CN114217599B - Aircraft ground energy control console - Google Patents
Aircraft ground energy control console Download PDFInfo
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- CN114217599B CN114217599B CN202111524968.0A CN202111524968A CN114217599B CN 114217599 B CN114217599 B CN 114217599B CN 202111524968 A CN202111524968 A CN 202111524968A CN 114217599 B CN114217599 B CN 114217599B
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course or altitude of land, water, air, or space vehicles, e.g. automatic pilot
- G05D1/0005—Control of position, course or altitude of land, water, air, or space vehicles, e.g. automatic pilot with arrangements to save energy
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
- B64D47/02—Arrangements or adaptations of signal or lighting devices
Abstract
The application discloses an aircraft ground energy control console, belongs to the technical field of aircraft electrical systems, and solves the problems of high cost and poor control intuitiveness of the existing aircraft ground energy control console. The ground energy console of the aircraft comprises a signal detection-control module and a power supply module; 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.
Description
Technical Field
The application relates to the technical field of aircraft electrical systems, in particular to an aircraft ground energy control console.
Background
In the ground joint debugging stage, the electric system of the aircraft needs to transmit control and test flows for multiple times for verification, and the process relates to power supply and distribution signals, initiating explosive devices, flight zero signals, analog battery activation signals and the like, and the detection process of the signals directly affects the verification link of the whole flow system of the aircraft.
Because the signals are distributed at different stages in the operation process of the aircraft electrical system, a technician can conveniently and intuitively and rapidly determine whether the signals are detected, and meanwhile, the cost of a detection control console can be reduced, so that the method is a technical problem which is urgently needed to be solved at present.
Disclosure of Invention
In view of the above analysis, the embodiment of the application aims to provide an aircraft ground energy control console, which is used for solving the problems of higher cost and poorer control intuitiveness of the existing aircraft ground energy control console.
The embodiment of the application discloses an aircraft ground energy control console, which comprises a signal detection-control module and a power supply module; wherein, the liquid crystal display device comprises a liquid crystal display device,
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.
Based on the scheme, the application also makes the following improvements:
further, one or more of the signal detection-control modules are included in the aircraft ground energy console.
Further, the manner of indicating the sustained response is continuous lighting of the indicator light.
Further, the flight zero signal detection submodule comprises a resistor RD1 and an indicator lamp LEDD1; wherein, the liquid crystal display device comprises a liquid crystal display device,
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.
Further, 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, the liquid crystal display device comprises a liquid crystal display device,
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.
Further, 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 liquid crystal display device comprises a liquid crystal display device,
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.
Further, the signal detection-control module further comprises a standby signal detection sub-module, wherein the standby signal detection sub-module comprises a resistor RF1 and an indicator lamp LEDF1; wherein, the liquid crystal display device comprises a liquid crystal display device,
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.
Further, the power supply module includes: fuse FA1, switches SA1-SA2, resistors RA1-RA2 and indicator lights LEDA1-LEDA 2; wherein, the liquid crystal display device comprises a liquid crystal display device,
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 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.
Further, the control console 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.
Compared with the prior art, the application has at least one of the following beneficial effects:
the aircraft ground energy console disclosed by the application has the following advantages:
(1) Real-time detection of an aircraft simulated thermal battery activation signal, an initiating explosive device ignition signal and a flight zero signal can be realized, and detection result indication of the signals is realized in a continuous response mode;
(2) The ground energy console of the aircraft 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 detect and indicate important electrical signals of the aircraft; in addition, the control console is convenient to detach and high in portability.
(3) The operation process of the control desk is simple, and the related signal can be determined to be detected through continuous lighting of the indicator lamp.
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 diagram of an aircraft ground energy console according to an embodiment of the present application;
FIG. 2 is a schematic view of another aircraft ground energy console according to an embodiment of the present application;
fig. 3 is a schematic view of an operation panel 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.
The application discloses an aircraft ground energy console, the structure of which is shown in fig. 1 and 2, wherein the console comprises a signal detection-control module and a power supply module; wherein, the liquid crystal display device comprises a liquid crystal display device,
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.
Preferably, one or more of said signal detection-control modules are included in said aircraft ground energy console. When the ground energy console of the aircraft comprises a plurality of signal detection-control modules, detection of related signals of a plurality of aircrafts can be achieved at the same time, and control efficiency of the console can be effectively improved. However, in order to ensure the control quality, a maximum of 4 signal detection-control modules are generally provided.
To facilitate a more intuitive understanding by the skilled person that the relevant signal has been detected, the present embodiment preferably provides a way of indicating the sustained response: the indicator light is continuously turned on. Of course, other response modes can also realize the reminding function, such as a buzzer and the like, and the intuitiveness of the indicator lamp is best.
Preferably, in this embodiment, 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; one end of a normally open switch of the relay is connected with a 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 a 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.
