CN107336841B - Information type aviation power supply vehicle - Google Patents
Information type aviation power supply vehicle Download PDFInfo
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- CN107336841B CN107336841B CN201710702053.1A CN201710702053A CN107336841B CN 107336841 B CN107336841 B CN 107336841B CN 201710702053 A CN201710702053 A CN 201710702053A CN 107336841 B CN107336841 B CN 107336841B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/36—Other airport installations
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60R—VEHICLES, VEHICLE FITTINGS, OR VEHICLE PARTS, NOT OTHERWISE PROVIDED FOR
- B60R16/00—Electric or fluid circuits specially adapted for vehicles and not otherwise provided for; Arrangement of elements of electric or fluid circuits specially adapted for vehicles and not otherwise provided for
- B60R16/02—Electric or fluid circuits specially adapted for vehicles and not otherwise provided for; Arrangement of elements of electric or fluid circuits specially adapted for vehicles and not otherwise provided for electric constitutive elements
- B60R16/023—Electric or fluid circuits specially adapted for vehicles and not otherwise provided for; Arrangement of elements of electric or fluid circuits specially adapted for vehicles and not otherwise provided for electric constitutive elements for transmission of signals between vehicle parts or subsystems
- B60R16/0231—Circuits relating to the driving or the functioning of the vehicle
- B60R16/0232—Circuits relating to the driving or the functioning of the vehicle for measuring vehicle parameters and indicating critical, abnormal or dangerous conditions
- B60R16/0234—Circuits relating to the driving or the functioning of the vehicle for measuring vehicle parameters and indicating critical, abnormal or dangerous conditions related to maintenance or repairing of vehicles
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/60—Other road transportation technologies with climate change mitigation effect
- Y02T10/72—Electric energy management in electromobility
Abstract
The invention discloses an informationized aviation power supply vehicle which comprises an automobile chassis and a power supply control cabin body, wherein an operation panel, a control module, an engine, a generator and a rectifying module are arranged in the power supply control cabin body, and the informationized aviation power supply vehicle is characterized by further comprising an information acquisition module and an information management module, wherein the operation panel 1 is connected with the control module, the engine, the generator and the rectifying module are sequentially connected, the control module and the information acquisition module are respectively connected with the engine, the generator and the rectifying module, and the information management module is connected with the control module and the information acquisition module.
Description
Technical Field
The invention relates to the field of aviation ground equipment, in particular to an informationized aviation power supply vehicle.
Background
The aviation power supply vehicle is aviation ground guarantee equipment integrating power generation and power supply functions, provides power supply guarantee for ground starting of an aircraft and ground inspection and maintenance of the aircraft, has the characteristics of good mobility and high reliability, and is one of important aviation ground guarantee equipment.
The common aviation power supply vehicle has no operation parameter memory capability, and when the aviation power supply vehicle fails to operate or special conditions occur in the use process of the aviation power supply vehicle, no original data capable of providing traceability is provided, so that great difficulty is caused to problem analysis and fault removal.
The operation power of the aviation power supply vehicle comes from a diesel engine, the maintenance of the diesel engine has strict operation hours, the common aviation power supply vehicle depends on an operator to record the operation hours, then a manual of the diesel engine is searched, the maintenance is carried out according to the manual requirement, and the maintenance management of the vehicle is inconvenient.
When the operation of the common aviation power supply vehicle fails, a fault indication can be sent out, but the fault location cannot be further carried out, the capability of guiding the vehicle to maintain is not provided, and the technical requirements on vehicle maintenance personnel are high.
Disclosure of Invention
The invention aims to solve the defects of the prior art and provide an informationized aviation power supply vehicle which has high reliability and high automation degree, can automatically position faults and automatically guide vehicle maintenance according to the self memory function.
