same ground. Therefore, the ground terminal of the backup signal needs to be connected to an appropriate ground according to the specific conditions of the backup signal.

For example, LED lights can be used as indicator lights in the device of this embodiment. In addition, in this embodiment, the resistors are used in series with the indicator light. Therefore, a matching resistor model can be selected according to the parameters of the indicator light and the supply voltage.

Figure 3 takes one control and four as an example to disclose a schematic diagram of the operation panel according to the embodiment of the present invention. The components on the operation panel correspond to Figure 2. By providing an operation panel of the console, it is more convenient for technicians to intuitively understand the real-time detection status of each signal, effectively improving control efficiency.

In summary, the aircraft ground energy control console provided by this embodiment has the following advantages:

(1) It can realize the detection of aircraft simulated thermal battery activation signal, pyrotechnics ignition signal and flight zero signal, and achieve signal detection result indication through continuous response;

(2) The aircraft ground energy console is simple to implement. It is mainly composed of some resistors, switches, indicator lights, relays and other hardware. It is low-cost, but can effectively detect and indicate important electrical signals of the aircraft; in addition, the console is easy to disassemble. , highly portable.

(3) The working process of the console is simple. It can be confirmed that the relevant signal has been detected by the continuous lighting of the indicator light.

Those skilled in the art can understand that all or part of the process of implementing the method of the above embodiments can be completed by instructing relevant hardware through a computer program, and the program can be stored in 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 above are only preferred specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto. Any person familiar with the technical field can easily think of changes or modifications within the technical scope disclosed in the present invention. All substitutions are within the scope of the present invention.

Claims (9)

1. An aircraft ground energy console, wherein the console comprises a signal detection-control module and a power supply module; wherein,,

the signal detection-control module includes:

the analog thermal battery signal detection and control submodule is used for sending out continuous response indicating detection of the analog thermal battery signal when the analog thermal battery activation signal is detected, and the analog thermal battery is used for supplying power to the aircraft;

the initiating explosive device ignition signal detection submodule is used for sending out continuous response indicating that the initiating explosive device ignition signal is detected when the initiating explosive device ignition signal is detected;

the flight zero signal detection sub-module is used for sending out continuous response indicating that the flight zero signal is detected when the flight zero signal is detected;

the power supply module is used for supplying power to the signal detection-control module;

the initiating explosive device ignition signal detection submodule is a relay closed-loop control circuit;

the relay closed-loop control circuit consists of a relay, diodes V1-V2, 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 V1 and one end of the resistor R1 are all connected with the control end of the relay; the anode of the diode V1 is a signal input end; 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 V2 is also reversely connected between the control end and the output end of the relay;

the signal input end of the initiating explosive device ignition signal detection submodule is used for receiving an initiating explosive device ignition signal output by an aircraft electrical system.

2. The aircraft ground energy console of claim 1, wherein one or more of said signal detection-control modules are included in said aircraft ground energy console.

3. An aircraft ground energy console according to claim 1 or claim 2, wherein the manner in which the sustained response is indicated is the sustained illumination of an indicator light.

4. An aircraft ground energy console as set forth in claim 3, wherein said zero-flight signal detection submodule includes a resistor RD1 and an indicator lamp LEDD1; wherein,,

the signal input end of the flight zero signal detection submodule is connected to one end of a resistor RD1, the other end of the resistor RD1 is connected with the positive electrode of an indicator lamp LEDD1, and the negative electrode of the indicator lamp LEDD1 is connected with the negative output end of the power supply module;

the signal input end of the flight zero signal detection submodule is used for receiving a flight zero signal output by an aircraft electrical system.

5. An aircraft ground energy console according to claim 3, wherein the analog thermal battery signal detection and control submodule 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 simulation thermal battery is used for supplying power to the aircraft;

the signal input end of the analog thermal battery signal detection and control sub-module is used for receiving an analog thermal battery activation signal output by an aircraft electrical system.

6. The aircraft ground energy console of claim 3, wherein the signal detection-control module further comprises a standby signal detection sub-module comprising a resistor RF1 and an indicator lamp LEDF1; wherein,,

the standby signal port XF1 is connected with one end of a resistor RF1, the other end of the resistor RF1 is connected with the positive electrode of an indicator lamp LEDF1, and the negative electrode of the indicator lamp LEDF1 is connected with the standby signal port XF2;

according to the high-low level property of the standby signal, the connection relation between the output end of the standby signal and the ground end of the standby signal and the standby signal ports XF1 and XF2 is determined, so that when the standby signal is received, the indicator lamp LEDF1 is lighted.

7. The aircraft ground energy console of claim 1, 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.

8. The aircraft ground energy console of claim 7, wherein,

an ammeter is also connected in series between the switch SA1 and the switch SA 2;

and a voltmeter is also connected in parallel between one end of the switch SA1 connected with the switch SA2 and the negative input end of the power supply module.

9. The aircraft ground energy console of claim 7 or 8, further comprising a power test module for performing auxiliary voltage tests on the positive and negative inputs of the power supply module.