In fig. 2, since the initiating explosive device ignition signal detection submodule C and the analog thermal battery signal detection and control submodule B each include a relay closed-loop control circuit, the symbols of the hardware used in the relay closed-loop control circuit are common symbols. However, when implemented in fig. 2, in order to facilitate distinguishing the hardware components in each part, the corresponding relationship can be confirmed by fig. 2 by distinguishing the hardware components by different reference numerals:
illustratively, in the initiating explosive device ignition signal detection submodule C, a diode is expressed as DC1, and is obtained by adding the identification of the module C on the basis of the original V1 and adjusting a symbol; 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 signal detection sub-module C is described as follows:
when an ignition signal of the initiating explosive device 1 is detected (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. 2 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 signal detection submodule 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.
Preferably, the analog thermal battery signal detection and control submodule includes: the relay closed-loop control circuit is used for simulating a thermal battery power supply loop; wherein, the liquid crystal display device comprises a liquid crystal display device,
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;
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.
In fig. 2, the analog thermal battery signal detection and control submodule 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 signal detection and control sub-module B is described as follows:
when the analog thermal battery activation signal (the voltage of which is greater than the on voltage of the diode DC 1) is detected, 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 attached to the actual working process of the aircraft electrical system, in the analog thermal battery signal detection and control submodule B, a switch SB1 can be closed, at this time, the voltage of the power supply anode of the analog thermal battery is the voltage at the endpoint B5, and the voltage of the power supply cathode of the analog 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 flight zero signal detection submodule comprises a resistor RD1 and an indicator lamp LEDD1; the signal input end of the flight zero signal detection sub-module 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.
In fig. 2, the zero-flight signal detection sub-module D is used to complete the detection and continuous response of the zero-flight signal. The zero-of-flight signal is a high signal. The endpoint D1 is a low level signal, the resistances of the indicator lights LERD1 and RD1 are designed between the endpoint D1 and the XD1, when the flight zero signal XD1 comes, a forward voltage drop is formed between the endpoint D1 and the endpoint D1, and the indicator light LERD1 is lightened to indicate that the flight zero signal is detected.
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 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. 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 apparatus further comprises a power supply test module E 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 E draws the power +out to XE1 and the power-out to XE2 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 voltage anomalies, the multimeter can be used to measure the voltage of module E for verification and troubleshooting.
In addition, to boost the number of controllable signals of the console, in this embodiment, the signal detection-control module further includes a standby signal detection sub-module, which includes a resistor RF1 and an indicator lamp LEDF1; 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.
Illustratively, during different aircraft design processes, the standby signal warranty status check signal may be active high or active low; at this time, a specific connection relationship can be determined according to the high-low level property of the protection state check signal; for example, the number of the cells to be processed,
when the pilot protection state check signal is valid at a high level, connecting the output end of the standby signal with the standby signal port XF1, and connecting the ground end of the standby signal with the standby signal port XF2, wherein at the moment, when the pilot protection state check signal at the high level is received, the indicator lamp LEDF1 is lighted;
when the pilot protection state check signal is valid at a low level, the output end of the standby signal is connected to the standby signal port XF2, and the ground end of the standby signal is connected to the standby signal port XF1, and at this time, the indicator lamp LEDF1 is turned on when the pilot protection state check signal at a low level is received.
The application range of the control console can be effectively expanded through the mode. It should be further noted that the ground of the standby signal may not be the same ground as the negative output of the power supply module, and therefore, the ground of the standby signal needs to be properly connected according to the specific situation of the standby signal.
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.
Fig. 3 is a schematic diagram of an operation panel according to an embodiment of the present application, taking a control four as an example. The devices on the operating panel correspond to fig. 2. Through the operation panel that provides the control cabinet, can make things convenient for the real-time detection condition of each signal that technicians know directly perceivedly more, effectively promote control efficiency.
In summary, the ground energy console for an aircraft provided in this embodiment has the following advantages:
(1) The method can realize the detection of the aircraft simulated thermal battery activation signal, the initiating explosive device ignition signal and the flight zero signal, and realize the signal detection result indication in a continuous response mode;
(2) The ground energy console of the aircraft 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 detect and indicate important electrical signals of the aircraft; in addition, the control console is convenient to detach and high in portability.
(3) The operation process of the control desk is simple, and the related signal can be determined to be detected through continuous lighting of the indicator lamp.
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 ground energy console, wherein the console comprises a signal detection-control module and a power supply module; wherein, the liquid crystal display device comprises a liquid crystal display device,
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, the liquid crystal display device comprises a liquid crystal display device,
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 liquid crystal display device comprises a liquid crystal display device,
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 liquid crystal display device comprises a liquid crystal display device,
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 liquid crystal display device comprises a liquid crystal display device,
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 liquid crystal display device comprises a liquid crystal display device,
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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111524968.0A CN114217599B (en) | 2021-12-14 | 2021-12-14 | Aircraft ground energy control console |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111524968.0A CN114217599B (en) | 2021-12-14 | 2021-12-14 | Aircraft ground energy control console |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114217599A CN114217599A (en) | 2022-03-22 |
| CN114217599B true CN114217599B (en) | 2023-10-17 |
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