The invention solves the technical problems as follows:
the utility model provides an information-based aviation power supply vehicle, includes the automobile chassis and the power control cabin body, be equipped with operating panel, control module, engine, generator, rectifier module in the power control cabin body, its characterized in that still includes information acquisition module and information management module, information acquisition module is to aviation power supply vehicle operating parameter's real-time collection and storage, information management module realizes aviation power supply vehicle operating parameter's playback, vehicle periodic maintenance suggestion and vehicle maintenance expert system etc. operating panel is connected with control module, engine, generator, rectifier module are connected in order, control module, information acquisition module are connected with engine, generator, rectifier module respectively, information management module is connected with control module, information acquisition module to reach through information acquisition module to aviation power supply vehicle operating parameter's real-time collection and storage, the rethread information management module realizes aviation power supply vehicle operating parameter's playback, vehicle periodic maintenance suggestion and vehicle maintenance expert system's function, when aviation power supply vehicle operation breaks down or the special condition takes place in the aviation power supply vehicle use, can be through operating parameter auxiliary analysis problem, the fault point locating problem when the fault finding has been needed to the substantial problem.
The control module comprises a VFD display, a memory, an A/D conversion module ADC1, a relay K2, a relay K3 and a relay K4, wherein a CAN interface is arranged on the engine; the generator comprises a current transformer T1, a current transformer T2, a current transformer T3, a current transformer T4, a current transformer T5 and a current transformer T6, the rectifying module comprises a current divider P1, a current divider P2, a transformer, a rectifying bridge group and a filter capacitor group, the information acquisition module comprises an A/D conversion module ADC2, a serial communication port COM1 and a serial communication port COM2, the information management module is provided with a touch screen display,
when the aviation power supply vehicle is in a static state, the operation switch S1 is pressed to send an operation instruction to the control module, the relay K1 acts to send a starting instruction to the engine, the engine is started to operate, and the aviation power supply vehicle enters an operation state; when the aviation power supply vehicle is in a running state, the operation switch S1 is pressed to send a stop instruction to the control module, the relay K1 acts to send a stop instruction to the engine, the engine stops running, and the aviation power supply vehicle enters a stop state;
when the engine operates at a rated rotation speed, the generator generates a three-phase alternating current power supply with 115V/200V and 400Hz frequency; the three-phase alternating current power supply with the voltage of 115V/200V and the frequency of 400Hz generated by the generator is used as an input power supply of the rectifying module; the transformer is used for reducing the voltage of the input three-phase alternating current power supply, the rectifier bridge group is used for carrying out full-bridge rectification on the reduced alternating current power supply, and the filter capacitor group is used for filtering the rectified power supply to obtain a direct current power supply with the voltage of 28V;
pressing down the operation switch S2, sending an alternating current I group power supply instruction to the control module, and enabling the relay K2 to be attracted to realize output power supply of the alternating current I group; when the operation switch S2 is pressed down again and an alternating current I group power-off instruction is sent to the control module, the relay K2 is reset, and the alternating current I group output power-off is realized;
and pressing the operation switch S3 to send an alternating current II group power supply instruction to the control module, and enabling the relay K3 to be attracted to realize the output power supply of the alternating current II group. When the operating switch S3 is pressed down again and an alternating current II group power-off instruction is sent to the control module, the relay K3 is reset, and the alternating current II group output power-off is realized;
pressing the operation switch S4 to send a direct current power supply instruction to the control module, and enabling the relay K4 to be attracted to realize direct current output power supply; when the operating switch S4 is pressed down again and a direct current power-off instruction is sent to the control module, the relay K4 is reset, and direct current output power-off is realized;
the control module is connected with the engine through the CAN interface, reads running data such as the rotating speed, the engine oil pressure, the cooling liquid temperature and the like of the engine, and displays the running data on the VFD display; the control module judges the current state of the aviation power supply vehicle according to the read rotating speed data of the engine, and when the aviation power supply vehicle is in an operating state, the control module automatically accumulates and records the operating hours of the aviation power supply vehicle; the control module judges whether the engine is normally operated according to the read engine oil pressure, cooling liquid temperature and other operation data, if the engine is abnormally operated, the control module displays engine fault information on the VFD display, the relay K1 resets to stop the engine operation, the aircraft and the aviation power supply vehicle are protected, and the engine fault information is recorded in the memory;
the control module acquires voltage and current signals of the generator and the rectifying module through an analog-to-digital (ADC) conversion module (ADC 1) and is used for monitoring the running state of the aviation power supply vehicle;
the control module is connected with an output terminal of the generator through an A/D conversion module ADC1, acquires an alternating voltage signal output by the generator, is connected with the current transformer T1, the current transformer T2 and the current transformer T3 through the A/D conversion module ADC1, acquires an alternating current signal output by the generator, and displays the acquired alternating voltage and current data on the VFD display; the control module judges whether the power generation and the power supply of the generator are normal according to the collected alternating voltage and current data, if the power generation and the power supply of the generator are abnormal, the control module displays alternating current fault information on the VFD display, relays K2 and K3 reset to stop alternating current power supply output, an aircraft and an aviation power supply vehicle are protected, and the alternating current fault information is recorded in the memory;
the control module is connected with an output terminal of the rectification module through an A/D conversion module ADC1, acquires a direct-current voltage signal output by the rectification module, is connected with the shunt P1 through the A/D conversion module ADC1, acquires a direct-current signal output by the rectification module, and displays the acquired direct-current voltage and current data on the VFD display; the control module judges whether rectification and output of the rectification module are normal according to the collected direct-current voltage and current data, if the rectification and output of the rectification module are abnormal, the control module displays direct-current fault information on the VFD display, the relay K4 resets to stop direct-current power supply output, an aircraft and an aviation power supply vehicle are protected, and the direct-current fault information is recorded in the memory.
The information acquisition module reads running data such as the rotating speed, the engine oil pressure, the cooling liquid temperature and the like of the engine through a CAN interface, and the information acquisition module stores the read running data of the engine through a memory;
the information acquisition module acquires voltage and current signals of the generator and the rectification module through the A/D conversion module ADC2, and is used for acquiring and storing operation data of the aviation power supply vehicle;
the information acquisition module is connected with an output terminal of the generator through an A/D conversion module ADC2 and acquires alternating voltage signals output by the generator, the information acquisition module is connected with the current transformer T4, the current transformer T5 and the current transformer T6 through the A/D conversion module ADC2 and acquires alternating current signals output by the generator, and the information acquisition module stores the acquired alternating voltage and current data in the memory;
the information acquisition module is connected with the output terminal of the rectification module through the A/D conversion module ADC2, acquires the direct-current voltage signal output by the rectification module, the information acquisition module is connected with the current divider P2 through the A/D conversion module ADC2, acquires the direct-current signal output by the rectification module, and the information acquisition module stores the acquired direct-current voltage and current data in the memory.
The information management module is connected with the information acquisition module through the serial communication port COM1, and reads the aviation power supply vehicle operation data stored by the information acquisition module. The information management module is provided with a touch screen display, and the information management module displays the read operation data of the aviation power supply vehicle on the touch screen display; when the operation of the aviation power supply vehicle fails or special conditions occur in the use of the aviation power supply vehicle, the touch screen display is operated, data record of a specific period of the information acquisition module can be read, data playback or curve playback is carried out, parameter values when the problem occurs are determined, the problem cause is checked in an auxiliary mode through the change of the operation data of the aviation power supply vehicle before and after the problem occurs, the problem location is carried out quickly, and unattended operation of the aviation power supply vehicle can be achieved;
the information acquisition module is connected with the control module through the serial communication port COM2, reads the running state of the aviation power supply vehicle, and transmits the running state to the information management module through the serial communication port COM1, when the aviation power supply vehicle runs and breaks down, the control module generates a fault code and transmits the fault code to the information acquisition module, the information acquisition module transmits the fault code to the information management module, the information management module immediately displays the fault name, the occurrence time and the fault type on the touch screen display, retrieves the running data stored by the information acquisition module, determines the specific numerical value when the fault occurs, simultaneously starts a vehicle maintenance expert system, further performs fault positioning, guides maintenance personnel to perform vehicle maintenance, and rapidly eliminates the fault;
the control module automatically records the operation hours of the informationized aviation power supply vehicle, and the operation hours of the aviation power supply vehicle are not recorded by an operator, so that the hidden trouble of manual recording errors is avoided; the information management module reads the operation hours recorded by the control module on line, compares the operation hours with a built-in engine periodic maintenance table, automatically sends out a maintenance signal when the operation hours of the aviation power supply vehicle reach the maintenance requirement, prompts a user to carry out vehicle maintenance, and provides convenience for vehicle maintenance management.
By adopting the structure, the invention has the advantages of high reliability, high automation degree, automatic fault positioning, automatic guiding of vehicle maintenance and the like according to the self memory function.
Drawings
Fig. 1 is a block diagram of the system architecture of the present invention.
Reference numerals: the system comprises an operation panel 1, a control module 2, an engine 3, a generator 4, a rectifying module 5, an information acquisition module 6 and an information management module 7.
Fig. 2 is an electrical schematic diagram of the operation panel 1.
Reference numerals: an operation switch S1, an operation switch S2, an operation switch S3, and an operation switch S4, respectively.
Fig. 3 is an electrical schematic of the control module 2.
Reference numerals: VFD display 21, memory MEM122, a/D conversion module ADC1 23, CAN interface 24, CPU 25, relay K1 26, relay K2 27, relay K3 28, relay K4 29.
Fig. 4 is an electrical schematic of the generator 4.
Reference numerals: generator stator coil 31, current transformer T1 32, current transformer T2 33, current transformer T3 34, current transformer T4 35, current transformer T5 36, current transformer T6 37.
Fig. 5 is an electrical schematic of the rectifying module 5.
Reference numerals: transformer 41, rectifier bridge group 42, filter capacitor group 43, shunt P1 44, and shunt P2 45.
Fig. 6 is an internal block diagram of the information acquisition module 6.
Reference numerals: the A/D conversion module ADC2 51, the serial communication port COM152, the serial communication port COM2 53, the memory MEM2 54 and the CAN interface 55.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
As shown in fig. 1, an informationized aviation power supply vehicle comprises an automobile chassis and a power supply control cabin, wherein an operation panel 1, a control module 2, an engine 3, a generator 4 and a rectifying module 5 are arranged in the power supply control cabin, and the informationized aviation power supply vehicle is characterized by further comprising an information acquisition module 6 and an information management module 7, wherein the information acquisition module 6 is used for acquiring and storing the operation parameters of the aviation power supply vehicle in real time, the information management module 7 is used for realizing the playback of the operation parameters of the aviation power supply vehicle, the periodic maintenance prompt of the vehicle, a vehicle maintenance expert system and the like, the operation panel is connected with the control module, the engine, the generator and the rectifying module are sequentially connected, the control module and the information acquisition module are respectively connected with the engine, the generator and the rectifying module, and the information management module is connected with the control module and the information acquisition module so as to realize the playback of the operation parameters of the aviation power supply vehicle through the information acquisition module, the periodic maintenance prompt of the vehicle and the functions of the vehicle expert system of the information management module.
As shown in fig. 2, the operation panel 1 of the present invention is provided with an operation switch S1, an operation switch S2, an operation switch S3, and an operation switch S14.
As shown in fig. 3, the control module 2 includes a VFD display 21, a memory MEM122, an a/D conversion module ADC1 23, a CAN interface 24, a CPU 25, a relay K1 26, a relay K2 27, a relay K3 28, and a relay K4 29.
As shown in fig. 4, the generator 4 includes a generator stator coil 31, a current transformer T1, a current transformer T2, a current transformer T3, 34, a current transformer T4, 35, a current transformer T5, 36, and a current transformer T6, 37.
As shown in fig. 5, the rectifying module 5 includes a transformer 41, a rectifying bridge group 42, a filter capacitor group 43, a shunt P1 44, and a shunt P2 45.
As shown in fig. 6, the information collecting module 6 includes an a/D conversion module ADC2 51, a serial communication port COM152, a serial communication port COM2 53, and a memory MEM2 54.
When the aviation power supply vehicle is in a static state, the operation switch S1 is pressed to send an operation instruction to the control module 2, the control module 2 relay K1 acts to send a starting instruction to the engine 3, the engine 3 is started to operate, and the aviation power supply vehicle enters an operation state; when the aviation power supply vehicle is in a running state, the operation switch S1 is pressed to send a stop instruction to the control module 2, the control module 2 relay K1 is operated to send a stop instruction to the engine 3, the engine 3 stops running, and the aviation power supply vehicle enters a stop state;
when the engine 3 operates at a rated rotation speed, the generator 4 generates a three-phase alternating current power supply with 115V/200V and 400Hz frequency; the three-phase alternating current power supply with the voltage of 115V/200V and the frequency of 400Hz generated by the generator 4 is used as the input power supply of the rectifying module 5; the transformer 41 steps down the input three-phase ac power, the rectifier bridge group 42 performs full-bridge rectification on the stepped-down ac power, and the filter capacitor group 43 filters the rectified power to obtain a dc power with a voltage of 28V;
pressing the operation switch S2 to send an alternating current I group power supply instruction to the control module 2, and enabling the control module 2 to conduct relay K2 27 suction to achieve alternating current I group output power supply; when the operation switch S2 is pressed down again and an alternating current I group power-off instruction is sent to the control module 2, the relay K2 27 of the control module 2 is reset, so that the alternating current I group output power-off is realized;
and the operation switch S3 13 is pressed down to send an alternating current II group power supply instruction to the control module 2, and the control module 2 is attracted by the relay K3 28 to realize the output power supply of the alternating current II group.
When the operation switch S3 13 is pressed down again and an alternating current II group power-off instruction is sent to the control module 2, the relay K3 28 of the control module 2 is reset, so that the alternating current II group output power-off is realized;
pressing the operation switch S4 to send a direct current power supply instruction to the control module 2, and enabling the control module 2 to conduct relay K4 29 attraction so as to achieve direct current output power supply; when the operating switch S4 is pressed down again and a direct current power-off instruction is sent to the control module 2, the relay K4 29 of the control module 2 is reset, so that direct current output power-off is realized;
the control module 2 is connected with the engine 3 through the CAN interface 24, reads running data such as the rotating speed, the engine oil pressure, the cooling liquid temperature and the like of the engine, transmits the running data to the CPU 25 for operation, and displays the running data on the VFD display 21; the CPU 25 judges the current state of the aviation power supply vehicle according to the read rotating speed data of the engine 3, and when the aviation power supply vehicle is in an operating state, the control module 2 automatically accumulates and records the operating hours of the aviation power supply vehicle; the control module 2 judges whether the engine 3 is normally operated according to the read engine oil pressure, cooling liquid temperature and other operation data, if the engine 3 is abnormally operated, the control module 2 displays engine fault information on the VFD display 21, the relay K1 11 resets to stop the operation of the engine 3, an aircraft and an aviation power supply vehicle are protected, and the engine fault information is recorded in the memory MEM1 22;
the control module 2 acquires voltage and current signals of the generator 4 and the rectifying module 5 through the A/D conversion module ADC1 and is used for monitoring the running state of the aviation power supply vehicle;
the control module 2 is connected with a generator stator coil 31 of the generator 4 through an A/D conversion module ADC1, collects alternating voltage signals output by the generator 4, the control module 2 is connected with the current transformer T1 32, the current transformer T2 33 and the current transformer T3 34 through the A/D conversion module ADC1, collects alternating current signals output by the generator 4, and the control module 2 displays the collected alternating voltage and current data on the VFD display 21; the control module 2 judges whether the power generation and the power supply of the generator 4 are normal according to the collected alternating voltage and current data, if the power generation and the power supply of the generator 4 are abnormal, the control module 2 displays alternating current fault information on the VFD display 21, the relays K2 27 and K3 28 reset to stop alternating current power supply output, an aircraft and an aviation power supply vehicle are protected, and the alternating current fault information is recorded in the memory MEM1 22;
the control module 2 is connected with an output terminal of the rectifying module 5 through an A/D conversion module ADC1, collects direct current voltage signals output by the rectifying module 5, the control module 2 is connected with the current divider P1 44 through the A/D conversion module ADC1, collects direct current signals output by the rectifying module 5, and the control module 2 transmits the collected direct current voltage and current data to the CPU 25 for calculation and display on the VFD display 21; the control module 2 judges whether rectification and output of the rectification module 5 are normal according to the collected direct-current voltage and current data, if the rectification and output of the rectification module 5 are abnormal, the control module 2 displays direct-current fault information on the VFD display 21, the relay K4 29 resets to stop direct-current power supply output, an aircraft and an aviation power supply vehicle are protected, and the direct-current fault information is recorded in the memory MEM 122;
the information acquisition module 6 reads operation data such as the rotating speed, the engine oil pressure, the cooling liquid temperature and the like of the engine 3 through the CAN interface 55, and the memory MEM2 54 of the information acquisition module 6 stores the read operation data of the engine 3;
the information acquisition module 6 acquires voltage and current signals of the generator 4 and the rectifying module 5 through the A/D conversion module ADC2 51, and is used for acquiring operation data of an aviation supply vehicle and storing the operation data in the memory MEM2 54;
the information acquisition module 6 is connected with an output terminal of the generator 4 through an A/D conversion module ADC2, acquires an alternating voltage signal output by the generator 4, the information acquisition module 6 is connected with the current transformer T4 35, the current transformer T5 36 and the current transformer T6 37 through the A/D conversion module ADC2, acquires an alternating current signal output by the generator 4, and the information acquisition module 6 stores the acquired alternating voltage and current data in the memory MEM2 54;
the information acquisition module 6 is connected with an output terminal of the rectification module 5 through an A/D conversion module ADC2, acquires a direct-current voltage signal output by the rectification module 5, the information acquisition module 6 is connected with the current divider P2 45 through the A/D conversion module ADC2, acquires a direct-current signal output by the rectification module 5, and the information acquisition module 6 stores the acquired direct-current voltage and current data in the memory MEM2 54;
the information management module 7 reads the aviation electric power car operation data stored by the information acquisition module 6 through a serial communication port COM152 of the information acquisition module 6;
the information management module 7 is provided with a touch screen display, and the read operation data of the aviation power supply vehicle are displayed on the touch screen display; when the operation of the aviation power supply vehicle fails or special conditions occur in the use of the aviation power supply vehicle, the touch screen display is operated, data record of a specific period of the information acquisition module 6 can be read, data playback or curve playback is carried out, parameter values when the problem occurs are determined, the problem cause is assisted to be checked by checking the change of the operation data of the aviation power supply vehicle before and after the problem occurs, the problem location is carried out quickly, and the aviation power supply vehicle can be unattended;
the information acquisition module 6 is connected with the control module 2 through the serial communication port COM2 53, reads the running state of the aviation power supply vehicle, and forwards the running state to the information management module 7 through the serial communication port COM 152; the information management module 7 is provided with a data chip, and a vehicle maintenance expert system and an engine periodic maintenance table are internally solidified; when the operation of the aviation power supply vehicle fails, the control module 2 generates a fault code and transmits the fault code to the information acquisition module 6, the information acquisition module 6 forwards the fault code to the information management module 7, the information management module 7 immediately displays the fault name, the occurrence time and the fault type on the touch screen display, retrieves the operation data stored by the information acquisition module 6, determines the specific numerical value when the fault occurs, and simultaneously starts a vehicle maintenance expert system to further perform fault positioning, guide maintenance personnel to perform vehicle maintenance and quickly remove the fault;
the control module 2 automatically records the operation hours of the informationized aviation power supply vehicle, and the operation hours of the aviation power supply vehicle are not recorded by an operator, so that the hidden trouble of manual recording errors is avoided; the information management module 7 reads the operation hours recorded by the control module 2 on line, compares the operation hours with a built-in engine periodic maintenance table, and automatically sends a maintenance signal to prompt a user to carry out vehicle maintenance when the operation hours of the aviation power supply vehicle reach the maintenance requirement, thereby providing convenience for vehicle maintenance management.
By adopting the structure, the invention has the advantages of high reliability, high automation degree, automatic fault positioning, automatic guiding of vehicle maintenance and the like according to the self memory function.
Claims (1)
1. The informationized aviation power supply vehicle comprises an automobile chassis and a power supply control cabin body, wherein an operation panel, a control module, an engine, a generator and a rectifying module are arranged in the power supply control cabin body, and the informationized aviation power supply vehicle is characterized by further comprising an information acquisition module and an information management module, wherein the operation panel is connected with the control module, the engine, the generator and the rectifying module are sequentially connected, the control module and the information acquisition module are respectively connected with the engine, the generator and the rectifying module, the information management module is connected with the control module and the information acquisition module, an operation switch S1, an operation switch S2, an operation switch S3 and an operation switch S4 are arranged on the operation panel, the control module comprises a VFD display, a memory, an A/D conversion module ADC1, a relay K2, a relay K3 and a relay K4, and a CAN interface is arranged on the engine; the generator comprises a current transformer T1, a current transformer T2, a current transformer T3, a current transformer T4, a current transformer T5 and a current transformer T6, the rectifying module comprises a current divider P1, a current divider P2, a transformer, a rectifying bridge group and a filter capacitor group, the information acquisition module comprises an A/D conversion module ADC2, a serial communication port COM1 and a serial communication port COM2, the information management module is provided with a touch screen display,
when the aviation power supply vehicle is in a static state, the operation switch S1 is pressed to send an operation instruction to the control module, the relay K1 acts to send a starting instruction to the engine, the engine is started to operate, and the aviation power supply vehicle enters an operation state; when the aviation power supply vehicle is in a running state, the operation switch S1 is pressed to send a stop instruction to the control module, the relay K1 acts to send a stop instruction to the engine, the engine stops running, and the aviation power supply vehicle enters a stop state;
when the engine operates at a rated rotation speed, the generator generates a three-phase alternating current power supply with 115V/200V and 400Hz frequency; the three-phase alternating current power supply with the voltage of 115V/200V and the frequency of 400Hz generated by the generator is used as an input power supply of the rectifying module; the transformer is used for reducing the voltage of the input three-phase alternating current power supply, the rectifier bridge group is used for carrying out full-bridge rectification on the reduced alternating current power supply, and the filter capacitor group is used for filtering the rectified power supply to obtain a direct current power supply with the voltage of 28V;
pressing down the operation switch S2, sending an alternating current I group power supply instruction to the control module, and enabling the relay K2 to be attracted to realize output power supply of the alternating current I group; when the operation switch S2 is pressed down again and an alternating current I group power-off instruction is sent to the control module, the relay K2 is reset, and the alternating current I group output power-off is realized;
pressing the operation switch S3 to send an alternating current II group power supply instruction to the control module, and enabling the relay K3 to be attracted to realize output power supply of the alternating current II group;
when the operating switch S3 is pressed down again and an alternating current II group power-off instruction is sent to the control module, the relay K3 is reset, and the alternating current II group output power-off is realized;
pressing the operation switch S4 to send a direct current power supply instruction to the control module, and enabling the relay K4 to be attracted to realize direct current output power supply; when the operating switch S4 is pressed down again and a direct current power-off instruction is sent to the control module, the relay K4 is reset, and direct current output power-off is realized;
the control module is connected with the engine through the CAN interface, reads the running data of the rotating speed, the engine oil pressure and the cooling liquid temperature of the engine, and displays the running data on the VFD display; the control module judges the current state of the aviation power supply vehicle according to the read rotating speed data of the engine, and when the aviation power supply vehicle is in an operating state, the control module automatically accumulates and records the operating hours of the aviation power supply vehicle; the control module judges whether the engine operates normally according to the read engine oil pressure and cooling liquid temperature operation data, if the engine operates abnormally, the control module displays engine fault information on the VFD display, the relay K1 resets to stop the engine operation, the aircraft and the aviation power supply vehicle are protected, and the engine fault information is recorded in the memory;
the control module acquires voltage and current signals of the generator and the rectifying module through an analog-to-digital (ADC) conversion module (ADC 1) and is used for monitoring the running state of the aviation power supply vehicle;
the control module is connected with an output terminal of the generator through an A/D conversion module ADC1, acquires an alternating voltage signal output by the generator, is connected with the current transformer T1, the current transformer T2 and the current transformer T3 through the A/D conversion module ADC1, acquires an alternating current signal output by the generator, and displays the acquired alternating voltage and current data on the VFD display; the control module judges whether the power generation and the power supply of the generator are normal according to the collected alternating voltage and current data, if the power generation and the power supply of the generator are abnormal, the control module displays alternating current fault information on the VFD display, relays K2 and K3 reset to stop alternating current power supply output, an aircraft and an aviation power supply vehicle are protected, and the alternating current fault information is recorded in the memory;
the control module is connected with an output terminal of the rectification module through an A/D conversion module ADC1, acquires a direct-current voltage signal output by the rectification module, is connected with the shunt P1 through the A/D conversion module ADC1, acquires a direct-current signal output by the rectification module, and displays the acquired direct-current voltage and current data on the VFD display; the control module judges whether rectification and output of the rectification module are normal according to the collected direct-current voltage and current data, if the rectification and output of the rectification module are abnormal, the control module displays direct-current fault information on the VFD display, the relay K4 resets to stop direct-current power supply output, an aircraft and an aviation power supply vehicle are protected, and the direct-current fault information is recorded in the memory;
the information acquisition module reads the running data of the rotating speed, the engine oil pressure and the cooling liquid temperature of the engine through a CAN interface, and the information acquisition module stores the read running data of the engine through a memory;
the information acquisition module acquires voltage and current signals of the generator and the rectification module through the A/D conversion module ADC2, and is used for acquiring and storing operation data of the aviation power supply vehicle;
the information acquisition module is connected with an output terminal of the generator through an A/D conversion module ADC2 and acquires alternating voltage signals output by the generator, the information acquisition module is connected with the current transformer T4, the current transformer T5 and the current transformer T6 through the A/D conversion module ADC2 and acquires alternating current signals output by the generator, and the information acquisition module stores the acquired alternating voltage and current data in the memory;
the information acquisition module is connected with an output terminal of the rectification module through an A/D conversion module ADC2, acquires a direct-current voltage signal output by the rectification module, is connected with the shunt P2 through the A/D conversion module ADC2, acquires a direct-current signal output by the rectification module, and stores the acquired direct-current voltage and current data in the memory;
the information management module is connected with the information acquisition module through the serial communication port COM1 and reads the aviation power supply vehicle operation data stored by the information acquisition module;
the information management module is provided with a touch screen display, and the information management module displays the read operation data of the aviation power supply vehicle on the touch screen display; when the operation of the aviation power supply vehicle fails or special conditions occur in the use of the aviation power supply vehicle, the touch screen display is operated, data records of the information acquisition module in a specific period are read, data playback or curve playback is carried out, parameter values when problems occur are determined, and the problem positioning is carried out quickly by checking the change of the operation data of the aviation power supply vehicle before and after the problems occur, so that the problem cause is assisted to be checked;
the information acquisition module is connected with the control module through the serial communication port COM2, reads the running state of the aviation power supply vehicle, and transmits the running state to the information management module through the serial communication port COM1, when the aviation power supply vehicle runs and breaks down, the control module generates a fault code and transmits the fault code to the information acquisition module, the information acquisition module transmits the fault code to the information management module, the information management module immediately displays the fault name, the occurrence time and the fault type on the touch screen display, retrieves the running data stored by the information acquisition module, determines the specific numerical value when the fault occurs, simultaneously starts a vehicle maintenance expert system, further performs fault positioning, guides maintenance personnel to perform vehicle maintenance, and rapidly eliminates the fault;
the information management module reads the operation hours recorded by the control module on line, compares the operation hours recorded by the control module with a periodic maintenance table of an engine built in the control module, and automatically sends a maintenance signal to prompt a user to carry out vehicle maintenance when the operation hours of the aviation power supply vehicle reach the maintenance requirement.
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| CN108121329B (en) * | 2018-02-14 | 2024-04-12 | 中国人民解放军第四三二八工厂 | Power supply vehicle data measurement and control system and method, power supply vehicle, computer system and medium |
| PL3570568T3 (en) * | 2018-03-22 | 2022-04-04 | Shenzhen Launch Software Co., Ltd. | Vehicle repairing method and apparatus |
| CN112529212A (en) * | 2019-08-27 | 2021-03-19 | 郑州宇通重工有限公司 | Sanitation vehicle, and automatic reminding method and system for sanitation vehicle maintenance |
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